national aeronautics and space ......at 45 m~nutes before ei the cmc update program p27 can be...

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i- ' ..... .... •• .' .' , . .. (JJ tof - 1 OJ :J.. / () (-7(-(£/1 -.;L'/i!,J) ) c.3 NATIONAL AERONAUTICS AND SPACE ADMINISTRATION MSC INTERNAL NOTE MSC-CF-P-69-7 APOLLO ENTRY SUMMARY DOCUMENT MISSION "F" (AS-505!106!LM-4) FINAL COpy LIBRARY COpy APR 9 1969 MANNED SPACECRAFT CENTER HOUSTON, TEXAS Reproduced by _ NATIONAL'TECHNICAL INFORMATION SERViCE Spnngfield, Va n151 HOUSTON TEXAS March 17, , .' 'c -::. , . MANNED SPACECRAFT CENTER I.. N70 - '1 I (ACCESSION NUMBER) "ITrur;;;,U") --- J I , 17 I (PA ES) (CODE) ii: - n "71 :::; . ? , (NASA CR OR TMX OR AD U BER) , L -- ----, - -'--

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Page 1: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

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NATIONAL AERONAUTICS AND SPACE ADMINISTRATION

MSC INTERNAL NOTE MSC-CF-P-69-7

APOLLO ENTRY SUMMARY DOCUMENT

MISSION F

(AS-505106LM-4)

FINAL COpy

LIBRARY COpyAPR 9 1969

MANNED SPACECRAFT CENTERHOUSTON TEXAS

Reproduced by _

NATIONALTECHNICALINFORMATION SERViCE

Spnngfield Va n151

HOUSTON TEXAS

March 17

~l~ c - ~

MANNED SPACECRAFT CENTERI N70 - 3rr8-~~ 1I ~ (ACCESSION NUMBER) --7-~ ITrurU)--- J

I ~ 17I (PA ES) (CODE)

ii - n 71 ~~~-=1---+I---I ~ (NASA CR OR TMX OR AD U BER) --~(CsTLEGO=RY-- ~

L -- ---- - ---

PREPARED BY

APPROVED BY

APOLLO ENTRY SUMMARY DOCUMENT

MISSION F (AS-505106LM-4)

-eamp R ~James O R1ppe~ ~----AST Launch and Entry Procedures Sect1on

D1ck1e K WarrenChlef Launch and Entry Procedures Sectlon

P-P C 7ltPaul C KramerChlef F1lght Procedures Branch

James VI Bl10deauAsslstant Chlef F1lght Crew Support Dlvlslon

WarrenChlef

March 17 1969

TABLE OF CONTENTS

41 Typlcal Retroflre and Entry Sequence of Events

56 Earth landing from superclrcular and earth orbitalentrles bull bull bull

51 Entry preparatlons for superclrcular and earth orbltalentr~es bull

20 Llst of Acronyms and Abbrevlatlons

1

2

5

8

10

12

13

15

16

17

17

23

29

35

40

45

47

50

52

55

57

59

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76

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Earth orbltal entrles bull bull55

54 Normal deorblts for earth orbltal entrles

53 GampN hybrid deorblts for earth orbltal entrles

52 Superclrcular entry

31 Reentry Guidance Events

33 Monltoring wlthout EMS bullbullbullbullbull bullbull

42 Retroflre and Entry Alternatlves

32 Summary of Monltorlng Checks for Entry

Introductlon bullbull

57 Post landing middot

60 TLI Aborts bull

61 TLI preparatlon procedures bull bull

62 10 mlnute TLI abort procedures

63 90 minute TLI abort procedures

70 Entry Pads bull bull bull bull

80 Entry Charts and TLI Charts bull

90 References middot

50 Detalled Entry Procedures bullbullbullbullbullbullbull

40 Earth Orbital Deorblt and Entry Technlques

30 Lunar Return Entry Technlques

10

-1-

10 INTRODUCTION

The purpose of the Entry Summary Document is to provide a singlesource of entry crew procedure ~nformat~on for use ~n fl~ght planshyn~ng crew tra~n~ng and prepar~ng onboard data The techn~ques

conta~ned ~n this document were generally der~ved from other docushymentat~on and are comblned here to serve as a slngle compacttra~n~ng package

In accordance wlth the Fllght Crew Operatlons Dlrectorate CREWPROCEDURES CONTROL PLAN dated March 1968 the prel~minary ESDedltions are dlstrlbuted for review and comment and simulatorval~datlon unt~l 5 months prlor to launch Thereafter flnal ESDprocedures are d~strlbuted and serve as a control ~ocument withchanges sUbJect to approval by the Crew Procedures Control Board

Comments to thls document should be d~rected to the Fl~ght Proshycedures Branch Fllght Crew Support Dlvislon extens~on 3436

-2-

20 LIST OF ACRONYMS AND ABBREVIATIONS

ComputerPilot

ModuleModuleModule

AccumlatorAmphherAntennaAcqu~s~t~on of S~gnal

Backup Bank AngleBeaconBlunt End ForwardCMC Commanded Bank AngleBody Mounted Att~tude GyroBank Reverse BankCab~n

CommanderCoupl~ng Data Un~t

C~rcuit

CommandCommandCommandCutoffCrew Opt~cal AI~gnment S~ght

Commun~cat~ons

Cryogen~c

Command Serv~ce ModuleCounterCaut~on Warn~ng SystemD~g~tal Auto P~lot

D~g~tal Event P~lot

Drag Acceleration at Sk~pout

Constant Drag Control Accelerat~on LevelD~splay and KeyboardDSKY EnterEnv~ronment Control SubsystemEntry InterfaceEntry Monltor SystemElectrlcal Power SubsystemEssent~al

Flight Combust~on Stab~lity MonitorFI~ght D~rector Att~tude Ind~cator

FunctionAccelerat~on 1n Earth Grav~tatlonal Un~ts

Gu~dance and ControlGround Elapsed TlffieGround Elapsed T1me of Ign~t~on

Gyro Display CouplerGlycolG~mbal

Guidance and Nav~gat1on

ACCUMAMPANTAOSBBABCNBEFBETABMAGBRBCBNCDRCDUCKTCMCMCCMPCOCOASCm1MCRYOCSMCTRCWSDAPDETDLDODSKYEECSEIEMSEPSESSFCSMFDAIFUNCGGampCGETGETIGDCGLYGMBLGampN GIN

-3-

Llst of Acronyms and Abbrevlatlons

GNDGPIG-VHAHEHPIMUKA

LIDLEBIMPLOSLVMANMCCMCC-HMESCMSFNMGAMKMNVRMaNMTRMTVCNOPTORIEN02PPGAPGNCSPIPAPLPLSSpassPRIMPRPLNTPSIAPTTPUGSPWRRRI R2 R3RADRCDRRCSROTREFSMMAT

GroundG~bal Posltlon IndlcatorAcceleratlon-VelocltyHelght of ApogeeHellumHeight of PerlgeeInertlal Measurement UnltDrag Acceleratlon necessary to lnltlate

constant drag controlLlft to Drag RatioLower Equlpment BayLunar Module PllotLoss of SlgnalLocal Vertlcal Llft Vector Launch VehlcleManualMldcourse CorrectlonMlssion Control Center - HoustonMaster Event Sequence ControllerManned Space Fllght NetworkMiddle Glmbal AngleMarkManeuverMonltorMotorManual Thrust Vector ControlDSKY NounOptlon OptlCSOrlentatlonOxygenPltch or CMC ProgramPressure Garment AssemblyPrlmary GUldance Navlgatlon and Control SystemPulse Integratlng Pendulous AccelerometerPlanetPortable Llfe Support SystemPosslblePrlmaryPropellantPounds Per Square Inch AbsolutePush to TalkPropellant Utllizatlon and Gaglng SystemPowerRoll or CMC RoutlneReglster 1 2 3RadlatorRecorderReactlon Control SystemAltltude RateReference to Stable Member Matrlx

-4-

L~st of Acronyms and Abbrev~at1ons

RELRET

RHCRNGROURRT

RSIRTGOSASCSSECSECSSELSEPSEQSFT

SM SIMSPASPSSTBYSXPSXTSTSTATBTBDTERMTFTFFTHBWLSTHCTIGTLITIl TLMTRNFR

TVCVVGVIOVLVMY

Rel1efReentry Elapsed TIme (Lunar Return Case) or Retro

Elapsed Time (Earth Orb~tal Case) For lunar returnsRET 1S zero at RRT For earth orb1tal entries RET iszero at the deorb1t burn tIme

Rotat1onal Hand ControllerRangeRout1neReentry Reference T~me (Based on MCC-H predicted time

of EI to nearest second)Roll Stab11~ty IndicatorRange to GoShaft AngleStab1lizat1on and Control SystemSecondarySequent1al Events Control SubsystemSelectSeparationSequentialShaft Angle for SXTS when spacecraft 1S at

ignit10n attitudeServ1ce ModuleCOAS Star P~tch AngleServ1ce Propuls~on SystemStandbyStar X Pos~t~on (COAS)SextantSextant StarTrunnion AngleTalkback D~splay T1me BaseTo Be DeterminedTerm~nate

Ttme FromTtme of FreefallThumbwheelsTranslational Hand ControllerTime of Ignit~on

Translunar Insert10nTelemetryTransferThrust Vector ControlVeloc~ty or DSKY VerbVeloc~ty To Be GatnedInertial Veloc~ty

Sktpout Veloc1tyVeloc~ty MeasuredYaw

-5-

3deg LUNAR REIUBN ENTRY TECHNIQUES

The t~mel~ne for lunar return entries is based on the recommendationsfound ~n reference 1 the s~mulator val~dated procedures ~n reference2 and the mission val~dated procedures listed in the onboard checkshylist for the C Pr~me m~ssion The event times are l~sted ~n reference3

The preparation for lunar return entr~es beg~ns at a conven~ent t~me

about 30 hours before entry ~nterface At th~s t=e MSFN sends up alldata suff~c~ent for reentry also an EMS entry selftest ~s made toassure max~mum confidence ~n the EMS operat~on during entry Thereshyafter var~ous system powerups and checks are ~n~t~ated as l~sted insect~on 51 and deta~led ~n reference 4 Nom~nally the PGNCS ~s upfor the ent~re m~ss~on However ~f ~t ~s not ~t ~s powered up atEI-7 hours ~n preparat~on for the last MCC and entry The last MCCdec~s~on ~s made at about EI-6 hours for the maneuver to be performedat EI-3 hours ~f needed Deta~ls of th~s maneuver are outl~ned ~n

reference 1 After the MCC time P52 ~s again selected and the IMU ~s

real~gned to the REFSMMAT If the IMU dr~ft ~s w~th~n tolerance thesubsequent IMUSCS dr~ft check will determ~ne if the SCS has dr~fted

excess~vely If so the other BMAGs are selected and the IMUSCScheck repeated Th~s check ~s followed by a repeat of the EMS ~V

counter check and accelerometer b~as check at EI-l hour 15 m~nutes

to determ~ne ~f the scale factor and b~as are adequate for entrymon~tor~ng F~nal stowage CM RCS preheat and pyro Cllcu~t and seshyquent~al tests are worked ~nto this t~meframe so that at EI-50 m~nutes

the MSFN w~ll be requested for a go to pyro arm by the crew ~n preparashyt~on for separat~on At 45 m~nutes before EI the CMC update programP27 can be selected to permit update of the landing po~nt locat~on andthe state vector The entry PAD data shown ~n sect~on 70 ~s thenvo~ced to the crew and recorded From th~s data the DET ~s set andstarted the EMS ~nit~al~zed and the RSI al~gned Prior to EI-20ffilnutes the crew w~ll have strapped-~n completed the~r presepara-t~on checkl~st and maneuvered to the entry att~tude At this pointEI-19 m~nutes the CMC entry program Fbl ~s selected by the CMP Ifthere was no entry PAD data because of commun~cat~on loss the veloshyc~ty and range to go from P61 ~s recorded and used ~n the EMS AtEI-15 m~nutes the spacecraft ~s p~tched down and the hor~zon ~s checkedagainst the 317 degree w~ndow scr~be l~ne and the FDAI att~tude Ifthere ~s s~gn~f~cant d~sagreement the PGNCS ~s suspected and the spaceshycraft ~s held on the w~ndow reference In P62 the spacecraft ~s yawed45 0 from th~s att~tude and separated from the SM After separat~on

the CM ~s yawed back ~n plane and the hor~zon check repeated At approxshy~mate1y EI-10 m~nutes the p~tch att~tude is w~th~n 450 of the CMCcommanded att~tude and P63 ~s entered automat~ca11y S~nce the CMCDAP tr~es to hold local p~tch attitude and the CMC ~s not ~n controlthe crew observes the p~tch error needle unpeg and approach zeroabout two m~nutes before 05g t~me Th~s serves as a gono go CMC

-6-

check for entry control If the FDAI pltch error does not decreaseto wlthln + 50 at 005g the PGNCS lS fa lied and the crew flies aconstant g-entry mode wlth EMS ranglng after the VelOClty decreaseto 25500 feet per second If the PGNCS lS acceptable the spaceshycraft control lS placed In CMC and the CMC mode lS placed ln autoshymatlc At 05g the EMS automatlcally starts lf the EMS mode sWltchwas posltloned to automatlc earller ThlS wlll be backed up manually3 seconds after the ground computed 05g tlme recorded on the entryPAD by placlng the EMS mode sWltch In manual lf lt has not startedautomatlcally At PGNCS 005g lndlcatlon the CMC program changesto P64 and from thls pOlnt the entry lS under entry DAP control

The lunar return entry nomlnally lS performed by the PGNCS to lnsurecontrol wlthln the overshoot and g llmlt llnes as well as optlmlzethe landlng point accuracy Although the hlgh speed entry lnvolvesa rapld sequency of events there are several monitorlng tasks forthe crew to determlne lf the automat~c contrails performlng correctly

An entry corr~dor ver~flcation check 1S made by observlng the lnltlalslope of the EMS V-g trace between 1 and 2 gs If the EMS lndlcatesthe need to reverse the LV orlentatlon and the lndependent g meterconflrms the EMS g lndlcatlon the SC lS immedlately orlented as aresult of the EMS ~nd~cat~on

The EMS g lnd~catlon ~s contlnuously checked durlng entry uSlng thelndependent g meter and the PGNCS g ~ndlcatlon as a thlrd voteDeC1Slons durlng the first entry (P64) are critlcal ln terms of bothexceSSlve g llnes and the PGNCS lS not commandlng (and SC respondlng)to correct the sltuatlon the PGNCS lS felled

The PGNCS gono go check for short range targets (1200-1400 n ml) forWhlCh P65 lS not used 1S d1fferent Slnce there are no CMC computedSk1p drag (DL) and skip velocity (VL) values The check uses the EMSscroll to determ1ne 1f the PGNCS lS commandlng the proper roll att1shytude to converge the EMS g level to a predetermlned PAD value (Do) ascomputed by MCC-H For the nom1nal target range of 1300 naut~cal

mlles the crew w1ll monltor the program change from P64 to P67 atapprox~matelyEI + 3 mlnutes For ranges greater than 1400 nauticalmlles the program w1ll transfer to the Upcontrol Program P65 whenVL ~s between 18000 and 25766 feet per second and constant drag hasbrought the CMC pred1cted range to wlthln 25 naut1cal m1les of thetarget range The P65 PGNCS gono go check cons1sts of determln1ng1pound both the DSKY d1splay of sk~pout drag (DL) and Sk1pout veloclty(VL) are w1thln the PAD llmlts In addltlon the EMS scroll lS mon1shytored to determ~ne lf the trace lS approach1ng the DL and VL values

Throughout entry the crew monltors the spacecraft response to the CMCroll commands by observlng the FDAI lndlcatlons If the commands are

-7-

apparently good and In agreement wlth the EMS but the spacecraftresponse is questlonable the crew manually takes over and fIlesthe CMC commands

If the Upcontrol Program P65 was entered the program wlll nomshylnally sWltch to the Flnal Entry Program P67 for target rangesbelow approxlmately 1800 nautlcal miles or to the Ballistlc Proshygram P66 for ranges greater than approxlmately 1800 nautlcalffilles The program transfer crlterla are more preclsely deflnedIn reference 1

If P66 lS entered the spacecraft lS automatlcally rolled to theIlftup heads-down attltude to permlt the horlzon to be vlewedfrom the wlndow durlng the second entry The entry attltude checklS made by comparlng the horlzon wlth a speclfled wlndow mark Ifthe check falls the crew manually malntalns the entry trlffi attltudeuSlng the horizon VleW for reference The EMS lS used for ranglngSlnce the veloclty has now decreased to below 25500 feet per second

The EMS scroll lS contlnuously used to monltor for exceSSlve g conshydltlons durlng the second entry If the EMS V-g trace vlolates theg Ilnes and the PGNCS lS not commandlng (and spacecraft respondlng)to correct the situatlon the PGNCS lS falled and the EMS lS usedfor ranglng after ltS g lndlcatlon has been conflrmed by the lndeshypendent g meter

The entry phase lS essentlally over when the relatlve veloclty ofthe spacecraft decreases to less than 1000 feet per second ThlSlS lndlcated In P67 when RTGO latltude and longltude are dlsplayedSlnce very Ilttle ranglng capablllty exists after thls pOlnt thespacecraft lS orlented elther full Ilft up or down dependlng on RTGOnegatlve or posltlve and the crew prepares for the earth landlngphase

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-13-

40 EARTH ORBITAL DEORBIT AND ENTRY TECHNIQUES

As outl~ned ~n reference 5 a nom~nal PGNCS entry from earth orb~t ~s

based on a preparat~on t~me of 2 hours and 40 m~nutes ~nclud~ng 2n~ght passes Th~s t~me ~ncludes approx~mately 20 minutes before thef~rst n~ght pass after the CMC update and PAD data have been rece2vedTh~s t~e also 2ncludes approx2mately 20 m2nutes after the secondn~ght pass to allow suffic~ent t2me to prepare for retrof2re after theIMU f2ne a12gnment It has been determ2ned coarse a12gnment accuracy~s adequate for retrof~re and entry and undoubtedly other funct20nscould be om2tted depend2ng on the c2rcumstances for the dec2s20n toreenter Descr2bed here2n are the nom2nal earth oro2tal entry proshycedures w2th pert2nent comments on system va12dat20n for real timeacceptance dec~s20ns

After the entry dec~s~on is made the crew transfers the PGNCS fromthe standby to the operate mode and rece~ves a CMe update w~th P27Next the maneuver PAD update ~s v02ced up and the 2n~t~al entry mode~s determ~ned During the ~n~tial n~ght pass the IMU or2entat~on ~s

estab12shed uS2ng P51 star s~ght2ngs to obta2n a REFSMMAT The preshyferred or~entat~on opt20n ~n P52 2S then selected to coarse a12gn theIMU uS2ng the des2red entry REFSMMAT determ2ned by MGG-H The GOO ~s

now al~gned to the IMU 2n preparat~on for an IMUSes dr~ft check Ifthe GOO ~nd~cates the ses dr2ft rate exceeds 10 degrees per hour ~n

any ax~s the check ~s repeated on the other BMAGs to estaol~sh if theGOO or Just the single set 2S unusuable Var20us sytem checks as 12sted2n sect20n 51 are performed as necessary cons2stent w2th the t2me12ned2ctates of the maJor act2v2t2es Included 2n these checks are the EMSself-tests and the dV counter test The latter requ2res the spacecraftbe placed ~n dr2ft2ng fl2ght w~th the funct20n sW2tch 2n the dV pos2t~on

If the counter reg2sters a change of more than 25 feet per second w2th2n100 seconds the scroll and counter are unre12able for mon2tor2ng thedeorb2t burn and entry rang2ng If the EMS self-test fails and t2medoes not allow further analysis a 5555 ERE entry 1S planned as thePGNGS backup entry mode After complet2on of these checks the entryPAD lS prov1ded by MeG-H The crew then selects the external dVprogram P30 and the appropr2ate deorb1t tbrust1ng program p40 or P41Dur2ng th2s per2od wh2ch 2ncludes the f1nal n2ght pass P52 may beselected to ver2fy the IMU a12gnment Since the retro att2tude hasbeen computed so that a w2ndow mark c01nc2des w2th the hor2zon atGETI th2s serves as the conclus2ve check on the PGNCS At 5 m2nutesbefore retrofire the att2tude check 1S made by ver1fY2ng that the 12degree scr~be 12ne ~s w2th2n 3 degrees of the hor2zon If not thePGNeS has fa2led and the ses 2S used for att2tude reference and the

V counter for burn durat~on control S2nce the ses att~tude wasa12gned to the IMU a real~gnment ~s necessary This ~s accompl~shed

by manually maneuver2ng the spacecraft to ma~nta1n the 24 degree wlodowmark on the hor2zon and releas1ng the GOO a12gn button at TIG - 2 m2nutes

-14-

Upon complet~on of the burn the tN res~duals are burned to W~th~n

02 feet per second If the PGNCS ~V counter or est~mated burnduration are ~n d~sagreement ~t must be estab1~shed whether suff~shy

c~ent veloc~ty has been suppl~ed to put the land~ng po~nt in thefootpr~nt The PGNCS data w~ll be used ~f ~t ~s conf~rmed by oneother source if not the ~V counter w~11 be used ~f ~t ~s conf~rmed

by the burn durat~on t~me If add~tional ~V ~s necessary the data~s ava~lable to the crew on an onboard chart found ~n Sect~on 80

Post burn entry preparat~on requ~res EMS ~n~t~al~zation RSI al~gnshy

ment and pre-separat~on funct~ons The crew then selects the ~n~t~al

entry program P61 and records the d~sp1ays as a check aga~nst PADdata Upon complet~on of these checks P62 ~s entered The crewmanually or~ents the spacecraft to the separat~on attitude and yaws450 to ~nsure aga~nst possible CM 8M recontact After separat~on

the spacecraft ~s maneuvered to the reentry tr~m att~tude wh~ch

places the hor~zon on the 3170 w~ndow mark at EI Shortly thereshyafter ~n P62 the entry DAP is act~vated and P63 in~t~ated Dur~ng

th~s t~e MCC-H has computed a postburn update and ~t ~s vo~ced tothe crew ~f d~fferent from preburn values The EMS scroll and rangecounter w~ll be adJusted accord~ngly ~f t~me perm~ts A f~nal PGNCScheck pr~or to 05g may be mon~tored at th~s t~e w~th the CMC modein free and the manual att~tude p~tch ~n acceleration command wh~le

the hor~zon reference ~s held the p~tch error needle w~ll decreaseto zero as EI ~s reached At RET 005g the EMS mode sw~tch ~s

turned to manual the entry 005-g sw~tch and EMS roll sw~tch areturned on and the spacecraft control sw~tched to CMC to beg~n DAPcontrol At the PGNCS 005-g ~ndicatwn the program change fromP63 to P64 ~s mon~tored and the t~e vo~ce recorded At th~s t~me

the EMS range counter check ~s made dur~ng the 10 second per~od

follow~ng EMS 005g Dur~ng th~s per~od the counter should countdown 40 + 10 naut~cal m~les At PGNCS 02-g ~nd~cation the changefrom P64-to P67 ~s monitored and the ~splay may be held by key~ngVERB ~n order to record the init~al downrange error d~splay andcompare ~t to the PAD value The PGNCS has fa~led ~f the two do notagree w~th~n + 100 naut~cal m~les In the event P67 has not appearedwhen both the-g-meter and the scroll ~nd~cate greater than 05g thePGNCS has sim~lar~ly fa~led In e~ther fa~lure the SCS is used foratt~tude reference w~th an EMS entry If the checks agree the crewrema~ns w~th automat~c DAP for the rema~nder of the entry

The entry phase ~s essentially over when the relat~ve velocity ofthe spacecraft decreases to less than 1000 feet per second Th~s

~s ~nd~cated ~n P67 when RTGO lat~tude and long~tude are d~splayed

S~nce very l~ttle rang~ng capab~l~ty exists after th~s pOint thespacecraft is or~ented either full l~ft up or down depending onRTGO negat~ve or pos~t~ve and the crew prepares for the earth land~ng

phase

-15-

41 TYP~cal Retrof~re and Entry Sequence of Events

Dec~s~on to reenter

P27 (CMC update)

Retrof~re PAD update

Entry mode dec~s~on

P51 (IMU or~entat~on determlnatlon) durlng f~rst dark per~od

P52 (IMU coarse allgnment)

EMS checks

Entry PAD update

P30 (external AV)

p40 (SPS thrust)

P52 (IMU f~ne al~gnment) durlng second dark per~od

p40 (SPS thrust)

Ign~t~on att~tude check

Retroflre

P61

P62

CMSM separat~on

P63

Postburn PAD update

Entry attltude check

p64 (beg~n DAP control at O05g)

P67 (PGNCS gono go check at O2g)

42

Retrof~re

and

En

try

Alt

ern

atlv

es

Sys

tem

fa~lure

PGNC

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-17-

5 0 DETAILED ENTRY PROCEDURES

In order to comblne slmilar procedures that are common to lunar returnentrles and earth orblt entrles the followlng procedures are dlvldedlnto categorles that allow a mlnlmum of dupllClty ThlS provldes asmaller tralnlng package and more closely resembles the onboard crewcheckllst when comparlson lS necessary

51 Entry Preparatlons for Superclucular and Earth Orbltal Entrles

1~e entry preparatlons are comblned In these procedures andsteps pecullar to elther superclrcular or earth orbltal entrlesare labeled accordlngly The tlme llstlngs In thlS sectlon areappllcable to only superclrcular entries Slnce the earth orbltalentry tlmellne lS a functlon of several varlables as descrlbedIn sectlon 40 and reference 5

-18-51 (Contlnued)

VEHICLE PREPARATION

l-

2

3

4

5

6 -0600h

7 -0535h

8

9

10 -0430h

INITIAL STOWAGE COMPLETED

CMC amp ISS START UP

SCS POWER UP

p51 - IMU ORIENTATION

LOAD DAPV48E 11102 01111 PRO ERO PRO

LAST MCC DECISION

NO COMM - P52 amp NAV SIGHTINGSNOMINAL - P2337 ONBOARD COMPARISON

DON MAE WESTS amp FOOT RESTRAINTS

VHF AM A - SIMPLEX

P 27 (SV REFSMMAT) MNVRamp ENTRY pAD UPDATES

11 -0415h P52 - IMU REALIGN(___) (OPTION 1)

12 P37 (NO COMM ONLY)

13

14

ECS CKS02 SUPPLY REFILLECS Monitor CkEVAP H20 CONT (2) vlvs - AUTOSUIT HEAT EXCH SEC GLY - FLOW

EPS CKS 1 3 4 (5 If reqd)

15 SPS CK (If req d)

16

17

18

RCS CKSSM RCS MOUlt CkCM RCS MOUlt Ck

CampW SYS CK

CMC SELF CK

19

20 -0345h

-03l5h-0300h

21

22

22A

-19-

DSKY COND LT TEST

MIDCOURSE MANEUVERP30 - EXT rVP404l - SPSRCS THRUSTINGMIDCOURSE (17) BURN

NO COMM NAV SIGHTINGS

ffiVR TO ENTRY ATT (Superc1rc only)V62E

V49E

22B F 06 22 DESIRED FINAL GMBL ANGLESLOAD ENTRY ATT PAD ANGLESPRO

22C F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) SC CONT - CMC

BMAG MODE (3) - RATE 2CMC MODE - AUTO

PRO(~N) SC CONT - SCS

MNVR to 22E

22D 06 18 AUTO MNVR TO FDAI RPY ANGLES

22E F 50 18 REQUEST TRIM(TRIM) Go to 22C(BYPASS) ENTR

23 -200hr BORESIGHT amp SXT STAR CHECKOPT MODE - CMCOPT ZERO - OFF

V41 N91E

F 21 92 SHAFT TRUNLoad SXTS angles

41 OPTICS DRIVE

CHECK SXT STAROPT ZERO - ZERO

CHECK BORESIGHT STAR (If ava11)

24 -0135h

25(___)

26

27 -0115h

-20-

P52 - lMU REALIGNRecord gyro torqu~ng anglesRp~----

YIf-7gt-Lno--re-c-ycle PS2If conflrmed use SCS for EMS entry

GDC ALIGNIf drlft gtLOohr change ratesource

FINAL STOWAGEOPTICS (except for hybrid)ORDEALGLY TO RAD SEC - BYPASS (verlfy)CooL pnl lnstalledY-Y struts (2) extendedStow Data Box R-12

EMS CHECKEMS FUNC - OFFcb EMS (2) - closeEMS MODE - STBYEMS FUNC - EMS TEST 1 (walt 5 sec)EMS MODE - NORMAL (walt 10 sec)

Check ind lts - offRANGE lnd - 00Slew halr1ine over notch

In self-test patternEMS FUNC - EMS TEST 2 (walt 10 sec)

05G It - on (all others out)EMS FUNC - EMS TEST 3

05G It - onRSI Lower It - on (10 sec Qater)Set RANGE counter to 58 nm+OO

EMS FUNC - EMS TEST 405G It - on (all others out)G-V trace w~thin pattern to lwr rt

corner 9GRANGE lnd counts down to 0+02

EMS FUNC - EMS TEST 505G It - onRSI upper lt - on (10 sec later)RANGE md - 00SCrlbe traces vertlcal llne 9g to

022+01ALIGN SCROLL TO ENTRY PATTERN (on

37K ft sec hne)EMS FUNC - RNG SET

G-V scroll assy traces vert llne022g to 0+01

EMS MODE - STBY

28

29

30 -OllOh

-21-

~V TEST (Deorb~t only)EMS FUNC - ~V SETVHF RNGSET ~V ~nd to 15868 fpsEMS MODE - NORMALEMS FUNC - ~V TEST

SPS THRUST LT - onoff (10 sec)~V ~nd stops at -01 to -415

EMS MODE - STBY

PRIMARY WATER EVAP ACTIVATIONGLY EVAP H20 FLOW - AUTOGLY EVAP STH PRESS - AUTOPRI ECS GLY PUMP - ACI

CM RCS PREHEATNote If sys test mtr 5cd6abcd

all read 39 vdc (28degF) or moreom~t preheat

cb RCS LOGIC (2) - closeCM RCS LOGIC - ONUP T1M CM - BLOCK (ver~fy)

cb CM RCS HTRS (2) - closeCM RCS HTRS - ON (LMP Conf~rm)

(20 mlU or III lowest rdg lS39 vdc) (Moultor Maufpress for press drop)

31 (___) FINAL GDC DRIFT CK (If req I d)If drlft gtlOohr Suspect GDC Do not

use RSI amp FDAI 2

32 -OO5Om

33

34

35

TERM CM RCS PREHEATUP TLM CM - BLOCK (venfy)CM RCS HTRS - OFFCM RCS LOGIC - OFF

SYSTEMS TEST PANEL CONFIGURATIONSYS TEST METER - 4BRNDZ XPNDR - OPERATECM RCS HTRS - OFFWASTE H20 DUMP - OFFURINE DUMP - OFF

LEB LIGHTING - OFF

SEC WATER EVAP ACTIVATIONGLY To RAD SEC vlv - BYPASSSEC COOL EVAP - EVAPSEC COOL PUMP - AC2

36

37

38 -OO45m

-22-

PYRO BATT CKcb PYRO A SEQ A - close (ver~fy)

cb PRYO B SEQ B - close (verify)DC IND - PYRO BAT A(B)

~If PYRO BAT A(B) lt 35 vdc cb PYRO A(B) seq A(B) - open~

PYRO A(B)BAT BUS A(B)TO PYRO~MN BUS TIE - close

cb MNA BAT C - closecb MNB BAT C - closeDC IND - MNBPNL 8 - All cbs closed except

PL VENT - open (ver~fy)

FLOAT BAG (3) - open (ver~fy)

DOCKING PROBE (2) - open (verlfy)EDS BAT (3) - open (ver~fy)

CM ReS HTRS (2) - open

CM RCS ACTIVATIONcb SECS ARM (2) - close (verlfy)cb SECS LOGIC (2) - close (verlfy)SECS LOGIC (2) - ONMSFN conflrm GO for PYRO ARM(~f poss)SECS PYRO ARM (2) - ARMCM RCS PRPLNT 1amp2 - ONCM RCS PRESS - ONRCS Ind sw - eMl then 2

He PRESS 3700-4400 pSlaMANF PRESS 287-302 pSla

SECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFF

P27 amp ENTRY PAD UPDATEGo To Entry Checkllst

Superclrc - pg ~2~3 _Hybnd - pg -----2~9L-__Normal Deorblt - pg __3L5L- _

-23-

52 SUPERCIRCULAR ENTRY

1 SET DET (up to ET)

2

3

4

5

3000(-30-00)

EMS INITIALIZATIONSET RNG TO PAD DATA RNGEMS FUNC - Vo SETSlew Scroll to Pad Data VIOEMS FUNC - ENTRY

RS I ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on (up)GDC ALIGN PB - PUSH amp HOLDYAW Tw - Pos~t~on RSI thru

45deg amp back to LIFT UPGDC ALIGN PB - ReleaseEMS ROLL - OFFA1~gn CDC to lMU

CM RCS RING A CKRCS TRNFR - CMcb CM RCS LOGIC MNB - openAUTO RCS SEL MNB (6) - OFFSC CONT - SCSTest R~ng A ThrustersSC CONT - CMCRCS TRNFR - SMAUTO RCS SEL (12) - MNAMNB

(hftoff conflg)cb CM RCS LOGIC MNB - close

OPTICS PWR - OFFCMP to COUCH

MN BUS TIE (2) - ONTAPE RCDR - REWIND

6 35middot0Om(-25middot 00)

-24-

SEPARATION CK LISTTVC SERVO PWR 1 - AClMNAcb ELS (2) - close (ver1fy)PRIM GLY TO RAn - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY vlv - OFFCAB PRESS REL vlv (2) - NORMGMBL MTRS (4) - STARTABORT SYS PRPLNT - RCS CMD (venfy)SM RCS PRIM PRPLNT (4) - ONVHF 11M (AampB) - OFFHI GAIN ANT PWR - OFFFC PUMPS (3) - OFFVer1fy s1ugle SU1t compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - 10101cb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2) - opencb HTRS OVLD (2) - openPOT H20 RTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANSEC COOL EVAP - RESETSEC COOL PUMP - off (etr)

MtiVR TO CMSM SEP P R ATTSC CONT - SCSCMC MODE - FREEMNVR TO PAD ATTR (0deg)PY----W)

-25-

SUPERCIRCULAR ENTRY (Cont~nued)

1

4100m(-1900)

P61 - ENTRY PREP

V37E 61E

k 05 09 01427 - ROLL REVERSED 05 09 01426 - IMU UNSAT ~

2 F 06 61 IMPACT LAT LONG HDS UPDN (+-)PRO (010

fps +00001)

3 F 06 60 GMAXVPREDGAMMA EIRecord

GMAXV400K----

GAMMA EI _PRO

(01deg fpsOldeg)

4 F 06 63 RTOGO (lnm) PAD _VIO (fps) PAD _TFE(m~n-sec)

Compare w~th ~M~SFN==C~f~o-r~P~GNS GONO GOIf NO COMM Set RTOGO amp VIO In EMS

amp lnltla11ze(ACCEPT) PRO(RECALC) V32E To 4

5 F 50 25

4300m

(-1700)

45 oOm(-1500)

500Om(-1000)

6 F 06 61

-26-

P62 - CMSM SEP amp PRE-ENTRY MNVRCAUTION Call No EXT Verbs In P62

00041 REQUEST CMSM SEPSC CONT - SCSFREE

COMPARE PITCH ATT WITH PAD DATA ---0=-

(W~thLU 5deg)YAW - 45deg OUT-OF-PLANE (LEFT)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTIRATE 2MN BUS TIE (2) - ON (ver~fy)

PRIM GLY TO RAD - BYPASS (verlfy)CM RCS LOGIC - ON (venfy)SECS LOGIC (2) - on (up)SECS PYRO ARM - ARMCMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 ps~a

CM RCS LOGIC - OFFSECS PYRO ARM (2) - SAFEMonltor VMAB

If lt25 vdc go to EMERGPOWERDOWN pg E6-l

AUTO RCS SEL AC ROLL (4) - OFFAUTO RCS SEL CM 2(6)-OFFAUTO RCS SEL CM 1(6)-MNAYAW back to 0degPITCH TO HORIZ TRACK ATT

ROLL - 0deg (LIFT UP)PITCH - 400K Horiz Mark (317deg)YAW - 0deg

ATT DB - MAXMAN ATT PITCH - ACCEL CMDEMS DATA - Ver~fy

EMS FliNC - ENTRY (ver~fy)

EMS MODE - NORMALcb SPS PampY (4) - openMAINT HORIZ TRK

PRO (Act ENTRY DAP)

IMPACT LATLONGHDSDN (01deg01deg-00001)PRO

7 POSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axis beyond 45deg of Vel vector)

8 06 64

58middot00m(-0200)

9

05G tlme(+0 )

(--=---)

06 68

-27-

P63 - ENTRY INIT

GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PIJR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRmDHORIZ CKPltch error needle goes toward

zero approachlng OSG tlmeMAN ATT (PITCH) - RATE CMD

If CMC lS GOBMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS I

FLY BETA If CMC NO GO ilt

1 SC CaNT - SCS I

FLY EMS k

p64 - ENTRY POST 05G

RTOGO AT 05G AGREES HITH EMS-venfyHORIZ CK05G Lt - ON (EMS START)

No EMS START wlthln 3 sec ~ EMS MODE - BACKUP VHF RNG c

05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds Llft DN

NNVR Llft DNEMS GONO GO

G-V Plot wlthln IlmltsRng ctr dwn 60plusmn7 durlng 10 sec

perlodMonltor G-meter for

convergence wlth pad data (Do)(Vlt27K fps) Go to 13

-28-

P65 - ENTRY - UP CONT (Vgt27K fps)

10 F 16 69 BETA (01middot) _DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT lt~ SC CONT - SCS FLY EMS

PRO

11 06 68 BETAVIHDOT (OIdegfpsfps)(VltV1+500 fps amp RnOT Neg) Go To 13

P66 - ENTRY - BALLISTIC (D(DL)

12 06 22 DESIRED GMBL ANGLES RPYMoultor horlz +12middot of 317middot mark

P67 - ENTRY - FINAL PHASE (02G)

13 06 66 BETACRSRNG ERRDNRNG ERR(010 1um 1um)

KEY VERBRecord DNRNG ERR _KEY RLSEMoultor l~ft vector ou RSI amp FDAI

16 67 RTOGOLATLONG (Vrel=1000fps)(lumOldegOldeg)

SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOWNMonitor a1t~meter

Go To EARTHLANDING pg ---4L5 _

-29-

53 GampN HYBRID DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL tV1 V37E 30E

2 F 06 33 GETI(ACCEPT) PRO (hrm~n Olsec)(REJECT) LOAD DESIRED GETI

3 F 06 81 tVXYZ (LV) (lfps)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

4 F 06 42 HAHPtV (lnm lfps)Record tV

(ACCEPT) PRO(REJECT) Reselect P30 or P27 Load new paramo

5 F 16 45 MTFIMGA (marksm~n-secOlO)

MGA -00002 ~f k

k lMU not al~gned

SET DETPRO

6

7

8

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (Pull)PLSS 02 vlv - FILL02 8M SUPPLY vlv - OFFCAB PRESS REL vlv (2) - NORMcb ELS (2) - closecb SECS ARM (2) - closecb SECS LOGIC (2) - close (ver~fy)

AUTO RCS SEL CM (12) - MNA or ~ffiB

(hftoff conhg)ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM (AampB) - OFF

CMP to Couch

9

10

11

-30-

MNVR TO PAD BURN ATTLOAD DAPBMAG MODE (3) - RATE 2SC CONT - CMCAUTOATT DB - MINMAN ATT (3) - RATE CMD

v62E

v49E

12 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLES

PRO

13 F 50 18 REQ MNVR TO FDAI RPY ANGLES (01deg)(AUTO) PRO(MAN) SC CONT - SCS

BMAG MODE (3) - RATE 2MNVR To 15

14 06 18 AUTO MNVR TO FDAI RPY ANGLES (01deg)

15 F 50 18 REQ TRIM TO FDAI RPY ANGLES (01deg)(TRIM) Go to 13(ByPASS) ENTR

16

17

CHECK BORESIGHT amp SKT STARSOPT MODE - CMCOPT ZERO - OFF

v41 N91E

18 F 21 92 SHAFTTRUN (01deg 001deg)Load SXTS angles

19 41 OPTICS DRIVECheck SKT STAR

OPT ZERO - ZEROCheck BORESIGHT STAR (~f ava~l)

20 V25 N17E (01deg)Load Pad Data GMBL Angles

for CM BURN ATTATT SETtw - SET

to PAD DATA GMBL ANGLESfor CM BURN ATT

21

22

-31-

PHR REDUCTIONHGA PHR - OFFFC PUMPS (3) - OFFVerify s~ngle su~t compr oper loads

balancedFC 2 MN AampB - OFFS BD PiR AMP - LOWcb ECS RAD CONTHTR (2) - opencb HASTE H20URINE DUMP HTRS(2)- opencb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANMN BUS TIE (2) - ONTVC SERVO PHR 1 - AC1MNAGMBL MTR (4) - START

p41 - RCS THRUSTINGV37E 41E

23 F 50 18 REQ MNVR TO LCL HORIZ (HDS ON)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CMCAUTOPRO To 24

(gtfANDAP) BMAG MODE (3) - RATE 2SC CONT - CMCHOLD

V62EMNVR To 25

24 06 18 AUTO MNVR TO FDAI RPY

25 F 50 18 REQ TRIM TO LCL HORIZ (01deg)ALIGN SC ROLL

(AUTO TRIM) PRO To 24(BYPASS) ATT DB - MIN

RATE - LOHMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTlRATE 2

ENTR

550Om26 06 85

59middot2527

-32-

VGXYZ (1fps)RECHECK BORESIGHT STARTRANS CONIR PWR - on (up)EMS MODE - STBY (ver~fy)

EMS FliNC - bV SETVHF RNGSET (IV for SM BURN _EMS FliNC - bVS BD ANT - OMNI CSECS LOGIC (2) - ONMSFN conhrm Go for PYRO ARMSECS PYRO ARM (2) - ARMCM RCS LOGIC - ON (ver~fy)

DSKY BLANKS

593028 16 85 VG XYZ (AVE G ON) (lfps)

RHCs amp THC - ARMEDLIMIT CYCLE - OFFTAPE RCDR - CMD RESETHBREMS MODE - NORMAL

000029 F 16 85 REQ NULL VG XYZ (lfps)

BURN EMS bV CTR TO ZERORESET DET amp COUNT UP

If SM ONLY burn go to step 32THC - LOCKEDSC CaNT - SCSFREERATE - HIGHPRIM GLY To RAD - BYPASS (ver~fy)

MN BUS TIE (2) - ON (ver~fy)

CMSM SEP (2) - on (up)CSMLM FNL SEP (2) - on (up) (verify)CampW MODE - CMRCS TRNFR - CMCM RCS LOGIC - OFF

Momtor VM ABIf lt25 vdc go to EMERGPOWER DOWN Pg E6-l

V63E

If CMC NO GO FDAI SOURCE - ATT FDAI SEL - 1 or 2 ATT SET - GDC

SET

-33-

~Uili ATT PITCH - ACCEL CMDFDAI SCALE - 55MNVR TO CM BURN ATT (NULL ERR NEEDLES)

R 0degPY --00--

30

31

CM RCS BURNRHC III-ContJnuous PJtch DownRHC HZ-Module PJtch to null needlesBURN VGZ TO ZERO

If only 1 RHC Pulse + P=5deg from retro att MaJnta~n rates lt3degsec

BURN COMPLETION ATllV CTR= or DET= _

V8ZE

32 F 16 44 HAHPTFF (1nmffiJn-sec)Check HP-

If gt Pad data contJnue burnuntJ1 lt Pad

PRO

33 F 16 85 VGXYZ (Ups)Read VG resJduals to MSFN

(HYBRID) PRO to 34(SM ONLY BURN)

PROF 37 ODE

EI-1500 V37E 47EF 16 83 twx Y Z (Ups)

SC CONT - SCSFREEMAN ATT (PITCH) - RATE CMDRATE - HIGHPRIM GLY To RAD - BYPASS (verJfy)MN BUS TIE (2) - ON (verJfy)CMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verJfy)Campl MODE - CMRCS TRNFR - CMCM ReS LOGIC - OFFSECS PYRO ~I (2) - SAFE

-34-

PROMonitor VMAB

If lt25 vdc go to EMERGPOWER DOWN

34 F 37 OOEPCM BIT RATE - LOWATT DB - MAXEMS MODE - STBYEMS FUNC - OFF

Go To EARTH ORBIT ENTRY pg _--40-__

-36-

8 SPS THRUSTING PREPCYCLE CRYO FANSSPS GAGING - ACI (ver~fy)

PUG MODE - NORM (venfy)BMAG MODE (3) - RATE 2tv CG - CSMCMC MODE - FREEAUTO RCS SEL (16) - MNA or HNB

(hftoff conbg)SC CONT - CMCAUTO

9 MNVR TO PAD BURN ATTV62E

10 V49E

11 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLESPRO

12 F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) PRO(HAN) SC CONT - ses

MNVR to 14

06 18 AUTO MNVR TO FDAI RPY ANGLES13

14 F 50 18 REO TRIH TO FDAI RPY ANGLES(TRIM) Go to 12(BYPASS) ENTR

15 BORESIGHT STAR CHECK

16 V37E 40EOPT PWR - OFF

17 F 50 18 REQUEST MNVR TO FDAI RPY ANGLES (01deg)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CHCAUTOPRO to 18

(MANDAP) BMAG HODE (3) - RATE 2SC CONT - CMCHOLDMNVR to 19

(HANseS) se eONT - sesMNVR to 19

-35-

54 NORMAL DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL ~V

1 V37E 30E

2 F 06 33 GETI (hrm~nOlsec)

(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

3 F 06 81 ~VXYZ (LV)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

( lfps)

4 F 06 42 HAHP~V (1nmlfps)Record W

(ACCEPT) PRO -----(REJECT) Rese1ect P30 or P27 Load new pa~am

5 F 16 45 MTFIMGA (marksmln-secOldeg)MGA -00002 If ~ lMU not a1~gned

SET DETPRO

6

7

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY v1v - OFFCAB PRESS REL v1v (2) - NORMcb ELS (2) - close (verify)cb SECS ARM (2) - close (ver~fy)

cb SECS LOGIC (2) - close (verlfy)AUTO RCS SEL CM (12) - ~mA or MNB

(l~ftoff conf~g)

ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM AampB - off (ctr)

18

-37-

06 18 AUTO MNVR TO FDAI RPY ANGLES (01 0)

19 l 50 18 REOUEST TRIM MNVR TOALIGN SIC ROLLGDC ALIGN

FDAI RPY ANGLES(010

)

+54-00m(-06-00)

TIG-5mJn

5500m(-0500)

TVC CHECK amp PREPcb STAB CONT SYS (all) - closecb SPS (12) - closeATT DB - MINRATE - LOl~

LIMIT CYCLE - ONMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE 2ROT CONTR PWR DIRECT (2) - OFFSCS TVC (2) - RATE CMD

If SCS SCS TVC (2) - AUTO SC CONT - SCS ~

TVC GMBL DRIVE PampY - AUTOMN BUS TIE (2) - ONTVC SERVO PWR 1 - AC1MNA

2 - AC2MNBTRANS CONTR PWR - ONROT CONTR PWR NORMAL 2 - ACRHC 2 - ARMED

HORIZ CHK - HorJz on 12deg wJndmlmark (LJffiJt +3 0 PNGCS GONO GO)

If NO GO set tw 180 0 180deg0 0

Track horJz wJth 24deg wJndow markAt TIG-2 mJn Ahgn GDC

PRIMARY TVC CHECKGMBL MOT P1-Y1 -STARTON(LMP confJrm)

If SCS verJfy Thumbwheel TrJmTHC - CWVenfy NO MTVC

SEC TVC CHECKGHBL MOT P2-Y2 -STARTON(LMP confJrm)SET GPI TRIHVenfy MTVCTHC NEUTRALGPI returns to 00 (CMC) or trJm (SCS)ROT CONT Pl~ NORM 2 - ACDC

(TRIM) Go to step 17(BYPASS) BMAG MODE(3) - ATTIRATE2 (ver1fy)

ENTR

-38-

20 F SO 25 00204 GMBL TEST OPTION(ACCEPT) SC CONT - GMC (ver~fy)

PROMonitor GPI Response

0020-2000020-200Tr~m

TEST FAIL SC CONT - SCS SCS TVC (2) - AUTO

(REJECT) ENTR

21 06 40 TFIVG~VM (m~n-sec1fps)

PROG ALM - TIG s1~pped

V5N9E 01703

KEY RLSE To 21 ROT CONTR PWR DIRECT (2) - MNABSPS He v1vs (2) - AUTO (ver~fy)

LIMIT CYCLE - OFFFDAI SCALE - SOIScb SPS P2Y2 - open (for cr~t burn)

5800(-02 00)

5925(-0035)

59middot 30(-0030)

06 40

59XX(-OOXX)

AV THRUST A(B) - NORMALTHC - ARMEDRlIC (2) - ARMEDTAPE RCDR - GID RESETHBR

DSKY BLANKS

(AVE G ON)EMS MODE - NORMAL

TFIVG~VM (m~n-seclfps)

CHECK PIPA BIAS lt2fps for 5 sec

ULLAGE AS REQ

IF NO ULLAGE DIR ULLAGE PB - PUSH~

CONTROL ATT WRlIC MONITOR AVM (R3) COUNTING UP

5955(-0005)

F 99 40 ENG ON ENABLE REQUEST(AUTO IGN) PRO AT TFI gt0 sec(BYPASS IGN) ENTR to 24

22 0000 IGN

-39-

If SCS - THRUST ON PB - PUSH

06 40 TFCVG~VM (m~n-seclfpslfps)

~F 97 40 SPS Thrust fall ~

~(RESTART) PRO To IGN (RECYCLE) ENTR To TIG-05 sec

SPS THRUST LITE - ONMONITOR THRUSTING

Pc 95-105 pSlaEMS COUNTING DOWNSPS IN3 v1vs (4) - OPENSPS He v1vs tb (2) - graySPS FUELOXID PRESS - 175-195 pSlaPUGS - BALANCED

PROG ALARM V5N9E 01407 VG INCTHC - CW FLY MTVC

ECOEMER SPS CUTOFF J

AV THRUST (2) - OFF

23 F 16 40 TFC(STATIC)VG~VM (mln-seclfps)~V THRUST AB - OFF

SPS IN3 v1vs (4) - CLOSEDSPS He tb (2) - bp

cb SPS P2Y2 - closed (verlfy)TVC SERVO PHR - AC1MNA (venfy)TVC SERVO PWR 2 - OFF

PRO

24 F 16 85 VG XYZ(CM) CUps)NULL RESIDUALSRECORD ~V CTR amp RESIDUALS I1VCEMS FUNC - OFF VGXEMS MODE - STBY VGYBMAG MODE (3) - RATE 2ATT DB - MAX VGZTRANS CONT PHR - OFF

PRO

25 F 37 V82E

26 F 16 44 HAHPTFF (lnmm~n-sec)

R3-59B59 HP gt494 nmPRO

27 F 37 OOE

-40-

55 EARTH ORBIT ENTRY

1 Venfy CMSMR __

P_shyY_-

SEP ATT(180deg)

(0deg )

2

3

4

EMS INITIALIZATIONEMS FUNC - RNG SETSET RNG TO PAD DATA RNGEMS FUNC - VA SETSlew scroll to pad data VIOEMS FUNC - ENTRY

RSI ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on(up)GDC ALIGN PB - PUSH amp HOLDYAW tw - Pos1tion RSI thru 45deg amp

back to LIFl UPGDC ALIGN PB - RELEASEEMS ROLL - OFFAl1gn GDC to lMU

PWR REDUCT (Norm Deorb Only)HGA PWR - OFFFC PUMPS (3) - OFFVer1fy s1ngle suit compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - Lowcb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2)-openlOb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MAN

-41-

P61 - ENTRY PREP

5 V37E 61E05 09 01427 - ROLL REVERSED05 09 01426 - IMU UNSAT

6 F 06 61 IMPACT LAT LONG liDS UPDN (+-)(01 0

010

+00001)

PRO

PAD VALUESLATLON==G------liDS UP DN _

7 F 06 60 GMAXV400KGAMMA EIRecord

GMAXV400K----GAMMA EI _

PRO

8 F 06 63 RTOGO (1nm) PAD _VIa (fps) PADTFE (mln-sec) ----Compare wlth MSFN for PGNS GONO GONO COMM SET RTOGO amp VIO IN EMS amp

INITIALIZE(ACCEPT) PRO(RECALC) V32E to 8

-42-

P62 - CMSM SEP amp PRE-ENTRY MNVR

9 F 50 25 00041 REQUEST CMSM SEPSC CONT - SCSFREEYAW - 45deg out-of-plane (left for RCS

nght for SPS)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE2PRIM GLY to RAD - BYPASS (verlfy)SECS LOGIC (2) - on (up)MSFN conflrm GO for PYRO ARMSECS PYRO ARM - ARMMN BUS TIE (2) - ON (verlfy)CMSM SEF (2) - ONCSMLM FNl SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 pSlaCM RCS LOGIC - OFFSECS PYRO ARM - SAFEMonltor VMAB

If lt25vdc go to EMERG POWERDOWN Pg E6-1AUTO RCS SEL AlC ROLL (4) - OFFAUTO RCS SEL CM 2(6) - OFFAUTO RCS SEL CM 1(6) - MNA or MNBYAW back to 00

PITCH TO ENTRY ATTROLL 0deg (LIFT UP)PITCH - HORIZ on 317deg MARK (400K)YAW 00

ATT DB - MAXMAN ATT (PITCH) - ACCEL CMDEMS DATA - VerifyEMS FUNC - ENTRY (verlfy)EMS MODE - NORMALMAINTAIN HORIZ TRK

PRO (Act ENTRY DAP)

10 F 06 61 IMPACT LAT LONG HDSDN(010 010 -00001)

PRO

11 FOSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axlS beyond 45deg of Vel vector)

-43-

P63 - ENTRY INIT

12 06 64 GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PWR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRHORIZ CKP~tch error needle goes toward

zero approach~ng 05G t~me

MAN ATT (PITCH) - RATE CMDIf CMC ~s GO

BMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS FLY BETA If CMC NO GO ~

SC CONT - SCS~

FLY EMS RCS Deorh Roll HDS UPTRACK HORIZ w~th 29deg w~ndow mk

P64 - ENTRY POST 05G

13

05G t=elt+0___)

06 68

RTOGO AT 05G AGREES WITH EMS - venfyHORIZ CK05E Lt - on (EMS start)

No EMS start w~th~n 3 secsEMS MODE - BACKUP VHF RNG 05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds L~ft DN

NNVR L~ft DNEMS GONO GO

G-V Plot w~th~n llm~ts

Rng ctr dwn 60 + 7 durlng 10 sec per~od

Mon~tor G-meter forconvergence wlth pad data (Do)

(Vlt27K fps) Go To 17

-44-

P65 - ENTRY - UP CONT (Vgt27K fps)

14 F 16 69 BETA (01deg)DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT~

SC CONT - SCS FLY EMS

PRO

15 06 68 BElA VI HOOT (01deg fpsfps)(VltVL +500 fps amp RDOT Neg) Go To 17

p66 - ENTRY - BALLISTIC (DltDL)

16 06 22 DESIRED GMBL ANGLES RPY (01deg)Mon~tor hor~z +12deg of 317deg mark

P67 - ENTRY - FINAL PHASE (02G)

17 0666 BETACRSRNG ERRDNRNG ERR (Oldeglnmlnm)KEY VERBRecord DNRNG ERR _KEY RLSEL~m~t +100nm from PAD DRE

Mon~tor l~ft vector on RSI amp FDAIF 16 67 RTOGOLATLONG (Vre1=1000fps)

(lnm 010 01deg)SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOlfflMon~tor altimeter

Go To EARTHLANDING pg _I4L5__

-45-

56 EARTHLANDING

90K STEAM PRESS - PEGGED50K CABIN PRESS REL vIv (2) - BOOSTENTRY

SECS PYRO ARM (2) - ARM

40K(90K + 63s)

CM UNSTABLE RCS CMD - OFF ~ 40K APEX COVER JETT PG-PUSH DROGUE DEPLOY PG - PUSH (2 secafter apex cover Jett)

30K ELS LOGIC - ON (up)ELS - AUTO

24K RCS hsable (auto)(90K+92s) RCS CMD - OFF

Apex cover Jett (auto)APEX COVER JETT PB - PUSH

(WAIT 2 SECS)Drogue parachutes deployed (auto)

DROGUE DEPLOY PB - PUSH~

If Drogues FallELS - ~ ~Stablllze CM 5K MAIN DPLY PB - PUSHELS - AUTO

235K Cabln Pressure lncreaslng (Drogues + 50s)If not lncreaSlng by 17K CABIN PRESS REL vlv (RR) - DUMP

-46-

10K Maln parachutes deployedMAIN DEPLOY PB - PUSH (wlthln 1 sec)VHF ANT - RECYVHF AMA - SIMPLEXVHF BCN - ONCABIN PRESS REL v1v (2) - CLOSEDIRECT 02 vlv - OPENCM RCS LOGIC - on (up)CM PRPLNT - DUMP (burn audlb1e)Monltor CM ReS 1amp2 for He press decrease

NO BURN or PRESS DECREASE USE BOTH RHCs DO NOT FIRE PITCH JETS

CM PRPLNT-PURGE (to zero He press)CM RCS He DUMP PB - PUSH RHC (2) - 30 sees NO PITCH k

STRUT LOCKS (2) - UNLOCK

cb FLT amp PL BAT BUS ABampBAT C (3) - closecb FLT amp PLT MNA amp B (2) - opencb ECS RAD HTR OVLD (2) - opencb SPS PampY (4) - open

3K CABIN PRESS REL v1v (RH) - DUMP (after purgecompleted)

FLOOD Lts - POST LDGCM RCS PRPLNT (2) - OFFROT CONTR PWR DIRECT (2) - OFF

800 CAB PRESS RELF vlv - CLOSE (latch off)MN BUS TIE (2) - OFF

AFTER LANDINGcb MAIN REL PYRO (2) - closeMAIN RELEASE - on(up)

Go to POSTLANDING pg _47L-__

I

2

3

-47-

57 POSTLANDING

STABILIZATION VENTILATION COMMUNICATIONS

DIRECT 02 vlv - CLOSE

Stablllzation after landlngELS - AUTO (verlfy)cb MAIN REL PYRO (2) - close (venfy)MAIN RELEASE - on (up) (verlfy)S~CS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb BAT RLY BUS (2) - open

No contact w1th recovery forcesVHF AM AampB - off (ctr) ~

VHF AM Rev ONLY - A cb PL VENT - closecb FLOAT BAG (3) - closecb UPRIGHT SYS COMPRESS (2) - closeIf Stable II

FLOAT BAG(3)-FILL t1ll 2 m1n afterupr1ght then - OFF

VHF AM AlB amp BCN - OFF whlle lnvertedIf Stable I

After 10 M1n Coollng Per1odFLOAT BAG (3) - FILL 7 mln then OFF

Post Stab1lizat1on And Ventllat10nPL BCN LT - BCN LT LOWPL VENT vlv - UNLOCK (Pull)Remove PL VENT Exh CoverPL VENT - HIGH or LOWPL DYE MARKER - ON (swlmmer comm)Release foots traps and_restralntscb MNA BAT BUS A amp BAT C (2) - opencb MNB BAT BUS B amp BAT C (2) - opencb FLT amp PL BAT C - opencb PYRO A SEQ A - opencb PYRO B SEQ B - open

EACH HR - CHECK DC VOLTSgt 275 V If Notmiddot cb FLT amp PL-BAT BUS AampB (2) -open cb FLT amp PL BAT C (1) - open GO TO LOW POWER CHECKLIST

Unstow and lnstall PLV DISTRIB DUCTDeploy grappllng hook and 11ne 1f req

4

-48-

Post Landing Communlcatl0nsVHF ANT-RECY (venfy)VHF BCN - ON (verlfy)

If no contact ~lth recovery forcesperform VHF BEACON Check

MONITOR VHF BEACON transmlSSlonnth VHF AM B Rcvr andor Su)vlval

TransceiverkVHF Beacon not operatlng ~connect Surv~val TranscelVer to antcable behlnd VHF ant access pnland place radio ln BCN mode

LOW POHER CHECKLISTVHF BCN - OFFVHF AM (3) - RCVFLOOD Lts - OFFVHF AM AampB - off (ctr)VHF AM RCV ONLY - A (venfy)COUCH LIGHTS - OFFPOSTLANDING VENT SYS mlnlmlze useSURV RADIO - plug mto VHF BCN ANT cableconn behind VHF ant acess pnl amp turn radloon l-n BCN mode

EGRESS PROCEDURES

CMPCDRLMPCDR

CMPCDRCMP

LMPLl1PCDR

STABLE IDlsconnect Umblll-calsNeck darn onCenter couch - 270 0 positionArmrests stowedConnect raft to SIC l-f desl-red wlth

green lanyardConnect raft ~hl-te lanyards to SUltS amp

lnflate water wlngs when eXltl-ngHATCH PISTON PRESS vlv - PRESS (Outbd)Slde Hatch openedPL VENT - OFFcb Pnl 250 (all) - openEgress with 11feraftPut hardware klt outEgress

or CDIPALL

CMF

CDRCMF

CDR

LMF

CMFCMP LMFCMP

UlP

CDR

-49-

STABLE IIcb CREW STA AUDIO (3) - openD~sconnect umb~1~ca1s

Release foots trapsRelease restra~nt harnessCouch seat pans (3) - 170 0 pos1t10nArm rests stowedSurv1va1 k~ts removed from stowageConnect life raft ma~n1~ne to CDR or SicConnect f~rst wh~te lanyard from

11fe raft to suitConnect th~rd wh~te lanyard from

l~fe raft to SU1tConnect rucksacks together to yellow

lanyard on raft bagPRESSURE EQUALIZATION vlv - OPENRemove and stow fwd hatchEX1t feet f1rst w1th rucksacks when clear

of siC 1nflate water w1ngs and raftExit feet f1rst when clear of SiC

1nflate water w1ngsEX1t feet f1rst when clear of sic

1nflate water w1ngs

-50-

60 TLI ABORTS

TLI Aborts are conta~ned ~n the ESD s~nce the bulk of the funct~ons

concern entry preparat20ns and performance Th~s allows a s2nglesource of procedures for procedure rev2ew val~dat~on checkout andtra~n~ng These procedures ~ncorporate TLI preparat20ns as found ~n

reference 6 w~th the TLI Abort Procedures and these t~e 2nto normallunar return Entry Procedures found ~n sect20n 5 The guidel~nes

for th~s cont2ngency are spec2f2ed 2n reference 7

In2t2al preparat~ons for TLI pos2t20n the necessary system sW2tches2n add~t~on to perform~ng an EMS ~V test and a GDC al~gnment Afterthe DET ~s set for mon2tor2ng TB6 the CMP ~ncreases the 12ght levelof the LEB DSKY to max~mum and returns to the h2s couch Th2s 2Sdone so that the LEB DSKY can be observed ~n the event sunl~ght orreflect20ns wash out the ma2n d2splay panel DSKY dur2ng cr2t2calmaneuvers The crew then straps ~n and prepares for mon2tor~ng TB6as 2nd2cated by the SII SEP L~te The t2mes se~uence of procedures2S keyed on th~s d~splay and ~ncludes the DET START funct~on andSIVB IGNITION Dur2ng the burn the crew mon2tors the FDAIs foratt~tude excurs20ns and abnormal rates report~ng status checks toM~ss2on Control at d2screet t~mes dur2ng the maneuver Upon SIVBSHUTDOWN the eMP records the DSKY d~splayed performance parametersand awa2ts ground conf2rmat~on

The rat~onal for TLI aborts ~s descr~bed 2n reference 7 A summar2shyzat20n 2S extracted to prov2de background and gu2de12nes 2n th2sdocument The abort procedures cover aborts 10 m2nutes after conshyt2ngent SIVE shutdown and aborts 90 m2nutes after normal SIVE shutshydown t2me

The 10 m~nute TLI abort ~s des2gned to be used dur~ng TLI ~n theevent a spacecraft problem develops Wh2Ch can result 2n catastrophe2f ~mmed~ate act~on 2S not taken If the s~tuat20n perm~ts the crewshould always allow the SIVB to complete TLI at wh~ch t~me the groundand crew can perform a malfunct~on analys~s to determ~ne ~f an abort~s adv~sable If a fa~lure occurs that necess2tates the shutdown ofthe SIVB and the ~u~ck return of the crew to earth th~s abort ~s

des~gned to be as ~nsens~t~ve to execut~on errors as poss~ble andst21l be targeted to m2dcorr2dor The burn att~tude w~th the f~ed

hor~zon reference ~s a constant value for any shutdown t~me Theburn durat~on 2S a funct20n of shutdown t2me and 2S ava21able fromcrew charts S~nce the pr~mary purpose of th~s abort ~s to returnto earth as qU2ckly as poss2ble there are no restr2ct20ns as toland~ng locat~on However ~f the t~me to EI is greater than abouttwo hours a midcourse correct20n should be ant~c~pated

The 90 m2nute TLI abort 2S to be used 2f a cr2t2cal subsystem malshyfunct~on ~s determ2ned and the dec2s~on to abort ~s made after the

-51-

TLI cutoff and before TLI cutoff plus approxlmately 80 m1nutesTh1S allows suff1c1ent separatlon and procedural t1me to set upfor the SPS deorb1t burn performed at about TLI + 90 Note thatgenerally the deorb1t burns w1ll be performed a fe11 m1nutes beforeTLI + 90 accord1ng to crew charts shown In reference 8 The no-comm except10n requ1res that 90 m1nutes be the 1nput t1me of 19n1shytlon for P-37 (onboard return-to-earth abort program) so that onshyboard calculatlons can correspond w1th ground calculat10ns to computethe CM land1ng p01nt Th1S TLI abort lS des1gned so that returnfl1ght t1me does not exceed 18 hours and abort ~V does not exceed7000 fps ThlS abort can be performed uSlng chart ~Vs and attltudesand the earths hor1zon serves as a suff1c1ent reference The maneushyver lS targeted to ach1eve the mldcorr1dor entry target Ilne andtlmed to result 1n a deslgnated recovery area

It 1S ObV10US for abort deC1S1ons early 1n the TLI + 90 m1nute t1meshyframe that a GampN SPS burn should be performed In order to keep theTLI abort procedures cons1stent and w1th emphasls on slmpl1c1ty theprocedures here reflect a SCS SPS abort burn to cover the full abortdec1s1on t1meframe

A m1dcourse correct1on for corr1dor control after a TLI abort may bedeS1red 1f the SPS burn d1d not meet expectat1ons The TLIabortprocedures 1n th1S sect10n adapt to the normal lunar return tlmel1neand procedures pr10r to the f1nal MCC

-52-

61 TLI PREPARATION PROCEDURES

GET = 150

CRO AOS(___)

CRO LOS( )(22142)

5100

Don Helmets amp Gloves

XLUNAR - INJECT (verify)EDS PWR - on (venfy)EMS FUNC - OFF (verlfy)EMS MODE - STBYEMS FUNC - IW SETVHF RNGEMS MODE - NORMALSet ~V indo to +15868 fpsEMS FUMC - ~V Test

SPS THRUST Lt - onoff (10 sec)~V lnd stops at -01 to -415

EMS MODE - STBYEMS FUMC - ~V SETVHF RNGSet ~VC

EMS FUNC---~~V=----

GDC ALIGNFDAI Select - liZcb SECS LOGIC (Z) - close (verify)cb SECS ARM (Z) - closeSECS LOGIC (Z) - on (up)MSFN Conflrm GO for PYRO ARM (If pass)SECS PYRO ARM (Z) - on (up)TRANS CONTROL PWR - ONROT CONTR PWR NORMAL (Z) - ACDC(verlfy)ROT CONTR PWR DIRECT (Z) - MNAMNBLV INnGPI - SIISIVB (venfy)LV GUID - IU (venfy)cb DIRECT ULLAGE (Z) - closedSet EVENT TIMER to 5100Begin MONITOR For TB6

CMP to Couch

TB 6 - SII SEP Lt on (TIG-9 mln 38 sec)KEY V83E

SET ORDEALFDAI Z ORB RATE at 180 0 0SII SEP Lt out (38 sec later)Start DET COUNTING UPSC CaNT - SCS (verify)MONITOR LV TANK PRESS

~P lt 36 psid (OXID gt FUEL)~P lt Z6 psid (FUEL gt OXID)

EMERGENCY CSMLV SEP UP TLM CM - BLOCK (verify)UP TLM IU - BLOCK (venfy)

-53-

+45degPY))0middot sec PY

lOK nmltHAlt25K nm

Two phas~ng mnvrs two SPS mnvrs to circular~ze at 150 nmearth orb~t

CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ssion 4K nmltHAltlOK nm CSM amp1M - Two phasing mnvrs two SPS mnvrs to circularize at 150 nm earth orb~t CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ss~on

CSM amp 1M - Two phas~ng mnvrs APS burn todepletion th~rd phasing mnvrSPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn tosem~sync orb~t

25K nmltHAlt40K nm CSM amp 1M - Two phasmg mnvrs APS burn to depletion third phas~ng mnvr SPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn to sem~sync orbit HA)40K nm DPS ava~l - DPS LOll circularize with SPS

DPS not ava~l - Lunar flyby or CSM only to lunar orbit (if reqd gtV lt4000 fps)

V37E 47E (check b~as) Record -=--rshy(Limit 98 fpsmm)

( 1fps)tVXYZN62EVIHDOTHPAD (fpsfpslnm)MONITOR VI ( ) at ECO

SCS TVC SERVO PWR 1 - ACIMNA2 - OFF

TAPE RCDR - CMD RESETHBREMS MODE - NORMAL

SIr SEP Lt - ONTLI Inhib~t S~gnals w~11 not be honored after 5942

SIVB ULLAGE BeginsSII SEP Lt - off (TIG - 18 sec)SIVB FUEL LEADSIVB ULLAGE d~scont~nues

LV ENG I Lt - onSIVB IGNITION ( GETI)LV ENG I Lt - off - -shyMONITOR THRUST amp ATTITUDEMONITOR LV TANK PRESSSIVE ECO (Lt on) (BEGIN TB7)

EMER SIVE CUTOFF AT 6 SEC PAST BURN TIME IF VI ATTAINEDTHC CCW ampNEUTRAL IN 1 SEC or SIISIVB sW - LV STAGEPremature Shutdown HAlt4K nm CSM amp 1M -

5700

58205836

F 16 835800

F 16 62

5838594259525955595900000002SUNRISE(___)

HAW AOS(__=_) KEY VERB (freeze d~splay)

SIVB ATT HOLD 20 sec amp BEGIN VENTINGSIVB NNVR TO ORB RT (HDS DN) (3middot sec)

Record VI -c---HDOT _

HPAD _

KEY RLSEF 16 62

F 16 83

HAW LOS(__=-)

KEYmiddotRLSE~VXYZ (lfps)

Record ~VX---_

~vy

WZ--

AVC---_

TAPE RCDR - off (ctr)EMS MODE - STBYEMS FUNC - OFFSECS PYRO ARM (2) - SAFE

PRO

BURN STATUS REPORT

____--~TIG

BT------VGX____-R

-----P----_Y

REMARKS

_____VI

______--HDOT______--H______---AVC______---FUEL_______OXID

_______UNBAL

F 3708=00 OOEGOS AOS CMP TO LEB

(-=-=-)

0000

0003

0005

0014

0100

-55-

62 TLI 10 MIN ABORTSECS LOGIC (2) - on (up)SECS PYRO ARM (2) - ARM

TRANS CONTR - CGH (4 sec) amp +XDET RESET (verlfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS GMD-ON

TRANS GONTR - neutral then +X for10 sec

SIVBGPI s~ - GPIExcesslve rates 6V THRUST A - NORMAL SPS THRUST - DIRECT When rates damped 6V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

TRANS CONTR +X - OFFV37E OOE

PITGH UP to LOGAL VERT (+X axlSto~ard the earth)

RATE - LOWBMAG MODE (3) - ATTIRATE 2EDS PHR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SEGS ARM (2) - opencb EDS (3) - open

TRANS CONTR -X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (180deg)P (199deg)Y (0deg)

RETRO UPDATEGETI _

JV _VG

Jtb ---GET 400K _

05G _GET DROGUE _

ENTRY P _R _

Y_--

0945

-56-

ALIGN HORIZ ON RET +1 MKGMBL CHECK (T11lle Pentattlng)MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conflnn)cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FUMC - JV SETVHF RNGSET JV from chartE~S FUMC - JVEMS fODE - NOIDlAL

lV THRUST A - NORMALV37E 47E (THRUST fONITOR)

F 16 83 lVXYZ (1 fps)

0950

1000

NOTE For aborts durlng 1st mln of TLIKEY V82E F 16 44 (HaHpTff)Burn untll Hp lt 19NM

TRANS CONTR +X

THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN JV reqdJV THRUST (2) - OFFReport cutoff

cb SPS P2 Y2- closeGfBL MTRS (4) - OFF (LMP Confinn)TRANS CONT PWR - OFFTVC SERVO PWR (2) - OFFMN BUS TIE (2) - OFFcb SPS P1amp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREIf est time to EIltOl5500 omlt fCC andenter the SUPERCIRC CKLIST as early as pos-slb1e Pg ~2~3~ __If est time to EI)Ol5500 anticlpate afCC Enter the ENTRY PREP CKLIST at step 9pg 18

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

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-70-

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NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

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TIME TO 400K FT ALTITUDE-MIN

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-71-

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-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 2: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

PREPARED BY

APPROVED BY

APOLLO ENTRY SUMMARY DOCUMENT

MISSION F (AS-505106LM-4)

-eamp R ~James O R1ppe~ ~----AST Launch and Entry Procedures Sect1on

D1ck1e K WarrenChlef Launch and Entry Procedures Sectlon

P-P C 7ltPaul C KramerChlef F1lght Procedures Branch

James VI Bl10deauAsslstant Chlef F1lght Crew Support Dlvlslon

WarrenChlef

March 17 1969

TABLE OF CONTENTS

41 Typlcal Retroflre and Entry Sequence of Events

56 Earth landing from superclrcular and earth orbitalentrles bull bull bull

51 Entry preparatlons for superclrcular and earth orbltalentr~es bull

20 Llst of Acronyms and Abbrevlatlons

1

2

5

8

10

12

13

15

16

17

17

23

29

35

40

45

47

50

52

55

57

59

bull 64

76

bull

bull

bull bull

bull bull

Earth orbltal entrles bull bull55

54 Normal deorblts for earth orbltal entrles

53 GampN hybrid deorblts for earth orbltal entrles

52 Superclrcular entry

31 Reentry Guidance Events

33 Monltoring wlthout EMS bullbullbullbullbull bullbull

42 Retroflre and Entry Alternatlves

32 Summary of Monltorlng Checks for Entry

Introductlon bullbull

57 Post landing middot

60 TLI Aborts bull

61 TLI preparatlon procedures bull bull

62 10 mlnute TLI abort procedures

63 90 minute TLI abort procedures

70 Entry Pads bull bull bull bull

80 Entry Charts and TLI Charts bull

90 References middot

50 Detalled Entry Procedures bullbullbullbullbullbullbull

40 Earth Orbital Deorblt and Entry Technlques

30 Lunar Return Entry Technlques

10

-1-

10 INTRODUCTION

The purpose of the Entry Summary Document is to provide a singlesource of entry crew procedure ~nformat~on for use ~n fl~ght planshyn~ng crew tra~n~ng and prepar~ng onboard data The techn~ques

conta~ned ~n this document were generally der~ved from other docushymentat~on and are comblned here to serve as a slngle compacttra~n~ng package

In accordance wlth the Fllght Crew Operatlons Dlrectorate CREWPROCEDURES CONTROL PLAN dated March 1968 the prel~minary ESDedltions are dlstrlbuted for review and comment and simulatorval~datlon unt~l 5 months prlor to launch Thereafter flnal ESDprocedures are d~strlbuted and serve as a control ~ocument withchanges sUbJect to approval by the Crew Procedures Control Board

Comments to thls document should be d~rected to the Fl~ght Proshycedures Branch Fllght Crew Support Dlvislon extens~on 3436

-2-

20 LIST OF ACRONYMS AND ABBREVIATIONS

ComputerPilot

ModuleModuleModule

AccumlatorAmphherAntennaAcqu~s~t~on of S~gnal

Backup Bank AngleBeaconBlunt End ForwardCMC Commanded Bank AngleBody Mounted Att~tude GyroBank Reverse BankCab~n

CommanderCoupl~ng Data Un~t

C~rcuit

CommandCommandCommandCutoffCrew Opt~cal AI~gnment S~ght

Commun~cat~ons

Cryogen~c

Command Serv~ce ModuleCounterCaut~on Warn~ng SystemD~g~tal Auto P~lot

D~g~tal Event P~lot

Drag Acceleration at Sk~pout

Constant Drag Control Accelerat~on LevelD~splay and KeyboardDSKY EnterEnv~ronment Control SubsystemEntry InterfaceEntry Monltor SystemElectrlcal Power SubsystemEssent~al

Flight Combust~on Stab~lity MonitorFI~ght D~rector Att~tude Ind~cator

FunctionAccelerat~on 1n Earth Grav~tatlonal Un~ts

Gu~dance and ControlGround Elapsed TlffieGround Elapsed T1me of Ign~t~on

Gyro Display CouplerGlycolG~mbal

Guidance and Nav~gat1on

ACCUMAMPANTAOSBBABCNBEFBETABMAGBRBCBNCDRCDUCKTCMCMCCMPCOCOASCm1MCRYOCSMCTRCWSDAPDETDLDODSKYEECSEIEMSEPSESSFCSMFDAIFUNCGGampCGETGETIGDCGLYGMBLGampN GIN

-3-

Llst of Acronyms and Abbrevlatlons

GNDGPIG-VHAHEHPIMUKA

LIDLEBIMPLOSLVMANMCCMCC-HMESCMSFNMGAMKMNVRMaNMTRMTVCNOPTORIEN02PPGAPGNCSPIPAPLPLSSpassPRIMPRPLNTPSIAPTTPUGSPWRRRI R2 R3RADRCDRRCSROTREFSMMAT

GroundG~bal Posltlon IndlcatorAcceleratlon-VelocltyHelght of ApogeeHellumHeight of PerlgeeInertlal Measurement UnltDrag Acceleratlon necessary to lnltlate

constant drag controlLlft to Drag RatioLower Equlpment BayLunar Module PllotLoss of SlgnalLocal Vertlcal Llft Vector Launch VehlcleManualMldcourse CorrectlonMlssion Control Center - HoustonMaster Event Sequence ControllerManned Space Fllght NetworkMiddle Glmbal AngleMarkManeuverMonltorMotorManual Thrust Vector ControlDSKY NounOptlon OptlCSOrlentatlonOxygenPltch or CMC ProgramPressure Garment AssemblyPrlmary GUldance Navlgatlon and Control SystemPulse Integratlng Pendulous AccelerometerPlanetPortable Llfe Support SystemPosslblePrlmaryPropellantPounds Per Square Inch AbsolutePush to TalkPropellant Utllizatlon and Gaglng SystemPowerRoll or CMC RoutlneReglster 1 2 3RadlatorRecorderReactlon Control SystemAltltude RateReference to Stable Member Matrlx

-4-

L~st of Acronyms and Abbrev~at1ons

RELRET

RHCRNGROURRT

RSIRTGOSASCSSECSECSSELSEPSEQSFT

SM SIMSPASPSSTBYSXPSXTSTSTATBTBDTERMTFTFFTHBWLSTHCTIGTLITIl TLMTRNFR

TVCVVGVIOVLVMY

Rel1efReentry Elapsed TIme (Lunar Return Case) or Retro

Elapsed Time (Earth Orb~tal Case) For lunar returnsRET 1S zero at RRT For earth orb1tal entries RET iszero at the deorb1t burn tIme

Rotat1onal Hand ControllerRangeRout1neReentry Reference T~me (Based on MCC-H predicted time

of EI to nearest second)Roll Stab11~ty IndicatorRange to GoShaft AngleStab1lizat1on and Control SystemSecondarySequent1al Events Control SubsystemSelectSeparationSequentialShaft Angle for SXTS when spacecraft 1S at

ignit10n attitudeServ1ce ModuleCOAS Star P~tch AngleServ1ce Propuls~on SystemStandbyStar X Pos~t~on (COAS)SextantSextant StarTrunnion AngleTalkback D~splay T1me BaseTo Be DeterminedTerm~nate

Ttme FromTtme of FreefallThumbwheelsTranslational Hand ControllerTime of Ignit~on

Translunar Insert10nTelemetryTransferThrust Vector ControlVeloc~ty or DSKY VerbVeloc~ty To Be GatnedInertial Veloc~ty

Sktpout Veloc1tyVeloc~ty MeasuredYaw

-5-

3deg LUNAR REIUBN ENTRY TECHNIQUES

The t~mel~ne for lunar return entries is based on the recommendationsfound ~n reference 1 the s~mulator val~dated procedures ~n reference2 and the mission val~dated procedures listed in the onboard checkshylist for the C Pr~me m~ssion The event times are l~sted ~n reference3

The preparation for lunar return entr~es beg~ns at a conven~ent t~me

about 30 hours before entry ~nterface At th~s t=e MSFN sends up alldata suff~c~ent for reentry also an EMS entry selftest ~s made toassure max~mum confidence ~n the EMS operat~on during entry Thereshyafter var~ous system powerups and checks are ~n~t~ated as l~sted insect~on 51 and deta~led ~n reference 4 Nom~nally the PGNCS ~s upfor the ent~re m~ss~on However ~f ~t ~s not ~t ~s powered up atEI-7 hours ~n preparat~on for the last MCC and entry The last MCCdec~s~on ~s made at about EI-6 hours for the maneuver to be performedat EI-3 hours ~f needed Deta~ls of th~s maneuver are outl~ned ~n

reference 1 After the MCC time P52 ~s again selected and the IMU ~s

real~gned to the REFSMMAT If the IMU dr~ft ~s w~th~n tolerance thesubsequent IMUSCS dr~ft check will determ~ne if the SCS has dr~fted

excess~vely If so the other BMAGs are selected and the IMUSCScheck repeated Th~s check ~s followed by a repeat of the EMS ~V

counter check and accelerometer b~as check at EI-l hour 15 m~nutes

to determ~ne ~f the scale factor and b~as are adequate for entrymon~tor~ng F~nal stowage CM RCS preheat and pyro Cllcu~t and seshyquent~al tests are worked ~nto this t~meframe so that at EI-50 m~nutes

the MSFN w~ll be requested for a go to pyro arm by the crew ~n preparashyt~on for separat~on At 45 m~nutes before EI the CMC update programP27 can be selected to permit update of the landing po~nt locat~on andthe state vector The entry PAD data shown ~n sect~on 70 ~s thenvo~ced to the crew and recorded From th~s data the DET ~s set andstarted the EMS ~nit~al~zed and the RSI al~gned Prior to EI-20ffilnutes the crew w~ll have strapped-~n completed the~r presepara-t~on checkl~st and maneuvered to the entry att~tude At this pointEI-19 m~nutes the CMC entry program Fbl ~s selected by the CMP Ifthere was no entry PAD data because of commun~cat~on loss the veloshyc~ty and range to go from P61 ~s recorded and used ~n the EMS AtEI-15 m~nutes the spacecraft ~s p~tched down and the hor~zon ~s checkedagainst the 317 degree w~ndow scr~be l~ne and the FDAI att~tude Ifthere ~s s~gn~f~cant d~sagreement the PGNCS ~s suspected and the spaceshycraft ~s held on the w~ndow reference In P62 the spacecraft ~s yawed45 0 from th~s att~tude and separated from the SM After separat~on

the CM ~s yawed back ~n plane and the hor~zon check repeated At approxshy~mate1y EI-10 m~nutes the p~tch att~tude is w~th~n 450 of the CMCcommanded att~tude and P63 ~s entered automat~ca11y S~nce the CMCDAP tr~es to hold local p~tch attitude and the CMC ~s not ~n controlthe crew observes the p~tch error needle unpeg and approach zeroabout two m~nutes before 05g t~me Th~s serves as a gono go CMC

-6-

check for entry control If the FDAI pltch error does not decreaseto wlthln + 50 at 005g the PGNCS lS fa lied and the crew flies aconstant g-entry mode wlth EMS ranglng after the VelOClty decreaseto 25500 feet per second If the PGNCS lS acceptable the spaceshycraft control lS placed In CMC and the CMC mode lS placed ln autoshymatlc At 05g the EMS automatlcally starts lf the EMS mode sWltchwas posltloned to automatlc earller ThlS wlll be backed up manually3 seconds after the ground computed 05g tlme recorded on the entryPAD by placlng the EMS mode sWltch In manual lf lt has not startedautomatlcally At PGNCS 005g lndlcatlon the CMC program changesto P64 and from thls pOlnt the entry lS under entry DAP control

The lunar return entry nomlnally lS performed by the PGNCS to lnsurecontrol wlthln the overshoot and g llmlt llnes as well as optlmlzethe landlng point accuracy Although the hlgh speed entry lnvolvesa rapld sequency of events there are several monitorlng tasks forthe crew to determlne lf the automat~c contrails performlng correctly

An entry corr~dor ver~flcation check 1S made by observlng the lnltlalslope of the EMS V-g trace between 1 and 2 gs If the EMS lndlcatesthe need to reverse the LV orlentatlon and the lndependent g meterconflrms the EMS g lndlcatlon the SC lS immedlately orlented as aresult of the EMS ~nd~cat~on

The EMS g lnd~catlon ~s contlnuously checked durlng entry uSlng thelndependent g meter and the PGNCS g ~ndlcatlon as a thlrd voteDeC1Slons durlng the first entry (P64) are critlcal ln terms of bothexceSSlve g llnes and the PGNCS lS not commandlng (and SC respondlng)to correct the sltuatlon the PGNCS lS felled

The PGNCS gono go check for short range targets (1200-1400 n ml) forWhlCh P65 lS not used 1S d1fferent Slnce there are no CMC computedSk1p drag (DL) and skip velocity (VL) values The check uses the EMSscroll to determ1ne 1f the PGNCS lS commandlng the proper roll att1shytude to converge the EMS g level to a predetermlned PAD value (Do) ascomputed by MCC-H For the nom1nal target range of 1300 naut~cal

mlles the crew w1ll monltor the program change from P64 to P67 atapprox~matelyEI + 3 mlnutes For ranges greater than 1400 nauticalmlles the program w1ll transfer to the Upcontrol Program P65 whenVL ~s between 18000 and 25766 feet per second and constant drag hasbrought the CMC pred1cted range to wlthln 25 naut1cal m1les of thetarget range The P65 PGNCS gono go check cons1sts of determln1ng1pound both the DSKY d1splay of sk~pout drag (DL) and Sk1pout veloclty(VL) are w1thln the PAD llmlts In addltlon the EMS scroll lS mon1shytored to determ~ne lf the trace lS approach1ng the DL and VL values

Throughout entry the crew monltors the spacecraft response to the CMCroll commands by observlng the FDAI lndlcatlons If the commands are

-7-

apparently good and In agreement wlth the EMS but the spacecraftresponse is questlonable the crew manually takes over and fIlesthe CMC commands

If the Upcontrol Program P65 was entered the program wlll nomshylnally sWltch to the Flnal Entry Program P67 for target rangesbelow approxlmately 1800 nautlcal miles or to the Ballistlc Proshygram P66 for ranges greater than approxlmately 1800 nautlcalffilles The program transfer crlterla are more preclsely deflnedIn reference 1

If P66 lS entered the spacecraft lS automatlcally rolled to theIlftup heads-down attltude to permlt the horlzon to be vlewedfrom the wlndow durlng the second entry The entry attltude checklS made by comparlng the horlzon wlth a speclfled wlndow mark Ifthe check falls the crew manually malntalns the entry trlffi attltudeuSlng the horizon VleW for reference The EMS lS used for ranglngSlnce the veloclty has now decreased to below 25500 feet per second

The EMS scroll lS contlnuously used to monltor for exceSSlve g conshydltlons durlng the second entry If the EMS V-g trace vlolates theg Ilnes and the PGNCS lS not commandlng (and spacecraft respondlng)to correct the situatlon the PGNCS lS falled and the EMS lS usedfor ranglng after ltS g lndlcatlon has been conflrmed by the lndeshypendent g meter

The entry phase lS essentlally over when the relatlve veloclty ofthe spacecraft decreases to less than 1000 feet per second ThlSlS lndlcated In P67 when RTGO latltude and longltude are dlsplayedSlnce very Ilttle ranglng capablllty exists after thls pOlnt thespacecraft lS orlented elther full Ilft up or down dependlng on RTGOnegatlve or posltlve and the crew prepares for the earth landlngphase

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-13-

40 EARTH ORBITAL DEORBIT AND ENTRY TECHNIQUES

As outl~ned ~n reference 5 a nom~nal PGNCS entry from earth orb~t ~s

based on a preparat~on t~me of 2 hours and 40 m~nutes ~nclud~ng 2n~ght passes Th~s t~me ~ncludes approx~mately 20 minutes before thef~rst n~ght pass after the CMC update and PAD data have been rece2vedTh~s t~e also 2ncludes approx2mately 20 m2nutes after the secondn~ght pass to allow suffic~ent t2me to prepare for retrof2re after theIMU f2ne a12gnment It has been determ2ned coarse a12gnment accuracy~s adequate for retrof~re and entry and undoubtedly other funct20nscould be om2tted depend2ng on the c2rcumstances for the dec2s20n toreenter Descr2bed here2n are the nom2nal earth oro2tal entry proshycedures w2th pert2nent comments on system va12dat20n for real timeacceptance dec~s20ns

After the entry dec~s~on is made the crew transfers the PGNCS fromthe standby to the operate mode and rece~ves a CMe update w~th P27Next the maneuver PAD update ~s v02ced up and the 2n~t~al entry mode~s determ~ned During the ~n~tial n~ght pass the IMU or2entat~on ~s

estab12shed uS2ng P51 star s~ght2ngs to obta2n a REFSMMAT The preshyferred or~entat~on opt20n ~n P52 2S then selected to coarse a12gn theIMU uS2ng the des2red entry REFSMMAT determ2ned by MGG-H The GOO ~s

now al~gned to the IMU 2n preparat~on for an IMUSes dr~ft check Ifthe GOO ~nd~cates the ses dr2ft rate exceeds 10 degrees per hour ~n

any ax~s the check ~s repeated on the other BMAGs to estaol~sh if theGOO or Just the single set 2S unusuable Var20us sytem checks as 12sted2n sect20n 51 are performed as necessary cons2stent w2th the t2me12ned2ctates of the maJor act2v2t2es Included 2n these checks are the EMSself-tests and the dV counter test The latter requ2res the spacecraftbe placed ~n dr2ft2ng fl2ght w~th the funct20n sW2tch 2n the dV pos2t~on

If the counter reg2sters a change of more than 25 feet per second w2th2n100 seconds the scroll and counter are unre12able for mon2tor2ng thedeorb2t burn and entry rang2ng If the EMS self-test fails and t2medoes not allow further analysis a 5555 ERE entry 1S planned as thePGNGS backup entry mode After complet2on of these checks the entryPAD lS prov1ded by MeG-H The crew then selects the external dVprogram P30 and the appropr2ate deorb1t tbrust1ng program p40 or P41Dur2ng th2s per2od wh2ch 2ncludes the f1nal n2ght pass P52 may beselected to ver2fy the IMU a12gnment Since the retro att2tude hasbeen computed so that a w2ndow mark c01nc2des w2th the hor2zon atGETI th2s serves as the conclus2ve check on the PGNCS At 5 m2nutesbefore retrofire the att2tude check 1S made by ver1fY2ng that the 12degree scr~be 12ne ~s w2th2n 3 degrees of the hor2zon If not thePGNeS has fa2led and the ses 2S used for att2tude reference and the

V counter for burn durat~on control S2nce the ses att~tude wasa12gned to the IMU a real~gnment ~s necessary This ~s accompl~shed

by manually maneuver2ng the spacecraft to ma~nta1n the 24 degree wlodowmark on the hor2zon and releas1ng the GOO a12gn button at TIG - 2 m2nutes

-14-

Upon complet~on of the burn the tN res~duals are burned to W~th~n

02 feet per second If the PGNCS ~V counter or est~mated burnduration are ~n d~sagreement ~t must be estab1~shed whether suff~shy

c~ent veloc~ty has been suppl~ed to put the land~ng po~nt in thefootpr~nt The PGNCS data w~ll be used ~f ~t ~s conf~rmed by oneother source if not the ~V counter w~11 be used ~f ~t ~s conf~rmed

by the burn durat~on t~me If add~tional ~V ~s necessary the data~s ava~lable to the crew on an onboard chart found ~n Sect~on 80

Post burn entry preparat~on requ~res EMS ~n~t~al~zation RSI al~gnshy

ment and pre-separat~on funct~ons The crew then selects the ~n~t~al

entry program P61 and records the d~sp1ays as a check aga~nst PADdata Upon complet~on of these checks P62 ~s entered The crewmanually or~ents the spacecraft to the separat~on attitude and yaws450 to ~nsure aga~nst possible CM 8M recontact After separat~on

the spacecraft ~s maneuvered to the reentry tr~m att~tude wh~ch

places the hor~zon on the 3170 w~ndow mark at EI Shortly thereshyafter ~n P62 the entry DAP is act~vated and P63 in~t~ated Dur~ng

th~s t~e MCC-H has computed a postburn update and ~t ~s vo~ced tothe crew ~f d~fferent from preburn values The EMS scroll and rangecounter w~ll be adJusted accord~ngly ~f t~me perm~ts A f~nal PGNCScheck pr~or to 05g may be mon~tored at th~s t~e w~th the CMC modein free and the manual att~tude p~tch ~n acceleration command wh~le

the hor~zon reference ~s held the p~tch error needle w~ll decreaseto zero as EI ~s reached At RET 005g the EMS mode sw~tch ~s

turned to manual the entry 005-g sw~tch and EMS roll sw~tch areturned on and the spacecraft control sw~tched to CMC to beg~n DAPcontrol At the PGNCS 005-g ~ndicatwn the program change fromP63 to P64 ~s mon~tored and the t~e vo~ce recorded At th~s t~me

the EMS range counter check ~s made dur~ng the 10 second per~od

follow~ng EMS 005g Dur~ng th~s per~od the counter should countdown 40 + 10 naut~cal m~les At PGNCS 02-g ~nd~cation the changefrom P64-to P67 ~s monitored and the ~splay may be held by key~ngVERB ~n order to record the init~al downrange error d~splay andcompare ~t to the PAD value The PGNCS has fa~led ~f the two do notagree w~th~n + 100 naut~cal m~les In the event P67 has not appearedwhen both the-g-meter and the scroll ~nd~cate greater than 05g thePGNCS has sim~lar~ly fa~led In e~ther fa~lure the SCS is used foratt~tude reference w~th an EMS entry If the checks agree the crewrema~ns w~th automat~c DAP for the rema~nder of the entry

The entry phase ~s essentially over when the relat~ve velocity ofthe spacecraft decreases to less than 1000 feet per second Th~s

~s ~nd~cated ~n P67 when RTGO lat~tude and long~tude are d~splayed

S~nce very l~ttle rang~ng capab~l~ty exists after th~s pOint thespacecraft is or~ented either full l~ft up or down depending onRTGO negat~ve or pos~t~ve and the crew prepares for the earth land~ng

phase

-15-

41 TYP~cal Retrof~re and Entry Sequence of Events

Dec~s~on to reenter

P27 (CMC update)

Retrof~re PAD update

Entry mode dec~s~on

P51 (IMU or~entat~on determlnatlon) durlng f~rst dark per~od

P52 (IMU coarse allgnment)

EMS checks

Entry PAD update

P30 (external AV)

p40 (SPS thrust)

P52 (IMU f~ne al~gnment) durlng second dark per~od

p40 (SPS thrust)

Ign~t~on att~tude check

Retroflre

P61

P62

CMSM separat~on

P63

Postburn PAD update

Entry attltude check

p64 (beg~n DAP control at O05g)

P67 (PGNCS gono go check at O2g)

42

Retrof~re

and

En

try

Alt

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Sys

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-17-

5 0 DETAILED ENTRY PROCEDURES

In order to comblne slmilar procedures that are common to lunar returnentrles and earth orblt entrles the followlng procedures are dlvldedlnto categorles that allow a mlnlmum of dupllClty ThlS provldes asmaller tralnlng package and more closely resembles the onboard crewcheckllst when comparlson lS necessary

51 Entry Preparatlons for Superclucular and Earth Orbltal Entrles

1~e entry preparatlons are comblned In these procedures andsteps pecullar to elther superclrcular or earth orbltal entrlesare labeled accordlngly The tlme llstlngs In thlS sectlon areappllcable to only superclrcular entries Slnce the earth orbltalentry tlmellne lS a functlon of several varlables as descrlbedIn sectlon 40 and reference 5

-18-51 (Contlnued)

VEHICLE PREPARATION

l-

2

3

4

5

6 -0600h

7 -0535h

8

9

10 -0430h

INITIAL STOWAGE COMPLETED

CMC amp ISS START UP

SCS POWER UP

p51 - IMU ORIENTATION

LOAD DAPV48E 11102 01111 PRO ERO PRO

LAST MCC DECISION

NO COMM - P52 amp NAV SIGHTINGSNOMINAL - P2337 ONBOARD COMPARISON

DON MAE WESTS amp FOOT RESTRAINTS

VHF AM A - SIMPLEX

P 27 (SV REFSMMAT) MNVRamp ENTRY pAD UPDATES

11 -0415h P52 - IMU REALIGN(___) (OPTION 1)

12 P37 (NO COMM ONLY)

13

14

ECS CKS02 SUPPLY REFILLECS Monitor CkEVAP H20 CONT (2) vlvs - AUTOSUIT HEAT EXCH SEC GLY - FLOW

EPS CKS 1 3 4 (5 If reqd)

15 SPS CK (If req d)

16

17

18

RCS CKSSM RCS MOUlt CkCM RCS MOUlt Ck

CampW SYS CK

CMC SELF CK

19

20 -0345h

-03l5h-0300h

21

22

22A

-19-

DSKY COND LT TEST

MIDCOURSE MANEUVERP30 - EXT rVP404l - SPSRCS THRUSTINGMIDCOURSE (17) BURN

NO COMM NAV SIGHTINGS

ffiVR TO ENTRY ATT (Superc1rc only)V62E

V49E

22B F 06 22 DESIRED FINAL GMBL ANGLESLOAD ENTRY ATT PAD ANGLESPRO

22C F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) SC CONT - CMC

BMAG MODE (3) - RATE 2CMC MODE - AUTO

PRO(~N) SC CONT - SCS

MNVR to 22E

22D 06 18 AUTO MNVR TO FDAI RPY ANGLES

22E F 50 18 REQUEST TRIM(TRIM) Go to 22C(BYPASS) ENTR

23 -200hr BORESIGHT amp SXT STAR CHECKOPT MODE - CMCOPT ZERO - OFF

V41 N91E

F 21 92 SHAFT TRUNLoad SXTS angles

41 OPTICS DRIVE

CHECK SXT STAROPT ZERO - ZERO

CHECK BORESIGHT STAR (If ava11)

24 -0135h

25(___)

26

27 -0115h

-20-

P52 - lMU REALIGNRecord gyro torqu~ng anglesRp~----

YIf-7gt-Lno--re-c-ycle PS2If conflrmed use SCS for EMS entry

GDC ALIGNIf drlft gtLOohr change ratesource

FINAL STOWAGEOPTICS (except for hybrid)ORDEALGLY TO RAD SEC - BYPASS (verlfy)CooL pnl lnstalledY-Y struts (2) extendedStow Data Box R-12

EMS CHECKEMS FUNC - OFFcb EMS (2) - closeEMS MODE - STBYEMS FUNC - EMS TEST 1 (walt 5 sec)EMS MODE - NORMAL (walt 10 sec)

Check ind lts - offRANGE lnd - 00Slew halr1ine over notch

In self-test patternEMS FUNC - EMS TEST 2 (walt 10 sec)

05G It - on (all others out)EMS FUNC - EMS TEST 3

05G It - onRSI Lower It - on (10 sec Qater)Set RANGE counter to 58 nm+OO

EMS FUNC - EMS TEST 405G It - on (all others out)G-V trace w~thin pattern to lwr rt

corner 9GRANGE lnd counts down to 0+02

EMS FUNC - EMS TEST 505G It - onRSI upper lt - on (10 sec later)RANGE md - 00SCrlbe traces vertlcal llne 9g to

022+01ALIGN SCROLL TO ENTRY PATTERN (on

37K ft sec hne)EMS FUNC - RNG SET

G-V scroll assy traces vert llne022g to 0+01

EMS MODE - STBY

28

29

30 -OllOh

-21-

~V TEST (Deorb~t only)EMS FUNC - ~V SETVHF RNGSET ~V ~nd to 15868 fpsEMS MODE - NORMALEMS FUNC - ~V TEST

SPS THRUST LT - onoff (10 sec)~V ~nd stops at -01 to -415

EMS MODE - STBY

PRIMARY WATER EVAP ACTIVATIONGLY EVAP H20 FLOW - AUTOGLY EVAP STH PRESS - AUTOPRI ECS GLY PUMP - ACI

CM RCS PREHEATNote If sys test mtr 5cd6abcd

all read 39 vdc (28degF) or moreom~t preheat

cb RCS LOGIC (2) - closeCM RCS LOGIC - ONUP T1M CM - BLOCK (ver~fy)

cb CM RCS HTRS (2) - closeCM RCS HTRS - ON (LMP Conf~rm)

(20 mlU or III lowest rdg lS39 vdc) (Moultor Maufpress for press drop)

31 (___) FINAL GDC DRIFT CK (If req I d)If drlft gtlOohr Suspect GDC Do not

use RSI amp FDAI 2

32 -OO5Om

33

34

35

TERM CM RCS PREHEATUP TLM CM - BLOCK (venfy)CM RCS HTRS - OFFCM RCS LOGIC - OFF

SYSTEMS TEST PANEL CONFIGURATIONSYS TEST METER - 4BRNDZ XPNDR - OPERATECM RCS HTRS - OFFWASTE H20 DUMP - OFFURINE DUMP - OFF

LEB LIGHTING - OFF

SEC WATER EVAP ACTIVATIONGLY To RAD SEC vlv - BYPASSSEC COOL EVAP - EVAPSEC COOL PUMP - AC2

36

37

38 -OO45m

-22-

PYRO BATT CKcb PYRO A SEQ A - close (ver~fy)

cb PRYO B SEQ B - close (verify)DC IND - PYRO BAT A(B)

~If PYRO BAT A(B) lt 35 vdc cb PYRO A(B) seq A(B) - open~

PYRO A(B)BAT BUS A(B)TO PYRO~MN BUS TIE - close

cb MNA BAT C - closecb MNB BAT C - closeDC IND - MNBPNL 8 - All cbs closed except

PL VENT - open (ver~fy)

FLOAT BAG (3) - open (ver~fy)

DOCKING PROBE (2) - open (verlfy)EDS BAT (3) - open (ver~fy)

CM ReS HTRS (2) - open

CM RCS ACTIVATIONcb SECS ARM (2) - close (verlfy)cb SECS LOGIC (2) - close (verlfy)SECS LOGIC (2) - ONMSFN conflrm GO for PYRO ARM(~f poss)SECS PYRO ARM (2) - ARMCM RCS PRPLNT 1amp2 - ONCM RCS PRESS - ONRCS Ind sw - eMl then 2

He PRESS 3700-4400 pSlaMANF PRESS 287-302 pSla

SECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFF

P27 amp ENTRY PAD UPDATEGo To Entry Checkllst

Superclrc - pg ~2~3 _Hybnd - pg -----2~9L-__Normal Deorblt - pg __3L5L- _

-23-

52 SUPERCIRCULAR ENTRY

1 SET DET (up to ET)

2

3

4

5

3000(-30-00)

EMS INITIALIZATIONSET RNG TO PAD DATA RNGEMS FUNC - Vo SETSlew Scroll to Pad Data VIOEMS FUNC - ENTRY

RS I ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on (up)GDC ALIGN PB - PUSH amp HOLDYAW Tw - Pos~t~on RSI thru

45deg amp back to LIFT UPGDC ALIGN PB - ReleaseEMS ROLL - OFFA1~gn CDC to lMU

CM RCS RING A CKRCS TRNFR - CMcb CM RCS LOGIC MNB - openAUTO RCS SEL MNB (6) - OFFSC CONT - SCSTest R~ng A ThrustersSC CONT - CMCRCS TRNFR - SMAUTO RCS SEL (12) - MNAMNB

(hftoff conflg)cb CM RCS LOGIC MNB - close

OPTICS PWR - OFFCMP to COUCH

MN BUS TIE (2) - ONTAPE RCDR - REWIND

6 35middot0Om(-25middot 00)

-24-

SEPARATION CK LISTTVC SERVO PWR 1 - AClMNAcb ELS (2) - close (ver1fy)PRIM GLY TO RAn - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY vlv - OFFCAB PRESS REL vlv (2) - NORMGMBL MTRS (4) - STARTABORT SYS PRPLNT - RCS CMD (venfy)SM RCS PRIM PRPLNT (4) - ONVHF 11M (AampB) - OFFHI GAIN ANT PWR - OFFFC PUMPS (3) - OFFVer1fy s1ugle SU1t compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - 10101cb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2) - opencb HTRS OVLD (2) - openPOT H20 RTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANSEC COOL EVAP - RESETSEC COOL PUMP - off (etr)

MtiVR TO CMSM SEP P R ATTSC CONT - SCSCMC MODE - FREEMNVR TO PAD ATTR (0deg)PY----W)

-25-

SUPERCIRCULAR ENTRY (Cont~nued)

1

4100m(-1900)

P61 - ENTRY PREP

V37E 61E

k 05 09 01427 - ROLL REVERSED 05 09 01426 - IMU UNSAT ~

2 F 06 61 IMPACT LAT LONG HDS UPDN (+-)PRO (010

fps +00001)

3 F 06 60 GMAXVPREDGAMMA EIRecord

GMAXV400K----

GAMMA EI _PRO

(01deg fpsOldeg)

4 F 06 63 RTOGO (lnm) PAD _VIO (fps) PAD _TFE(m~n-sec)

Compare w~th ~M~SFN==C~f~o-r~P~GNS GONO GOIf NO COMM Set RTOGO amp VIO In EMS

amp lnltla11ze(ACCEPT) PRO(RECALC) V32E To 4

5 F 50 25

4300m

(-1700)

45 oOm(-1500)

500Om(-1000)

6 F 06 61

-26-

P62 - CMSM SEP amp PRE-ENTRY MNVRCAUTION Call No EXT Verbs In P62

00041 REQUEST CMSM SEPSC CONT - SCSFREE

COMPARE PITCH ATT WITH PAD DATA ---0=-

(W~thLU 5deg)YAW - 45deg OUT-OF-PLANE (LEFT)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTIRATE 2MN BUS TIE (2) - ON (ver~fy)

PRIM GLY TO RAD - BYPASS (verlfy)CM RCS LOGIC - ON (venfy)SECS LOGIC (2) - on (up)SECS PYRO ARM - ARMCMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 ps~a

CM RCS LOGIC - OFFSECS PYRO ARM (2) - SAFEMonltor VMAB

If lt25 vdc go to EMERGPOWERDOWN pg E6-l

AUTO RCS SEL AC ROLL (4) - OFFAUTO RCS SEL CM 2(6)-OFFAUTO RCS SEL CM 1(6)-MNAYAW back to 0degPITCH TO HORIZ TRACK ATT

ROLL - 0deg (LIFT UP)PITCH - 400K Horiz Mark (317deg)YAW - 0deg

ATT DB - MAXMAN ATT PITCH - ACCEL CMDEMS DATA - Ver~fy

EMS FliNC - ENTRY (ver~fy)

EMS MODE - NORMALcb SPS PampY (4) - openMAINT HORIZ TRK

PRO (Act ENTRY DAP)

IMPACT LATLONGHDSDN (01deg01deg-00001)PRO

7 POSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axis beyond 45deg of Vel vector)

8 06 64

58middot00m(-0200)

9

05G tlme(+0 )

(--=---)

06 68

-27-

P63 - ENTRY INIT

GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PIJR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRmDHORIZ CKPltch error needle goes toward

zero approachlng OSG tlmeMAN ATT (PITCH) - RATE CMD

If CMC lS GOBMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS I

FLY BETA If CMC NO GO ilt

1 SC CaNT - SCS I

FLY EMS k

p64 - ENTRY POST 05G

RTOGO AT 05G AGREES HITH EMS-venfyHORIZ CK05G Lt - ON (EMS START)

No EMS START wlthln 3 sec ~ EMS MODE - BACKUP VHF RNG c

05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds Llft DN

NNVR Llft DNEMS GONO GO

G-V Plot wlthln IlmltsRng ctr dwn 60plusmn7 durlng 10 sec

perlodMonltor G-meter for

convergence wlth pad data (Do)(Vlt27K fps) Go to 13

-28-

P65 - ENTRY - UP CONT (Vgt27K fps)

10 F 16 69 BETA (01middot) _DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT lt~ SC CONT - SCS FLY EMS

PRO

11 06 68 BETAVIHDOT (OIdegfpsfps)(VltV1+500 fps amp RnOT Neg) Go To 13

P66 - ENTRY - BALLISTIC (D(DL)

12 06 22 DESIRED GMBL ANGLES RPYMoultor horlz +12middot of 317middot mark

P67 - ENTRY - FINAL PHASE (02G)

13 06 66 BETACRSRNG ERRDNRNG ERR(010 1um 1um)

KEY VERBRecord DNRNG ERR _KEY RLSEMoultor l~ft vector ou RSI amp FDAI

16 67 RTOGOLATLONG (Vrel=1000fps)(lumOldegOldeg)

SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOWNMonitor a1t~meter

Go To EARTHLANDING pg ---4L5 _

-29-

53 GampN HYBRID DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL tV1 V37E 30E

2 F 06 33 GETI(ACCEPT) PRO (hrm~n Olsec)(REJECT) LOAD DESIRED GETI

3 F 06 81 tVXYZ (LV) (lfps)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

4 F 06 42 HAHPtV (lnm lfps)Record tV

(ACCEPT) PRO(REJECT) Reselect P30 or P27 Load new paramo

5 F 16 45 MTFIMGA (marksm~n-secOlO)

MGA -00002 ~f k

k lMU not al~gned

SET DETPRO

6

7

8

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (Pull)PLSS 02 vlv - FILL02 8M SUPPLY vlv - OFFCAB PRESS REL vlv (2) - NORMcb ELS (2) - closecb SECS ARM (2) - closecb SECS LOGIC (2) - close (ver~fy)

AUTO RCS SEL CM (12) - MNA or ~ffiB

(hftoff conhg)ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM (AampB) - OFF

CMP to Couch

9

10

11

-30-

MNVR TO PAD BURN ATTLOAD DAPBMAG MODE (3) - RATE 2SC CONT - CMCAUTOATT DB - MINMAN ATT (3) - RATE CMD

v62E

v49E

12 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLES

PRO

13 F 50 18 REQ MNVR TO FDAI RPY ANGLES (01deg)(AUTO) PRO(MAN) SC CONT - SCS

BMAG MODE (3) - RATE 2MNVR To 15

14 06 18 AUTO MNVR TO FDAI RPY ANGLES (01deg)

15 F 50 18 REQ TRIM TO FDAI RPY ANGLES (01deg)(TRIM) Go to 13(ByPASS) ENTR

16

17

CHECK BORESIGHT amp SKT STARSOPT MODE - CMCOPT ZERO - OFF

v41 N91E

18 F 21 92 SHAFTTRUN (01deg 001deg)Load SXTS angles

19 41 OPTICS DRIVECheck SKT STAR

OPT ZERO - ZEROCheck BORESIGHT STAR (~f ava~l)

20 V25 N17E (01deg)Load Pad Data GMBL Angles

for CM BURN ATTATT SETtw - SET

to PAD DATA GMBL ANGLESfor CM BURN ATT

21

22

-31-

PHR REDUCTIONHGA PHR - OFFFC PUMPS (3) - OFFVerify s~ngle su~t compr oper loads

balancedFC 2 MN AampB - OFFS BD PiR AMP - LOWcb ECS RAD CONTHTR (2) - opencb HASTE H20URINE DUMP HTRS(2)- opencb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANMN BUS TIE (2) - ONTVC SERVO PHR 1 - AC1MNAGMBL MTR (4) - START

p41 - RCS THRUSTINGV37E 41E

23 F 50 18 REQ MNVR TO LCL HORIZ (HDS ON)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CMCAUTOPRO To 24

(gtfANDAP) BMAG MODE (3) - RATE 2SC CONT - CMCHOLD

V62EMNVR To 25

24 06 18 AUTO MNVR TO FDAI RPY

25 F 50 18 REQ TRIM TO LCL HORIZ (01deg)ALIGN SC ROLL

(AUTO TRIM) PRO To 24(BYPASS) ATT DB - MIN

RATE - LOHMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTlRATE 2

ENTR

550Om26 06 85

59middot2527

-32-

VGXYZ (1fps)RECHECK BORESIGHT STARTRANS CONIR PWR - on (up)EMS MODE - STBY (ver~fy)

EMS FliNC - bV SETVHF RNGSET (IV for SM BURN _EMS FliNC - bVS BD ANT - OMNI CSECS LOGIC (2) - ONMSFN conhrm Go for PYRO ARMSECS PYRO ARM (2) - ARMCM RCS LOGIC - ON (ver~fy)

DSKY BLANKS

593028 16 85 VG XYZ (AVE G ON) (lfps)

RHCs amp THC - ARMEDLIMIT CYCLE - OFFTAPE RCDR - CMD RESETHBREMS MODE - NORMAL

000029 F 16 85 REQ NULL VG XYZ (lfps)

BURN EMS bV CTR TO ZERORESET DET amp COUNT UP

If SM ONLY burn go to step 32THC - LOCKEDSC CaNT - SCSFREERATE - HIGHPRIM GLY To RAD - BYPASS (ver~fy)

MN BUS TIE (2) - ON (ver~fy)

CMSM SEP (2) - on (up)CSMLM FNL SEP (2) - on (up) (verify)CampW MODE - CMRCS TRNFR - CMCM RCS LOGIC - OFF

Momtor VM ABIf lt25 vdc go to EMERGPOWER DOWN Pg E6-l

V63E

If CMC NO GO FDAI SOURCE - ATT FDAI SEL - 1 or 2 ATT SET - GDC

SET

-33-

~Uili ATT PITCH - ACCEL CMDFDAI SCALE - 55MNVR TO CM BURN ATT (NULL ERR NEEDLES)

R 0degPY --00--

30

31

CM RCS BURNRHC III-ContJnuous PJtch DownRHC HZ-Module PJtch to null needlesBURN VGZ TO ZERO

If only 1 RHC Pulse + P=5deg from retro att MaJnta~n rates lt3degsec

BURN COMPLETION ATllV CTR= or DET= _

V8ZE

32 F 16 44 HAHPTFF (1nmffiJn-sec)Check HP-

If gt Pad data contJnue burnuntJ1 lt Pad

PRO

33 F 16 85 VGXYZ (Ups)Read VG resJduals to MSFN

(HYBRID) PRO to 34(SM ONLY BURN)

PROF 37 ODE

EI-1500 V37E 47EF 16 83 twx Y Z (Ups)

SC CONT - SCSFREEMAN ATT (PITCH) - RATE CMDRATE - HIGHPRIM GLY To RAD - BYPASS (verJfy)MN BUS TIE (2) - ON (verJfy)CMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verJfy)Campl MODE - CMRCS TRNFR - CMCM ReS LOGIC - OFFSECS PYRO ~I (2) - SAFE

-34-

PROMonitor VMAB

If lt25 vdc go to EMERGPOWER DOWN

34 F 37 OOEPCM BIT RATE - LOWATT DB - MAXEMS MODE - STBYEMS FUNC - OFF

Go To EARTH ORBIT ENTRY pg _--40-__

-36-

8 SPS THRUSTING PREPCYCLE CRYO FANSSPS GAGING - ACI (ver~fy)

PUG MODE - NORM (venfy)BMAG MODE (3) - RATE 2tv CG - CSMCMC MODE - FREEAUTO RCS SEL (16) - MNA or HNB

(hftoff conbg)SC CONT - CMCAUTO

9 MNVR TO PAD BURN ATTV62E

10 V49E

11 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLESPRO

12 F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) PRO(HAN) SC CONT - ses

MNVR to 14

06 18 AUTO MNVR TO FDAI RPY ANGLES13

14 F 50 18 REO TRIH TO FDAI RPY ANGLES(TRIM) Go to 12(BYPASS) ENTR

15 BORESIGHT STAR CHECK

16 V37E 40EOPT PWR - OFF

17 F 50 18 REQUEST MNVR TO FDAI RPY ANGLES (01deg)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CHCAUTOPRO to 18

(MANDAP) BMAG HODE (3) - RATE 2SC CONT - CMCHOLDMNVR to 19

(HANseS) se eONT - sesMNVR to 19

-35-

54 NORMAL DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL ~V

1 V37E 30E

2 F 06 33 GETI (hrm~nOlsec)

(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

3 F 06 81 ~VXYZ (LV)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

( lfps)

4 F 06 42 HAHP~V (1nmlfps)Record W

(ACCEPT) PRO -----(REJECT) Rese1ect P30 or P27 Load new pa~am

5 F 16 45 MTFIMGA (marksmln-secOldeg)MGA -00002 If ~ lMU not a1~gned

SET DETPRO

6

7

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY v1v - OFFCAB PRESS REL v1v (2) - NORMcb ELS (2) - close (verify)cb SECS ARM (2) - close (ver~fy)

cb SECS LOGIC (2) - close (verlfy)AUTO RCS SEL CM (12) - ~mA or MNB

(l~ftoff conf~g)

ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM AampB - off (ctr)

18

-37-

06 18 AUTO MNVR TO FDAI RPY ANGLES (01 0)

19 l 50 18 REOUEST TRIM MNVR TOALIGN SIC ROLLGDC ALIGN

FDAI RPY ANGLES(010

)

+54-00m(-06-00)

TIG-5mJn

5500m(-0500)

TVC CHECK amp PREPcb STAB CONT SYS (all) - closecb SPS (12) - closeATT DB - MINRATE - LOl~

LIMIT CYCLE - ONMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE 2ROT CONTR PWR DIRECT (2) - OFFSCS TVC (2) - RATE CMD

If SCS SCS TVC (2) - AUTO SC CONT - SCS ~

TVC GMBL DRIVE PampY - AUTOMN BUS TIE (2) - ONTVC SERVO PWR 1 - AC1MNA

2 - AC2MNBTRANS CONTR PWR - ONROT CONTR PWR NORMAL 2 - ACRHC 2 - ARMED

HORIZ CHK - HorJz on 12deg wJndmlmark (LJffiJt +3 0 PNGCS GONO GO)

If NO GO set tw 180 0 180deg0 0

Track horJz wJth 24deg wJndow markAt TIG-2 mJn Ahgn GDC

PRIMARY TVC CHECKGMBL MOT P1-Y1 -STARTON(LMP confJrm)

If SCS verJfy Thumbwheel TrJmTHC - CWVenfy NO MTVC

SEC TVC CHECKGHBL MOT P2-Y2 -STARTON(LMP confJrm)SET GPI TRIHVenfy MTVCTHC NEUTRALGPI returns to 00 (CMC) or trJm (SCS)ROT CONT Pl~ NORM 2 - ACDC

(TRIM) Go to step 17(BYPASS) BMAG MODE(3) - ATTIRATE2 (ver1fy)

ENTR

-38-

20 F SO 25 00204 GMBL TEST OPTION(ACCEPT) SC CONT - GMC (ver~fy)

PROMonitor GPI Response

0020-2000020-200Tr~m

TEST FAIL SC CONT - SCS SCS TVC (2) - AUTO

(REJECT) ENTR

21 06 40 TFIVG~VM (m~n-sec1fps)

PROG ALM - TIG s1~pped

V5N9E 01703

KEY RLSE To 21 ROT CONTR PWR DIRECT (2) - MNABSPS He v1vs (2) - AUTO (ver~fy)

LIMIT CYCLE - OFFFDAI SCALE - SOIScb SPS P2Y2 - open (for cr~t burn)

5800(-02 00)

5925(-0035)

59middot 30(-0030)

06 40

59XX(-OOXX)

AV THRUST A(B) - NORMALTHC - ARMEDRlIC (2) - ARMEDTAPE RCDR - GID RESETHBR

DSKY BLANKS

(AVE G ON)EMS MODE - NORMAL

TFIVG~VM (m~n-seclfps)

CHECK PIPA BIAS lt2fps for 5 sec

ULLAGE AS REQ

IF NO ULLAGE DIR ULLAGE PB - PUSH~

CONTROL ATT WRlIC MONITOR AVM (R3) COUNTING UP

5955(-0005)

F 99 40 ENG ON ENABLE REQUEST(AUTO IGN) PRO AT TFI gt0 sec(BYPASS IGN) ENTR to 24

22 0000 IGN

-39-

If SCS - THRUST ON PB - PUSH

06 40 TFCVG~VM (m~n-seclfpslfps)

~F 97 40 SPS Thrust fall ~

~(RESTART) PRO To IGN (RECYCLE) ENTR To TIG-05 sec

SPS THRUST LITE - ONMONITOR THRUSTING

Pc 95-105 pSlaEMS COUNTING DOWNSPS IN3 v1vs (4) - OPENSPS He v1vs tb (2) - graySPS FUELOXID PRESS - 175-195 pSlaPUGS - BALANCED

PROG ALARM V5N9E 01407 VG INCTHC - CW FLY MTVC

ECOEMER SPS CUTOFF J

AV THRUST (2) - OFF

23 F 16 40 TFC(STATIC)VG~VM (mln-seclfps)~V THRUST AB - OFF

SPS IN3 v1vs (4) - CLOSEDSPS He tb (2) - bp

cb SPS P2Y2 - closed (verlfy)TVC SERVO PHR - AC1MNA (venfy)TVC SERVO PWR 2 - OFF

PRO

24 F 16 85 VG XYZ(CM) CUps)NULL RESIDUALSRECORD ~V CTR amp RESIDUALS I1VCEMS FUNC - OFF VGXEMS MODE - STBY VGYBMAG MODE (3) - RATE 2ATT DB - MAX VGZTRANS CONT PHR - OFF

PRO

25 F 37 V82E

26 F 16 44 HAHPTFF (lnmm~n-sec)

R3-59B59 HP gt494 nmPRO

27 F 37 OOE

-40-

55 EARTH ORBIT ENTRY

1 Venfy CMSMR __

P_shyY_-

SEP ATT(180deg)

(0deg )

2

3

4

EMS INITIALIZATIONEMS FUNC - RNG SETSET RNG TO PAD DATA RNGEMS FUNC - VA SETSlew scroll to pad data VIOEMS FUNC - ENTRY

RSI ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on(up)GDC ALIGN PB - PUSH amp HOLDYAW tw - Pos1tion RSI thru 45deg amp

back to LIFl UPGDC ALIGN PB - RELEASEEMS ROLL - OFFAl1gn GDC to lMU

PWR REDUCT (Norm Deorb Only)HGA PWR - OFFFC PUMPS (3) - OFFVer1fy s1ngle suit compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - Lowcb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2)-openlOb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MAN

-41-

P61 - ENTRY PREP

5 V37E 61E05 09 01427 - ROLL REVERSED05 09 01426 - IMU UNSAT

6 F 06 61 IMPACT LAT LONG liDS UPDN (+-)(01 0

010

+00001)

PRO

PAD VALUESLATLON==G------liDS UP DN _

7 F 06 60 GMAXV400KGAMMA EIRecord

GMAXV400K----GAMMA EI _

PRO

8 F 06 63 RTOGO (1nm) PAD _VIa (fps) PADTFE (mln-sec) ----Compare wlth MSFN for PGNS GONO GONO COMM SET RTOGO amp VIO IN EMS amp

INITIALIZE(ACCEPT) PRO(RECALC) V32E to 8

-42-

P62 - CMSM SEP amp PRE-ENTRY MNVR

9 F 50 25 00041 REQUEST CMSM SEPSC CONT - SCSFREEYAW - 45deg out-of-plane (left for RCS

nght for SPS)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE2PRIM GLY to RAD - BYPASS (verlfy)SECS LOGIC (2) - on (up)MSFN conflrm GO for PYRO ARMSECS PYRO ARM - ARMMN BUS TIE (2) - ON (verlfy)CMSM SEF (2) - ONCSMLM FNl SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 pSlaCM RCS LOGIC - OFFSECS PYRO ARM - SAFEMonltor VMAB

If lt25vdc go to EMERG POWERDOWN Pg E6-1AUTO RCS SEL AlC ROLL (4) - OFFAUTO RCS SEL CM 2(6) - OFFAUTO RCS SEL CM 1(6) - MNA or MNBYAW back to 00

PITCH TO ENTRY ATTROLL 0deg (LIFT UP)PITCH - HORIZ on 317deg MARK (400K)YAW 00

ATT DB - MAXMAN ATT (PITCH) - ACCEL CMDEMS DATA - VerifyEMS FUNC - ENTRY (verlfy)EMS MODE - NORMALMAINTAIN HORIZ TRK

PRO (Act ENTRY DAP)

10 F 06 61 IMPACT LAT LONG HDSDN(010 010 -00001)

PRO

11 FOSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axlS beyond 45deg of Vel vector)

-43-

P63 - ENTRY INIT

12 06 64 GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PWR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRHORIZ CKP~tch error needle goes toward

zero approach~ng 05G t~me

MAN ATT (PITCH) - RATE CMDIf CMC ~s GO

BMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS FLY BETA If CMC NO GO ~

SC CONT - SCS~

FLY EMS RCS Deorh Roll HDS UPTRACK HORIZ w~th 29deg w~ndow mk

P64 - ENTRY POST 05G

13

05G t=elt+0___)

06 68

RTOGO AT 05G AGREES WITH EMS - venfyHORIZ CK05E Lt - on (EMS start)

No EMS start w~th~n 3 secsEMS MODE - BACKUP VHF RNG 05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds L~ft DN

NNVR L~ft DNEMS GONO GO

G-V Plot w~th~n llm~ts

Rng ctr dwn 60 + 7 durlng 10 sec per~od

Mon~tor G-meter forconvergence wlth pad data (Do)

(Vlt27K fps) Go To 17

-44-

P65 - ENTRY - UP CONT (Vgt27K fps)

14 F 16 69 BETA (01deg)DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT~

SC CONT - SCS FLY EMS

PRO

15 06 68 BElA VI HOOT (01deg fpsfps)(VltVL +500 fps amp RDOT Neg) Go To 17

p66 - ENTRY - BALLISTIC (DltDL)

16 06 22 DESIRED GMBL ANGLES RPY (01deg)Mon~tor hor~z +12deg of 317deg mark

P67 - ENTRY - FINAL PHASE (02G)

17 0666 BETACRSRNG ERRDNRNG ERR (Oldeglnmlnm)KEY VERBRecord DNRNG ERR _KEY RLSEL~m~t +100nm from PAD DRE

Mon~tor l~ft vector on RSI amp FDAIF 16 67 RTOGOLATLONG (Vre1=1000fps)

(lnm 010 01deg)SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOlfflMon~tor altimeter

Go To EARTHLANDING pg _I4L5__

-45-

56 EARTHLANDING

90K STEAM PRESS - PEGGED50K CABIN PRESS REL vIv (2) - BOOSTENTRY

SECS PYRO ARM (2) - ARM

40K(90K + 63s)

CM UNSTABLE RCS CMD - OFF ~ 40K APEX COVER JETT PG-PUSH DROGUE DEPLOY PG - PUSH (2 secafter apex cover Jett)

30K ELS LOGIC - ON (up)ELS - AUTO

24K RCS hsable (auto)(90K+92s) RCS CMD - OFF

Apex cover Jett (auto)APEX COVER JETT PB - PUSH

(WAIT 2 SECS)Drogue parachutes deployed (auto)

DROGUE DEPLOY PB - PUSH~

If Drogues FallELS - ~ ~Stablllze CM 5K MAIN DPLY PB - PUSHELS - AUTO

235K Cabln Pressure lncreaslng (Drogues + 50s)If not lncreaSlng by 17K CABIN PRESS REL vlv (RR) - DUMP

-46-

10K Maln parachutes deployedMAIN DEPLOY PB - PUSH (wlthln 1 sec)VHF ANT - RECYVHF AMA - SIMPLEXVHF BCN - ONCABIN PRESS REL v1v (2) - CLOSEDIRECT 02 vlv - OPENCM RCS LOGIC - on (up)CM PRPLNT - DUMP (burn audlb1e)Monltor CM ReS 1amp2 for He press decrease

NO BURN or PRESS DECREASE USE BOTH RHCs DO NOT FIRE PITCH JETS

CM PRPLNT-PURGE (to zero He press)CM RCS He DUMP PB - PUSH RHC (2) - 30 sees NO PITCH k

STRUT LOCKS (2) - UNLOCK

cb FLT amp PL BAT BUS ABampBAT C (3) - closecb FLT amp PLT MNA amp B (2) - opencb ECS RAD HTR OVLD (2) - opencb SPS PampY (4) - open

3K CABIN PRESS REL v1v (RH) - DUMP (after purgecompleted)

FLOOD Lts - POST LDGCM RCS PRPLNT (2) - OFFROT CONTR PWR DIRECT (2) - OFF

800 CAB PRESS RELF vlv - CLOSE (latch off)MN BUS TIE (2) - OFF

AFTER LANDINGcb MAIN REL PYRO (2) - closeMAIN RELEASE - on(up)

Go to POSTLANDING pg _47L-__

I

2

3

-47-

57 POSTLANDING

STABILIZATION VENTILATION COMMUNICATIONS

DIRECT 02 vlv - CLOSE

Stablllzation after landlngELS - AUTO (verlfy)cb MAIN REL PYRO (2) - close (venfy)MAIN RELEASE - on (up) (verlfy)S~CS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb BAT RLY BUS (2) - open

No contact w1th recovery forcesVHF AM AampB - off (ctr) ~

VHF AM Rev ONLY - A cb PL VENT - closecb FLOAT BAG (3) - closecb UPRIGHT SYS COMPRESS (2) - closeIf Stable II

FLOAT BAG(3)-FILL t1ll 2 m1n afterupr1ght then - OFF

VHF AM AlB amp BCN - OFF whlle lnvertedIf Stable I

After 10 M1n Coollng Per1odFLOAT BAG (3) - FILL 7 mln then OFF

Post Stab1lizat1on And Ventllat10nPL BCN LT - BCN LT LOWPL VENT vlv - UNLOCK (Pull)Remove PL VENT Exh CoverPL VENT - HIGH or LOWPL DYE MARKER - ON (swlmmer comm)Release foots traps and_restralntscb MNA BAT BUS A amp BAT C (2) - opencb MNB BAT BUS B amp BAT C (2) - opencb FLT amp PL BAT C - opencb PYRO A SEQ A - opencb PYRO B SEQ B - open

EACH HR - CHECK DC VOLTSgt 275 V If Notmiddot cb FLT amp PL-BAT BUS AampB (2) -open cb FLT amp PL BAT C (1) - open GO TO LOW POWER CHECKLIST

Unstow and lnstall PLV DISTRIB DUCTDeploy grappllng hook and 11ne 1f req

4

-48-

Post Landing Communlcatl0nsVHF ANT-RECY (venfy)VHF BCN - ON (verlfy)

If no contact ~lth recovery forcesperform VHF BEACON Check

MONITOR VHF BEACON transmlSSlonnth VHF AM B Rcvr andor Su)vlval

TransceiverkVHF Beacon not operatlng ~connect Surv~val TranscelVer to antcable behlnd VHF ant access pnland place radio ln BCN mode

LOW POHER CHECKLISTVHF BCN - OFFVHF AM (3) - RCVFLOOD Lts - OFFVHF AM AampB - off (ctr)VHF AM RCV ONLY - A (venfy)COUCH LIGHTS - OFFPOSTLANDING VENT SYS mlnlmlze useSURV RADIO - plug mto VHF BCN ANT cableconn behind VHF ant acess pnl amp turn radloon l-n BCN mode

EGRESS PROCEDURES

CMPCDRLMPCDR

CMPCDRCMP

LMPLl1PCDR

STABLE IDlsconnect Umblll-calsNeck darn onCenter couch - 270 0 positionArmrests stowedConnect raft to SIC l-f desl-red wlth

green lanyardConnect raft ~hl-te lanyards to SUltS amp

lnflate water wlngs when eXltl-ngHATCH PISTON PRESS vlv - PRESS (Outbd)Slde Hatch openedPL VENT - OFFcb Pnl 250 (all) - openEgress with 11feraftPut hardware klt outEgress

or CDIPALL

CMF

CDRCMF

CDR

LMF

CMFCMP LMFCMP

UlP

CDR

-49-

STABLE IIcb CREW STA AUDIO (3) - openD~sconnect umb~1~ca1s

Release foots trapsRelease restra~nt harnessCouch seat pans (3) - 170 0 pos1t10nArm rests stowedSurv1va1 k~ts removed from stowageConnect life raft ma~n1~ne to CDR or SicConnect f~rst wh~te lanyard from

11fe raft to suitConnect th~rd wh~te lanyard from

l~fe raft to SU1tConnect rucksacks together to yellow

lanyard on raft bagPRESSURE EQUALIZATION vlv - OPENRemove and stow fwd hatchEX1t feet f1rst w1th rucksacks when clear

of siC 1nflate water w1ngs and raftExit feet f1rst when clear of SiC

1nflate water w1ngsEX1t feet f1rst when clear of sic

1nflate water w1ngs

-50-

60 TLI ABORTS

TLI Aborts are conta~ned ~n the ESD s~nce the bulk of the funct~ons

concern entry preparat20ns and performance Th~s allows a s2nglesource of procedures for procedure rev2ew val~dat~on checkout andtra~n~ng These procedures ~ncorporate TLI preparat20ns as found ~n

reference 6 w~th the TLI Abort Procedures and these t~e 2nto normallunar return Entry Procedures found ~n sect20n 5 The guidel~nes

for th~s cont2ngency are spec2f2ed 2n reference 7

In2t2al preparat~ons for TLI pos2t20n the necessary system sW2tches2n add~t~on to perform~ng an EMS ~V test and a GDC al~gnment Afterthe DET ~s set for mon2tor2ng TB6 the CMP ~ncreases the 12ght levelof the LEB DSKY to max~mum and returns to the h2s couch Th2s 2Sdone so that the LEB DSKY can be observed ~n the event sunl~ght orreflect20ns wash out the ma2n d2splay panel DSKY dur2ng cr2t2calmaneuvers The crew then straps ~n and prepares for mon2tor~ng TB6as 2nd2cated by the SII SEP L~te The t2mes se~uence of procedures2S keyed on th~s d~splay and ~ncludes the DET START funct~on andSIVB IGNITION Dur2ng the burn the crew mon2tors the FDAIs foratt~tude excurs20ns and abnormal rates report~ng status checks toM~ss2on Control at d2screet t~mes dur2ng the maneuver Upon SIVBSHUTDOWN the eMP records the DSKY d~splayed performance parametersand awa2ts ground conf2rmat~on

The rat~onal for TLI aborts ~s descr~bed 2n reference 7 A summar2shyzat20n 2S extracted to prov2de background and gu2de12nes 2n th2sdocument The abort procedures cover aborts 10 m2nutes after conshyt2ngent SIVE shutdown and aborts 90 m2nutes after normal SIVE shutshydown t2me

The 10 m~nute TLI abort ~s des2gned to be used dur~ng TLI ~n theevent a spacecraft problem develops Wh2Ch can result 2n catastrophe2f ~mmed~ate act~on 2S not taken If the s~tuat20n perm~ts the crewshould always allow the SIVB to complete TLI at wh~ch t~me the groundand crew can perform a malfunct~on analys~s to determ~ne ~f an abort~s adv~sable If a fa~lure occurs that necess2tates the shutdown ofthe SIVB and the ~u~ck return of the crew to earth th~s abort ~s

des~gned to be as ~nsens~t~ve to execut~on errors as poss~ble andst21l be targeted to m2dcorr2dor The burn att~tude w~th the f~ed

hor~zon reference ~s a constant value for any shutdown t~me Theburn durat~on 2S a funct20n of shutdown t2me and 2S ava21able fromcrew charts S~nce the pr~mary purpose of th~s abort ~s to returnto earth as qU2ckly as poss2ble there are no restr2ct20ns as toland~ng locat~on However ~f the t~me to EI is greater than abouttwo hours a midcourse correct20n should be ant~c~pated

The 90 m2nute TLI abort 2S to be used 2f a cr2t2cal subsystem malshyfunct~on ~s determ2ned and the dec2s~on to abort ~s made after the

-51-

TLI cutoff and before TLI cutoff plus approxlmately 80 m1nutesTh1S allows suff1c1ent separatlon and procedural t1me to set upfor the SPS deorb1t burn performed at about TLI + 90 Note thatgenerally the deorb1t burns w1ll be performed a fe11 m1nutes beforeTLI + 90 accord1ng to crew charts shown In reference 8 The no-comm except10n requ1res that 90 m1nutes be the 1nput t1me of 19n1shytlon for P-37 (onboard return-to-earth abort program) so that onshyboard calculatlons can correspond w1th ground calculat10ns to computethe CM land1ng p01nt Th1S TLI abort lS des1gned so that returnfl1ght t1me does not exceed 18 hours and abort ~V does not exceed7000 fps ThlS abort can be performed uSlng chart ~Vs and attltudesand the earths hor1zon serves as a suff1c1ent reference The maneushyver lS targeted to ach1eve the mldcorr1dor entry target Ilne andtlmed to result 1n a deslgnated recovery area

It 1S ObV10US for abort deC1S1ons early 1n the TLI + 90 m1nute t1meshyframe that a GampN SPS burn should be performed In order to keep theTLI abort procedures cons1stent and w1th emphasls on slmpl1c1ty theprocedures here reflect a SCS SPS abort burn to cover the full abortdec1s1on t1meframe

A m1dcourse correct1on for corr1dor control after a TLI abort may bedeS1red 1f the SPS burn d1d not meet expectat1ons The TLIabortprocedures 1n th1S sect10n adapt to the normal lunar return tlmel1neand procedures pr10r to the f1nal MCC

-52-

61 TLI PREPARATION PROCEDURES

GET = 150

CRO AOS(___)

CRO LOS( )(22142)

5100

Don Helmets amp Gloves

XLUNAR - INJECT (verify)EDS PWR - on (venfy)EMS FUNC - OFF (verlfy)EMS MODE - STBYEMS FUNC - IW SETVHF RNGEMS MODE - NORMALSet ~V indo to +15868 fpsEMS FUMC - ~V Test

SPS THRUST Lt - onoff (10 sec)~V lnd stops at -01 to -415

EMS MODE - STBYEMS FUMC - ~V SETVHF RNGSet ~VC

EMS FUNC---~~V=----

GDC ALIGNFDAI Select - liZcb SECS LOGIC (Z) - close (verify)cb SECS ARM (Z) - closeSECS LOGIC (Z) - on (up)MSFN Conflrm GO for PYRO ARM (If pass)SECS PYRO ARM (Z) - on (up)TRANS CONTROL PWR - ONROT CONTR PWR NORMAL (Z) - ACDC(verlfy)ROT CONTR PWR DIRECT (Z) - MNAMNBLV INnGPI - SIISIVB (venfy)LV GUID - IU (venfy)cb DIRECT ULLAGE (Z) - closedSet EVENT TIMER to 5100Begin MONITOR For TB6

CMP to Couch

TB 6 - SII SEP Lt on (TIG-9 mln 38 sec)KEY V83E

SET ORDEALFDAI Z ORB RATE at 180 0 0SII SEP Lt out (38 sec later)Start DET COUNTING UPSC CaNT - SCS (verify)MONITOR LV TANK PRESS

~P lt 36 psid (OXID gt FUEL)~P lt Z6 psid (FUEL gt OXID)

EMERGENCY CSMLV SEP UP TLM CM - BLOCK (verify)UP TLM IU - BLOCK (venfy)

-53-

+45degPY))0middot sec PY

lOK nmltHAlt25K nm

Two phas~ng mnvrs two SPS mnvrs to circular~ze at 150 nmearth orb~t

CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ssion 4K nmltHAltlOK nm CSM amp1M - Two phasing mnvrs two SPS mnvrs to circularize at 150 nm earth orb~t CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ss~on

CSM amp 1M - Two phas~ng mnvrs APS burn todepletion th~rd phasing mnvrSPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn tosem~sync orb~t

25K nmltHAlt40K nm CSM amp 1M - Two phasmg mnvrs APS burn to depletion third phas~ng mnvr SPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn to sem~sync orbit HA)40K nm DPS ava~l - DPS LOll circularize with SPS

DPS not ava~l - Lunar flyby or CSM only to lunar orbit (if reqd gtV lt4000 fps)

V37E 47E (check b~as) Record -=--rshy(Limit 98 fpsmm)

( 1fps)tVXYZN62EVIHDOTHPAD (fpsfpslnm)MONITOR VI ( ) at ECO

SCS TVC SERVO PWR 1 - ACIMNA2 - OFF

TAPE RCDR - CMD RESETHBREMS MODE - NORMAL

SIr SEP Lt - ONTLI Inhib~t S~gnals w~11 not be honored after 5942

SIVB ULLAGE BeginsSII SEP Lt - off (TIG - 18 sec)SIVB FUEL LEADSIVB ULLAGE d~scont~nues

LV ENG I Lt - onSIVB IGNITION ( GETI)LV ENG I Lt - off - -shyMONITOR THRUST amp ATTITUDEMONITOR LV TANK PRESSSIVE ECO (Lt on) (BEGIN TB7)

EMER SIVE CUTOFF AT 6 SEC PAST BURN TIME IF VI ATTAINEDTHC CCW ampNEUTRAL IN 1 SEC or SIISIVB sW - LV STAGEPremature Shutdown HAlt4K nm CSM amp 1M -

5700

58205836

F 16 835800

F 16 62

5838594259525955595900000002SUNRISE(___)

HAW AOS(__=_) KEY VERB (freeze d~splay)

SIVB ATT HOLD 20 sec amp BEGIN VENTINGSIVB NNVR TO ORB RT (HDS DN) (3middot sec)

Record VI -c---HDOT _

HPAD _

KEY RLSEF 16 62

F 16 83

HAW LOS(__=-)

KEYmiddotRLSE~VXYZ (lfps)

Record ~VX---_

~vy

WZ--

AVC---_

TAPE RCDR - off (ctr)EMS MODE - STBYEMS FUNC - OFFSECS PYRO ARM (2) - SAFE

PRO

BURN STATUS REPORT

____--~TIG

BT------VGX____-R

-----P----_Y

REMARKS

_____VI

______--HDOT______--H______---AVC______---FUEL_______OXID

_______UNBAL

F 3708=00 OOEGOS AOS CMP TO LEB

(-=-=-)

0000

0003

0005

0014

0100

-55-

62 TLI 10 MIN ABORTSECS LOGIC (2) - on (up)SECS PYRO ARM (2) - ARM

TRANS CONTR - CGH (4 sec) amp +XDET RESET (verlfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS GMD-ON

TRANS GONTR - neutral then +X for10 sec

SIVBGPI s~ - GPIExcesslve rates 6V THRUST A - NORMAL SPS THRUST - DIRECT When rates damped 6V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

TRANS CONTR +X - OFFV37E OOE

PITGH UP to LOGAL VERT (+X axlSto~ard the earth)

RATE - LOWBMAG MODE (3) - ATTIRATE 2EDS PHR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SEGS ARM (2) - opencb EDS (3) - open

TRANS CONTR -X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (180deg)P (199deg)Y (0deg)

RETRO UPDATEGETI _

JV _VG

Jtb ---GET 400K _

05G _GET DROGUE _

ENTRY P _R _

Y_--

0945

-56-

ALIGN HORIZ ON RET +1 MKGMBL CHECK (T11lle Pentattlng)MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conflnn)cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FUMC - JV SETVHF RNGSET JV from chartE~S FUMC - JVEMS fODE - NOIDlAL

lV THRUST A - NORMALV37E 47E (THRUST fONITOR)

F 16 83 lVXYZ (1 fps)

0950

1000

NOTE For aborts durlng 1st mln of TLIKEY V82E F 16 44 (HaHpTff)Burn untll Hp lt 19NM

TRANS CONTR +X

THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN JV reqdJV THRUST (2) - OFFReport cutoff

cb SPS P2 Y2- closeGfBL MTRS (4) - OFF (LMP Confinn)TRANS CONT PWR - OFFTVC SERVO PWR (2) - OFFMN BUS TIE (2) - OFFcb SPS P1amp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREIf est time to EIltOl5500 omlt fCC andenter the SUPERCIRC CKLIST as early as pos-slb1e Pg ~2~3~ __If est time to EI)Ol5500 anticlpate afCC Enter the ENTRY PREP CKLIST at step 9pg 18

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

-2tl C

l I W gt- ~-4

z laquo I I- 0 -6

l- I J u gt- ~-8

z w w -10

~_ONSANT

9O

VER

SHO

OT

BOU

ND

ARY

LIF

TV

EC

TOR

OR

IEN

TATI

ON

LIN

E

SH

ALL

OW

TAR

GE

TLI

NE

STE

EP

TAR

GE

TLI

NE 12

gU

ND

ERSH

OO

TBO

UN

DAR

Y

RE

EN

TRY

CO

RR

IDO

R

I ~ I

-12 24

26

28

30

32

34

RE

EN

TRY

VE

LOC

ITY

VE

1-F

TS

EC

Ch

art

1

36

3B

6-i

~

5CM

CC

ON

ST

NT

DR

VI z gt

~

I4

0 Cl W

I

gtamp

J+

-I

-

J Cl z

2U

l z 0_bull

bull-1

+-

u ubullbull

~r

U

)

2829

JOn

J23

33

43

5IN

ER

TIA

LR

EE

NTR

YV

ELO

CIT

YA

T4

00

00

0fl

VE

I-F

TS

EC

Ch

art

2

J63

73

8X

03

-i- rtREQUIRED PITCH GIMBAL ANG LETO OBTAIN HOR-IZON AT 317

DEGREES IN wiiiiDOW

260

z~I- ~ i5 24000

1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

-I

-1-

NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

I LU HD~-

LUHD

lt0 120UJ0

~

80 HOLD PRESENT TRIMgt LU HD013

~Y~HOIgtlt

TOP OF WINDOWa 40to

31 7 SCRIBEaaI

80 TTOM OF WINDOWi= 0

0--ltoa

-40t-z

~~~Uw w u lt0 -80

HOLO PRESENT TRIlJCl

LOHU0 lt0

J gt -120 HOLD 059 TRIMlt0 z

LDHUlt0 FIELD OF VI S10 NLDHU LIFT-DOWNHEADS -UPLUHD LIFT-UP HEADS-DOWN

~~H~-160 q - P63 LIMITI- NOrE-VALIO ONLY FO~t~--

LUNAR RETURN VELOCITY

plusmnl8020 244middot 8 12 16

TIME TO 400K FT ALTITUDE-MIN

4

P37

LONG

ITUD

ECO

RREC

TION

TOOB

TAIN

1350

NM

ENTR

YRA

NGE

Ugt

UJ

cgt

3z 0 I- u U

J0

0

0

2I

U~

UJ

cgt

I

gtI- U

gt z 0 J ltJ

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90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 3: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

TABLE OF CONTENTS

41 Typlcal Retroflre and Entry Sequence of Events

56 Earth landing from superclrcular and earth orbitalentrles bull bull bull

51 Entry preparatlons for superclrcular and earth orbltalentr~es bull

20 Llst of Acronyms and Abbrevlatlons

1

2

5

8

10

12

13

15

16

17

17

23

29

35

40

45

47

50

52

55

57

59

bull 64

76

bull

bull

bull bull

bull bull

Earth orbltal entrles bull bull55

54 Normal deorblts for earth orbltal entrles

53 GampN hybrid deorblts for earth orbltal entrles

52 Superclrcular entry

31 Reentry Guidance Events

33 Monltoring wlthout EMS bullbullbullbullbull bullbull

42 Retroflre and Entry Alternatlves

32 Summary of Monltorlng Checks for Entry

Introductlon bullbull

57 Post landing middot

60 TLI Aborts bull

61 TLI preparatlon procedures bull bull

62 10 mlnute TLI abort procedures

63 90 minute TLI abort procedures

70 Entry Pads bull bull bull bull

80 Entry Charts and TLI Charts bull

90 References middot

50 Detalled Entry Procedures bullbullbullbullbullbullbull

40 Earth Orbital Deorblt and Entry Technlques

30 Lunar Return Entry Technlques

10

-1-

10 INTRODUCTION

The purpose of the Entry Summary Document is to provide a singlesource of entry crew procedure ~nformat~on for use ~n fl~ght planshyn~ng crew tra~n~ng and prepar~ng onboard data The techn~ques

conta~ned ~n this document were generally der~ved from other docushymentat~on and are comblned here to serve as a slngle compacttra~n~ng package

In accordance wlth the Fllght Crew Operatlons Dlrectorate CREWPROCEDURES CONTROL PLAN dated March 1968 the prel~minary ESDedltions are dlstrlbuted for review and comment and simulatorval~datlon unt~l 5 months prlor to launch Thereafter flnal ESDprocedures are d~strlbuted and serve as a control ~ocument withchanges sUbJect to approval by the Crew Procedures Control Board

Comments to thls document should be d~rected to the Fl~ght Proshycedures Branch Fllght Crew Support Dlvislon extens~on 3436

-2-

20 LIST OF ACRONYMS AND ABBREVIATIONS

ComputerPilot

ModuleModuleModule

AccumlatorAmphherAntennaAcqu~s~t~on of S~gnal

Backup Bank AngleBeaconBlunt End ForwardCMC Commanded Bank AngleBody Mounted Att~tude GyroBank Reverse BankCab~n

CommanderCoupl~ng Data Un~t

C~rcuit

CommandCommandCommandCutoffCrew Opt~cal AI~gnment S~ght

Commun~cat~ons

Cryogen~c

Command Serv~ce ModuleCounterCaut~on Warn~ng SystemD~g~tal Auto P~lot

D~g~tal Event P~lot

Drag Acceleration at Sk~pout

Constant Drag Control Accelerat~on LevelD~splay and KeyboardDSKY EnterEnv~ronment Control SubsystemEntry InterfaceEntry Monltor SystemElectrlcal Power SubsystemEssent~al

Flight Combust~on Stab~lity MonitorFI~ght D~rector Att~tude Ind~cator

FunctionAccelerat~on 1n Earth Grav~tatlonal Un~ts

Gu~dance and ControlGround Elapsed TlffieGround Elapsed T1me of Ign~t~on

Gyro Display CouplerGlycolG~mbal

Guidance and Nav~gat1on

ACCUMAMPANTAOSBBABCNBEFBETABMAGBRBCBNCDRCDUCKTCMCMCCMPCOCOASCm1MCRYOCSMCTRCWSDAPDETDLDODSKYEECSEIEMSEPSESSFCSMFDAIFUNCGGampCGETGETIGDCGLYGMBLGampN GIN

-3-

Llst of Acronyms and Abbrevlatlons

GNDGPIG-VHAHEHPIMUKA

LIDLEBIMPLOSLVMANMCCMCC-HMESCMSFNMGAMKMNVRMaNMTRMTVCNOPTORIEN02PPGAPGNCSPIPAPLPLSSpassPRIMPRPLNTPSIAPTTPUGSPWRRRI R2 R3RADRCDRRCSROTREFSMMAT

GroundG~bal Posltlon IndlcatorAcceleratlon-VelocltyHelght of ApogeeHellumHeight of PerlgeeInertlal Measurement UnltDrag Acceleratlon necessary to lnltlate

constant drag controlLlft to Drag RatioLower Equlpment BayLunar Module PllotLoss of SlgnalLocal Vertlcal Llft Vector Launch VehlcleManualMldcourse CorrectlonMlssion Control Center - HoustonMaster Event Sequence ControllerManned Space Fllght NetworkMiddle Glmbal AngleMarkManeuverMonltorMotorManual Thrust Vector ControlDSKY NounOptlon OptlCSOrlentatlonOxygenPltch or CMC ProgramPressure Garment AssemblyPrlmary GUldance Navlgatlon and Control SystemPulse Integratlng Pendulous AccelerometerPlanetPortable Llfe Support SystemPosslblePrlmaryPropellantPounds Per Square Inch AbsolutePush to TalkPropellant Utllizatlon and Gaglng SystemPowerRoll or CMC RoutlneReglster 1 2 3RadlatorRecorderReactlon Control SystemAltltude RateReference to Stable Member Matrlx

-4-

L~st of Acronyms and Abbrev~at1ons

RELRET

RHCRNGROURRT

RSIRTGOSASCSSECSECSSELSEPSEQSFT

SM SIMSPASPSSTBYSXPSXTSTSTATBTBDTERMTFTFFTHBWLSTHCTIGTLITIl TLMTRNFR

TVCVVGVIOVLVMY

Rel1efReentry Elapsed TIme (Lunar Return Case) or Retro

Elapsed Time (Earth Orb~tal Case) For lunar returnsRET 1S zero at RRT For earth orb1tal entries RET iszero at the deorb1t burn tIme

Rotat1onal Hand ControllerRangeRout1neReentry Reference T~me (Based on MCC-H predicted time

of EI to nearest second)Roll Stab11~ty IndicatorRange to GoShaft AngleStab1lizat1on and Control SystemSecondarySequent1al Events Control SubsystemSelectSeparationSequentialShaft Angle for SXTS when spacecraft 1S at

ignit10n attitudeServ1ce ModuleCOAS Star P~tch AngleServ1ce Propuls~on SystemStandbyStar X Pos~t~on (COAS)SextantSextant StarTrunnion AngleTalkback D~splay T1me BaseTo Be DeterminedTerm~nate

Ttme FromTtme of FreefallThumbwheelsTranslational Hand ControllerTime of Ignit~on

Translunar Insert10nTelemetryTransferThrust Vector ControlVeloc~ty or DSKY VerbVeloc~ty To Be GatnedInertial Veloc~ty

Sktpout Veloc1tyVeloc~ty MeasuredYaw

-5-

3deg LUNAR REIUBN ENTRY TECHNIQUES

The t~mel~ne for lunar return entries is based on the recommendationsfound ~n reference 1 the s~mulator val~dated procedures ~n reference2 and the mission val~dated procedures listed in the onboard checkshylist for the C Pr~me m~ssion The event times are l~sted ~n reference3

The preparation for lunar return entr~es beg~ns at a conven~ent t~me

about 30 hours before entry ~nterface At th~s t=e MSFN sends up alldata suff~c~ent for reentry also an EMS entry selftest ~s made toassure max~mum confidence ~n the EMS operat~on during entry Thereshyafter var~ous system powerups and checks are ~n~t~ated as l~sted insect~on 51 and deta~led ~n reference 4 Nom~nally the PGNCS ~s upfor the ent~re m~ss~on However ~f ~t ~s not ~t ~s powered up atEI-7 hours ~n preparat~on for the last MCC and entry The last MCCdec~s~on ~s made at about EI-6 hours for the maneuver to be performedat EI-3 hours ~f needed Deta~ls of th~s maneuver are outl~ned ~n

reference 1 After the MCC time P52 ~s again selected and the IMU ~s

real~gned to the REFSMMAT If the IMU dr~ft ~s w~th~n tolerance thesubsequent IMUSCS dr~ft check will determ~ne if the SCS has dr~fted

excess~vely If so the other BMAGs are selected and the IMUSCScheck repeated Th~s check ~s followed by a repeat of the EMS ~V

counter check and accelerometer b~as check at EI-l hour 15 m~nutes

to determ~ne ~f the scale factor and b~as are adequate for entrymon~tor~ng F~nal stowage CM RCS preheat and pyro Cllcu~t and seshyquent~al tests are worked ~nto this t~meframe so that at EI-50 m~nutes

the MSFN w~ll be requested for a go to pyro arm by the crew ~n preparashyt~on for separat~on At 45 m~nutes before EI the CMC update programP27 can be selected to permit update of the landing po~nt locat~on andthe state vector The entry PAD data shown ~n sect~on 70 ~s thenvo~ced to the crew and recorded From th~s data the DET ~s set andstarted the EMS ~nit~al~zed and the RSI al~gned Prior to EI-20ffilnutes the crew w~ll have strapped-~n completed the~r presepara-t~on checkl~st and maneuvered to the entry att~tude At this pointEI-19 m~nutes the CMC entry program Fbl ~s selected by the CMP Ifthere was no entry PAD data because of commun~cat~on loss the veloshyc~ty and range to go from P61 ~s recorded and used ~n the EMS AtEI-15 m~nutes the spacecraft ~s p~tched down and the hor~zon ~s checkedagainst the 317 degree w~ndow scr~be l~ne and the FDAI att~tude Ifthere ~s s~gn~f~cant d~sagreement the PGNCS ~s suspected and the spaceshycraft ~s held on the w~ndow reference In P62 the spacecraft ~s yawed45 0 from th~s att~tude and separated from the SM After separat~on

the CM ~s yawed back ~n plane and the hor~zon check repeated At approxshy~mate1y EI-10 m~nutes the p~tch att~tude is w~th~n 450 of the CMCcommanded att~tude and P63 ~s entered automat~ca11y S~nce the CMCDAP tr~es to hold local p~tch attitude and the CMC ~s not ~n controlthe crew observes the p~tch error needle unpeg and approach zeroabout two m~nutes before 05g t~me Th~s serves as a gono go CMC

-6-

check for entry control If the FDAI pltch error does not decreaseto wlthln + 50 at 005g the PGNCS lS fa lied and the crew flies aconstant g-entry mode wlth EMS ranglng after the VelOClty decreaseto 25500 feet per second If the PGNCS lS acceptable the spaceshycraft control lS placed In CMC and the CMC mode lS placed ln autoshymatlc At 05g the EMS automatlcally starts lf the EMS mode sWltchwas posltloned to automatlc earller ThlS wlll be backed up manually3 seconds after the ground computed 05g tlme recorded on the entryPAD by placlng the EMS mode sWltch In manual lf lt has not startedautomatlcally At PGNCS 005g lndlcatlon the CMC program changesto P64 and from thls pOlnt the entry lS under entry DAP control

The lunar return entry nomlnally lS performed by the PGNCS to lnsurecontrol wlthln the overshoot and g llmlt llnes as well as optlmlzethe landlng point accuracy Although the hlgh speed entry lnvolvesa rapld sequency of events there are several monitorlng tasks forthe crew to determlne lf the automat~c contrails performlng correctly

An entry corr~dor ver~flcation check 1S made by observlng the lnltlalslope of the EMS V-g trace between 1 and 2 gs If the EMS lndlcatesthe need to reverse the LV orlentatlon and the lndependent g meterconflrms the EMS g lndlcatlon the SC lS immedlately orlented as aresult of the EMS ~nd~cat~on

The EMS g lnd~catlon ~s contlnuously checked durlng entry uSlng thelndependent g meter and the PGNCS g ~ndlcatlon as a thlrd voteDeC1Slons durlng the first entry (P64) are critlcal ln terms of bothexceSSlve g llnes and the PGNCS lS not commandlng (and SC respondlng)to correct the sltuatlon the PGNCS lS felled

The PGNCS gono go check for short range targets (1200-1400 n ml) forWhlCh P65 lS not used 1S d1fferent Slnce there are no CMC computedSk1p drag (DL) and skip velocity (VL) values The check uses the EMSscroll to determ1ne 1f the PGNCS lS commandlng the proper roll att1shytude to converge the EMS g level to a predetermlned PAD value (Do) ascomputed by MCC-H For the nom1nal target range of 1300 naut~cal

mlles the crew w1ll monltor the program change from P64 to P67 atapprox~matelyEI + 3 mlnutes For ranges greater than 1400 nauticalmlles the program w1ll transfer to the Upcontrol Program P65 whenVL ~s between 18000 and 25766 feet per second and constant drag hasbrought the CMC pred1cted range to wlthln 25 naut1cal m1les of thetarget range The P65 PGNCS gono go check cons1sts of determln1ng1pound both the DSKY d1splay of sk~pout drag (DL) and Sk1pout veloclty(VL) are w1thln the PAD llmlts In addltlon the EMS scroll lS mon1shytored to determ~ne lf the trace lS approach1ng the DL and VL values

Throughout entry the crew monltors the spacecraft response to the CMCroll commands by observlng the FDAI lndlcatlons If the commands are

-7-

apparently good and In agreement wlth the EMS but the spacecraftresponse is questlonable the crew manually takes over and fIlesthe CMC commands

If the Upcontrol Program P65 was entered the program wlll nomshylnally sWltch to the Flnal Entry Program P67 for target rangesbelow approxlmately 1800 nautlcal miles or to the Ballistlc Proshygram P66 for ranges greater than approxlmately 1800 nautlcalffilles The program transfer crlterla are more preclsely deflnedIn reference 1

If P66 lS entered the spacecraft lS automatlcally rolled to theIlftup heads-down attltude to permlt the horlzon to be vlewedfrom the wlndow durlng the second entry The entry attltude checklS made by comparlng the horlzon wlth a speclfled wlndow mark Ifthe check falls the crew manually malntalns the entry trlffi attltudeuSlng the horizon VleW for reference The EMS lS used for ranglngSlnce the veloclty has now decreased to below 25500 feet per second

The EMS scroll lS contlnuously used to monltor for exceSSlve g conshydltlons durlng the second entry If the EMS V-g trace vlolates theg Ilnes and the PGNCS lS not commandlng (and spacecraft respondlng)to correct the situatlon the PGNCS lS falled and the EMS lS usedfor ranglng after ltS g lndlcatlon has been conflrmed by the lndeshypendent g meter

The entry phase lS essentlally over when the relatlve veloclty ofthe spacecraft decreases to less than 1000 feet per second ThlSlS lndlcated In P67 when RTGO latltude and longltude are dlsplayedSlnce very Ilttle ranglng capablllty exists after thls pOlnt thespacecraft lS orlented elther full Ilft up or down dependlng on RTGOnegatlve or posltlve and the crew prepares for the earth landlngphase

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-13-

40 EARTH ORBITAL DEORBIT AND ENTRY TECHNIQUES

As outl~ned ~n reference 5 a nom~nal PGNCS entry from earth orb~t ~s

based on a preparat~on t~me of 2 hours and 40 m~nutes ~nclud~ng 2n~ght passes Th~s t~me ~ncludes approx~mately 20 minutes before thef~rst n~ght pass after the CMC update and PAD data have been rece2vedTh~s t~e also 2ncludes approx2mately 20 m2nutes after the secondn~ght pass to allow suffic~ent t2me to prepare for retrof2re after theIMU f2ne a12gnment It has been determ2ned coarse a12gnment accuracy~s adequate for retrof~re and entry and undoubtedly other funct20nscould be om2tted depend2ng on the c2rcumstances for the dec2s20n toreenter Descr2bed here2n are the nom2nal earth oro2tal entry proshycedures w2th pert2nent comments on system va12dat20n for real timeacceptance dec~s20ns

After the entry dec~s~on is made the crew transfers the PGNCS fromthe standby to the operate mode and rece~ves a CMe update w~th P27Next the maneuver PAD update ~s v02ced up and the 2n~t~al entry mode~s determ~ned During the ~n~tial n~ght pass the IMU or2entat~on ~s

estab12shed uS2ng P51 star s~ght2ngs to obta2n a REFSMMAT The preshyferred or~entat~on opt20n ~n P52 2S then selected to coarse a12gn theIMU uS2ng the des2red entry REFSMMAT determ2ned by MGG-H The GOO ~s

now al~gned to the IMU 2n preparat~on for an IMUSes dr~ft check Ifthe GOO ~nd~cates the ses dr2ft rate exceeds 10 degrees per hour ~n

any ax~s the check ~s repeated on the other BMAGs to estaol~sh if theGOO or Just the single set 2S unusuable Var20us sytem checks as 12sted2n sect20n 51 are performed as necessary cons2stent w2th the t2me12ned2ctates of the maJor act2v2t2es Included 2n these checks are the EMSself-tests and the dV counter test The latter requ2res the spacecraftbe placed ~n dr2ft2ng fl2ght w~th the funct20n sW2tch 2n the dV pos2t~on

If the counter reg2sters a change of more than 25 feet per second w2th2n100 seconds the scroll and counter are unre12able for mon2tor2ng thedeorb2t burn and entry rang2ng If the EMS self-test fails and t2medoes not allow further analysis a 5555 ERE entry 1S planned as thePGNGS backup entry mode After complet2on of these checks the entryPAD lS prov1ded by MeG-H The crew then selects the external dVprogram P30 and the appropr2ate deorb1t tbrust1ng program p40 or P41Dur2ng th2s per2od wh2ch 2ncludes the f1nal n2ght pass P52 may beselected to ver2fy the IMU a12gnment Since the retro att2tude hasbeen computed so that a w2ndow mark c01nc2des w2th the hor2zon atGETI th2s serves as the conclus2ve check on the PGNCS At 5 m2nutesbefore retrofire the att2tude check 1S made by ver1fY2ng that the 12degree scr~be 12ne ~s w2th2n 3 degrees of the hor2zon If not thePGNeS has fa2led and the ses 2S used for att2tude reference and the

V counter for burn durat~on control S2nce the ses att~tude wasa12gned to the IMU a real~gnment ~s necessary This ~s accompl~shed

by manually maneuver2ng the spacecraft to ma~nta1n the 24 degree wlodowmark on the hor2zon and releas1ng the GOO a12gn button at TIG - 2 m2nutes

-14-

Upon complet~on of the burn the tN res~duals are burned to W~th~n

02 feet per second If the PGNCS ~V counter or est~mated burnduration are ~n d~sagreement ~t must be estab1~shed whether suff~shy

c~ent veloc~ty has been suppl~ed to put the land~ng po~nt in thefootpr~nt The PGNCS data w~ll be used ~f ~t ~s conf~rmed by oneother source if not the ~V counter w~11 be used ~f ~t ~s conf~rmed

by the burn durat~on t~me If add~tional ~V ~s necessary the data~s ava~lable to the crew on an onboard chart found ~n Sect~on 80

Post burn entry preparat~on requ~res EMS ~n~t~al~zation RSI al~gnshy

ment and pre-separat~on funct~ons The crew then selects the ~n~t~al

entry program P61 and records the d~sp1ays as a check aga~nst PADdata Upon complet~on of these checks P62 ~s entered The crewmanually or~ents the spacecraft to the separat~on attitude and yaws450 to ~nsure aga~nst possible CM 8M recontact After separat~on

the spacecraft ~s maneuvered to the reentry tr~m att~tude wh~ch

places the hor~zon on the 3170 w~ndow mark at EI Shortly thereshyafter ~n P62 the entry DAP is act~vated and P63 in~t~ated Dur~ng

th~s t~e MCC-H has computed a postburn update and ~t ~s vo~ced tothe crew ~f d~fferent from preburn values The EMS scroll and rangecounter w~ll be adJusted accord~ngly ~f t~me perm~ts A f~nal PGNCScheck pr~or to 05g may be mon~tored at th~s t~e w~th the CMC modein free and the manual att~tude p~tch ~n acceleration command wh~le

the hor~zon reference ~s held the p~tch error needle w~ll decreaseto zero as EI ~s reached At RET 005g the EMS mode sw~tch ~s

turned to manual the entry 005-g sw~tch and EMS roll sw~tch areturned on and the spacecraft control sw~tched to CMC to beg~n DAPcontrol At the PGNCS 005-g ~ndicatwn the program change fromP63 to P64 ~s mon~tored and the t~e vo~ce recorded At th~s t~me

the EMS range counter check ~s made dur~ng the 10 second per~od

follow~ng EMS 005g Dur~ng th~s per~od the counter should countdown 40 + 10 naut~cal m~les At PGNCS 02-g ~nd~cation the changefrom P64-to P67 ~s monitored and the ~splay may be held by key~ngVERB ~n order to record the init~al downrange error d~splay andcompare ~t to the PAD value The PGNCS has fa~led ~f the two do notagree w~th~n + 100 naut~cal m~les In the event P67 has not appearedwhen both the-g-meter and the scroll ~nd~cate greater than 05g thePGNCS has sim~lar~ly fa~led In e~ther fa~lure the SCS is used foratt~tude reference w~th an EMS entry If the checks agree the crewrema~ns w~th automat~c DAP for the rema~nder of the entry

The entry phase ~s essentially over when the relat~ve velocity ofthe spacecraft decreases to less than 1000 feet per second Th~s

~s ~nd~cated ~n P67 when RTGO lat~tude and long~tude are d~splayed

S~nce very l~ttle rang~ng capab~l~ty exists after th~s pOint thespacecraft is or~ented either full l~ft up or down depending onRTGO negat~ve or pos~t~ve and the crew prepares for the earth land~ng

phase

-15-

41 TYP~cal Retrof~re and Entry Sequence of Events

Dec~s~on to reenter

P27 (CMC update)

Retrof~re PAD update

Entry mode dec~s~on

P51 (IMU or~entat~on determlnatlon) durlng f~rst dark per~od

P52 (IMU coarse allgnment)

EMS checks

Entry PAD update

P30 (external AV)

p40 (SPS thrust)

P52 (IMU f~ne al~gnment) durlng second dark per~od

p40 (SPS thrust)

Ign~t~on att~tude check

Retroflre

P61

P62

CMSM separat~on

P63

Postburn PAD update

Entry attltude check

p64 (beg~n DAP control at O05g)

P67 (PGNCS gono go check at O2g)

42

Retrof~re

and

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try

Alt

ern

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-17-

5 0 DETAILED ENTRY PROCEDURES

In order to comblne slmilar procedures that are common to lunar returnentrles and earth orblt entrles the followlng procedures are dlvldedlnto categorles that allow a mlnlmum of dupllClty ThlS provldes asmaller tralnlng package and more closely resembles the onboard crewcheckllst when comparlson lS necessary

51 Entry Preparatlons for Superclucular and Earth Orbltal Entrles

1~e entry preparatlons are comblned In these procedures andsteps pecullar to elther superclrcular or earth orbltal entrlesare labeled accordlngly The tlme llstlngs In thlS sectlon areappllcable to only superclrcular entries Slnce the earth orbltalentry tlmellne lS a functlon of several varlables as descrlbedIn sectlon 40 and reference 5

-18-51 (Contlnued)

VEHICLE PREPARATION

l-

2

3

4

5

6 -0600h

7 -0535h

8

9

10 -0430h

INITIAL STOWAGE COMPLETED

CMC amp ISS START UP

SCS POWER UP

p51 - IMU ORIENTATION

LOAD DAPV48E 11102 01111 PRO ERO PRO

LAST MCC DECISION

NO COMM - P52 amp NAV SIGHTINGSNOMINAL - P2337 ONBOARD COMPARISON

DON MAE WESTS amp FOOT RESTRAINTS

VHF AM A - SIMPLEX

P 27 (SV REFSMMAT) MNVRamp ENTRY pAD UPDATES

11 -0415h P52 - IMU REALIGN(___) (OPTION 1)

12 P37 (NO COMM ONLY)

13

14

ECS CKS02 SUPPLY REFILLECS Monitor CkEVAP H20 CONT (2) vlvs - AUTOSUIT HEAT EXCH SEC GLY - FLOW

EPS CKS 1 3 4 (5 If reqd)

15 SPS CK (If req d)

16

17

18

RCS CKSSM RCS MOUlt CkCM RCS MOUlt Ck

CampW SYS CK

CMC SELF CK

19

20 -0345h

-03l5h-0300h

21

22

22A

-19-

DSKY COND LT TEST

MIDCOURSE MANEUVERP30 - EXT rVP404l - SPSRCS THRUSTINGMIDCOURSE (17) BURN

NO COMM NAV SIGHTINGS

ffiVR TO ENTRY ATT (Superc1rc only)V62E

V49E

22B F 06 22 DESIRED FINAL GMBL ANGLESLOAD ENTRY ATT PAD ANGLESPRO

22C F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) SC CONT - CMC

BMAG MODE (3) - RATE 2CMC MODE - AUTO

PRO(~N) SC CONT - SCS

MNVR to 22E

22D 06 18 AUTO MNVR TO FDAI RPY ANGLES

22E F 50 18 REQUEST TRIM(TRIM) Go to 22C(BYPASS) ENTR

23 -200hr BORESIGHT amp SXT STAR CHECKOPT MODE - CMCOPT ZERO - OFF

V41 N91E

F 21 92 SHAFT TRUNLoad SXTS angles

41 OPTICS DRIVE

CHECK SXT STAROPT ZERO - ZERO

CHECK BORESIGHT STAR (If ava11)

24 -0135h

25(___)

26

27 -0115h

-20-

P52 - lMU REALIGNRecord gyro torqu~ng anglesRp~----

YIf-7gt-Lno--re-c-ycle PS2If conflrmed use SCS for EMS entry

GDC ALIGNIf drlft gtLOohr change ratesource

FINAL STOWAGEOPTICS (except for hybrid)ORDEALGLY TO RAD SEC - BYPASS (verlfy)CooL pnl lnstalledY-Y struts (2) extendedStow Data Box R-12

EMS CHECKEMS FUNC - OFFcb EMS (2) - closeEMS MODE - STBYEMS FUNC - EMS TEST 1 (walt 5 sec)EMS MODE - NORMAL (walt 10 sec)

Check ind lts - offRANGE lnd - 00Slew halr1ine over notch

In self-test patternEMS FUNC - EMS TEST 2 (walt 10 sec)

05G It - on (all others out)EMS FUNC - EMS TEST 3

05G It - onRSI Lower It - on (10 sec Qater)Set RANGE counter to 58 nm+OO

EMS FUNC - EMS TEST 405G It - on (all others out)G-V trace w~thin pattern to lwr rt

corner 9GRANGE lnd counts down to 0+02

EMS FUNC - EMS TEST 505G It - onRSI upper lt - on (10 sec later)RANGE md - 00SCrlbe traces vertlcal llne 9g to

022+01ALIGN SCROLL TO ENTRY PATTERN (on

37K ft sec hne)EMS FUNC - RNG SET

G-V scroll assy traces vert llne022g to 0+01

EMS MODE - STBY

28

29

30 -OllOh

-21-

~V TEST (Deorb~t only)EMS FUNC - ~V SETVHF RNGSET ~V ~nd to 15868 fpsEMS MODE - NORMALEMS FUNC - ~V TEST

SPS THRUST LT - onoff (10 sec)~V ~nd stops at -01 to -415

EMS MODE - STBY

PRIMARY WATER EVAP ACTIVATIONGLY EVAP H20 FLOW - AUTOGLY EVAP STH PRESS - AUTOPRI ECS GLY PUMP - ACI

CM RCS PREHEATNote If sys test mtr 5cd6abcd

all read 39 vdc (28degF) or moreom~t preheat

cb RCS LOGIC (2) - closeCM RCS LOGIC - ONUP T1M CM - BLOCK (ver~fy)

cb CM RCS HTRS (2) - closeCM RCS HTRS - ON (LMP Conf~rm)

(20 mlU or III lowest rdg lS39 vdc) (Moultor Maufpress for press drop)

31 (___) FINAL GDC DRIFT CK (If req I d)If drlft gtlOohr Suspect GDC Do not

use RSI amp FDAI 2

32 -OO5Om

33

34

35

TERM CM RCS PREHEATUP TLM CM - BLOCK (venfy)CM RCS HTRS - OFFCM RCS LOGIC - OFF

SYSTEMS TEST PANEL CONFIGURATIONSYS TEST METER - 4BRNDZ XPNDR - OPERATECM RCS HTRS - OFFWASTE H20 DUMP - OFFURINE DUMP - OFF

LEB LIGHTING - OFF

SEC WATER EVAP ACTIVATIONGLY To RAD SEC vlv - BYPASSSEC COOL EVAP - EVAPSEC COOL PUMP - AC2

36

37

38 -OO45m

-22-

PYRO BATT CKcb PYRO A SEQ A - close (ver~fy)

cb PRYO B SEQ B - close (verify)DC IND - PYRO BAT A(B)

~If PYRO BAT A(B) lt 35 vdc cb PYRO A(B) seq A(B) - open~

PYRO A(B)BAT BUS A(B)TO PYRO~MN BUS TIE - close

cb MNA BAT C - closecb MNB BAT C - closeDC IND - MNBPNL 8 - All cbs closed except

PL VENT - open (ver~fy)

FLOAT BAG (3) - open (ver~fy)

DOCKING PROBE (2) - open (verlfy)EDS BAT (3) - open (ver~fy)

CM ReS HTRS (2) - open

CM RCS ACTIVATIONcb SECS ARM (2) - close (verlfy)cb SECS LOGIC (2) - close (verlfy)SECS LOGIC (2) - ONMSFN conflrm GO for PYRO ARM(~f poss)SECS PYRO ARM (2) - ARMCM RCS PRPLNT 1amp2 - ONCM RCS PRESS - ONRCS Ind sw - eMl then 2

He PRESS 3700-4400 pSlaMANF PRESS 287-302 pSla

SECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFF

P27 amp ENTRY PAD UPDATEGo To Entry Checkllst

Superclrc - pg ~2~3 _Hybnd - pg -----2~9L-__Normal Deorblt - pg __3L5L- _

-23-

52 SUPERCIRCULAR ENTRY

1 SET DET (up to ET)

2

3

4

5

3000(-30-00)

EMS INITIALIZATIONSET RNG TO PAD DATA RNGEMS FUNC - Vo SETSlew Scroll to Pad Data VIOEMS FUNC - ENTRY

RS I ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on (up)GDC ALIGN PB - PUSH amp HOLDYAW Tw - Pos~t~on RSI thru

45deg amp back to LIFT UPGDC ALIGN PB - ReleaseEMS ROLL - OFFA1~gn CDC to lMU

CM RCS RING A CKRCS TRNFR - CMcb CM RCS LOGIC MNB - openAUTO RCS SEL MNB (6) - OFFSC CONT - SCSTest R~ng A ThrustersSC CONT - CMCRCS TRNFR - SMAUTO RCS SEL (12) - MNAMNB

(hftoff conflg)cb CM RCS LOGIC MNB - close

OPTICS PWR - OFFCMP to COUCH

MN BUS TIE (2) - ONTAPE RCDR - REWIND

6 35middot0Om(-25middot 00)

-24-

SEPARATION CK LISTTVC SERVO PWR 1 - AClMNAcb ELS (2) - close (ver1fy)PRIM GLY TO RAn - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY vlv - OFFCAB PRESS REL vlv (2) - NORMGMBL MTRS (4) - STARTABORT SYS PRPLNT - RCS CMD (venfy)SM RCS PRIM PRPLNT (4) - ONVHF 11M (AampB) - OFFHI GAIN ANT PWR - OFFFC PUMPS (3) - OFFVer1fy s1ugle SU1t compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - 10101cb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2) - opencb HTRS OVLD (2) - openPOT H20 RTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANSEC COOL EVAP - RESETSEC COOL PUMP - off (etr)

MtiVR TO CMSM SEP P R ATTSC CONT - SCSCMC MODE - FREEMNVR TO PAD ATTR (0deg)PY----W)

-25-

SUPERCIRCULAR ENTRY (Cont~nued)

1

4100m(-1900)

P61 - ENTRY PREP

V37E 61E

k 05 09 01427 - ROLL REVERSED 05 09 01426 - IMU UNSAT ~

2 F 06 61 IMPACT LAT LONG HDS UPDN (+-)PRO (010

fps +00001)

3 F 06 60 GMAXVPREDGAMMA EIRecord

GMAXV400K----

GAMMA EI _PRO

(01deg fpsOldeg)

4 F 06 63 RTOGO (lnm) PAD _VIO (fps) PAD _TFE(m~n-sec)

Compare w~th ~M~SFN==C~f~o-r~P~GNS GONO GOIf NO COMM Set RTOGO amp VIO In EMS

amp lnltla11ze(ACCEPT) PRO(RECALC) V32E To 4

5 F 50 25

4300m

(-1700)

45 oOm(-1500)

500Om(-1000)

6 F 06 61

-26-

P62 - CMSM SEP amp PRE-ENTRY MNVRCAUTION Call No EXT Verbs In P62

00041 REQUEST CMSM SEPSC CONT - SCSFREE

COMPARE PITCH ATT WITH PAD DATA ---0=-

(W~thLU 5deg)YAW - 45deg OUT-OF-PLANE (LEFT)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTIRATE 2MN BUS TIE (2) - ON (ver~fy)

PRIM GLY TO RAD - BYPASS (verlfy)CM RCS LOGIC - ON (venfy)SECS LOGIC (2) - on (up)SECS PYRO ARM - ARMCMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 ps~a

CM RCS LOGIC - OFFSECS PYRO ARM (2) - SAFEMonltor VMAB

If lt25 vdc go to EMERGPOWERDOWN pg E6-l

AUTO RCS SEL AC ROLL (4) - OFFAUTO RCS SEL CM 2(6)-OFFAUTO RCS SEL CM 1(6)-MNAYAW back to 0degPITCH TO HORIZ TRACK ATT

ROLL - 0deg (LIFT UP)PITCH - 400K Horiz Mark (317deg)YAW - 0deg

ATT DB - MAXMAN ATT PITCH - ACCEL CMDEMS DATA - Ver~fy

EMS FliNC - ENTRY (ver~fy)

EMS MODE - NORMALcb SPS PampY (4) - openMAINT HORIZ TRK

PRO (Act ENTRY DAP)

IMPACT LATLONGHDSDN (01deg01deg-00001)PRO

7 POSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axis beyond 45deg of Vel vector)

8 06 64

58middot00m(-0200)

9

05G tlme(+0 )

(--=---)

06 68

-27-

P63 - ENTRY INIT

GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PIJR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRmDHORIZ CKPltch error needle goes toward

zero approachlng OSG tlmeMAN ATT (PITCH) - RATE CMD

If CMC lS GOBMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS I

FLY BETA If CMC NO GO ilt

1 SC CaNT - SCS I

FLY EMS k

p64 - ENTRY POST 05G

RTOGO AT 05G AGREES HITH EMS-venfyHORIZ CK05G Lt - ON (EMS START)

No EMS START wlthln 3 sec ~ EMS MODE - BACKUP VHF RNG c

05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds Llft DN

NNVR Llft DNEMS GONO GO

G-V Plot wlthln IlmltsRng ctr dwn 60plusmn7 durlng 10 sec

perlodMonltor G-meter for

convergence wlth pad data (Do)(Vlt27K fps) Go to 13

-28-

P65 - ENTRY - UP CONT (Vgt27K fps)

10 F 16 69 BETA (01middot) _DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT lt~ SC CONT - SCS FLY EMS

PRO

11 06 68 BETAVIHDOT (OIdegfpsfps)(VltV1+500 fps amp RnOT Neg) Go To 13

P66 - ENTRY - BALLISTIC (D(DL)

12 06 22 DESIRED GMBL ANGLES RPYMoultor horlz +12middot of 317middot mark

P67 - ENTRY - FINAL PHASE (02G)

13 06 66 BETACRSRNG ERRDNRNG ERR(010 1um 1um)

KEY VERBRecord DNRNG ERR _KEY RLSEMoultor l~ft vector ou RSI amp FDAI

16 67 RTOGOLATLONG (Vrel=1000fps)(lumOldegOldeg)

SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOWNMonitor a1t~meter

Go To EARTHLANDING pg ---4L5 _

-29-

53 GampN HYBRID DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL tV1 V37E 30E

2 F 06 33 GETI(ACCEPT) PRO (hrm~n Olsec)(REJECT) LOAD DESIRED GETI

3 F 06 81 tVXYZ (LV) (lfps)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

4 F 06 42 HAHPtV (lnm lfps)Record tV

(ACCEPT) PRO(REJECT) Reselect P30 or P27 Load new paramo

5 F 16 45 MTFIMGA (marksm~n-secOlO)

MGA -00002 ~f k

k lMU not al~gned

SET DETPRO

6

7

8

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (Pull)PLSS 02 vlv - FILL02 8M SUPPLY vlv - OFFCAB PRESS REL vlv (2) - NORMcb ELS (2) - closecb SECS ARM (2) - closecb SECS LOGIC (2) - close (ver~fy)

AUTO RCS SEL CM (12) - MNA or ~ffiB

(hftoff conhg)ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM (AampB) - OFF

CMP to Couch

9

10

11

-30-

MNVR TO PAD BURN ATTLOAD DAPBMAG MODE (3) - RATE 2SC CONT - CMCAUTOATT DB - MINMAN ATT (3) - RATE CMD

v62E

v49E

12 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLES

PRO

13 F 50 18 REQ MNVR TO FDAI RPY ANGLES (01deg)(AUTO) PRO(MAN) SC CONT - SCS

BMAG MODE (3) - RATE 2MNVR To 15

14 06 18 AUTO MNVR TO FDAI RPY ANGLES (01deg)

15 F 50 18 REQ TRIM TO FDAI RPY ANGLES (01deg)(TRIM) Go to 13(ByPASS) ENTR

16

17

CHECK BORESIGHT amp SKT STARSOPT MODE - CMCOPT ZERO - OFF

v41 N91E

18 F 21 92 SHAFTTRUN (01deg 001deg)Load SXTS angles

19 41 OPTICS DRIVECheck SKT STAR

OPT ZERO - ZEROCheck BORESIGHT STAR (~f ava~l)

20 V25 N17E (01deg)Load Pad Data GMBL Angles

for CM BURN ATTATT SETtw - SET

to PAD DATA GMBL ANGLESfor CM BURN ATT

21

22

-31-

PHR REDUCTIONHGA PHR - OFFFC PUMPS (3) - OFFVerify s~ngle su~t compr oper loads

balancedFC 2 MN AampB - OFFS BD PiR AMP - LOWcb ECS RAD CONTHTR (2) - opencb HASTE H20URINE DUMP HTRS(2)- opencb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANMN BUS TIE (2) - ONTVC SERVO PHR 1 - AC1MNAGMBL MTR (4) - START

p41 - RCS THRUSTINGV37E 41E

23 F 50 18 REQ MNVR TO LCL HORIZ (HDS ON)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CMCAUTOPRO To 24

(gtfANDAP) BMAG MODE (3) - RATE 2SC CONT - CMCHOLD

V62EMNVR To 25

24 06 18 AUTO MNVR TO FDAI RPY

25 F 50 18 REQ TRIM TO LCL HORIZ (01deg)ALIGN SC ROLL

(AUTO TRIM) PRO To 24(BYPASS) ATT DB - MIN

RATE - LOHMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTlRATE 2

ENTR

550Om26 06 85

59middot2527

-32-

VGXYZ (1fps)RECHECK BORESIGHT STARTRANS CONIR PWR - on (up)EMS MODE - STBY (ver~fy)

EMS FliNC - bV SETVHF RNGSET (IV for SM BURN _EMS FliNC - bVS BD ANT - OMNI CSECS LOGIC (2) - ONMSFN conhrm Go for PYRO ARMSECS PYRO ARM (2) - ARMCM RCS LOGIC - ON (ver~fy)

DSKY BLANKS

593028 16 85 VG XYZ (AVE G ON) (lfps)

RHCs amp THC - ARMEDLIMIT CYCLE - OFFTAPE RCDR - CMD RESETHBREMS MODE - NORMAL

000029 F 16 85 REQ NULL VG XYZ (lfps)

BURN EMS bV CTR TO ZERORESET DET amp COUNT UP

If SM ONLY burn go to step 32THC - LOCKEDSC CaNT - SCSFREERATE - HIGHPRIM GLY To RAD - BYPASS (ver~fy)

MN BUS TIE (2) - ON (ver~fy)

CMSM SEP (2) - on (up)CSMLM FNL SEP (2) - on (up) (verify)CampW MODE - CMRCS TRNFR - CMCM RCS LOGIC - OFF

Momtor VM ABIf lt25 vdc go to EMERGPOWER DOWN Pg E6-l

V63E

If CMC NO GO FDAI SOURCE - ATT FDAI SEL - 1 or 2 ATT SET - GDC

SET

-33-

~Uili ATT PITCH - ACCEL CMDFDAI SCALE - 55MNVR TO CM BURN ATT (NULL ERR NEEDLES)

R 0degPY --00--

30

31

CM RCS BURNRHC III-ContJnuous PJtch DownRHC HZ-Module PJtch to null needlesBURN VGZ TO ZERO

If only 1 RHC Pulse + P=5deg from retro att MaJnta~n rates lt3degsec

BURN COMPLETION ATllV CTR= or DET= _

V8ZE

32 F 16 44 HAHPTFF (1nmffiJn-sec)Check HP-

If gt Pad data contJnue burnuntJ1 lt Pad

PRO

33 F 16 85 VGXYZ (Ups)Read VG resJduals to MSFN

(HYBRID) PRO to 34(SM ONLY BURN)

PROF 37 ODE

EI-1500 V37E 47EF 16 83 twx Y Z (Ups)

SC CONT - SCSFREEMAN ATT (PITCH) - RATE CMDRATE - HIGHPRIM GLY To RAD - BYPASS (verJfy)MN BUS TIE (2) - ON (verJfy)CMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verJfy)Campl MODE - CMRCS TRNFR - CMCM ReS LOGIC - OFFSECS PYRO ~I (2) - SAFE

-34-

PROMonitor VMAB

If lt25 vdc go to EMERGPOWER DOWN

34 F 37 OOEPCM BIT RATE - LOWATT DB - MAXEMS MODE - STBYEMS FUNC - OFF

Go To EARTH ORBIT ENTRY pg _--40-__

-36-

8 SPS THRUSTING PREPCYCLE CRYO FANSSPS GAGING - ACI (ver~fy)

PUG MODE - NORM (venfy)BMAG MODE (3) - RATE 2tv CG - CSMCMC MODE - FREEAUTO RCS SEL (16) - MNA or HNB

(hftoff conbg)SC CONT - CMCAUTO

9 MNVR TO PAD BURN ATTV62E

10 V49E

11 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLESPRO

12 F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) PRO(HAN) SC CONT - ses

MNVR to 14

06 18 AUTO MNVR TO FDAI RPY ANGLES13

14 F 50 18 REO TRIH TO FDAI RPY ANGLES(TRIM) Go to 12(BYPASS) ENTR

15 BORESIGHT STAR CHECK

16 V37E 40EOPT PWR - OFF

17 F 50 18 REQUEST MNVR TO FDAI RPY ANGLES (01deg)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CHCAUTOPRO to 18

(MANDAP) BMAG HODE (3) - RATE 2SC CONT - CMCHOLDMNVR to 19

(HANseS) se eONT - sesMNVR to 19

-35-

54 NORMAL DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL ~V

1 V37E 30E

2 F 06 33 GETI (hrm~nOlsec)

(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

3 F 06 81 ~VXYZ (LV)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

( lfps)

4 F 06 42 HAHP~V (1nmlfps)Record W

(ACCEPT) PRO -----(REJECT) Rese1ect P30 or P27 Load new pa~am

5 F 16 45 MTFIMGA (marksmln-secOldeg)MGA -00002 If ~ lMU not a1~gned

SET DETPRO

6

7

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY v1v - OFFCAB PRESS REL v1v (2) - NORMcb ELS (2) - close (verify)cb SECS ARM (2) - close (ver~fy)

cb SECS LOGIC (2) - close (verlfy)AUTO RCS SEL CM (12) - ~mA or MNB

(l~ftoff conf~g)

ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM AampB - off (ctr)

18

-37-

06 18 AUTO MNVR TO FDAI RPY ANGLES (01 0)

19 l 50 18 REOUEST TRIM MNVR TOALIGN SIC ROLLGDC ALIGN

FDAI RPY ANGLES(010

)

+54-00m(-06-00)

TIG-5mJn

5500m(-0500)

TVC CHECK amp PREPcb STAB CONT SYS (all) - closecb SPS (12) - closeATT DB - MINRATE - LOl~

LIMIT CYCLE - ONMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE 2ROT CONTR PWR DIRECT (2) - OFFSCS TVC (2) - RATE CMD

If SCS SCS TVC (2) - AUTO SC CONT - SCS ~

TVC GMBL DRIVE PampY - AUTOMN BUS TIE (2) - ONTVC SERVO PWR 1 - AC1MNA

2 - AC2MNBTRANS CONTR PWR - ONROT CONTR PWR NORMAL 2 - ACRHC 2 - ARMED

HORIZ CHK - HorJz on 12deg wJndmlmark (LJffiJt +3 0 PNGCS GONO GO)

If NO GO set tw 180 0 180deg0 0

Track horJz wJth 24deg wJndow markAt TIG-2 mJn Ahgn GDC

PRIMARY TVC CHECKGMBL MOT P1-Y1 -STARTON(LMP confJrm)

If SCS verJfy Thumbwheel TrJmTHC - CWVenfy NO MTVC

SEC TVC CHECKGHBL MOT P2-Y2 -STARTON(LMP confJrm)SET GPI TRIHVenfy MTVCTHC NEUTRALGPI returns to 00 (CMC) or trJm (SCS)ROT CONT Pl~ NORM 2 - ACDC

(TRIM) Go to step 17(BYPASS) BMAG MODE(3) - ATTIRATE2 (ver1fy)

ENTR

-38-

20 F SO 25 00204 GMBL TEST OPTION(ACCEPT) SC CONT - GMC (ver~fy)

PROMonitor GPI Response

0020-2000020-200Tr~m

TEST FAIL SC CONT - SCS SCS TVC (2) - AUTO

(REJECT) ENTR

21 06 40 TFIVG~VM (m~n-sec1fps)

PROG ALM - TIG s1~pped

V5N9E 01703

KEY RLSE To 21 ROT CONTR PWR DIRECT (2) - MNABSPS He v1vs (2) - AUTO (ver~fy)

LIMIT CYCLE - OFFFDAI SCALE - SOIScb SPS P2Y2 - open (for cr~t burn)

5800(-02 00)

5925(-0035)

59middot 30(-0030)

06 40

59XX(-OOXX)

AV THRUST A(B) - NORMALTHC - ARMEDRlIC (2) - ARMEDTAPE RCDR - GID RESETHBR

DSKY BLANKS

(AVE G ON)EMS MODE - NORMAL

TFIVG~VM (m~n-seclfps)

CHECK PIPA BIAS lt2fps for 5 sec

ULLAGE AS REQ

IF NO ULLAGE DIR ULLAGE PB - PUSH~

CONTROL ATT WRlIC MONITOR AVM (R3) COUNTING UP

5955(-0005)

F 99 40 ENG ON ENABLE REQUEST(AUTO IGN) PRO AT TFI gt0 sec(BYPASS IGN) ENTR to 24

22 0000 IGN

-39-

If SCS - THRUST ON PB - PUSH

06 40 TFCVG~VM (m~n-seclfpslfps)

~F 97 40 SPS Thrust fall ~

~(RESTART) PRO To IGN (RECYCLE) ENTR To TIG-05 sec

SPS THRUST LITE - ONMONITOR THRUSTING

Pc 95-105 pSlaEMS COUNTING DOWNSPS IN3 v1vs (4) - OPENSPS He v1vs tb (2) - graySPS FUELOXID PRESS - 175-195 pSlaPUGS - BALANCED

PROG ALARM V5N9E 01407 VG INCTHC - CW FLY MTVC

ECOEMER SPS CUTOFF J

AV THRUST (2) - OFF

23 F 16 40 TFC(STATIC)VG~VM (mln-seclfps)~V THRUST AB - OFF

SPS IN3 v1vs (4) - CLOSEDSPS He tb (2) - bp

cb SPS P2Y2 - closed (verlfy)TVC SERVO PHR - AC1MNA (venfy)TVC SERVO PWR 2 - OFF

PRO

24 F 16 85 VG XYZ(CM) CUps)NULL RESIDUALSRECORD ~V CTR amp RESIDUALS I1VCEMS FUNC - OFF VGXEMS MODE - STBY VGYBMAG MODE (3) - RATE 2ATT DB - MAX VGZTRANS CONT PHR - OFF

PRO

25 F 37 V82E

26 F 16 44 HAHPTFF (lnmm~n-sec)

R3-59B59 HP gt494 nmPRO

27 F 37 OOE

-40-

55 EARTH ORBIT ENTRY

1 Venfy CMSMR __

P_shyY_-

SEP ATT(180deg)

(0deg )

2

3

4

EMS INITIALIZATIONEMS FUNC - RNG SETSET RNG TO PAD DATA RNGEMS FUNC - VA SETSlew scroll to pad data VIOEMS FUNC - ENTRY

RSI ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on(up)GDC ALIGN PB - PUSH amp HOLDYAW tw - Pos1tion RSI thru 45deg amp

back to LIFl UPGDC ALIGN PB - RELEASEEMS ROLL - OFFAl1gn GDC to lMU

PWR REDUCT (Norm Deorb Only)HGA PWR - OFFFC PUMPS (3) - OFFVer1fy s1ngle suit compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - Lowcb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2)-openlOb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MAN

-41-

P61 - ENTRY PREP

5 V37E 61E05 09 01427 - ROLL REVERSED05 09 01426 - IMU UNSAT

6 F 06 61 IMPACT LAT LONG liDS UPDN (+-)(01 0

010

+00001)

PRO

PAD VALUESLATLON==G------liDS UP DN _

7 F 06 60 GMAXV400KGAMMA EIRecord

GMAXV400K----GAMMA EI _

PRO

8 F 06 63 RTOGO (1nm) PAD _VIa (fps) PADTFE (mln-sec) ----Compare wlth MSFN for PGNS GONO GONO COMM SET RTOGO amp VIO IN EMS amp

INITIALIZE(ACCEPT) PRO(RECALC) V32E to 8

-42-

P62 - CMSM SEP amp PRE-ENTRY MNVR

9 F 50 25 00041 REQUEST CMSM SEPSC CONT - SCSFREEYAW - 45deg out-of-plane (left for RCS

nght for SPS)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE2PRIM GLY to RAD - BYPASS (verlfy)SECS LOGIC (2) - on (up)MSFN conflrm GO for PYRO ARMSECS PYRO ARM - ARMMN BUS TIE (2) - ON (verlfy)CMSM SEF (2) - ONCSMLM FNl SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 pSlaCM RCS LOGIC - OFFSECS PYRO ARM - SAFEMonltor VMAB

If lt25vdc go to EMERG POWERDOWN Pg E6-1AUTO RCS SEL AlC ROLL (4) - OFFAUTO RCS SEL CM 2(6) - OFFAUTO RCS SEL CM 1(6) - MNA or MNBYAW back to 00

PITCH TO ENTRY ATTROLL 0deg (LIFT UP)PITCH - HORIZ on 317deg MARK (400K)YAW 00

ATT DB - MAXMAN ATT (PITCH) - ACCEL CMDEMS DATA - VerifyEMS FUNC - ENTRY (verlfy)EMS MODE - NORMALMAINTAIN HORIZ TRK

PRO (Act ENTRY DAP)

10 F 06 61 IMPACT LAT LONG HDSDN(010 010 -00001)

PRO

11 FOSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axlS beyond 45deg of Vel vector)

-43-

P63 - ENTRY INIT

12 06 64 GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PWR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRHORIZ CKP~tch error needle goes toward

zero approach~ng 05G t~me

MAN ATT (PITCH) - RATE CMDIf CMC ~s GO

BMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS FLY BETA If CMC NO GO ~

SC CONT - SCS~

FLY EMS RCS Deorh Roll HDS UPTRACK HORIZ w~th 29deg w~ndow mk

P64 - ENTRY POST 05G

13

05G t=elt+0___)

06 68

RTOGO AT 05G AGREES WITH EMS - venfyHORIZ CK05E Lt - on (EMS start)

No EMS start w~th~n 3 secsEMS MODE - BACKUP VHF RNG 05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds L~ft DN

NNVR L~ft DNEMS GONO GO

G-V Plot w~th~n llm~ts

Rng ctr dwn 60 + 7 durlng 10 sec per~od

Mon~tor G-meter forconvergence wlth pad data (Do)

(Vlt27K fps) Go To 17

-44-

P65 - ENTRY - UP CONT (Vgt27K fps)

14 F 16 69 BETA (01deg)DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT~

SC CONT - SCS FLY EMS

PRO

15 06 68 BElA VI HOOT (01deg fpsfps)(VltVL +500 fps amp RDOT Neg) Go To 17

p66 - ENTRY - BALLISTIC (DltDL)

16 06 22 DESIRED GMBL ANGLES RPY (01deg)Mon~tor hor~z +12deg of 317deg mark

P67 - ENTRY - FINAL PHASE (02G)

17 0666 BETACRSRNG ERRDNRNG ERR (Oldeglnmlnm)KEY VERBRecord DNRNG ERR _KEY RLSEL~m~t +100nm from PAD DRE

Mon~tor l~ft vector on RSI amp FDAIF 16 67 RTOGOLATLONG (Vre1=1000fps)

(lnm 010 01deg)SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOlfflMon~tor altimeter

Go To EARTHLANDING pg _I4L5__

-45-

56 EARTHLANDING

90K STEAM PRESS - PEGGED50K CABIN PRESS REL vIv (2) - BOOSTENTRY

SECS PYRO ARM (2) - ARM

40K(90K + 63s)

CM UNSTABLE RCS CMD - OFF ~ 40K APEX COVER JETT PG-PUSH DROGUE DEPLOY PG - PUSH (2 secafter apex cover Jett)

30K ELS LOGIC - ON (up)ELS - AUTO

24K RCS hsable (auto)(90K+92s) RCS CMD - OFF

Apex cover Jett (auto)APEX COVER JETT PB - PUSH

(WAIT 2 SECS)Drogue parachutes deployed (auto)

DROGUE DEPLOY PB - PUSH~

If Drogues FallELS - ~ ~Stablllze CM 5K MAIN DPLY PB - PUSHELS - AUTO

235K Cabln Pressure lncreaslng (Drogues + 50s)If not lncreaSlng by 17K CABIN PRESS REL vlv (RR) - DUMP

-46-

10K Maln parachutes deployedMAIN DEPLOY PB - PUSH (wlthln 1 sec)VHF ANT - RECYVHF AMA - SIMPLEXVHF BCN - ONCABIN PRESS REL v1v (2) - CLOSEDIRECT 02 vlv - OPENCM RCS LOGIC - on (up)CM PRPLNT - DUMP (burn audlb1e)Monltor CM ReS 1amp2 for He press decrease

NO BURN or PRESS DECREASE USE BOTH RHCs DO NOT FIRE PITCH JETS

CM PRPLNT-PURGE (to zero He press)CM RCS He DUMP PB - PUSH RHC (2) - 30 sees NO PITCH k

STRUT LOCKS (2) - UNLOCK

cb FLT amp PL BAT BUS ABampBAT C (3) - closecb FLT amp PLT MNA amp B (2) - opencb ECS RAD HTR OVLD (2) - opencb SPS PampY (4) - open

3K CABIN PRESS REL v1v (RH) - DUMP (after purgecompleted)

FLOOD Lts - POST LDGCM RCS PRPLNT (2) - OFFROT CONTR PWR DIRECT (2) - OFF

800 CAB PRESS RELF vlv - CLOSE (latch off)MN BUS TIE (2) - OFF

AFTER LANDINGcb MAIN REL PYRO (2) - closeMAIN RELEASE - on(up)

Go to POSTLANDING pg _47L-__

I

2

3

-47-

57 POSTLANDING

STABILIZATION VENTILATION COMMUNICATIONS

DIRECT 02 vlv - CLOSE

Stablllzation after landlngELS - AUTO (verlfy)cb MAIN REL PYRO (2) - close (venfy)MAIN RELEASE - on (up) (verlfy)S~CS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb BAT RLY BUS (2) - open

No contact w1th recovery forcesVHF AM AampB - off (ctr) ~

VHF AM Rev ONLY - A cb PL VENT - closecb FLOAT BAG (3) - closecb UPRIGHT SYS COMPRESS (2) - closeIf Stable II

FLOAT BAG(3)-FILL t1ll 2 m1n afterupr1ght then - OFF

VHF AM AlB amp BCN - OFF whlle lnvertedIf Stable I

After 10 M1n Coollng Per1odFLOAT BAG (3) - FILL 7 mln then OFF

Post Stab1lizat1on And Ventllat10nPL BCN LT - BCN LT LOWPL VENT vlv - UNLOCK (Pull)Remove PL VENT Exh CoverPL VENT - HIGH or LOWPL DYE MARKER - ON (swlmmer comm)Release foots traps and_restralntscb MNA BAT BUS A amp BAT C (2) - opencb MNB BAT BUS B amp BAT C (2) - opencb FLT amp PL BAT C - opencb PYRO A SEQ A - opencb PYRO B SEQ B - open

EACH HR - CHECK DC VOLTSgt 275 V If Notmiddot cb FLT amp PL-BAT BUS AampB (2) -open cb FLT amp PL BAT C (1) - open GO TO LOW POWER CHECKLIST

Unstow and lnstall PLV DISTRIB DUCTDeploy grappllng hook and 11ne 1f req

4

-48-

Post Landing Communlcatl0nsVHF ANT-RECY (venfy)VHF BCN - ON (verlfy)

If no contact ~lth recovery forcesperform VHF BEACON Check

MONITOR VHF BEACON transmlSSlonnth VHF AM B Rcvr andor Su)vlval

TransceiverkVHF Beacon not operatlng ~connect Surv~val TranscelVer to antcable behlnd VHF ant access pnland place radio ln BCN mode

LOW POHER CHECKLISTVHF BCN - OFFVHF AM (3) - RCVFLOOD Lts - OFFVHF AM AampB - off (ctr)VHF AM RCV ONLY - A (venfy)COUCH LIGHTS - OFFPOSTLANDING VENT SYS mlnlmlze useSURV RADIO - plug mto VHF BCN ANT cableconn behind VHF ant acess pnl amp turn radloon l-n BCN mode

EGRESS PROCEDURES

CMPCDRLMPCDR

CMPCDRCMP

LMPLl1PCDR

STABLE IDlsconnect Umblll-calsNeck darn onCenter couch - 270 0 positionArmrests stowedConnect raft to SIC l-f desl-red wlth

green lanyardConnect raft ~hl-te lanyards to SUltS amp

lnflate water wlngs when eXltl-ngHATCH PISTON PRESS vlv - PRESS (Outbd)Slde Hatch openedPL VENT - OFFcb Pnl 250 (all) - openEgress with 11feraftPut hardware klt outEgress

or CDIPALL

CMF

CDRCMF

CDR

LMF

CMFCMP LMFCMP

UlP

CDR

-49-

STABLE IIcb CREW STA AUDIO (3) - openD~sconnect umb~1~ca1s

Release foots trapsRelease restra~nt harnessCouch seat pans (3) - 170 0 pos1t10nArm rests stowedSurv1va1 k~ts removed from stowageConnect life raft ma~n1~ne to CDR or SicConnect f~rst wh~te lanyard from

11fe raft to suitConnect th~rd wh~te lanyard from

l~fe raft to SU1tConnect rucksacks together to yellow

lanyard on raft bagPRESSURE EQUALIZATION vlv - OPENRemove and stow fwd hatchEX1t feet f1rst w1th rucksacks when clear

of siC 1nflate water w1ngs and raftExit feet f1rst when clear of SiC

1nflate water w1ngsEX1t feet f1rst when clear of sic

1nflate water w1ngs

-50-

60 TLI ABORTS

TLI Aborts are conta~ned ~n the ESD s~nce the bulk of the funct~ons

concern entry preparat20ns and performance Th~s allows a s2nglesource of procedures for procedure rev2ew val~dat~on checkout andtra~n~ng These procedures ~ncorporate TLI preparat20ns as found ~n

reference 6 w~th the TLI Abort Procedures and these t~e 2nto normallunar return Entry Procedures found ~n sect20n 5 The guidel~nes

for th~s cont2ngency are spec2f2ed 2n reference 7

In2t2al preparat~ons for TLI pos2t20n the necessary system sW2tches2n add~t~on to perform~ng an EMS ~V test and a GDC al~gnment Afterthe DET ~s set for mon2tor2ng TB6 the CMP ~ncreases the 12ght levelof the LEB DSKY to max~mum and returns to the h2s couch Th2s 2Sdone so that the LEB DSKY can be observed ~n the event sunl~ght orreflect20ns wash out the ma2n d2splay panel DSKY dur2ng cr2t2calmaneuvers The crew then straps ~n and prepares for mon2tor~ng TB6as 2nd2cated by the SII SEP L~te The t2mes se~uence of procedures2S keyed on th~s d~splay and ~ncludes the DET START funct~on andSIVB IGNITION Dur2ng the burn the crew mon2tors the FDAIs foratt~tude excurs20ns and abnormal rates report~ng status checks toM~ss2on Control at d2screet t~mes dur2ng the maneuver Upon SIVBSHUTDOWN the eMP records the DSKY d~splayed performance parametersand awa2ts ground conf2rmat~on

The rat~onal for TLI aborts ~s descr~bed 2n reference 7 A summar2shyzat20n 2S extracted to prov2de background and gu2de12nes 2n th2sdocument The abort procedures cover aborts 10 m2nutes after conshyt2ngent SIVE shutdown and aborts 90 m2nutes after normal SIVE shutshydown t2me

The 10 m~nute TLI abort ~s des2gned to be used dur~ng TLI ~n theevent a spacecraft problem develops Wh2Ch can result 2n catastrophe2f ~mmed~ate act~on 2S not taken If the s~tuat20n perm~ts the crewshould always allow the SIVB to complete TLI at wh~ch t~me the groundand crew can perform a malfunct~on analys~s to determ~ne ~f an abort~s adv~sable If a fa~lure occurs that necess2tates the shutdown ofthe SIVB and the ~u~ck return of the crew to earth th~s abort ~s

des~gned to be as ~nsens~t~ve to execut~on errors as poss~ble andst21l be targeted to m2dcorr2dor The burn att~tude w~th the f~ed

hor~zon reference ~s a constant value for any shutdown t~me Theburn durat~on 2S a funct20n of shutdown t2me and 2S ava21able fromcrew charts S~nce the pr~mary purpose of th~s abort ~s to returnto earth as qU2ckly as poss2ble there are no restr2ct20ns as toland~ng locat~on However ~f the t~me to EI is greater than abouttwo hours a midcourse correct20n should be ant~c~pated

The 90 m2nute TLI abort 2S to be used 2f a cr2t2cal subsystem malshyfunct~on ~s determ2ned and the dec2s~on to abort ~s made after the

-51-

TLI cutoff and before TLI cutoff plus approxlmately 80 m1nutesTh1S allows suff1c1ent separatlon and procedural t1me to set upfor the SPS deorb1t burn performed at about TLI + 90 Note thatgenerally the deorb1t burns w1ll be performed a fe11 m1nutes beforeTLI + 90 accord1ng to crew charts shown In reference 8 The no-comm except10n requ1res that 90 m1nutes be the 1nput t1me of 19n1shytlon for P-37 (onboard return-to-earth abort program) so that onshyboard calculatlons can correspond w1th ground calculat10ns to computethe CM land1ng p01nt Th1S TLI abort lS des1gned so that returnfl1ght t1me does not exceed 18 hours and abort ~V does not exceed7000 fps ThlS abort can be performed uSlng chart ~Vs and attltudesand the earths hor1zon serves as a suff1c1ent reference The maneushyver lS targeted to ach1eve the mldcorr1dor entry target Ilne andtlmed to result 1n a deslgnated recovery area

It 1S ObV10US for abort deC1S1ons early 1n the TLI + 90 m1nute t1meshyframe that a GampN SPS burn should be performed In order to keep theTLI abort procedures cons1stent and w1th emphasls on slmpl1c1ty theprocedures here reflect a SCS SPS abort burn to cover the full abortdec1s1on t1meframe

A m1dcourse correct1on for corr1dor control after a TLI abort may bedeS1red 1f the SPS burn d1d not meet expectat1ons The TLIabortprocedures 1n th1S sect10n adapt to the normal lunar return tlmel1neand procedures pr10r to the f1nal MCC

-52-

61 TLI PREPARATION PROCEDURES

GET = 150

CRO AOS(___)

CRO LOS( )(22142)

5100

Don Helmets amp Gloves

XLUNAR - INJECT (verify)EDS PWR - on (venfy)EMS FUNC - OFF (verlfy)EMS MODE - STBYEMS FUNC - IW SETVHF RNGEMS MODE - NORMALSet ~V indo to +15868 fpsEMS FUMC - ~V Test

SPS THRUST Lt - onoff (10 sec)~V lnd stops at -01 to -415

EMS MODE - STBYEMS FUMC - ~V SETVHF RNGSet ~VC

EMS FUNC---~~V=----

GDC ALIGNFDAI Select - liZcb SECS LOGIC (Z) - close (verify)cb SECS ARM (Z) - closeSECS LOGIC (Z) - on (up)MSFN Conflrm GO for PYRO ARM (If pass)SECS PYRO ARM (Z) - on (up)TRANS CONTROL PWR - ONROT CONTR PWR NORMAL (Z) - ACDC(verlfy)ROT CONTR PWR DIRECT (Z) - MNAMNBLV INnGPI - SIISIVB (venfy)LV GUID - IU (venfy)cb DIRECT ULLAGE (Z) - closedSet EVENT TIMER to 5100Begin MONITOR For TB6

CMP to Couch

TB 6 - SII SEP Lt on (TIG-9 mln 38 sec)KEY V83E

SET ORDEALFDAI Z ORB RATE at 180 0 0SII SEP Lt out (38 sec later)Start DET COUNTING UPSC CaNT - SCS (verify)MONITOR LV TANK PRESS

~P lt 36 psid (OXID gt FUEL)~P lt Z6 psid (FUEL gt OXID)

EMERGENCY CSMLV SEP UP TLM CM - BLOCK (verify)UP TLM IU - BLOCK (venfy)

-53-

+45degPY))0middot sec PY

lOK nmltHAlt25K nm

Two phas~ng mnvrs two SPS mnvrs to circular~ze at 150 nmearth orb~t

CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ssion 4K nmltHAltlOK nm CSM amp1M - Two phasing mnvrs two SPS mnvrs to circularize at 150 nm earth orb~t CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ss~on

CSM amp 1M - Two phas~ng mnvrs APS burn todepletion th~rd phasing mnvrSPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn tosem~sync orb~t

25K nmltHAlt40K nm CSM amp 1M - Two phasmg mnvrs APS burn to depletion third phas~ng mnvr SPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn to sem~sync orbit HA)40K nm DPS ava~l - DPS LOll circularize with SPS

DPS not ava~l - Lunar flyby or CSM only to lunar orbit (if reqd gtV lt4000 fps)

V37E 47E (check b~as) Record -=--rshy(Limit 98 fpsmm)

( 1fps)tVXYZN62EVIHDOTHPAD (fpsfpslnm)MONITOR VI ( ) at ECO

SCS TVC SERVO PWR 1 - ACIMNA2 - OFF

TAPE RCDR - CMD RESETHBREMS MODE - NORMAL

SIr SEP Lt - ONTLI Inhib~t S~gnals w~11 not be honored after 5942

SIVB ULLAGE BeginsSII SEP Lt - off (TIG - 18 sec)SIVB FUEL LEADSIVB ULLAGE d~scont~nues

LV ENG I Lt - onSIVB IGNITION ( GETI)LV ENG I Lt - off - -shyMONITOR THRUST amp ATTITUDEMONITOR LV TANK PRESSSIVE ECO (Lt on) (BEGIN TB7)

EMER SIVE CUTOFF AT 6 SEC PAST BURN TIME IF VI ATTAINEDTHC CCW ampNEUTRAL IN 1 SEC or SIISIVB sW - LV STAGEPremature Shutdown HAlt4K nm CSM amp 1M -

5700

58205836

F 16 835800

F 16 62

5838594259525955595900000002SUNRISE(___)

HAW AOS(__=_) KEY VERB (freeze d~splay)

SIVB ATT HOLD 20 sec amp BEGIN VENTINGSIVB NNVR TO ORB RT (HDS DN) (3middot sec)

Record VI -c---HDOT _

HPAD _

KEY RLSEF 16 62

F 16 83

HAW LOS(__=-)

KEYmiddotRLSE~VXYZ (lfps)

Record ~VX---_

~vy

WZ--

AVC---_

TAPE RCDR - off (ctr)EMS MODE - STBYEMS FUNC - OFFSECS PYRO ARM (2) - SAFE

PRO

BURN STATUS REPORT

____--~TIG

BT------VGX____-R

-----P----_Y

REMARKS

_____VI

______--HDOT______--H______---AVC______---FUEL_______OXID

_______UNBAL

F 3708=00 OOEGOS AOS CMP TO LEB

(-=-=-)

0000

0003

0005

0014

0100

-55-

62 TLI 10 MIN ABORTSECS LOGIC (2) - on (up)SECS PYRO ARM (2) - ARM

TRANS CONTR - CGH (4 sec) amp +XDET RESET (verlfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS GMD-ON

TRANS GONTR - neutral then +X for10 sec

SIVBGPI s~ - GPIExcesslve rates 6V THRUST A - NORMAL SPS THRUST - DIRECT When rates damped 6V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

TRANS CONTR +X - OFFV37E OOE

PITGH UP to LOGAL VERT (+X axlSto~ard the earth)

RATE - LOWBMAG MODE (3) - ATTIRATE 2EDS PHR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SEGS ARM (2) - opencb EDS (3) - open

TRANS CONTR -X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (180deg)P (199deg)Y (0deg)

RETRO UPDATEGETI _

JV _VG

Jtb ---GET 400K _

05G _GET DROGUE _

ENTRY P _R _

Y_--

0945

-56-

ALIGN HORIZ ON RET +1 MKGMBL CHECK (T11lle Pentattlng)MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conflnn)cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FUMC - JV SETVHF RNGSET JV from chartE~S FUMC - JVEMS fODE - NOIDlAL

lV THRUST A - NORMALV37E 47E (THRUST fONITOR)

F 16 83 lVXYZ (1 fps)

0950

1000

NOTE For aborts durlng 1st mln of TLIKEY V82E F 16 44 (HaHpTff)Burn untll Hp lt 19NM

TRANS CONTR +X

THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN JV reqdJV THRUST (2) - OFFReport cutoff

cb SPS P2 Y2- closeGfBL MTRS (4) - OFF (LMP Confinn)TRANS CONT PWR - OFFTVC SERVO PWR (2) - OFFMN BUS TIE (2) - OFFcb SPS P1amp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREIf est time to EIltOl5500 omlt fCC andenter the SUPERCIRC CKLIST as early as pos-slb1e Pg ~2~3~ __If est time to EI)Ol5500 anticlpate afCC Enter the ENTRY PREP CKLIST at step 9pg 18

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

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DEGREES IN wiiiiDOW

260

z~I- ~ i5 24000

1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

-I

-1-

NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

I LU HD~-

LUHD

lt0 120UJ0

~

80 HOLD PRESENT TRIMgt LU HD013

~Y~HOIgtlt

TOP OF WINDOWa 40to

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80 TTOM OF WINDOWi= 0

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HOLO PRESENT TRIlJCl

LOHU0 lt0

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LDHUlt0 FIELD OF VI S10 NLDHU LIFT-DOWNHEADS -UPLUHD LIFT-UP HEADS-DOWN

~~H~-160 q - P63 LIMITI- NOrE-VALIO ONLY FO~t~--

LUNAR RETURN VELOCITY

plusmnl8020 244middot 8 12 16

TIME TO 400K FT ALTITUDE-MIN

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320

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320

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-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 4: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

-1-

10 INTRODUCTION

The purpose of the Entry Summary Document is to provide a singlesource of entry crew procedure ~nformat~on for use ~n fl~ght planshyn~ng crew tra~n~ng and prepar~ng onboard data The techn~ques

conta~ned ~n this document were generally der~ved from other docushymentat~on and are comblned here to serve as a slngle compacttra~n~ng package

In accordance wlth the Fllght Crew Operatlons Dlrectorate CREWPROCEDURES CONTROL PLAN dated March 1968 the prel~minary ESDedltions are dlstrlbuted for review and comment and simulatorval~datlon unt~l 5 months prlor to launch Thereafter flnal ESDprocedures are d~strlbuted and serve as a control ~ocument withchanges sUbJect to approval by the Crew Procedures Control Board

Comments to thls document should be d~rected to the Fl~ght Proshycedures Branch Fllght Crew Support Dlvislon extens~on 3436

-2-

20 LIST OF ACRONYMS AND ABBREVIATIONS

ComputerPilot

ModuleModuleModule

AccumlatorAmphherAntennaAcqu~s~t~on of S~gnal

Backup Bank AngleBeaconBlunt End ForwardCMC Commanded Bank AngleBody Mounted Att~tude GyroBank Reverse BankCab~n

CommanderCoupl~ng Data Un~t

C~rcuit

CommandCommandCommandCutoffCrew Opt~cal AI~gnment S~ght

Commun~cat~ons

Cryogen~c

Command Serv~ce ModuleCounterCaut~on Warn~ng SystemD~g~tal Auto P~lot

D~g~tal Event P~lot

Drag Acceleration at Sk~pout

Constant Drag Control Accelerat~on LevelD~splay and KeyboardDSKY EnterEnv~ronment Control SubsystemEntry InterfaceEntry Monltor SystemElectrlcal Power SubsystemEssent~al

Flight Combust~on Stab~lity MonitorFI~ght D~rector Att~tude Ind~cator

FunctionAccelerat~on 1n Earth Grav~tatlonal Un~ts

Gu~dance and ControlGround Elapsed TlffieGround Elapsed T1me of Ign~t~on

Gyro Display CouplerGlycolG~mbal

Guidance and Nav~gat1on

ACCUMAMPANTAOSBBABCNBEFBETABMAGBRBCBNCDRCDUCKTCMCMCCMPCOCOASCm1MCRYOCSMCTRCWSDAPDETDLDODSKYEECSEIEMSEPSESSFCSMFDAIFUNCGGampCGETGETIGDCGLYGMBLGampN GIN

-3-

Llst of Acronyms and Abbrevlatlons

GNDGPIG-VHAHEHPIMUKA

LIDLEBIMPLOSLVMANMCCMCC-HMESCMSFNMGAMKMNVRMaNMTRMTVCNOPTORIEN02PPGAPGNCSPIPAPLPLSSpassPRIMPRPLNTPSIAPTTPUGSPWRRRI R2 R3RADRCDRRCSROTREFSMMAT

GroundG~bal Posltlon IndlcatorAcceleratlon-VelocltyHelght of ApogeeHellumHeight of PerlgeeInertlal Measurement UnltDrag Acceleratlon necessary to lnltlate

constant drag controlLlft to Drag RatioLower Equlpment BayLunar Module PllotLoss of SlgnalLocal Vertlcal Llft Vector Launch VehlcleManualMldcourse CorrectlonMlssion Control Center - HoustonMaster Event Sequence ControllerManned Space Fllght NetworkMiddle Glmbal AngleMarkManeuverMonltorMotorManual Thrust Vector ControlDSKY NounOptlon OptlCSOrlentatlonOxygenPltch or CMC ProgramPressure Garment AssemblyPrlmary GUldance Navlgatlon and Control SystemPulse Integratlng Pendulous AccelerometerPlanetPortable Llfe Support SystemPosslblePrlmaryPropellantPounds Per Square Inch AbsolutePush to TalkPropellant Utllizatlon and Gaglng SystemPowerRoll or CMC RoutlneReglster 1 2 3RadlatorRecorderReactlon Control SystemAltltude RateReference to Stable Member Matrlx

-4-

L~st of Acronyms and Abbrev~at1ons

RELRET

RHCRNGROURRT

RSIRTGOSASCSSECSECSSELSEPSEQSFT

SM SIMSPASPSSTBYSXPSXTSTSTATBTBDTERMTFTFFTHBWLSTHCTIGTLITIl TLMTRNFR

TVCVVGVIOVLVMY

Rel1efReentry Elapsed TIme (Lunar Return Case) or Retro

Elapsed Time (Earth Orb~tal Case) For lunar returnsRET 1S zero at RRT For earth orb1tal entries RET iszero at the deorb1t burn tIme

Rotat1onal Hand ControllerRangeRout1neReentry Reference T~me (Based on MCC-H predicted time

of EI to nearest second)Roll Stab11~ty IndicatorRange to GoShaft AngleStab1lizat1on and Control SystemSecondarySequent1al Events Control SubsystemSelectSeparationSequentialShaft Angle for SXTS when spacecraft 1S at

ignit10n attitudeServ1ce ModuleCOAS Star P~tch AngleServ1ce Propuls~on SystemStandbyStar X Pos~t~on (COAS)SextantSextant StarTrunnion AngleTalkback D~splay T1me BaseTo Be DeterminedTerm~nate

Ttme FromTtme of FreefallThumbwheelsTranslational Hand ControllerTime of Ignit~on

Translunar Insert10nTelemetryTransferThrust Vector ControlVeloc~ty or DSKY VerbVeloc~ty To Be GatnedInertial Veloc~ty

Sktpout Veloc1tyVeloc~ty MeasuredYaw

-5-

3deg LUNAR REIUBN ENTRY TECHNIQUES

The t~mel~ne for lunar return entries is based on the recommendationsfound ~n reference 1 the s~mulator val~dated procedures ~n reference2 and the mission val~dated procedures listed in the onboard checkshylist for the C Pr~me m~ssion The event times are l~sted ~n reference3

The preparation for lunar return entr~es beg~ns at a conven~ent t~me

about 30 hours before entry ~nterface At th~s t=e MSFN sends up alldata suff~c~ent for reentry also an EMS entry selftest ~s made toassure max~mum confidence ~n the EMS operat~on during entry Thereshyafter var~ous system powerups and checks are ~n~t~ated as l~sted insect~on 51 and deta~led ~n reference 4 Nom~nally the PGNCS ~s upfor the ent~re m~ss~on However ~f ~t ~s not ~t ~s powered up atEI-7 hours ~n preparat~on for the last MCC and entry The last MCCdec~s~on ~s made at about EI-6 hours for the maneuver to be performedat EI-3 hours ~f needed Deta~ls of th~s maneuver are outl~ned ~n

reference 1 After the MCC time P52 ~s again selected and the IMU ~s

real~gned to the REFSMMAT If the IMU dr~ft ~s w~th~n tolerance thesubsequent IMUSCS dr~ft check will determ~ne if the SCS has dr~fted

excess~vely If so the other BMAGs are selected and the IMUSCScheck repeated Th~s check ~s followed by a repeat of the EMS ~V

counter check and accelerometer b~as check at EI-l hour 15 m~nutes

to determ~ne ~f the scale factor and b~as are adequate for entrymon~tor~ng F~nal stowage CM RCS preheat and pyro Cllcu~t and seshyquent~al tests are worked ~nto this t~meframe so that at EI-50 m~nutes

the MSFN w~ll be requested for a go to pyro arm by the crew ~n preparashyt~on for separat~on At 45 m~nutes before EI the CMC update programP27 can be selected to permit update of the landing po~nt locat~on andthe state vector The entry PAD data shown ~n sect~on 70 ~s thenvo~ced to the crew and recorded From th~s data the DET ~s set andstarted the EMS ~nit~al~zed and the RSI al~gned Prior to EI-20ffilnutes the crew w~ll have strapped-~n completed the~r presepara-t~on checkl~st and maneuvered to the entry att~tude At this pointEI-19 m~nutes the CMC entry program Fbl ~s selected by the CMP Ifthere was no entry PAD data because of commun~cat~on loss the veloshyc~ty and range to go from P61 ~s recorded and used ~n the EMS AtEI-15 m~nutes the spacecraft ~s p~tched down and the hor~zon ~s checkedagainst the 317 degree w~ndow scr~be l~ne and the FDAI att~tude Ifthere ~s s~gn~f~cant d~sagreement the PGNCS ~s suspected and the spaceshycraft ~s held on the w~ndow reference In P62 the spacecraft ~s yawed45 0 from th~s att~tude and separated from the SM After separat~on

the CM ~s yawed back ~n plane and the hor~zon check repeated At approxshy~mate1y EI-10 m~nutes the p~tch att~tude is w~th~n 450 of the CMCcommanded att~tude and P63 ~s entered automat~ca11y S~nce the CMCDAP tr~es to hold local p~tch attitude and the CMC ~s not ~n controlthe crew observes the p~tch error needle unpeg and approach zeroabout two m~nutes before 05g t~me Th~s serves as a gono go CMC

-6-

check for entry control If the FDAI pltch error does not decreaseto wlthln + 50 at 005g the PGNCS lS fa lied and the crew flies aconstant g-entry mode wlth EMS ranglng after the VelOClty decreaseto 25500 feet per second If the PGNCS lS acceptable the spaceshycraft control lS placed In CMC and the CMC mode lS placed ln autoshymatlc At 05g the EMS automatlcally starts lf the EMS mode sWltchwas posltloned to automatlc earller ThlS wlll be backed up manually3 seconds after the ground computed 05g tlme recorded on the entryPAD by placlng the EMS mode sWltch In manual lf lt has not startedautomatlcally At PGNCS 005g lndlcatlon the CMC program changesto P64 and from thls pOlnt the entry lS under entry DAP control

The lunar return entry nomlnally lS performed by the PGNCS to lnsurecontrol wlthln the overshoot and g llmlt llnes as well as optlmlzethe landlng point accuracy Although the hlgh speed entry lnvolvesa rapld sequency of events there are several monitorlng tasks forthe crew to determlne lf the automat~c contrails performlng correctly

An entry corr~dor ver~flcation check 1S made by observlng the lnltlalslope of the EMS V-g trace between 1 and 2 gs If the EMS lndlcatesthe need to reverse the LV orlentatlon and the lndependent g meterconflrms the EMS g lndlcatlon the SC lS immedlately orlented as aresult of the EMS ~nd~cat~on

The EMS g lnd~catlon ~s contlnuously checked durlng entry uSlng thelndependent g meter and the PGNCS g ~ndlcatlon as a thlrd voteDeC1Slons durlng the first entry (P64) are critlcal ln terms of bothexceSSlve g llnes and the PGNCS lS not commandlng (and SC respondlng)to correct the sltuatlon the PGNCS lS felled

The PGNCS gono go check for short range targets (1200-1400 n ml) forWhlCh P65 lS not used 1S d1fferent Slnce there are no CMC computedSk1p drag (DL) and skip velocity (VL) values The check uses the EMSscroll to determ1ne 1f the PGNCS lS commandlng the proper roll att1shytude to converge the EMS g level to a predetermlned PAD value (Do) ascomputed by MCC-H For the nom1nal target range of 1300 naut~cal

mlles the crew w1ll monltor the program change from P64 to P67 atapprox~matelyEI + 3 mlnutes For ranges greater than 1400 nauticalmlles the program w1ll transfer to the Upcontrol Program P65 whenVL ~s between 18000 and 25766 feet per second and constant drag hasbrought the CMC pred1cted range to wlthln 25 naut1cal m1les of thetarget range The P65 PGNCS gono go check cons1sts of determln1ng1pound both the DSKY d1splay of sk~pout drag (DL) and Sk1pout veloclty(VL) are w1thln the PAD llmlts In addltlon the EMS scroll lS mon1shytored to determ~ne lf the trace lS approach1ng the DL and VL values

Throughout entry the crew monltors the spacecraft response to the CMCroll commands by observlng the FDAI lndlcatlons If the commands are

-7-

apparently good and In agreement wlth the EMS but the spacecraftresponse is questlonable the crew manually takes over and fIlesthe CMC commands

If the Upcontrol Program P65 was entered the program wlll nomshylnally sWltch to the Flnal Entry Program P67 for target rangesbelow approxlmately 1800 nautlcal miles or to the Ballistlc Proshygram P66 for ranges greater than approxlmately 1800 nautlcalffilles The program transfer crlterla are more preclsely deflnedIn reference 1

If P66 lS entered the spacecraft lS automatlcally rolled to theIlftup heads-down attltude to permlt the horlzon to be vlewedfrom the wlndow durlng the second entry The entry attltude checklS made by comparlng the horlzon wlth a speclfled wlndow mark Ifthe check falls the crew manually malntalns the entry trlffi attltudeuSlng the horizon VleW for reference The EMS lS used for ranglngSlnce the veloclty has now decreased to below 25500 feet per second

The EMS scroll lS contlnuously used to monltor for exceSSlve g conshydltlons durlng the second entry If the EMS V-g trace vlolates theg Ilnes and the PGNCS lS not commandlng (and spacecraft respondlng)to correct the situatlon the PGNCS lS falled and the EMS lS usedfor ranglng after ltS g lndlcatlon has been conflrmed by the lndeshypendent g meter

The entry phase lS essentlally over when the relatlve veloclty ofthe spacecraft decreases to less than 1000 feet per second ThlSlS lndlcated In P67 when RTGO latltude and longltude are dlsplayedSlnce very Ilttle ranglng capablllty exists after thls pOlnt thespacecraft lS orlented elther full Ilft up or down dependlng on RTGOnegatlve or posltlve and the crew prepares for the earth landlngphase

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-13-

40 EARTH ORBITAL DEORBIT AND ENTRY TECHNIQUES

As outl~ned ~n reference 5 a nom~nal PGNCS entry from earth orb~t ~s

based on a preparat~on t~me of 2 hours and 40 m~nutes ~nclud~ng 2n~ght passes Th~s t~me ~ncludes approx~mately 20 minutes before thef~rst n~ght pass after the CMC update and PAD data have been rece2vedTh~s t~e also 2ncludes approx2mately 20 m2nutes after the secondn~ght pass to allow suffic~ent t2me to prepare for retrof2re after theIMU f2ne a12gnment It has been determ2ned coarse a12gnment accuracy~s adequate for retrof~re and entry and undoubtedly other funct20nscould be om2tted depend2ng on the c2rcumstances for the dec2s20n toreenter Descr2bed here2n are the nom2nal earth oro2tal entry proshycedures w2th pert2nent comments on system va12dat20n for real timeacceptance dec~s20ns

After the entry dec~s~on is made the crew transfers the PGNCS fromthe standby to the operate mode and rece~ves a CMe update w~th P27Next the maneuver PAD update ~s v02ced up and the 2n~t~al entry mode~s determ~ned During the ~n~tial n~ght pass the IMU or2entat~on ~s

estab12shed uS2ng P51 star s~ght2ngs to obta2n a REFSMMAT The preshyferred or~entat~on opt20n ~n P52 2S then selected to coarse a12gn theIMU uS2ng the des2red entry REFSMMAT determ2ned by MGG-H The GOO ~s

now al~gned to the IMU 2n preparat~on for an IMUSes dr~ft check Ifthe GOO ~nd~cates the ses dr2ft rate exceeds 10 degrees per hour ~n

any ax~s the check ~s repeated on the other BMAGs to estaol~sh if theGOO or Just the single set 2S unusuable Var20us sytem checks as 12sted2n sect20n 51 are performed as necessary cons2stent w2th the t2me12ned2ctates of the maJor act2v2t2es Included 2n these checks are the EMSself-tests and the dV counter test The latter requ2res the spacecraftbe placed ~n dr2ft2ng fl2ght w~th the funct20n sW2tch 2n the dV pos2t~on

If the counter reg2sters a change of more than 25 feet per second w2th2n100 seconds the scroll and counter are unre12able for mon2tor2ng thedeorb2t burn and entry rang2ng If the EMS self-test fails and t2medoes not allow further analysis a 5555 ERE entry 1S planned as thePGNGS backup entry mode After complet2on of these checks the entryPAD lS prov1ded by MeG-H The crew then selects the external dVprogram P30 and the appropr2ate deorb1t tbrust1ng program p40 or P41Dur2ng th2s per2od wh2ch 2ncludes the f1nal n2ght pass P52 may beselected to ver2fy the IMU a12gnment Since the retro att2tude hasbeen computed so that a w2ndow mark c01nc2des w2th the hor2zon atGETI th2s serves as the conclus2ve check on the PGNCS At 5 m2nutesbefore retrofire the att2tude check 1S made by ver1fY2ng that the 12degree scr~be 12ne ~s w2th2n 3 degrees of the hor2zon If not thePGNeS has fa2led and the ses 2S used for att2tude reference and the

V counter for burn durat~on control S2nce the ses att~tude wasa12gned to the IMU a real~gnment ~s necessary This ~s accompl~shed

by manually maneuver2ng the spacecraft to ma~nta1n the 24 degree wlodowmark on the hor2zon and releas1ng the GOO a12gn button at TIG - 2 m2nutes

-14-

Upon complet~on of the burn the tN res~duals are burned to W~th~n

02 feet per second If the PGNCS ~V counter or est~mated burnduration are ~n d~sagreement ~t must be estab1~shed whether suff~shy

c~ent veloc~ty has been suppl~ed to put the land~ng po~nt in thefootpr~nt The PGNCS data w~ll be used ~f ~t ~s conf~rmed by oneother source if not the ~V counter w~11 be used ~f ~t ~s conf~rmed

by the burn durat~on t~me If add~tional ~V ~s necessary the data~s ava~lable to the crew on an onboard chart found ~n Sect~on 80

Post burn entry preparat~on requ~res EMS ~n~t~al~zation RSI al~gnshy

ment and pre-separat~on funct~ons The crew then selects the ~n~t~al

entry program P61 and records the d~sp1ays as a check aga~nst PADdata Upon complet~on of these checks P62 ~s entered The crewmanually or~ents the spacecraft to the separat~on attitude and yaws450 to ~nsure aga~nst possible CM 8M recontact After separat~on

the spacecraft ~s maneuvered to the reentry tr~m att~tude wh~ch

places the hor~zon on the 3170 w~ndow mark at EI Shortly thereshyafter ~n P62 the entry DAP is act~vated and P63 in~t~ated Dur~ng

th~s t~e MCC-H has computed a postburn update and ~t ~s vo~ced tothe crew ~f d~fferent from preburn values The EMS scroll and rangecounter w~ll be adJusted accord~ngly ~f t~me perm~ts A f~nal PGNCScheck pr~or to 05g may be mon~tored at th~s t~e w~th the CMC modein free and the manual att~tude p~tch ~n acceleration command wh~le

the hor~zon reference ~s held the p~tch error needle w~ll decreaseto zero as EI ~s reached At RET 005g the EMS mode sw~tch ~s

turned to manual the entry 005-g sw~tch and EMS roll sw~tch areturned on and the spacecraft control sw~tched to CMC to beg~n DAPcontrol At the PGNCS 005-g ~ndicatwn the program change fromP63 to P64 ~s mon~tored and the t~e vo~ce recorded At th~s t~me

the EMS range counter check ~s made dur~ng the 10 second per~od

follow~ng EMS 005g Dur~ng th~s per~od the counter should countdown 40 + 10 naut~cal m~les At PGNCS 02-g ~nd~cation the changefrom P64-to P67 ~s monitored and the ~splay may be held by key~ngVERB ~n order to record the init~al downrange error d~splay andcompare ~t to the PAD value The PGNCS has fa~led ~f the two do notagree w~th~n + 100 naut~cal m~les In the event P67 has not appearedwhen both the-g-meter and the scroll ~nd~cate greater than 05g thePGNCS has sim~lar~ly fa~led In e~ther fa~lure the SCS is used foratt~tude reference w~th an EMS entry If the checks agree the crewrema~ns w~th automat~c DAP for the rema~nder of the entry

The entry phase ~s essentially over when the relat~ve velocity ofthe spacecraft decreases to less than 1000 feet per second Th~s

~s ~nd~cated ~n P67 when RTGO lat~tude and long~tude are d~splayed

S~nce very l~ttle rang~ng capab~l~ty exists after th~s pOint thespacecraft is or~ented either full l~ft up or down depending onRTGO negat~ve or pos~t~ve and the crew prepares for the earth land~ng

phase

-15-

41 TYP~cal Retrof~re and Entry Sequence of Events

Dec~s~on to reenter

P27 (CMC update)

Retrof~re PAD update

Entry mode dec~s~on

P51 (IMU or~entat~on determlnatlon) durlng f~rst dark per~od

P52 (IMU coarse allgnment)

EMS checks

Entry PAD update

P30 (external AV)

p40 (SPS thrust)

P52 (IMU f~ne al~gnment) durlng second dark per~od

p40 (SPS thrust)

Ign~t~on att~tude check

Retroflre

P61

P62

CMSM separat~on

P63

Postburn PAD update

Entry attltude check

p64 (beg~n DAP control at O05g)

P67 (PGNCS gono go check at O2g)

42

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and

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-17-

5 0 DETAILED ENTRY PROCEDURES

In order to comblne slmilar procedures that are common to lunar returnentrles and earth orblt entrles the followlng procedures are dlvldedlnto categorles that allow a mlnlmum of dupllClty ThlS provldes asmaller tralnlng package and more closely resembles the onboard crewcheckllst when comparlson lS necessary

51 Entry Preparatlons for Superclucular and Earth Orbltal Entrles

1~e entry preparatlons are comblned In these procedures andsteps pecullar to elther superclrcular or earth orbltal entrlesare labeled accordlngly The tlme llstlngs In thlS sectlon areappllcable to only superclrcular entries Slnce the earth orbltalentry tlmellne lS a functlon of several varlables as descrlbedIn sectlon 40 and reference 5

-18-51 (Contlnued)

VEHICLE PREPARATION

l-

2

3

4

5

6 -0600h

7 -0535h

8

9

10 -0430h

INITIAL STOWAGE COMPLETED

CMC amp ISS START UP

SCS POWER UP

p51 - IMU ORIENTATION

LOAD DAPV48E 11102 01111 PRO ERO PRO

LAST MCC DECISION

NO COMM - P52 amp NAV SIGHTINGSNOMINAL - P2337 ONBOARD COMPARISON

DON MAE WESTS amp FOOT RESTRAINTS

VHF AM A - SIMPLEX

P 27 (SV REFSMMAT) MNVRamp ENTRY pAD UPDATES

11 -0415h P52 - IMU REALIGN(___) (OPTION 1)

12 P37 (NO COMM ONLY)

13

14

ECS CKS02 SUPPLY REFILLECS Monitor CkEVAP H20 CONT (2) vlvs - AUTOSUIT HEAT EXCH SEC GLY - FLOW

EPS CKS 1 3 4 (5 If reqd)

15 SPS CK (If req d)

16

17

18

RCS CKSSM RCS MOUlt CkCM RCS MOUlt Ck

CampW SYS CK

CMC SELF CK

19

20 -0345h

-03l5h-0300h

21

22

22A

-19-

DSKY COND LT TEST

MIDCOURSE MANEUVERP30 - EXT rVP404l - SPSRCS THRUSTINGMIDCOURSE (17) BURN

NO COMM NAV SIGHTINGS

ffiVR TO ENTRY ATT (Superc1rc only)V62E

V49E

22B F 06 22 DESIRED FINAL GMBL ANGLESLOAD ENTRY ATT PAD ANGLESPRO

22C F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) SC CONT - CMC

BMAG MODE (3) - RATE 2CMC MODE - AUTO

PRO(~N) SC CONT - SCS

MNVR to 22E

22D 06 18 AUTO MNVR TO FDAI RPY ANGLES

22E F 50 18 REQUEST TRIM(TRIM) Go to 22C(BYPASS) ENTR

23 -200hr BORESIGHT amp SXT STAR CHECKOPT MODE - CMCOPT ZERO - OFF

V41 N91E

F 21 92 SHAFT TRUNLoad SXTS angles

41 OPTICS DRIVE

CHECK SXT STAROPT ZERO - ZERO

CHECK BORESIGHT STAR (If ava11)

24 -0135h

25(___)

26

27 -0115h

-20-

P52 - lMU REALIGNRecord gyro torqu~ng anglesRp~----

YIf-7gt-Lno--re-c-ycle PS2If conflrmed use SCS for EMS entry

GDC ALIGNIf drlft gtLOohr change ratesource

FINAL STOWAGEOPTICS (except for hybrid)ORDEALGLY TO RAD SEC - BYPASS (verlfy)CooL pnl lnstalledY-Y struts (2) extendedStow Data Box R-12

EMS CHECKEMS FUNC - OFFcb EMS (2) - closeEMS MODE - STBYEMS FUNC - EMS TEST 1 (walt 5 sec)EMS MODE - NORMAL (walt 10 sec)

Check ind lts - offRANGE lnd - 00Slew halr1ine over notch

In self-test patternEMS FUNC - EMS TEST 2 (walt 10 sec)

05G It - on (all others out)EMS FUNC - EMS TEST 3

05G It - onRSI Lower It - on (10 sec Qater)Set RANGE counter to 58 nm+OO

EMS FUNC - EMS TEST 405G It - on (all others out)G-V trace w~thin pattern to lwr rt

corner 9GRANGE lnd counts down to 0+02

EMS FUNC - EMS TEST 505G It - onRSI upper lt - on (10 sec later)RANGE md - 00SCrlbe traces vertlcal llne 9g to

022+01ALIGN SCROLL TO ENTRY PATTERN (on

37K ft sec hne)EMS FUNC - RNG SET

G-V scroll assy traces vert llne022g to 0+01

EMS MODE - STBY

28

29

30 -OllOh

-21-

~V TEST (Deorb~t only)EMS FUNC - ~V SETVHF RNGSET ~V ~nd to 15868 fpsEMS MODE - NORMALEMS FUNC - ~V TEST

SPS THRUST LT - onoff (10 sec)~V ~nd stops at -01 to -415

EMS MODE - STBY

PRIMARY WATER EVAP ACTIVATIONGLY EVAP H20 FLOW - AUTOGLY EVAP STH PRESS - AUTOPRI ECS GLY PUMP - ACI

CM RCS PREHEATNote If sys test mtr 5cd6abcd

all read 39 vdc (28degF) or moreom~t preheat

cb RCS LOGIC (2) - closeCM RCS LOGIC - ONUP T1M CM - BLOCK (ver~fy)

cb CM RCS HTRS (2) - closeCM RCS HTRS - ON (LMP Conf~rm)

(20 mlU or III lowest rdg lS39 vdc) (Moultor Maufpress for press drop)

31 (___) FINAL GDC DRIFT CK (If req I d)If drlft gtlOohr Suspect GDC Do not

use RSI amp FDAI 2

32 -OO5Om

33

34

35

TERM CM RCS PREHEATUP TLM CM - BLOCK (venfy)CM RCS HTRS - OFFCM RCS LOGIC - OFF

SYSTEMS TEST PANEL CONFIGURATIONSYS TEST METER - 4BRNDZ XPNDR - OPERATECM RCS HTRS - OFFWASTE H20 DUMP - OFFURINE DUMP - OFF

LEB LIGHTING - OFF

SEC WATER EVAP ACTIVATIONGLY To RAD SEC vlv - BYPASSSEC COOL EVAP - EVAPSEC COOL PUMP - AC2

36

37

38 -OO45m

-22-

PYRO BATT CKcb PYRO A SEQ A - close (ver~fy)

cb PRYO B SEQ B - close (verify)DC IND - PYRO BAT A(B)

~If PYRO BAT A(B) lt 35 vdc cb PYRO A(B) seq A(B) - open~

PYRO A(B)BAT BUS A(B)TO PYRO~MN BUS TIE - close

cb MNA BAT C - closecb MNB BAT C - closeDC IND - MNBPNL 8 - All cbs closed except

PL VENT - open (ver~fy)

FLOAT BAG (3) - open (ver~fy)

DOCKING PROBE (2) - open (verlfy)EDS BAT (3) - open (ver~fy)

CM ReS HTRS (2) - open

CM RCS ACTIVATIONcb SECS ARM (2) - close (verlfy)cb SECS LOGIC (2) - close (verlfy)SECS LOGIC (2) - ONMSFN conflrm GO for PYRO ARM(~f poss)SECS PYRO ARM (2) - ARMCM RCS PRPLNT 1amp2 - ONCM RCS PRESS - ONRCS Ind sw - eMl then 2

He PRESS 3700-4400 pSlaMANF PRESS 287-302 pSla

SECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFF

P27 amp ENTRY PAD UPDATEGo To Entry Checkllst

Superclrc - pg ~2~3 _Hybnd - pg -----2~9L-__Normal Deorblt - pg __3L5L- _

-23-

52 SUPERCIRCULAR ENTRY

1 SET DET (up to ET)

2

3

4

5

3000(-30-00)

EMS INITIALIZATIONSET RNG TO PAD DATA RNGEMS FUNC - Vo SETSlew Scroll to Pad Data VIOEMS FUNC - ENTRY

RS I ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on (up)GDC ALIGN PB - PUSH amp HOLDYAW Tw - Pos~t~on RSI thru

45deg amp back to LIFT UPGDC ALIGN PB - ReleaseEMS ROLL - OFFA1~gn CDC to lMU

CM RCS RING A CKRCS TRNFR - CMcb CM RCS LOGIC MNB - openAUTO RCS SEL MNB (6) - OFFSC CONT - SCSTest R~ng A ThrustersSC CONT - CMCRCS TRNFR - SMAUTO RCS SEL (12) - MNAMNB

(hftoff conflg)cb CM RCS LOGIC MNB - close

OPTICS PWR - OFFCMP to COUCH

MN BUS TIE (2) - ONTAPE RCDR - REWIND

6 35middot0Om(-25middot 00)

-24-

SEPARATION CK LISTTVC SERVO PWR 1 - AClMNAcb ELS (2) - close (ver1fy)PRIM GLY TO RAn - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY vlv - OFFCAB PRESS REL vlv (2) - NORMGMBL MTRS (4) - STARTABORT SYS PRPLNT - RCS CMD (venfy)SM RCS PRIM PRPLNT (4) - ONVHF 11M (AampB) - OFFHI GAIN ANT PWR - OFFFC PUMPS (3) - OFFVer1fy s1ugle SU1t compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - 10101cb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2) - opencb HTRS OVLD (2) - openPOT H20 RTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANSEC COOL EVAP - RESETSEC COOL PUMP - off (etr)

MtiVR TO CMSM SEP P R ATTSC CONT - SCSCMC MODE - FREEMNVR TO PAD ATTR (0deg)PY----W)

-25-

SUPERCIRCULAR ENTRY (Cont~nued)

1

4100m(-1900)

P61 - ENTRY PREP

V37E 61E

k 05 09 01427 - ROLL REVERSED 05 09 01426 - IMU UNSAT ~

2 F 06 61 IMPACT LAT LONG HDS UPDN (+-)PRO (010

fps +00001)

3 F 06 60 GMAXVPREDGAMMA EIRecord

GMAXV400K----

GAMMA EI _PRO

(01deg fpsOldeg)

4 F 06 63 RTOGO (lnm) PAD _VIO (fps) PAD _TFE(m~n-sec)

Compare w~th ~M~SFN==C~f~o-r~P~GNS GONO GOIf NO COMM Set RTOGO amp VIO In EMS

amp lnltla11ze(ACCEPT) PRO(RECALC) V32E To 4

5 F 50 25

4300m

(-1700)

45 oOm(-1500)

500Om(-1000)

6 F 06 61

-26-

P62 - CMSM SEP amp PRE-ENTRY MNVRCAUTION Call No EXT Verbs In P62

00041 REQUEST CMSM SEPSC CONT - SCSFREE

COMPARE PITCH ATT WITH PAD DATA ---0=-

(W~thLU 5deg)YAW - 45deg OUT-OF-PLANE (LEFT)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTIRATE 2MN BUS TIE (2) - ON (ver~fy)

PRIM GLY TO RAD - BYPASS (verlfy)CM RCS LOGIC - ON (venfy)SECS LOGIC (2) - on (up)SECS PYRO ARM - ARMCMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 ps~a

CM RCS LOGIC - OFFSECS PYRO ARM (2) - SAFEMonltor VMAB

If lt25 vdc go to EMERGPOWERDOWN pg E6-l

AUTO RCS SEL AC ROLL (4) - OFFAUTO RCS SEL CM 2(6)-OFFAUTO RCS SEL CM 1(6)-MNAYAW back to 0degPITCH TO HORIZ TRACK ATT

ROLL - 0deg (LIFT UP)PITCH - 400K Horiz Mark (317deg)YAW - 0deg

ATT DB - MAXMAN ATT PITCH - ACCEL CMDEMS DATA - Ver~fy

EMS FliNC - ENTRY (ver~fy)

EMS MODE - NORMALcb SPS PampY (4) - openMAINT HORIZ TRK

PRO (Act ENTRY DAP)

IMPACT LATLONGHDSDN (01deg01deg-00001)PRO

7 POSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axis beyond 45deg of Vel vector)

8 06 64

58middot00m(-0200)

9

05G tlme(+0 )

(--=---)

06 68

-27-

P63 - ENTRY INIT

GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PIJR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRmDHORIZ CKPltch error needle goes toward

zero approachlng OSG tlmeMAN ATT (PITCH) - RATE CMD

If CMC lS GOBMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS I

FLY BETA If CMC NO GO ilt

1 SC CaNT - SCS I

FLY EMS k

p64 - ENTRY POST 05G

RTOGO AT 05G AGREES HITH EMS-venfyHORIZ CK05G Lt - ON (EMS START)

No EMS START wlthln 3 sec ~ EMS MODE - BACKUP VHF RNG c

05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds Llft DN

NNVR Llft DNEMS GONO GO

G-V Plot wlthln IlmltsRng ctr dwn 60plusmn7 durlng 10 sec

perlodMonltor G-meter for

convergence wlth pad data (Do)(Vlt27K fps) Go to 13

-28-

P65 - ENTRY - UP CONT (Vgt27K fps)

10 F 16 69 BETA (01middot) _DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT lt~ SC CONT - SCS FLY EMS

PRO

11 06 68 BETAVIHDOT (OIdegfpsfps)(VltV1+500 fps amp RnOT Neg) Go To 13

P66 - ENTRY - BALLISTIC (D(DL)

12 06 22 DESIRED GMBL ANGLES RPYMoultor horlz +12middot of 317middot mark

P67 - ENTRY - FINAL PHASE (02G)

13 06 66 BETACRSRNG ERRDNRNG ERR(010 1um 1um)

KEY VERBRecord DNRNG ERR _KEY RLSEMoultor l~ft vector ou RSI amp FDAI

16 67 RTOGOLATLONG (Vrel=1000fps)(lumOldegOldeg)

SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOWNMonitor a1t~meter

Go To EARTHLANDING pg ---4L5 _

-29-

53 GampN HYBRID DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL tV1 V37E 30E

2 F 06 33 GETI(ACCEPT) PRO (hrm~n Olsec)(REJECT) LOAD DESIRED GETI

3 F 06 81 tVXYZ (LV) (lfps)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

4 F 06 42 HAHPtV (lnm lfps)Record tV

(ACCEPT) PRO(REJECT) Reselect P30 or P27 Load new paramo

5 F 16 45 MTFIMGA (marksm~n-secOlO)

MGA -00002 ~f k

k lMU not al~gned

SET DETPRO

6

7

8

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (Pull)PLSS 02 vlv - FILL02 8M SUPPLY vlv - OFFCAB PRESS REL vlv (2) - NORMcb ELS (2) - closecb SECS ARM (2) - closecb SECS LOGIC (2) - close (ver~fy)

AUTO RCS SEL CM (12) - MNA or ~ffiB

(hftoff conhg)ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM (AampB) - OFF

CMP to Couch

9

10

11

-30-

MNVR TO PAD BURN ATTLOAD DAPBMAG MODE (3) - RATE 2SC CONT - CMCAUTOATT DB - MINMAN ATT (3) - RATE CMD

v62E

v49E

12 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLES

PRO

13 F 50 18 REQ MNVR TO FDAI RPY ANGLES (01deg)(AUTO) PRO(MAN) SC CONT - SCS

BMAG MODE (3) - RATE 2MNVR To 15

14 06 18 AUTO MNVR TO FDAI RPY ANGLES (01deg)

15 F 50 18 REQ TRIM TO FDAI RPY ANGLES (01deg)(TRIM) Go to 13(ByPASS) ENTR

16

17

CHECK BORESIGHT amp SKT STARSOPT MODE - CMCOPT ZERO - OFF

v41 N91E

18 F 21 92 SHAFTTRUN (01deg 001deg)Load SXTS angles

19 41 OPTICS DRIVECheck SKT STAR

OPT ZERO - ZEROCheck BORESIGHT STAR (~f ava~l)

20 V25 N17E (01deg)Load Pad Data GMBL Angles

for CM BURN ATTATT SETtw - SET

to PAD DATA GMBL ANGLESfor CM BURN ATT

21

22

-31-

PHR REDUCTIONHGA PHR - OFFFC PUMPS (3) - OFFVerify s~ngle su~t compr oper loads

balancedFC 2 MN AampB - OFFS BD PiR AMP - LOWcb ECS RAD CONTHTR (2) - opencb HASTE H20URINE DUMP HTRS(2)- opencb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANMN BUS TIE (2) - ONTVC SERVO PHR 1 - AC1MNAGMBL MTR (4) - START

p41 - RCS THRUSTINGV37E 41E

23 F 50 18 REQ MNVR TO LCL HORIZ (HDS ON)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CMCAUTOPRO To 24

(gtfANDAP) BMAG MODE (3) - RATE 2SC CONT - CMCHOLD

V62EMNVR To 25

24 06 18 AUTO MNVR TO FDAI RPY

25 F 50 18 REQ TRIM TO LCL HORIZ (01deg)ALIGN SC ROLL

(AUTO TRIM) PRO To 24(BYPASS) ATT DB - MIN

RATE - LOHMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTlRATE 2

ENTR

550Om26 06 85

59middot2527

-32-

VGXYZ (1fps)RECHECK BORESIGHT STARTRANS CONIR PWR - on (up)EMS MODE - STBY (ver~fy)

EMS FliNC - bV SETVHF RNGSET (IV for SM BURN _EMS FliNC - bVS BD ANT - OMNI CSECS LOGIC (2) - ONMSFN conhrm Go for PYRO ARMSECS PYRO ARM (2) - ARMCM RCS LOGIC - ON (ver~fy)

DSKY BLANKS

593028 16 85 VG XYZ (AVE G ON) (lfps)

RHCs amp THC - ARMEDLIMIT CYCLE - OFFTAPE RCDR - CMD RESETHBREMS MODE - NORMAL

000029 F 16 85 REQ NULL VG XYZ (lfps)

BURN EMS bV CTR TO ZERORESET DET amp COUNT UP

If SM ONLY burn go to step 32THC - LOCKEDSC CaNT - SCSFREERATE - HIGHPRIM GLY To RAD - BYPASS (ver~fy)

MN BUS TIE (2) - ON (ver~fy)

CMSM SEP (2) - on (up)CSMLM FNL SEP (2) - on (up) (verify)CampW MODE - CMRCS TRNFR - CMCM RCS LOGIC - OFF

Momtor VM ABIf lt25 vdc go to EMERGPOWER DOWN Pg E6-l

V63E

If CMC NO GO FDAI SOURCE - ATT FDAI SEL - 1 or 2 ATT SET - GDC

SET

-33-

~Uili ATT PITCH - ACCEL CMDFDAI SCALE - 55MNVR TO CM BURN ATT (NULL ERR NEEDLES)

R 0degPY --00--

30

31

CM RCS BURNRHC III-ContJnuous PJtch DownRHC HZ-Module PJtch to null needlesBURN VGZ TO ZERO

If only 1 RHC Pulse + P=5deg from retro att MaJnta~n rates lt3degsec

BURN COMPLETION ATllV CTR= or DET= _

V8ZE

32 F 16 44 HAHPTFF (1nmffiJn-sec)Check HP-

If gt Pad data contJnue burnuntJ1 lt Pad

PRO

33 F 16 85 VGXYZ (Ups)Read VG resJduals to MSFN

(HYBRID) PRO to 34(SM ONLY BURN)

PROF 37 ODE

EI-1500 V37E 47EF 16 83 twx Y Z (Ups)

SC CONT - SCSFREEMAN ATT (PITCH) - RATE CMDRATE - HIGHPRIM GLY To RAD - BYPASS (verJfy)MN BUS TIE (2) - ON (verJfy)CMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verJfy)Campl MODE - CMRCS TRNFR - CMCM ReS LOGIC - OFFSECS PYRO ~I (2) - SAFE

-34-

PROMonitor VMAB

If lt25 vdc go to EMERGPOWER DOWN

34 F 37 OOEPCM BIT RATE - LOWATT DB - MAXEMS MODE - STBYEMS FUNC - OFF

Go To EARTH ORBIT ENTRY pg _--40-__

-36-

8 SPS THRUSTING PREPCYCLE CRYO FANSSPS GAGING - ACI (ver~fy)

PUG MODE - NORM (venfy)BMAG MODE (3) - RATE 2tv CG - CSMCMC MODE - FREEAUTO RCS SEL (16) - MNA or HNB

(hftoff conbg)SC CONT - CMCAUTO

9 MNVR TO PAD BURN ATTV62E

10 V49E

11 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLESPRO

12 F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) PRO(HAN) SC CONT - ses

MNVR to 14

06 18 AUTO MNVR TO FDAI RPY ANGLES13

14 F 50 18 REO TRIH TO FDAI RPY ANGLES(TRIM) Go to 12(BYPASS) ENTR

15 BORESIGHT STAR CHECK

16 V37E 40EOPT PWR - OFF

17 F 50 18 REQUEST MNVR TO FDAI RPY ANGLES (01deg)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CHCAUTOPRO to 18

(MANDAP) BMAG HODE (3) - RATE 2SC CONT - CMCHOLDMNVR to 19

(HANseS) se eONT - sesMNVR to 19

-35-

54 NORMAL DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL ~V

1 V37E 30E

2 F 06 33 GETI (hrm~nOlsec)

(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

3 F 06 81 ~VXYZ (LV)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

( lfps)

4 F 06 42 HAHP~V (1nmlfps)Record W

(ACCEPT) PRO -----(REJECT) Rese1ect P30 or P27 Load new pa~am

5 F 16 45 MTFIMGA (marksmln-secOldeg)MGA -00002 If ~ lMU not a1~gned

SET DETPRO

6

7

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY v1v - OFFCAB PRESS REL v1v (2) - NORMcb ELS (2) - close (verify)cb SECS ARM (2) - close (ver~fy)

cb SECS LOGIC (2) - close (verlfy)AUTO RCS SEL CM (12) - ~mA or MNB

(l~ftoff conf~g)

ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM AampB - off (ctr)

18

-37-

06 18 AUTO MNVR TO FDAI RPY ANGLES (01 0)

19 l 50 18 REOUEST TRIM MNVR TOALIGN SIC ROLLGDC ALIGN

FDAI RPY ANGLES(010

)

+54-00m(-06-00)

TIG-5mJn

5500m(-0500)

TVC CHECK amp PREPcb STAB CONT SYS (all) - closecb SPS (12) - closeATT DB - MINRATE - LOl~

LIMIT CYCLE - ONMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE 2ROT CONTR PWR DIRECT (2) - OFFSCS TVC (2) - RATE CMD

If SCS SCS TVC (2) - AUTO SC CONT - SCS ~

TVC GMBL DRIVE PampY - AUTOMN BUS TIE (2) - ONTVC SERVO PWR 1 - AC1MNA

2 - AC2MNBTRANS CONTR PWR - ONROT CONTR PWR NORMAL 2 - ACRHC 2 - ARMED

HORIZ CHK - HorJz on 12deg wJndmlmark (LJffiJt +3 0 PNGCS GONO GO)

If NO GO set tw 180 0 180deg0 0

Track horJz wJth 24deg wJndow markAt TIG-2 mJn Ahgn GDC

PRIMARY TVC CHECKGMBL MOT P1-Y1 -STARTON(LMP confJrm)

If SCS verJfy Thumbwheel TrJmTHC - CWVenfy NO MTVC

SEC TVC CHECKGHBL MOT P2-Y2 -STARTON(LMP confJrm)SET GPI TRIHVenfy MTVCTHC NEUTRALGPI returns to 00 (CMC) or trJm (SCS)ROT CONT Pl~ NORM 2 - ACDC

(TRIM) Go to step 17(BYPASS) BMAG MODE(3) - ATTIRATE2 (ver1fy)

ENTR

-38-

20 F SO 25 00204 GMBL TEST OPTION(ACCEPT) SC CONT - GMC (ver~fy)

PROMonitor GPI Response

0020-2000020-200Tr~m

TEST FAIL SC CONT - SCS SCS TVC (2) - AUTO

(REJECT) ENTR

21 06 40 TFIVG~VM (m~n-sec1fps)

PROG ALM - TIG s1~pped

V5N9E 01703

KEY RLSE To 21 ROT CONTR PWR DIRECT (2) - MNABSPS He v1vs (2) - AUTO (ver~fy)

LIMIT CYCLE - OFFFDAI SCALE - SOIScb SPS P2Y2 - open (for cr~t burn)

5800(-02 00)

5925(-0035)

59middot 30(-0030)

06 40

59XX(-OOXX)

AV THRUST A(B) - NORMALTHC - ARMEDRlIC (2) - ARMEDTAPE RCDR - GID RESETHBR

DSKY BLANKS

(AVE G ON)EMS MODE - NORMAL

TFIVG~VM (m~n-seclfps)

CHECK PIPA BIAS lt2fps for 5 sec

ULLAGE AS REQ

IF NO ULLAGE DIR ULLAGE PB - PUSH~

CONTROL ATT WRlIC MONITOR AVM (R3) COUNTING UP

5955(-0005)

F 99 40 ENG ON ENABLE REQUEST(AUTO IGN) PRO AT TFI gt0 sec(BYPASS IGN) ENTR to 24

22 0000 IGN

-39-

If SCS - THRUST ON PB - PUSH

06 40 TFCVG~VM (m~n-seclfpslfps)

~F 97 40 SPS Thrust fall ~

~(RESTART) PRO To IGN (RECYCLE) ENTR To TIG-05 sec

SPS THRUST LITE - ONMONITOR THRUSTING

Pc 95-105 pSlaEMS COUNTING DOWNSPS IN3 v1vs (4) - OPENSPS He v1vs tb (2) - graySPS FUELOXID PRESS - 175-195 pSlaPUGS - BALANCED

PROG ALARM V5N9E 01407 VG INCTHC - CW FLY MTVC

ECOEMER SPS CUTOFF J

AV THRUST (2) - OFF

23 F 16 40 TFC(STATIC)VG~VM (mln-seclfps)~V THRUST AB - OFF

SPS IN3 v1vs (4) - CLOSEDSPS He tb (2) - bp

cb SPS P2Y2 - closed (verlfy)TVC SERVO PHR - AC1MNA (venfy)TVC SERVO PWR 2 - OFF

PRO

24 F 16 85 VG XYZ(CM) CUps)NULL RESIDUALSRECORD ~V CTR amp RESIDUALS I1VCEMS FUNC - OFF VGXEMS MODE - STBY VGYBMAG MODE (3) - RATE 2ATT DB - MAX VGZTRANS CONT PHR - OFF

PRO

25 F 37 V82E

26 F 16 44 HAHPTFF (lnmm~n-sec)

R3-59B59 HP gt494 nmPRO

27 F 37 OOE

-40-

55 EARTH ORBIT ENTRY

1 Venfy CMSMR __

P_shyY_-

SEP ATT(180deg)

(0deg )

2

3

4

EMS INITIALIZATIONEMS FUNC - RNG SETSET RNG TO PAD DATA RNGEMS FUNC - VA SETSlew scroll to pad data VIOEMS FUNC - ENTRY

RSI ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on(up)GDC ALIGN PB - PUSH amp HOLDYAW tw - Pos1tion RSI thru 45deg amp

back to LIFl UPGDC ALIGN PB - RELEASEEMS ROLL - OFFAl1gn GDC to lMU

PWR REDUCT (Norm Deorb Only)HGA PWR - OFFFC PUMPS (3) - OFFVer1fy s1ngle suit compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - Lowcb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2)-openlOb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MAN

-41-

P61 - ENTRY PREP

5 V37E 61E05 09 01427 - ROLL REVERSED05 09 01426 - IMU UNSAT

6 F 06 61 IMPACT LAT LONG liDS UPDN (+-)(01 0

010

+00001)

PRO

PAD VALUESLATLON==G------liDS UP DN _

7 F 06 60 GMAXV400KGAMMA EIRecord

GMAXV400K----GAMMA EI _

PRO

8 F 06 63 RTOGO (1nm) PAD _VIa (fps) PADTFE (mln-sec) ----Compare wlth MSFN for PGNS GONO GONO COMM SET RTOGO amp VIO IN EMS amp

INITIALIZE(ACCEPT) PRO(RECALC) V32E to 8

-42-

P62 - CMSM SEP amp PRE-ENTRY MNVR

9 F 50 25 00041 REQUEST CMSM SEPSC CONT - SCSFREEYAW - 45deg out-of-plane (left for RCS

nght for SPS)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE2PRIM GLY to RAD - BYPASS (verlfy)SECS LOGIC (2) - on (up)MSFN conflrm GO for PYRO ARMSECS PYRO ARM - ARMMN BUS TIE (2) - ON (verlfy)CMSM SEF (2) - ONCSMLM FNl SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 pSlaCM RCS LOGIC - OFFSECS PYRO ARM - SAFEMonltor VMAB

If lt25vdc go to EMERG POWERDOWN Pg E6-1AUTO RCS SEL AlC ROLL (4) - OFFAUTO RCS SEL CM 2(6) - OFFAUTO RCS SEL CM 1(6) - MNA or MNBYAW back to 00

PITCH TO ENTRY ATTROLL 0deg (LIFT UP)PITCH - HORIZ on 317deg MARK (400K)YAW 00

ATT DB - MAXMAN ATT (PITCH) - ACCEL CMDEMS DATA - VerifyEMS FUNC - ENTRY (verlfy)EMS MODE - NORMALMAINTAIN HORIZ TRK

PRO (Act ENTRY DAP)

10 F 06 61 IMPACT LAT LONG HDSDN(010 010 -00001)

PRO

11 FOSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axlS beyond 45deg of Vel vector)

-43-

P63 - ENTRY INIT

12 06 64 GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PWR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRHORIZ CKP~tch error needle goes toward

zero approach~ng 05G t~me

MAN ATT (PITCH) - RATE CMDIf CMC ~s GO

BMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS FLY BETA If CMC NO GO ~

SC CONT - SCS~

FLY EMS RCS Deorh Roll HDS UPTRACK HORIZ w~th 29deg w~ndow mk

P64 - ENTRY POST 05G

13

05G t=elt+0___)

06 68

RTOGO AT 05G AGREES WITH EMS - venfyHORIZ CK05E Lt - on (EMS start)

No EMS start w~th~n 3 secsEMS MODE - BACKUP VHF RNG 05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds L~ft DN

NNVR L~ft DNEMS GONO GO

G-V Plot w~th~n llm~ts

Rng ctr dwn 60 + 7 durlng 10 sec per~od

Mon~tor G-meter forconvergence wlth pad data (Do)

(Vlt27K fps) Go To 17

-44-

P65 - ENTRY - UP CONT (Vgt27K fps)

14 F 16 69 BETA (01deg)DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT~

SC CONT - SCS FLY EMS

PRO

15 06 68 BElA VI HOOT (01deg fpsfps)(VltVL +500 fps amp RDOT Neg) Go To 17

p66 - ENTRY - BALLISTIC (DltDL)

16 06 22 DESIRED GMBL ANGLES RPY (01deg)Mon~tor hor~z +12deg of 317deg mark

P67 - ENTRY - FINAL PHASE (02G)

17 0666 BETACRSRNG ERRDNRNG ERR (Oldeglnmlnm)KEY VERBRecord DNRNG ERR _KEY RLSEL~m~t +100nm from PAD DRE

Mon~tor l~ft vector on RSI amp FDAIF 16 67 RTOGOLATLONG (Vre1=1000fps)

(lnm 010 01deg)SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOlfflMon~tor altimeter

Go To EARTHLANDING pg _I4L5__

-45-

56 EARTHLANDING

90K STEAM PRESS - PEGGED50K CABIN PRESS REL vIv (2) - BOOSTENTRY

SECS PYRO ARM (2) - ARM

40K(90K + 63s)

CM UNSTABLE RCS CMD - OFF ~ 40K APEX COVER JETT PG-PUSH DROGUE DEPLOY PG - PUSH (2 secafter apex cover Jett)

30K ELS LOGIC - ON (up)ELS - AUTO

24K RCS hsable (auto)(90K+92s) RCS CMD - OFF

Apex cover Jett (auto)APEX COVER JETT PB - PUSH

(WAIT 2 SECS)Drogue parachutes deployed (auto)

DROGUE DEPLOY PB - PUSH~

If Drogues FallELS - ~ ~Stablllze CM 5K MAIN DPLY PB - PUSHELS - AUTO

235K Cabln Pressure lncreaslng (Drogues + 50s)If not lncreaSlng by 17K CABIN PRESS REL vlv (RR) - DUMP

-46-

10K Maln parachutes deployedMAIN DEPLOY PB - PUSH (wlthln 1 sec)VHF ANT - RECYVHF AMA - SIMPLEXVHF BCN - ONCABIN PRESS REL v1v (2) - CLOSEDIRECT 02 vlv - OPENCM RCS LOGIC - on (up)CM PRPLNT - DUMP (burn audlb1e)Monltor CM ReS 1amp2 for He press decrease

NO BURN or PRESS DECREASE USE BOTH RHCs DO NOT FIRE PITCH JETS

CM PRPLNT-PURGE (to zero He press)CM RCS He DUMP PB - PUSH RHC (2) - 30 sees NO PITCH k

STRUT LOCKS (2) - UNLOCK

cb FLT amp PL BAT BUS ABampBAT C (3) - closecb FLT amp PLT MNA amp B (2) - opencb ECS RAD HTR OVLD (2) - opencb SPS PampY (4) - open

3K CABIN PRESS REL v1v (RH) - DUMP (after purgecompleted)

FLOOD Lts - POST LDGCM RCS PRPLNT (2) - OFFROT CONTR PWR DIRECT (2) - OFF

800 CAB PRESS RELF vlv - CLOSE (latch off)MN BUS TIE (2) - OFF

AFTER LANDINGcb MAIN REL PYRO (2) - closeMAIN RELEASE - on(up)

Go to POSTLANDING pg _47L-__

I

2

3

-47-

57 POSTLANDING

STABILIZATION VENTILATION COMMUNICATIONS

DIRECT 02 vlv - CLOSE

Stablllzation after landlngELS - AUTO (verlfy)cb MAIN REL PYRO (2) - close (venfy)MAIN RELEASE - on (up) (verlfy)S~CS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb BAT RLY BUS (2) - open

No contact w1th recovery forcesVHF AM AampB - off (ctr) ~

VHF AM Rev ONLY - A cb PL VENT - closecb FLOAT BAG (3) - closecb UPRIGHT SYS COMPRESS (2) - closeIf Stable II

FLOAT BAG(3)-FILL t1ll 2 m1n afterupr1ght then - OFF

VHF AM AlB amp BCN - OFF whlle lnvertedIf Stable I

After 10 M1n Coollng Per1odFLOAT BAG (3) - FILL 7 mln then OFF

Post Stab1lizat1on And Ventllat10nPL BCN LT - BCN LT LOWPL VENT vlv - UNLOCK (Pull)Remove PL VENT Exh CoverPL VENT - HIGH or LOWPL DYE MARKER - ON (swlmmer comm)Release foots traps and_restralntscb MNA BAT BUS A amp BAT C (2) - opencb MNB BAT BUS B amp BAT C (2) - opencb FLT amp PL BAT C - opencb PYRO A SEQ A - opencb PYRO B SEQ B - open

EACH HR - CHECK DC VOLTSgt 275 V If Notmiddot cb FLT amp PL-BAT BUS AampB (2) -open cb FLT amp PL BAT C (1) - open GO TO LOW POWER CHECKLIST

Unstow and lnstall PLV DISTRIB DUCTDeploy grappllng hook and 11ne 1f req

4

-48-

Post Landing Communlcatl0nsVHF ANT-RECY (venfy)VHF BCN - ON (verlfy)

If no contact ~lth recovery forcesperform VHF BEACON Check

MONITOR VHF BEACON transmlSSlonnth VHF AM B Rcvr andor Su)vlval

TransceiverkVHF Beacon not operatlng ~connect Surv~val TranscelVer to antcable behlnd VHF ant access pnland place radio ln BCN mode

LOW POHER CHECKLISTVHF BCN - OFFVHF AM (3) - RCVFLOOD Lts - OFFVHF AM AampB - off (ctr)VHF AM RCV ONLY - A (venfy)COUCH LIGHTS - OFFPOSTLANDING VENT SYS mlnlmlze useSURV RADIO - plug mto VHF BCN ANT cableconn behind VHF ant acess pnl amp turn radloon l-n BCN mode

EGRESS PROCEDURES

CMPCDRLMPCDR

CMPCDRCMP

LMPLl1PCDR

STABLE IDlsconnect Umblll-calsNeck darn onCenter couch - 270 0 positionArmrests stowedConnect raft to SIC l-f desl-red wlth

green lanyardConnect raft ~hl-te lanyards to SUltS amp

lnflate water wlngs when eXltl-ngHATCH PISTON PRESS vlv - PRESS (Outbd)Slde Hatch openedPL VENT - OFFcb Pnl 250 (all) - openEgress with 11feraftPut hardware klt outEgress

or CDIPALL

CMF

CDRCMF

CDR

LMF

CMFCMP LMFCMP

UlP

CDR

-49-

STABLE IIcb CREW STA AUDIO (3) - openD~sconnect umb~1~ca1s

Release foots trapsRelease restra~nt harnessCouch seat pans (3) - 170 0 pos1t10nArm rests stowedSurv1va1 k~ts removed from stowageConnect life raft ma~n1~ne to CDR or SicConnect f~rst wh~te lanyard from

11fe raft to suitConnect th~rd wh~te lanyard from

l~fe raft to SU1tConnect rucksacks together to yellow

lanyard on raft bagPRESSURE EQUALIZATION vlv - OPENRemove and stow fwd hatchEX1t feet f1rst w1th rucksacks when clear

of siC 1nflate water w1ngs and raftExit feet f1rst when clear of SiC

1nflate water w1ngsEX1t feet f1rst when clear of sic

1nflate water w1ngs

-50-

60 TLI ABORTS

TLI Aborts are conta~ned ~n the ESD s~nce the bulk of the funct~ons

concern entry preparat20ns and performance Th~s allows a s2nglesource of procedures for procedure rev2ew val~dat~on checkout andtra~n~ng These procedures ~ncorporate TLI preparat20ns as found ~n

reference 6 w~th the TLI Abort Procedures and these t~e 2nto normallunar return Entry Procedures found ~n sect20n 5 The guidel~nes

for th~s cont2ngency are spec2f2ed 2n reference 7

In2t2al preparat~ons for TLI pos2t20n the necessary system sW2tches2n add~t~on to perform~ng an EMS ~V test and a GDC al~gnment Afterthe DET ~s set for mon2tor2ng TB6 the CMP ~ncreases the 12ght levelof the LEB DSKY to max~mum and returns to the h2s couch Th2s 2Sdone so that the LEB DSKY can be observed ~n the event sunl~ght orreflect20ns wash out the ma2n d2splay panel DSKY dur2ng cr2t2calmaneuvers The crew then straps ~n and prepares for mon2tor~ng TB6as 2nd2cated by the SII SEP L~te The t2mes se~uence of procedures2S keyed on th~s d~splay and ~ncludes the DET START funct~on andSIVB IGNITION Dur2ng the burn the crew mon2tors the FDAIs foratt~tude excurs20ns and abnormal rates report~ng status checks toM~ss2on Control at d2screet t~mes dur2ng the maneuver Upon SIVBSHUTDOWN the eMP records the DSKY d~splayed performance parametersand awa2ts ground conf2rmat~on

The rat~onal for TLI aborts ~s descr~bed 2n reference 7 A summar2shyzat20n 2S extracted to prov2de background and gu2de12nes 2n th2sdocument The abort procedures cover aborts 10 m2nutes after conshyt2ngent SIVE shutdown and aborts 90 m2nutes after normal SIVE shutshydown t2me

The 10 m~nute TLI abort ~s des2gned to be used dur~ng TLI ~n theevent a spacecraft problem develops Wh2Ch can result 2n catastrophe2f ~mmed~ate act~on 2S not taken If the s~tuat20n perm~ts the crewshould always allow the SIVB to complete TLI at wh~ch t~me the groundand crew can perform a malfunct~on analys~s to determ~ne ~f an abort~s adv~sable If a fa~lure occurs that necess2tates the shutdown ofthe SIVB and the ~u~ck return of the crew to earth th~s abort ~s

des~gned to be as ~nsens~t~ve to execut~on errors as poss~ble andst21l be targeted to m2dcorr2dor The burn att~tude w~th the f~ed

hor~zon reference ~s a constant value for any shutdown t~me Theburn durat~on 2S a funct20n of shutdown t2me and 2S ava21able fromcrew charts S~nce the pr~mary purpose of th~s abort ~s to returnto earth as qU2ckly as poss2ble there are no restr2ct20ns as toland~ng locat~on However ~f the t~me to EI is greater than abouttwo hours a midcourse correct20n should be ant~c~pated

The 90 m2nute TLI abort 2S to be used 2f a cr2t2cal subsystem malshyfunct~on ~s determ2ned and the dec2s~on to abort ~s made after the

-51-

TLI cutoff and before TLI cutoff plus approxlmately 80 m1nutesTh1S allows suff1c1ent separatlon and procedural t1me to set upfor the SPS deorb1t burn performed at about TLI + 90 Note thatgenerally the deorb1t burns w1ll be performed a fe11 m1nutes beforeTLI + 90 accord1ng to crew charts shown In reference 8 The no-comm except10n requ1res that 90 m1nutes be the 1nput t1me of 19n1shytlon for P-37 (onboard return-to-earth abort program) so that onshyboard calculatlons can correspond w1th ground calculat10ns to computethe CM land1ng p01nt Th1S TLI abort lS des1gned so that returnfl1ght t1me does not exceed 18 hours and abort ~V does not exceed7000 fps ThlS abort can be performed uSlng chart ~Vs and attltudesand the earths hor1zon serves as a suff1c1ent reference The maneushyver lS targeted to ach1eve the mldcorr1dor entry target Ilne andtlmed to result 1n a deslgnated recovery area

It 1S ObV10US for abort deC1S1ons early 1n the TLI + 90 m1nute t1meshyframe that a GampN SPS burn should be performed In order to keep theTLI abort procedures cons1stent and w1th emphasls on slmpl1c1ty theprocedures here reflect a SCS SPS abort burn to cover the full abortdec1s1on t1meframe

A m1dcourse correct1on for corr1dor control after a TLI abort may bedeS1red 1f the SPS burn d1d not meet expectat1ons The TLIabortprocedures 1n th1S sect10n adapt to the normal lunar return tlmel1neand procedures pr10r to the f1nal MCC

-52-

61 TLI PREPARATION PROCEDURES

GET = 150

CRO AOS(___)

CRO LOS( )(22142)

5100

Don Helmets amp Gloves

XLUNAR - INJECT (verify)EDS PWR - on (venfy)EMS FUNC - OFF (verlfy)EMS MODE - STBYEMS FUNC - IW SETVHF RNGEMS MODE - NORMALSet ~V indo to +15868 fpsEMS FUMC - ~V Test

SPS THRUST Lt - onoff (10 sec)~V lnd stops at -01 to -415

EMS MODE - STBYEMS FUMC - ~V SETVHF RNGSet ~VC

EMS FUNC---~~V=----

GDC ALIGNFDAI Select - liZcb SECS LOGIC (Z) - close (verify)cb SECS ARM (Z) - closeSECS LOGIC (Z) - on (up)MSFN Conflrm GO for PYRO ARM (If pass)SECS PYRO ARM (Z) - on (up)TRANS CONTROL PWR - ONROT CONTR PWR NORMAL (Z) - ACDC(verlfy)ROT CONTR PWR DIRECT (Z) - MNAMNBLV INnGPI - SIISIVB (venfy)LV GUID - IU (venfy)cb DIRECT ULLAGE (Z) - closedSet EVENT TIMER to 5100Begin MONITOR For TB6

CMP to Couch

TB 6 - SII SEP Lt on (TIG-9 mln 38 sec)KEY V83E

SET ORDEALFDAI Z ORB RATE at 180 0 0SII SEP Lt out (38 sec later)Start DET COUNTING UPSC CaNT - SCS (verify)MONITOR LV TANK PRESS

~P lt 36 psid (OXID gt FUEL)~P lt Z6 psid (FUEL gt OXID)

EMERGENCY CSMLV SEP UP TLM CM - BLOCK (verify)UP TLM IU - BLOCK (venfy)

-53-

+45degPY))0middot sec PY

lOK nmltHAlt25K nm

Two phas~ng mnvrs two SPS mnvrs to circular~ze at 150 nmearth orb~t

CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ssion 4K nmltHAltlOK nm CSM amp1M - Two phasing mnvrs two SPS mnvrs to circularize at 150 nm earth orb~t CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ss~on

CSM amp 1M - Two phas~ng mnvrs APS burn todepletion th~rd phasing mnvrSPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn tosem~sync orb~t

25K nmltHAlt40K nm CSM amp 1M - Two phasmg mnvrs APS burn to depletion third phas~ng mnvr SPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn to sem~sync orbit HA)40K nm DPS ava~l - DPS LOll circularize with SPS

DPS not ava~l - Lunar flyby or CSM only to lunar orbit (if reqd gtV lt4000 fps)

V37E 47E (check b~as) Record -=--rshy(Limit 98 fpsmm)

( 1fps)tVXYZN62EVIHDOTHPAD (fpsfpslnm)MONITOR VI ( ) at ECO

SCS TVC SERVO PWR 1 - ACIMNA2 - OFF

TAPE RCDR - CMD RESETHBREMS MODE - NORMAL

SIr SEP Lt - ONTLI Inhib~t S~gnals w~11 not be honored after 5942

SIVB ULLAGE BeginsSII SEP Lt - off (TIG - 18 sec)SIVB FUEL LEADSIVB ULLAGE d~scont~nues

LV ENG I Lt - onSIVB IGNITION ( GETI)LV ENG I Lt - off - -shyMONITOR THRUST amp ATTITUDEMONITOR LV TANK PRESSSIVE ECO (Lt on) (BEGIN TB7)

EMER SIVE CUTOFF AT 6 SEC PAST BURN TIME IF VI ATTAINEDTHC CCW ampNEUTRAL IN 1 SEC or SIISIVB sW - LV STAGEPremature Shutdown HAlt4K nm CSM amp 1M -

5700

58205836

F 16 835800

F 16 62

5838594259525955595900000002SUNRISE(___)

HAW AOS(__=_) KEY VERB (freeze d~splay)

SIVB ATT HOLD 20 sec amp BEGIN VENTINGSIVB NNVR TO ORB RT (HDS DN) (3middot sec)

Record VI -c---HDOT _

HPAD _

KEY RLSEF 16 62

F 16 83

HAW LOS(__=-)

KEYmiddotRLSE~VXYZ (lfps)

Record ~VX---_

~vy

WZ--

AVC---_

TAPE RCDR - off (ctr)EMS MODE - STBYEMS FUNC - OFFSECS PYRO ARM (2) - SAFE

PRO

BURN STATUS REPORT

____--~TIG

BT------VGX____-R

-----P----_Y

REMARKS

_____VI

______--HDOT______--H______---AVC______---FUEL_______OXID

_______UNBAL

F 3708=00 OOEGOS AOS CMP TO LEB

(-=-=-)

0000

0003

0005

0014

0100

-55-

62 TLI 10 MIN ABORTSECS LOGIC (2) - on (up)SECS PYRO ARM (2) - ARM

TRANS CONTR - CGH (4 sec) amp +XDET RESET (verlfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS GMD-ON

TRANS GONTR - neutral then +X for10 sec

SIVBGPI s~ - GPIExcesslve rates 6V THRUST A - NORMAL SPS THRUST - DIRECT When rates damped 6V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

TRANS CONTR +X - OFFV37E OOE

PITGH UP to LOGAL VERT (+X axlSto~ard the earth)

RATE - LOWBMAG MODE (3) - ATTIRATE 2EDS PHR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SEGS ARM (2) - opencb EDS (3) - open

TRANS CONTR -X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (180deg)P (199deg)Y (0deg)

RETRO UPDATEGETI _

JV _VG

Jtb ---GET 400K _

05G _GET DROGUE _

ENTRY P _R _

Y_--

0945

-56-

ALIGN HORIZ ON RET +1 MKGMBL CHECK (T11lle Pentattlng)MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conflnn)cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FUMC - JV SETVHF RNGSET JV from chartE~S FUMC - JVEMS fODE - NOIDlAL

lV THRUST A - NORMALV37E 47E (THRUST fONITOR)

F 16 83 lVXYZ (1 fps)

0950

1000

NOTE For aborts durlng 1st mln of TLIKEY V82E F 16 44 (HaHpTff)Burn untll Hp lt 19NM

TRANS CONTR +X

THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN JV reqdJV THRUST (2) - OFFReport cutoff

cb SPS P2 Y2- closeGfBL MTRS (4) - OFF (LMP Confinn)TRANS CONT PWR - OFFTVC SERVO PWR (2) - OFFMN BUS TIE (2) - OFFcb SPS P1amp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREIf est time to EIltOl5500 omlt fCC andenter the SUPERCIRC CKLIST as early as pos-slb1e Pg ~2~3~ __If est time to EI)Ol5500 anticlpate afCC Enter the ENTRY PREP CKLIST at step 9pg 18

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

-2tl C

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UN

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26

28

30

32

34

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90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 5: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

-2-

20 LIST OF ACRONYMS AND ABBREVIATIONS

ComputerPilot

ModuleModuleModule

AccumlatorAmphherAntennaAcqu~s~t~on of S~gnal

Backup Bank AngleBeaconBlunt End ForwardCMC Commanded Bank AngleBody Mounted Att~tude GyroBank Reverse BankCab~n

CommanderCoupl~ng Data Un~t

C~rcuit

CommandCommandCommandCutoffCrew Opt~cal AI~gnment S~ght

Commun~cat~ons

Cryogen~c

Command Serv~ce ModuleCounterCaut~on Warn~ng SystemD~g~tal Auto P~lot

D~g~tal Event P~lot

Drag Acceleration at Sk~pout

Constant Drag Control Accelerat~on LevelD~splay and KeyboardDSKY EnterEnv~ronment Control SubsystemEntry InterfaceEntry Monltor SystemElectrlcal Power SubsystemEssent~al

Flight Combust~on Stab~lity MonitorFI~ght D~rector Att~tude Ind~cator

FunctionAccelerat~on 1n Earth Grav~tatlonal Un~ts

Gu~dance and ControlGround Elapsed TlffieGround Elapsed T1me of Ign~t~on

Gyro Display CouplerGlycolG~mbal

Guidance and Nav~gat1on

ACCUMAMPANTAOSBBABCNBEFBETABMAGBRBCBNCDRCDUCKTCMCMCCMPCOCOASCm1MCRYOCSMCTRCWSDAPDETDLDODSKYEECSEIEMSEPSESSFCSMFDAIFUNCGGampCGETGETIGDCGLYGMBLGampN GIN

-3-

Llst of Acronyms and Abbrevlatlons

GNDGPIG-VHAHEHPIMUKA

LIDLEBIMPLOSLVMANMCCMCC-HMESCMSFNMGAMKMNVRMaNMTRMTVCNOPTORIEN02PPGAPGNCSPIPAPLPLSSpassPRIMPRPLNTPSIAPTTPUGSPWRRRI R2 R3RADRCDRRCSROTREFSMMAT

GroundG~bal Posltlon IndlcatorAcceleratlon-VelocltyHelght of ApogeeHellumHeight of PerlgeeInertlal Measurement UnltDrag Acceleratlon necessary to lnltlate

constant drag controlLlft to Drag RatioLower Equlpment BayLunar Module PllotLoss of SlgnalLocal Vertlcal Llft Vector Launch VehlcleManualMldcourse CorrectlonMlssion Control Center - HoustonMaster Event Sequence ControllerManned Space Fllght NetworkMiddle Glmbal AngleMarkManeuverMonltorMotorManual Thrust Vector ControlDSKY NounOptlon OptlCSOrlentatlonOxygenPltch or CMC ProgramPressure Garment AssemblyPrlmary GUldance Navlgatlon and Control SystemPulse Integratlng Pendulous AccelerometerPlanetPortable Llfe Support SystemPosslblePrlmaryPropellantPounds Per Square Inch AbsolutePush to TalkPropellant Utllizatlon and Gaglng SystemPowerRoll or CMC RoutlneReglster 1 2 3RadlatorRecorderReactlon Control SystemAltltude RateReference to Stable Member Matrlx

-4-

L~st of Acronyms and Abbrev~at1ons

RELRET

RHCRNGROURRT

RSIRTGOSASCSSECSECSSELSEPSEQSFT

SM SIMSPASPSSTBYSXPSXTSTSTATBTBDTERMTFTFFTHBWLSTHCTIGTLITIl TLMTRNFR

TVCVVGVIOVLVMY

Rel1efReentry Elapsed TIme (Lunar Return Case) or Retro

Elapsed Time (Earth Orb~tal Case) For lunar returnsRET 1S zero at RRT For earth orb1tal entries RET iszero at the deorb1t burn tIme

Rotat1onal Hand ControllerRangeRout1neReentry Reference T~me (Based on MCC-H predicted time

of EI to nearest second)Roll Stab11~ty IndicatorRange to GoShaft AngleStab1lizat1on and Control SystemSecondarySequent1al Events Control SubsystemSelectSeparationSequentialShaft Angle for SXTS when spacecraft 1S at

ignit10n attitudeServ1ce ModuleCOAS Star P~tch AngleServ1ce Propuls~on SystemStandbyStar X Pos~t~on (COAS)SextantSextant StarTrunnion AngleTalkback D~splay T1me BaseTo Be DeterminedTerm~nate

Ttme FromTtme of FreefallThumbwheelsTranslational Hand ControllerTime of Ignit~on

Translunar Insert10nTelemetryTransferThrust Vector ControlVeloc~ty or DSKY VerbVeloc~ty To Be GatnedInertial Veloc~ty

Sktpout Veloc1tyVeloc~ty MeasuredYaw

-5-

3deg LUNAR REIUBN ENTRY TECHNIQUES

The t~mel~ne for lunar return entries is based on the recommendationsfound ~n reference 1 the s~mulator val~dated procedures ~n reference2 and the mission val~dated procedures listed in the onboard checkshylist for the C Pr~me m~ssion The event times are l~sted ~n reference3

The preparation for lunar return entr~es beg~ns at a conven~ent t~me

about 30 hours before entry ~nterface At th~s t=e MSFN sends up alldata suff~c~ent for reentry also an EMS entry selftest ~s made toassure max~mum confidence ~n the EMS operat~on during entry Thereshyafter var~ous system powerups and checks are ~n~t~ated as l~sted insect~on 51 and deta~led ~n reference 4 Nom~nally the PGNCS ~s upfor the ent~re m~ss~on However ~f ~t ~s not ~t ~s powered up atEI-7 hours ~n preparat~on for the last MCC and entry The last MCCdec~s~on ~s made at about EI-6 hours for the maneuver to be performedat EI-3 hours ~f needed Deta~ls of th~s maneuver are outl~ned ~n

reference 1 After the MCC time P52 ~s again selected and the IMU ~s

real~gned to the REFSMMAT If the IMU dr~ft ~s w~th~n tolerance thesubsequent IMUSCS dr~ft check will determ~ne if the SCS has dr~fted

excess~vely If so the other BMAGs are selected and the IMUSCScheck repeated Th~s check ~s followed by a repeat of the EMS ~V

counter check and accelerometer b~as check at EI-l hour 15 m~nutes

to determ~ne ~f the scale factor and b~as are adequate for entrymon~tor~ng F~nal stowage CM RCS preheat and pyro Cllcu~t and seshyquent~al tests are worked ~nto this t~meframe so that at EI-50 m~nutes

the MSFN w~ll be requested for a go to pyro arm by the crew ~n preparashyt~on for separat~on At 45 m~nutes before EI the CMC update programP27 can be selected to permit update of the landing po~nt locat~on andthe state vector The entry PAD data shown ~n sect~on 70 ~s thenvo~ced to the crew and recorded From th~s data the DET ~s set andstarted the EMS ~nit~al~zed and the RSI al~gned Prior to EI-20ffilnutes the crew w~ll have strapped-~n completed the~r presepara-t~on checkl~st and maneuvered to the entry att~tude At this pointEI-19 m~nutes the CMC entry program Fbl ~s selected by the CMP Ifthere was no entry PAD data because of commun~cat~on loss the veloshyc~ty and range to go from P61 ~s recorded and used ~n the EMS AtEI-15 m~nutes the spacecraft ~s p~tched down and the hor~zon ~s checkedagainst the 317 degree w~ndow scr~be l~ne and the FDAI att~tude Ifthere ~s s~gn~f~cant d~sagreement the PGNCS ~s suspected and the spaceshycraft ~s held on the w~ndow reference In P62 the spacecraft ~s yawed45 0 from th~s att~tude and separated from the SM After separat~on

the CM ~s yawed back ~n plane and the hor~zon check repeated At approxshy~mate1y EI-10 m~nutes the p~tch att~tude is w~th~n 450 of the CMCcommanded att~tude and P63 ~s entered automat~ca11y S~nce the CMCDAP tr~es to hold local p~tch attitude and the CMC ~s not ~n controlthe crew observes the p~tch error needle unpeg and approach zeroabout two m~nutes before 05g t~me Th~s serves as a gono go CMC

-6-

check for entry control If the FDAI pltch error does not decreaseto wlthln + 50 at 005g the PGNCS lS fa lied and the crew flies aconstant g-entry mode wlth EMS ranglng after the VelOClty decreaseto 25500 feet per second If the PGNCS lS acceptable the spaceshycraft control lS placed In CMC and the CMC mode lS placed ln autoshymatlc At 05g the EMS automatlcally starts lf the EMS mode sWltchwas posltloned to automatlc earller ThlS wlll be backed up manually3 seconds after the ground computed 05g tlme recorded on the entryPAD by placlng the EMS mode sWltch In manual lf lt has not startedautomatlcally At PGNCS 005g lndlcatlon the CMC program changesto P64 and from thls pOlnt the entry lS under entry DAP control

The lunar return entry nomlnally lS performed by the PGNCS to lnsurecontrol wlthln the overshoot and g llmlt llnes as well as optlmlzethe landlng point accuracy Although the hlgh speed entry lnvolvesa rapld sequency of events there are several monitorlng tasks forthe crew to determlne lf the automat~c contrails performlng correctly

An entry corr~dor ver~flcation check 1S made by observlng the lnltlalslope of the EMS V-g trace between 1 and 2 gs If the EMS lndlcatesthe need to reverse the LV orlentatlon and the lndependent g meterconflrms the EMS g lndlcatlon the SC lS immedlately orlented as aresult of the EMS ~nd~cat~on

The EMS g lnd~catlon ~s contlnuously checked durlng entry uSlng thelndependent g meter and the PGNCS g ~ndlcatlon as a thlrd voteDeC1Slons durlng the first entry (P64) are critlcal ln terms of bothexceSSlve g llnes and the PGNCS lS not commandlng (and SC respondlng)to correct the sltuatlon the PGNCS lS felled

The PGNCS gono go check for short range targets (1200-1400 n ml) forWhlCh P65 lS not used 1S d1fferent Slnce there are no CMC computedSk1p drag (DL) and skip velocity (VL) values The check uses the EMSscroll to determ1ne 1f the PGNCS lS commandlng the proper roll att1shytude to converge the EMS g level to a predetermlned PAD value (Do) ascomputed by MCC-H For the nom1nal target range of 1300 naut~cal

mlles the crew w1ll monltor the program change from P64 to P67 atapprox~matelyEI + 3 mlnutes For ranges greater than 1400 nauticalmlles the program w1ll transfer to the Upcontrol Program P65 whenVL ~s between 18000 and 25766 feet per second and constant drag hasbrought the CMC pred1cted range to wlthln 25 naut1cal m1les of thetarget range The P65 PGNCS gono go check cons1sts of determln1ng1pound both the DSKY d1splay of sk~pout drag (DL) and Sk1pout veloclty(VL) are w1thln the PAD llmlts In addltlon the EMS scroll lS mon1shytored to determ~ne lf the trace lS approach1ng the DL and VL values

Throughout entry the crew monltors the spacecraft response to the CMCroll commands by observlng the FDAI lndlcatlons If the commands are

-7-

apparently good and In agreement wlth the EMS but the spacecraftresponse is questlonable the crew manually takes over and fIlesthe CMC commands

If the Upcontrol Program P65 was entered the program wlll nomshylnally sWltch to the Flnal Entry Program P67 for target rangesbelow approxlmately 1800 nautlcal miles or to the Ballistlc Proshygram P66 for ranges greater than approxlmately 1800 nautlcalffilles The program transfer crlterla are more preclsely deflnedIn reference 1

If P66 lS entered the spacecraft lS automatlcally rolled to theIlftup heads-down attltude to permlt the horlzon to be vlewedfrom the wlndow durlng the second entry The entry attltude checklS made by comparlng the horlzon wlth a speclfled wlndow mark Ifthe check falls the crew manually malntalns the entry trlffi attltudeuSlng the horizon VleW for reference The EMS lS used for ranglngSlnce the veloclty has now decreased to below 25500 feet per second

The EMS scroll lS contlnuously used to monltor for exceSSlve g conshydltlons durlng the second entry If the EMS V-g trace vlolates theg Ilnes and the PGNCS lS not commandlng (and spacecraft respondlng)to correct the situatlon the PGNCS lS falled and the EMS lS usedfor ranglng after ltS g lndlcatlon has been conflrmed by the lndeshypendent g meter

The entry phase lS essentlally over when the relatlve veloclty ofthe spacecraft decreases to less than 1000 feet per second ThlSlS lndlcated In P67 when RTGO latltude and longltude are dlsplayedSlnce very Ilttle ranglng capablllty exists after thls pOlnt thespacecraft lS orlented elther full Ilft up or down dependlng on RTGOnegatlve or posltlve and the crew prepares for the earth landlngphase

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-13-

40 EARTH ORBITAL DEORBIT AND ENTRY TECHNIQUES

As outl~ned ~n reference 5 a nom~nal PGNCS entry from earth orb~t ~s

based on a preparat~on t~me of 2 hours and 40 m~nutes ~nclud~ng 2n~ght passes Th~s t~me ~ncludes approx~mately 20 minutes before thef~rst n~ght pass after the CMC update and PAD data have been rece2vedTh~s t~e also 2ncludes approx2mately 20 m2nutes after the secondn~ght pass to allow suffic~ent t2me to prepare for retrof2re after theIMU f2ne a12gnment It has been determ2ned coarse a12gnment accuracy~s adequate for retrof~re and entry and undoubtedly other funct20nscould be om2tted depend2ng on the c2rcumstances for the dec2s20n toreenter Descr2bed here2n are the nom2nal earth oro2tal entry proshycedures w2th pert2nent comments on system va12dat20n for real timeacceptance dec~s20ns

After the entry dec~s~on is made the crew transfers the PGNCS fromthe standby to the operate mode and rece~ves a CMe update w~th P27Next the maneuver PAD update ~s v02ced up and the 2n~t~al entry mode~s determ~ned During the ~n~tial n~ght pass the IMU or2entat~on ~s

estab12shed uS2ng P51 star s~ght2ngs to obta2n a REFSMMAT The preshyferred or~entat~on opt20n ~n P52 2S then selected to coarse a12gn theIMU uS2ng the des2red entry REFSMMAT determ2ned by MGG-H The GOO ~s

now al~gned to the IMU 2n preparat~on for an IMUSes dr~ft check Ifthe GOO ~nd~cates the ses dr2ft rate exceeds 10 degrees per hour ~n

any ax~s the check ~s repeated on the other BMAGs to estaol~sh if theGOO or Just the single set 2S unusuable Var20us sytem checks as 12sted2n sect20n 51 are performed as necessary cons2stent w2th the t2me12ned2ctates of the maJor act2v2t2es Included 2n these checks are the EMSself-tests and the dV counter test The latter requ2res the spacecraftbe placed ~n dr2ft2ng fl2ght w~th the funct20n sW2tch 2n the dV pos2t~on

If the counter reg2sters a change of more than 25 feet per second w2th2n100 seconds the scroll and counter are unre12able for mon2tor2ng thedeorb2t burn and entry rang2ng If the EMS self-test fails and t2medoes not allow further analysis a 5555 ERE entry 1S planned as thePGNGS backup entry mode After complet2on of these checks the entryPAD lS prov1ded by MeG-H The crew then selects the external dVprogram P30 and the appropr2ate deorb1t tbrust1ng program p40 or P41Dur2ng th2s per2od wh2ch 2ncludes the f1nal n2ght pass P52 may beselected to ver2fy the IMU a12gnment Since the retro att2tude hasbeen computed so that a w2ndow mark c01nc2des w2th the hor2zon atGETI th2s serves as the conclus2ve check on the PGNCS At 5 m2nutesbefore retrofire the att2tude check 1S made by ver1fY2ng that the 12degree scr~be 12ne ~s w2th2n 3 degrees of the hor2zon If not thePGNeS has fa2led and the ses 2S used for att2tude reference and the

V counter for burn durat~on control S2nce the ses att~tude wasa12gned to the IMU a real~gnment ~s necessary This ~s accompl~shed

by manually maneuver2ng the spacecraft to ma~nta1n the 24 degree wlodowmark on the hor2zon and releas1ng the GOO a12gn button at TIG - 2 m2nutes

-14-

Upon complet~on of the burn the tN res~duals are burned to W~th~n

02 feet per second If the PGNCS ~V counter or est~mated burnduration are ~n d~sagreement ~t must be estab1~shed whether suff~shy

c~ent veloc~ty has been suppl~ed to put the land~ng po~nt in thefootpr~nt The PGNCS data w~ll be used ~f ~t ~s conf~rmed by oneother source if not the ~V counter w~11 be used ~f ~t ~s conf~rmed

by the burn durat~on t~me If add~tional ~V ~s necessary the data~s ava~lable to the crew on an onboard chart found ~n Sect~on 80

Post burn entry preparat~on requ~res EMS ~n~t~al~zation RSI al~gnshy

ment and pre-separat~on funct~ons The crew then selects the ~n~t~al

entry program P61 and records the d~sp1ays as a check aga~nst PADdata Upon complet~on of these checks P62 ~s entered The crewmanually or~ents the spacecraft to the separat~on attitude and yaws450 to ~nsure aga~nst possible CM 8M recontact After separat~on

the spacecraft ~s maneuvered to the reentry tr~m att~tude wh~ch

places the hor~zon on the 3170 w~ndow mark at EI Shortly thereshyafter ~n P62 the entry DAP is act~vated and P63 in~t~ated Dur~ng

th~s t~e MCC-H has computed a postburn update and ~t ~s vo~ced tothe crew ~f d~fferent from preburn values The EMS scroll and rangecounter w~ll be adJusted accord~ngly ~f t~me perm~ts A f~nal PGNCScheck pr~or to 05g may be mon~tored at th~s t~e w~th the CMC modein free and the manual att~tude p~tch ~n acceleration command wh~le

the hor~zon reference ~s held the p~tch error needle w~ll decreaseto zero as EI ~s reached At RET 005g the EMS mode sw~tch ~s

turned to manual the entry 005-g sw~tch and EMS roll sw~tch areturned on and the spacecraft control sw~tched to CMC to beg~n DAPcontrol At the PGNCS 005-g ~ndicatwn the program change fromP63 to P64 ~s mon~tored and the t~e vo~ce recorded At th~s t~me

the EMS range counter check ~s made dur~ng the 10 second per~od

follow~ng EMS 005g Dur~ng th~s per~od the counter should countdown 40 + 10 naut~cal m~les At PGNCS 02-g ~nd~cation the changefrom P64-to P67 ~s monitored and the ~splay may be held by key~ngVERB ~n order to record the init~al downrange error d~splay andcompare ~t to the PAD value The PGNCS has fa~led ~f the two do notagree w~th~n + 100 naut~cal m~les In the event P67 has not appearedwhen both the-g-meter and the scroll ~nd~cate greater than 05g thePGNCS has sim~lar~ly fa~led In e~ther fa~lure the SCS is used foratt~tude reference w~th an EMS entry If the checks agree the crewrema~ns w~th automat~c DAP for the rema~nder of the entry

The entry phase ~s essentially over when the relat~ve velocity ofthe spacecraft decreases to less than 1000 feet per second Th~s

~s ~nd~cated ~n P67 when RTGO lat~tude and long~tude are d~splayed

S~nce very l~ttle rang~ng capab~l~ty exists after th~s pOint thespacecraft is or~ented either full l~ft up or down depending onRTGO negat~ve or pos~t~ve and the crew prepares for the earth land~ng

phase

-15-

41 TYP~cal Retrof~re and Entry Sequence of Events

Dec~s~on to reenter

P27 (CMC update)

Retrof~re PAD update

Entry mode dec~s~on

P51 (IMU or~entat~on determlnatlon) durlng f~rst dark per~od

P52 (IMU coarse allgnment)

EMS checks

Entry PAD update

P30 (external AV)

p40 (SPS thrust)

P52 (IMU f~ne al~gnment) durlng second dark per~od

p40 (SPS thrust)

Ign~t~on att~tude check

Retroflre

P61

P62

CMSM separat~on

P63

Postburn PAD update

Entry attltude check

p64 (beg~n DAP control at O05g)

P67 (PGNCS gono go check at O2g)

42

Retrof~re

and

En

try

Alt

ern

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-17-

5 0 DETAILED ENTRY PROCEDURES

In order to comblne slmilar procedures that are common to lunar returnentrles and earth orblt entrles the followlng procedures are dlvldedlnto categorles that allow a mlnlmum of dupllClty ThlS provldes asmaller tralnlng package and more closely resembles the onboard crewcheckllst when comparlson lS necessary

51 Entry Preparatlons for Superclucular and Earth Orbltal Entrles

1~e entry preparatlons are comblned In these procedures andsteps pecullar to elther superclrcular or earth orbltal entrlesare labeled accordlngly The tlme llstlngs In thlS sectlon areappllcable to only superclrcular entries Slnce the earth orbltalentry tlmellne lS a functlon of several varlables as descrlbedIn sectlon 40 and reference 5

-18-51 (Contlnued)

VEHICLE PREPARATION

l-

2

3

4

5

6 -0600h

7 -0535h

8

9

10 -0430h

INITIAL STOWAGE COMPLETED

CMC amp ISS START UP

SCS POWER UP

p51 - IMU ORIENTATION

LOAD DAPV48E 11102 01111 PRO ERO PRO

LAST MCC DECISION

NO COMM - P52 amp NAV SIGHTINGSNOMINAL - P2337 ONBOARD COMPARISON

DON MAE WESTS amp FOOT RESTRAINTS

VHF AM A - SIMPLEX

P 27 (SV REFSMMAT) MNVRamp ENTRY pAD UPDATES

11 -0415h P52 - IMU REALIGN(___) (OPTION 1)

12 P37 (NO COMM ONLY)

13

14

ECS CKS02 SUPPLY REFILLECS Monitor CkEVAP H20 CONT (2) vlvs - AUTOSUIT HEAT EXCH SEC GLY - FLOW

EPS CKS 1 3 4 (5 If reqd)

15 SPS CK (If req d)

16

17

18

RCS CKSSM RCS MOUlt CkCM RCS MOUlt Ck

CampW SYS CK

CMC SELF CK

19

20 -0345h

-03l5h-0300h

21

22

22A

-19-

DSKY COND LT TEST

MIDCOURSE MANEUVERP30 - EXT rVP404l - SPSRCS THRUSTINGMIDCOURSE (17) BURN

NO COMM NAV SIGHTINGS

ffiVR TO ENTRY ATT (Superc1rc only)V62E

V49E

22B F 06 22 DESIRED FINAL GMBL ANGLESLOAD ENTRY ATT PAD ANGLESPRO

22C F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) SC CONT - CMC

BMAG MODE (3) - RATE 2CMC MODE - AUTO

PRO(~N) SC CONT - SCS

MNVR to 22E

22D 06 18 AUTO MNVR TO FDAI RPY ANGLES

22E F 50 18 REQUEST TRIM(TRIM) Go to 22C(BYPASS) ENTR

23 -200hr BORESIGHT amp SXT STAR CHECKOPT MODE - CMCOPT ZERO - OFF

V41 N91E

F 21 92 SHAFT TRUNLoad SXTS angles

41 OPTICS DRIVE

CHECK SXT STAROPT ZERO - ZERO

CHECK BORESIGHT STAR (If ava11)

24 -0135h

25(___)

26

27 -0115h

-20-

P52 - lMU REALIGNRecord gyro torqu~ng anglesRp~----

YIf-7gt-Lno--re-c-ycle PS2If conflrmed use SCS for EMS entry

GDC ALIGNIf drlft gtLOohr change ratesource

FINAL STOWAGEOPTICS (except for hybrid)ORDEALGLY TO RAD SEC - BYPASS (verlfy)CooL pnl lnstalledY-Y struts (2) extendedStow Data Box R-12

EMS CHECKEMS FUNC - OFFcb EMS (2) - closeEMS MODE - STBYEMS FUNC - EMS TEST 1 (walt 5 sec)EMS MODE - NORMAL (walt 10 sec)

Check ind lts - offRANGE lnd - 00Slew halr1ine over notch

In self-test patternEMS FUNC - EMS TEST 2 (walt 10 sec)

05G It - on (all others out)EMS FUNC - EMS TEST 3

05G It - onRSI Lower It - on (10 sec Qater)Set RANGE counter to 58 nm+OO

EMS FUNC - EMS TEST 405G It - on (all others out)G-V trace w~thin pattern to lwr rt

corner 9GRANGE lnd counts down to 0+02

EMS FUNC - EMS TEST 505G It - onRSI upper lt - on (10 sec later)RANGE md - 00SCrlbe traces vertlcal llne 9g to

022+01ALIGN SCROLL TO ENTRY PATTERN (on

37K ft sec hne)EMS FUNC - RNG SET

G-V scroll assy traces vert llne022g to 0+01

EMS MODE - STBY

28

29

30 -OllOh

-21-

~V TEST (Deorb~t only)EMS FUNC - ~V SETVHF RNGSET ~V ~nd to 15868 fpsEMS MODE - NORMALEMS FUNC - ~V TEST

SPS THRUST LT - onoff (10 sec)~V ~nd stops at -01 to -415

EMS MODE - STBY

PRIMARY WATER EVAP ACTIVATIONGLY EVAP H20 FLOW - AUTOGLY EVAP STH PRESS - AUTOPRI ECS GLY PUMP - ACI

CM RCS PREHEATNote If sys test mtr 5cd6abcd

all read 39 vdc (28degF) or moreom~t preheat

cb RCS LOGIC (2) - closeCM RCS LOGIC - ONUP T1M CM - BLOCK (ver~fy)

cb CM RCS HTRS (2) - closeCM RCS HTRS - ON (LMP Conf~rm)

(20 mlU or III lowest rdg lS39 vdc) (Moultor Maufpress for press drop)

31 (___) FINAL GDC DRIFT CK (If req I d)If drlft gtlOohr Suspect GDC Do not

use RSI amp FDAI 2

32 -OO5Om

33

34

35

TERM CM RCS PREHEATUP TLM CM - BLOCK (venfy)CM RCS HTRS - OFFCM RCS LOGIC - OFF

SYSTEMS TEST PANEL CONFIGURATIONSYS TEST METER - 4BRNDZ XPNDR - OPERATECM RCS HTRS - OFFWASTE H20 DUMP - OFFURINE DUMP - OFF

LEB LIGHTING - OFF

SEC WATER EVAP ACTIVATIONGLY To RAD SEC vlv - BYPASSSEC COOL EVAP - EVAPSEC COOL PUMP - AC2

36

37

38 -OO45m

-22-

PYRO BATT CKcb PYRO A SEQ A - close (ver~fy)

cb PRYO B SEQ B - close (verify)DC IND - PYRO BAT A(B)

~If PYRO BAT A(B) lt 35 vdc cb PYRO A(B) seq A(B) - open~

PYRO A(B)BAT BUS A(B)TO PYRO~MN BUS TIE - close

cb MNA BAT C - closecb MNB BAT C - closeDC IND - MNBPNL 8 - All cbs closed except

PL VENT - open (ver~fy)

FLOAT BAG (3) - open (ver~fy)

DOCKING PROBE (2) - open (verlfy)EDS BAT (3) - open (ver~fy)

CM ReS HTRS (2) - open

CM RCS ACTIVATIONcb SECS ARM (2) - close (verlfy)cb SECS LOGIC (2) - close (verlfy)SECS LOGIC (2) - ONMSFN conflrm GO for PYRO ARM(~f poss)SECS PYRO ARM (2) - ARMCM RCS PRPLNT 1amp2 - ONCM RCS PRESS - ONRCS Ind sw - eMl then 2

He PRESS 3700-4400 pSlaMANF PRESS 287-302 pSla

SECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFF

P27 amp ENTRY PAD UPDATEGo To Entry Checkllst

Superclrc - pg ~2~3 _Hybnd - pg -----2~9L-__Normal Deorblt - pg __3L5L- _

-23-

52 SUPERCIRCULAR ENTRY

1 SET DET (up to ET)

2

3

4

5

3000(-30-00)

EMS INITIALIZATIONSET RNG TO PAD DATA RNGEMS FUNC - Vo SETSlew Scroll to Pad Data VIOEMS FUNC - ENTRY

RS I ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on (up)GDC ALIGN PB - PUSH amp HOLDYAW Tw - Pos~t~on RSI thru

45deg amp back to LIFT UPGDC ALIGN PB - ReleaseEMS ROLL - OFFA1~gn CDC to lMU

CM RCS RING A CKRCS TRNFR - CMcb CM RCS LOGIC MNB - openAUTO RCS SEL MNB (6) - OFFSC CONT - SCSTest R~ng A ThrustersSC CONT - CMCRCS TRNFR - SMAUTO RCS SEL (12) - MNAMNB

(hftoff conflg)cb CM RCS LOGIC MNB - close

OPTICS PWR - OFFCMP to COUCH

MN BUS TIE (2) - ONTAPE RCDR - REWIND

6 35middot0Om(-25middot 00)

-24-

SEPARATION CK LISTTVC SERVO PWR 1 - AClMNAcb ELS (2) - close (ver1fy)PRIM GLY TO RAn - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY vlv - OFFCAB PRESS REL vlv (2) - NORMGMBL MTRS (4) - STARTABORT SYS PRPLNT - RCS CMD (venfy)SM RCS PRIM PRPLNT (4) - ONVHF 11M (AampB) - OFFHI GAIN ANT PWR - OFFFC PUMPS (3) - OFFVer1fy s1ugle SU1t compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - 10101cb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2) - opencb HTRS OVLD (2) - openPOT H20 RTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANSEC COOL EVAP - RESETSEC COOL PUMP - off (etr)

MtiVR TO CMSM SEP P R ATTSC CONT - SCSCMC MODE - FREEMNVR TO PAD ATTR (0deg)PY----W)

-25-

SUPERCIRCULAR ENTRY (Cont~nued)

1

4100m(-1900)

P61 - ENTRY PREP

V37E 61E

k 05 09 01427 - ROLL REVERSED 05 09 01426 - IMU UNSAT ~

2 F 06 61 IMPACT LAT LONG HDS UPDN (+-)PRO (010

fps +00001)

3 F 06 60 GMAXVPREDGAMMA EIRecord

GMAXV400K----

GAMMA EI _PRO

(01deg fpsOldeg)

4 F 06 63 RTOGO (lnm) PAD _VIO (fps) PAD _TFE(m~n-sec)

Compare w~th ~M~SFN==C~f~o-r~P~GNS GONO GOIf NO COMM Set RTOGO amp VIO In EMS

amp lnltla11ze(ACCEPT) PRO(RECALC) V32E To 4

5 F 50 25

4300m

(-1700)

45 oOm(-1500)

500Om(-1000)

6 F 06 61

-26-

P62 - CMSM SEP amp PRE-ENTRY MNVRCAUTION Call No EXT Verbs In P62

00041 REQUEST CMSM SEPSC CONT - SCSFREE

COMPARE PITCH ATT WITH PAD DATA ---0=-

(W~thLU 5deg)YAW - 45deg OUT-OF-PLANE (LEFT)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTIRATE 2MN BUS TIE (2) - ON (ver~fy)

PRIM GLY TO RAD - BYPASS (verlfy)CM RCS LOGIC - ON (venfy)SECS LOGIC (2) - on (up)SECS PYRO ARM - ARMCMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 ps~a

CM RCS LOGIC - OFFSECS PYRO ARM (2) - SAFEMonltor VMAB

If lt25 vdc go to EMERGPOWERDOWN pg E6-l

AUTO RCS SEL AC ROLL (4) - OFFAUTO RCS SEL CM 2(6)-OFFAUTO RCS SEL CM 1(6)-MNAYAW back to 0degPITCH TO HORIZ TRACK ATT

ROLL - 0deg (LIFT UP)PITCH - 400K Horiz Mark (317deg)YAW - 0deg

ATT DB - MAXMAN ATT PITCH - ACCEL CMDEMS DATA - Ver~fy

EMS FliNC - ENTRY (ver~fy)

EMS MODE - NORMALcb SPS PampY (4) - openMAINT HORIZ TRK

PRO (Act ENTRY DAP)

IMPACT LATLONGHDSDN (01deg01deg-00001)PRO

7 POSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axis beyond 45deg of Vel vector)

8 06 64

58middot00m(-0200)

9

05G tlme(+0 )

(--=---)

06 68

-27-

P63 - ENTRY INIT

GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PIJR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRmDHORIZ CKPltch error needle goes toward

zero approachlng OSG tlmeMAN ATT (PITCH) - RATE CMD

If CMC lS GOBMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS I

FLY BETA If CMC NO GO ilt

1 SC CaNT - SCS I

FLY EMS k

p64 - ENTRY POST 05G

RTOGO AT 05G AGREES HITH EMS-venfyHORIZ CK05G Lt - ON (EMS START)

No EMS START wlthln 3 sec ~ EMS MODE - BACKUP VHF RNG c

05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds Llft DN

NNVR Llft DNEMS GONO GO

G-V Plot wlthln IlmltsRng ctr dwn 60plusmn7 durlng 10 sec

perlodMonltor G-meter for

convergence wlth pad data (Do)(Vlt27K fps) Go to 13

-28-

P65 - ENTRY - UP CONT (Vgt27K fps)

10 F 16 69 BETA (01middot) _DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT lt~ SC CONT - SCS FLY EMS

PRO

11 06 68 BETAVIHDOT (OIdegfpsfps)(VltV1+500 fps amp RnOT Neg) Go To 13

P66 - ENTRY - BALLISTIC (D(DL)

12 06 22 DESIRED GMBL ANGLES RPYMoultor horlz +12middot of 317middot mark

P67 - ENTRY - FINAL PHASE (02G)

13 06 66 BETACRSRNG ERRDNRNG ERR(010 1um 1um)

KEY VERBRecord DNRNG ERR _KEY RLSEMoultor l~ft vector ou RSI amp FDAI

16 67 RTOGOLATLONG (Vrel=1000fps)(lumOldegOldeg)

SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOWNMonitor a1t~meter

Go To EARTHLANDING pg ---4L5 _

-29-

53 GampN HYBRID DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL tV1 V37E 30E

2 F 06 33 GETI(ACCEPT) PRO (hrm~n Olsec)(REJECT) LOAD DESIRED GETI

3 F 06 81 tVXYZ (LV) (lfps)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

4 F 06 42 HAHPtV (lnm lfps)Record tV

(ACCEPT) PRO(REJECT) Reselect P30 or P27 Load new paramo

5 F 16 45 MTFIMGA (marksm~n-secOlO)

MGA -00002 ~f k

k lMU not al~gned

SET DETPRO

6

7

8

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (Pull)PLSS 02 vlv - FILL02 8M SUPPLY vlv - OFFCAB PRESS REL vlv (2) - NORMcb ELS (2) - closecb SECS ARM (2) - closecb SECS LOGIC (2) - close (ver~fy)

AUTO RCS SEL CM (12) - MNA or ~ffiB

(hftoff conhg)ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM (AampB) - OFF

CMP to Couch

9

10

11

-30-

MNVR TO PAD BURN ATTLOAD DAPBMAG MODE (3) - RATE 2SC CONT - CMCAUTOATT DB - MINMAN ATT (3) - RATE CMD

v62E

v49E

12 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLES

PRO

13 F 50 18 REQ MNVR TO FDAI RPY ANGLES (01deg)(AUTO) PRO(MAN) SC CONT - SCS

BMAG MODE (3) - RATE 2MNVR To 15

14 06 18 AUTO MNVR TO FDAI RPY ANGLES (01deg)

15 F 50 18 REQ TRIM TO FDAI RPY ANGLES (01deg)(TRIM) Go to 13(ByPASS) ENTR

16

17

CHECK BORESIGHT amp SKT STARSOPT MODE - CMCOPT ZERO - OFF

v41 N91E

18 F 21 92 SHAFTTRUN (01deg 001deg)Load SXTS angles

19 41 OPTICS DRIVECheck SKT STAR

OPT ZERO - ZEROCheck BORESIGHT STAR (~f ava~l)

20 V25 N17E (01deg)Load Pad Data GMBL Angles

for CM BURN ATTATT SETtw - SET

to PAD DATA GMBL ANGLESfor CM BURN ATT

21

22

-31-

PHR REDUCTIONHGA PHR - OFFFC PUMPS (3) - OFFVerify s~ngle su~t compr oper loads

balancedFC 2 MN AampB - OFFS BD PiR AMP - LOWcb ECS RAD CONTHTR (2) - opencb HASTE H20URINE DUMP HTRS(2)- opencb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANMN BUS TIE (2) - ONTVC SERVO PHR 1 - AC1MNAGMBL MTR (4) - START

p41 - RCS THRUSTINGV37E 41E

23 F 50 18 REQ MNVR TO LCL HORIZ (HDS ON)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CMCAUTOPRO To 24

(gtfANDAP) BMAG MODE (3) - RATE 2SC CONT - CMCHOLD

V62EMNVR To 25

24 06 18 AUTO MNVR TO FDAI RPY

25 F 50 18 REQ TRIM TO LCL HORIZ (01deg)ALIGN SC ROLL

(AUTO TRIM) PRO To 24(BYPASS) ATT DB - MIN

RATE - LOHMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTlRATE 2

ENTR

550Om26 06 85

59middot2527

-32-

VGXYZ (1fps)RECHECK BORESIGHT STARTRANS CONIR PWR - on (up)EMS MODE - STBY (ver~fy)

EMS FliNC - bV SETVHF RNGSET (IV for SM BURN _EMS FliNC - bVS BD ANT - OMNI CSECS LOGIC (2) - ONMSFN conhrm Go for PYRO ARMSECS PYRO ARM (2) - ARMCM RCS LOGIC - ON (ver~fy)

DSKY BLANKS

593028 16 85 VG XYZ (AVE G ON) (lfps)

RHCs amp THC - ARMEDLIMIT CYCLE - OFFTAPE RCDR - CMD RESETHBREMS MODE - NORMAL

000029 F 16 85 REQ NULL VG XYZ (lfps)

BURN EMS bV CTR TO ZERORESET DET amp COUNT UP

If SM ONLY burn go to step 32THC - LOCKEDSC CaNT - SCSFREERATE - HIGHPRIM GLY To RAD - BYPASS (ver~fy)

MN BUS TIE (2) - ON (ver~fy)

CMSM SEP (2) - on (up)CSMLM FNL SEP (2) - on (up) (verify)CampW MODE - CMRCS TRNFR - CMCM RCS LOGIC - OFF

Momtor VM ABIf lt25 vdc go to EMERGPOWER DOWN Pg E6-l

V63E

If CMC NO GO FDAI SOURCE - ATT FDAI SEL - 1 or 2 ATT SET - GDC

SET

-33-

~Uili ATT PITCH - ACCEL CMDFDAI SCALE - 55MNVR TO CM BURN ATT (NULL ERR NEEDLES)

R 0degPY --00--

30

31

CM RCS BURNRHC III-ContJnuous PJtch DownRHC HZ-Module PJtch to null needlesBURN VGZ TO ZERO

If only 1 RHC Pulse + P=5deg from retro att MaJnta~n rates lt3degsec

BURN COMPLETION ATllV CTR= or DET= _

V8ZE

32 F 16 44 HAHPTFF (1nmffiJn-sec)Check HP-

If gt Pad data contJnue burnuntJ1 lt Pad

PRO

33 F 16 85 VGXYZ (Ups)Read VG resJduals to MSFN

(HYBRID) PRO to 34(SM ONLY BURN)

PROF 37 ODE

EI-1500 V37E 47EF 16 83 twx Y Z (Ups)

SC CONT - SCSFREEMAN ATT (PITCH) - RATE CMDRATE - HIGHPRIM GLY To RAD - BYPASS (verJfy)MN BUS TIE (2) - ON (verJfy)CMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verJfy)Campl MODE - CMRCS TRNFR - CMCM ReS LOGIC - OFFSECS PYRO ~I (2) - SAFE

-34-

PROMonitor VMAB

If lt25 vdc go to EMERGPOWER DOWN

34 F 37 OOEPCM BIT RATE - LOWATT DB - MAXEMS MODE - STBYEMS FUNC - OFF

Go To EARTH ORBIT ENTRY pg _--40-__

-36-

8 SPS THRUSTING PREPCYCLE CRYO FANSSPS GAGING - ACI (ver~fy)

PUG MODE - NORM (venfy)BMAG MODE (3) - RATE 2tv CG - CSMCMC MODE - FREEAUTO RCS SEL (16) - MNA or HNB

(hftoff conbg)SC CONT - CMCAUTO

9 MNVR TO PAD BURN ATTV62E

10 V49E

11 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLESPRO

12 F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) PRO(HAN) SC CONT - ses

MNVR to 14

06 18 AUTO MNVR TO FDAI RPY ANGLES13

14 F 50 18 REO TRIH TO FDAI RPY ANGLES(TRIM) Go to 12(BYPASS) ENTR

15 BORESIGHT STAR CHECK

16 V37E 40EOPT PWR - OFF

17 F 50 18 REQUEST MNVR TO FDAI RPY ANGLES (01deg)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CHCAUTOPRO to 18

(MANDAP) BMAG HODE (3) - RATE 2SC CONT - CMCHOLDMNVR to 19

(HANseS) se eONT - sesMNVR to 19

-35-

54 NORMAL DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL ~V

1 V37E 30E

2 F 06 33 GETI (hrm~nOlsec)

(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

3 F 06 81 ~VXYZ (LV)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

( lfps)

4 F 06 42 HAHP~V (1nmlfps)Record W

(ACCEPT) PRO -----(REJECT) Rese1ect P30 or P27 Load new pa~am

5 F 16 45 MTFIMGA (marksmln-secOldeg)MGA -00002 If ~ lMU not a1~gned

SET DETPRO

6

7

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY v1v - OFFCAB PRESS REL v1v (2) - NORMcb ELS (2) - close (verify)cb SECS ARM (2) - close (ver~fy)

cb SECS LOGIC (2) - close (verlfy)AUTO RCS SEL CM (12) - ~mA or MNB

(l~ftoff conf~g)

ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM AampB - off (ctr)

18

-37-

06 18 AUTO MNVR TO FDAI RPY ANGLES (01 0)

19 l 50 18 REOUEST TRIM MNVR TOALIGN SIC ROLLGDC ALIGN

FDAI RPY ANGLES(010

)

+54-00m(-06-00)

TIG-5mJn

5500m(-0500)

TVC CHECK amp PREPcb STAB CONT SYS (all) - closecb SPS (12) - closeATT DB - MINRATE - LOl~

LIMIT CYCLE - ONMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE 2ROT CONTR PWR DIRECT (2) - OFFSCS TVC (2) - RATE CMD

If SCS SCS TVC (2) - AUTO SC CONT - SCS ~

TVC GMBL DRIVE PampY - AUTOMN BUS TIE (2) - ONTVC SERVO PWR 1 - AC1MNA

2 - AC2MNBTRANS CONTR PWR - ONROT CONTR PWR NORMAL 2 - ACRHC 2 - ARMED

HORIZ CHK - HorJz on 12deg wJndmlmark (LJffiJt +3 0 PNGCS GONO GO)

If NO GO set tw 180 0 180deg0 0

Track horJz wJth 24deg wJndow markAt TIG-2 mJn Ahgn GDC

PRIMARY TVC CHECKGMBL MOT P1-Y1 -STARTON(LMP confJrm)

If SCS verJfy Thumbwheel TrJmTHC - CWVenfy NO MTVC

SEC TVC CHECKGHBL MOT P2-Y2 -STARTON(LMP confJrm)SET GPI TRIHVenfy MTVCTHC NEUTRALGPI returns to 00 (CMC) or trJm (SCS)ROT CONT Pl~ NORM 2 - ACDC

(TRIM) Go to step 17(BYPASS) BMAG MODE(3) - ATTIRATE2 (ver1fy)

ENTR

-38-

20 F SO 25 00204 GMBL TEST OPTION(ACCEPT) SC CONT - GMC (ver~fy)

PROMonitor GPI Response

0020-2000020-200Tr~m

TEST FAIL SC CONT - SCS SCS TVC (2) - AUTO

(REJECT) ENTR

21 06 40 TFIVG~VM (m~n-sec1fps)

PROG ALM - TIG s1~pped

V5N9E 01703

KEY RLSE To 21 ROT CONTR PWR DIRECT (2) - MNABSPS He v1vs (2) - AUTO (ver~fy)

LIMIT CYCLE - OFFFDAI SCALE - SOIScb SPS P2Y2 - open (for cr~t burn)

5800(-02 00)

5925(-0035)

59middot 30(-0030)

06 40

59XX(-OOXX)

AV THRUST A(B) - NORMALTHC - ARMEDRlIC (2) - ARMEDTAPE RCDR - GID RESETHBR

DSKY BLANKS

(AVE G ON)EMS MODE - NORMAL

TFIVG~VM (m~n-seclfps)

CHECK PIPA BIAS lt2fps for 5 sec

ULLAGE AS REQ

IF NO ULLAGE DIR ULLAGE PB - PUSH~

CONTROL ATT WRlIC MONITOR AVM (R3) COUNTING UP

5955(-0005)

F 99 40 ENG ON ENABLE REQUEST(AUTO IGN) PRO AT TFI gt0 sec(BYPASS IGN) ENTR to 24

22 0000 IGN

-39-

If SCS - THRUST ON PB - PUSH

06 40 TFCVG~VM (m~n-seclfpslfps)

~F 97 40 SPS Thrust fall ~

~(RESTART) PRO To IGN (RECYCLE) ENTR To TIG-05 sec

SPS THRUST LITE - ONMONITOR THRUSTING

Pc 95-105 pSlaEMS COUNTING DOWNSPS IN3 v1vs (4) - OPENSPS He v1vs tb (2) - graySPS FUELOXID PRESS - 175-195 pSlaPUGS - BALANCED

PROG ALARM V5N9E 01407 VG INCTHC - CW FLY MTVC

ECOEMER SPS CUTOFF J

AV THRUST (2) - OFF

23 F 16 40 TFC(STATIC)VG~VM (mln-seclfps)~V THRUST AB - OFF

SPS IN3 v1vs (4) - CLOSEDSPS He tb (2) - bp

cb SPS P2Y2 - closed (verlfy)TVC SERVO PHR - AC1MNA (venfy)TVC SERVO PWR 2 - OFF

PRO

24 F 16 85 VG XYZ(CM) CUps)NULL RESIDUALSRECORD ~V CTR amp RESIDUALS I1VCEMS FUNC - OFF VGXEMS MODE - STBY VGYBMAG MODE (3) - RATE 2ATT DB - MAX VGZTRANS CONT PHR - OFF

PRO

25 F 37 V82E

26 F 16 44 HAHPTFF (lnmm~n-sec)

R3-59B59 HP gt494 nmPRO

27 F 37 OOE

-40-

55 EARTH ORBIT ENTRY

1 Venfy CMSMR __

P_shyY_-

SEP ATT(180deg)

(0deg )

2

3

4

EMS INITIALIZATIONEMS FUNC - RNG SETSET RNG TO PAD DATA RNGEMS FUNC - VA SETSlew scroll to pad data VIOEMS FUNC - ENTRY

RSI ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on(up)GDC ALIGN PB - PUSH amp HOLDYAW tw - Pos1tion RSI thru 45deg amp

back to LIFl UPGDC ALIGN PB - RELEASEEMS ROLL - OFFAl1gn GDC to lMU

PWR REDUCT (Norm Deorb Only)HGA PWR - OFFFC PUMPS (3) - OFFVer1fy s1ngle suit compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - Lowcb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2)-openlOb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MAN

-41-

P61 - ENTRY PREP

5 V37E 61E05 09 01427 - ROLL REVERSED05 09 01426 - IMU UNSAT

6 F 06 61 IMPACT LAT LONG liDS UPDN (+-)(01 0

010

+00001)

PRO

PAD VALUESLATLON==G------liDS UP DN _

7 F 06 60 GMAXV400KGAMMA EIRecord

GMAXV400K----GAMMA EI _

PRO

8 F 06 63 RTOGO (1nm) PAD _VIa (fps) PADTFE (mln-sec) ----Compare wlth MSFN for PGNS GONO GONO COMM SET RTOGO amp VIO IN EMS amp

INITIALIZE(ACCEPT) PRO(RECALC) V32E to 8

-42-

P62 - CMSM SEP amp PRE-ENTRY MNVR

9 F 50 25 00041 REQUEST CMSM SEPSC CONT - SCSFREEYAW - 45deg out-of-plane (left for RCS

nght for SPS)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE2PRIM GLY to RAD - BYPASS (verlfy)SECS LOGIC (2) - on (up)MSFN conflrm GO for PYRO ARMSECS PYRO ARM - ARMMN BUS TIE (2) - ON (verlfy)CMSM SEF (2) - ONCSMLM FNl SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 pSlaCM RCS LOGIC - OFFSECS PYRO ARM - SAFEMonltor VMAB

If lt25vdc go to EMERG POWERDOWN Pg E6-1AUTO RCS SEL AlC ROLL (4) - OFFAUTO RCS SEL CM 2(6) - OFFAUTO RCS SEL CM 1(6) - MNA or MNBYAW back to 00

PITCH TO ENTRY ATTROLL 0deg (LIFT UP)PITCH - HORIZ on 317deg MARK (400K)YAW 00

ATT DB - MAXMAN ATT (PITCH) - ACCEL CMDEMS DATA - VerifyEMS FUNC - ENTRY (verlfy)EMS MODE - NORMALMAINTAIN HORIZ TRK

PRO (Act ENTRY DAP)

10 F 06 61 IMPACT LAT LONG HDSDN(010 010 -00001)

PRO

11 FOSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axlS beyond 45deg of Vel vector)

-43-

P63 - ENTRY INIT

12 06 64 GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PWR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRHORIZ CKP~tch error needle goes toward

zero approach~ng 05G t~me

MAN ATT (PITCH) - RATE CMDIf CMC ~s GO

BMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS FLY BETA If CMC NO GO ~

SC CONT - SCS~

FLY EMS RCS Deorh Roll HDS UPTRACK HORIZ w~th 29deg w~ndow mk

P64 - ENTRY POST 05G

13

05G t=elt+0___)

06 68

RTOGO AT 05G AGREES WITH EMS - venfyHORIZ CK05E Lt - on (EMS start)

No EMS start w~th~n 3 secsEMS MODE - BACKUP VHF RNG 05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds L~ft DN

NNVR L~ft DNEMS GONO GO

G-V Plot w~th~n llm~ts

Rng ctr dwn 60 + 7 durlng 10 sec per~od

Mon~tor G-meter forconvergence wlth pad data (Do)

(Vlt27K fps) Go To 17

-44-

P65 - ENTRY - UP CONT (Vgt27K fps)

14 F 16 69 BETA (01deg)DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT~

SC CONT - SCS FLY EMS

PRO

15 06 68 BElA VI HOOT (01deg fpsfps)(VltVL +500 fps amp RDOT Neg) Go To 17

p66 - ENTRY - BALLISTIC (DltDL)

16 06 22 DESIRED GMBL ANGLES RPY (01deg)Mon~tor hor~z +12deg of 317deg mark

P67 - ENTRY - FINAL PHASE (02G)

17 0666 BETACRSRNG ERRDNRNG ERR (Oldeglnmlnm)KEY VERBRecord DNRNG ERR _KEY RLSEL~m~t +100nm from PAD DRE

Mon~tor l~ft vector on RSI amp FDAIF 16 67 RTOGOLATLONG (Vre1=1000fps)

(lnm 010 01deg)SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOlfflMon~tor altimeter

Go To EARTHLANDING pg _I4L5__

-45-

56 EARTHLANDING

90K STEAM PRESS - PEGGED50K CABIN PRESS REL vIv (2) - BOOSTENTRY

SECS PYRO ARM (2) - ARM

40K(90K + 63s)

CM UNSTABLE RCS CMD - OFF ~ 40K APEX COVER JETT PG-PUSH DROGUE DEPLOY PG - PUSH (2 secafter apex cover Jett)

30K ELS LOGIC - ON (up)ELS - AUTO

24K RCS hsable (auto)(90K+92s) RCS CMD - OFF

Apex cover Jett (auto)APEX COVER JETT PB - PUSH

(WAIT 2 SECS)Drogue parachutes deployed (auto)

DROGUE DEPLOY PB - PUSH~

If Drogues FallELS - ~ ~Stablllze CM 5K MAIN DPLY PB - PUSHELS - AUTO

235K Cabln Pressure lncreaslng (Drogues + 50s)If not lncreaSlng by 17K CABIN PRESS REL vlv (RR) - DUMP

-46-

10K Maln parachutes deployedMAIN DEPLOY PB - PUSH (wlthln 1 sec)VHF ANT - RECYVHF AMA - SIMPLEXVHF BCN - ONCABIN PRESS REL v1v (2) - CLOSEDIRECT 02 vlv - OPENCM RCS LOGIC - on (up)CM PRPLNT - DUMP (burn audlb1e)Monltor CM ReS 1amp2 for He press decrease

NO BURN or PRESS DECREASE USE BOTH RHCs DO NOT FIRE PITCH JETS

CM PRPLNT-PURGE (to zero He press)CM RCS He DUMP PB - PUSH RHC (2) - 30 sees NO PITCH k

STRUT LOCKS (2) - UNLOCK

cb FLT amp PL BAT BUS ABampBAT C (3) - closecb FLT amp PLT MNA amp B (2) - opencb ECS RAD HTR OVLD (2) - opencb SPS PampY (4) - open

3K CABIN PRESS REL v1v (RH) - DUMP (after purgecompleted)

FLOOD Lts - POST LDGCM RCS PRPLNT (2) - OFFROT CONTR PWR DIRECT (2) - OFF

800 CAB PRESS RELF vlv - CLOSE (latch off)MN BUS TIE (2) - OFF

AFTER LANDINGcb MAIN REL PYRO (2) - closeMAIN RELEASE - on(up)

Go to POSTLANDING pg _47L-__

I

2

3

-47-

57 POSTLANDING

STABILIZATION VENTILATION COMMUNICATIONS

DIRECT 02 vlv - CLOSE

Stablllzation after landlngELS - AUTO (verlfy)cb MAIN REL PYRO (2) - close (venfy)MAIN RELEASE - on (up) (verlfy)S~CS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb BAT RLY BUS (2) - open

No contact w1th recovery forcesVHF AM AampB - off (ctr) ~

VHF AM Rev ONLY - A cb PL VENT - closecb FLOAT BAG (3) - closecb UPRIGHT SYS COMPRESS (2) - closeIf Stable II

FLOAT BAG(3)-FILL t1ll 2 m1n afterupr1ght then - OFF

VHF AM AlB amp BCN - OFF whlle lnvertedIf Stable I

After 10 M1n Coollng Per1odFLOAT BAG (3) - FILL 7 mln then OFF

Post Stab1lizat1on And Ventllat10nPL BCN LT - BCN LT LOWPL VENT vlv - UNLOCK (Pull)Remove PL VENT Exh CoverPL VENT - HIGH or LOWPL DYE MARKER - ON (swlmmer comm)Release foots traps and_restralntscb MNA BAT BUS A amp BAT C (2) - opencb MNB BAT BUS B amp BAT C (2) - opencb FLT amp PL BAT C - opencb PYRO A SEQ A - opencb PYRO B SEQ B - open

EACH HR - CHECK DC VOLTSgt 275 V If Notmiddot cb FLT amp PL-BAT BUS AampB (2) -open cb FLT amp PL BAT C (1) - open GO TO LOW POWER CHECKLIST

Unstow and lnstall PLV DISTRIB DUCTDeploy grappllng hook and 11ne 1f req

4

-48-

Post Landing Communlcatl0nsVHF ANT-RECY (venfy)VHF BCN - ON (verlfy)

If no contact ~lth recovery forcesperform VHF BEACON Check

MONITOR VHF BEACON transmlSSlonnth VHF AM B Rcvr andor Su)vlval

TransceiverkVHF Beacon not operatlng ~connect Surv~val TranscelVer to antcable behlnd VHF ant access pnland place radio ln BCN mode

LOW POHER CHECKLISTVHF BCN - OFFVHF AM (3) - RCVFLOOD Lts - OFFVHF AM AampB - off (ctr)VHF AM RCV ONLY - A (venfy)COUCH LIGHTS - OFFPOSTLANDING VENT SYS mlnlmlze useSURV RADIO - plug mto VHF BCN ANT cableconn behind VHF ant acess pnl amp turn radloon l-n BCN mode

EGRESS PROCEDURES

CMPCDRLMPCDR

CMPCDRCMP

LMPLl1PCDR

STABLE IDlsconnect Umblll-calsNeck darn onCenter couch - 270 0 positionArmrests stowedConnect raft to SIC l-f desl-red wlth

green lanyardConnect raft ~hl-te lanyards to SUltS amp

lnflate water wlngs when eXltl-ngHATCH PISTON PRESS vlv - PRESS (Outbd)Slde Hatch openedPL VENT - OFFcb Pnl 250 (all) - openEgress with 11feraftPut hardware klt outEgress

or CDIPALL

CMF

CDRCMF

CDR

LMF

CMFCMP LMFCMP

UlP

CDR

-49-

STABLE IIcb CREW STA AUDIO (3) - openD~sconnect umb~1~ca1s

Release foots trapsRelease restra~nt harnessCouch seat pans (3) - 170 0 pos1t10nArm rests stowedSurv1va1 k~ts removed from stowageConnect life raft ma~n1~ne to CDR or SicConnect f~rst wh~te lanyard from

11fe raft to suitConnect th~rd wh~te lanyard from

l~fe raft to SU1tConnect rucksacks together to yellow

lanyard on raft bagPRESSURE EQUALIZATION vlv - OPENRemove and stow fwd hatchEX1t feet f1rst w1th rucksacks when clear

of siC 1nflate water w1ngs and raftExit feet f1rst when clear of SiC

1nflate water w1ngsEX1t feet f1rst when clear of sic

1nflate water w1ngs

-50-

60 TLI ABORTS

TLI Aborts are conta~ned ~n the ESD s~nce the bulk of the funct~ons

concern entry preparat20ns and performance Th~s allows a s2nglesource of procedures for procedure rev2ew val~dat~on checkout andtra~n~ng These procedures ~ncorporate TLI preparat20ns as found ~n

reference 6 w~th the TLI Abort Procedures and these t~e 2nto normallunar return Entry Procedures found ~n sect20n 5 The guidel~nes

for th~s cont2ngency are spec2f2ed 2n reference 7

In2t2al preparat~ons for TLI pos2t20n the necessary system sW2tches2n add~t~on to perform~ng an EMS ~V test and a GDC al~gnment Afterthe DET ~s set for mon2tor2ng TB6 the CMP ~ncreases the 12ght levelof the LEB DSKY to max~mum and returns to the h2s couch Th2s 2Sdone so that the LEB DSKY can be observed ~n the event sunl~ght orreflect20ns wash out the ma2n d2splay panel DSKY dur2ng cr2t2calmaneuvers The crew then straps ~n and prepares for mon2tor~ng TB6as 2nd2cated by the SII SEP L~te The t2mes se~uence of procedures2S keyed on th~s d~splay and ~ncludes the DET START funct~on andSIVB IGNITION Dur2ng the burn the crew mon2tors the FDAIs foratt~tude excurs20ns and abnormal rates report~ng status checks toM~ss2on Control at d2screet t~mes dur2ng the maneuver Upon SIVBSHUTDOWN the eMP records the DSKY d~splayed performance parametersand awa2ts ground conf2rmat~on

The rat~onal for TLI aborts ~s descr~bed 2n reference 7 A summar2shyzat20n 2S extracted to prov2de background and gu2de12nes 2n th2sdocument The abort procedures cover aborts 10 m2nutes after conshyt2ngent SIVE shutdown and aborts 90 m2nutes after normal SIVE shutshydown t2me

The 10 m~nute TLI abort ~s des2gned to be used dur~ng TLI ~n theevent a spacecraft problem develops Wh2Ch can result 2n catastrophe2f ~mmed~ate act~on 2S not taken If the s~tuat20n perm~ts the crewshould always allow the SIVB to complete TLI at wh~ch t~me the groundand crew can perform a malfunct~on analys~s to determ~ne ~f an abort~s adv~sable If a fa~lure occurs that necess2tates the shutdown ofthe SIVB and the ~u~ck return of the crew to earth th~s abort ~s

des~gned to be as ~nsens~t~ve to execut~on errors as poss~ble andst21l be targeted to m2dcorr2dor The burn att~tude w~th the f~ed

hor~zon reference ~s a constant value for any shutdown t~me Theburn durat~on 2S a funct20n of shutdown t2me and 2S ava21able fromcrew charts S~nce the pr~mary purpose of th~s abort ~s to returnto earth as qU2ckly as poss2ble there are no restr2ct20ns as toland~ng locat~on However ~f the t~me to EI is greater than abouttwo hours a midcourse correct20n should be ant~c~pated

The 90 m2nute TLI abort 2S to be used 2f a cr2t2cal subsystem malshyfunct~on ~s determ2ned and the dec2s~on to abort ~s made after the

-51-

TLI cutoff and before TLI cutoff plus approxlmately 80 m1nutesTh1S allows suff1c1ent separatlon and procedural t1me to set upfor the SPS deorb1t burn performed at about TLI + 90 Note thatgenerally the deorb1t burns w1ll be performed a fe11 m1nutes beforeTLI + 90 accord1ng to crew charts shown In reference 8 The no-comm except10n requ1res that 90 m1nutes be the 1nput t1me of 19n1shytlon for P-37 (onboard return-to-earth abort program) so that onshyboard calculatlons can correspond w1th ground calculat10ns to computethe CM land1ng p01nt Th1S TLI abort lS des1gned so that returnfl1ght t1me does not exceed 18 hours and abort ~V does not exceed7000 fps ThlS abort can be performed uSlng chart ~Vs and attltudesand the earths hor1zon serves as a suff1c1ent reference The maneushyver lS targeted to ach1eve the mldcorr1dor entry target Ilne andtlmed to result 1n a deslgnated recovery area

It 1S ObV10US for abort deC1S1ons early 1n the TLI + 90 m1nute t1meshyframe that a GampN SPS burn should be performed In order to keep theTLI abort procedures cons1stent and w1th emphasls on slmpl1c1ty theprocedures here reflect a SCS SPS abort burn to cover the full abortdec1s1on t1meframe

A m1dcourse correct1on for corr1dor control after a TLI abort may bedeS1red 1f the SPS burn d1d not meet expectat1ons The TLIabortprocedures 1n th1S sect10n adapt to the normal lunar return tlmel1neand procedures pr10r to the f1nal MCC

-52-

61 TLI PREPARATION PROCEDURES

GET = 150

CRO AOS(___)

CRO LOS( )(22142)

5100

Don Helmets amp Gloves

XLUNAR - INJECT (verify)EDS PWR - on (venfy)EMS FUNC - OFF (verlfy)EMS MODE - STBYEMS FUNC - IW SETVHF RNGEMS MODE - NORMALSet ~V indo to +15868 fpsEMS FUMC - ~V Test

SPS THRUST Lt - onoff (10 sec)~V lnd stops at -01 to -415

EMS MODE - STBYEMS FUMC - ~V SETVHF RNGSet ~VC

EMS FUNC---~~V=----

GDC ALIGNFDAI Select - liZcb SECS LOGIC (Z) - close (verify)cb SECS ARM (Z) - closeSECS LOGIC (Z) - on (up)MSFN Conflrm GO for PYRO ARM (If pass)SECS PYRO ARM (Z) - on (up)TRANS CONTROL PWR - ONROT CONTR PWR NORMAL (Z) - ACDC(verlfy)ROT CONTR PWR DIRECT (Z) - MNAMNBLV INnGPI - SIISIVB (venfy)LV GUID - IU (venfy)cb DIRECT ULLAGE (Z) - closedSet EVENT TIMER to 5100Begin MONITOR For TB6

CMP to Couch

TB 6 - SII SEP Lt on (TIG-9 mln 38 sec)KEY V83E

SET ORDEALFDAI Z ORB RATE at 180 0 0SII SEP Lt out (38 sec later)Start DET COUNTING UPSC CaNT - SCS (verify)MONITOR LV TANK PRESS

~P lt 36 psid (OXID gt FUEL)~P lt Z6 psid (FUEL gt OXID)

EMERGENCY CSMLV SEP UP TLM CM - BLOCK (verify)UP TLM IU - BLOCK (venfy)

-53-

+45degPY))0middot sec PY

lOK nmltHAlt25K nm

Two phas~ng mnvrs two SPS mnvrs to circular~ze at 150 nmearth orb~t

CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ssion 4K nmltHAltlOK nm CSM amp1M - Two phasing mnvrs two SPS mnvrs to circularize at 150 nm earth orb~t CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ss~on

CSM amp 1M - Two phas~ng mnvrs APS burn todepletion th~rd phasing mnvrSPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn tosem~sync orb~t

25K nmltHAlt40K nm CSM amp 1M - Two phasmg mnvrs APS burn to depletion third phas~ng mnvr SPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn to sem~sync orbit HA)40K nm DPS ava~l - DPS LOll circularize with SPS

DPS not ava~l - Lunar flyby or CSM only to lunar orbit (if reqd gtV lt4000 fps)

V37E 47E (check b~as) Record -=--rshy(Limit 98 fpsmm)

( 1fps)tVXYZN62EVIHDOTHPAD (fpsfpslnm)MONITOR VI ( ) at ECO

SCS TVC SERVO PWR 1 - ACIMNA2 - OFF

TAPE RCDR - CMD RESETHBREMS MODE - NORMAL

SIr SEP Lt - ONTLI Inhib~t S~gnals w~11 not be honored after 5942

SIVB ULLAGE BeginsSII SEP Lt - off (TIG - 18 sec)SIVB FUEL LEADSIVB ULLAGE d~scont~nues

LV ENG I Lt - onSIVB IGNITION ( GETI)LV ENG I Lt - off - -shyMONITOR THRUST amp ATTITUDEMONITOR LV TANK PRESSSIVE ECO (Lt on) (BEGIN TB7)

EMER SIVE CUTOFF AT 6 SEC PAST BURN TIME IF VI ATTAINEDTHC CCW ampNEUTRAL IN 1 SEC or SIISIVB sW - LV STAGEPremature Shutdown HAlt4K nm CSM amp 1M -

5700

58205836

F 16 835800

F 16 62

5838594259525955595900000002SUNRISE(___)

HAW AOS(__=_) KEY VERB (freeze d~splay)

SIVB ATT HOLD 20 sec amp BEGIN VENTINGSIVB NNVR TO ORB RT (HDS DN) (3middot sec)

Record VI -c---HDOT _

HPAD _

KEY RLSEF 16 62

F 16 83

HAW LOS(__=-)

KEYmiddotRLSE~VXYZ (lfps)

Record ~VX---_

~vy

WZ--

AVC---_

TAPE RCDR - off (ctr)EMS MODE - STBYEMS FUNC - OFFSECS PYRO ARM (2) - SAFE

PRO

BURN STATUS REPORT

____--~TIG

BT------VGX____-R

-----P----_Y

REMARKS

_____VI

______--HDOT______--H______---AVC______---FUEL_______OXID

_______UNBAL

F 3708=00 OOEGOS AOS CMP TO LEB

(-=-=-)

0000

0003

0005

0014

0100

-55-

62 TLI 10 MIN ABORTSECS LOGIC (2) - on (up)SECS PYRO ARM (2) - ARM

TRANS CONTR - CGH (4 sec) amp +XDET RESET (verlfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS GMD-ON

TRANS GONTR - neutral then +X for10 sec

SIVBGPI s~ - GPIExcesslve rates 6V THRUST A - NORMAL SPS THRUST - DIRECT When rates damped 6V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

TRANS CONTR +X - OFFV37E OOE

PITGH UP to LOGAL VERT (+X axlSto~ard the earth)

RATE - LOWBMAG MODE (3) - ATTIRATE 2EDS PHR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SEGS ARM (2) - opencb EDS (3) - open

TRANS CONTR -X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (180deg)P (199deg)Y (0deg)

RETRO UPDATEGETI _

JV _VG

Jtb ---GET 400K _

05G _GET DROGUE _

ENTRY P _R _

Y_--

0945

-56-

ALIGN HORIZ ON RET +1 MKGMBL CHECK (T11lle Pentattlng)MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conflnn)cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FUMC - JV SETVHF RNGSET JV from chartE~S FUMC - JVEMS fODE - NOIDlAL

lV THRUST A - NORMALV37E 47E (THRUST fONITOR)

F 16 83 lVXYZ (1 fps)

0950

1000

NOTE For aborts durlng 1st mln of TLIKEY V82E F 16 44 (HaHpTff)Burn untll Hp lt 19NM

TRANS CONTR +X

THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN JV reqdJV THRUST (2) - OFFReport cutoff

cb SPS P2 Y2- closeGfBL MTRS (4) - OFF (LMP Confinn)TRANS CONT PWR - OFFTVC SERVO PWR (2) - OFFMN BUS TIE (2) - OFFcb SPS P1amp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREIf est time to EIltOl5500 omlt fCC andenter the SUPERCIRC CKLIST as early as pos-slb1e Pg ~2~3~ __If est time to EI)Ol5500 anticlpate afCC Enter the ENTRY PREP CKLIST at step 9pg 18

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

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DEGREES IN wiiiiDOW

260

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-70-

~ I

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-1-

NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

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LUNAR RETURN VELOCITY

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TIME TO 400K FT ALTITUDE-MIN

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-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 6: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

-3-

Llst of Acronyms and Abbrevlatlons

GNDGPIG-VHAHEHPIMUKA

LIDLEBIMPLOSLVMANMCCMCC-HMESCMSFNMGAMKMNVRMaNMTRMTVCNOPTORIEN02PPGAPGNCSPIPAPLPLSSpassPRIMPRPLNTPSIAPTTPUGSPWRRRI R2 R3RADRCDRRCSROTREFSMMAT

GroundG~bal Posltlon IndlcatorAcceleratlon-VelocltyHelght of ApogeeHellumHeight of PerlgeeInertlal Measurement UnltDrag Acceleratlon necessary to lnltlate

constant drag controlLlft to Drag RatioLower Equlpment BayLunar Module PllotLoss of SlgnalLocal Vertlcal Llft Vector Launch VehlcleManualMldcourse CorrectlonMlssion Control Center - HoustonMaster Event Sequence ControllerManned Space Fllght NetworkMiddle Glmbal AngleMarkManeuverMonltorMotorManual Thrust Vector ControlDSKY NounOptlon OptlCSOrlentatlonOxygenPltch or CMC ProgramPressure Garment AssemblyPrlmary GUldance Navlgatlon and Control SystemPulse Integratlng Pendulous AccelerometerPlanetPortable Llfe Support SystemPosslblePrlmaryPropellantPounds Per Square Inch AbsolutePush to TalkPropellant Utllizatlon and Gaglng SystemPowerRoll or CMC RoutlneReglster 1 2 3RadlatorRecorderReactlon Control SystemAltltude RateReference to Stable Member Matrlx

-4-

L~st of Acronyms and Abbrev~at1ons

RELRET

RHCRNGROURRT

RSIRTGOSASCSSECSECSSELSEPSEQSFT

SM SIMSPASPSSTBYSXPSXTSTSTATBTBDTERMTFTFFTHBWLSTHCTIGTLITIl TLMTRNFR

TVCVVGVIOVLVMY

Rel1efReentry Elapsed TIme (Lunar Return Case) or Retro

Elapsed Time (Earth Orb~tal Case) For lunar returnsRET 1S zero at RRT For earth orb1tal entries RET iszero at the deorb1t burn tIme

Rotat1onal Hand ControllerRangeRout1neReentry Reference T~me (Based on MCC-H predicted time

of EI to nearest second)Roll Stab11~ty IndicatorRange to GoShaft AngleStab1lizat1on and Control SystemSecondarySequent1al Events Control SubsystemSelectSeparationSequentialShaft Angle for SXTS when spacecraft 1S at

ignit10n attitudeServ1ce ModuleCOAS Star P~tch AngleServ1ce Propuls~on SystemStandbyStar X Pos~t~on (COAS)SextantSextant StarTrunnion AngleTalkback D~splay T1me BaseTo Be DeterminedTerm~nate

Ttme FromTtme of FreefallThumbwheelsTranslational Hand ControllerTime of Ignit~on

Translunar Insert10nTelemetryTransferThrust Vector ControlVeloc~ty or DSKY VerbVeloc~ty To Be GatnedInertial Veloc~ty

Sktpout Veloc1tyVeloc~ty MeasuredYaw

-5-

3deg LUNAR REIUBN ENTRY TECHNIQUES

The t~mel~ne for lunar return entries is based on the recommendationsfound ~n reference 1 the s~mulator val~dated procedures ~n reference2 and the mission val~dated procedures listed in the onboard checkshylist for the C Pr~me m~ssion The event times are l~sted ~n reference3

The preparation for lunar return entr~es beg~ns at a conven~ent t~me

about 30 hours before entry ~nterface At th~s t=e MSFN sends up alldata suff~c~ent for reentry also an EMS entry selftest ~s made toassure max~mum confidence ~n the EMS operat~on during entry Thereshyafter var~ous system powerups and checks are ~n~t~ated as l~sted insect~on 51 and deta~led ~n reference 4 Nom~nally the PGNCS ~s upfor the ent~re m~ss~on However ~f ~t ~s not ~t ~s powered up atEI-7 hours ~n preparat~on for the last MCC and entry The last MCCdec~s~on ~s made at about EI-6 hours for the maneuver to be performedat EI-3 hours ~f needed Deta~ls of th~s maneuver are outl~ned ~n

reference 1 After the MCC time P52 ~s again selected and the IMU ~s

real~gned to the REFSMMAT If the IMU dr~ft ~s w~th~n tolerance thesubsequent IMUSCS dr~ft check will determ~ne if the SCS has dr~fted

excess~vely If so the other BMAGs are selected and the IMUSCScheck repeated Th~s check ~s followed by a repeat of the EMS ~V

counter check and accelerometer b~as check at EI-l hour 15 m~nutes

to determ~ne ~f the scale factor and b~as are adequate for entrymon~tor~ng F~nal stowage CM RCS preheat and pyro Cllcu~t and seshyquent~al tests are worked ~nto this t~meframe so that at EI-50 m~nutes

the MSFN w~ll be requested for a go to pyro arm by the crew ~n preparashyt~on for separat~on At 45 m~nutes before EI the CMC update programP27 can be selected to permit update of the landing po~nt locat~on andthe state vector The entry PAD data shown ~n sect~on 70 ~s thenvo~ced to the crew and recorded From th~s data the DET ~s set andstarted the EMS ~nit~al~zed and the RSI al~gned Prior to EI-20ffilnutes the crew w~ll have strapped-~n completed the~r presepara-t~on checkl~st and maneuvered to the entry att~tude At this pointEI-19 m~nutes the CMC entry program Fbl ~s selected by the CMP Ifthere was no entry PAD data because of commun~cat~on loss the veloshyc~ty and range to go from P61 ~s recorded and used ~n the EMS AtEI-15 m~nutes the spacecraft ~s p~tched down and the hor~zon ~s checkedagainst the 317 degree w~ndow scr~be l~ne and the FDAI att~tude Ifthere ~s s~gn~f~cant d~sagreement the PGNCS ~s suspected and the spaceshycraft ~s held on the w~ndow reference In P62 the spacecraft ~s yawed45 0 from th~s att~tude and separated from the SM After separat~on

the CM ~s yawed back ~n plane and the hor~zon check repeated At approxshy~mate1y EI-10 m~nutes the p~tch att~tude is w~th~n 450 of the CMCcommanded att~tude and P63 ~s entered automat~ca11y S~nce the CMCDAP tr~es to hold local p~tch attitude and the CMC ~s not ~n controlthe crew observes the p~tch error needle unpeg and approach zeroabout two m~nutes before 05g t~me Th~s serves as a gono go CMC

-6-

check for entry control If the FDAI pltch error does not decreaseto wlthln + 50 at 005g the PGNCS lS fa lied and the crew flies aconstant g-entry mode wlth EMS ranglng after the VelOClty decreaseto 25500 feet per second If the PGNCS lS acceptable the spaceshycraft control lS placed In CMC and the CMC mode lS placed ln autoshymatlc At 05g the EMS automatlcally starts lf the EMS mode sWltchwas posltloned to automatlc earller ThlS wlll be backed up manually3 seconds after the ground computed 05g tlme recorded on the entryPAD by placlng the EMS mode sWltch In manual lf lt has not startedautomatlcally At PGNCS 005g lndlcatlon the CMC program changesto P64 and from thls pOlnt the entry lS under entry DAP control

The lunar return entry nomlnally lS performed by the PGNCS to lnsurecontrol wlthln the overshoot and g llmlt llnes as well as optlmlzethe landlng point accuracy Although the hlgh speed entry lnvolvesa rapld sequency of events there are several monitorlng tasks forthe crew to determlne lf the automat~c contrails performlng correctly

An entry corr~dor ver~flcation check 1S made by observlng the lnltlalslope of the EMS V-g trace between 1 and 2 gs If the EMS lndlcatesthe need to reverse the LV orlentatlon and the lndependent g meterconflrms the EMS g lndlcatlon the SC lS immedlately orlented as aresult of the EMS ~nd~cat~on

The EMS g lnd~catlon ~s contlnuously checked durlng entry uSlng thelndependent g meter and the PGNCS g ~ndlcatlon as a thlrd voteDeC1Slons durlng the first entry (P64) are critlcal ln terms of bothexceSSlve g llnes and the PGNCS lS not commandlng (and SC respondlng)to correct the sltuatlon the PGNCS lS felled

The PGNCS gono go check for short range targets (1200-1400 n ml) forWhlCh P65 lS not used 1S d1fferent Slnce there are no CMC computedSk1p drag (DL) and skip velocity (VL) values The check uses the EMSscroll to determ1ne 1f the PGNCS lS commandlng the proper roll att1shytude to converge the EMS g level to a predetermlned PAD value (Do) ascomputed by MCC-H For the nom1nal target range of 1300 naut~cal

mlles the crew w1ll monltor the program change from P64 to P67 atapprox~matelyEI + 3 mlnutes For ranges greater than 1400 nauticalmlles the program w1ll transfer to the Upcontrol Program P65 whenVL ~s between 18000 and 25766 feet per second and constant drag hasbrought the CMC pred1cted range to wlthln 25 naut1cal m1les of thetarget range The P65 PGNCS gono go check cons1sts of determln1ng1pound both the DSKY d1splay of sk~pout drag (DL) and Sk1pout veloclty(VL) are w1thln the PAD llmlts In addltlon the EMS scroll lS mon1shytored to determ~ne lf the trace lS approach1ng the DL and VL values

Throughout entry the crew monltors the spacecraft response to the CMCroll commands by observlng the FDAI lndlcatlons If the commands are

-7-

apparently good and In agreement wlth the EMS but the spacecraftresponse is questlonable the crew manually takes over and fIlesthe CMC commands

If the Upcontrol Program P65 was entered the program wlll nomshylnally sWltch to the Flnal Entry Program P67 for target rangesbelow approxlmately 1800 nautlcal miles or to the Ballistlc Proshygram P66 for ranges greater than approxlmately 1800 nautlcalffilles The program transfer crlterla are more preclsely deflnedIn reference 1

If P66 lS entered the spacecraft lS automatlcally rolled to theIlftup heads-down attltude to permlt the horlzon to be vlewedfrom the wlndow durlng the second entry The entry attltude checklS made by comparlng the horlzon wlth a speclfled wlndow mark Ifthe check falls the crew manually malntalns the entry trlffi attltudeuSlng the horizon VleW for reference The EMS lS used for ranglngSlnce the veloclty has now decreased to below 25500 feet per second

The EMS scroll lS contlnuously used to monltor for exceSSlve g conshydltlons durlng the second entry If the EMS V-g trace vlolates theg Ilnes and the PGNCS lS not commandlng (and spacecraft respondlng)to correct the situatlon the PGNCS lS falled and the EMS lS usedfor ranglng after ltS g lndlcatlon has been conflrmed by the lndeshypendent g meter

The entry phase lS essentlally over when the relatlve veloclty ofthe spacecraft decreases to less than 1000 feet per second ThlSlS lndlcated In P67 when RTGO latltude and longltude are dlsplayedSlnce very Ilttle ranglng capablllty exists after thls pOlnt thespacecraft lS orlented elther full Ilft up or down dependlng on RTGOnegatlve or posltlve and the crew prepares for the earth landlngphase

31

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-13-

40 EARTH ORBITAL DEORBIT AND ENTRY TECHNIQUES

As outl~ned ~n reference 5 a nom~nal PGNCS entry from earth orb~t ~s

based on a preparat~on t~me of 2 hours and 40 m~nutes ~nclud~ng 2n~ght passes Th~s t~me ~ncludes approx~mately 20 minutes before thef~rst n~ght pass after the CMC update and PAD data have been rece2vedTh~s t~e also 2ncludes approx2mately 20 m2nutes after the secondn~ght pass to allow suffic~ent t2me to prepare for retrof2re after theIMU f2ne a12gnment It has been determ2ned coarse a12gnment accuracy~s adequate for retrof~re and entry and undoubtedly other funct20nscould be om2tted depend2ng on the c2rcumstances for the dec2s20n toreenter Descr2bed here2n are the nom2nal earth oro2tal entry proshycedures w2th pert2nent comments on system va12dat20n for real timeacceptance dec~s20ns

After the entry dec~s~on is made the crew transfers the PGNCS fromthe standby to the operate mode and rece~ves a CMe update w~th P27Next the maneuver PAD update ~s v02ced up and the 2n~t~al entry mode~s determ~ned During the ~n~tial n~ght pass the IMU or2entat~on ~s

estab12shed uS2ng P51 star s~ght2ngs to obta2n a REFSMMAT The preshyferred or~entat~on opt20n ~n P52 2S then selected to coarse a12gn theIMU uS2ng the des2red entry REFSMMAT determ2ned by MGG-H The GOO ~s

now al~gned to the IMU 2n preparat~on for an IMUSes dr~ft check Ifthe GOO ~nd~cates the ses dr2ft rate exceeds 10 degrees per hour ~n

any ax~s the check ~s repeated on the other BMAGs to estaol~sh if theGOO or Just the single set 2S unusuable Var20us sytem checks as 12sted2n sect20n 51 are performed as necessary cons2stent w2th the t2me12ned2ctates of the maJor act2v2t2es Included 2n these checks are the EMSself-tests and the dV counter test The latter requ2res the spacecraftbe placed ~n dr2ft2ng fl2ght w~th the funct20n sW2tch 2n the dV pos2t~on

If the counter reg2sters a change of more than 25 feet per second w2th2n100 seconds the scroll and counter are unre12able for mon2tor2ng thedeorb2t burn and entry rang2ng If the EMS self-test fails and t2medoes not allow further analysis a 5555 ERE entry 1S planned as thePGNGS backup entry mode After complet2on of these checks the entryPAD lS prov1ded by MeG-H The crew then selects the external dVprogram P30 and the appropr2ate deorb1t tbrust1ng program p40 or P41Dur2ng th2s per2od wh2ch 2ncludes the f1nal n2ght pass P52 may beselected to ver2fy the IMU a12gnment Since the retro att2tude hasbeen computed so that a w2ndow mark c01nc2des w2th the hor2zon atGETI th2s serves as the conclus2ve check on the PGNCS At 5 m2nutesbefore retrofire the att2tude check 1S made by ver1fY2ng that the 12degree scr~be 12ne ~s w2th2n 3 degrees of the hor2zon If not thePGNeS has fa2led and the ses 2S used for att2tude reference and the

V counter for burn durat~on control S2nce the ses att~tude wasa12gned to the IMU a real~gnment ~s necessary This ~s accompl~shed

by manually maneuver2ng the spacecraft to ma~nta1n the 24 degree wlodowmark on the hor2zon and releas1ng the GOO a12gn button at TIG - 2 m2nutes

-14-

Upon complet~on of the burn the tN res~duals are burned to W~th~n

02 feet per second If the PGNCS ~V counter or est~mated burnduration are ~n d~sagreement ~t must be estab1~shed whether suff~shy

c~ent veloc~ty has been suppl~ed to put the land~ng po~nt in thefootpr~nt The PGNCS data w~ll be used ~f ~t ~s conf~rmed by oneother source if not the ~V counter w~11 be used ~f ~t ~s conf~rmed

by the burn durat~on t~me If add~tional ~V ~s necessary the data~s ava~lable to the crew on an onboard chart found ~n Sect~on 80

Post burn entry preparat~on requ~res EMS ~n~t~al~zation RSI al~gnshy

ment and pre-separat~on funct~ons The crew then selects the ~n~t~al

entry program P61 and records the d~sp1ays as a check aga~nst PADdata Upon complet~on of these checks P62 ~s entered The crewmanually or~ents the spacecraft to the separat~on attitude and yaws450 to ~nsure aga~nst possible CM 8M recontact After separat~on

the spacecraft ~s maneuvered to the reentry tr~m att~tude wh~ch

places the hor~zon on the 3170 w~ndow mark at EI Shortly thereshyafter ~n P62 the entry DAP is act~vated and P63 in~t~ated Dur~ng

th~s t~e MCC-H has computed a postburn update and ~t ~s vo~ced tothe crew ~f d~fferent from preburn values The EMS scroll and rangecounter w~ll be adJusted accord~ngly ~f t~me perm~ts A f~nal PGNCScheck pr~or to 05g may be mon~tored at th~s t~e w~th the CMC modein free and the manual att~tude p~tch ~n acceleration command wh~le

the hor~zon reference ~s held the p~tch error needle w~ll decreaseto zero as EI ~s reached At RET 005g the EMS mode sw~tch ~s

turned to manual the entry 005-g sw~tch and EMS roll sw~tch areturned on and the spacecraft control sw~tched to CMC to beg~n DAPcontrol At the PGNCS 005-g ~ndicatwn the program change fromP63 to P64 ~s mon~tored and the t~e vo~ce recorded At th~s t~me

the EMS range counter check ~s made dur~ng the 10 second per~od

follow~ng EMS 005g Dur~ng th~s per~od the counter should countdown 40 + 10 naut~cal m~les At PGNCS 02-g ~nd~cation the changefrom P64-to P67 ~s monitored and the ~splay may be held by key~ngVERB ~n order to record the init~al downrange error d~splay andcompare ~t to the PAD value The PGNCS has fa~led ~f the two do notagree w~th~n + 100 naut~cal m~les In the event P67 has not appearedwhen both the-g-meter and the scroll ~nd~cate greater than 05g thePGNCS has sim~lar~ly fa~led In e~ther fa~lure the SCS is used foratt~tude reference w~th an EMS entry If the checks agree the crewrema~ns w~th automat~c DAP for the rema~nder of the entry

The entry phase ~s essentially over when the relat~ve velocity ofthe spacecraft decreases to less than 1000 feet per second Th~s

~s ~nd~cated ~n P67 when RTGO lat~tude and long~tude are d~splayed

S~nce very l~ttle rang~ng capab~l~ty exists after th~s pOint thespacecraft is or~ented either full l~ft up or down depending onRTGO negat~ve or pos~t~ve and the crew prepares for the earth land~ng

phase

-15-

41 TYP~cal Retrof~re and Entry Sequence of Events

Dec~s~on to reenter

P27 (CMC update)

Retrof~re PAD update

Entry mode dec~s~on

P51 (IMU or~entat~on determlnatlon) durlng f~rst dark per~od

P52 (IMU coarse allgnment)

EMS checks

Entry PAD update

P30 (external AV)

p40 (SPS thrust)

P52 (IMU f~ne al~gnment) durlng second dark per~od

p40 (SPS thrust)

Ign~t~on att~tude check

Retroflre

P61

P62

CMSM separat~on

P63

Postburn PAD update

Entry attltude check

p64 (beg~n DAP control at O05g)

P67 (PGNCS gono go check at O2g)

42

Retrof~re

and

En

try

Alt

ern

atlv

es

Sys

tem

fa~lure

PGNC

S

PGNC

San

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S

PGNC

San

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Fal

lure

bef

ore

Fal

lure

aft

er

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-3m~ns)

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bu

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SCS

bu

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GET

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Ian

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--

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-17-

5 0 DETAILED ENTRY PROCEDURES

In order to comblne slmilar procedures that are common to lunar returnentrles and earth orblt entrles the followlng procedures are dlvldedlnto categorles that allow a mlnlmum of dupllClty ThlS provldes asmaller tralnlng package and more closely resembles the onboard crewcheckllst when comparlson lS necessary

51 Entry Preparatlons for Superclucular and Earth Orbltal Entrles

1~e entry preparatlons are comblned In these procedures andsteps pecullar to elther superclrcular or earth orbltal entrlesare labeled accordlngly The tlme llstlngs In thlS sectlon areappllcable to only superclrcular entries Slnce the earth orbltalentry tlmellne lS a functlon of several varlables as descrlbedIn sectlon 40 and reference 5

-18-51 (Contlnued)

VEHICLE PREPARATION

l-

2

3

4

5

6 -0600h

7 -0535h

8

9

10 -0430h

INITIAL STOWAGE COMPLETED

CMC amp ISS START UP

SCS POWER UP

p51 - IMU ORIENTATION

LOAD DAPV48E 11102 01111 PRO ERO PRO

LAST MCC DECISION

NO COMM - P52 amp NAV SIGHTINGSNOMINAL - P2337 ONBOARD COMPARISON

DON MAE WESTS amp FOOT RESTRAINTS

VHF AM A - SIMPLEX

P 27 (SV REFSMMAT) MNVRamp ENTRY pAD UPDATES

11 -0415h P52 - IMU REALIGN(___) (OPTION 1)

12 P37 (NO COMM ONLY)

13

14

ECS CKS02 SUPPLY REFILLECS Monitor CkEVAP H20 CONT (2) vlvs - AUTOSUIT HEAT EXCH SEC GLY - FLOW

EPS CKS 1 3 4 (5 If reqd)

15 SPS CK (If req d)

16

17

18

RCS CKSSM RCS MOUlt CkCM RCS MOUlt Ck

CampW SYS CK

CMC SELF CK

19

20 -0345h

-03l5h-0300h

21

22

22A

-19-

DSKY COND LT TEST

MIDCOURSE MANEUVERP30 - EXT rVP404l - SPSRCS THRUSTINGMIDCOURSE (17) BURN

NO COMM NAV SIGHTINGS

ffiVR TO ENTRY ATT (Superc1rc only)V62E

V49E

22B F 06 22 DESIRED FINAL GMBL ANGLESLOAD ENTRY ATT PAD ANGLESPRO

22C F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) SC CONT - CMC

BMAG MODE (3) - RATE 2CMC MODE - AUTO

PRO(~N) SC CONT - SCS

MNVR to 22E

22D 06 18 AUTO MNVR TO FDAI RPY ANGLES

22E F 50 18 REQUEST TRIM(TRIM) Go to 22C(BYPASS) ENTR

23 -200hr BORESIGHT amp SXT STAR CHECKOPT MODE - CMCOPT ZERO - OFF

V41 N91E

F 21 92 SHAFT TRUNLoad SXTS angles

41 OPTICS DRIVE

CHECK SXT STAROPT ZERO - ZERO

CHECK BORESIGHT STAR (If ava11)

24 -0135h

25(___)

26

27 -0115h

-20-

P52 - lMU REALIGNRecord gyro torqu~ng anglesRp~----

YIf-7gt-Lno--re-c-ycle PS2If conflrmed use SCS for EMS entry

GDC ALIGNIf drlft gtLOohr change ratesource

FINAL STOWAGEOPTICS (except for hybrid)ORDEALGLY TO RAD SEC - BYPASS (verlfy)CooL pnl lnstalledY-Y struts (2) extendedStow Data Box R-12

EMS CHECKEMS FUNC - OFFcb EMS (2) - closeEMS MODE - STBYEMS FUNC - EMS TEST 1 (walt 5 sec)EMS MODE - NORMAL (walt 10 sec)

Check ind lts - offRANGE lnd - 00Slew halr1ine over notch

In self-test patternEMS FUNC - EMS TEST 2 (walt 10 sec)

05G It - on (all others out)EMS FUNC - EMS TEST 3

05G It - onRSI Lower It - on (10 sec Qater)Set RANGE counter to 58 nm+OO

EMS FUNC - EMS TEST 405G It - on (all others out)G-V trace w~thin pattern to lwr rt

corner 9GRANGE lnd counts down to 0+02

EMS FUNC - EMS TEST 505G It - onRSI upper lt - on (10 sec later)RANGE md - 00SCrlbe traces vertlcal llne 9g to

022+01ALIGN SCROLL TO ENTRY PATTERN (on

37K ft sec hne)EMS FUNC - RNG SET

G-V scroll assy traces vert llne022g to 0+01

EMS MODE - STBY

28

29

30 -OllOh

-21-

~V TEST (Deorb~t only)EMS FUNC - ~V SETVHF RNGSET ~V ~nd to 15868 fpsEMS MODE - NORMALEMS FUNC - ~V TEST

SPS THRUST LT - onoff (10 sec)~V ~nd stops at -01 to -415

EMS MODE - STBY

PRIMARY WATER EVAP ACTIVATIONGLY EVAP H20 FLOW - AUTOGLY EVAP STH PRESS - AUTOPRI ECS GLY PUMP - ACI

CM RCS PREHEATNote If sys test mtr 5cd6abcd

all read 39 vdc (28degF) or moreom~t preheat

cb RCS LOGIC (2) - closeCM RCS LOGIC - ONUP T1M CM - BLOCK (ver~fy)

cb CM RCS HTRS (2) - closeCM RCS HTRS - ON (LMP Conf~rm)

(20 mlU or III lowest rdg lS39 vdc) (Moultor Maufpress for press drop)

31 (___) FINAL GDC DRIFT CK (If req I d)If drlft gtlOohr Suspect GDC Do not

use RSI amp FDAI 2

32 -OO5Om

33

34

35

TERM CM RCS PREHEATUP TLM CM - BLOCK (venfy)CM RCS HTRS - OFFCM RCS LOGIC - OFF

SYSTEMS TEST PANEL CONFIGURATIONSYS TEST METER - 4BRNDZ XPNDR - OPERATECM RCS HTRS - OFFWASTE H20 DUMP - OFFURINE DUMP - OFF

LEB LIGHTING - OFF

SEC WATER EVAP ACTIVATIONGLY To RAD SEC vlv - BYPASSSEC COOL EVAP - EVAPSEC COOL PUMP - AC2

36

37

38 -OO45m

-22-

PYRO BATT CKcb PYRO A SEQ A - close (ver~fy)

cb PRYO B SEQ B - close (verify)DC IND - PYRO BAT A(B)

~If PYRO BAT A(B) lt 35 vdc cb PYRO A(B) seq A(B) - open~

PYRO A(B)BAT BUS A(B)TO PYRO~MN BUS TIE - close

cb MNA BAT C - closecb MNB BAT C - closeDC IND - MNBPNL 8 - All cbs closed except

PL VENT - open (ver~fy)

FLOAT BAG (3) - open (ver~fy)

DOCKING PROBE (2) - open (verlfy)EDS BAT (3) - open (ver~fy)

CM ReS HTRS (2) - open

CM RCS ACTIVATIONcb SECS ARM (2) - close (verlfy)cb SECS LOGIC (2) - close (verlfy)SECS LOGIC (2) - ONMSFN conflrm GO for PYRO ARM(~f poss)SECS PYRO ARM (2) - ARMCM RCS PRPLNT 1amp2 - ONCM RCS PRESS - ONRCS Ind sw - eMl then 2

He PRESS 3700-4400 pSlaMANF PRESS 287-302 pSla

SECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFF

P27 amp ENTRY PAD UPDATEGo To Entry Checkllst

Superclrc - pg ~2~3 _Hybnd - pg -----2~9L-__Normal Deorblt - pg __3L5L- _

-23-

52 SUPERCIRCULAR ENTRY

1 SET DET (up to ET)

2

3

4

5

3000(-30-00)

EMS INITIALIZATIONSET RNG TO PAD DATA RNGEMS FUNC - Vo SETSlew Scroll to Pad Data VIOEMS FUNC - ENTRY

RS I ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on (up)GDC ALIGN PB - PUSH amp HOLDYAW Tw - Pos~t~on RSI thru

45deg amp back to LIFT UPGDC ALIGN PB - ReleaseEMS ROLL - OFFA1~gn CDC to lMU

CM RCS RING A CKRCS TRNFR - CMcb CM RCS LOGIC MNB - openAUTO RCS SEL MNB (6) - OFFSC CONT - SCSTest R~ng A ThrustersSC CONT - CMCRCS TRNFR - SMAUTO RCS SEL (12) - MNAMNB

(hftoff conflg)cb CM RCS LOGIC MNB - close

OPTICS PWR - OFFCMP to COUCH

MN BUS TIE (2) - ONTAPE RCDR - REWIND

6 35middot0Om(-25middot 00)

-24-

SEPARATION CK LISTTVC SERVO PWR 1 - AClMNAcb ELS (2) - close (ver1fy)PRIM GLY TO RAn - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY vlv - OFFCAB PRESS REL vlv (2) - NORMGMBL MTRS (4) - STARTABORT SYS PRPLNT - RCS CMD (venfy)SM RCS PRIM PRPLNT (4) - ONVHF 11M (AampB) - OFFHI GAIN ANT PWR - OFFFC PUMPS (3) - OFFVer1fy s1ugle SU1t compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - 10101cb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2) - opencb HTRS OVLD (2) - openPOT H20 RTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANSEC COOL EVAP - RESETSEC COOL PUMP - off (etr)

MtiVR TO CMSM SEP P R ATTSC CONT - SCSCMC MODE - FREEMNVR TO PAD ATTR (0deg)PY----W)

-25-

SUPERCIRCULAR ENTRY (Cont~nued)

1

4100m(-1900)

P61 - ENTRY PREP

V37E 61E

k 05 09 01427 - ROLL REVERSED 05 09 01426 - IMU UNSAT ~

2 F 06 61 IMPACT LAT LONG HDS UPDN (+-)PRO (010

fps +00001)

3 F 06 60 GMAXVPREDGAMMA EIRecord

GMAXV400K----

GAMMA EI _PRO

(01deg fpsOldeg)

4 F 06 63 RTOGO (lnm) PAD _VIO (fps) PAD _TFE(m~n-sec)

Compare w~th ~M~SFN==C~f~o-r~P~GNS GONO GOIf NO COMM Set RTOGO amp VIO In EMS

amp lnltla11ze(ACCEPT) PRO(RECALC) V32E To 4

5 F 50 25

4300m

(-1700)

45 oOm(-1500)

500Om(-1000)

6 F 06 61

-26-

P62 - CMSM SEP amp PRE-ENTRY MNVRCAUTION Call No EXT Verbs In P62

00041 REQUEST CMSM SEPSC CONT - SCSFREE

COMPARE PITCH ATT WITH PAD DATA ---0=-

(W~thLU 5deg)YAW - 45deg OUT-OF-PLANE (LEFT)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTIRATE 2MN BUS TIE (2) - ON (ver~fy)

PRIM GLY TO RAD - BYPASS (verlfy)CM RCS LOGIC - ON (venfy)SECS LOGIC (2) - on (up)SECS PYRO ARM - ARMCMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 ps~a

CM RCS LOGIC - OFFSECS PYRO ARM (2) - SAFEMonltor VMAB

If lt25 vdc go to EMERGPOWERDOWN pg E6-l

AUTO RCS SEL AC ROLL (4) - OFFAUTO RCS SEL CM 2(6)-OFFAUTO RCS SEL CM 1(6)-MNAYAW back to 0degPITCH TO HORIZ TRACK ATT

ROLL - 0deg (LIFT UP)PITCH - 400K Horiz Mark (317deg)YAW - 0deg

ATT DB - MAXMAN ATT PITCH - ACCEL CMDEMS DATA - Ver~fy

EMS FliNC - ENTRY (ver~fy)

EMS MODE - NORMALcb SPS PampY (4) - openMAINT HORIZ TRK

PRO (Act ENTRY DAP)

IMPACT LATLONGHDSDN (01deg01deg-00001)PRO

7 POSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axis beyond 45deg of Vel vector)

8 06 64

58middot00m(-0200)

9

05G tlme(+0 )

(--=---)

06 68

-27-

P63 - ENTRY INIT

GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PIJR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRmDHORIZ CKPltch error needle goes toward

zero approachlng OSG tlmeMAN ATT (PITCH) - RATE CMD

If CMC lS GOBMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS I

FLY BETA If CMC NO GO ilt

1 SC CaNT - SCS I

FLY EMS k

p64 - ENTRY POST 05G

RTOGO AT 05G AGREES HITH EMS-venfyHORIZ CK05G Lt - ON (EMS START)

No EMS START wlthln 3 sec ~ EMS MODE - BACKUP VHF RNG c

05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds Llft DN

NNVR Llft DNEMS GONO GO

G-V Plot wlthln IlmltsRng ctr dwn 60plusmn7 durlng 10 sec

perlodMonltor G-meter for

convergence wlth pad data (Do)(Vlt27K fps) Go to 13

-28-

P65 - ENTRY - UP CONT (Vgt27K fps)

10 F 16 69 BETA (01middot) _DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT lt~ SC CONT - SCS FLY EMS

PRO

11 06 68 BETAVIHDOT (OIdegfpsfps)(VltV1+500 fps amp RnOT Neg) Go To 13

P66 - ENTRY - BALLISTIC (D(DL)

12 06 22 DESIRED GMBL ANGLES RPYMoultor horlz +12middot of 317middot mark

P67 - ENTRY - FINAL PHASE (02G)

13 06 66 BETACRSRNG ERRDNRNG ERR(010 1um 1um)

KEY VERBRecord DNRNG ERR _KEY RLSEMoultor l~ft vector ou RSI amp FDAI

16 67 RTOGOLATLONG (Vrel=1000fps)(lumOldegOldeg)

SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOWNMonitor a1t~meter

Go To EARTHLANDING pg ---4L5 _

-29-

53 GampN HYBRID DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL tV1 V37E 30E

2 F 06 33 GETI(ACCEPT) PRO (hrm~n Olsec)(REJECT) LOAD DESIRED GETI

3 F 06 81 tVXYZ (LV) (lfps)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

4 F 06 42 HAHPtV (lnm lfps)Record tV

(ACCEPT) PRO(REJECT) Reselect P30 or P27 Load new paramo

5 F 16 45 MTFIMGA (marksm~n-secOlO)

MGA -00002 ~f k

k lMU not al~gned

SET DETPRO

6

7

8

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (Pull)PLSS 02 vlv - FILL02 8M SUPPLY vlv - OFFCAB PRESS REL vlv (2) - NORMcb ELS (2) - closecb SECS ARM (2) - closecb SECS LOGIC (2) - close (ver~fy)

AUTO RCS SEL CM (12) - MNA or ~ffiB

(hftoff conhg)ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM (AampB) - OFF

CMP to Couch

9

10

11

-30-

MNVR TO PAD BURN ATTLOAD DAPBMAG MODE (3) - RATE 2SC CONT - CMCAUTOATT DB - MINMAN ATT (3) - RATE CMD

v62E

v49E

12 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLES

PRO

13 F 50 18 REQ MNVR TO FDAI RPY ANGLES (01deg)(AUTO) PRO(MAN) SC CONT - SCS

BMAG MODE (3) - RATE 2MNVR To 15

14 06 18 AUTO MNVR TO FDAI RPY ANGLES (01deg)

15 F 50 18 REQ TRIM TO FDAI RPY ANGLES (01deg)(TRIM) Go to 13(ByPASS) ENTR

16

17

CHECK BORESIGHT amp SKT STARSOPT MODE - CMCOPT ZERO - OFF

v41 N91E

18 F 21 92 SHAFTTRUN (01deg 001deg)Load SXTS angles

19 41 OPTICS DRIVECheck SKT STAR

OPT ZERO - ZEROCheck BORESIGHT STAR (~f ava~l)

20 V25 N17E (01deg)Load Pad Data GMBL Angles

for CM BURN ATTATT SETtw - SET

to PAD DATA GMBL ANGLESfor CM BURN ATT

21

22

-31-

PHR REDUCTIONHGA PHR - OFFFC PUMPS (3) - OFFVerify s~ngle su~t compr oper loads

balancedFC 2 MN AampB - OFFS BD PiR AMP - LOWcb ECS RAD CONTHTR (2) - opencb HASTE H20URINE DUMP HTRS(2)- opencb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANMN BUS TIE (2) - ONTVC SERVO PHR 1 - AC1MNAGMBL MTR (4) - START

p41 - RCS THRUSTINGV37E 41E

23 F 50 18 REQ MNVR TO LCL HORIZ (HDS ON)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CMCAUTOPRO To 24

(gtfANDAP) BMAG MODE (3) - RATE 2SC CONT - CMCHOLD

V62EMNVR To 25

24 06 18 AUTO MNVR TO FDAI RPY

25 F 50 18 REQ TRIM TO LCL HORIZ (01deg)ALIGN SC ROLL

(AUTO TRIM) PRO To 24(BYPASS) ATT DB - MIN

RATE - LOHMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTlRATE 2

ENTR

550Om26 06 85

59middot2527

-32-

VGXYZ (1fps)RECHECK BORESIGHT STARTRANS CONIR PWR - on (up)EMS MODE - STBY (ver~fy)

EMS FliNC - bV SETVHF RNGSET (IV for SM BURN _EMS FliNC - bVS BD ANT - OMNI CSECS LOGIC (2) - ONMSFN conhrm Go for PYRO ARMSECS PYRO ARM (2) - ARMCM RCS LOGIC - ON (ver~fy)

DSKY BLANKS

593028 16 85 VG XYZ (AVE G ON) (lfps)

RHCs amp THC - ARMEDLIMIT CYCLE - OFFTAPE RCDR - CMD RESETHBREMS MODE - NORMAL

000029 F 16 85 REQ NULL VG XYZ (lfps)

BURN EMS bV CTR TO ZERORESET DET amp COUNT UP

If SM ONLY burn go to step 32THC - LOCKEDSC CaNT - SCSFREERATE - HIGHPRIM GLY To RAD - BYPASS (ver~fy)

MN BUS TIE (2) - ON (ver~fy)

CMSM SEP (2) - on (up)CSMLM FNL SEP (2) - on (up) (verify)CampW MODE - CMRCS TRNFR - CMCM RCS LOGIC - OFF

Momtor VM ABIf lt25 vdc go to EMERGPOWER DOWN Pg E6-l

V63E

If CMC NO GO FDAI SOURCE - ATT FDAI SEL - 1 or 2 ATT SET - GDC

SET

-33-

~Uili ATT PITCH - ACCEL CMDFDAI SCALE - 55MNVR TO CM BURN ATT (NULL ERR NEEDLES)

R 0degPY --00--

30

31

CM RCS BURNRHC III-ContJnuous PJtch DownRHC HZ-Module PJtch to null needlesBURN VGZ TO ZERO

If only 1 RHC Pulse + P=5deg from retro att MaJnta~n rates lt3degsec

BURN COMPLETION ATllV CTR= or DET= _

V8ZE

32 F 16 44 HAHPTFF (1nmffiJn-sec)Check HP-

If gt Pad data contJnue burnuntJ1 lt Pad

PRO

33 F 16 85 VGXYZ (Ups)Read VG resJduals to MSFN

(HYBRID) PRO to 34(SM ONLY BURN)

PROF 37 ODE

EI-1500 V37E 47EF 16 83 twx Y Z (Ups)

SC CONT - SCSFREEMAN ATT (PITCH) - RATE CMDRATE - HIGHPRIM GLY To RAD - BYPASS (verJfy)MN BUS TIE (2) - ON (verJfy)CMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verJfy)Campl MODE - CMRCS TRNFR - CMCM ReS LOGIC - OFFSECS PYRO ~I (2) - SAFE

-34-

PROMonitor VMAB

If lt25 vdc go to EMERGPOWER DOWN

34 F 37 OOEPCM BIT RATE - LOWATT DB - MAXEMS MODE - STBYEMS FUNC - OFF

Go To EARTH ORBIT ENTRY pg _--40-__

-36-

8 SPS THRUSTING PREPCYCLE CRYO FANSSPS GAGING - ACI (ver~fy)

PUG MODE - NORM (venfy)BMAG MODE (3) - RATE 2tv CG - CSMCMC MODE - FREEAUTO RCS SEL (16) - MNA or HNB

(hftoff conbg)SC CONT - CMCAUTO

9 MNVR TO PAD BURN ATTV62E

10 V49E

11 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLESPRO

12 F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) PRO(HAN) SC CONT - ses

MNVR to 14

06 18 AUTO MNVR TO FDAI RPY ANGLES13

14 F 50 18 REO TRIH TO FDAI RPY ANGLES(TRIM) Go to 12(BYPASS) ENTR

15 BORESIGHT STAR CHECK

16 V37E 40EOPT PWR - OFF

17 F 50 18 REQUEST MNVR TO FDAI RPY ANGLES (01deg)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CHCAUTOPRO to 18

(MANDAP) BMAG HODE (3) - RATE 2SC CONT - CMCHOLDMNVR to 19

(HANseS) se eONT - sesMNVR to 19

-35-

54 NORMAL DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL ~V

1 V37E 30E

2 F 06 33 GETI (hrm~nOlsec)

(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

3 F 06 81 ~VXYZ (LV)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

( lfps)

4 F 06 42 HAHP~V (1nmlfps)Record W

(ACCEPT) PRO -----(REJECT) Rese1ect P30 or P27 Load new pa~am

5 F 16 45 MTFIMGA (marksmln-secOldeg)MGA -00002 If ~ lMU not a1~gned

SET DETPRO

6

7

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY v1v - OFFCAB PRESS REL v1v (2) - NORMcb ELS (2) - close (verify)cb SECS ARM (2) - close (ver~fy)

cb SECS LOGIC (2) - close (verlfy)AUTO RCS SEL CM (12) - ~mA or MNB

(l~ftoff conf~g)

ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM AampB - off (ctr)

18

-37-

06 18 AUTO MNVR TO FDAI RPY ANGLES (01 0)

19 l 50 18 REOUEST TRIM MNVR TOALIGN SIC ROLLGDC ALIGN

FDAI RPY ANGLES(010

)

+54-00m(-06-00)

TIG-5mJn

5500m(-0500)

TVC CHECK amp PREPcb STAB CONT SYS (all) - closecb SPS (12) - closeATT DB - MINRATE - LOl~

LIMIT CYCLE - ONMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE 2ROT CONTR PWR DIRECT (2) - OFFSCS TVC (2) - RATE CMD

If SCS SCS TVC (2) - AUTO SC CONT - SCS ~

TVC GMBL DRIVE PampY - AUTOMN BUS TIE (2) - ONTVC SERVO PWR 1 - AC1MNA

2 - AC2MNBTRANS CONTR PWR - ONROT CONTR PWR NORMAL 2 - ACRHC 2 - ARMED

HORIZ CHK - HorJz on 12deg wJndmlmark (LJffiJt +3 0 PNGCS GONO GO)

If NO GO set tw 180 0 180deg0 0

Track horJz wJth 24deg wJndow markAt TIG-2 mJn Ahgn GDC

PRIMARY TVC CHECKGMBL MOT P1-Y1 -STARTON(LMP confJrm)

If SCS verJfy Thumbwheel TrJmTHC - CWVenfy NO MTVC

SEC TVC CHECKGHBL MOT P2-Y2 -STARTON(LMP confJrm)SET GPI TRIHVenfy MTVCTHC NEUTRALGPI returns to 00 (CMC) or trJm (SCS)ROT CONT Pl~ NORM 2 - ACDC

(TRIM) Go to step 17(BYPASS) BMAG MODE(3) - ATTIRATE2 (ver1fy)

ENTR

-38-

20 F SO 25 00204 GMBL TEST OPTION(ACCEPT) SC CONT - GMC (ver~fy)

PROMonitor GPI Response

0020-2000020-200Tr~m

TEST FAIL SC CONT - SCS SCS TVC (2) - AUTO

(REJECT) ENTR

21 06 40 TFIVG~VM (m~n-sec1fps)

PROG ALM - TIG s1~pped

V5N9E 01703

KEY RLSE To 21 ROT CONTR PWR DIRECT (2) - MNABSPS He v1vs (2) - AUTO (ver~fy)

LIMIT CYCLE - OFFFDAI SCALE - SOIScb SPS P2Y2 - open (for cr~t burn)

5800(-02 00)

5925(-0035)

59middot 30(-0030)

06 40

59XX(-OOXX)

AV THRUST A(B) - NORMALTHC - ARMEDRlIC (2) - ARMEDTAPE RCDR - GID RESETHBR

DSKY BLANKS

(AVE G ON)EMS MODE - NORMAL

TFIVG~VM (m~n-seclfps)

CHECK PIPA BIAS lt2fps for 5 sec

ULLAGE AS REQ

IF NO ULLAGE DIR ULLAGE PB - PUSH~

CONTROL ATT WRlIC MONITOR AVM (R3) COUNTING UP

5955(-0005)

F 99 40 ENG ON ENABLE REQUEST(AUTO IGN) PRO AT TFI gt0 sec(BYPASS IGN) ENTR to 24

22 0000 IGN

-39-

If SCS - THRUST ON PB - PUSH

06 40 TFCVG~VM (m~n-seclfpslfps)

~F 97 40 SPS Thrust fall ~

~(RESTART) PRO To IGN (RECYCLE) ENTR To TIG-05 sec

SPS THRUST LITE - ONMONITOR THRUSTING

Pc 95-105 pSlaEMS COUNTING DOWNSPS IN3 v1vs (4) - OPENSPS He v1vs tb (2) - graySPS FUELOXID PRESS - 175-195 pSlaPUGS - BALANCED

PROG ALARM V5N9E 01407 VG INCTHC - CW FLY MTVC

ECOEMER SPS CUTOFF J

AV THRUST (2) - OFF

23 F 16 40 TFC(STATIC)VG~VM (mln-seclfps)~V THRUST AB - OFF

SPS IN3 v1vs (4) - CLOSEDSPS He tb (2) - bp

cb SPS P2Y2 - closed (verlfy)TVC SERVO PHR - AC1MNA (venfy)TVC SERVO PWR 2 - OFF

PRO

24 F 16 85 VG XYZ(CM) CUps)NULL RESIDUALSRECORD ~V CTR amp RESIDUALS I1VCEMS FUNC - OFF VGXEMS MODE - STBY VGYBMAG MODE (3) - RATE 2ATT DB - MAX VGZTRANS CONT PHR - OFF

PRO

25 F 37 V82E

26 F 16 44 HAHPTFF (lnmm~n-sec)

R3-59B59 HP gt494 nmPRO

27 F 37 OOE

-40-

55 EARTH ORBIT ENTRY

1 Venfy CMSMR __

P_shyY_-

SEP ATT(180deg)

(0deg )

2

3

4

EMS INITIALIZATIONEMS FUNC - RNG SETSET RNG TO PAD DATA RNGEMS FUNC - VA SETSlew scroll to pad data VIOEMS FUNC - ENTRY

RSI ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on(up)GDC ALIGN PB - PUSH amp HOLDYAW tw - Pos1tion RSI thru 45deg amp

back to LIFl UPGDC ALIGN PB - RELEASEEMS ROLL - OFFAl1gn GDC to lMU

PWR REDUCT (Norm Deorb Only)HGA PWR - OFFFC PUMPS (3) - OFFVer1fy s1ngle suit compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - Lowcb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2)-openlOb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MAN

-41-

P61 - ENTRY PREP

5 V37E 61E05 09 01427 - ROLL REVERSED05 09 01426 - IMU UNSAT

6 F 06 61 IMPACT LAT LONG liDS UPDN (+-)(01 0

010

+00001)

PRO

PAD VALUESLATLON==G------liDS UP DN _

7 F 06 60 GMAXV400KGAMMA EIRecord

GMAXV400K----GAMMA EI _

PRO

8 F 06 63 RTOGO (1nm) PAD _VIa (fps) PADTFE (mln-sec) ----Compare wlth MSFN for PGNS GONO GONO COMM SET RTOGO amp VIO IN EMS amp

INITIALIZE(ACCEPT) PRO(RECALC) V32E to 8

-42-

P62 - CMSM SEP amp PRE-ENTRY MNVR

9 F 50 25 00041 REQUEST CMSM SEPSC CONT - SCSFREEYAW - 45deg out-of-plane (left for RCS

nght for SPS)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE2PRIM GLY to RAD - BYPASS (verlfy)SECS LOGIC (2) - on (up)MSFN conflrm GO for PYRO ARMSECS PYRO ARM - ARMMN BUS TIE (2) - ON (verlfy)CMSM SEF (2) - ONCSMLM FNl SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 pSlaCM RCS LOGIC - OFFSECS PYRO ARM - SAFEMonltor VMAB

If lt25vdc go to EMERG POWERDOWN Pg E6-1AUTO RCS SEL AlC ROLL (4) - OFFAUTO RCS SEL CM 2(6) - OFFAUTO RCS SEL CM 1(6) - MNA or MNBYAW back to 00

PITCH TO ENTRY ATTROLL 0deg (LIFT UP)PITCH - HORIZ on 317deg MARK (400K)YAW 00

ATT DB - MAXMAN ATT (PITCH) - ACCEL CMDEMS DATA - VerifyEMS FUNC - ENTRY (verlfy)EMS MODE - NORMALMAINTAIN HORIZ TRK

PRO (Act ENTRY DAP)

10 F 06 61 IMPACT LAT LONG HDSDN(010 010 -00001)

PRO

11 FOSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axlS beyond 45deg of Vel vector)

-43-

P63 - ENTRY INIT

12 06 64 GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PWR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRHORIZ CKP~tch error needle goes toward

zero approach~ng 05G t~me

MAN ATT (PITCH) - RATE CMDIf CMC ~s GO

BMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS FLY BETA If CMC NO GO ~

SC CONT - SCS~

FLY EMS RCS Deorh Roll HDS UPTRACK HORIZ w~th 29deg w~ndow mk

P64 - ENTRY POST 05G

13

05G t=elt+0___)

06 68

RTOGO AT 05G AGREES WITH EMS - venfyHORIZ CK05E Lt - on (EMS start)

No EMS start w~th~n 3 secsEMS MODE - BACKUP VHF RNG 05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds L~ft DN

NNVR L~ft DNEMS GONO GO

G-V Plot w~th~n llm~ts

Rng ctr dwn 60 + 7 durlng 10 sec per~od

Mon~tor G-meter forconvergence wlth pad data (Do)

(Vlt27K fps) Go To 17

-44-

P65 - ENTRY - UP CONT (Vgt27K fps)

14 F 16 69 BETA (01deg)DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT~

SC CONT - SCS FLY EMS

PRO

15 06 68 BElA VI HOOT (01deg fpsfps)(VltVL +500 fps amp RDOT Neg) Go To 17

p66 - ENTRY - BALLISTIC (DltDL)

16 06 22 DESIRED GMBL ANGLES RPY (01deg)Mon~tor hor~z +12deg of 317deg mark

P67 - ENTRY - FINAL PHASE (02G)

17 0666 BETACRSRNG ERRDNRNG ERR (Oldeglnmlnm)KEY VERBRecord DNRNG ERR _KEY RLSEL~m~t +100nm from PAD DRE

Mon~tor l~ft vector on RSI amp FDAIF 16 67 RTOGOLATLONG (Vre1=1000fps)

(lnm 010 01deg)SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOlfflMon~tor altimeter

Go To EARTHLANDING pg _I4L5__

-45-

56 EARTHLANDING

90K STEAM PRESS - PEGGED50K CABIN PRESS REL vIv (2) - BOOSTENTRY

SECS PYRO ARM (2) - ARM

40K(90K + 63s)

CM UNSTABLE RCS CMD - OFF ~ 40K APEX COVER JETT PG-PUSH DROGUE DEPLOY PG - PUSH (2 secafter apex cover Jett)

30K ELS LOGIC - ON (up)ELS - AUTO

24K RCS hsable (auto)(90K+92s) RCS CMD - OFF

Apex cover Jett (auto)APEX COVER JETT PB - PUSH

(WAIT 2 SECS)Drogue parachutes deployed (auto)

DROGUE DEPLOY PB - PUSH~

If Drogues FallELS - ~ ~Stablllze CM 5K MAIN DPLY PB - PUSHELS - AUTO

235K Cabln Pressure lncreaslng (Drogues + 50s)If not lncreaSlng by 17K CABIN PRESS REL vlv (RR) - DUMP

-46-

10K Maln parachutes deployedMAIN DEPLOY PB - PUSH (wlthln 1 sec)VHF ANT - RECYVHF AMA - SIMPLEXVHF BCN - ONCABIN PRESS REL v1v (2) - CLOSEDIRECT 02 vlv - OPENCM RCS LOGIC - on (up)CM PRPLNT - DUMP (burn audlb1e)Monltor CM ReS 1amp2 for He press decrease

NO BURN or PRESS DECREASE USE BOTH RHCs DO NOT FIRE PITCH JETS

CM PRPLNT-PURGE (to zero He press)CM RCS He DUMP PB - PUSH RHC (2) - 30 sees NO PITCH k

STRUT LOCKS (2) - UNLOCK

cb FLT amp PL BAT BUS ABampBAT C (3) - closecb FLT amp PLT MNA amp B (2) - opencb ECS RAD HTR OVLD (2) - opencb SPS PampY (4) - open

3K CABIN PRESS REL v1v (RH) - DUMP (after purgecompleted)

FLOOD Lts - POST LDGCM RCS PRPLNT (2) - OFFROT CONTR PWR DIRECT (2) - OFF

800 CAB PRESS RELF vlv - CLOSE (latch off)MN BUS TIE (2) - OFF

AFTER LANDINGcb MAIN REL PYRO (2) - closeMAIN RELEASE - on(up)

Go to POSTLANDING pg _47L-__

I

2

3

-47-

57 POSTLANDING

STABILIZATION VENTILATION COMMUNICATIONS

DIRECT 02 vlv - CLOSE

Stablllzation after landlngELS - AUTO (verlfy)cb MAIN REL PYRO (2) - close (venfy)MAIN RELEASE - on (up) (verlfy)S~CS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb BAT RLY BUS (2) - open

No contact w1th recovery forcesVHF AM AampB - off (ctr) ~

VHF AM Rev ONLY - A cb PL VENT - closecb FLOAT BAG (3) - closecb UPRIGHT SYS COMPRESS (2) - closeIf Stable II

FLOAT BAG(3)-FILL t1ll 2 m1n afterupr1ght then - OFF

VHF AM AlB amp BCN - OFF whlle lnvertedIf Stable I

After 10 M1n Coollng Per1odFLOAT BAG (3) - FILL 7 mln then OFF

Post Stab1lizat1on And Ventllat10nPL BCN LT - BCN LT LOWPL VENT vlv - UNLOCK (Pull)Remove PL VENT Exh CoverPL VENT - HIGH or LOWPL DYE MARKER - ON (swlmmer comm)Release foots traps and_restralntscb MNA BAT BUS A amp BAT C (2) - opencb MNB BAT BUS B amp BAT C (2) - opencb FLT amp PL BAT C - opencb PYRO A SEQ A - opencb PYRO B SEQ B - open

EACH HR - CHECK DC VOLTSgt 275 V If Notmiddot cb FLT amp PL-BAT BUS AampB (2) -open cb FLT amp PL BAT C (1) - open GO TO LOW POWER CHECKLIST

Unstow and lnstall PLV DISTRIB DUCTDeploy grappllng hook and 11ne 1f req

4

-48-

Post Landing Communlcatl0nsVHF ANT-RECY (venfy)VHF BCN - ON (verlfy)

If no contact ~lth recovery forcesperform VHF BEACON Check

MONITOR VHF BEACON transmlSSlonnth VHF AM B Rcvr andor Su)vlval

TransceiverkVHF Beacon not operatlng ~connect Surv~val TranscelVer to antcable behlnd VHF ant access pnland place radio ln BCN mode

LOW POHER CHECKLISTVHF BCN - OFFVHF AM (3) - RCVFLOOD Lts - OFFVHF AM AampB - off (ctr)VHF AM RCV ONLY - A (venfy)COUCH LIGHTS - OFFPOSTLANDING VENT SYS mlnlmlze useSURV RADIO - plug mto VHF BCN ANT cableconn behind VHF ant acess pnl amp turn radloon l-n BCN mode

EGRESS PROCEDURES

CMPCDRLMPCDR

CMPCDRCMP

LMPLl1PCDR

STABLE IDlsconnect Umblll-calsNeck darn onCenter couch - 270 0 positionArmrests stowedConnect raft to SIC l-f desl-red wlth

green lanyardConnect raft ~hl-te lanyards to SUltS amp

lnflate water wlngs when eXltl-ngHATCH PISTON PRESS vlv - PRESS (Outbd)Slde Hatch openedPL VENT - OFFcb Pnl 250 (all) - openEgress with 11feraftPut hardware klt outEgress

or CDIPALL

CMF

CDRCMF

CDR

LMF

CMFCMP LMFCMP

UlP

CDR

-49-

STABLE IIcb CREW STA AUDIO (3) - openD~sconnect umb~1~ca1s

Release foots trapsRelease restra~nt harnessCouch seat pans (3) - 170 0 pos1t10nArm rests stowedSurv1va1 k~ts removed from stowageConnect life raft ma~n1~ne to CDR or SicConnect f~rst wh~te lanyard from

11fe raft to suitConnect th~rd wh~te lanyard from

l~fe raft to SU1tConnect rucksacks together to yellow

lanyard on raft bagPRESSURE EQUALIZATION vlv - OPENRemove and stow fwd hatchEX1t feet f1rst w1th rucksacks when clear

of siC 1nflate water w1ngs and raftExit feet f1rst when clear of SiC

1nflate water w1ngsEX1t feet f1rst when clear of sic

1nflate water w1ngs

-50-

60 TLI ABORTS

TLI Aborts are conta~ned ~n the ESD s~nce the bulk of the funct~ons

concern entry preparat20ns and performance Th~s allows a s2nglesource of procedures for procedure rev2ew val~dat~on checkout andtra~n~ng These procedures ~ncorporate TLI preparat20ns as found ~n

reference 6 w~th the TLI Abort Procedures and these t~e 2nto normallunar return Entry Procedures found ~n sect20n 5 The guidel~nes

for th~s cont2ngency are spec2f2ed 2n reference 7

In2t2al preparat~ons for TLI pos2t20n the necessary system sW2tches2n add~t~on to perform~ng an EMS ~V test and a GDC al~gnment Afterthe DET ~s set for mon2tor2ng TB6 the CMP ~ncreases the 12ght levelof the LEB DSKY to max~mum and returns to the h2s couch Th2s 2Sdone so that the LEB DSKY can be observed ~n the event sunl~ght orreflect20ns wash out the ma2n d2splay panel DSKY dur2ng cr2t2calmaneuvers The crew then straps ~n and prepares for mon2tor~ng TB6as 2nd2cated by the SII SEP L~te The t2mes se~uence of procedures2S keyed on th~s d~splay and ~ncludes the DET START funct~on andSIVB IGNITION Dur2ng the burn the crew mon2tors the FDAIs foratt~tude excurs20ns and abnormal rates report~ng status checks toM~ss2on Control at d2screet t~mes dur2ng the maneuver Upon SIVBSHUTDOWN the eMP records the DSKY d~splayed performance parametersand awa2ts ground conf2rmat~on

The rat~onal for TLI aborts ~s descr~bed 2n reference 7 A summar2shyzat20n 2S extracted to prov2de background and gu2de12nes 2n th2sdocument The abort procedures cover aborts 10 m2nutes after conshyt2ngent SIVE shutdown and aborts 90 m2nutes after normal SIVE shutshydown t2me

The 10 m~nute TLI abort ~s des2gned to be used dur~ng TLI ~n theevent a spacecraft problem develops Wh2Ch can result 2n catastrophe2f ~mmed~ate act~on 2S not taken If the s~tuat20n perm~ts the crewshould always allow the SIVB to complete TLI at wh~ch t~me the groundand crew can perform a malfunct~on analys~s to determ~ne ~f an abort~s adv~sable If a fa~lure occurs that necess2tates the shutdown ofthe SIVB and the ~u~ck return of the crew to earth th~s abort ~s

des~gned to be as ~nsens~t~ve to execut~on errors as poss~ble andst21l be targeted to m2dcorr2dor The burn att~tude w~th the f~ed

hor~zon reference ~s a constant value for any shutdown t~me Theburn durat~on 2S a funct20n of shutdown t2me and 2S ava21able fromcrew charts S~nce the pr~mary purpose of th~s abort ~s to returnto earth as qU2ckly as poss2ble there are no restr2ct20ns as toland~ng locat~on However ~f the t~me to EI is greater than abouttwo hours a midcourse correct20n should be ant~c~pated

The 90 m2nute TLI abort 2S to be used 2f a cr2t2cal subsystem malshyfunct~on ~s determ2ned and the dec2s~on to abort ~s made after the

-51-

TLI cutoff and before TLI cutoff plus approxlmately 80 m1nutesTh1S allows suff1c1ent separatlon and procedural t1me to set upfor the SPS deorb1t burn performed at about TLI + 90 Note thatgenerally the deorb1t burns w1ll be performed a fe11 m1nutes beforeTLI + 90 accord1ng to crew charts shown In reference 8 The no-comm except10n requ1res that 90 m1nutes be the 1nput t1me of 19n1shytlon for P-37 (onboard return-to-earth abort program) so that onshyboard calculatlons can correspond w1th ground calculat10ns to computethe CM land1ng p01nt Th1S TLI abort lS des1gned so that returnfl1ght t1me does not exceed 18 hours and abort ~V does not exceed7000 fps ThlS abort can be performed uSlng chart ~Vs and attltudesand the earths hor1zon serves as a suff1c1ent reference The maneushyver lS targeted to ach1eve the mldcorr1dor entry target Ilne andtlmed to result 1n a deslgnated recovery area

It 1S ObV10US for abort deC1S1ons early 1n the TLI + 90 m1nute t1meshyframe that a GampN SPS burn should be performed In order to keep theTLI abort procedures cons1stent and w1th emphasls on slmpl1c1ty theprocedures here reflect a SCS SPS abort burn to cover the full abortdec1s1on t1meframe

A m1dcourse correct1on for corr1dor control after a TLI abort may bedeS1red 1f the SPS burn d1d not meet expectat1ons The TLIabortprocedures 1n th1S sect10n adapt to the normal lunar return tlmel1neand procedures pr10r to the f1nal MCC

-52-

61 TLI PREPARATION PROCEDURES

GET = 150

CRO AOS(___)

CRO LOS( )(22142)

5100

Don Helmets amp Gloves

XLUNAR - INJECT (verify)EDS PWR - on (venfy)EMS FUNC - OFF (verlfy)EMS MODE - STBYEMS FUNC - IW SETVHF RNGEMS MODE - NORMALSet ~V indo to +15868 fpsEMS FUMC - ~V Test

SPS THRUST Lt - onoff (10 sec)~V lnd stops at -01 to -415

EMS MODE - STBYEMS FUMC - ~V SETVHF RNGSet ~VC

EMS FUNC---~~V=----

GDC ALIGNFDAI Select - liZcb SECS LOGIC (Z) - close (verify)cb SECS ARM (Z) - closeSECS LOGIC (Z) - on (up)MSFN Conflrm GO for PYRO ARM (If pass)SECS PYRO ARM (Z) - on (up)TRANS CONTROL PWR - ONROT CONTR PWR NORMAL (Z) - ACDC(verlfy)ROT CONTR PWR DIRECT (Z) - MNAMNBLV INnGPI - SIISIVB (venfy)LV GUID - IU (venfy)cb DIRECT ULLAGE (Z) - closedSet EVENT TIMER to 5100Begin MONITOR For TB6

CMP to Couch

TB 6 - SII SEP Lt on (TIG-9 mln 38 sec)KEY V83E

SET ORDEALFDAI Z ORB RATE at 180 0 0SII SEP Lt out (38 sec later)Start DET COUNTING UPSC CaNT - SCS (verify)MONITOR LV TANK PRESS

~P lt 36 psid (OXID gt FUEL)~P lt Z6 psid (FUEL gt OXID)

EMERGENCY CSMLV SEP UP TLM CM - BLOCK (verify)UP TLM IU - BLOCK (venfy)

-53-

+45degPY))0middot sec PY

lOK nmltHAlt25K nm

Two phas~ng mnvrs two SPS mnvrs to circular~ze at 150 nmearth orb~t

CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ssion 4K nmltHAltlOK nm CSM amp1M - Two phasing mnvrs two SPS mnvrs to circularize at 150 nm earth orb~t CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ss~on

CSM amp 1M - Two phas~ng mnvrs APS burn todepletion th~rd phasing mnvrSPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn tosem~sync orb~t

25K nmltHAlt40K nm CSM amp 1M - Two phasmg mnvrs APS burn to depletion third phas~ng mnvr SPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn to sem~sync orbit HA)40K nm DPS ava~l - DPS LOll circularize with SPS

DPS not ava~l - Lunar flyby or CSM only to lunar orbit (if reqd gtV lt4000 fps)

V37E 47E (check b~as) Record -=--rshy(Limit 98 fpsmm)

( 1fps)tVXYZN62EVIHDOTHPAD (fpsfpslnm)MONITOR VI ( ) at ECO

SCS TVC SERVO PWR 1 - ACIMNA2 - OFF

TAPE RCDR - CMD RESETHBREMS MODE - NORMAL

SIr SEP Lt - ONTLI Inhib~t S~gnals w~11 not be honored after 5942

SIVB ULLAGE BeginsSII SEP Lt - off (TIG - 18 sec)SIVB FUEL LEADSIVB ULLAGE d~scont~nues

LV ENG I Lt - onSIVB IGNITION ( GETI)LV ENG I Lt - off - -shyMONITOR THRUST amp ATTITUDEMONITOR LV TANK PRESSSIVE ECO (Lt on) (BEGIN TB7)

EMER SIVE CUTOFF AT 6 SEC PAST BURN TIME IF VI ATTAINEDTHC CCW ampNEUTRAL IN 1 SEC or SIISIVB sW - LV STAGEPremature Shutdown HAlt4K nm CSM amp 1M -

5700

58205836

F 16 835800

F 16 62

5838594259525955595900000002SUNRISE(___)

HAW AOS(__=_) KEY VERB (freeze d~splay)

SIVB ATT HOLD 20 sec amp BEGIN VENTINGSIVB NNVR TO ORB RT (HDS DN) (3middot sec)

Record VI -c---HDOT _

HPAD _

KEY RLSEF 16 62

F 16 83

HAW LOS(__=-)

KEYmiddotRLSE~VXYZ (lfps)

Record ~VX---_

~vy

WZ--

AVC---_

TAPE RCDR - off (ctr)EMS MODE - STBYEMS FUNC - OFFSECS PYRO ARM (2) - SAFE

PRO

BURN STATUS REPORT

____--~TIG

BT------VGX____-R

-----P----_Y

REMARKS

_____VI

______--HDOT______--H______---AVC______---FUEL_______OXID

_______UNBAL

F 3708=00 OOEGOS AOS CMP TO LEB

(-=-=-)

0000

0003

0005

0014

0100

-55-

62 TLI 10 MIN ABORTSECS LOGIC (2) - on (up)SECS PYRO ARM (2) - ARM

TRANS CONTR - CGH (4 sec) amp +XDET RESET (verlfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS GMD-ON

TRANS GONTR - neutral then +X for10 sec

SIVBGPI s~ - GPIExcesslve rates 6V THRUST A - NORMAL SPS THRUST - DIRECT When rates damped 6V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

TRANS CONTR +X - OFFV37E OOE

PITGH UP to LOGAL VERT (+X axlSto~ard the earth)

RATE - LOWBMAG MODE (3) - ATTIRATE 2EDS PHR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SEGS ARM (2) - opencb EDS (3) - open

TRANS CONTR -X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (180deg)P (199deg)Y (0deg)

RETRO UPDATEGETI _

JV _VG

Jtb ---GET 400K _

05G _GET DROGUE _

ENTRY P _R _

Y_--

0945

-56-

ALIGN HORIZ ON RET +1 MKGMBL CHECK (T11lle Pentattlng)MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conflnn)cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FUMC - JV SETVHF RNGSET JV from chartE~S FUMC - JVEMS fODE - NOIDlAL

lV THRUST A - NORMALV37E 47E (THRUST fONITOR)

F 16 83 lVXYZ (1 fps)

0950

1000

NOTE For aborts durlng 1st mln of TLIKEY V82E F 16 44 (HaHpTff)Burn untll Hp lt 19NM

TRANS CONTR +X

THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN JV reqdJV THRUST (2) - OFFReport cutoff

cb SPS P2 Y2- closeGfBL MTRS (4) - OFF (LMP Confinn)TRANS CONT PWR - OFFTVC SERVO PWR (2) - OFFMN BUS TIE (2) - OFFcb SPS P1amp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREIf est time to EIltOl5500 omlt fCC andenter the SUPERCIRC CKLIST as early as pos-slb1e Pg ~2~3~ __If est time to EI)Ol5500 anticlpate afCC Enter the ENTRY PREP CKLIST at step 9pg 18

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

-2tl C

l I W gt- ~-4

z laquo I I- 0 -6

l- I J u gt- ~-8

z w w -10

~_ONSANT

9O

VER

SHO

OT

BOU

ND

ARY

LIF

TV

EC

TOR

OR

IEN

TATI

ON

LIN

E

SH

ALL

OW

TAR

GE

TLI

NE

STE

EP

TAR

GE

TLI

NE 12

gU

ND

ERSH

OO

TBO

UN

DAR

Y

RE

EN

TRY

CO

RR

IDO

R

I ~ I

-12 24

26

28

30

32

34

RE

EN

TRY

VE

LOC

ITY

VE

1-F

TS

EC

Ch

art

1

36

3B

6-i

~

5CM

CC

ON

ST

NT

DR

VI z gt

~

I4

0 Cl W

I

gtamp

J+

-I

-

J Cl z

2U

l z 0_bull

bull-1

+-

u ubullbull

~r

U

)

2829

JOn

J23

33

43

5IN

ER

TIA

LR

EE

NTR

YV

ELO

CIT

YA

T4

00

00

0fl

VE

I-F

TS

EC

Ch

art

2

J63

73

8X

03

-i- rtREQUIRED PITCH GIMBAL ANG LETO OBTAIN HOR-IZON AT 317

DEGREES IN wiiiiDOW

260

z~I- ~ i5 24000

1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

-I

-1-

NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

I LU HD~-

LUHD

lt0 120UJ0

~

80 HOLD PRESENT TRIMgt LU HD013

~Y~HOIgtlt

TOP OF WINDOWa 40to

31 7 SCRIBEaaI

80 TTOM OF WINDOWi= 0

0--ltoa

-40t-z

~~~Uw w u lt0 -80

HOLO PRESENT TRIlJCl

LOHU0 lt0

J gt -120 HOLD 059 TRIMlt0 z

LDHUlt0 FIELD OF VI S10 NLDHU LIFT-DOWNHEADS -UPLUHD LIFT-UP HEADS-DOWN

~~H~-160 q - P63 LIMITI- NOrE-VALIO ONLY FO~t~--

LUNAR RETURN VELOCITY

plusmnl8020 244middot 8 12 16

TIME TO 400K FT ALTITUDE-MIN

4

P37

LONG

ITUD

ECO

RREC

TION

TOOB

TAIN

1350

NM

ENTR

YRA

NGE

Ugt

UJ

cgt

3z 0 I- u U

J0

0

0

2I

U~

UJ

cgt

I

gtI- U

gt z 0 J ltJ

1 -0

340

344

348

352

356

364

368

x10

3

CMC

INER

TIAL

VELO

CITY

AT40

0KAL

TITU

DE-

FTS

EC

Ch

art

5

I l I

o

20 100 -40

-10

-50

30

-20

--

+

-BB

A+

lrBB

A

=----

-----

t~I

AB

SA_

-04

0A

AV

Z=

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D_

+

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plusmniff

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90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 7: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

-4-

L~st of Acronyms and Abbrev~at1ons

RELRET

RHCRNGROURRT

RSIRTGOSASCSSECSECSSELSEPSEQSFT

SM SIMSPASPSSTBYSXPSXTSTSTATBTBDTERMTFTFFTHBWLSTHCTIGTLITIl TLMTRNFR

TVCVVGVIOVLVMY

Rel1efReentry Elapsed TIme (Lunar Return Case) or Retro

Elapsed Time (Earth Orb~tal Case) For lunar returnsRET 1S zero at RRT For earth orb1tal entries RET iszero at the deorb1t burn tIme

Rotat1onal Hand ControllerRangeRout1neReentry Reference T~me (Based on MCC-H predicted time

of EI to nearest second)Roll Stab11~ty IndicatorRange to GoShaft AngleStab1lizat1on and Control SystemSecondarySequent1al Events Control SubsystemSelectSeparationSequentialShaft Angle for SXTS when spacecraft 1S at

ignit10n attitudeServ1ce ModuleCOAS Star P~tch AngleServ1ce Propuls~on SystemStandbyStar X Pos~t~on (COAS)SextantSextant StarTrunnion AngleTalkback D~splay T1me BaseTo Be DeterminedTerm~nate

Ttme FromTtme of FreefallThumbwheelsTranslational Hand ControllerTime of Ignit~on

Translunar Insert10nTelemetryTransferThrust Vector ControlVeloc~ty or DSKY VerbVeloc~ty To Be GatnedInertial Veloc~ty

Sktpout Veloc1tyVeloc~ty MeasuredYaw

-5-

3deg LUNAR REIUBN ENTRY TECHNIQUES

The t~mel~ne for lunar return entries is based on the recommendationsfound ~n reference 1 the s~mulator val~dated procedures ~n reference2 and the mission val~dated procedures listed in the onboard checkshylist for the C Pr~me m~ssion The event times are l~sted ~n reference3

The preparation for lunar return entr~es beg~ns at a conven~ent t~me

about 30 hours before entry ~nterface At th~s t=e MSFN sends up alldata suff~c~ent for reentry also an EMS entry selftest ~s made toassure max~mum confidence ~n the EMS operat~on during entry Thereshyafter var~ous system powerups and checks are ~n~t~ated as l~sted insect~on 51 and deta~led ~n reference 4 Nom~nally the PGNCS ~s upfor the ent~re m~ss~on However ~f ~t ~s not ~t ~s powered up atEI-7 hours ~n preparat~on for the last MCC and entry The last MCCdec~s~on ~s made at about EI-6 hours for the maneuver to be performedat EI-3 hours ~f needed Deta~ls of th~s maneuver are outl~ned ~n

reference 1 After the MCC time P52 ~s again selected and the IMU ~s

real~gned to the REFSMMAT If the IMU dr~ft ~s w~th~n tolerance thesubsequent IMUSCS dr~ft check will determ~ne if the SCS has dr~fted

excess~vely If so the other BMAGs are selected and the IMUSCScheck repeated Th~s check ~s followed by a repeat of the EMS ~V

counter check and accelerometer b~as check at EI-l hour 15 m~nutes

to determ~ne ~f the scale factor and b~as are adequate for entrymon~tor~ng F~nal stowage CM RCS preheat and pyro Cllcu~t and seshyquent~al tests are worked ~nto this t~meframe so that at EI-50 m~nutes

the MSFN w~ll be requested for a go to pyro arm by the crew ~n preparashyt~on for separat~on At 45 m~nutes before EI the CMC update programP27 can be selected to permit update of the landing po~nt locat~on andthe state vector The entry PAD data shown ~n sect~on 70 ~s thenvo~ced to the crew and recorded From th~s data the DET ~s set andstarted the EMS ~nit~al~zed and the RSI al~gned Prior to EI-20ffilnutes the crew w~ll have strapped-~n completed the~r presepara-t~on checkl~st and maneuvered to the entry att~tude At this pointEI-19 m~nutes the CMC entry program Fbl ~s selected by the CMP Ifthere was no entry PAD data because of commun~cat~on loss the veloshyc~ty and range to go from P61 ~s recorded and used ~n the EMS AtEI-15 m~nutes the spacecraft ~s p~tched down and the hor~zon ~s checkedagainst the 317 degree w~ndow scr~be l~ne and the FDAI att~tude Ifthere ~s s~gn~f~cant d~sagreement the PGNCS ~s suspected and the spaceshycraft ~s held on the w~ndow reference In P62 the spacecraft ~s yawed45 0 from th~s att~tude and separated from the SM After separat~on

the CM ~s yawed back ~n plane and the hor~zon check repeated At approxshy~mate1y EI-10 m~nutes the p~tch att~tude is w~th~n 450 of the CMCcommanded att~tude and P63 ~s entered automat~ca11y S~nce the CMCDAP tr~es to hold local p~tch attitude and the CMC ~s not ~n controlthe crew observes the p~tch error needle unpeg and approach zeroabout two m~nutes before 05g t~me Th~s serves as a gono go CMC

-6-

check for entry control If the FDAI pltch error does not decreaseto wlthln + 50 at 005g the PGNCS lS fa lied and the crew flies aconstant g-entry mode wlth EMS ranglng after the VelOClty decreaseto 25500 feet per second If the PGNCS lS acceptable the spaceshycraft control lS placed In CMC and the CMC mode lS placed ln autoshymatlc At 05g the EMS automatlcally starts lf the EMS mode sWltchwas posltloned to automatlc earller ThlS wlll be backed up manually3 seconds after the ground computed 05g tlme recorded on the entryPAD by placlng the EMS mode sWltch In manual lf lt has not startedautomatlcally At PGNCS 005g lndlcatlon the CMC program changesto P64 and from thls pOlnt the entry lS under entry DAP control

The lunar return entry nomlnally lS performed by the PGNCS to lnsurecontrol wlthln the overshoot and g llmlt llnes as well as optlmlzethe landlng point accuracy Although the hlgh speed entry lnvolvesa rapld sequency of events there are several monitorlng tasks forthe crew to determlne lf the automat~c contrails performlng correctly

An entry corr~dor ver~flcation check 1S made by observlng the lnltlalslope of the EMS V-g trace between 1 and 2 gs If the EMS lndlcatesthe need to reverse the LV orlentatlon and the lndependent g meterconflrms the EMS g lndlcatlon the SC lS immedlately orlented as aresult of the EMS ~nd~cat~on

The EMS g lnd~catlon ~s contlnuously checked durlng entry uSlng thelndependent g meter and the PGNCS g ~ndlcatlon as a thlrd voteDeC1Slons durlng the first entry (P64) are critlcal ln terms of bothexceSSlve g llnes and the PGNCS lS not commandlng (and SC respondlng)to correct the sltuatlon the PGNCS lS felled

The PGNCS gono go check for short range targets (1200-1400 n ml) forWhlCh P65 lS not used 1S d1fferent Slnce there are no CMC computedSk1p drag (DL) and skip velocity (VL) values The check uses the EMSscroll to determ1ne 1f the PGNCS lS commandlng the proper roll att1shytude to converge the EMS g level to a predetermlned PAD value (Do) ascomputed by MCC-H For the nom1nal target range of 1300 naut~cal

mlles the crew w1ll monltor the program change from P64 to P67 atapprox~matelyEI + 3 mlnutes For ranges greater than 1400 nauticalmlles the program w1ll transfer to the Upcontrol Program P65 whenVL ~s between 18000 and 25766 feet per second and constant drag hasbrought the CMC pred1cted range to wlthln 25 naut1cal m1les of thetarget range The P65 PGNCS gono go check cons1sts of determln1ng1pound both the DSKY d1splay of sk~pout drag (DL) and Sk1pout veloclty(VL) are w1thln the PAD llmlts In addltlon the EMS scroll lS mon1shytored to determ~ne lf the trace lS approach1ng the DL and VL values

Throughout entry the crew monltors the spacecraft response to the CMCroll commands by observlng the FDAI lndlcatlons If the commands are

-7-

apparently good and In agreement wlth the EMS but the spacecraftresponse is questlonable the crew manually takes over and fIlesthe CMC commands

If the Upcontrol Program P65 was entered the program wlll nomshylnally sWltch to the Flnal Entry Program P67 for target rangesbelow approxlmately 1800 nautlcal miles or to the Ballistlc Proshygram P66 for ranges greater than approxlmately 1800 nautlcalffilles The program transfer crlterla are more preclsely deflnedIn reference 1

If P66 lS entered the spacecraft lS automatlcally rolled to theIlftup heads-down attltude to permlt the horlzon to be vlewedfrom the wlndow durlng the second entry The entry attltude checklS made by comparlng the horlzon wlth a speclfled wlndow mark Ifthe check falls the crew manually malntalns the entry trlffi attltudeuSlng the horizon VleW for reference The EMS lS used for ranglngSlnce the veloclty has now decreased to below 25500 feet per second

The EMS scroll lS contlnuously used to monltor for exceSSlve g conshydltlons durlng the second entry If the EMS V-g trace vlolates theg Ilnes and the PGNCS lS not commandlng (and spacecraft respondlng)to correct the situatlon the PGNCS lS falled and the EMS lS usedfor ranglng after ltS g lndlcatlon has been conflrmed by the lndeshypendent g meter

The entry phase lS essentlally over when the relatlve veloclty ofthe spacecraft decreases to less than 1000 feet per second ThlSlS lndlcated In P67 when RTGO latltude and longltude are dlsplayedSlnce very Ilttle ranglng capablllty exists after thls pOlnt thespacecraft lS orlented elther full Ilft up or down dependlng on RTGOnegatlve or posltlve and the crew prepares for the earth landlngphase

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-13-

40 EARTH ORBITAL DEORBIT AND ENTRY TECHNIQUES

As outl~ned ~n reference 5 a nom~nal PGNCS entry from earth orb~t ~s

based on a preparat~on t~me of 2 hours and 40 m~nutes ~nclud~ng 2n~ght passes Th~s t~me ~ncludes approx~mately 20 minutes before thef~rst n~ght pass after the CMC update and PAD data have been rece2vedTh~s t~e also 2ncludes approx2mately 20 m2nutes after the secondn~ght pass to allow suffic~ent t2me to prepare for retrof2re after theIMU f2ne a12gnment It has been determ2ned coarse a12gnment accuracy~s adequate for retrof~re and entry and undoubtedly other funct20nscould be om2tted depend2ng on the c2rcumstances for the dec2s20n toreenter Descr2bed here2n are the nom2nal earth oro2tal entry proshycedures w2th pert2nent comments on system va12dat20n for real timeacceptance dec~s20ns

After the entry dec~s~on is made the crew transfers the PGNCS fromthe standby to the operate mode and rece~ves a CMe update w~th P27Next the maneuver PAD update ~s v02ced up and the 2n~t~al entry mode~s determ~ned During the ~n~tial n~ght pass the IMU or2entat~on ~s

estab12shed uS2ng P51 star s~ght2ngs to obta2n a REFSMMAT The preshyferred or~entat~on opt20n ~n P52 2S then selected to coarse a12gn theIMU uS2ng the des2red entry REFSMMAT determ2ned by MGG-H The GOO ~s

now al~gned to the IMU 2n preparat~on for an IMUSes dr~ft check Ifthe GOO ~nd~cates the ses dr2ft rate exceeds 10 degrees per hour ~n

any ax~s the check ~s repeated on the other BMAGs to estaol~sh if theGOO or Just the single set 2S unusuable Var20us sytem checks as 12sted2n sect20n 51 are performed as necessary cons2stent w2th the t2me12ned2ctates of the maJor act2v2t2es Included 2n these checks are the EMSself-tests and the dV counter test The latter requ2res the spacecraftbe placed ~n dr2ft2ng fl2ght w~th the funct20n sW2tch 2n the dV pos2t~on

If the counter reg2sters a change of more than 25 feet per second w2th2n100 seconds the scroll and counter are unre12able for mon2tor2ng thedeorb2t burn and entry rang2ng If the EMS self-test fails and t2medoes not allow further analysis a 5555 ERE entry 1S planned as thePGNGS backup entry mode After complet2on of these checks the entryPAD lS prov1ded by MeG-H The crew then selects the external dVprogram P30 and the appropr2ate deorb1t tbrust1ng program p40 or P41Dur2ng th2s per2od wh2ch 2ncludes the f1nal n2ght pass P52 may beselected to ver2fy the IMU a12gnment Since the retro att2tude hasbeen computed so that a w2ndow mark c01nc2des w2th the hor2zon atGETI th2s serves as the conclus2ve check on the PGNCS At 5 m2nutesbefore retrofire the att2tude check 1S made by ver1fY2ng that the 12degree scr~be 12ne ~s w2th2n 3 degrees of the hor2zon If not thePGNeS has fa2led and the ses 2S used for att2tude reference and the

V counter for burn durat~on control S2nce the ses att~tude wasa12gned to the IMU a real~gnment ~s necessary This ~s accompl~shed

by manually maneuver2ng the spacecraft to ma~nta1n the 24 degree wlodowmark on the hor2zon and releas1ng the GOO a12gn button at TIG - 2 m2nutes

-14-

Upon complet~on of the burn the tN res~duals are burned to W~th~n

02 feet per second If the PGNCS ~V counter or est~mated burnduration are ~n d~sagreement ~t must be estab1~shed whether suff~shy

c~ent veloc~ty has been suppl~ed to put the land~ng po~nt in thefootpr~nt The PGNCS data w~ll be used ~f ~t ~s conf~rmed by oneother source if not the ~V counter w~11 be used ~f ~t ~s conf~rmed

by the burn durat~on t~me If add~tional ~V ~s necessary the data~s ava~lable to the crew on an onboard chart found ~n Sect~on 80

Post burn entry preparat~on requ~res EMS ~n~t~al~zation RSI al~gnshy

ment and pre-separat~on funct~ons The crew then selects the ~n~t~al

entry program P61 and records the d~sp1ays as a check aga~nst PADdata Upon complet~on of these checks P62 ~s entered The crewmanually or~ents the spacecraft to the separat~on attitude and yaws450 to ~nsure aga~nst possible CM 8M recontact After separat~on

the spacecraft ~s maneuvered to the reentry tr~m att~tude wh~ch

places the hor~zon on the 3170 w~ndow mark at EI Shortly thereshyafter ~n P62 the entry DAP is act~vated and P63 in~t~ated Dur~ng

th~s t~e MCC-H has computed a postburn update and ~t ~s vo~ced tothe crew ~f d~fferent from preburn values The EMS scroll and rangecounter w~ll be adJusted accord~ngly ~f t~me perm~ts A f~nal PGNCScheck pr~or to 05g may be mon~tored at th~s t~e w~th the CMC modein free and the manual att~tude p~tch ~n acceleration command wh~le

the hor~zon reference ~s held the p~tch error needle w~ll decreaseto zero as EI ~s reached At RET 005g the EMS mode sw~tch ~s

turned to manual the entry 005-g sw~tch and EMS roll sw~tch areturned on and the spacecraft control sw~tched to CMC to beg~n DAPcontrol At the PGNCS 005-g ~ndicatwn the program change fromP63 to P64 ~s mon~tored and the t~e vo~ce recorded At th~s t~me

the EMS range counter check ~s made dur~ng the 10 second per~od

follow~ng EMS 005g Dur~ng th~s per~od the counter should countdown 40 + 10 naut~cal m~les At PGNCS 02-g ~nd~cation the changefrom P64-to P67 ~s monitored and the ~splay may be held by key~ngVERB ~n order to record the init~al downrange error d~splay andcompare ~t to the PAD value The PGNCS has fa~led ~f the two do notagree w~th~n + 100 naut~cal m~les In the event P67 has not appearedwhen both the-g-meter and the scroll ~nd~cate greater than 05g thePGNCS has sim~lar~ly fa~led In e~ther fa~lure the SCS is used foratt~tude reference w~th an EMS entry If the checks agree the crewrema~ns w~th automat~c DAP for the rema~nder of the entry

The entry phase ~s essentially over when the relat~ve velocity ofthe spacecraft decreases to less than 1000 feet per second Th~s

~s ~nd~cated ~n P67 when RTGO lat~tude and long~tude are d~splayed

S~nce very l~ttle rang~ng capab~l~ty exists after th~s pOint thespacecraft is or~ented either full l~ft up or down depending onRTGO negat~ve or pos~t~ve and the crew prepares for the earth land~ng

phase

-15-

41 TYP~cal Retrof~re and Entry Sequence of Events

Dec~s~on to reenter

P27 (CMC update)

Retrof~re PAD update

Entry mode dec~s~on

P51 (IMU or~entat~on determlnatlon) durlng f~rst dark per~od

P52 (IMU coarse allgnment)

EMS checks

Entry PAD update

P30 (external AV)

p40 (SPS thrust)

P52 (IMU f~ne al~gnment) durlng second dark per~od

p40 (SPS thrust)

Ign~t~on att~tude check

Retroflre

P61

P62

CMSM separat~on

P63

Postburn PAD update

Entry attltude check

p64 (beg~n DAP control at O05g)

P67 (PGNCS gono go check at O2g)

42

Retrof~re

and

En

try

Alt

ern

atlv

es

Sys

tem

fa~lure

PGNC

S

PGNC

San

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PGNC

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del

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y

-17-

5 0 DETAILED ENTRY PROCEDURES

In order to comblne slmilar procedures that are common to lunar returnentrles and earth orblt entrles the followlng procedures are dlvldedlnto categorles that allow a mlnlmum of dupllClty ThlS provldes asmaller tralnlng package and more closely resembles the onboard crewcheckllst when comparlson lS necessary

51 Entry Preparatlons for Superclucular and Earth Orbltal Entrles

1~e entry preparatlons are comblned In these procedures andsteps pecullar to elther superclrcular or earth orbltal entrlesare labeled accordlngly The tlme llstlngs In thlS sectlon areappllcable to only superclrcular entries Slnce the earth orbltalentry tlmellne lS a functlon of several varlables as descrlbedIn sectlon 40 and reference 5

-18-51 (Contlnued)

VEHICLE PREPARATION

l-

2

3

4

5

6 -0600h

7 -0535h

8

9

10 -0430h

INITIAL STOWAGE COMPLETED

CMC amp ISS START UP

SCS POWER UP

p51 - IMU ORIENTATION

LOAD DAPV48E 11102 01111 PRO ERO PRO

LAST MCC DECISION

NO COMM - P52 amp NAV SIGHTINGSNOMINAL - P2337 ONBOARD COMPARISON

DON MAE WESTS amp FOOT RESTRAINTS

VHF AM A - SIMPLEX

P 27 (SV REFSMMAT) MNVRamp ENTRY pAD UPDATES

11 -0415h P52 - IMU REALIGN(___) (OPTION 1)

12 P37 (NO COMM ONLY)

13

14

ECS CKS02 SUPPLY REFILLECS Monitor CkEVAP H20 CONT (2) vlvs - AUTOSUIT HEAT EXCH SEC GLY - FLOW

EPS CKS 1 3 4 (5 If reqd)

15 SPS CK (If req d)

16

17

18

RCS CKSSM RCS MOUlt CkCM RCS MOUlt Ck

CampW SYS CK

CMC SELF CK

19

20 -0345h

-03l5h-0300h

21

22

22A

-19-

DSKY COND LT TEST

MIDCOURSE MANEUVERP30 - EXT rVP404l - SPSRCS THRUSTINGMIDCOURSE (17) BURN

NO COMM NAV SIGHTINGS

ffiVR TO ENTRY ATT (Superc1rc only)V62E

V49E

22B F 06 22 DESIRED FINAL GMBL ANGLESLOAD ENTRY ATT PAD ANGLESPRO

22C F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) SC CONT - CMC

BMAG MODE (3) - RATE 2CMC MODE - AUTO

PRO(~N) SC CONT - SCS

MNVR to 22E

22D 06 18 AUTO MNVR TO FDAI RPY ANGLES

22E F 50 18 REQUEST TRIM(TRIM) Go to 22C(BYPASS) ENTR

23 -200hr BORESIGHT amp SXT STAR CHECKOPT MODE - CMCOPT ZERO - OFF

V41 N91E

F 21 92 SHAFT TRUNLoad SXTS angles

41 OPTICS DRIVE

CHECK SXT STAROPT ZERO - ZERO

CHECK BORESIGHT STAR (If ava11)

24 -0135h

25(___)

26

27 -0115h

-20-

P52 - lMU REALIGNRecord gyro torqu~ng anglesRp~----

YIf-7gt-Lno--re-c-ycle PS2If conflrmed use SCS for EMS entry

GDC ALIGNIf drlft gtLOohr change ratesource

FINAL STOWAGEOPTICS (except for hybrid)ORDEALGLY TO RAD SEC - BYPASS (verlfy)CooL pnl lnstalledY-Y struts (2) extendedStow Data Box R-12

EMS CHECKEMS FUNC - OFFcb EMS (2) - closeEMS MODE - STBYEMS FUNC - EMS TEST 1 (walt 5 sec)EMS MODE - NORMAL (walt 10 sec)

Check ind lts - offRANGE lnd - 00Slew halr1ine over notch

In self-test patternEMS FUNC - EMS TEST 2 (walt 10 sec)

05G It - on (all others out)EMS FUNC - EMS TEST 3

05G It - onRSI Lower It - on (10 sec Qater)Set RANGE counter to 58 nm+OO

EMS FUNC - EMS TEST 405G It - on (all others out)G-V trace w~thin pattern to lwr rt

corner 9GRANGE lnd counts down to 0+02

EMS FUNC - EMS TEST 505G It - onRSI upper lt - on (10 sec later)RANGE md - 00SCrlbe traces vertlcal llne 9g to

022+01ALIGN SCROLL TO ENTRY PATTERN (on

37K ft sec hne)EMS FUNC - RNG SET

G-V scroll assy traces vert llne022g to 0+01

EMS MODE - STBY

28

29

30 -OllOh

-21-

~V TEST (Deorb~t only)EMS FUNC - ~V SETVHF RNGSET ~V ~nd to 15868 fpsEMS MODE - NORMALEMS FUNC - ~V TEST

SPS THRUST LT - onoff (10 sec)~V ~nd stops at -01 to -415

EMS MODE - STBY

PRIMARY WATER EVAP ACTIVATIONGLY EVAP H20 FLOW - AUTOGLY EVAP STH PRESS - AUTOPRI ECS GLY PUMP - ACI

CM RCS PREHEATNote If sys test mtr 5cd6abcd

all read 39 vdc (28degF) or moreom~t preheat

cb RCS LOGIC (2) - closeCM RCS LOGIC - ONUP T1M CM - BLOCK (ver~fy)

cb CM RCS HTRS (2) - closeCM RCS HTRS - ON (LMP Conf~rm)

(20 mlU or III lowest rdg lS39 vdc) (Moultor Maufpress for press drop)

31 (___) FINAL GDC DRIFT CK (If req I d)If drlft gtlOohr Suspect GDC Do not

use RSI amp FDAI 2

32 -OO5Om

33

34

35

TERM CM RCS PREHEATUP TLM CM - BLOCK (venfy)CM RCS HTRS - OFFCM RCS LOGIC - OFF

SYSTEMS TEST PANEL CONFIGURATIONSYS TEST METER - 4BRNDZ XPNDR - OPERATECM RCS HTRS - OFFWASTE H20 DUMP - OFFURINE DUMP - OFF

LEB LIGHTING - OFF

SEC WATER EVAP ACTIVATIONGLY To RAD SEC vlv - BYPASSSEC COOL EVAP - EVAPSEC COOL PUMP - AC2

36

37

38 -OO45m

-22-

PYRO BATT CKcb PYRO A SEQ A - close (ver~fy)

cb PRYO B SEQ B - close (verify)DC IND - PYRO BAT A(B)

~If PYRO BAT A(B) lt 35 vdc cb PYRO A(B) seq A(B) - open~

PYRO A(B)BAT BUS A(B)TO PYRO~MN BUS TIE - close

cb MNA BAT C - closecb MNB BAT C - closeDC IND - MNBPNL 8 - All cbs closed except

PL VENT - open (ver~fy)

FLOAT BAG (3) - open (ver~fy)

DOCKING PROBE (2) - open (verlfy)EDS BAT (3) - open (ver~fy)

CM ReS HTRS (2) - open

CM RCS ACTIVATIONcb SECS ARM (2) - close (verlfy)cb SECS LOGIC (2) - close (verlfy)SECS LOGIC (2) - ONMSFN conflrm GO for PYRO ARM(~f poss)SECS PYRO ARM (2) - ARMCM RCS PRPLNT 1amp2 - ONCM RCS PRESS - ONRCS Ind sw - eMl then 2

He PRESS 3700-4400 pSlaMANF PRESS 287-302 pSla

SECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFF

P27 amp ENTRY PAD UPDATEGo To Entry Checkllst

Superclrc - pg ~2~3 _Hybnd - pg -----2~9L-__Normal Deorblt - pg __3L5L- _

-23-

52 SUPERCIRCULAR ENTRY

1 SET DET (up to ET)

2

3

4

5

3000(-30-00)

EMS INITIALIZATIONSET RNG TO PAD DATA RNGEMS FUNC - Vo SETSlew Scroll to Pad Data VIOEMS FUNC - ENTRY

RS I ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on (up)GDC ALIGN PB - PUSH amp HOLDYAW Tw - Pos~t~on RSI thru

45deg amp back to LIFT UPGDC ALIGN PB - ReleaseEMS ROLL - OFFA1~gn CDC to lMU

CM RCS RING A CKRCS TRNFR - CMcb CM RCS LOGIC MNB - openAUTO RCS SEL MNB (6) - OFFSC CONT - SCSTest R~ng A ThrustersSC CONT - CMCRCS TRNFR - SMAUTO RCS SEL (12) - MNAMNB

(hftoff conflg)cb CM RCS LOGIC MNB - close

OPTICS PWR - OFFCMP to COUCH

MN BUS TIE (2) - ONTAPE RCDR - REWIND

6 35middot0Om(-25middot 00)

-24-

SEPARATION CK LISTTVC SERVO PWR 1 - AClMNAcb ELS (2) - close (ver1fy)PRIM GLY TO RAn - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY vlv - OFFCAB PRESS REL vlv (2) - NORMGMBL MTRS (4) - STARTABORT SYS PRPLNT - RCS CMD (venfy)SM RCS PRIM PRPLNT (4) - ONVHF 11M (AampB) - OFFHI GAIN ANT PWR - OFFFC PUMPS (3) - OFFVer1fy s1ugle SU1t compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - 10101cb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2) - opencb HTRS OVLD (2) - openPOT H20 RTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANSEC COOL EVAP - RESETSEC COOL PUMP - off (etr)

MtiVR TO CMSM SEP P R ATTSC CONT - SCSCMC MODE - FREEMNVR TO PAD ATTR (0deg)PY----W)

-25-

SUPERCIRCULAR ENTRY (Cont~nued)

1

4100m(-1900)

P61 - ENTRY PREP

V37E 61E

k 05 09 01427 - ROLL REVERSED 05 09 01426 - IMU UNSAT ~

2 F 06 61 IMPACT LAT LONG HDS UPDN (+-)PRO (010

fps +00001)

3 F 06 60 GMAXVPREDGAMMA EIRecord

GMAXV400K----

GAMMA EI _PRO

(01deg fpsOldeg)

4 F 06 63 RTOGO (lnm) PAD _VIO (fps) PAD _TFE(m~n-sec)

Compare w~th ~M~SFN==C~f~o-r~P~GNS GONO GOIf NO COMM Set RTOGO amp VIO In EMS

amp lnltla11ze(ACCEPT) PRO(RECALC) V32E To 4

5 F 50 25

4300m

(-1700)

45 oOm(-1500)

500Om(-1000)

6 F 06 61

-26-

P62 - CMSM SEP amp PRE-ENTRY MNVRCAUTION Call No EXT Verbs In P62

00041 REQUEST CMSM SEPSC CONT - SCSFREE

COMPARE PITCH ATT WITH PAD DATA ---0=-

(W~thLU 5deg)YAW - 45deg OUT-OF-PLANE (LEFT)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTIRATE 2MN BUS TIE (2) - ON (ver~fy)

PRIM GLY TO RAD - BYPASS (verlfy)CM RCS LOGIC - ON (venfy)SECS LOGIC (2) - on (up)SECS PYRO ARM - ARMCMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 ps~a

CM RCS LOGIC - OFFSECS PYRO ARM (2) - SAFEMonltor VMAB

If lt25 vdc go to EMERGPOWERDOWN pg E6-l

AUTO RCS SEL AC ROLL (4) - OFFAUTO RCS SEL CM 2(6)-OFFAUTO RCS SEL CM 1(6)-MNAYAW back to 0degPITCH TO HORIZ TRACK ATT

ROLL - 0deg (LIFT UP)PITCH - 400K Horiz Mark (317deg)YAW - 0deg

ATT DB - MAXMAN ATT PITCH - ACCEL CMDEMS DATA - Ver~fy

EMS FliNC - ENTRY (ver~fy)

EMS MODE - NORMALcb SPS PampY (4) - openMAINT HORIZ TRK

PRO (Act ENTRY DAP)

IMPACT LATLONGHDSDN (01deg01deg-00001)PRO

7 POSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axis beyond 45deg of Vel vector)

8 06 64

58middot00m(-0200)

9

05G tlme(+0 )

(--=---)

06 68

-27-

P63 - ENTRY INIT

GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PIJR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRmDHORIZ CKPltch error needle goes toward

zero approachlng OSG tlmeMAN ATT (PITCH) - RATE CMD

If CMC lS GOBMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS I

FLY BETA If CMC NO GO ilt

1 SC CaNT - SCS I

FLY EMS k

p64 - ENTRY POST 05G

RTOGO AT 05G AGREES HITH EMS-venfyHORIZ CK05G Lt - ON (EMS START)

No EMS START wlthln 3 sec ~ EMS MODE - BACKUP VHF RNG c

05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds Llft DN

NNVR Llft DNEMS GONO GO

G-V Plot wlthln IlmltsRng ctr dwn 60plusmn7 durlng 10 sec

perlodMonltor G-meter for

convergence wlth pad data (Do)(Vlt27K fps) Go to 13

-28-

P65 - ENTRY - UP CONT (Vgt27K fps)

10 F 16 69 BETA (01middot) _DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT lt~ SC CONT - SCS FLY EMS

PRO

11 06 68 BETAVIHDOT (OIdegfpsfps)(VltV1+500 fps amp RnOT Neg) Go To 13

P66 - ENTRY - BALLISTIC (D(DL)

12 06 22 DESIRED GMBL ANGLES RPYMoultor horlz +12middot of 317middot mark

P67 - ENTRY - FINAL PHASE (02G)

13 06 66 BETACRSRNG ERRDNRNG ERR(010 1um 1um)

KEY VERBRecord DNRNG ERR _KEY RLSEMoultor l~ft vector ou RSI amp FDAI

16 67 RTOGOLATLONG (Vrel=1000fps)(lumOldegOldeg)

SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOWNMonitor a1t~meter

Go To EARTHLANDING pg ---4L5 _

-29-

53 GampN HYBRID DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL tV1 V37E 30E

2 F 06 33 GETI(ACCEPT) PRO (hrm~n Olsec)(REJECT) LOAD DESIRED GETI

3 F 06 81 tVXYZ (LV) (lfps)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

4 F 06 42 HAHPtV (lnm lfps)Record tV

(ACCEPT) PRO(REJECT) Reselect P30 or P27 Load new paramo

5 F 16 45 MTFIMGA (marksm~n-secOlO)

MGA -00002 ~f k

k lMU not al~gned

SET DETPRO

6

7

8

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (Pull)PLSS 02 vlv - FILL02 8M SUPPLY vlv - OFFCAB PRESS REL vlv (2) - NORMcb ELS (2) - closecb SECS ARM (2) - closecb SECS LOGIC (2) - close (ver~fy)

AUTO RCS SEL CM (12) - MNA or ~ffiB

(hftoff conhg)ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM (AampB) - OFF

CMP to Couch

9

10

11

-30-

MNVR TO PAD BURN ATTLOAD DAPBMAG MODE (3) - RATE 2SC CONT - CMCAUTOATT DB - MINMAN ATT (3) - RATE CMD

v62E

v49E

12 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLES

PRO

13 F 50 18 REQ MNVR TO FDAI RPY ANGLES (01deg)(AUTO) PRO(MAN) SC CONT - SCS

BMAG MODE (3) - RATE 2MNVR To 15

14 06 18 AUTO MNVR TO FDAI RPY ANGLES (01deg)

15 F 50 18 REQ TRIM TO FDAI RPY ANGLES (01deg)(TRIM) Go to 13(ByPASS) ENTR

16

17

CHECK BORESIGHT amp SKT STARSOPT MODE - CMCOPT ZERO - OFF

v41 N91E

18 F 21 92 SHAFTTRUN (01deg 001deg)Load SXTS angles

19 41 OPTICS DRIVECheck SKT STAR

OPT ZERO - ZEROCheck BORESIGHT STAR (~f ava~l)

20 V25 N17E (01deg)Load Pad Data GMBL Angles

for CM BURN ATTATT SETtw - SET

to PAD DATA GMBL ANGLESfor CM BURN ATT

21

22

-31-

PHR REDUCTIONHGA PHR - OFFFC PUMPS (3) - OFFVerify s~ngle su~t compr oper loads

balancedFC 2 MN AampB - OFFS BD PiR AMP - LOWcb ECS RAD CONTHTR (2) - opencb HASTE H20URINE DUMP HTRS(2)- opencb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANMN BUS TIE (2) - ONTVC SERVO PHR 1 - AC1MNAGMBL MTR (4) - START

p41 - RCS THRUSTINGV37E 41E

23 F 50 18 REQ MNVR TO LCL HORIZ (HDS ON)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CMCAUTOPRO To 24

(gtfANDAP) BMAG MODE (3) - RATE 2SC CONT - CMCHOLD

V62EMNVR To 25

24 06 18 AUTO MNVR TO FDAI RPY

25 F 50 18 REQ TRIM TO LCL HORIZ (01deg)ALIGN SC ROLL

(AUTO TRIM) PRO To 24(BYPASS) ATT DB - MIN

RATE - LOHMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTlRATE 2

ENTR

550Om26 06 85

59middot2527

-32-

VGXYZ (1fps)RECHECK BORESIGHT STARTRANS CONIR PWR - on (up)EMS MODE - STBY (ver~fy)

EMS FliNC - bV SETVHF RNGSET (IV for SM BURN _EMS FliNC - bVS BD ANT - OMNI CSECS LOGIC (2) - ONMSFN conhrm Go for PYRO ARMSECS PYRO ARM (2) - ARMCM RCS LOGIC - ON (ver~fy)

DSKY BLANKS

593028 16 85 VG XYZ (AVE G ON) (lfps)

RHCs amp THC - ARMEDLIMIT CYCLE - OFFTAPE RCDR - CMD RESETHBREMS MODE - NORMAL

000029 F 16 85 REQ NULL VG XYZ (lfps)

BURN EMS bV CTR TO ZERORESET DET amp COUNT UP

If SM ONLY burn go to step 32THC - LOCKEDSC CaNT - SCSFREERATE - HIGHPRIM GLY To RAD - BYPASS (ver~fy)

MN BUS TIE (2) - ON (ver~fy)

CMSM SEP (2) - on (up)CSMLM FNL SEP (2) - on (up) (verify)CampW MODE - CMRCS TRNFR - CMCM RCS LOGIC - OFF

Momtor VM ABIf lt25 vdc go to EMERGPOWER DOWN Pg E6-l

V63E

If CMC NO GO FDAI SOURCE - ATT FDAI SEL - 1 or 2 ATT SET - GDC

SET

-33-

~Uili ATT PITCH - ACCEL CMDFDAI SCALE - 55MNVR TO CM BURN ATT (NULL ERR NEEDLES)

R 0degPY --00--

30

31

CM RCS BURNRHC III-ContJnuous PJtch DownRHC HZ-Module PJtch to null needlesBURN VGZ TO ZERO

If only 1 RHC Pulse + P=5deg from retro att MaJnta~n rates lt3degsec

BURN COMPLETION ATllV CTR= or DET= _

V8ZE

32 F 16 44 HAHPTFF (1nmffiJn-sec)Check HP-

If gt Pad data contJnue burnuntJ1 lt Pad

PRO

33 F 16 85 VGXYZ (Ups)Read VG resJduals to MSFN

(HYBRID) PRO to 34(SM ONLY BURN)

PROF 37 ODE

EI-1500 V37E 47EF 16 83 twx Y Z (Ups)

SC CONT - SCSFREEMAN ATT (PITCH) - RATE CMDRATE - HIGHPRIM GLY To RAD - BYPASS (verJfy)MN BUS TIE (2) - ON (verJfy)CMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verJfy)Campl MODE - CMRCS TRNFR - CMCM ReS LOGIC - OFFSECS PYRO ~I (2) - SAFE

-34-

PROMonitor VMAB

If lt25 vdc go to EMERGPOWER DOWN

34 F 37 OOEPCM BIT RATE - LOWATT DB - MAXEMS MODE - STBYEMS FUNC - OFF

Go To EARTH ORBIT ENTRY pg _--40-__

-36-

8 SPS THRUSTING PREPCYCLE CRYO FANSSPS GAGING - ACI (ver~fy)

PUG MODE - NORM (venfy)BMAG MODE (3) - RATE 2tv CG - CSMCMC MODE - FREEAUTO RCS SEL (16) - MNA or HNB

(hftoff conbg)SC CONT - CMCAUTO

9 MNVR TO PAD BURN ATTV62E

10 V49E

11 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLESPRO

12 F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) PRO(HAN) SC CONT - ses

MNVR to 14

06 18 AUTO MNVR TO FDAI RPY ANGLES13

14 F 50 18 REO TRIH TO FDAI RPY ANGLES(TRIM) Go to 12(BYPASS) ENTR

15 BORESIGHT STAR CHECK

16 V37E 40EOPT PWR - OFF

17 F 50 18 REQUEST MNVR TO FDAI RPY ANGLES (01deg)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CHCAUTOPRO to 18

(MANDAP) BMAG HODE (3) - RATE 2SC CONT - CMCHOLDMNVR to 19

(HANseS) se eONT - sesMNVR to 19

-35-

54 NORMAL DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL ~V

1 V37E 30E

2 F 06 33 GETI (hrm~nOlsec)

(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

3 F 06 81 ~VXYZ (LV)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

( lfps)

4 F 06 42 HAHP~V (1nmlfps)Record W

(ACCEPT) PRO -----(REJECT) Rese1ect P30 or P27 Load new pa~am

5 F 16 45 MTFIMGA (marksmln-secOldeg)MGA -00002 If ~ lMU not a1~gned

SET DETPRO

6

7

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY v1v - OFFCAB PRESS REL v1v (2) - NORMcb ELS (2) - close (verify)cb SECS ARM (2) - close (ver~fy)

cb SECS LOGIC (2) - close (verlfy)AUTO RCS SEL CM (12) - ~mA or MNB

(l~ftoff conf~g)

ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM AampB - off (ctr)

18

-37-

06 18 AUTO MNVR TO FDAI RPY ANGLES (01 0)

19 l 50 18 REOUEST TRIM MNVR TOALIGN SIC ROLLGDC ALIGN

FDAI RPY ANGLES(010

)

+54-00m(-06-00)

TIG-5mJn

5500m(-0500)

TVC CHECK amp PREPcb STAB CONT SYS (all) - closecb SPS (12) - closeATT DB - MINRATE - LOl~

LIMIT CYCLE - ONMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE 2ROT CONTR PWR DIRECT (2) - OFFSCS TVC (2) - RATE CMD

If SCS SCS TVC (2) - AUTO SC CONT - SCS ~

TVC GMBL DRIVE PampY - AUTOMN BUS TIE (2) - ONTVC SERVO PWR 1 - AC1MNA

2 - AC2MNBTRANS CONTR PWR - ONROT CONTR PWR NORMAL 2 - ACRHC 2 - ARMED

HORIZ CHK - HorJz on 12deg wJndmlmark (LJffiJt +3 0 PNGCS GONO GO)

If NO GO set tw 180 0 180deg0 0

Track horJz wJth 24deg wJndow markAt TIG-2 mJn Ahgn GDC

PRIMARY TVC CHECKGMBL MOT P1-Y1 -STARTON(LMP confJrm)

If SCS verJfy Thumbwheel TrJmTHC - CWVenfy NO MTVC

SEC TVC CHECKGHBL MOT P2-Y2 -STARTON(LMP confJrm)SET GPI TRIHVenfy MTVCTHC NEUTRALGPI returns to 00 (CMC) or trJm (SCS)ROT CONT Pl~ NORM 2 - ACDC

(TRIM) Go to step 17(BYPASS) BMAG MODE(3) - ATTIRATE2 (ver1fy)

ENTR

-38-

20 F SO 25 00204 GMBL TEST OPTION(ACCEPT) SC CONT - GMC (ver~fy)

PROMonitor GPI Response

0020-2000020-200Tr~m

TEST FAIL SC CONT - SCS SCS TVC (2) - AUTO

(REJECT) ENTR

21 06 40 TFIVG~VM (m~n-sec1fps)

PROG ALM - TIG s1~pped

V5N9E 01703

KEY RLSE To 21 ROT CONTR PWR DIRECT (2) - MNABSPS He v1vs (2) - AUTO (ver~fy)

LIMIT CYCLE - OFFFDAI SCALE - SOIScb SPS P2Y2 - open (for cr~t burn)

5800(-02 00)

5925(-0035)

59middot 30(-0030)

06 40

59XX(-OOXX)

AV THRUST A(B) - NORMALTHC - ARMEDRlIC (2) - ARMEDTAPE RCDR - GID RESETHBR

DSKY BLANKS

(AVE G ON)EMS MODE - NORMAL

TFIVG~VM (m~n-seclfps)

CHECK PIPA BIAS lt2fps for 5 sec

ULLAGE AS REQ

IF NO ULLAGE DIR ULLAGE PB - PUSH~

CONTROL ATT WRlIC MONITOR AVM (R3) COUNTING UP

5955(-0005)

F 99 40 ENG ON ENABLE REQUEST(AUTO IGN) PRO AT TFI gt0 sec(BYPASS IGN) ENTR to 24

22 0000 IGN

-39-

If SCS - THRUST ON PB - PUSH

06 40 TFCVG~VM (m~n-seclfpslfps)

~F 97 40 SPS Thrust fall ~

~(RESTART) PRO To IGN (RECYCLE) ENTR To TIG-05 sec

SPS THRUST LITE - ONMONITOR THRUSTING

Pc 95-105 pSlaEMS COUNTING DOWNSPS IN3 v1vs (4) - OPENSPS He v1vs tb (2) - graySPS FUELOXID PRESS - 175-195 pSlaPUGS - BALANCED

PROG ALARM V5N9E 01407 VG INCTHC - CW FLY MTVC

ECOEMER SPS CUTOFF J

AV THRUST (2) - OFF

23 F 16 40 TFC(STATIC)VG~VM (mln-seclfps)~V THRUST AB - OFF

SPS IN3 v1vs (4) - CLOSEDSPS He tb (2) - bp

cb SPS P2Y2 - closed (verlfy)TVC SERVO PHR - AC1MNA (venfy)TVC SERVO PWR 2 - OFF

PRO

24 F 16 85 VG XYZ(CM) CUps)NULL RESIDUALSRECORD ~V CTR amp RESIDUALS I1VCEMS FUNC - OFF VGXEMS MODE - STBY VGYBMAG MODE (3) - RATE 2ATT DB - MAX VGZTRANS CONT PHR - OFF

PRO

25 F 37 V82E

26 F 16 44 HAHPTFF (lnmm~n-sec)

R3-59B59 HP gt494 nmPRO

27 F 37 OOE

-40-

55 EARTH ORBIT ENTRY

1 Venfy CMSMR __

P_shyY_-

SEP ATT(180deg)

(0deg )

2

3

4

EMS INITIALIZATIONEMS FUNC - RNG SETSET RNG TO PAD DATA RNGEMS FUNC - VA SETSlew scroll to pad data VIOEMS FUNC - ENTRY

RSI ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on(up)GDC ALIGN PB - PUSH amp HOLDYAW tw - Pos1tion RSI thru 45deg amp

back to LIFl UPGDC ALIGN PB - RELEASEEMS ROLL - OFFAl1gn GDC to lMU

PWR REDUCT (Norm Deorb Only)HGA PWR - OFFFC PUMPS (3) - OFFVer1fy s1ngle suit compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - Lowcb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2)-openlOb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MAN

-41-

P61 - ENTRY PREP

5 V37E 61E05 09 01427 - ROLL REVERSED05 09 01426 - IMU UNSAT

6 F 06 61 IMPACT LAT LONG liDS UPDN (+-)(01 0

010

+00001)

PRO

PAD VALUESLATLON==G------liDS UP DN _

7 F 06 60 GMAXV400KGAMMA EIRecord

GMAXV400K----GAMMA EI _

PRO

8 F 06 63 RTOGO (1nm) PAD _VIa (fps) PADTFE (mln-sec) ----Compare wlth MSFN for PGNS GONO GONO COMM SET RTOGO amp VIO IN EMS amp

INITIALIZE(ACCEPT) PRO(RECALC) V32E to 8

-42-

P62 - CMSM SEP amp PRE-ENTRY MNVR

9 F 50 25 00041 REQUEST CMSM SEPSC CONT - SCSFREEYAW - 45deg out-of-plane (left for RCS

nght for SPS)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE2PRIM GLY to RAD - BYPASS (verlfy)SECS LOGIC (2) - on (up)MSFN conflrm GO for PYRO ARMSECS PYRO ARM - ARMMN BUS TIE (2) - ON (verlfy)CMSM SEF (2) - ONCSMLM FNl SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 pSlaCM RCS LOGIC - OFFSECS PYRO ARM - SAFEMonltor VMAB

If lt25vdc go to EMERG POWERDOWN Pg E6-1AUTO RCS SEL AlC ROLL (4) - OFFAUTO RCS SEL CM 2(6) - OFFAUTO RCS SEL CM 1(6) - MNA or MNBYAW back to 00

PITCH TO ENTRY ATTROLL 0deg (LIFT UP)PITCH - HORIZ on 317deg MARK (400K)YAW 00

ATT DB - MAXMAN ATT (PITCH) - ACCEL CMDEMS DATA - VerifyEMS FUNC - ENTRY (verlfy)EMS MODE - NORMALMAINTAIN HORIZ TRK

PRO (Act ENTRY DAP)

10 F 06 61 IMPACT LAT LONG HDSDN(010 010 -00001)

PRO

11 FOSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axlS beyond 45deg of Vel vector)

-43-

P63 - ENTRY INIT

12 06 64 GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PWR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRHORIZ CKP~tch error needle goes toward

zero approach~ng 05G t~me

MAN ATT (PITCH) - RATE CMDIf CMC ~s GO

BMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS FLY BETA If CMC NO GO ~

SC CONT - SCS~

FLY EMS RCS Deorh Roll HDS UPTRACK HORIZ w~th 29deg w~ndow mk

P64 - ENTRY POST 05G

13

05G t=elt+0___)

06 68

RTOGO AT 05G AGREES WITH EMS - venfyHORIZ CK05E Lt - on (EMS start)

No EMS start w~th~n 3 secsEMS MODE - BACKUP VHF RNG 05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds L~ft DN

NNVR L~ft DNEMS GONO GO

G-V Plot w~th~n llm~ts

Rng ctr dwn 60 + 7 durlng 10 sec per~od

Mon~tor G-meter forconvergence wlth pad data (Do)

(Vlt27K fps) Go To 17

-44-

P65 - ENTRY - UP CONT (Vgt27K fps)

14 F 16 69 BETA (01deg)DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT~

SC CONT - SCS FLY EMS

PRO

15 06 68 BElA VI HOOT (01deg fpsfps)(VltVL +500 fps amp RDOT Neg) Go To 17

p66 - ENTRY - BALLISTIC (DltDL)

16 06 22 DESIRED GMBL ANGLES RPY (01deg)Mon~tor hor~z +12deg of 317deg mark

P67 - ENTRY - FINAL PHASE (02G)

17 0666 BETACRSRNG ERRDNRNG ERR (Oldeglnmlnm)KEY VERBRecord DNRNG ERR _KEY RLSEL~m~t +100nm from PAD DRE

Mon~tor l~ft vector on RSI amp FDAIF 16 67 RTOGOLATLONG (Vre1=1000fps)

(lnm 010 01deg)SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOlfflMon~tor altimeter

Go To EARTHLANDING pg _I4L5__

-45-

56 EARTHLANDING

90K STEAM PRESS - PEGGED50K CABIN PRESS REL vIv (2) - BOOSTENTRY

SECS PYRO ARM (2) - ARM

40K(90K + 63s)

CM UNSTABLE RCS CMD - OFF ~ 40K APEX COVER JETT PG-PUSH DROGUE DEPLOY PG - PUSH (2 secafter apex cover Jett)

30K ELS LOGIC - ON (up)ELS - AUTO

24K RCS hsable (auto)(90K+92s) RCS CMD - OFF

Apex cover Jett (auto)APEX COVER JETT PB - PUSH

(WAIT 2 SECS)Drogue parachutes deployed (auto)

DROGUE DEPLOY PB - PUSH~

If Drogues FallELS - ~ ~Stablllze CM 5K MAIN DPLY PB - PUSHELS - AUTO

235K Cabln Pressure lncreaslng (Drogues + 50s)If not lncreaSlng by 17K CABIN PRESS REL vlv (RR) - DUMP

-46-

10K Maln parachutes deployedMAIN DEPLOY PB - PUSH (wlthln 1 sec)VHF ANT - RECYVHF AMA - SIMPLEXVHF BCN - ONCABIN PRESS REL v1v (2) - CLOSEDIRECT 02 vlv - OPENCM RCS LOGIC - on (up)CM PRPLNT - DUMP (burn audlb1e)Monltor CM ReS 1amp2 for He press decrease

NO BURN or PRESS DECREASE USE BOTH RHCs DO NOT FIRE PITCH JETS

CM PRPLNT-PURGE (to zero He press)CM RCS He DUMP PB - PUSH RHC (2) - 30 sees NO PITCH k

STRUT LOCKS (2) - UNLOCK

cb FLT amp PL BAT BUS ABampBAT C (3) - closecb FLT amp PLT MNA amp B (2) - opencb ECS RAD HTR OVLD (2) - opencb SPS PampY (4) - open

3K CABIN PRESS REL v1v (RH) - DUMP (after purgecompleted)

FLOOD Lts - POST LDGCM RCS PRPLNT (2) - OFFROT CONTR PWR DIRECT (2) - OFF

800 CAB PRESS RELF vlv - CLOSE (latch off)MN BUS TIE (2) - OFF

AFTER LANDINGcb MAIN REL PYRO (2) - closeMAIN RELEASE - on(up)

Go to POSTLANDING pg _47L-__

I

2

3

-47-

57 POSTLANDING

STABILIZATION VENTILATION COMMUNICATIONS

DIRECT 02 vlv - CLOSE

Stablllzation after landlngELS - AUTO (verlfy)cb MAIN REL PYRO (2) - close (venfy)MAIN RELEASE - on (up) (verlfy)S~CS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb BAT RLY BUS (2) - open

No contact w1th recovery forcesVHF AM AampB - off (ctr) ~

VHF AM Rev ONLY - A cb PL VENT - closecb FLOAT BAG (3) - closecb UPRIGHT SYS COMPRESS (2) - closeIf Stable II

FLOAT BAG(3)-FILL t1ll 2 m1n afterupr1ght then - OFF

VHF AM AlB amp BCN - OFF whlle lnvertedIf Stable I

After 10 M1n Coollng Per1odFLOAT BAG (3) - FILL 7 mln then OFF

Post Stab1lizat1on And Ventllat10nPL BCN LT - BCN LT LOWPL VENT vlv - UNLOCK (Pull)Remove PL VENT Exh CoverPL VENT - HIGH or LOWPL DYE MARKER - ON (swlmmer comm)Release foots traps and_restralntscb MNA BAT BUS A amp BAT C (2) - opencb MNB BAT BUS B amp BAT C (2) - opencb FLT amp PL BAT C - opencb PYRO A SEQ A - opencb PYRO B SEQ B - open

EACH HR - CHECK DC VOLTSgt 275 V If Notmiddot cb FLT amp PL-BAT BUS AampB (2) -open cb FLT amp PL BAT C (1) - open GO TO LOW POWER CHECKLIST

Unstow and lnstall PLV DISTRIB DUCTDeploy grappllng hook and 11ne 1f req

4

-48-

Post Landing Communlcatl0nsVHF ANT-RECY (venfy)VHF BCN - ON (verlfy)

If no contact ~lth recovery forcesperform VHF BEACON Check

MONITOR VHF BEACON transmlSSlonnth VHF AM B Rcvr andor Su)vlval

TransceiverkVHF Beacon not operatlng ~connect Surv~val TranscelVer to antcable behlnd VHF ant access pnland place radio ln BCN mode

LOW POHER CHECKLISTVHF BCN - OFFVHF AM (3) - RCVFLOOD Lts - OFFVHF AM AampB - off (ctr)VHF AM RCV ONLY - A (venfy)COUCH LIGHTS - OFFPOSTLANDING VENT SYS mlnlmlze useSURV RADIO - plug mto VHF BCN ANT cableconn behind VHF ant acess pnl amp turn radloon l-n BCN mode

EGRESS PROCEDURES

CMPCDRLMPCDR

CMPCDRCMP

LMPLl1PCDR

STABLE IDlsconnect Umblll-calsNeck darn onCenter couch - 270 0 positionArmrests stowedConnect raft to SIC l-f desl-red wlth

green lanyardConnect raft ~hl-te lanyards to SUltS amp

lnflate water wlngs when eXltl-ngHATCH PISTON PRESS vlv - PRESS (Outbd)Slde Hatch openedPL VENT - OFFcb Pnl 250 (all) - openEgress with 11feraftPut hardware klt outEgress

or CDIPALL

CMF

CDRCMF

CDR

LMF

CMFCMP LMFCMP

UlP

CDR

-49-

STABLE IIcb CREW STA AUDIO (3) - openD~sconnect umb~1~ca1s

Release foots trapsRelease restra~nt harnessCouch seat pans (3) - 170 0 pos1t10nArm rests stowedSurv1va1 k~ts removed from stowageConnect life raft ma~n1~ne to CDR or SicConnect f~rst wh~te lanyard from

11fe raft to suitConnect th~rd wh~te lanyard from

l~fe raft to SU1tConnect rucksacks together to yellow

lanyard on raft bagPRESSURE EQUALIZATION vlv - OPENRemove and stow fwd hatchEX1t feet f1rst w1th rucksacks when clear

of siC 1nflate water w1ngs and raftExit feet f1rst when clear of SiC

1nflate water w1ngsEX1t feet f1rst when clear of sic

1nflate water w1ngs

-50-

60 TLI ABORTS

TLI Aborts are conta~ned ~n the ESD s~nce the bulk of the funct~ons

concern entry preparat20ns and performance Th~s allows a s2nglesource of procedures for procedure rev2ew val~dat~on checkout andtra~n~ng These procedures ~ncorporate TLI preparat20ns as found ~n

reference 6 w~th the TLI Abort Procedures and these t~e 2nto normallunar return Entry Procedures found ~n sect20n 5 The guidel~nes

for th~s cont2ngency are spec2f2ed 2n reference 7

In2t2al preparat~ons for TLI pos2t20n the necessary system sW2tches2n add~t~on to perform~ng an EMS ~V test and a GDC al~gnment Afterthe DET ~s set for mon2tor2ng TB6 the CMP ~ncreases the 12ght levelof the LEB DSKY to max~mum and returns to the h2s couch Th2s 2Sdone so that the LEB DSKY can be observed ~n the event sunl~ght orreflect20ns wash out the ma2n d2splay panel DSKY dur2ng cr2t2calmaneuvers The crew then straps ~n and prepares for mon2tor~ng TB6as 2nd2cated by the SII SEP L~te The t2mes se~uence of procedures2S keyed on th~s d~splay and ~ncludes the DET START funct~on andSIVB IGNITION Dur2ng the burn the crew mon2tors the FDAIs foratt~tude excurs20ns and abnormal rates report~ng status checks toM~ss2on Control at d2screet t~mes dur2ng the maneuver Upon SIVBSHUTDOWN the eMP records the DSKY d~splayed performance parametersand awa2ts ground conf2rmat~on

The rat~onal for TLI aborts ~s descr~bed 2n reference 7 A summar2shyzat20n 2S extracted to prov2de background and gu2de12nes 2n th2sdocument The abort procedures cover aborts 10 m2nutes after conshyt2ngent SIVE shutdown and aborts 90 m2nutes after normal SIVE shutshydown t2me

The 10 m~nute TLI abort ~s des2gned to be used dur~ng TLI ~n theevent a spacecraft problem develops Wh2Ch can result 2n catastrophe2f ~mmed~ate act~on 2S not taken If the s~tuat20n perm~ts the crewshould always allow the SIVB to complete TLI at wh~ch t~me the groundand crew can perform a malfunct~on analys~s to determ~ne ~f an abort~s adv~sable If a fa~lure occurs that necess2tates the shutdown ofthe SIVB and the ~u~ck return of the crew to earth th~s abort ~s

des~gned to be as ~nsens~t~ve to execut~on errors as poss~ble andst21l be targeted to m2dcorr2dor The burn att~tude w~th the f~ed

hor~zon reference ~s a constant value for any shutdown t~me Theburn durat~on 2S a funct20n of shutdown t2me and 2S ava21able fromcrew charts S~nce the pr~mary purpose of th~s abort ~s to returnto earth as qU2ckly as poss2ble there are no restr2ct20ns as toland~ng locat~on However ~f the t~me to EI is greater than abouttwo hours a midcourse correct20n should be ant~c~pated

The 90 m2nute TLI abort 2S to be used 2f a cr2t2cal subsystem malshyfunct~on ~s determ2ned and the dec2s~on to abort ~s made after the

-51-

TLI cutoff and before TLI cutoff plus approxlmately 80 m1nutesTh1S allows suff1c1ent separatlon and procedural t1me to set upfor the SPS deorb1t burn performed at about TLI + 90 Note thatgenerally the deorb1t burns w1ll be performed a fe11 m1nutes beforeTLI + 90 accord1ng to crew charts shown In reference 8 The no-comm except10n requ1res that 90 m1nutes be the 1nput t1me of 19n1shytlon for P-37 (onboard return-to-earth abort program) so that onshyboard calculatlons can correspond w1th ground calculat10ns to computethe CM land1ng p01nt Th1S TLI abort lS des1gned so that returnfl1ght t1me does not exceed 18 hours and abort ~V does not exceed7000 fps ThlS abort can be performed uSlng chart ~Vs and attltudesand the earths hor1zon serves as a suff1c1ent reference The maneushyver lS targeted to ach1eve the mldcorr1dor entry target Ilne andtlmed to result 1n a deslgnated recovery area

It 1S ObV10US for abort deC1S1ons early 1n the TLI + 90 m1nute t1meshyframe that a GampN SPS burn should be performed In order to keep theTLI abort procedures cons1stent and w1th emphasls on slmpl1c1ty theprocedures here reflect a SCS SPS abort burn to cover the full abortdec1s1on t1meframe

A m1dcourse correct1on for corr1dor control after a TLI abort may bedeS1red 1f the SPS burn d1d not meet expectat1ons The TLIabortprocedures 1n th1S sect10n adapt to the normal lunar return tlmel1neand procedures pr10r to the f1nal MCC

-52-

61 TLI PREPARATION PROCEDURES

GET = 150

CRO AOS(___)

CRO LOS( )(22142)

5100

Don Helmets amp Gloves

XLUNAR - INJECT (verify)EDS PWR - on (venfy)EMS FUNC - OFF (verlfy)EMS MODE - STBYEMS FUNC - IW SETVHF RNGEMS MODE - NORMALSet ~V indo to +15868 fpsEMS FUMC - ~V Test

SPS THRUST Lt - onoff (10 sec)~V lnd stops at -01 to -415

EMS MODE - STBYEMS FUMC - ~V SETVHF RNGSet ~VC

EMS FUNC---~~V=----

GDC ALIGNFDAI Select - liZcb SECS LOGIC (Z) - close (verify)cb SECS ARM (Z) - closeSECS LOGIC (Z) - on (up)MSFN Conflrm GO for PYRO ARM (If pass)SECS PYRO ARM (Z) - on (up)TRANS CONTROL PWR - ONROT CONTR PWR NORMAL (Z) - ACDC(verlfy)ROT CONTR PWR DIRECT (Z) - MNAMNBLV INnGPI - SIISIVB (venfy)LV GUID - IU (venfy)cb DIRECT ULLAGE (Z) - closedSet EVENT TIMER to 5100Begin MONITOR For TB6

CMP to Couch

TB 6 - SII SEP Lt on (TIG-9 mln 38 sec)KEY V83E

SET ORDEALFDAI Z ORB RATE at 180 0 0SII SEP Lt out (38 sec later)Start DET COUNTING UPSC CaNT - SCS (verify)MONITOR LV TANK PRESS

~P lt 36 psid (OXID gt FUEL)~P lt Z6 psid (FUEL gt OXID)

EMERGENCY CSMLV SEP UP TLM CM - BLOCK (verify)UP TLM IU - BLOCK (venfy)

-53-

+45degPY))0middot sec PY

lOK nmltHAlt25K nm

Two phas~ng mnvrs two SPS mnvrs to circular~ze at 150 nmearth orb~t

CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ssion 4K nmltHAltlOK nm CSM amp1M - Two phasing mnvrs two SPS mnvrs to circularize at 150 nm earth orb~t CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ss~on

CSM amp 1M - Two phas~ng mnvrs APS burn todepletion th~rd phasing mnvrSPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn tosem~sync orb~t

25K nmltHAlt40K nm CSM amp 1M - Two phasmg mnvrs APS burn to depletion third phas~ng mnvr SPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn to sem~sync orbit HA)40K nm DPS ava~l - DPS LOll circularize with SPS

DPS not ava~l - Lunar flyby or CSM only to lunar orbit (if reqd gtV lt4000 fps)

V37E 47E (check b~as) Record -=--rshy(Limit 98 fpsmm)

( 1fps)tVXYZN62EVIHDOTHPAD (fpsfpslnm)MONITOR VI ( ) at ECO

SCS TVC SERVO PWR 1 - ACIMNA2 - OFF

TAPE RCDR - CMD RESETHBREMS MODE - NORMAL

SIr SEP Lt - ONTLI Inhib~t S~gnals w~11 not be honored after 5942

SIVB ULLAGE BeginsSII SEP Lt - off (TIG - 18 sec)SIVB FUEL LEADSIVB ULLAGE d~scont~nues

LV ENG I Lt - onSIVB IGNITION ( GETI)LV ENG I Lt - off - -shyMONITOR THRUST amp ATTITUDEMONITOR LV TANK PRESSSIVE ECO (Lt on) (BEGIN TB7)

EMER SIVE CUTOFF AT 6 SEC PAST BURN TIME IF VI ATTAINEDTHC CCW ampNEUTRAL IN 1 SEC or SIISIVB sW - LV STAGEPremature Shutdown HAlt4K nm CSM amp 1M -

5700

58205836

F 16 835800

F 16 62

5838594259525955595900000002SUNRISE(___)

HAW AOS(__=_) KEY VERB (freeze d~splay)

SIVB ATT HOLD 20 sec amp BEGIN VENTINGSIVB NNVR TO ORB RT (HDS DN) (3middot sec)

Record VI -c---HDOT _

HPAD _

KEY RLSEF 16 62

F 16 83

HAW LOS(__=-)

KEYmiddotRLSE~VXYZ (lfps)

Record ~VX---_

~vy

WZ--

AVC---_

TAPE RCDR - off (ctr)EMS MODE - STBYEMS FUNC - OFFSECS PYRO ARM (2) - SAFE

PRO

BURN STATUS REPORT

____--~TIG

BT------VGX____-R

-----P----_Y

REMARKS

_____VI

______--HDOT______--H______---AVC______---FUEL_______OXID

_______UNBAL

F 3708=00 OOEGOS AOS CMP TO LEB

(-=-=-)

0000

0003

0005

0014

0100

-55-

62 TLI 10 MIN ABORTSECS LOGIC (2) - on (up)SECS PYRO ARM (2) - ARM

TRANS CONTR - CGH (4 sec) amp +XDET RESET (verlfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS GMD-ON

TRANS GONTR - neutral then +X for10 sec

SIVBGPI s~ - GPIExcesslve rates 6V THRUST A - NORMAL SPS THRUST - DIRECT When rates damped 6V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

TRANS CONTR +X - OFFV37E OOE

PITGH UP to LOGAL VERT (+X axlSto~ard the earth)

RATE - LOWBMAG MODE (3) - ATTIRATE 2EDS PHR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SEGS ARM (2) - opencb EDS (3) - open

TRANS CONTR -X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (180deg)P (199deg)Y (0deg)

RETRO UPDATEGETI _

JV _VG

Jtb ---GET 400K _

05G _GET DROGUE _

ENTRY P _R _

Y_--

0945

-56-

ALIGN HORIZ ON RET +1 MKGMBL CHECK (T11lle Pentattlng)MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conflnn)cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FUMC - JV SETVHF RNGSET JV from chartE~S FUMC - JVEMS fODE - NOIDlAL

lV THRUST A - NORMALV37E 47E (THRUST fONITOR)

F 16 83 lVXYZ (1 fps)

0950

1000

NOTE For aborts durlng 1st mln of TLIKEY V82E F 16 44 (HaHpTff)Burn untll Hp lt 19NM

TRANS CONTR +X

THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN JV reqdJV THRUST (2) - OFFReport cutoff

cb SPS P2 Y2- closeGfBL MTRS (4) - OFF (LMP Confinn)TRANS CONT PWR - OFFTVC SERVO PWR (2) - OFFMN BUS TIE (2) - OFFcb SPS P1amp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREIf est time to EIltOl5500 omlt fCC andenter the SUPERCIRC CKLIST as early as pos-slb1e Pg ~2~3~ __If est time to EI)Ol5500 anticlpate afCC Enter the ENTRY PREP CKLIST at step 9pg 18

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

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-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 8: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

-5-

3deg LUNAR REIUBN ENTRY TECHNIQUES

The t~mel~ne for lunar return entries is based on the recommendationsfound ~n reference 1 the s~mulator val~dated procedures ~n reference2 and the mission val~dated procedures listed in the onboard checkshylist for the C Pr~me m~ssion The event times are l~sted ~n reference3

The preparation for lunar return entr~es beg~ns at a conven~ent t~me

about 30 hours before entry ~nterface At th~s t=e MSFN sends up alldata suff~c~ent for reentry also an EMS entry selftest ~s made toassure max~mum confidence ~n the EMS operat~on during entry Thereshyafter var~ous system powerups and checks are ~n~t~ated as l~sted insect~on 51 and deta~led ~n reference 4 Nom~nally the PGNCS ~s upfor the ent~re m~ss~on However ~f ~t ~s not ~t ~s powered up atEI-7 hours ~n preparat~on for the last MCC and entry The last MCCdec~s~on ~s made at about EI-6 hours for the maneuver to be performedat EI-3 hours ~f needed Deta~ls of th~s maneuver are outl~ned ~n

reference 1 After the MCC time P52 ~s again selected and the IMU ~s

real~gned to the REFSMMAT If the IMU dr~ft ~s w~th~n tolerance thesubsequent IMUSCS dr~ft check will determ~ne if the SCS has dr~fted

excess~vely If so the other BMAGs are selected and the IMUSCScheck repeated Th~s check ~s followed by a repeat of the EMS ~V

counter check and accelerometer b~as check at EI-l hour 15 m~nutes

to determ~ne ~f the scale factor and b~as are adequate for entrymon~tor~ng F~nal stowage CM RCS preheat and pyro Cllcu~t and seshyquent~al tests are worked ~nto this t~meframe so that at EI-50 m~nutes

the MSFN w~ll be requested for a go to pyro arm by the crew ~n preparashyt~on for separat~on At 45 m~nutes before EI the CMC update programP27 can be selected to permit update of the landing po~nt locat~on andthe state vector The entry PAD data shown ~n sect~on 70 ~s thenvo~ced to the crew and recorded From th~s data the DET ~s set andstarted the EMS ~nit~al~zed and the RSI al~gned Prior to EI-20ffilnutes the crew w~ll have strapped-~n completed the~r presepara-t~on checkl~st and maneuvered to the entry att~tude At this pointEI-19 m~nutes the CMC entry program Fbl ~s selected by the CMP Ifthere was no entry PAD data because of commun~cat~on loss the veloshyc~ty and range to go from P61 ~s recorded and used ~n the EMS AtEI-15 m~nutes the spacecraft ~s p~tched down and the hor~zon ~s checkedagainst the 317 degree w~ndow scr~be l~ne and the FDAI att~tude Ifthere ~s s~gn~f~cant d~sagreement the PGNCS ~s suspected and the spaceshycraft ~s held on the w~ndow reference In P62 the spacecraft ~s yawed45 0 from th~s att~tude and separated from the SM After separat~on

the CM ~s yawed back ~n plane and the hor~zon check repeated At approxshy~mate1y EI-10 m~nutes the p~tch att~tude is w~th~n 450 of the CMCcommanded att~tude and P63 ~s entered automat~ca11y S~nce the CMCDAP tr~es to hold local p~tch attitude and the CMC ~s not ~n controlthe crew observes the p~tch error needle unpeg and approach zeroabout two m~nutes before 05g t~me Th~s serves as a gono go CMC

-6-

check for entry control If the FDAI pltch error does not decreaseto wlthln + 50 at 005g the PGNCS lS fa lied and the crew flies aconstant g-entry mode wlth EMS ranglng after the VelOClty decreaseto 25500 feet per second If the PGNCS lS acceptable the spaceshycraft control lS placed In CMC and the CMC mode lS placed ln autoshymatlc At 05g the EMS automatlcally starts lf the EMS mode sWltchwas posltloned to automatlc earller ThlS wlll be backed up manually3 seconds after the ground computed 05g tlme recorded on the entryPAD by placlng the EMS mode sWltch In manual lf lt has not startedautomatlcally At PGNCS 005g lndlcatlon the CMC program changesto P64 and from thls pOlnt the entry lS under entry DAP control

The lunar return entry nomlnally lS performed by the PGNCS to lnsurecontrol wlthln the overshoot and g llmlt llnes as well as optlmlzethe landlng point accuracy Although the hlgh speed entry lnvolvesa rapld sequency of events there are several monitorlng tasks forthe crew to determlne lf the automat~c contrails performlng correctly

An entry corr~dor ver~flcation check 1S made by observlng the lnltlalslope of the EMS V-g trace between 1 and 2 gs If the EMS lndlcatesthe need to reverse the LV orlentatlon and the lndependent g meterconflrms the EMS g lndlcatlon the SC lS immedlately orlented as aresult of the EMS ~nd~cat~on

The EMS g lnd~catlon ~s contlnuously checked durlng entry uSlng thelndependent g meter and the PGNCS g ~ndlcatlon as a thlrd voteDeC1Slons durlng the first entry (P64) are critlcal ln terms of bothexceSSlve g llnes and the PGNCS lS not commandlng (and SC respondlng)to correct the sltuatlon the PGNCS lS felled

The PGNCS gono go check for short range targets (1200-1400 n ml) forWhlCh P65 lS not used 1S d1fferent Slnce there are no CMC computedSk1p drag (DL) and skip velocity (VL) values The check uses the EMSscroll to determ1ne 1f the PGNCS lS commandlng the proper roll att1shytude to converge the EMS g level to a predetermlned PAD value (Do) ascomputed by MCC-H For the nom1nal target range of 1300 naut~cal

mlles the crew w1ll monltor the program change from P64 to P67 atapprox~matelyEI + 3 mlnutes For ranges greater than 1400 nauticalmlles the program w1ll transfer to the Upcontrol Program P65 whenVL ~s between 18000 and 25766 feet per second and constant drag hasbrought the CMC pred1cted range to wlthln 25 naut1cal m1les of thetarget range The P65 PGNCS gono go check cons1sts of determln1ng1pound both the DSKY d1splay of sk~pout drag (DL) and Sk1pout veloclty(VL) are w1thln the PAD llmlts In addltlon the EMS scroll lS mon1shytored to determ~ne lf the trace lS approach1ng the DL and VL values

Throughout entry the crew monltors the spacecraft response to the CMCroll commands by observlng the FDAI lndlcatlons If the commands are

-7-

apparently good and In agreement wlth the EMS but the spacecraftresponse is questlonable the crew manually takes over and fIlesthe CMC commands

If the Upcontrol Program P65 was entered the program wlll nomshylnally sWltch to the Flnal Entry Program P67 for target rangesbelow approxlmately 1800 nautlcal miles or to the Ballistlc Proshygram P66 for ranges greater than approxlmately 1800 nautlcalffilles The program transfer crlterla are more preclsely deflnedIn reference 1

If P66 lS entered the spacecraft lS automatlcally rolled to theIlftup heads-down attltude to permlt the horlzon to be vlewedfrom the wlndow durlng the second entry The entry attltude checklS made by comparlng the horlzon wlth a speclfled wlndow mark Ifthe check falls the crew manually malntalns the entry trlffi attltudeuSlng the horizon VleW for reference The EMS lS used for ranglngSlnce the veloclty has now decreased to below 25500 feet per second

The EMS scroll lS contlnuously used to monltor for exceSSlve g conshydltlons durlng the second entry If the EMS V-g trace vlolates theg Ilnes and the PGNCS lS not commandlng (and spacecraft respondlng)to correct the situatlon the PGNCS lS falled and the EMS lS usedfor ranglng after ltS g lndlcatlon has been conflrmed by the lndeshypendent g meter

The entry phase lS essentlally over when the relatlve veloclty ofthe spacecraft decreases to less than 1000 feet per second ThlSlS lndlcated In P67 when RTGO latltude and longltude are dlsplayedSlnce very Ilttle ranglng capablllty exists after thls pOlnt thespacecraft lS orlented elther full Ilft up or down dependlng on RTGOnegatlve or posltlve and the crew prepares for the earth landlngphase

31

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-13-

40 EARTH ORBITAL DEORBIT AND ENTRY TECHNIQUES

As outl~ned ~n reference 5 a nom~nal PGNCS entry from earth orb~t ~s

based on a preparat~on t~me of 2 hours and 40 m~nutes ~nclud~ng 2n~ght passes Th~s t~me ~ncludes approx~mately 20 minutes before thef~rst n~ght pass after the CMC update and PAD data have been rece2vedTh~s t~e also 2ncludes approx2mately 20 m2nutes after the secondn~ght pass to allow suffic~ent t2me to prepare for retrof2re after theIMU f2ne a12gnment It has been determ2ned coarse a12gnment accuracy~s adequate for retrof~re and entry and undoubtedly other funct20nscould be om2tted depend2ng on the c2rcumstances for the dec2s20n toreenter Descr2bed here2n are the nom2nal earth oro2tal entry proshycedures w2th pert2nent comments on system va12dat20n for real timeacceptance dec~s20ns

After the entry dec~s~on is made the crew transfers the PGNCS fromthe standby to the operate mode and rece~ves a CMe update w~th P27Next the maneuver PAD update ~s v02ced up and the 2n~t~al entry mode~s determ~ned During the ~n~tial n~ght pass the IMU or2entat~on ~s

estab12shed uS2ng P51 star s~ght2ngs to obta2n a REFSMMAT The preshyferred or~entat~on opt20n ~n P52 2S then selected to coarse a12gn theIMU uS2ng the des2red entry REFSMMAT determ2ned by MGG-H The GOO ~s

now al~gned to the IMU 2n preparat~on for an IMUSes dr~ft check Ifthe GOO ~nd~cates the ses dr2ft rate exceeds 10 degrees per hour ~n

any ax~s the check ~s repeated on the other BMAGs to estaol~sh if theGOO or Just the single set 2S unusuable Var20us sytem checks as 12sted2n sect20n 51 are performed as necessary cons2stent w2th the t2me12ned2ctates of the maJor act2v2t2es Included 2n these checks are the EMSself-tests and the dV counter test The latter requ2res the spacecraftbe placed ~n dr2ft2ng fl2ght w~th the funct20n sW2tch 2n the dV pos2t~on

If the counter reg2sters a change of more than 25 feet per second w2th2n100 seconds the scroll and counter are unre12able for mon2tor2ng thedeorb2t burn and entry rang2ng If the EMS self-test fails and t2medoes not allow further analysis a 5555 ERE entry 1S planned as thePGNGS backup entry mode After complet2on of these checks the entryPAD lS prov1ded by MeG-H The crew then selects the external dVprogram P30 and the appropr2ate deorb1t tbrust1ng program p40 or P41Dur2ng th2s per2od wh2ch 2ncludes the f1nal n2ght pass P52 may beselected to ver2fy the IMU a12gnment Since the retro att2tude hasbeen computed so that a w2ndow mark c01nc2des w2th the hor2zon atGETI th2s serves as the conclus2ve check on the PGNCS At 5 m2nutesbefore retrofire the att2tude check 1S made by ver1fY2ng that the 12degree scr~be 12ne ~s w2th2n 3 degrees of the hor2zon If not thePGNeS has fa2led and the ses 2S used for att2tude reference and the

V counter for burn durat~on control S2nce the ses att~tude wasa12gned to the IMU a real~gnment ~s necessary This ~s accompl~shed

by manually maneuver2ng the spacecraft to ma~nta1n the 24 degree wlodowmark on the hor2zon and releas1ng the GOO a12gn button at TIG - 2 m2nutes

-14-

Upon complet~on of the burn the tN res~duals are burned to W~th~n

02 feet per second If the PGNCS ~V counter or est~mated burnduration are ~n d~sagreement ~t must be estab1~shed whether suff~shy

c~ent veloc~ty has been suppl~ed to put the land~ng po~nt in thefootpr~nt The PGNCS data w~ll be used ~f ~t ~s conf~rmed by oneother source if not the ~V counter w~11 be used ~f ~t ~s conf~rmed

by the burn durat~on t~me If add~tional ~V ~s necessary the data~s ava~lable to the crew on an onboard chart found ~n Sect~on 80

Post burn entry preparat~on requ~res EMS ~n~t~al~zation RSI al~gnshy

ment and pre-separat~on funct~ons The crew then selects the ~n~t~al

entry program P61 and records the d~sp1ays as a check aga~nst PADdata Upon complet~on of these checks P62 ~s entered The crewmanually or~ents the spacecraft to the separat~on attitude and yaws450 to ~nsure aga~nst possible CM 8M recontact After separat~on

the spacecraft ~s maneuvered to the reentry tr~m att~tude wh~ch

places the hor~zon on the 3170 w~ndow mark at EI Shortly thereshyafter ~n P62 the entry DAP is act~vated and P63 in~t~ated Dur~ng

th~s t~e MCC-H has computed a postburn update and ~t ~s vo~ced tothe crew ~f d~fferent from preburn values The EMS scroll and rangecounter w~ll be adJusted accord~ngly ~f t~me perm~ts A f~nal PGNCScheck pr~or to 05g may be mon~tored at th~s t~e w~th the CMC modein free and the manual att~tude p~tch ~n acceleration command wh~le

the hor~zon reference ~s held the p~tch error needle w~ll decreaseto zero as EI ~s reached At RET 005g the EMS mode sw~tch ~s

turned to manual the entry 005-g sw~tch and EMS roll sw~tch areturned on and the spacecraft control sw~tched to CMC to beg~n DAPcontrol At the PGNCS 005-g ~ndicatwn the program change fromP63 to P64 ~s mon~tored and the t~e vo~ce recorded At th~s t~me

the EMS range counter check ~s made dur~ng the 10 second per~od

follow~ng EMS 005g Dur~ng th~s per~od the counter should countdown 40 + 10 naut~cal m~les At PGNCS 02-g ~nd~cation the changefrom P64-to P67 ~s monitored and the ~splay may be held by key~ngVERB ~n order to record the init~al downrange error d~splay andcompare ~t to the PAD value The PGNCS has fa~led ~f the two do notagree w~th~n + 100 naut~cal m~les In the event P67 has not appearedwhen both the-g-meter and the scroll ~nd~cate greater than 05g thePGNCS has sim~lar~ly fa~led In e~ther fa~lure the SCS is used foratt~tude reference w~th an EMS entry If the checks agree the crewrema~ns w~th automat~c DAP for the rema~nder of the entry

The entry phase ~s essentially over when the relat~ve velocity ofthe spacecraft decreases to less than 1000 feet per second Th~s

~s ~nd~cated ~n P67 when RTGO lat~tude and long~tude are d~splayed

S~nce very l~ttle rang~ng capab~l~ty exists after th~s pOint thespacecraft is or~ented either full l~ft up or down depending onRTGO negat~ve or pos~t~ve and the crew prepares for the earth land~ng

phase

-15-

41 TYP~cal Retrof~re and Entry Sequence of Events

Dec~s~on to reenter

P27 (CMC update)

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Entry mode dec~s~on

P51 (IMU or~entat~on determlnatlon) durlng f~rst dark per~od

P52 (IMU coarse allgnment)

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P30 (external AV)

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p64 (beg~n DAP control at O05g)

P67 (PGNCS gono go check at O2g)

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-17-

5 0 DETAILED ENTRY PROCEDURES

In order to comblne slmilar procedures that are common to lunar returnentrles and earth orblt entrles the followlng procedures are dlvldedlnto categorles that allow a mlnlmum of dupllClty ThlS provldes asmaller tralnlng package and more closely resembles the onboard crewcheckllst when comparlson lS necessary

51 Entry Preparatlons for Superclucular and Earth Orbltal Entrles

1~e entry preparatlons are comblned In these procedures andsteps pecullar to elther superclrcular or earth orbltal entrlesare labeled accordlngly The tlme llstlngs In thlS sectlon areappllcable to only superclrcular entries Slnce the earth orbltalentry tlmellne lS a functlon of several varlables as descrlbedIn sectlon 40 and reference 5

-18-51 (Contlnued)

VEHICLE PREPARATION

l-

2

3

4

5

6 -0600h

7 -0535h

8

9

10 -0430h

INITIAL STOWAGE COMPLETED

CMC amp ISS START UP

SCS POWER UP

p51 - IMU ORIENTATION

LOAD DAPV48E 11102 01111 PRO ERO PRO

LAST MCC DECISION

NO COMM - P52 amp NAV SIGHTINGSNOMINAL - P2337 ONBOARD COMPARISON

DON MAE WESTS amp FOOT RESTRAINTS

VHF AM A - SIMPLEX

P 27 (SV REFSMMAT) MNVRamp ENTRY pAD UPDATES

11 -0415h P52 - IMU REALIGN(___) (OPTION 1)

12 P37 (NO COMM ONLY)

13

14

ECS CKS02 SUPPLY REFILLECS Monitor CkEVAP H20 CONT (2) vlvs - AUTOSUIT HEAT EXCH SEC GLY - FLOW

EPS CKS 1 3 4 (5 If reqd)

15 SPS CK (If req d)

16

17

18

RCS CKSSM RCS MOUlt CkCM RCS MOUlt Ck

CampW SYS CK

CMC SELF CK

19

20 -0345h

-03l5h-0300h

21

22

22A

-19-

DSKY COND LT TEST

MIDCOURSE MANEUVERP30 - EXT rVP404l - SPSRCS THRUSTINGMIDCOURSE (17) BURN

NO COMM NAV SIGHTINGS

ffiVR TO ENTRY ATT (Superc1rc only)V62E

V49E

22B F 06 22 DESIRED FINAL GMBL ANGLESLOAD ENTRY ATT PAD ANGLESPRO

22C F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) SC CONT - CMC

BMAG MODE (3) - RATE 2CMC MODE - AUTO

PRO(~N) SC CONT - SCS

MNVR to 22E

22D 06 18 AUTO MNVR TO FDAI RPY ANGLES

22E F 50 18 REQUEST TRIM(TRIM) Go to 22C(BYPASS) ENTR

23 -200hr BORESIGHT amp SXT STAR CHECKOPT MODE - CMCOPT ZERO - OFF

V41 N91E

F 21 92 SHAFT TRUNLoad SXTS angles

41 OPTICS DRIVE

CHECK SXT STAROPT ZERO - ZERO

CHECK BORESIGHT STAR (If ava11)

24 -0135h

25(___)

26

27 -0115h

-20-

P52 - lMU REALIGNRecord gyro torqu~ng anglesRp~----

YIf-7gt-Lno--re-c-ycle PS2If conflrmed use SCS for EMS entry

GDC ALIGNIf drlft gtLOohr change ratesource

FINAL STOWAGEOPTICS (except for hybrid)ORDEALGLY TO RAD SEC - BYPASS (verlfy)CooL pnl lnstalledY-Y struts (2) extendedStow Data Box R-12

EMS CHECKEMS FUNC - OFFcb EMS (2) - closeEMS MODE - STBYEMS FUNC - EMS TEST 1 (walt 5 sec)EMS MODE - NORMAL (walt 10 sec)

Check ind lts - offRANGE lnd - 00Slew halr1ine over notch

In self-test patternEMS FUNC - EMS TEST 2 (walt 10 sec)

05G It - on (all others out)EMS FUNC - EMS TEST 3

05G It - onRSI Lower It - on (10 sec Qater)Set RANGE counter to 58 nm+OO

EMS FUNC - EMS TEST 405G It - on (all others out)G-V trace w~thin pattern to lwr rt

corner 9GRANGE lnd counts down to 0+02

EMS FUNC - EMS TEST 505G It - onRSI upper lt - on (10 sec later)RANGE md - 00SCrlbe traces vertlcal llne 9g to

022+01ALIGN SCROLL TO ENTRY PATTERN (on

37K ft sec hne)EMS FUNC - RNG SET

G-V scroll assy traces vert llne022g to 0+01

EMS MODE - STBY

28

29

30 -OllOh

-21-

~V TEST (Deorb~t only)EMS FUNC - ~V SETVHF RNGSET ~V ~nd to 15868 fpsEMS MODE - NORMALEMS FUNC - ~V TEST

SPS THRUST LT - onoff (10 sec)~V ~nd stops at -01 to -415

EMS MODE - STBY

PRIMARY WATER EVAP ACTIVATIONGLY EVAP H20 FLOW - AUTOGLY EVAP STH PRESS - AUTOPRI ECS GLY PUMP - ACI

CM RCS PREHEATNote If sys test mtr 5cd6abcd

all read 39 vdc (28degF) or moreom~t preheat

cb RCS LOGIC (2) - closeCM RCS LOGIC - ONUP T1M CM - BLOCK (ver~fy)

cb CM RCS HTRS (2) - closeCM RCS HTRS - ON (LMP Conf~rm)

(20 mlU or III lowest rdg lS39 vdc) (Moultor Maufpress for press drop)

31 (___) FINAL GDC DRIFT CK (If req I d)If drlft gtlOohr Suspect GDC Do not

use RSI amp FDAI 2

32 -OO5Om

33

34

35

TERM CM RCS PREHEATUP TLM CM - BLOCK (venfy)CM RCS HTRS - OFFCM RCS LOGIC - OFF

SYSTEMS TEST PANEL CONFIGURATIONSYS TEST METER - 4BRNDZ XPNDR - OPERATECM RCS HTRS - OFFWASTE H20 DUMP - OFFURINE DUMP - OFF

LEB LIGHTING - OFF

SEC WATER EVAP ACTIVATIONGLY To RAD SEC vlv - BYPASSSEC COOL EVAP - EVAPSEC COOL PUMP - AC2

36

37

38 -OO45m

-22-

PYRO BATT CKcb PYRO A SEQ A - close (ver~fy)

cb PRYO B SEQ B - close (verify)DC IND - PYRO BAT A(B)

~If PYRO BAT A(B) lt 35 vdc cb PYRO A(B) seq A(B) - open~

PYRO A(B)BAT BUS A(B)TO PYRO~MN BUS TIE - close

cb MNA BAT C - closecb MNB BAT C - closeDC IND - MNBPNL 8 - All cbs closed except

PL VENT - open (ver~fy)

FLOAT BAG (3) - open (ver~fy)

DOCKING PROBE (2) - open (verlfy)EDS BAT (3) - open (ver~fy)

CM ReS HTRS (2) - open

CM RCS ACTIVATIONcb SECS ARM (2) - close (verlfy)cb SECS LOGIC (2) - close (verlfy)SECS LOGIC (2) - ONMSFN conflrm GO for PYRO ARM(~f poss)SECS PYRO ARM (2) - ARMCM RCS PRPLNT 1amp2 - ONCM RCS PRESS - ONRCS Ind sw - eMl then 2

He PRESS 3700-4400 pSlaMANF PRESS 287-302 pSla

SECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFF

P27 amp ENTRY PAD UPDATEGo To Entry Checkllst

Superclrc - pg ~2~3 _Hybnd - pg -----2~9L-__Normal Deorblt - pg __3L5L- _

-23-

52 SUPERCIRCULAR ENTRY

1 SET DET (up to ET)

2

3

4

5

3000(-30-00)

EMS INITIALIZATIONSET RNG TO PAD DATA RNGEMS FUNC - Vo SETSlew Scroll to Pad Data VIOEMS FUNC - ENTRY

RS I ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on (up)GDC ALIGN PB - PUSH amp HOLDYAW Tw - Pos~t~on RSI thru

45deg amp back to LIFT UPGDC ALIGN PB - ReleaseEMS ROLL - OFFA1~gn CDC to lMU

CM RCS RING A CKRCS TRNFR - CMcb CM RCS LOGIC MNB - openAUTO RCS SEL MNB (6) - OFFSC CONT - SCSTest R~ng A ThrustersSC CONT - CMCRCS TRNFR - SMAUTO RCS SEL (12) - MNAMNB

(hftoff conflg)cb CM RCS LOGIC MNB - close

OPTICS PWR - OFFCMP to COUCH

MN BUS TIE (2) - ONTAPE RCDR - REWIND

6 35middot0Om(-25middot 00)

-24-

SEPARATION CK LISTTVC SERVO PWR 1 - AClMNAcb ELS (2) - close (ver1fy)PRIM GLY TO RAn - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY vlv - OFFCAB PRESS REL vlv (2) - NORMGMBL MTRS (4) - STARTABORT SYS PRPLNT - RCS CMD (venfy)SM RCS PRIM PRPLNT (4) - ONVHF 11M (AampB) - OFFHI GAIN ANT PWR - OFFFC PUMPS (3) - OFFVer1fy s1ugle SU1t compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - 10101cb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2) - opencb HTRS OVLD (2) - openPOT H20 RTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANSEC COOL EVAP - RESETSEC COOL PUMP - off (etr)

MtiVR TO CMSM SEP P R ATTSC CONT - SCSCMC MODE - FREEMNVR TO PAD ATTR (0deg)PY----W)

-25-

SUPERCIRCULAR ENTRY (Cont~nued)

1

4100m(-1900)

P61 - ENTRY PREP

V37E 61E

k 05 09 01427 - ROLL REVERSED 05 09 01426 - IMU UNSAT ~

2 F 06 61 IMPACT LAT LONG HDS UPDN (+-)PRO (010

fps +00001)

3 F 06 60 GMAXVPREDGAMMA EIRecord

GMAXV400K----

GAMMA EI _PRO

(01deg fpsOldeg)

4 F 06 63 RTOGO (lnm) PAD _VIO (fps) PAD _TFE(m~n-sec)

Compare w~th ~M~SFN==C~f~o-r~P~GNS GONO GOIf NO COMM Set RTOGO amp VIO In EMS

amp lnltla11ze(ACCEPT) PRO(RECALC) V32E To 4

5 F 50 25

4300m

(-1700)

45 oOm(-1500)

500Om(-1000)

6 F 06 61

-26-

P62 - CMSM SEP amp PRE-ENTRY MNVRCAUTION Call No EXT Verbs In P62

00041 REQUEST CMSM SEPSC CONT - SCSFREE

COMPARE PITCH ATT WITH PAD DATA ---0=-

(W~thLU 5deg)YAW - 45deg OUT-OF-PLANE (LEFT)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTIRATE 2MN BUS TIE (2) - ON (ver~fy)

PRIM GLY TO RAD - BYPASS (verlfy)CM RCS LOGIC - ON (venfy)SECS LOGIC (2) - on (up)SECS PYRO ARM - ARMCMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 ps~a

CM RCS LOGIC - OFFSECS PYRO ARM (2) - SAFEMonltor VMAB

If lt25 vdc go to EMERGPOWERDOWN pg E6-l

AUTO RCS SEL AC ROLL (4) - OFFAUTO RCS SEL CM 2(6)-OFFAUTO RCS SEL CM 1(6)-MNAYAW back to 0degPITCH TO HORIZ TRACK ATT

ROLL - 0deg (LIFT UP)PITCH - 400K Horiz Mark (317deg)YAW - 0deg

ATT DB - MAXMAN ATT PITCH - ACCEL CMDEMS DATA - Ver~fy

EMS FliNC - ENTRY (ver~fy)

EMS MODE - NORMALcb SPS PampY (4) - openMAINT HORIZ TRK

PRO (Act ENTRY DAP)

IMPACT LATLONGHDSDN (01deg01deg-00001)PRO

7 POSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axis beyond 45deg of Vel vector)

8 06 64

58middot00m(-0200)

9

05G tlme(+0 )

(--=---)

06 68

-27-

P63 - ENTRY INIT

GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PIJR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRmDHORIZ CKPltch error needle goes toward

zero approachlng OSG tlmeMAN ATT (PITCH) - RATE CMD

If CMC lS GOBMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS I

FLY BETA If CMC NO GO ilt

1 SC CaNT - SCS I

FLY EMS k

p64 - ENTRY POST 05G

RTOGO AT 05G AGREES HITH EMS-venfyHORIZ CK05G Lt - ON (EMS START)

No EMS START wlthln 3 sec ~ EMS MODE - BACKUP VHF RNG c

05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds Llft DN

NNVR Llft DNEMS GONO GO

G-V Plot wlthln IlmltsRng ctr dwn 60plusmn7 durlng 10 sec

perlodMonltor G-meter for

convergence wlth pad data (Do)(Vlt27K fps) Go to 13

-28-

P65 - ENTRY - UP CONT (Vgt27K fps)

10 F 16 69 BETA (01middot) _DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT lt~ SC CONT - SCS FLY EMS

PRO

11 06 68 BETAVIHDOT (OIdegfpsfps)(VltV1+500 fps amp RnOT Neg) Go To 13

P66 - ENTRY - BALLISTIC (D(DL)

12 06 22 DESIRED GMBL ANGLES RPYMoultor horlz +12middot of 317middot mark

P67 - ENTRY - FINAL PHASE (02G)

13 06 66 BETACRSRNG ERRDNRNG ERR(010 1um 1um)

KEY VERBRecord DNRNG ERR _KEY RLSEMoultor l~ft vector ou RSI amp FDAI

16 67 RTOGOLATLONG (Vrel=1000fps)(lumOldegOldeg)

SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOWNMonitor a1t~meter

Go To EARTHLANDING pg ---4L5 _

-29-

53 GampN HYBRID DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL tV1 V37E 30E

2 F 06 33 GETI(ACCEPT) PRO (hrm~n Olsec)(REJECT) LOAD DESIRED GETI

3 F 06 81 tVXYZ (LV) (lfps)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

4 F 06 42 HAHPtV (lnm lfps)Record tV

(ACCEPT) PRO(REJECT) Reselect P30 or P27 Load new paramo

5 F 16 45 MTFIMGA (marksm~n-secOlO)

MGA -00002 ~f k

k lMU not al~gned

SET DETPRO

6

7

8

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (Pull)PLSS 02 vlv - FILL02 8M SUPPLY vlv - OFFCAB PRESS REL vlv (2) - NORMcb ELS (2) - closecb SECS ARM (2) - closecb SECS LOGIC (2) - close (ver~fy)

AUTO RCS SEL CM (12) - MNA or ~ffiB

(hftoff conhg)ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM (AampB) - OFF

CMP to Couch

9

10

11

-30-

MNVR TO PAD BURN ATTLOAD DAPBMAG MODE (3) - RATE 2SC CONT - CMCAUTOATT DB - MINMAN ATT (3) - RATE CMD

v62E

v49E

12 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLES

PRO

13 F 50 18 REQ MNVR TO FDAI RPY ANGLES (01deg)(AUTO) PRO(MAN) SC CONT - SCS

BMAG MODE (3) - RATE 2MNVR To 15

14 06 18 AUTO MNVR TO FDAI RPY ANGLES (01deg)

15 F 50 18 REQ TRIM TO FDAI RPY ANGLES (01deg)(TRIM) Go to 13(ByPASS) ENTR

16

17

CHECK BORESIGHT amp SKT STARSOPT MODE - CMCOPT ZERO - OFF

v41 N91E

18 F 21 92 SHAFTTRUN (01deg 001deg)Load SXTS angles

19 41 OPTICS DRIVECheck SKT STAR

OPT ZERO - ZEROCheck BORESIGHT STAR (~f ava~l)

20 V25 N17E (01deg)Load Pad Data GMBL Angles

for CM BURN ATTATT SETtw - SET

to PAD DATA GMBL ANGLESfor CM BURN ATT

21

22

-31-

PHR REDUCTIONHGA PHR - OFFFC PUMPS (3) - OFFVerify s~ngle su~t compr oper loads

balancedFC 2 MN AampB - OFFS BD PiR AMP - LOWcb ECS RAD CONTHTR (2) - opencb HASTE H20URINE DUMP HTRS(2)- opencb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANMN BUS TIE (2) - ONTVC SERVO PHR 1 - AC1MNAGMBL MTR (4) - START

p41 - RCS THRUSTINGV37E 41E

23 F 50 18 REQ MNVR TO LCL HORIZ (HDS ON)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CMCAUTOPRO To 24

(gtfANDAP) BMAG MODE (3) - RATE 2SC CONT - CMCHOLD

V62EMNVR To 25

24 06 18 AUTO MNVR TO FDAI RPY

25 F 50 18 REQ TRIM TO LCL HORIZ (01deg)ALIGN SC ROLL

(AUTO TRIM) PRO To 24(BYPASS) ATT DB - MIN

RATE - LOHMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTlRATE 2

ENTR

550Om26 06 85

59middot2527

-32-

VGXYZ (1fps)RECHECK BORESIGHT STARTRANS CONIR PWR - on (up)EMS MODE - STBY (ver~fy)

EMS FliNC - bV SETVHF RNGSET (IV for SM BURN _EMS FliNC - bVS BD ANT - OMNI CSECS LOGIC (2) - ONMSFN conhrm Go for PYRO ARMSECS PYRO ARM (2) - ARMCM RCS LOGIC - ON (ver~fy)

DSKY BLANKS

593028 16 85 VG XYZ (AVE G ON) (lfps)

RHCs amp THC - ARMEDLIMIT CYCLE - OFFTAPE RCDR - CMD RESETHBREMS MODE - NORMAL

000029 F 16 85 REQ NULL VG XYZ (lfps)

BURN EMS bV CTR TO ZERORESET DET amp COUNT UP

If SM ONLY burn go to step 32THC - LOCKEDSC CaNT - SCSFREERATE - HIGHPRIM GLY To RAD - BYPASS (ver~fy)

MN BUS TIE (2) - ON (ver~fy)

CMSM SEP (2) - on (up)CSMLM FNL SEP (2) - on (up) (verify)CampW MODE - CMRCS TRNFR - CMCM RCS LOGIC - OFF

Momtor VM ABIf lt25 vdc go to EMERGPOWER DOWN Pg E6-l

V63E

If CMC NO GO FDAI SOURCE - ATT FDAI SEL - 1 or 2 ATT SET - GDC

SET

-33-

~Uili ATT PITCH - ACCEL CMDFDAI SCALE - 55MNVR TO CM BURN ATT (NULL ERR NEEDLES)

R 0degPY --00--

30

31

CM RCS BURNRHC III-ContJnuous PJtch DownRHC HZ-Module PJtch to null needlesBURN VGZ TO ZERO

If only 1 RHC Pulse + P=5deg from retro att MaJnta~n rates lt3degsec

BURN COMPLETION ATllV CTR= or DET= _

V8ZE

32 F 16 44 HAHPTFF (1nmffiJn-sec)Check HP-

If gt Pad data contJnue burnuntJ1 lt Pad

PRO

33 F 16 85 VGXYZ (Ups)Read VG resJduals to MSFN

(HYBRID) PRO to 34(SM ONLY BURN)

PROF 37 ODE

EI-1500 V37E 47EF 16 83 twx Y Z (Ups)

SC CONT - SCSFREEMAN ATT (PITCH) - RATE CMDRATE - HIGHPRIM GLY To RAD - BYPASS (verJfy)MN BUS TIE (2) - ON (verJfy)CMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verJfy)Campl MODE - CMRCS TRNFR - CMCM ReS LOGIC - OFFSECS PYRO ~I (2) - SAFE

-34-

PROMonitor VMAB

If lt25 vdc go to EMERGPOWER DOWN

34 F 37 OOEPCM BIT RATE - LOWATT DB - MAXEMS MODE - STBYEMS FUNC - OFF

Go To EARTH ORBIT ENTRY pg _--40-__

-36-

8 SPS THRUSTING PREPCYCLE CRYO FANSSPS GAGING - ACI (ver~fy)

PUG MODE - NORM (venfy)BMAG MODE (3) - RATE 2tv CG - CSMCMC MODE - FREEAUTO RCS SEL (16) - MNA or HNB

(hftoff conbg)SC CONT - CMCAUTO

9 MNVR TO PAD BURN ATTV62E

10 V49E

11 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLESPRO

12 F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) PRO(HAN) SC CONT - ses

MNVR to 14

06 18 AUTO MNVR TO FDAI RPY ANGLES13

14 F 50 18 REO TRIH TO FDAI RPY ANGLES(TRIM) Go to 12(BYPASS) ENTR

15 BORESIGHT STAR CHECK

16 V37E 40EOPT PWR - OFF

17 F 50 18 REQUEST MNVR TO FDAI RPY ANGLES (01deg)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CHCAUTOPRO to 18

(MANDAP) BMAG HODE (3) - RATE 2SC CONT - CMCHOLDMNVR to 19

(HANseS) se eONT - sesMNVR to 19

-35-

54 NORMAL DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL ~V

1 V37E 30E

2 F 06 33 GETI (hrm~nOlsec)

(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

3 F 06 81 ~VXYZ (LV)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

( lfps)

4 F 06 42 HAHP~V (1nmlfps)Record W

(ACCEPT) PRO -----(REJECT) Rese1ect P30 or P27 Load new pa~am

5 F 16 45 MTFIMGA (marksmln-secOldeg)MGA -00002 If ~ lMU not a1~gned

SET DETPRO

6

7

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY v1v - OFFCAB PRESS REL v1v (2) - NORMcb ELS (2) - close (verify)cb SECS ARM (2) - close (ver~fy)

cb SECS LOGIC (2) - close (verlfy)AUTO RCS SEL CM (12) - ~mA or MNB

(l~ftoff conf~g)

ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM AampB - off (ctr)

18

-37-

06 18 AUTO MNVR TO FDAI RPY ANGLES (01 0)

19 l 50 18 REOUEST TRIM MNVR TOALIGN SIC ROLLGDC ALIGN

FDAI RPY ANGLES(010

)

+54-00m(-06-00)

TIG-5mJn

5500m(-0500)

TVC CHECK amp PREPcb STAB CONT SYS (all) - closecb SPS (12) - closeATT DB - MINRATE - LOl~

LIMIT CYCLE - ONMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE 2ROT CONTR PWR DIRECT (2) - OFFSCS TVC (2) - RATE CMD

If SCS SCS TVC (2) - AUTO SC CONT - SCS ~

TVC GMBL DRIVE PampY - AUTOMN BUS TIE (2) - ONTVC SERVO PWR 1 - AC1MNA

2 - AC2MNBTRANS CONTR PWR - ONROT CONTR PWR NORMAL 2 - ACRHC 2 - ARMED

HORIZ CHK - HorJz on 12deg wJndmlmark (LJffiJt +3 0 PNGCS GONO GO)

If NO GO set tw 180 0 180deg0 0

Track horJz wJth 24deg wJndow markAt TIG-2 mJn Ahgn GDC

PRIMARY TVC CHECKGMBL MOT P1-Y1 -STARTON(LMP confJrm)

If SCS verJfy Thumbwheel TrJmTHC - CWVenfy NO MTVC

SEC TVC CHECKGHBL MOT P2-Y2 -STARTON(LMP confJrm)SET GPI TRIHVenfy MTVCTHC NEUTRALGPI returns to 00 (CMC) or trJm (SCS)ROT CONT Pl~ NORM 2 - ACDC

(TRIM) Go to step 17(BYPASS) BMAG MODE(3) - ATTIRATE2 (ver1fy)

ENTR

-38-

20 F SO 25 00204 GMBL TEST OPTION(ACCEPT) SC CONT - GMC (ver~fy)

PROMonitor GPI Response

0020-2000020-200Tr~m

TEST FAIL SC CONT - SCS SCS TVC (2) - AUTO

(REJECT) ENTR

21 06 40 TFIVG~VM (m~n-sec1fps)

PROG ALM - TIG s1~pped

V5N9E 01703

KEY RLSE To 21 ROT CONTR PWR DIRECT (2) - MNABSPS He v1vs (2) - AUTO (ver~fy)

LIMIT CYCLE - OFFFDAI SCALE - SOIScb SPS P2Y2 - open (for cr~t burn)

5800(-02 00)

5925(-0035)

59middot 30(-0030)

06 40

59XX(-OOXX)

AV THRUST A(B) - NORMALTHC - ARMEDRlIC (2) - ARMEDTAPE RCDR - GID RESETHBR

DSKY BLANKS

(AVE G ON)EMS MODE - NORMAL

TFIVG~VM (m~n-seclfps)

CHECK PIPA BIAS lt2fps for 5 sec

ULLAGE AS REQ

IF NO ULLAGE DIR ULLAGE PB - PUSH~

CONTROL ATT WRlIC MONITOR AVM (R3) COUNTING UP

5955(-0005)

F 99 40 ENG ON ENABLE REQUEST(AUTO IGN) PRO AT TFI gt0 sec(BYPASS IGN) ENTR to 24

22 0000 IGN

-39-

If SCS - THRUST ON PB - PUSH

06 40 TFCVG~VM (m~n-seclfpslfps)

~F 97 40 SPS Thrust fall ~

~(RESTART) PRO To IGN (RECYCLE) ENTR To TIG-05 sec

SPS THRUST LITE - ONMONITOR THRUSTING

Pc 95-105 pSlaEMS COUNTING DOWNSPS IN3 v1vs (4) - OPENSPS He v1vs tb (2) - graySPS FUELOXID PRESS - 175-195 pSlaPUGS - BALANCED

PROG ALARM V5N9E 01407 VG INCTHC - CW FLY MTVC

ECOEMER SPS CUTOFF J

AV THRUST (2) - OFF

23 F 16 40 TFC(STATIC)VG~VM (mln-seclfps)~V THRUST AB - OFF

SPS IN3 v1vs (4) - CLOSEDSPS He tb (2) - bp

cb SPS P2Y2 - closed (verlfy)TVC SERVO PHR - AC1MNA (venfy)TVC SERVO PWR 2 - OFF

PRO

24 F 16 85 VG XYZ(CM) CUps)NULL RESIDUALSRECORD ~V CTR amp RESIDUALS I1VCEMS FUNC - OFF VGXEMS MODE - STBY VGYBMAG MODE (3) - RATE 2ATT DB - MAX VGZTRANS CONT PHR - OFF

PRO

25 F 37 V82E

26 F 16 44 HAHPTFF (lnmm~n-sec)

R3-59B59 HP gt494 nmPRO

27 F 37 OOE

-40-

55 EARTH ORBIT ENTRY

1 Venfy CMSMR __

P_shyY_-

SEP ATT(180deg)

(0deg )

2

3

4

EMS INITIALIZATIONEMS FUNC - RNG SETSET RNG TO PAD DATA RNGEMS FUNC - VA SETSlew scroll to pad data VIOEMS FUNC - ENTRY

RSI ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on(up)GDC ALIGN PB - PUSH amp HOLDYAW tw - Pos1tion RSI thru 45deg amp

back to LIFl UPGDC ALIGN PB - RELEASEEMS ROLL - OFFAl1gn GDC to lMU

PWR REDUCT (Norm Deorb Only)HGA PWR - OFFFC PUMPS (3) - OFFVer1fy s1ngle suit compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - Lowcb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2)-openlOb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MAN

-41-

P61 - ENTRY PREP

5 V37E 61E05 09 01427 - ROLL REVERSED05 09 01426 - IMU UNSAT

6 F 06 61 IMPACT LAT LONG liDS UPDN (+-)(01 0

010

+00001)

PRO

PAD VALUESLATLON==G------liDS UP DN _

7 F 06 60 GMAXV400KGAMMA EIRecord

GMAXV400K----GAMMA EI _

PRO

8 F 06 63 RTOGO (1nm) PAD _VIa (fps) PADTFE (mln-sec) ----Compare wlth MSFN for PGNS GONO GONO COMM SET RTOGO amp VIO IN EMS amp

INITIALIZE(ACCEPT) PRO(RECALC) V32E to 8

-42-

P62 - CMSM SEP amp PRE-ENTRY MNVR

9 F 50 25 00041 REQUEST CMSM SEPSC CONT - SCSFREEYAW - 45deg out-of-plane (left for RCS

nght for SPS)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE2PRIM GLY to RAD - BYPASS (verlfy)SECS LOGIC (2) - on (up)MSFN conflrm GO for PYRO ARMSECS PYRO ARM - ARMMN BUS TIE (2) - ON (verlfy)CMSM SEF (2) - ONCSMLM FNl SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 pSlaCM RCS LOGIC - OFFSECS PYRO ARM - SAFEMonltor VMAB

If lt25vdc go to EMERG POWERDOWN Pg E6-1AUTO RCS SEL AlC ROLL (4) - OFFAUTO RCS SEL CM 2(6) - OFFAUTO RCS SEL CM 1(6) - MNA or MNBYAW back to 00

PITCH TO ENTRY ATTROLL 0deg (LIFT UP)PITCH - HORIZ on 317deg MARK (400K)YAW 00

ATT DB - MAXMAN ATT (PITCH) - ACCEL CMDEMS DATA - VerifyEMS FUNC - ENTRY (verlfy)EMS MODE - NORMALMAINTAIN HORIZ TRK

PRO (Act ENTRY DAP)

10 F 06 61 IMPACT LAT LONG HDSDN(010 010 -00001)

PRO

11 FOSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axlS beyond 45deg of Vel vector)

-43-

P63 - ENTRY INIT

12 06 64 GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PWR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRHORIZ CKP~tch error needle goes toward

zero approach~ng 05G t~me

MAN ATT (PITCH) - RATE CMDIf CMC ~s GO

BMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS FLY BETA If CMC NO GO ~

SC CONT - SCS~

FLY EMS RCS Deorh Roll HDS UPTRACK HORIZ w~th 29deg w~ndow mk

P64 - ENTRY POST 05G

13

05G t=elt+0___)

06 68

RTOGO AT 05G AGREES WITH EMS - venfyHORIZ CK05E Lt - on (EMS start)

No EMS start w~th~n 3 secsEMS MODE - BACKUP VHF RNG 05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds L~ft DN

NNVR L~ft DNEMS GONO GO

G-V Plot w~th~n llm~ts

Rng ctr dwn 60 + 7 durlng 10 sec per~od

Mon~tor G-meter forconvergence wlth pad data (Do)

(Vlt27K fps) Go To 17

-44-

P65 - ENTRY - UP CONT (Vgt27K fps)

14 F 16 69 BETA (01deg)DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT~

SC CONT - SCS FLY EMS

PRO

15 06 68 BElA VI HOOT (01deg fpsfps)(VltVL +500 fps amp RDOT Neg) Go To 17

p66 - ENTRY - BALLISTIC (DltDL)

16 06 22 DESIRED GMBL ANGLES RPY (01deg)Mon~tor hor~z +12deg of 317deg mark

P67 - ENTRY - FINAL PHASE (02G)

17 0666 BETACRSRNG ERRDNRNG ERR (Oldeglnmlnm)KEY VERBRecord DNRNG ERR _KEY RLSEL~m~t +100nm from PAD DRE

Mon~tor l~ft vector on RSI amp FDAIF 16 67 RTOGOLATLONG (Vre1=1000fps)

(lnm 010 01deg)SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOlfflMon~tor altimeter

Go To EARTHLANDING pg _I4L5__

-45-

56 EARTHLANDING

90K STEAM PRESS - PEGGED50K CABIN PRESS REL vIv (2) - BOOSTENTRY

SECS PYRO ARM (2) - ARM

40K(90K + 63s)

CM UNSTABLE RCS CMD - OFF ~ 40K APEX COVER JETT PG-PUSH DROGUE DEPLOY PG - PUSH (2 secafter apex cover Jett)

30K ELS LOGIC - ON (up)ELS - AUTO

24K RCS hsable (auto)(90K+92s) RCS CMD - OFF

Apex cover Jett (auto)APEX COVER JETT PB - PUSH

(WAIT 2 SECS)Drogue parachutes deployed (auto)

DROGUE DEPLOY PB - PUSH~

If Drogues FallELS - ~ ~Stablllze CM 5K MAIN DPLY PB - PUSHELS - AUTO

235K Cabln Pressure lncreaslng (Drogues + 50s)If not lncreaSlng by 17K CABIN PRESS REL vlv (RR) - DUMP

-46-

10K Maln parachutes deployedMAIN DEPLOY PB - PUSH (wlthln 1 sec)VHF ANT - RECYVHF AMA - SIMPLEXVHF BCN - ONCABIN PRESS REL v1v (2) - CLOSEDIRECT 02 vlv - OPENCM RCS LOGIC - on (up)CM PRPLNT - DUMP (burn audlb1e)Monltor CM ReS 1amp2 for He press decrease

NO BURN or PRESS DECREASE USE BOTH RHCs DO NOT FIRE PITCH JETS

CM PRPLNT-PURGE (to zero He press)CM RCS He DUMP PB - PUSH RHC (2) - 30 sees NO PITCH k

STRUT LOCKS (2) - UNLOCK

cb FLT amp PL BAT BUS ABampBAT C (3) - closecb FLT amp PLT MNA amp B (2) - opencb ECS RAD HTR OVLD (2) - opencb SPS PampY (4) - open

3K CABIN PRESS REL v1v (RH) - DUMP (after purgecompleted)

FLOOD Lts - POST LDGCM RCS PRPLNT (2) - OFFROT CONTR PWR DIRECT (2) - OFF

800 CAB PRESS RELF vlv - CLOSE (latch off)MN BUS TIE (2) - OFF

AFTER LANDINGcb MAIN REL PYRO (2) - closeMAIN RELEASE - on(up)

Go to POSTLANDING pg _47L-__

I

2

3

-47-

57 POSTLANDING

STABILIZATION VENTILATION COMMUNICATIONS

DIRECT 02 vlv - CLOSE

Stablllzation after landlngELS - AUTO (verlfy)cb MAIN REL PYRO (2) - close (venfy)MAIN RELEASE - on (up) (verlfy)S~CS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb BAT RLY BUS (2) - open

No contact w1th recovery forcesVHF AM AampB - off (ctr) ~

VHF AM Rev ONLY - A cb PL VENT - closecb FLOAT BAG (3) - closecb UPRIGHT SYS COMPRESS (2) - closeIf Stable II

FLOAT BAG(3)-FILL t1ll 2 m1n afterupr1ght then - OFF

VHF AM AlB amp BCN - OFF whlle lnvertedIf Stable I

After 10 M1n Coollng Per1odFLOAT BAG (3) - FILL 7 mln then OFF

Post Stab1lizat1on And Ventllat10nPL BCN LT - BCN LT LOWPL VENT vlv - UNLOCK (Pull)Remove PL VENT Exh CoverPL VENT - HIGH or LOWPL DYE MARKER - ON (swlmmer comm)Release foots traps and_restralntscb MNA BAT BUS A amp BAT C (2) - opencb MNB BAT BUS B amp BAT C (2) - opencb FLT amp PL BAT C - opencb PYRO A SEQ A - opencb PYRO B SEQ B - open

EACH HR - CHECK DC VOLTSgt 275 V If Notmiddot cb FLT amp PL-BAT BUS AampB (2) -open cb FLT amp PL BAT C (1) - open GO TO LOW POWER CHECKLIST

Unstow and lnstall PLV DISTRIB DUCTDeploy grappllng hook and 11ne 1f req

4

-48-

Post Landing Communlcatl0nsVHF ANT-RECY (venfy)VHF BCN - ON (verlfy)

If no contact ~lth recovery forcesperform VHF BEACON Check

MONITOR VHF BEACON transmlSSlonnth VHF AM B Rcvr andor Su)vlval

TransceiverkVHF Beacon not operatlng ~connect Surv~val TranscelVer to antcable behlnd VHF ant access pnland place radio ln BCN mode

LOW POHER CHECKLISTVHF BCN - OFFVHF AM (3) - RCVFLOOD Lts - OFFVHF AM AampB - off (ctr)VHF AM RCV ONLY - A (venfy)COUCH LIGHTS - OFFPOSTLANDING VENT SYS mlnlmlze useSURV RADIO - plug mto VHF BCN ANT cableconn behind VHF ant acess pnl amp turn radloon l-n BCN mode

EGRESS PROCEDURES

CMPCDRLMPCDR

CMPCDRCMP

LMPLl1PCDR

STABLE IDlsconnect Umblll-calsNeck darn onCenter couch - 270 0 positionArmrests stowedConnect raft to SIC l-f desl-red wlth

green lanyardConnect raft ~hl-te lanyards to SUltS amp

lnflate water wlngs when eXltl-ngHATCH PISTON PRESS vlv - PRESS (Outbd)Slde Hatch openedPL VENT - OFFcb Pnl 250 (all) - openEgress with 11feraftPut hardware klt outEgress

or CDIPALL

CMF

CDRCMF

CDR

LMF

CMFCMP LMFCMP

UlP

CDR

-49-

STABLE IIcb CREW STA AUDIO (3) - openD~sconnect umb~1~ca1s

Release foots trapsRelease restra~nt harnessCouch seat pans (3) - 170 0 pos1t10nArm rests stowedSurv1va1 k~ts removed from stowageConnect life raft ma~n1~ne to CDR or SicConnect f~rst wh~te lanyard from

11fe raft to suitConnect th~rd wh~te lanyard from

l~fe raft to SU1tConnect rucksacks together to yellow

lanyard on raft bagPRESSURE EQUALIZATION vlv - OPENRemove and stow fwd hatchEX1t feet f1rst w1th rucksacks when clear

of siC 1nflate water w1ngs and raftExit feet f1rst when clear of SiC

1nflate water w1ngsEX1t feet f1rst when clear of sic

1nflate water w1ngs

-50-

60 TLI ABORTS

TLI Aborts are conta~ned ~n the ESD s~nce the bulk of the funct~ons

concern entry preparat20ns and performance Th~s allows a s2nglesource of procedures for procedure rev2ew val~dat~on checkout andtra~n~ng These procedures ~ncorporate TLI preparat20ns as found ~n

reference 6 w~th the TLI Abort Procedures and these t~e 2nto normallunar return Entry Procedures found ~n sect20n 5 The guidel~nes

for th~s cont2ngency are spec2f2ed 2n reference 7

In2t2al preparat~ons for TLI pos2t20n the necessary system sW2tches2n add~t~on to perform~ng an EMS ~V test and a GDC al~gnment Afterthe DET ~s set for mon2tor2ng TB6 the CMP ~ncreases the 12ght levelof the LEB DSKY to max~mum and returns to the h2s couch Th2s 2Sdone so that the LEB DSKY can be observed ~n the event sunl~ght orreflect20ns wash out the ma2n d2splay panel DSKY dur2ng cr2t2calmaneuvers The crew then straps ~n and prepares for mon2tor~ng TB6as 2nd2cated by the SII SEP L~te The t2mes se~uence of procedures2S keyed on th~s d~splay and ~ncludes the DET START funct~on andSIVB IGNITION Dur2ng the burn the crew mon2tors the FDAIs foratt~tude excurs20ns and abnormal rates report~ng status checks toM~ss2on Control at d2screet t~mes dur2ng the maneuver Upon SIVBSHUTDOWN the eMP records the DSKY d~splayed performance parametersand awa2ts ground conf2rmat~on

The rat~onal for TLI aborts ~s descr~bed 2n reference 7 A summar2shyzat20n 2S extracted to prov2de background and gu2de12nes 2n th2sdocument The abort procedures cover aborts 10 m2nutes after conshyt2ngent SIVE shutdown and aborts 90 m2nutes after normal SIVE shutshydown t2me

The 10 m~nute TLI abort ~s des2gned to be used dur~ng TLI ~n theevent a spacecraft problem develops Wh2Ch can result 2n catastrophe2f ~mmed~ate act~on 2S not taken If the s~tuat20n perm~ts the crewshould always allow the SIVB to complete TLI at wh~ch t~me the groundand crew can perform a malfunct~on analys~s to determ~ne ~f an abort~s adv~sable If a fa~lure occurs that necess2tates the shutdown ofthe SIVB and the ~u~ck return of the crew to earth th~s abort ~s

des~gned to be as ~nsens~t~ve to execut~on errors as poss~ble andst21l be targeted to m2dcorr2dor The burn att~tude w~th the f~ed

hor~zon reference ~s a constant value for any shutdown t~me Theburn durat~on 2S a funct20n of shutdown t2me and 2S ava21able fromcrew charts S~nce the pr~mary purpose of th~s abort ~s to returnto earth as qU2ckly as poss2ble there are no restr2ct20ns as toland~ng locat~on However ~f the t~me to EI is greater than abouttwo hours a midcourse correct20n should be ant~c~pated

The 90 m2nute TLI abort 2S to be used 2f a cr2t2cal subsystem malshyfunct~on ~s determ2ned and the dec2s~on to abort ~s made after the

-51-

TLI cutoff and before TLI cutoff plus approxlmately 80 m1nutesTh1S allows suff1c1ent separatlon and procedural t1me to set upfor the SPS deorb1t burn performed at about TLI + 90 Note thatgenerally the deorb1t burns w1ll be performed a fe11 m1nutes beforeTLI + 90 accord1ng to crew charts shown In reference 8 The no-comm except10n requ1res that 90 m1nutes be the 1nput t1me of 19n1shytlon for P-37 (onboard return-to-earth abort program) so that onshyboard calculatlons can correspond w1th ground calculat10ns to computethe CM land1ng p01nt Th1S TLI abort lS des1gned so that returnfl1ght t1me does not exceed 18 hours and abort ~V does not exceed7000 fps ThlS abort can be performed uSlng chart ~Vs and attltudesand the earths hor1zon serves as a suff1c1ent reference The maneushyver lS targeted to ach1eve the mldcorr1dor entry target Ilne andtlmed to result 1n a deslgnated recovery area

It 1S ObV10US for abort deC1S1ons early 1n the TLI + 90 m1nute t1meshyframe that a GampN SPS burn should be performed In order to keep theTLI abort procedures cons1stent and w1th emphasls on slmpl1c1ty theprocedures here reflect a SCS SPS abort burn to cover the full abortdec1s1on t1meframe

A m1dcourse correct1on for corr1dor control after a TLI abort may bedeS1red 1f the SPS burn d1d not meet expectat1ons The TLIabortprocedures 1n th1S sect10n adapt to the normal lunar return tlmel1neand procedures pr10r to the f1nal MCC

-52-

61 TLI PREPARATION PROCEDURES

GET = 150

CRO AOS(___)

CRO LOS( )(22142)

5100

Don Helmets amp Gloves

XLUNAR - INJECT (verify)EDS PWR - on (venfy)EMS FUNC - OFF (verlfy)EMS MODE - STBYEMS FUNC - IW SETVHF RNGEMS MODE - NORMALSet ~V indo to +15868 fpsEMS FUMC - ~V Test

SPS THRUST Lt - onoff (10 sec)~V lnd stops at -01 to -415

EMS MODE - STBYEMS FUMC - ~V SETVHF RNGSet ~VC

EMS FUNC---~~V=----

GDC ALIGNFDAI Select - liZcb SECS LOGIC (Z) - close (verify)cb SECS ARM (Z) - closeSECS LOGIC (Z) - on (up)MSFN Conflrm GO for PYRO ARM (If pass)SECS PYRO ARM (Z) - on (up)TRANS CONTROL PWR - ONROT CONTR PWR NORMAL (Z) - ACDC(verlfy)ROT CONTR PWR DIRECT (Z) - MNAMNBLV INnGPI - SIISIVB (venfy)LV GUID - IU (venfy)cb DIRECT ULLAGE (Z) - closedSet EVENT TIMER to 5100Begin MONITOR For TB6

CMP to Couch

TB 6 - SII SEP Lt on (TIG-9 mln 38 sec)KEY V83E

SET ORDEALFDAI Z ORB RATE at 180 0 0SII SEP Lt out (38 sec later)Start DET COUNTING UPSC CaNT - SCS (verify)MONITOR LV TANK PRESS

~P lt 36 psid (OXID gt FUEL)~P lt Z6 psid (FUEL gt OXID)

EMERGENCY CSMLV SEP UP TLM CM - BLOCK (verify)UP TLM IU - BLOCK (venfy)

-53-

+45degPY))0middot sec PY

lOK nmltHAlt25K nm

Two phas~ng mnvrs two SPS mnvrs to circular~ze at 150 nmearth orb~t

CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ssion 4K nmltHAltlOK nm CSM amp1M - Two phasing mnvrs two SPS mnvrs to circularize at 150 nm earth orb~t CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ss~on

CSM amp 1M - Two phas~ng mnvrs APS burn todepletion th~rd phasing mnvrSPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn tosem~sync orb~t

25K nmltHAlt40K nm CSM amp 1M - Two phasmg mnvrs APS burn to depletion third phas~ng mnvr SPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn to sem~sync orbit HA)40K nm DPS ava~l - DPS LOll circularize with SPS

DPS not ava~l - Lunar flyby or CSM only to lunar orbit (if reqd gtV lt4000 fps)

V37E 47E (check b~as) Record -=--rshy(Limit 98 fpsmm)

( 1fps)tVXYZN62EVIHDOTHPAD (fpsfpslnm)MONITOR VI ( ) at ECO

SCS TVC SERVO PWR 1 - ACIMNA2 - OFF

TAPE RCDR - CMD RESETHBREMS MODE - NORMAL

SIr SEP Lt - ONTLI Inhib~t S~gnals w~11 not be honored after 5942

SIVB ULLAGE BeginsSII SEP Lt - off (TIG - 18 sec)SIVB FUEL LEADSIVB ULLAGE d~scont~nues

LV ENG I Lt - onSIVB IGNITION ( GETI)LV ENG I Lt - off - -shyMONITOR THRUST amp ATTITUDEMONITOR LV TANK PRESSSIVE ECO (Lt on) (BEGIN TB7)

EMER SIVE CUTOFF AT 6 SEC PAST BURN TIME IF VI ATTAINEDTHC CCW ampNEUTRAL IN 1 SEC or SIISIVB sW - LV STAGEPremature Shutdown HAlt4K nm CSM amp 1M -

5700

58205836

F 16 835800

F 16 62

5838594259525955595900000002SUNRISE(___)

HAW AOS(__=_) KEY VERB (freeze d~splay)

SIVB ATT HOLD 20 sec amp BEGIN VENTINGSIVB NNVR TO ORB RT (HDS DN) (3middot sec)

Record VI -c---HDOT _

HPAD _

KEY RLSEF 16 62

F 16 83

HAW LOS(__=-)

KEYmiddotRLSE~VXYZ (lfps)

Record ~VX---_

~vy

WZ--

AVC---_

TAPE RCDR - off (ctr)EMS MODE - STBYEMS FUNC - OFFSECS PYRO ARM (2) - SAFE

PRO

BURN STATUS REPORT

____--~TIG

BT------VGX____-R

-----P----_Y

REMARKS

_____VI

______--HDOT______--H______---AVC______---FUEL_______OXID

_______UNBAL

F 3708=00 OOEGOS AOS CMP TO LEB

(-=-=-)

0000

0003

0005

0014

0100

-55-

62 TLI 10 MIN ABORTSECS LOGIC (2) - on (up)SECS PYRO ARM (2) - ARM

TRANS CONTR - CGH (4 sec) amp +XDET RESET (verlfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS GMD-ON

TRANS GONTR - neutral then +X for10 sec

SIVBGPI s~ - GPIExcesslve rates 6V THRUST A - NORMAL SPS THRUST - DIRECT When rates damped 6V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

TRANS CONTR +X - OFFV37E OOE

PITGH UP to LOGAL VERT (+X axlSto~ard the earth)

RATE - LOWBMAG MODE (3) - ATTIRATE 2EDS PHR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SEGS ARM (2) - opencb EDS (3) - open

TRANS CONTR -X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (180deg)P (199deg)Y (0deg)

RETRO UPDATEGETI _

JV _VG

Jtb ---GET 400K _

05G _GET DROGUE _

ENTRY P _R _

Y_--

0945

-56-

ALIGN HORIZ ON RET +1 MKGMBL CHECK (T11lle Pentattlng)MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conflnn)cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FUMC - JV SETVHF RNGSET JV from chartE~S FUMC - JVEMS fODE - NOIDlAL

lV THRUST A - NORMALV37E 47E (THRUST fONITOR)

F 16 83 lVXYZ (1 fps)

0950

1000

NOTE For aborts durlng 1st mln of TLIKEY V82E F 16 44 (HaHpTff)Burn untll Hp lt 19NM

TRANS CONTR +X

THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN JV reqdJV THRUST (2) - OFFReport cutoff

cb SPS P2 Y2- closeGfBL MTRS (4) - OFF (LMP Confinn)TRANS CONT PWR - OFFTVC SERVO PWR (2) - OFFMN BUS TIE (2) - OFFcb SPS P1amp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREIf est time to EIltOl5500 omlt fCC andenter the SUPERCIRC CKLIST as early as pos-slb1e Pg ~2~3~ __If est time to EI)Ol5500 anticlpate afCC Enter the ENTRY PREP CKLIST at step 9pg 18

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

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DEGREES IN wiiiiDOW

260

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1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

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NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

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LUNAR RETURN VELOCITY

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-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 9: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

-6-

check for entry control If the FDAI pltch error does not decreaseto wlthln + 50 at 005g the PGNCS lS fa lied and the crew flies aconstant g-entry mode wlth EMS ranglng after the VelOClty decreaseto 25500 feet per second If the PGNCS lS acceptable the spaceshycraft control lS placed In CMC and the CMC mode lS placed ln autoshymatlc At 05g the EMS automatlcally starts lf the EMS mode sWltchwas posltloned to automatlc earller ThlS wlll be backed up manually3 seconds after the ground computed 05g tlme recorded on the entryPAD by placlng the EMS mode sWltch In manual lf lt has not startedautomatlcally At PGNCS 005g lndlcatlon the CMC program changesto P64 and from thls pOlnt the entry lS under entry DAP control

The lunar return entry nomlnally lS performed by the PGNCS to lnsurecontrol wlthln the overshoot and g llmlt llnes as well as optlmlzethe landlng point accuracy Although the hlgh speed entry lnvolvesa rapld sequency of events there are several monitorlng tasks forthe crew to determlne lf the automat~c contrails performlng correctly

An entry corr~dor ver~flcation check 1S made by observlng the lnltlalslope of the EMS V-g trace between 1 and 2 gs If the EMS lndlcatesthe need to reverse the LV orlentatlon and the lndependent g meterconflrms the EMS g lndlcatlon the SC lS immedlately orlented as aresult of the EMS ~nd~cat~on

The EMS g lnd~catlon ~s contlnuously checked durlng entry uSlng thelndependent g meter and the PGNCS g ~ndlcatlon as a thlrd voteDeC1Slons durlng the first entry (P64) are critlcal ln terms of bothexceSSlve g llnes and the PGNCS lS not commandlng (and SC respondlng)to correct the sltuatlon the PGNCS lS felled

The PGNCS gono go check for short range targets (1200-1400 n ml) forWhlCh P65 lS not used 1S d1fferent Slnce there are no CMC computedSk1p drag (DL) and skip velocity (VL) values The check uses the EMSscroll to determ1ne 1f the PGNCS lS commandlng the proper roll att1shytude to converge the EMS g level to a predetermlned PAD value (Do) ascomputed by MCC-H For the nom1nal target range of 1300 naut~cal

mlles the crew w1ll monltor the program change from P64 to P67 atapprox~matelyEI + 3 mlnutes For ranges greater than 1400 nauticalmlles the program w1ll transfer to the Upcontrol Program P65 whenVL ~s between 18000 and 25766 feet per second and constant drag hasbrought the CMC pred1cted range to wlthln 25 naut1cal m1les of thetarget range The P65 PGNCS gono go check cons1sts of determln1ng1pound both the DSKY d1splay of sk~pout drag (DL) and Sk1pout veloclty(VL) are w1thln the PAD llmlts In addltlon the EMS scroll lS mon1shytored to determ~ne lf the trace lS approach1ng the DL and VL values

Throughout entry the crew monltors the spacecraft response to the CMCroll commands by observlng the FDAI lndlcatlons If the commands are

-7-

apparently good and In agreement wlth the EMS but the spacecraftresponse is questlonable the crew manually takes over and fIlesthe CMC commands

If the Upcontrol Program P65 was entered the program wlll nomshylnally sWltch to the Flnal Entry Program P67 for target rangesbelow approxlmately 1800 nautlcal miles or to the Ballistlc Proshygram P66 for ranges greater than approxlmately 1800 nautlcalffilles The program transfer crlterla are more preclsely deflnedIn reference 1

If P66 lS entered the spacecraft lS automatlcally rolled to theIlftup heads-down attltude to permlt the horlzon to be vlewedfrom the wlndow durlng the second entry The entry attltude checklS made by comparlng the horlzon wlth a speclfled wlndow mark Ifthe check falls the crew manually malntalns the entry trlffi attltudeuSlng the horizon VleW for reference The EMS lS used for ranglngSlnce the veloclty has now decreased to below 25500 feet per second

The EMS scroll lS contlnuously used to monltor for exceSSlve g conshydltlons durlng the second entry If the EMS V-g trace vlolates theg Ilnes and the PGNCS lS not commandlng (and spacecraft respondlng)to correct the situatlon the PGNCS lS falled and the EMS lS usedfor ranglng after ltS g lndlcatlon has been conflrmed by the lndeshypendent g meter

The entry phase lS essentlally over when the relatlve veloclty ofthe spacecraft decreases to less than 1000 feet per second ThlSlS lndlcated In P67 when RTGO latltude and longltude are dlsplayedSlnce very Ilttle ranglng capablllty exists after thls pOlnt thespacecraft lS orlented elther full Ilft up or down dependlng on RTGOnegatlve or posltlve and the crew prepares for the earth landlngphase

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-13-

40 EARTH ORBITAL DEORBIT AND ENTRY TECHNIQUES

As outl~ned ~n reference 5 a nom~nal PGNCS entry from earth orb~t ~s

based on a preparat~on t~me of 2 hours and 40 m~nutes ~nclud~ng 2n~ght passes Th~s t~me ~ncludes approx~mately 20 minutes before thef~rst n~ght pass after the CMC update and PAD data have been rece2vedTh~s t~e also 2ncludes approx2mately 20 m2nutes after the secondn~ght pass to allow suffic~ent t2me to prepare for retrof2re after theIMU f2ne a12gnment It has been determ2ned coarse a12gnment accuracy~s adequate for retrof~re and entry and undoubtedly other funct20nscould be om2tted depend2ng on the c2rcumstances for the dec2s20n toreenter Descr2bed here2n are the nom2nal earth oro2tal entry proshycedures w2th pert2nent comments on system va12dat20n for real timeacceptance dec~s20ns

After the entry dec~s~on is made the crew transfers the PGNCS fromthe standby to the operate mode and rece~ves a CMe update w~th P27Next the maneuver PAD update ~s v02ced up and the 2n~t~al entry mode~s determ~ned During the ~n~tial n~ght pass the IMU or2entat~on ~s

estab12shed uS2ng P51 star s~ght2ngs to obta2n a REFSMMAT The preshyferred or~entat~on opt20n ~n P52 2S then selected to coarse a12gn theIMU uS2ng the des2red entry REFSMMAT determ2ned by MGG-H The GOO ~s

now al~gned to the IMU 2n preparat~on for an IMUSes dr~ft check Ifthe GOO ~nd~cates the ses dr2ft rate exceeds 10 degrees per hour ~n

any ax~s the check ~s repeated on the other BMAGs to estaol~sh if theGOO or Just the single set 2S unusuable Var20us sytem checks as 12sted2n sect20n 51 are performed as necessary cons2stent w2th the t2me12ned2ctates of the maJor act2v2t2es Included 2n these checks are the EMSself-tests and the dV counter test The latter requ2res the spacecraftbe placed ~n dr2ft2ng fl2ght w~th the funct20n sW2tch 2n the dV pos2t~on

If the counter reg2sters a change of more than 25 feet per second w2th2n100 seconds the scroll and counter are unre12able for mon2tor2ng thedeorb2t burn and entry rang2ng If the EMS self-test fails and t2medoes not allow further analysis a 5555 ERE entry 1S planned as thePGNGS backup entry mode After complet2on of these checks the entryPAD lS prov1ded by MeG-H The crew then selects the external dVprogram P30 and the appropr2ate deorb1t tbrust1ng program p40 or P41Dur2ng th2s per2od wh2ch 2ncludes the f1nal n2ght pass P52 may beselected to ver2fy the IMU a12gnment Since the retro att2tude hasbeen computed so that a w2ndow mark c01nc2des w2th the hor2zon atGETI th2s serves as the conclus2ve check on the PGNCS At 5 m2nutesbefore retrofire the att2tude check 1S made by ver1fY2ng that the 12degree scr~be 12ne ~s w2th2n 3 degrees of the hor2zon If not thePGNeS has fa2led and the ses 2S used for att2tude reference and the

V counter for burn durat~on control S2nce the ses att~tude wasa12gned to the IMU a real~gnment ~s necessary This ~s accompl~shed

by manually maneuver2ng the spacecraft to ma~nta1n the 24 degree wlodowmark on the hor2zon and releas1ng the GOO a12gn button at TIG - 2 m2nutes

-14-

Upon complet~on of the burn the tN res~duals are burned to W~th~n

02 feet per second If the PGNCS ~V counter or est~mated burnduration are ~n d~sagreement ~t must be estab1~shed whether suff~shy

c~ent veloc~ty has been suppl~ed to put the land~ng po~nt in thefootpr~nt The PGNCS data w~ll be used ~f ~t ~s conf~rmed by oneother source if not the ~V counter w~11 be used ~f ~t ~s conf~rmed

by the burn durat~on t~me If add~tional ~V ~s necessary the data~s ava~lable to the crew on an onboard chart found ~n Sect~on 80

Post burn entry preparat~on requ~res EMS ~n~t~al~zation RSI al~gnshy

ment and pre-separat~on funct~ons The crew then selects the ~n~t~al

entry program P61 and records the d~sp1ays as a check aga~nst PADdata Upon complet~on of these checks P62 ~s entered The crewmanually or~ents the spacecraft to the separat~on attitude and yaws450 to ~nsure aga~nst possible CM 8M recontact After separat~on

the spacecraft ~s maneuvered to the reentry tr~m att~tude wh~ch

places the hor~zon on the 3170 w~ndow mark at EI Shortly thereshyafter ~n P62 the entry DAP is act~vated and P63 in~t~ated Dur~ng

th~s t~e MCC-H has computed a postburn update and ~t ~s vo~ced tothe crew ~f d~fferent from preburn values The EMS scroll and rangecounter w~ll be adJusted accord~ngly ~f t~me perm~ts A f~nal PGNCScheck pr~or to 05g may be mon~tored at th~s t~e w~th the CMC modein free and the manual att~tude p~tch ~n acceleration command wh~le

the hor~zon reference ~s held the p~tch error needle w~ll decreaseto zero as EI ~s reached At RET 005g the EMS mode sw~tch ~s

turned to manual the entry 005-g sw~tch and EMS roll sw~tch areturned on and the spacecraft control sw~tched to CMC to beg~n DAPcontrol At the PGNCS 005-g ~ndicatwn the program change fromP63 to P64 ~s mon~tored and the t~e vo~ce recorded At th~s t~me

the EMS range counter check ~s made dur~ng the 10 second per~od

follow~ng EMS 005g Dur~ng th~s per~od the counter should countdown 40 + 10 naut~cal m~les At PGNCS 02-g ~nd~cation the changefrom P64-to P67 ~s monitored and the ~splay may be held by key~ngVERB ~n order to record the init~al downrange error d~splay andcompare ~t to the PAD value The PGNCS has fa~led ~f the two do notagree w~th~n + 100 naut~cal m~les In the event P67 has not appearedwhen both the-g-meter and the scroll ~nd~cate greater than 05g thePGNCS has sim~lar~ly fa~led In e~ther fa~lure the SCS is used foratt~tude reference w~th an EMS entry If the checks agree the crewrema~ns w~th automat~c DAP for the rema~nder of the entry

The entry phase ~s essentially over when the relat~ve velocity ofthe spacecraft decreases to less than 1000 feet per second Th~s

~s ~nd~cated ~n P67 when RTGO lat~tude and long~tude are d~splayed

S~nce very l~ttle rang~ng capab~l~ty exists after th~s pOint thespacecraft is or~ented either full l~ft up or down depending onRTGO negat~ve or pos~t~ve and the crew prepares for the earth land~ng

phase

-15-

41 TYP~cal Retrof~re and Entry Sequence of Events

Dec~s~on to reenter

P27 (CMC update)

Retrof~re PAD update

Entry mode dec~s~on

P51 (IMU or~entat~on determlnatlon) durlng f~rst dark per~od

P52 (IMU coarse allgnment)

EMS checks

Entry PAD update

P30 (external AV)

p40 (SPS thrust)

P52 (IMU f~ne al~gnment) durlng second dark per~od

p40 (SPS thrust)

Ign~t~on att~tude check

Retroflre

P61

P62

CMSM separat~on

P63

Postburn PAD update

Entry attltude check

p64 (beg~n DAP control at O05g)

P67 (PGNCS gono go check at O2g)

42

Retrof~re

and

En

try

Alt

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atlv

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Sys

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fa~lure

PGNC

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PGNC

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Fal

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Fal

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aft

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-17-

5 0 DETAILED ENTRY PROCEDURES

In order to comblne slmilar procedures that are common to lunar returnentrles and earth orblt entrles the followlng procedures are dlvldedlnto categorles that allow a mlnlmum of dupllClty ThlS provldes asmaller tralnlng package and more closely resembles the onboard crewcheckllst when comparlson lS necessary

51 Entry Preparatlons for Superclucular and Earth Orbltal Entrles

1~e entry preparatlons are comblned In these procedures andsteps pecullar to elther superclrcular or earth orbltal entrlesare labeled accordlngly The tlme llstlngs In thlS sectlon areappllcable to only superclrcular entries Slnce the earth orbltalentry tlmellne lS a functlon of several varlables as descrlbedIn sectlon 40 and reference 5

-18-51 (Contlnued)

VEHICLE PREPARATION

l-

2

3

4

5

6 -0600h

7 -0535h

8

9

10 -0430h

INITIAL STOWAGE COMPLETED

CMC amp ISS START UP

SCS POWER UP

p51 - IMU ORIENTATION

LOAD DAPV48E 11102 01111 PRO ERO PRO

LAST MCC DECISION

NO COMM - P52 amp NAV SIGHTINGSNOMINAL - P2337 ONBOARD COMPARISON

DON MAE WESTS amp FOOT RESTRAINTS

VHF AM A - SIMPLEX

P 27 (SV REFSMMAT) MNVRamp ENTRY pAD UPDATES

11 -0415h P52 - IMU REALIGN(___) (OPTION 1)

12 P37 (NO COMM ONLY)

13

14

ECS CKS02 SUPPLY REFILLECS Monitor CkEVAP H20 CONT (2) vlvs - AUTOSUIT HEAT EXCH SEC GLY - FLOW

EPS CKS 1 3 4 (5 If reqd)

15 SPS CK (If req d)

16

17

18

RCS CKSSM RCS MOUlt CkCM RCS MOUlt Ck

CampW SYS CK

CMC SELF CK

19

20 -0345h

-03l5h-0300h

21

22

22A

-19-

DSKY COND LT TEST

MIDCOURSE MANEUVERP30 - EXT rVP404l - SPSRCS THRUSTINGMIDCOURSE (17) BURN

NO COMM NAV SIGHTINGS

ffiVR TO ENTRY ATT (Superc1rc only)V62E

V49E

22B F 06 22 DESIRED FINAL GMBL ANGLESLOAD ENTRY ATT PAD ANGLESPRO

22C F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) SC CONT - CMC

BMAG MODE (3) - RATE 2CMC MODE - AUTO

PRO(~N) SC CONT - SCS

MNVR to 22E

22D 06 18 AUTO MNVR TO FDAI RPY ANGLES

22E F 50 18 REQUEST TRIM(TRIM) Go to 22C(BYPASS) ENTR

23 -200hr BORESIGHT amp SXT STAR CHECKOPT MODE - CMCOPT ZERO - OFF

V41 N91E

F 21 92 SHAFT TRUNLoad SXTS angles

41 OPTICS DRIVE

CHECK SXT STAROPT ZERO - ZERO

CHECK BORESIGHT STAR (If ava11)

24 -0135h

25(___)

26

27 -0115h

-20-

P52 - lMU REALIGNRecord gyro torqu~ng anglesRp~----

YIf-7gt-Lno--re-c-ycle PS2If conflrmed use SCS for EMS entry

GDC ALIGNIf drlft gtLOohr change ratesource

FINAL STOWAGEOPTICS (except for hybrid)ORDEALGLY TO RAD SEC - BYPASS (verlfy)CooL pnl lnstalledY-Y struts (2) extendedStow Data Box R-12

EMS CHECKEMS FUNC - OFFcb EMS (2) - closeEMS MODE - STBYEMS FUNC - EMS TEST 1 (walt 5 sec)EMS MODE - NORMAL (walt 10 sec)

Check ind lts - offRANGE lnd - 00Slew halr1ine over notch

In self-test patternEMS FUNC - EMS TEST 2 (walt 10 sec)

05G It - on (all others out)EMS FUNC - EMS TEST 3

05G It - onRSI Lower It - on (10 sec Qater)Set RANGE counter to 58 nm+OO

EMS FUNC - EMS TEST 405G It - on (all others out)G-V trace w~thin pattern to lwr rt

corner 9GRANGE lnd counts down to 0+02

EMS FUNC - EMS TEST 505G It - onRSI upper lt - on (10 sec later)RANGE md - 00SCrlbe traces vertlcal llne 9g to

022+01ALIGN SCROLL TO ENTRY PATTERN (on

37K ft sec hne)EMS FUNC - RNG SET

G-V scroll assy traces vert llne022g to 0+01

EMS MODE - STBY

28

29

30 -OllOh

-21-

~V TEST (Deorb~t only)EMS FUNC - ~V SETVHF RNGSET ~V ~nd to 15868 fpsEMS MODE - NORMALEMS FUNC - ~V TEST

SPS THRUST LT - onoff (10 sec)~V ~nd stops at -01 to -415

EMS MODE - STBY

PRIMARY WATER EVAP ACTIVATIONGLY EVAP H20 FLOW - AUTOGLY EVAP STH PRESS - AUTOPRI ECS GLY PUMP - ACI

CM RCS PREHEATNote If sys test mtr 5cd6abcd

all read 39 vdc (28degF) or moreom~t preheat

cb RCS LOGIC (2) - closeCM RCS LOGIC - ONUP T1M CM - BLOCK (ver~fy)

cb CM RCS HTRS (2) - closeCM RCS HTRS - ON (LMP Conf~rm)

(20 mlU or III lowest rdg lS39 vdc) (Moultor Maufpress for press drop)

31 (___) FINAL GDC DRIFT CK (If req I d)If drlft gtlOohr Suspect GDC Do not

use RSI amp FDAI 2

32 -OO5Om

33

34

35

TERM CM RCS PREHEATUP TLM CM - BLOCK (venfy)CM RCS HTRS - OFFCM RCS LOGIC - OFF

SYSTEMS TEST PANEL CONFIGURATIONSYS TEST METER - 4BRNDZ XPNDR - OPERATECM RCS HTRS - OFFWASTE H20 DUMP - OFFURINE DUMP - OFF

LEB LIGHTING - OFF

SEC WATER EVAP ACTIVATIONGLY To RAD SEC vlv - BYPASSSEC COOL EVAP - EVAPSEC COOL PUMP - AC2

36

37

38 -OO45m

-22-

PYRO BATT CKcb PYRO A SEQ A - close (ver~fy)

cb PRYO B SEQ B - close (verify)DC IND - PYRO BAT A(B)

~If PYRO BAT A(B) lt 35 vdc cb PYRO A(B) seq A(B) - open~

PYRO A(B)BAT BUS A(B)TO PYRO~MN BUS TIE - close

cb MNA BAT C - closecb MNB BAT C - closeDC IND - MNBPNL 8 - All cbs closed except

PL VENT - open (ver~fy)

FLOAT BAG (3) - open (ver~fy)

DOCKING PROBE (2) - open (verlfy)EDS BAT (3) - open (ver~fy)

CM ReS HTRS (2) - open

CM RCS ACTIVATIONcb SECS ARM (2) - close (verlfy)cb SECS LOGIC (2) - close (verlfy)SECS LOGIC (2) - ONMSFN conflrm GO for PYRO ARM(~f poss)SECS PYRO ARM (2) - ARMCM RCS PRPLNT 1amp2 - ONCM RCS PRESS - ONRCS Ind sw - eMl then 2

He PRESS 3700-4400 pSlaMANF PRESS 287-302 pSla

SECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFF

P27 amp ENTRY PAD UPDATEGo To Entry Checkllst

Superclrc - pg ~2~3 _Hybnd - pg -----2~9L-__Normal Deorblt - pg __3L5L- _

-23-

52 SUPERCIRCULAR ENTRY

1 SET DET (up to ET)

2

3

4

5

3000(-30-00)

EMS INITIALIZATIONSET RNG TO PAD DATA RNGEMS FUNC - Vo SETSlew Scroll to Pad Data VIOEMS FUNC - ENTRY

RS I ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on (up)GDC ALIGN PB - PUSH amp HOLDYAW Tw - Pos~t~on RSI thru

45deg amp back to LIFT UPGDC ALIGN PB - ReleaseEMS ROLL - OFFA1~gn CDC to lMU

CM RCS RING A CKRCS TRNFR - CMcb CM RCS LOGIC MNB - openAUTO RCS SEL MNB (6) - OFFSC CONT - SCSTest R~ng A ThrustersSC CONT - CMCRCS TRNFR - SMAUTO RCS SEL (12) - MNAMNB

(hftoff conflg)cb CM RCS LOGIC MNB - close

OPTICS PWR - OFFCMP to COUCH

MN BUS TIE (2) - ONTAPE RCDR - REWIND

6 35middot0Om(-25middot 00)

-24-

SEPARATION CK LISTTVC SERVO PWR 1 - AClMNAcb ELS (2) - close (ver1fy)PRIM GLY TO RAn - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY vlv - OFFCAB PRESS REL vlv (2) - NORMGMBL MTRS (4) - STARTABORT SYS PRPLNT - RCS CMD (venfy)SM RCS PRIM PRPLNT (4) - ONVHF 11M (AampB) - OFFHI GAIN ANT PWR - OFFFC PUMPS (3) - OFFVer1fy s1ugle SU1t compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - 10101cb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2) - opencb HTRS OVLD (2) - openPOT H20 RTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANSEC COOL EVAP - RESETSEC COOL PUMP - off (etr)

MtiVR TO CMSM SEP P R ATTSC CONT - SCSCMC MODE - FREEMNVR TO PAD ATTR (0deg)PY----W)

-25-

SUPERCIRCULAR ENTRY (Cont~nued)

1

4100m(-1900)

P61 - ENTRY PREP

V37E 61E

k 05 09 01427 - ROLL REVERSED 05 09 01426 - IMU UNSAT ~

2 F 06 61 IMPACT LAT LONG HDS UPDN (+-)PRO (010

fps +00001)

3 F 06 60 GMAXVPREDGAMMA EIRecord

GMAXV400K----

GAMMA EI _PRO

(01deg fpsOldeg)

4 F 06 63 RTOGO (lnm) PAD _VIO (fps) PAD _TFE(m~n-sec)

Compare w~th ~M~SFN==C~f~o-r~P~GNS GONO GOIf NO COMM Set RTOGO amp VIO In EMS

amp lnltla11ze(ACCEPT) PRO(RECALC) V32E To 4

5 F 50 25

4300m

(-1700)

45 oOm(-1500)

500Om(-1000)

6 F 06 61

-26-

P62 - CMSM SEP amp PRE-ENTRY MNVRCAUTION Call No EXT Verbs In P62

00041 REQUEST CMSM SEPSC CONT - SCSFREE

COMPARE PITCH ATT WITH PAD DATA ---0=-

(W~thLU 5deg)YAW - 45deg OUT-OF-PLANE (LEFT)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTIRATE 2MN BUS TIE (2) - ON (ver~fy)

PRIM GLY TO RAD - BYPASS (verlfy)CM RCS LOGIC - ON (venfy)SECS LOGIC (2) - on (up)SECS PYRO ARM - ARMCMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 ps~a

CM RCS LOGIC - OFFSECS PYRO ARM (2) - SAFEMonltor VMAB

If lt25 vdc go to EMERGPOWERDOWN pg E6-l

AUTO RCS SEL AC ROLL (4) - OFFAUTO RCS SEL CM 2(6)-OFFAUTO RCS SEL CM 1(6)-MNAYAW back to 0degPITCH TO HORIZ TRACK ATT

ROLL - 0deg (LIFT UP)PITCH - 400K Horiz Mark (317deg)YAW - 0deg

ATT DB - MAXMAN ATT PITCH - ACCEL CMDEMS DATA - Ver~fy

EMS FliNC - ENTRY (ver~fy)

EMS MODE - NORMALcb SPS PampY (4) - openMAINT HORIZ TRK

PRO (Act ENTRY DAP)

IMPACT LATLONGHDSDN (01deg01deg-00001)PRO

7 POSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axis beyond 45deg of Vel vector)

8 06 64

58middot00m(-0200)

9

05G tlme(+0 )

(--=---)

06 68

-27-

P63 - ENTRY INIT

GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PIJR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRmDHORIZ CKPltch error needle goes toward

zero approachlng OSG tlmeMAN ATT (PITCH) - RATE CMD

If CMC lS GOBMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS I

FLY BETA If CMC NO GO ilt

1 SC CaNT - SCS I

FLY EMS k

p64 - ENTRY POST 05G

RTOGO AT 05G AGREES HITH EMS-venfyHORIZ CK05G Lt - ON (EMS START)

No EMS START wlthln 3 sec ~ EMS MODE - BACKUP VHF RNG c

05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds Llft DN

NNVR Llft DNEMS GONO GO

G-V Plot wlthln IlmltsRng ctr dwn 60plusmn7 durlng 10 sec

perlodMonltor G-meter for

convergence wlth pad data (Do)(Vlt27K fps) Go to 13

-28-

P65 - ENTRY - UP CONT (Vgt27K fps)

10 F 16 69 BETA (01middot) _DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT lt~ SC CONT - SCS FLY EMS

PRO

11 06 68 BETAVIHDOT (OIdegfpsfps)(VltV1+500 fps amp RnOT Neg) Go To 13

P66 - ENTRY - BALLISTIC (D(DL)

12 06 22 DESIRED GMBL ANGLES RPYMoultor horlz +12middot of 317middot mark

P67 - ENTRY - FINAL PHASE (02G)

13 06 66 BETACRSRNG ERRDNRNG ERR(010 1um 1um)

KEY VERBRecord DNRNG ERR _KEY RLSEMoultor l~ft vector ou RSI amp FDAI

16 67 RTOGOLATLONG (Vrel=1000fps)(lumOldegOldeg)

SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOWNMonitor a1t~meter

Go To EARTHLANDING pg ---4L5 _

-29-

53 GampN HYBRID DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL tV1 V37E 30E

2 F 06 33 GETI(ACCEPT) PRO (hrm~n Olsec)(REJECT) LOAD DESIRED GETI

3 F 06 81 tVXYZ (LV) (lfps)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

4 F 06 42 HAHPtV (lnm lfps)Record tV

(ACCEPT) PRO(REJECT) Reselect P30 or P27 Load new paramo

5 F 16 45 MTFIMGA (marksm~n-secOlO)

MGA -00002 ~f k

k lMU not al~gned

SET DETPRO

6

7

8

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (Pull)PLSS 02 vlv - FILL02 8M SUPPLY vlv - OFFCAB PRESS REL vlv (2) - NORMcb ELS (2) - closecb SECS ARM (2) - closecb SECS LOGIC (2) - close (ver~fy)

AUTO RCS SEL CM (12) - MNA or ~ffiB

(hftoff conhg)ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM (AampB) - OFF

CMP to Couch

9

10

11

-30-

MNVR TO PAD BURN ATTLOAD DAPBMAG MODE (3) - RATE 2SC CONT - CMCAUTOATT DB - MINMAN ATT (3) - RATE CMD

v62E

v49E

12 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLES

PRO

13 F 50 18 REQ MNVR TO FDAI RPY ANGLES (01deg)(AUTO) PRO(MAN) SC CONT - SCS

BMAG MODE (3) - RATE 2MNVR To 15

14 06 18 AUTO MNVR TO FDAI RPY ANGLES (01deg)

15 F 50 18 REQ TRIM TO FDAI RPY ANGLES (01deg)(TRIM) Go to 13(ByPASS) ENTR

16

17

CHECK BORESIGHT amp SKT STARSOPT MODE - CMCOPT ZERO - OFF

v41 N91E

18 F 21 92 SHAFTTRUN (01deg 001deg)Load SXTS angles

19 41 OPTICS DRIVECheck SKT STAR

OPT ZERO - ZEROCheck BORESIGHT STAR (~f ava~l)

20 V25 N17E (01deg)Load Pad Data GMBL Angles

for CM BURN ATTATT SETtw - SET

to PAD DATA GMBL ANGLESfor CM BURN ATT

21

22

-31-

PHR REDUCTIONHGA PHR - OFFFC PUMPS (3) - OFFVerify s~ngle su~t compr oper loads

balancedFC 2 MN AampB - OFFS BD PiR AMP - LOWcb ECS RAD CONTHTR (2) - opencb HASTE H20URINE DUMP HTRS(2)- opencb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANMN BUS TIE (2) - ONTVC SERVO PHR 1 - AC1MNAGMBL MTR (4) - START

p41 - RCS THRUSTINGV37E 41E

23 F 50 18 REQ MNVR TO LCL HORIZ (HDS ON)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CMCAUTOPRO To 24

(gtfANDAP) BMAG MODE (3) - RATE 2SC CONT - CMCHOLD

V62EMNVR To 25

24 06 18 AUTO MNVR TO FDAI RPY

25 F 50 18 REQ TRIM TO LCL HORIZ (01deg)ALIGN SC ROLL

(AUTO TRIM) PRO To 24(BYPASS) ATT DB - MIN

RATE - LOHMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTlRATE 2

ENTR

550Om26 06 85

59middot2527

-32-

VGXYZ (1fps)RECHECK BORESIGHT STARTRANS CONIR PWR - on (up)EMS MODE - STBY (ver~fy)

EMS FliNC - bV SETVHF RNGSET (IV for SM BURN _EMS FliNC - bVS BD ANT - OMNI CSECS LOGIC (2) - ONMSFN conhrm Go for PYRO ARMSECS PYRO ARM (2) - ARMCM RCS LOGIC - ON (ver~fy)

DSKY BLANKS

593028 16 85 VG XYZ (AVE G ON) (lfps)

RHCs amp THC - ARMEDLIMIT CYCLE - OFFTAPE RCDR - CMD RESETHBREMS MODE - NORMAL

000029 F 16 85 REQ NULL VG XYZ (lfps)

BURN EMS bV CTR TO ZERORESET DET amp COUNT UP

If SM ONLY burn go to step 32THC - LOCKEDSC CaNT - SCSFREERATE - HIGHPRIM GLY To RAD - BYPASS (ver~fy)

MN BUS TIE (2) - ON (ver~fy)

CMSM SEP (2) - on (up)CSMLM FNL SEP (2) - on (up) (verify)CampW MODE - CMRCS TRNFR - CMCM RCS LOGIC - OFF

Momtor VM ABIf lt25 vdc go to EMERGPOWER DOWN Pg E6-l

V63E

If CMC NO GO FDAI SOURCE - ATT FDAI SEL - 1 or 2 ATT SET - GDC

SET

-33-

~Uili ATT PITCH - ACCEL CMDFDAI SCALE - 55MNVR TO CM BURN ATT (NULL ERR NEEDLES)

R 0degPY --00--

30

31

CM RCS BURNRHC III-ContJnuous PJtch DownRHC HZ-Module PJtch to null needlesBURN VGZ TO ZERO

If only 1 RHC Pulse + P=5deg from retro att MaJnta~n rates lt3degsec

BURN COMPLETION ATllV CTR= or DET= _

V8ZE

32 F 16 44 HAHPTFF (1nmffiJn-sec)Check HP-

If gt Pad data contJnue burnuntJ1 lt Pad

PRO

33 F 16 85 VGXYZ (Ups)Read VG resJduals to MSFN

(HYBRID) PRO to 34(SM ONLY BURN)

PROF 37 ODE

EI-1500 V37E 47EF 16 83 twx Y Z (Ups)

SC CONT - SCSFREEMAN ATT (PITCH) - RATE CMDRATE - HIGHPRIM GLY To RAD - BYPASS (verJfy)MN BUS TIE (2) - ON (verJfy)CMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verJfy)Campl MODE - CMRCS TRNFR - CMCM ReS LOGIC - OFFSECS PYRO ~I (2) - SAFE

-34-

PROMonitor VMAB

If lt25 vdc go to EMERGPOWER DOWN

34 F 37 OOEPCM BIT RATE - LOWATT DB - MAXEMS MODE - STBYEMS FUNC - OFF

Go To EARTH ORBIT ENTRY pg _--40-__

-36-

8 SPS THRUSTING PREPCYCLE CRYO FANSSPS GAGING - ACI (ver~fy)

PUG MODE - NORM (venfy)BMAG MODE (3) - RATE 2tv CG - CSMCMC MODE - FREEAUTO RCS SEL (16) - MNA or HNB

(hftoff conbg)SC CONT - CMCAUTO

9 MNVR TO PAD BURN ATTV62E

10 V49E

11 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLESPRO

12 F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) PRO(HAN) SC CONT - ses

MNVR to 14

06 18 AUTO MNVR TO FDAI RPY ANGLES13

14 F 50 18 REO TRIH TO FDAI RPY ANGLES(TRIM) Go to 12(BYPASS) ENTR

15 BORESIGHT STAR CHECK

16 V37E 40EOPT PWR - OFF

17 F 50 18 REQUEST MNVR TO FDAI RPY ANGLES (01deg)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CHCAUTOPRO to 18

(MANDAP) BMAG HODE (3) - RATE 2SC CONT - CMCHOLDMNVR to 19

(HANseS) se eONT - sesMNVR to 19

-35-

54 NORMAL DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL ~V

1 V37E 30E

2 F 06 33 GETI (hrm~nOlsec)

(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

3 F 06 81 ~VXYZ (LV)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

( lfps)

4 F 06 42 HAHP~V (1nmlfps)Record W

(ACCEPT) PRO -----(REJECT) Rese1ect P30 or P27 Load new pa~am

5 F 16 45 MTFIMGA (marksmln-secOldeg)MGA -00002 If ~ lMU not a1~gned

SET DETPRO

6

7

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY v1v - OFFCAB PRESS REL v1v (2) - NORMcb ELS (2) - close (verify)cb SECS ARM (2) - close (ver~fy)

cb SECS LOGIC (2) - close (verlfy)AUTO RCS SEL CM (12) - ~mA or MNB

(l~ftoff conf~g)

ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM AampB - off (ctr)

18

-37-

06 18 AUTO MNVR TO FDAI RPY ANGLES (01 0)

19 l 50 18 REOUEST TRIM MNVR TOALIGN SIC ROLLGDC ALIGN

FDAI RPY ANGLES(010

)

+54-00m(-06-00)

TIG-5mJn

5500m(-0500)

TVC CHECK amp PREPcb STAB CONT SYS (all) - closecb SPS (12) - closeATT DB - MINRATE - LOl~

LIMIT CYCLE - ONMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE 2ROT CONTR PWR DIRECT (2) - OFFSCS TVC (2) - RATE CMD

If SCS SCS TVC (2) - AUTO SC CONT - SCS ~

TVC GMBL DRIVE PampY - AUTOMN BUS TIE (2) - ONTVC SERVO PWR 1 - AC1MNA

2 - AC2MNBTRANS CONTR PWR - ONROT CONTR PWR NORMAL 2 - ACRHC 2 - ARMED

HORIZ CHK - HorJz on 12deg wJndmlmark (LJffiJt +3 0 PNGCS GONO GO)

If NO GO set tw 180 0 180deg0 0

Track horJz wJth 24deg wJndow markAt TIG-2 mJn Ahgn GDC

PRIMARY TVC CHECKGMBL MOT P1-Y1 -STARTON(LMP confJrm)

If SCS verJfy Thumbwheel TrJmTHC - CWVenfy NO MTVC

SEC TVC CHECKGHBL MOT P2-Y2 -STARTON(LMP confJrm)SET GPI TRIHVenfy MTVCTHC NEUTRALGPI returns to 00 (CMC) or trJm (SCS)ROT CONT Pl~ NORM 2 - ACDC

(TRIM) Go to step 17(BYPASS) BMAG MODE(3) - ATTIRATE2 (ver1fy)

ENTR

-38-

20 F SO 25 00204 GMBL TEST OPTION(ACCEPT) SC CONT - GMC (ver~fy)

PROMonitor GPI Response

0020-2000020-200Tr~m

TEST FAIL SC CONT - SCS SCS TVC (2) - AUTO

(REJECT) ENTR

21 06 40 TFIVG~VM (m~n-sec1fps)

PROG ALM - TIG s1~pped

V5N9E 01703

KEY RLSE To 21 ROT CONTR PWR DIRECT (2) - MNABSPS He v1vs (2) - AUTO (ver~fy)

LIMIT CYCLE - OFFFDAI SCALE - SOIScb SPS P2Y2 - open (for cr~t burn)

5800(-02 00)

5925(-0035)

59middot 30(-0030)

06 40

59XX(-OOXX)

AV THRUST A(B) - NORMALTHC - ARMEDRlIC (2) - ARMEDTAPE RCDR - GID RESETHBR

DSKY BLANKS

(AVE G ON)EMS MODE - NORMAL

TFIVG~VM (m~n-seclfps)

CHECK PIPA BIAS lt2fps for 5 sec

ULLAGE AS REQ

IF NO ULLAGE DIR ULLAGE PB - PUSH~

CONTROL ATT WRlIC MONITOR AVM (R3) COUNTING UP

5955(-0005)

F 99 40 ENG ON ENABLE REQUEST(AUTO IGN) PRO AT TFI gt0 sec(BYPASS IGN) ENTR to 24

22 0000 IGN

-39-

If SCS - THRUST ON PB - PUSH

06 40 TFCVG~VM (m~n-seclfpslfps)

~F 97 40 SPS Thrust fall ~

~(RESTART) PRO To IGN (RECYCLE) ENTR To TIG-05 sec

SPS THRUST LITE - ONMONITOR THRUSTING

Pc 95-105 pSlaEMS COUNTING DOWNSPS IN3 v1vs (4) - OPENSPS He v1vs tb (2) - graySPS FUELOXID PRESS - 175-195 pSlaPUGS - BALANCED

PROG ALARM V5N9E 01407 VG INCTHC - CW FLY MTVC

ECOEMER SPS CUTOFF J

AV THRUST (2) - OFF

23 F 16 40 TFC(STATIC)VG~VM (mln-seclfps)~V THRUST AB - OFF

SPS IN3 v1vs (4) - CLOSEDSPS He tb (2) - bp

cb SPS P2Y2 - closed (verlfy)TVC SERVO PHR - AC1MNA (venfy)TVC SERVO PWR 2 - OFF

PRO

24 F 16 85 VG XYZ(CM) CUps)NULL RESIDUALSRECORD ~V CTR amp RESIDUALS I1VCEMS FUNC - OFF VGXEMS MODE - STBY VGYBMAG MODE (3) - RATE 2ATT DB - MAX VGZTRANS CONT PHR - OFF

PRO

25 F 37 V82E

26 F 16 44 HAHPTFF (lnmm~n-sec)

R3-59B59 HP gt494 nmPRO

27 F 37 OOE

-40-

55 EARTH ORBIT ENTRY

1 Venfy CMSMR __

P_shyY_-

SEP ATT(180deg)

(0deg )

2

3

4

EMS INITIALIZATIONEMS FUNC - RNG SETSET RNG TO PAD DATA RNGEMS FUNC - VA SETSlew scroll to pad data VIOEMS FUNC - ENTRY

RSI ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on(up)GDC ALIGN PB - PUSH amp HOLDYAW tw - Pos1tion RSI thru 45deg amp

back to LIFl UPGDC ALIGN PB - RELEASEEMS ROLL - OFFAl1gn GDC to lMU

PWR REDUCT (Norm Deorb Only)HGA PWR - OFFFC PUMPS (3) - OFFVer1fy s1ngle suit compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - Lowcb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2)-openlOb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MAN

-41-

P61 - ENTRY PREP

5 V37E 61E05 09 01427 - ROLL REVERSED05 09 01426 - IMU UNSAT

6 F 06 61 IMPACT LAT LONG liDS UPDN (+-)(01 0

010

+00001)

PRO

PAD VALUESLATLON==G------liDS UP DN _

7 F 06 60 GMAXV400KGAMMA EIRecord

GMAXV400K----GAMMA EI _

PRO

8 F 06 63 RTOGO (1nm) PAD _VIa (fps) PADTFE (mln-sec) ----Compare wlth MSFN for PGNS GONO GONO COMM SET RTOGO amp VIO IN EMS amp

INITIALIZE(ACCEPT) PRO(RECALC) V32E to 8

-42-

P62 - CMSM SEP amp PRE-ENTRY MNVR

9 F 50 25 00041 REQUEST CMSM SEPSC CONT - SCSFREEYAW - 45deg out-of-plane (left for RCS

nght for SPS)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE2PRIM GLY to RAD - BYPASS (verlfy)SECS LOGIC (2) - on (up)MSFN conflrm GO for PYRO ARMSECS PYRO ARM - ARMMN BUS TIE (2) - ON (verlfy)CMSM SEF (2) - ONCSMLM FNl SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 pSlaCM RCS LOGIC - OFFSECS PYRO ARM - SAFEMonltor VMAB

If lt25vdc go to EMERG POWERDOWN Pg E6-1AUTO RCS SEL AlC ROLL (4) - OFFAUTO RCS SEL CM 2(6) - OFFAUTO RCS SEL CM 1(6) - MNA or MNBYAW back to 00

PITCH TO ENTRY ATTROLL 0deg (LIFT UP)PITCH - HORIZ on 317deg MARK (400K)YAW 00

ATT DB - MAXMAN ATT (PITCH) - ACCEL CMDEMS DATA - VerifyEMS FUNC - ENTRY (verlfy)EMS MODE - NORMALMAINTAIN HORIZ TRK

PRO (Act ENTRY DAP)

10 F 06 61 IMPACT LAT LONG HDSDN(010 010 -00001)

PRO

11 FOSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axlS beyond 45deg of Vel vector)

-43-

P63 - ENTRY INIT

12 06 64 GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PWR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRHORIZ CKP~tch error needle goes toward

zero approach~ng 05G t~me

MAN ATT (PITCH) - RATE CMDIf CMC ~s GO

BMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS FLY BETA If CMC NO GO ~

SC CONT - SCS~

FLY EMS RCS Deorh Roll HDS UPTRACK HORIZ w~th 29deg w~ndow mk

P64 - ENTRY POST 05G

13

05G t=elt+0___)

06 68

RTOGO AT 05G AGREES WITH EMS - venfyHORIZ CK05E Lt - on (EMS start)

No EMS start w~th~n 3 secsEMS MODE - BACKUP VHF RNG 05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds L~ft DN

NNVR L~ft DNEMS GONO GO

G-V Plot w~th~n llm~ts

Rng ctr dwn 60 + 7 durlng 10 sec per~od

Mon~tor G-meter forconvergence wlth pad data (Do)

(Vlt27K fps) Go To 17

-44-

P65 - ENTRY - UP CONT (Vgt27K fps)

14 F 16 69 BETA (01deg)DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT~

SC CONT - SCS FLY EMS

PRO

15 06 68 BElA VI HOOT (01deg fpsfps)(VltVL +500 fps amp RDOT Neg) Go To 17

p66 - ENTRY - BALLISTIC (DltDL)

16 06 22 DESIRED GMBL ANGLES RPY (01deg)Mon~tor hor~z +12deg of 317deg mark

P67 - ENTRY - FINAL PHASE (02G)

17 0666 BETACRSRNG ERRDNRNG ERR (Oldeglnmlnm)KEY VERBRecord DNRNG ERR _KEY RLSEL~m~t +100nm from PAD DRE

Mon~tor l~ft vector on RSI amp FDAIF 16 67 RTOGOLATLONG (Vre1=1000fps)

(lnm 010 01deg)SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOlfflMon~tor altimeter

Go To EARTHLANDING pg _I4L5__

-45-

56 EARTHLANDING

90K STEAM PRESS - PEGGED50K CABIN PRESS REL vIv (2) - BOOSTENTRY

SECS PYRO ARM (2) - ARM

40K(90K + 63s)

CM UNSTABLE RCS CMD - OFF ~ 40K APEX COVER JETT PG-PUSH DROGUE DEPLOY PG - PUSH (2 secafter apex cover Jett)

30K ELS LOGIC - ON (up)ELS - AUTO

24K RCS hsable (auto)(90K+92s) RCS CMD - OFF

Apex cover Jett (auto)APEX COVER JETT PB - PUSH

(WAIT 2 SECS)Drogue parachutes deployed (auto)

DROGUE DEPLOY PB - PUSH~

If Drogues FallELS - ~ ~Stablllze CM 5K MAIN DPLY PB - PUSHELS - AUTO

235K Cabln Pressure lncreaslng (Drogues + 50s)If not lncreaSlng by 17K CABIN PRESS REL vlv (RR) - DUMP

-46-

10K Maln parachutes deployedMAIN DEPLOY PB - PUSH (wlthln 1 sec)VHF ANT - RECYVHF AMA - SIMPLEXVHF BCN - ONCABIN PRESS REL v1v (2) - CLOSEDIRECT 02 vlv - OPENCM RCS LOGIC - on (up)CM PRPLNT - DUMP (burn audlb1e)Monltor CM ReS 1amp2 for He press decrease

NO BURN or PRESS DECREASE USE BOTH RHCs DO NOT FIRE PITCH JETS

CM PRPLNT-PURGE (to zero He press)CM RCS He DUMP PB - PUSH RHC (2) - 30 sees NO PITCH k

STRUT LOCKS (2) - UNLOCK

cb FLT amp PL BAT BUS ABampBAT C (3) - closecb FLT amp PLT MNA amp B (2) - opencb ECS RAD HTR OVLD (2) - opencb SPS PampY (4) - open

3K CABIN PRESS REL v1v (RH) - DUMP (after purgecompleted)

FLOOD Lts - POST LDGCM RCS PRPLNT (2) - OFFROT CONTR PWR DIRECT (2) - OFF

800 CAB PRESS RELF vlv - CLOSE (latch off)MN BUS TIE (2) - OFF

AFTER LANDINGcb MAIN REL PYRO (2) - closeMAIN RELEASE - on(up)

Go to POSTLANDING pg _47L-__

I

2

3

-47-

57 POSTLANDING

STABILIZATION VENTILATION COMMUNICATIONS

DIRECT 02 vlv - CLOSE

Stablllzation after landlngELS - AUTO (verlfy)cb MAIN REL PYRO (2) - close (venfy)MAIN RELEASE - on (up) (verlfy)S~CS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb BAT RLY BUS (2) - open

No contact w1th recovery forcesVHF AM AampB - off (ctr) ~

VHF AM Rev ONLY - A cb PL VENT - closecb FLOAT BAG (3) - closecb UPRIGHT SYS COMPRESS (2) - closeIf Stable II

FLOAT BAG(3)-FILL t1ll 2 m1n afterupr1ght then - OFF

VHF AM AlB amp BCN - OFF whlle lnvertedIf Stable I

After 10 M1n Coollng Per1odFLOAT BAG (3) - FILL 7 mln then OFF

Post Stab1lizat1on And Ventllat10nPL BCN LT - BCN LT LOWPL VENT vlv - UNLOCK (Pull)Remove PL VENT Exh CoverPL VENT - HIGH or LOWPL DYE MARKER - ON (swlmmer comm)Release foots traps and_restralntscb MNA BAT BUS A amp BAT C (2) - opencb MNB BAT BUS B amp BAT C (2) - opencb FLT amp PL BAT C - opencb PYRO A SEQ A - opencb PYRO B SEQ B - open

EACH HR - CHECK DC VOLTSgt 275 V If Notmiddot cb FLT amp PL-BAT BUS AampB (2) -open cb FLT amp PL BAT C (1) - open GO TO LOW POWER CHECKLIST

Unstow and lnstall PLV DISTRIB DUCTDeploy grappllng hook and 11ne 1f req

4

-48-

Post Landing Communlcatl0nsVHF ANT-RECY (venfy)VHF BCN - ON (verlfy)

If no contact ~lth recovery forcesperform VHF BEACON Check

MONITOR VHF BEACON transmlSSlonnth VHF AM B Rcvr andor Su)vlval

TransceiverkVHF Beacon not operatlng ~connect Surv~val TranscelVer to antcable behlnd VHF ant access pnland place radio ln BCN mode

LOW POHER CHECKLISTVHF BCN - OFFVHF AM (3) - RCVFLOOD Lts - OFFVHF AM AampB - off (ctr)VHF AM RCV ONLY - A (venfy)COUCH LIGHTS - OFFPOSTLANDING VENT SYS mlnlmlze useSURV RADIO - plug mto VHF BCN ANT cableconn behind VHF ant acess pnl amp turn radloon l-n BCN mode

EGRESS PROCEDURES

CMPCDRLMPCDR

CMPCDRCMP

LMPLl1PCDR

STABLE IDlsconnect Umblll-calsNeck darn onCenter couch - 270 0 positionArmrests stowedConnect raft to SIC l-f desl-red wlth

green lanyardConnect raft ~hl-te lanyards to SUltS amp

lnflate water wlngs when eXltl-ngHATCH PISTON PRESS vlv - PRESS (Outbd)Slde Hatch openedPL VENT - OFFcb Pnl 250 (all) - openEgress with 11feraftPut hardware klt outEgress

or CDIPALL

CMF

CDRCMF

CDR

LMF

CMFCMP LMFCMP

UlP

CDR

-49-

STABLE IIcb CREW STA AUDIO (3) - openD~sconnect umb~1~ca1s

Release foots trapsRelease restra~nt harnessCouch seat pans (3) - 170 0 pos1t10nArm rests stowedSurv1va1 k~ts removed from stowageConnect life raft ma~n1~ne to CDR or SicConnect f~rst wh~te lanyard from

11fe raft to suitConnect th~rd wh~te lanyard from

l~fe raft to SU1tConnect rucksacks together to yellow

lanyard on raft bagPRESSURE EQUALIZATION vlv - OPENRemove and stow fwd hatchEX1t feet f1rst w1th rucksacks when clear

of siC 1nflate water w1ngs and raftExit feet f1rst when clear of SiC

1nflate water w1ngsEX1t feet f1rst when clear of sic

1nflate water w1ngs

-50-

60 TLI ABORTS

TLI Aborts are conta~ned ~n the ESD s~nce the bulk of the funct~ons

concern entry preparat20ns and performance Th~s allows a s2nglesource of procedures for procedure rev2ew val~dat~on checkout andtra~n~ng These procedures ~ncorporate TLI preparat20ns as found ~n

reference 6 w~th the TLI Abort Procedures and these t~e 2nto normallunar return Entry Procedures found ~n sect20n 5 The guidel~nes

for th~s cont2ngency are spec2f2ed 2n reference 7

In2t2al preparat~ons for TLI pos2t20n the necessary system sW2tches2n add~t~on to perform~ng an EMS ~V test and a GDC al~gnment Afterthe DET ~s set for mon2tor2ng TB6 the CMP ~ncreases the 12ght levelof the LEB DSKY to max~mum and returns to the h2s couch Th2s 2Sdone so that the LEB DSKY can be observed ~n the event sunl~ght orreflect20ns wash out the ma2n d2splay panel DSKY dur2ng cr2t2calmaneuvers The crew then straps ~n and prepares for mon2tor~ng TB6as 2nd2cated by the SII SEP L~te The t2mes se~uence of procedures2S keyed on th~s d~splay and ~ncludes the DET START funct~on andSIVB IGNITION Dur2ng the burn the crew mon2tors the FDAIs foratt~tude excurs20ns and abnormal rates report~ng status checks toM~ss2on Control at d2screet t~mes dur2ng the maneuver Upon SIVBSHUTDOWN the eMP records the DSKY d~splayed performance parametersand awa2ts ground conf2rmat~on

The rat~onal for TLI aborts ~s descr~bed 2n reference 7 A summar2shyzat20n 2S extracted to prov2de background and gu2de12nes 2n th2sdocument The abort procedures cover aborts 10 m2nutes after conshyt2ngent SIVE shutdown and aborts 90 m2nutes after normal SIVE shutshydown t2me

The 10 m~nute TLI abort ~s des2gned to be used dur~ng TLI ~n theevent a spacecraft problem develops Wh2Ch can result 2n catastrophe2f ~mmed~ate act~on 2S not taken If the s~tuat20n perm~ts the crewshould always allow the SIVB to complete TLI at wh~ch t~me the groundand crew can perform a malfunct~on analys~s to determ~ne ~f an abort~s adv~sable If a fa~lure occurs that necess2tates the shutdown ofthe SIVB and the ~u~ck return of the crew to earth th~s abort ~s

des~gned to be as ~nsens~t~ve to execut~on errors as poss~ble andst21l be targeted to m2dcorr2dor The burn att~tude w~th the f~ed

hor~zon reference ~s a constant value for any shutdown t~me Theburn durat~on 2S a funct20n of shutdown t2me and 2S ava21able fromcrew charts S~nce the pr~mary purpose of th~s abort ~s to returnto earth as qU2ckly as poss2ble there are no restr2ct20ns as toland~ng locat~on However ~f the t~me to EI is greater than abouttwo hours a midcourse correct20n should be ant~c~pated

The 90 m2nute TLI abort 2S to be used 2f a cr2t2cal subsystem malshyfunct~on ~s determ2ned and the dec2s~on to abort ~s made after the

-51-

TLI cutoff and before TLI cutoff plus approxlmately 80 m1nutesTh1S allows suff1c1ent separatlon and procedural t1me to set upfor the SPS deorb1t burn performed at about TLI + 90 Note thatgenerally the deorb1t burns w1ll be performed a fe11 m1nutes beforeTLI + 90 accord1ng to crew charts shown In reference 8 The no-comm except10n requ1res that 90 m1nutes be the 1nput t1me of 19n1shytlon for P-37 (onboard return-to-earth abort program) so that onshyboard calculatlons can correspond w1th ground calculat10ns to computethe CM land1ng p01nt Th1S TLI abort lS des1gned so that returnfl1ght t1me does not exceed 18 hours and abort ~V does not exceed7000 fps ThlS abort can be performed uSlng chart ~Vs and attltudesand the earths hor1zon serves as a suff1c1ent reference The maneushyver lS targeted to ach1eve the mldcorr1dor entry target Ilne andtlmed to result 1n a deslgnated recovery area

It 1S ObV10US for abort deC1S1ons early 1n the TLI + 90 m1nute t1meshyframe that a GampN SPS burn should be performed In order to keep theTLI abort procedures cons1stent and w1th emphasls on slmpl1c1ty theprocedures here reflect a SCS SPS abort burn to cover the full abortdec1s1on t1meframe

A m1dcourse correct1on for corr1dor control after a TLI abort may bedeS1red 1f the SPS burn d1d not meet expectat1ons The TLIabortprocedures 1n th1S sect10n adapt to the normal lunar return tlmel1neand procedures pr10r to the f1nal MCC

-52-

61 TLI PREPARATION PROCEDURES

GET = 150

CRO AOS(___)

CRO LOS( )(22142)

5100

Don Helmets amp Gloves

XLUNAR - INJECT (verify)EDS PWR - on (venfy)EMS FUNC - OFF (verlfy)EMS MODE - STBYEMS FUNC - IW SETVHF RNGEMS MODE - NORMALSet ~V indo to +15868 fpsEMS FUMC - ~V Test

SPS THRUST Lt - onoff (10 sec)~V lnd stops at -01 to -415

EMS MODE - STBYEMS FUMC - ~V SETVHF RNGSet ~VC

EMS FUNC---~~V=----

GDC ALIGNFDAI Select - liZcb SECS LOGIC (Z) - close (verify)cb SECS ARM (Z) - closeSECS LOGIC (Z) - on (up)MSFN Conflrm GO for PYRO ARM (If pass)SECS PYRO ARM (Z) - on (up)TRANS CONTROL PWR - ONROT CONTR PWR NORMAL (Z) - ACDC(verlfy)ROT CONTR PWR DIRECT (Z) - MNAMNBLV INnGPI - SIISIVB (venfy)LV GUID - IU (venfy)cb DIRECT ULLAGE (Z) - closedSet EVENT TIMER to 5100Begin MONITOR For TB6

CMP to Couch

TB 6 - SII SEP Lt on (TIG-9 mln 38 sec)KEY V83E

SET ORDEALFDAI Z ORB RATE at 180 0 0SII SEP Lt out (38 sec later)Start DET COUNTING UPSC CaNT - SCS (verify)MONITOR LV TANK PRESS

~P lt 36 psid (OXID gt FUEL)~P lt Z6 psid (FUEL gt OXID)

EMERGENCY CSMLV SEP UP TLM CM - BLOCK (verify)UP TLM IU - BLOCK (venfy)

-53-

+45degPY))0middot sec PY

lOK nmltHAlt25K nm

Two phas~ng mnvrs two SPS mnvrs to circular~ze at 150 nmearth orb~t

CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ssion 4K nmltHAltlOK nm CSM amp1M - Two phasing mnvrs two SPS mnvrs to circularize at 150 nm earth orb~t CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ss~on

CSM amp 1M - Two phas~ng mnvrs APS burn todepletion th~rd phasing mnvrSPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn tosem~sync orb~t

25K nmltHAlt40K nm CSM amp 1M - Two phasmg mnvrs APS burn to depletion third phas~ng mnvr SPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn to sem~sync orbit HA)40K nm DPS ava~l - DPS LOll circularize with SPS

DPS not ava~l - Lunar flyby or CSM only to lunar orbit (if reqd gtV lt4000 fps)

V37E 47E (check b~as) Record -=--rshy(Limit 98 fpsmm)

( 1fps)tVXYZN62EVIHDOTHPAD (fpsfpslnm)MONITOR VI ( ) at ECO

SCS TVC SERVO PWR 1 - ACIMNA2 - OFF

TAPE RCDR - CMD RESETHBREMS MODE - NORMAL

SIr SEP Lt - ONTLI Inhib~t S~gnals w~11 not be honored after 5942

SIVB ULLAGE BeginsSII SEP Lt - off (TIG - 18 sec)SIVB FUEL LEADSIVB ULLAGE d~scont~nues

LV ENG I Lt - onSIVB IGNITION ( GETI)LV ENG I Lt - off - -shyMONITOR THRUST amp ATTITUDEMONITOR LV TANK PRESSSIVE ECO (Lt on) (BEGIN TB7)

EMER SIVE CUTOFF AT 6 SEC PAST BURN TIME IF VI ATTAINEDTHC CCW ampNEUTRAL IN 1 SEC or SIISIVB sW - LV STAGEPremature Shutdown HAlt4K nm CSM amp 1M -

5700

58205836

F 16 835800

F 16 62

5838594259525955595900000002SUNRISE(___)

HAW AOS(__=_) KEY VERB (freeze d~splay)

SIVB ATT HOLD 20 sec amp BEGIN VENTINGSIVB NNVR TO ORB RT (HDS DN) (3middot sec)

Record VI -c---HDOT _

HPAD _

KEY RLSEF 16 62

F 16 83

HAW LOS(__=-)

KEYmiddotRLSE~VXYZ (lfps)

Record ~VX---_

~vy

WZ--

AVC---_

TAPE RCDR - off (ctr)EMS MODE - STBYEMS FUNC - OFFSECS PYRO ARM (2) - SAFE

PRO

BURN STATUS REPORT

____--~TIG

BT------VGX____-R

-----P----_Y

REMARKS

_____VI

______--HDOT______--H______---AVC______---FUEL_______OXID

_______UNBAL

F 3708=00 OOEGOS AOS CMP TO LEB

(-=-=-)

0000

0003

0005

0014

0100

-55-

62 TLI 10 MIN ABORTSECS LOGIC (2) - on (up)SECS PYRO ARM (2) - ARM

TRANS CONTR - CGH (4 sec) amp +XDET RESET (verlfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS GMD-ON

TRANS GONTR - neutral then +X for10 sec

SIVBGPI s~ - GPIExcesslve rates 6V THRUST A - NORMAL SPS THRUST - DIRECT When rates damped 6V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

TRANS CONTR +X - OFFV37E OOE

PITGH UP to LOGAL VERT (+X axlSto~ard the earth)

RATE - LOWBMAG MODE (3) - ATTIRATE 2EDS PHR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SEGS ARM (2) - opencb EDS (3) - open

TRANS CONTR -X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (180deg)P (199deg)Y (0deg)

RETRO UPDATEGETI _

JV _VG

Jtb ---GET 400K _

05G _GET DROGUE _

ENTRY P _R _

Y_--

0945

-56-

ALIGN HORIZ ON RET +1 MKGMBL CHECK (T11lle Pentattlng)MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conflnn)cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FUMC - JV SETVHF RNGSET JV from chartE~S FUMC - JVEMS fODE - NOIDlAL

lV THRUST A - NORMALV37E 47E (THRUST fONITOR)

F 16 83 lVXYZ (1 fps)

0950

1000

NOTE For aborts durlng 1st mln of TLIKEY V82E F 16 44 (HaHpTff)Burn untll Hp lt 19NM

TRANS CONTR +X

THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN JV reqdJV THRUST (2) - OFFReport cutoff

cb SPS P2 Y2- closeGfBL MTRS (4) - OFF (LMP Confinn)TRANS CONT PWR - OFFTVC SERVO PWR (2) - OFFMN BUS TIE (2) - OFFcb SPS P1amp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREIf est time to EIltOl5500 omlt fCC andenter the SUPERCIRC CKLIST as early as pos-slb1e Pg ~2~3~ __If est time to EI)Ol5500 anticlpate afCC Enter the ENTRY PREP CKLIST at step 9pg 18

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

-2tl C

l I W gt- ~-4

z laquo I I- 0 -6

l- I J u gt- ~-8

z w w -10

~_ONSANT

9O

VER

SHO

OT

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ARY

LIF

TV

EC

TOR

OR

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TATI

ON

LIN

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SH

ALL

OW

TAR

GE

TLI

NE

STE

EP

TAR

GE

TLI

NE 12

gU

ND

ERSH

OO

TBO

UN

DAR

Y

RE

EN

TRY

CO

RR

IDO

R

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-12 24

26

28

30

32

34

RE

EN

TRY

VE

LOC

ITY

VE

1-F

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EC

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36

3B

6-i

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CC

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73

8X

03

-i- rtREQUIRED PITCH GIMBAL ANG LETO OBTAIN HOR-IZON AT 317

DEGREES IN wiiiiDOW

260

z~I- ~ i5 24000

1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

-I

-1-

NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

I LU HD~-

LUHD

lt0 120UJ0

~

80 HOLD PRESENT TRIMgt LU HD013

~Y~HOIgtlt

TOP OF WINDOWa 40to

31 7 SCRIBEaaI

80 TTOM OF WINDOWi= 0

0--ltoa

-40t-z

~~~Uw w u lt0 -80

HOLO PRESENT TRIlJCl

LOHU0 lt0

J gt -120 HOLD 059 TRIMlt0 z

LDHUlt0 FIELD OF VI S10 NLDHU LIFT-DOWNHEADS -UPLUHD LIFT-UP HEADS-DOWN

~~H~-160 q - P63 LIMITI- NOrE-VALIO ONLY FO~t~--

LUNAR RETURN VELOCITY

plusmnl8020 244middot 8 12 16

TIME TO 400K FT ALTITUDE-MIN

4

P37

LONG

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TOOB

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1350

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340

344

348

352

356

364

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120

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2627

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0050

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0030

0020

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Cll-

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120

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320

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-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 10: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

-7-

apparently good and In agreement wlth the EMS but the spacecraftresponse is questlonable the crew manually takes over and fIlesthe CMC commands

If the Upcontrol Program P65 was entered the program wlll nomshylnally sWltch to the Flnal Entry Program P67 for target rangesbelow approxlmately 1800 nautlcal miles or to the Ballistlc Proshygram P66 for ranges greater than approxlmately 1800 nautlcalffilles The program transfer crlterla are more preclsely deflnedIn reference 1

If P66 lS entered the spacecraft lS automatlcally rolled to theIlftup heads-down attltude to permlt the horlzon to be vlewedfrom the wlndow durlng the second entry The entry attltude checklS made by comparlng the horlzon wlth a speclfled wlndow mark Ifthe check falls the crew manually malntalns the entry trlffi attltudeuSlng the horizon VleW for reference The EMS lS used for ranglngSlnce the veloclty has now decreased to below 25500 feet per second

The EMS scroll lS contlnuously used to monltor for exceSSlve g conshydltlons durlng the second entry If the EMS V-g trace vlolates theg Ilnes and the PGNCS lS not commandlng (and spacecraft respondlng)to correct the situatlon the PGNCS lS falled and the EMS lS usedfor ranglng after ltS g lndlcatlon has been conflrmed by the lndeshypendent g meter

The entry phase lS essentlally over when the relatlve veloclty ofthe spacecraft decreases to less than 1000 feet per second ThlSlS lndlcated In P67 when RTGO latltude and longltude are dlsplayedSlnce very Ilttle ranglng capablllty exists after thls pOlnt thespacecraft lS orlented elther full Ilft up or down dependlng on RTGOnegatlve or posltlve and the crew prepares for the earth landlngphase

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-13-

40 EARTH ORBITAL DEORBIT AND ENTRY TECHNIQUES

As outl~ned ~n reference 5 a nom~nal PGNCS entry from earth orb~t ~s

based on a preparat~on t~me of 2 hours and 40 m~nutes ~nclud~ng 2n~ght passes Th~s t~me ~ncludes approx~mately 20 minutes before thef~rst n~ght pass after the CMC update and PAD data have been rece2vedTh~s t~e also 2ncludes approx2mately 20 m2nutes after the secondn~ght pass to allow suffic~ent t2me to prepare for retrof2re after theIMU f2ne a12gnment It has been determ2ned coarse a12gnment accuracy~s adequate for retrof~re and entry and undoubtedly other funct20nscould be om2tted depend2ng on the c2rcumstances for the dec2s20n toreenter Descr2bed here2n are the nom2nal earth oro2tal entry proshycedures w2th pert2nent comments on system va12dat20n for real timeacceptance dec~s20ns

After the entry dec~s~on is made the crew transfers the PGNCS fromthe standby to the operate mode and rece~ves a CMe update w~th P27Next the maneuver PAD update ~s v02ced up and the 2n~t~al entry mode~s determ~ned During the ~n~tial n~ght pass the IMU or2entat~on ~s

estab12shed uS2ng P51 star s~ght2ngs to obta2n a REFSMMAT The preshyferred or~entat~on opt20n ~n P52 2S then selected to coarse a12gn theIMU uS2ng the des2red entry REFSMMAT determ2ned by MGG-H The GOO ~s

now al~gned to the IMU 2n preparat~on for an IMUSes dr~ft check Ifthe GOO ~nd~cates the ses dr2ft rate exceeds 10 degrees per hour ~n

any ax~s the check ~s repeated on the other BMAGs to estaol~sh if theGOO or Just the single set 2S unusuable Var20us sytem checks as 12sted2n sect20n 51 are performed as necessary cons2stent w2th the t2me12ned2ctates of the maJor act2v2t2es Included 2n these checks are the EMSself-tests and the dV counter test The latter requ2res the spacecraftbe placed ~n dr2ft2ng fl2ght w~th the funct20n sW2tch 2n the dV pos2t~on

If the counter reg2sters a change of more than 25 feet per second w2th2n100 seconds the scroll and counter are unre12able for mon2tor2ng thedeorb2t burn and entry rang2ng If the EMS self-test fails and t2medoes not allow further analysis a 5555 ERE entry 1S planned as thePGNGS backup entry mode After complet2on of these checks the entryPAD lS prov1ded by MeG-H The crew then selects the external dVprogram P30 and the appropr2ate deorb1t tbrust1ng program p40 or P41Dur2ng th2s per2od wh2ch 2ncludes the f1nal n2ght pass P52 may beselected to ver2fy the IMU a12gnment Since the retro att2tude hasbeen computed so that a w2ndow mark c01nc2des w2th the hor2zon atGETI th2s serves as the conclus2ve check on the PGNCS At 5 m2nutesbefore retrofire the att2tude check 1S made by ver1fY2ng that the 12degree scr~be 12ne ~s w2th2n 3 degrees of the hor2zon If not thePGNeS has fa2led and the ses 2S used for att2tude reference and the

V counter for burn durat~on control S2nce the ses att~tude wasa12gned to the IMU a real~gnment ~s necessary This ~s accompl~shed

by manually maneuver2ng the spacecraft to ma~nta1n the 24 degree wlodowmark on the hor2zon and releas1ng the GOO a12gn button at TIG - 2 m2nutes

-14-

Upon complet~on of the burn the tN res~duals are burned to W~th~n

02 feet per second If the PGNCS ~V counter or est~mated burnduration are ~n d~sagreement ~t must be estab1~shed whether suff~shy

c~ent veloc~ty has been suppl~ed to put the land~ng po~nt in thefootpr~nt The PGNCS data w~ll be used ~f ~t ~s conf~rmed by oneother source if not the ~V counter w~11 be used ~f ~t ~s conf~rmed

by the burn durat~on t~me If add~tional ~V ~s necessary the data~s ava~lable to the crew on an onboard chart found ~n Sect~on 80

Post burn entry preparat~on requ~res EMS ~n~t~al~zation RSI al~gnshy

ment and pre-separat~on funct~ons The crew then selects the ~n~t~al

entry program P61 and records the d~sp1ays as a check aga~nst PADdata Upon complet~on of these checks P62 ~s entered The crewmanually or~ents the spacecraft to the separat~on attitude and yaws450 to ~nsure aga~nst possible CM 8M recontact After separat~on

the spacecraft ~s maneuvered to the reentry tr~m att~tude wh~ch

places the hor~zon on the 3170 w~ndow mark at EI Shortly thereshyafter ~n P62 the entry DAP is act~vated and P63 in~t~ated Dur~ng

th~s t~e MCC-H has computed a postburn update and ~t ~s vo~ced tothe crew ~f d~fferent from preburn values The EMS scroll and rangecounter w~ll be adJusted accord~ngly ~f t~me perm~ts A f~nal PGNCScheck pr~or to 05g may be mon~tored at th~s t~e w~th the CMC modein free and the manual att~tude p~tch ~n acceleration command wh~le

the hor~zon reference ~s held the p~tch error needle w~ll decreaseto zero as EI ~s reached At RET 005g the EMS mode sw~tch ~s

turned to manual the entry 005-g sw~tch and EMS roll sw~tch areturned on and the spacecraft control sw~tched to CMC to beg~n DAPcontrol At the PGNCS 005-g ~ndicatwn the program change fromP63 to P64 ~s mon~tored and the t~e vo~ce recorded At th~s t~me

the EMS range counter check ~s made dur~ng the 10 second per~od

follow~ng EMS 005g Dur~ng th~s per~od the counter should countdown 40 + 10 naut~cal m~les At PGNCS 02-g ~nd~cation the changefrom P64-to P67 ~s monitored and the ~splay may be held by key~ngVERB ~n order to record the init~al downrange error d~splay andcompare ~t to the PAD value The PGNCS has fa~led ~f the two do notagree w~th~n + 100 naut~cal m~les In the event P67 has not appearedwhen both the-g-meter and the scroll ~nd~cate greater than 05g thePGNCS has sim~lar~ly fa~led In e~ther fa~lure the SCS is used foratt~tude reference w~th an EMS entry If the checks agree the crewrema~ns w~th automat~c DAP for the rema~nder of the entry

The entry phase ~s essentially over when the relat~ve velocity ofthe spacecraft decreases to less than 1000 feet per second Th~s

~s ~nd~cated ~n P67 when RTGO lat~tude and long~tude are d~splayed

S~nce very l~ttle rang~ng capab~l~ty exists after th~s pOint thespacecraft is or~ented either full l~ft up or down depending onRTGO negat~ve or pos~t~ve and the crew prepares for the earth land~ng

phase

-15-

41 TYP~cal Retrof~re and Entry Sequence of Events

Dec~s~on to reenter

P27 (CMC update)

Retrof~re PAD update

Entry mode dec~s~on

P51 (IMU or~entat~on determlnatlon) durlng f~rst dark per~od

P52 (IMU coarse allgnment)

EMS checks

Entry PAD update

P30 (external AV)

p40 (SPS thrust)

P52 (IMU f~ne al~gnment) durlng second dark per~od

p40 (SPS thrust)

Ign~t~on att~tude check

Retroflre

P61

P62

CMSM separat~on

P63

Postburn PAD update

Entry attltude check

p64 (beg~n DAP control at O05g)

P67 (PGNCS gono go check at O2g)

42

Retrof~re

and

En

try

Alt

ern

atlv

es

Sys

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fa~lure

PGNC

S

PGNC

San

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PGNC

San

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Fal

lure

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Fal

lure

aft

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-17-

5 0 DETAILED ENTRY PROCEDURES

In order to comblne slmilar procedures that are common to lunar returnentrles and earth orblt entrles the followlng procedures are dlvldedlnto categorles that allow a mlnlmum of dupllClty ThlS provldes asmaller tralnlng package and more closely resembles the onboard crewcheckllst when comparlson lS necessary

51 Entry Preparatlons for Superclucular and Earth Orbltal Entrles

1~e entry preparatlons are comblned In these procedures andsteps pecullar to elther superclrcular or earth orbltal entrlesare labeled accordlngly The tlme llstlngs In thlS sectlon areappllcable to only superclrcular entries Slnce the earth orbltalentry tlmellne lS a functlon of several varlables as descrlbedIn sectlon 40 and reference 5

-18-51 (Contlnued)

VEHICLE PREPARATION

l-

2

3

4

5

6 -0600h

7 -0535h

8

9

10 -0430h

INITIAL STOWAGE COMPLETED

CMC amp ISS START UP

SCS POWER UP

p51 - IMU ORIENTATION

LOAD DAPV48E 11102 01111 PRO ERO PRO

LAST MCC DECISION

NO COMM - P52 amp NAV SIGHTINGSNOMINAL - P2337 ONBOARD COMPARISON

DON MAE WESTS amp FOOT RESTRAINTS

VHF AM A - SIMPLEX

P 27 (SV REFSMMAT) MNVRamp ENTRY pAD UPDATES

11 -0415h P52 - IMU REALIGN(___) (OPTION 1)

12 P37 (NO COMM ONLY)

13

14

ECS CKS02 SUPPLY REFILLECS Monitor CkEVAP H20 CONT (2) vlvs - AUTOSUIT HEAT EXCH SEC GLY - FLOW

EPS CKS 1 3 4 (5 If reqd)

15 SPS CK (If req d)

16

17

18

RCS CKSSM RCS MOUlt CkCM RCS MOUlt Ck

CampW SYS CK

CMC SELF CK

19

20 -0345h

-03l5h-0300h

21

22

22A

-19-

DSKY COND LT TEST

MIDCOURSE MANEUVERP30 - EXT rVP404l - SPSRCS THRUSTINGMIDCOURSE (17) BURN

NO COMM NAV SIGHTINGS

ffiVR TO ENTRY ATT (Superc1rc only)V62E

V49E

22B F 06 22 DESIRED FINAL GMBL ANGLESLOAD ENTRY ATT PAD ANGLESPRO

22C F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) SC CONT - CMC

BMAG MODE (3) - RATE 2CMC MODE - AUTO

PRO(~N) SC CONT - SCS

MNVR to 22E

22D 06 18 AUTO MNVR TO FDAI RPY ANGLES

22E F 50 18 REQUEST TRIM(TRIM) Go to 22C(BYPASS) ENTR

23 -200hr BORESIGHT amp SXT STAR CHECKOPT MODE - CMCOPT ZERO - OFF

V41 N91E

F 21 92 SHAFT TRUNLoad SXTS angles

41 OPTICS DRIVE

CHECK SXT STAROPT ZERO - ZERO

CHECK BORESIGHT STAR (If ava11)

24 -0135h

25(___)

26

27 -0115h

-20-

P52 - lMU REALIGNRecord gyro torqu~ng anglesRp~----

YIf-7gt-Lno--re-c-ycle PS2If conflrmed use SCS for EMS entry

GDC ALIGNIf drlft gtLOohr change ratesource

FINAL STOWAGEOPTICS (except for hybrid)ORDEALGLY TO RAD SEC - BYPASS (verlfy)CooL pnl lnstalledY-Y struts (2) extendedStow Data Box R-12

EMS CHECKEMS FUNC - OFFcb EMS (2) - closeEMS MODE - STBYEMS FUNC - EMS TEST 1 (walt 5 sec)EMS MODE - NORMAL (walt 10 sec)

Check ind lts - offRANGE lnd - 00Slew halr1ine over notch

In self-test patternEMS FUNC - EMS TEST 2 (walt 10 sec)

05G It - on (all others out)EMS FUNC - EMS TEST 3

05G It - onRSI Lower It - on (10 sec Qater)Set RANGE counter to 58 nm+OO

EMS FUNC - EMS TEST 405G It - on (all others out)G-V trace w~thin pattern to lwr rt

corner 9GRANGE lnd counts down to 0+02

EMS FUNC - EMS TEST 505G It - onRSI upper lt - on (10 sec later)RANGE md - 00SCrlbe traces vertlcal llne 9g to

022+01ALIGN SCROLL TO ENTRY PATTERN (on

37K ft sec hne)EMS FUNC - RNG SET

G-V scroll assy traces vert llne022g to 0+01

EMS MODE - STBY

28

29

30 -OllOh

-21-

~V TEST (Deorb~t only)EMS FUNC - ~V SETVHF RNGSET ~V ~nd to 15868 fpsEMS MODE - NORMALEMS FUNC - ~V TEST

SPS THRUST LT - onoff (10 sec)~V ~nd stops at -01 to -415

EMS MODE - STBY

PRIMARY WATER EVAP ACTIVATIONGLY EVAP H20 FLOW - AUTOGLY EVAP STH PRESS - AUTOPRI ECS GLY PUMP - ACI

CM RCS PREHEATNote If sys test mtr 5cd6abcd

all read 39 vdc (28degF) or moreom~t preheat

cb RCS LOGIC (2) - closeCM RCS LOGIC - ONUP T1M CM - BLOCK (ver~fy)

cb CM RCS HTRS (2) - closeCM RCS HTRS - ON (LMP Conf~rm)

(20 mlU or III lowest rdg lS39 vdc) (Moultor Maufpress for press drop)

31 (___) FINAL GDC DRIFT CK (If req I d)If drlft gtlOohr Suspect GDC Do not

use RSI amp FDAI 2

32 -OO5Om

33

34

35

TERM CM RCS PREHEATUP TLM CM - BLOCK (venfy)CM RCS HTRS - OFFCM RCS LOGIC - OFF

SYSTEMS TEST PANEL CONFIGURATIONSYS TEST METER - 4BRNDZ XPNDR - OPERATECM RCS HTRS - OFFWASTE H20 DUMP - OFFURINE DUMP - OFF

LEB LIGHTING - OFF

SEC WATER EVAP ACTIVATIONGLY To RAD SEC vlv - BYPASSSEC COOL EVAP - EVAPSEC COOL PUMP - AC2

36

37

38 -OO45m

-22-

PYRO BATT CKcb PYRO A SEQ A - close (ver~fy)

cb PRYO B SEQ B - close (verify)DC IND - PYRO BAT A(B)

~If PYRO BAT A(B) lt 35 vdc cb PYRO A(B) seq A(B) - open~

PYRO A(B)BAT BUS A(B)TO PYRO~MN BUS TIE - close

cb MNA BAT C - closecb MNB BAT C - closeDC IND - MNBPNL 8 - All cbs closed except

PL VENT - open (ver~fy)

FLOAT BAG (3) - open (ver~fy)

DOCKING PROBE (2) - open (verlfy)EDS BAT (3) - open (ver~fy)

CM ReS HTRS (2) - open

CM RCS ACTIVATIONcb SECS ARM (2) - close (verlfy)cb SECS LOGIC (2) - close (verlfy)SECS LOGIC (2) - ONMSFN conflrm GO for PYRO ARM(~f poss)SECS PYRO ARM (2) - ARMCM RCS PRPLNT 1amp2 - ONCM RCS PRESS - ONRCS Ind sw - eMl then 2

He PRESS 3700-4400 pSlaMANF PRESS 287-302 pSla

SECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFF

P27 amp ENTRY PAD UPDATEGo To Entry Checkllst

Superclrc - pg ~2~3 _Hybnd - pg -----2~9L-__Normal Deorblt - pg __3L5L- _

-23-

52 SUPERCIRCULAR ENTRY

1 SET DET (up to ET)

2

3

4

5

3000(-30-00)

EMS INITIALIZATIONSET RNG TO PAD DATA RNGEMS FUNC - Vo SETSlew Scroll to Pad Data VIOEMS FUNC - ENTRY

RS I ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on (up)GDC ALIGN PB - PUSH amp HOLDYAW Tw - Pos~t~on RSI thru

45deg amp back to LIFT UPGDC ALIGN PB - ReleaseEMS ROLL - OFFA1~gn CDC to lMU

CM RCS RING A CKRCS TRNFR - CMcb CM RCS LOGIC MNB - openAUTO RCS SEL MNB (6) - OFFSC CONT - SCSTest R~ng A ThrustersSC CONT - CMCRCS TRNFR - SMAUTO RCS SEL (12) - MNAMNB

(hftoff conflg)cb CM RCS LOGIC MNB - close

OPTICS PWR - OFFCMP to COUCH

MN BUS TIE (2) - ONTAPE RCDR - REWIND

6 35middot0Om(-25middot 00)

-24-

SEPARATION CK LISTTVC SERVO PWR 1 - AClMNAcb ELS (2) - close (ver1fy)PRIM GLY TO RAn - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY vlv - OFFCAB PRESS REL vlv (2) - NORMGMBL MTRS (4) - STARTABORT SYS PRPLNT - RCS CMD (venfy)SM RCS PRIM PRPLNT (4) - ONVHF 11M (AampB) - OFFHI GAIN ANT PWR - OFFFC PUMPS (3) - OFFVer1fy s1ugle SU1t compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - 10101cb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2) - opencb HTRS OVLD (2) - openPOT H20 RTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANSEC COOL EVAP - RESETSEC COOL PUMP - off (etr)

MtiVR TO CMSM SEP P R ATTSC CONT - SCSCMC MODE - FREEMNVR TO PAD ATTR (0deg)PY----W)

-25-

SUPERCIRCULAR ENTRY (Cont~nued)

1

4100m(-1900)

P61 - ENTRY PREP

V37E 61E

k 05 09 01427 - ROLL REVERSED 05 09 01426 - IMU UNSAT ~

2 F 06 61 IMPACT LAT LONG HDS UPDN (+-)PRO (010

fps +00001)

3 F 06 60 GMAXVPREDGAMMA EIRecord

GMAXV400K----

GAMMA EI _PRO

(01deg fpsOldeg)

4 F 06 63 RTOGO (lnm) PAD _VIO (fps) PAD _TFE(m~n-sec)

Compare w~th ~M~SFN==C~f~o-r~P~GNS GONO GOIf NO COMM Set RTOGO amp VIO In EMS

amp lnltla11ze(ACCEPT) PRO(RECALC) V32E To 4

5 F 50 25

4300m

(-1700)

45 oOm(-1500)

500Om(-1000)

6 F 06 61

-26-

P62 - CMSM SEP amp PRE-ENTRY MNVRCAUTION Call No EXT Verbs In P62

00041 REQUEST CMSM SEPSC CONT - SCSFREE

COMPARE PITCH ATT WITH PAD DATA ---0=-

(W~thLU 5deg)YAW - 45deg OUT-OF-PLANE (LEFT)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTIRATE 2MN BUS TIE (2) - ON (ver~fy)

PRIM GLY TO RAD - BYPASS (verlfy)CM RCS LOGIC - ON (venfy)SECS LOGIC (2) - on (up)SECS PYRO ARM - ARMCMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 ps~a

CM RCS LOGIC - OFFSECS PYRO ARM (2) - SAFEMonltor VMAB

If lt25 vdc go to EMERGPOWERDOWN pg E6-l

AUTO RCS SEL AC ROLL (4) - OFFAUTO RCS SEL CM 2(6)-OFFAUTO RCS SEL CM 1(6)-MNAYAW back to 0degPITCH TO HORIZ TRACK ATT

ROLL - 0deg (LIFT UP)PITCH - 400K Horiz Mark (317deg)YAW - 0deg

ATT DB - MAXMAN ATT PITCH - ACCEL CMDEMS DATA - Ver~fy

EMS FliNC - ENTRY (ver~fy)

EMS MODE - NORMALcb SPS PampY (4) - openMAINT HORIZ TRK

PRO (Act ENTRY DAP)

IMPACT LATLONGHDSDN (01deg01deg-00001)PRO

7 POSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axis beyond 45deg of Vel vector)

8 06 64

58middot00m(-0200)

9

05G tlme(+0 )

(--=---)

06 68

-27-

P63 - ENTRY INIT

GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PIJR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRmDHORIZ CKPltch error needle goes toward

zero approachlng OSG tlmeMAN ATT (PITCH) - RATE CMD

If CMC lS GOBMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS I

FLY BETA If CMC NO GO ilt

1 SC CaNT - SCS I

FLY EMS k

p64 - ENTRY POST 05G

RTOGO AT 05G AGREES HITH EMS-venfyHORIZ CK05G Lt - ON (EMS START)

No EMS START wlthln 3 sec ~ EMS MODE - BACKUP VHF RNG c

05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds Llft DN

NNVR Llft DNEMS GONO GO

G-V Plot wlthln IlmltsRng ctr dwn 60plusmn7 durlng 10 sec

perlodMonltor G-meter for

convergence wlth pad data (Do)(Vlt27K fps) Go to 13

-28-

P65 - ENTRY - UP CONT (Vgt27K fps)

10 F 16 69 BETA (01middot) _DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT lt~ SC CONT - SCS FLY EMS

PRO

11 06 68 BETAVIHDOT (OIdegfpsfps)(VltV1+500 fps amp RnOT Neg) Go To 13

P66 - ENTRY - BALLISTIC (D(DL)

12 06 22 DESIRED GMBL ANGLES RPYMoultor horlz +12middot of 317middot mark

P67 - ENTRY - FINAL PHASE (02G)

13 06 66 BETACRSRNG ERRDNRNG ERR(010 1um 1um)

KEY VERBRecord DNRNG ERR _KEY RLSEMoultor l~ft vector ou RSI amp FDAI

16 67 RTOGOLATLONG (Vrel=1000fps)(lumOldegOldeg)

SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOWNMonitor a1t~meter

Go To EARTHLANDING pg ---4L5 _

-29-

53 GampN HYBRID DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL tV1 V37E 30E

2 F 06 33 GETI(ACCEPT) PRO (hrm~n Olsec)(REJECT) LOAD DESIRED GETI

3 F 06 81 tVXYZ (LV) (lfps)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

4 F 06 42 HAHPtV (lnm lfps)Record tV

(ACCEPT) PRO(REJECT) Reselect P30 or P27 Load new paramo

5 F 16 45 MTFIMGA (marksm~n-secOlO)

MGA -00002 ~f k

k lMU not al~gned

SET DETPRO

6

7

8

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (Pull)PLSS 02 vlv - FILL02 8M SUPPLY vlv - OFFCAB PRESS REL vlv (2) - NORMcb ELS (2) - closecb SECS ARM (2) - closecb SECS LOGIC (2) - close (ver~fy)

AUTO RCS SEL CM (12) - MNA or ~ffiB

(hftoff conhg)ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM (AampB) - OFF

CMP to Couch

9

10

11

-30-

MNVR TO PAD BURN ATTLOAD DAPBMAG MODE (3) - RATE 2SC CONT - CMCAUTOATT DB - MINMAN ATT (3) - RATE CMD

v62E

v49E

12 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLES

PRO

13 F 50 18 REQ MNVR TO FDAI RPY ANGLES (01deg)(AUTO) PRO(MAN) SC CONT - SCS

BMAG MODE (3) - RATE 2MNVR To 15

14 06 18 AUTO MNVR TO FDAI RPY ANGLES (01deg)

15 F 50 18 REQ TRIM TO FDAI RPY ANGLES (01deg)(TRIM) Go to 13(ByPASS) ENTR

16

17

CHECK BORESIGHT amp SKT STARSOPT MODE - CMCOPT ZERO - OFF

v41 N91E

18 F 21 92 SHAFTTRUN (01deg 001deg)Load SXTS angles

19 41 OPTICS DRIVECheck SKT STAR

OPT ZERO - ZEROCheck BORESIGHT STAR (~f ava~l)

20 V25 N17E (01deg)Load Pad Data GMBL Angles

for CM BURN ATTATT SETtw - SET

to PAD DATA GMBL ANGLESfor CM BURN ATT

21

22

-31-

PHR REDUCTIONHGA PHR - OFFFC PUMPS (3) - OFFVerify s~ngle su~t compr oper loads

balancedFC 2 MN AampB - OFFS BD PiR AMP - LOWcb ECS RAD CONTHTR (2) - opencb HASTE H20URINE DUMP HTRS(2)- opencb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANMN BUS TIE (2) - ONTVC SERVO PHR 1 - AC1MNAGMBL MTR (4) - START

p41 - RCS THRUSTINGV37E 41E

23 F 50 18 REQ MNVR TO LCL HORIZ (HDS ON)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CMCAUTOPRO To 24

(gtfANDAP) BMAG MODE (3) - RATE 2SC CONT - CMCHOLD

V62EMNVR To 25

24 06 18 AUTO MNVR TO FDAI RPY

25 F 50 18 REQ TRIM TO LCL HORIZ (01deg)ALIGN SC ROLL

(AUTO TRIM) PRO To 24(BYPASS) ATT DB - MIN

RATE - LOHMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTlRATE 2

ENTR

550Om26 06 85

59middot2527

-32-

VGXYZ (1fps)RECHECK BORESIGHT STARTRANS CONIR PWR - on (up)EMS MODE - STBY (ver~fy)

EMS FliNC - bV SETVHF RNGSET (IV for SM BURN _EMS FliNC - bVS BD ANT - OMNI CSECS LOGIC (2) - ONMSFN conhrm Go for PYRO ARMSECS PYRO ARM (2) - ARMCM RCS LOGIC - ON (ver~fy)

DSKY BLANKS

593028 16 85 VG XYZ (AVE G ON) (lfps)

RHCs amp THC - ARMEDLIMIT CYCLE - OFFTAPE RCDR - CMD RESETHBREMS MODE - NORMAL

000029 F 16 85 REQ NULL VG XYZ (lfps)

BURN EMS bV CTR TO ZERORESET DET amp COUNT UP

If SM ONLY burn go to step 32THC - LOCKEDSC CaNT - SCSFREERATE - HIGHPRIM GLY To RAD - BYPASS (ver~fy)

MN BUS TIE (2) - ON (ver~fy)

CMSM SEP (2) - on (up)CSMLM FNL SEP (2) - on (up) (verify)CampW MODE - CMRCS TRNFR - CMCM RCS LOGIC - OFF

Momtor VM ABIf lt25 vdc go to EMERGPOWER DOWN Pg E6-l

V63E

If CMC NO GO FDAI SOURCE - ATT FDAI SEL - 1 or 2 ATT SET - GDC

SET

-33-

~Uili ATT PITCH - ACCEL CMDFDAI SCALE - 55MNVR TO CM BURN ATT (NULL ERR NEEDLES)

R 0degPY --00--

30

31

CM RCS BURNRHC III-ContJnuous PJtch DownRHC HZ-Module PJtch to null needlesBURN VGZ TO ZERO

If only 1 RHC Pulse + P=5deg from retro att MaJnta~n rates lt3degsec

BURN COMPLETION ATllV CTR= or DET= _

V8ZE

32 F 16 44 HAHPTFF (1nmffiJn-sec)Check HP-

If gt Pad data contJnue burnuntJ1 lt Pad

PRO

33 F 16 85 VGXYZ (Ups)Read VG resJduals to MSFN

(HYBRID) PRO to 34(SM ONLY BURN)

PROF 37 ODE

EI-1500 V37E 47EF 16 83 twx Y Z (Ups)

SC CONT - SCSFREEMAN ATT (PITCH) - RATE CMDRATE - HIGHPRIM GLY To RAD - BYPASS (verJfy)MN BUS TIE (2) - ON (verJfy)CMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verJfy)Campl MODE - CMRCS TRNFR - CMCM ReS LOGIC - OFFSECS PYRO ~I (2) - SAFE

-34-

PROMonitor VMAB

If lt25 vdc go to EMERGPOWER DOWN

34 F 37 OOEPCM BIT RATE - LOWATT DB - MAXEMS MODE - STBYEMS FUNC - OFF

Go To EARTH ORBIT ENTRY pg _--40-__

-36-

8 SPS THRUSTING PREPCYCLE CRYO FANSSPS GAGING - ACI (ver~fy)

PUG MODE - NORM (venfy)BMAG MODE (3) - RATE 2tv CG - CSMCMC MODE - FREEAUTO RCS SEL (16) - MNA or HNB

(hftoff conbg)SC CONT - CMCAUTO

9 MNVR TO PAD BURN ATTV62E

10 V49E

11 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLESPRO

12 F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) PRO(HAN) SC CONT - ses

MNVR to 14

06 18 AUTO MNVR TO FDAI RPY ANGLES13

14 F 50 18 REO TRIH TO FDAI RPY ANGLES(TRIM) Go to 12(BYPASS) ENTR

15 BORESIGHT STAR CHECK

16 V37E 40EOPT PWR - OFF

17 F 50 18 REQUEST MNVR TO FDAI RPY ANGLES (01deg)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CHCAUTOPRO to 18

(MANDAP) BMAG HODE (3) - RATE 2SC CONT - CMCHOLDMNVR to 19

(HANseS) se eONT - sesMNVR to 19

-35-

54 NORMAL DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL ~V

1 V37E 30E

2 F 06 33 GETI (hrm~nOlsec)

(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

3 F 06 81 ~VXYZ (LV)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

( lfps)

4 F 06 42 HAHP~V (1nmlfps)Record W

(ACCEPT) PRO -----(REJECT) Rese1ect P30 or P27 Load new pa~am

5 F 16 45 MTFIMGA (marksmln-secOldeg)MGA -00002 If ~ lMU not a1~gned

SET DETPRO

6

7

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY v1v - OFFCAB PRESS REL v1v (2) - NORMcb ELS (2) - close (verify)cb SECS ARM (2) - close (ver~fy)

cb SECS LOGIC (2) - close (verlfy)AUTO RCS SEL CM (12) - ~mA or MNB

(l~ftoff conf~g)

ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM AampB - off (ctr)

18

-37-

06 18 AUTO MNVR TO FDAI RPY ANGLES (01 0)

19 l 50 18 REOUEST TRIM MNVR TOALIGN SIC ROLLGDC ALIGN

FDAI RPY ANGLES(010

)

+54-00m(-06-00)

TIG-5mJn

5500m(-0500)

TVC CHECK amp PREPcb STAB CONT SYS (all) - closecb SPS (12) - closeATT DB - MINRATE - LOl~

LIMIT CYCLE - ONMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE 2ROT CONTR PWR DIRECT (2) - OFFSCS TVC (2) - RATE CMD

If SCS SCS TVC (2) - AUTO SC CONT - SCS ~

TVC GMBL DRIVE PampY - AUTOMN BUS TIE (2) - ONTVC SERVO PWR 1 - AC1MNA

2 - AC2MNBTRANS CONTR PWR - ONROT CONTR PWR NORMAL 2 - ACRHC 2 - ARMED

HORIZ CHK - HorJz on 12deg wJndmlmark (LJffiJt +3 0 PNGCS GONO GO)

If NO GO set tw 180 0 180deg0 0

Track horJz wJth 24deg wJndow markAt TIG-2 mJn Ahgn GDC

PRIMARY TVC CHECKGMBL MOT P1-Y1 -STARTON(LMP confJrm)

If SCS verJfy Thumbwheel TrJmTHC - CWVenfy NO MTVC

SEC TVC CHECKGHBL MOT P2-Y2 -STARTON(LMP confJrm)SET GPI TRIHVenfy MTVCTHC NEUTRALGPI returns to 00 (CMC) or trJm (SCS)ROT CONT Pl~ NORM 2 - ACDC

(TRIM) Go to step 17(BYPASS) BMAG MODE(3) - ATTIRATE2 (ver1fy)

ENTR

-38-

20 F SO 25 00204 GMBL TEST OPTION(ACCEPT) SC CONT - GMC (ver~fy)

PROMonitor GPI Response

0020-2000020-200Tr~m

TEST FAIL SC CONT - SCS SCS TVC (2) - AUTO

(REJECT) ENTR

21 06 40 TFIVG~VM (m~n-sec1fps)

PROG ALM - TIG s1~pped

V5N9E 01703

KEY RLSE To 21 ROT CONTR PWR DIRECT (2) - MNABSPS He v1vs (2) - AUTO (ver~fy)

LIMIT CYCLE - OFFFDAI SCALE - SOIScb SPS P2Y2 - open (for cr~t burn)

5800(-02 00)

5925(-0035)

59middot 30(-0030)

06 40

59XX(-OOXX)

AV THRUST A(B) - NORMALTHC - ARMEDRlIC (2) - ARMEDTAPE RCDR - GID RESETHBR

DSKY BLANKS

(AVE G ON)EMS MODE - NORMAL

TFIVG~VM (m~n-seclfps)

CHECK PIPA BIAS lt2fps for 5 sec

ULLAGE AS REQ

IF NO ULLAGE DIR ULLAGE PB - PUSH~

CONTROL ATT WRlIC MONITOR AVM (R3) COUNTING UP

5955(-0005)

F 99 40 ENG ON ENABLE REQUEST(AUTO IGN) PRO AT TFI gt0 sec(BYPASS IGN) ENTR to 24

22 0000 IGN

-39-

If SCS - THRUST ON PB - PUSH

06 40 TFCVG~VM (m~n-seclfpslfps)

~F 97 40 SPS Thrust fall ~

~(RESTART) PRO To IGN (RECYCLE) ENTR To TIG-05 sec

SPS THRUST LITE - ONMONITOR THRUSTING

Pc 95-105 pSlaEMS COUNTING DOWNSPS IN3 v1vs (4) - OPENSPS He v1vs tb (2) - graySPS FUELOXID PRESS - 175-195 pSlaPUGS - BALANCED

PROG ALARM V5N9E 01407 VG INCTHC - CW FLY MTVC

ECOEMER SPS CUTOFF J

AV THRUST (2) - OFF

23 F 16 40 TFC(STATIC)VG~VM (mln-seclfps)~V THRUST AB - OFF

SPS IN3 v1vs (4) - CLOSEDSPS He tb (2) - bp

cb SPS P2Y2 - closed (verlfy)TVC SERVO PHR - AC1MNA (venfy)TVC SERVO PWR 2 - OFF

PRO

24 F 16 85 VG XYZ(CM) CUps)NULL RESIDUALSRECORD ~V CTR amp RESIDUALS I1VCEMS FUNC - OFF VGXEMS MODE - STBY VGYBMAG MODE (3) - RATE 2ATT DB - MAX VGZTRANS CONT PHR - OFF

PRO

25 F 37 V82E

26 F 16 44 HAHPTFF (lnmm~n-sec)

R3-59B59 HP gt494 nmPRO

27 F 37 OOE

-40-

55 EARTH ORBIT ENTRY

1 Venfy CMSMR __

P_shyY_-

SEP ATT(180deg)

(0deg )

2

3

4

EMS INITIALIZATIONEMS FUNC - RNG SETSET RNG TO PAD DATA RNGEMS FUNC - VA SETSlew scroll to pad data VIOEMS FUNC - ENTRY

RSI ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on(up)GDC ALIGN PB - PUSH amp HOLDYAW tw - Pos1tion RSI thru 45deg amp

back to LIFl UPGDC ALIGN PB - RELEASEEMS ROLL - OFFAl1gn GDC to lMU

PWR REDUCT (Norm Deorb Only)HGA PWR - OFFFC PUMPS (3) - OFFVer1fy s1ngle suit compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - Lowcb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2)-openlOb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MAN

-41-

P61 - ENTRY PREP

5 V37E 61E05 09 01427 - ROLL REVERSED05 09 01426 - IMU UNSAT

6 F 06 61 IMPACT LAT LONG liDS UPDN (+-)(01 0

010

+00001)

PRO

PAD VALUESLATLON==G------liDS UP DN _

7 F 06 60 GMAXV400KGAMMA EIRecord

GMAXV400K----GAMMA EI _

PRO

8 F 06 63 RTOGO (1nm) PAD _VIa (fps) PADTFE (mln-sec) ----Compare wlth MSFN for PGNS GONO GONO COMM SET RTOGO amp VIO IN EMS amp

INITIALIZE(ACCEPT) PRO(RECALC) V32E to 8

-42-

P62 - CMSM SEP amp PRE-ENTRY MNVR

9 F 50 25 00041 REQUEST CMSM SEPSC CONT - SCSFREEYAW - 45deg out-of-plane (left for RCS

nght for SPS)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE2PRIM GLY to RAD - BYPASS (verlfy)SECS LOGIC (2) - on (up)MSFN conflrm GO for PYRO ARMSECS PYRO ARM - ARMMN BUS TIE (2) - ON (verlfy)CMSM SEF (2) - ONCSMLM FNl SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 pSlaCM RCS LOGIC - OFFSECS PYRO ARM - SAFEMonltor VMAB

If lt25vdc go to EMERG POWERDOWN Pg E6-1AUTO RCS SEL AlC ROLL (4) - OFFAUTO RCS SEL CM 2(6) - OFFAUTO RCS SEL CM 1(6) - MNA or MNBYAW back to 00

PITCH TO ENTRY ATTROLL 0deg (LIFT UP)PITCH - HORIZ on 317deg MARK (400K)YAW 00

ATT DB - MAXMAN ATT (PITCH) - ACCEL CMDEMS DATA - VerifyEMS FUNC - ENTRY (verlfy)EMS MODE - NORMALMAINTAIN HORIZ TRK

PRO (Act ENTRY DAP)

10 F 06 61 IMPACT LAT LONG HDSDN(010 010 -00001)

PRO

11 FOSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axlS beyond 45deg of Vel vector)

-43-

P63 - ENTRY INIT

12 06 64 GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PWR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRHORIZ CKP~tch error needle goes toward

zero approach~ng 05G t~me

MAN ATT (PITCH) - RATE CMDIf CMC ~s GO

BMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS FLY BETA If CMC NO GO ~

SC CONT - SCS~

FLY EMS RCS Deorh Roll HDS UPTRACK HORIZ w~th 29deg w~ndow mk

P64 - ENTRY POST 05G

13

05G t=elt+0___)

06 68

RTOGO AT 05G AGREES WITH EMS - venfyHORIZ CK05E Lt - on (EMS start)

No EMS start w~th~n 3 secsEMS MODE - BACKUP VHF RNG 05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds L~ft DN

NNVR L~ft DNEMS GONO GO

G-V Plot w~th~n llm~ts

Rng ctr dwn 60 + 7 durlng 10 sec per~od

Mon~tor G-meter forconvergence wlth pad data (Do)

(Vlt27K fps) Go To 17

-44-

P65 - ENTRY - UP CONT (Vgt27K fps)

14 F 16 69 BETA (01deg)DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT~

SC CONT - SCS FLY EMS

PRO

15 06 68 BElA VI HOOT (01deg fpsfps)(VltVL +500 fps amp RDOT Neg) Go To 17

p66 - ENTRY - BALLISTIC (DltDL)

16 06 22 DESIRED GMBL ANGLES RPY (01deg)Mon~tor hor~z +12deg of 317deg mark

P67 - ENTRY - FINAL PHASE (02G)

17 0666 BETACRSRNG ERRDNRNG ERR (Oldeglnmlnm)KEY VERBRecord DNRNG ERR _KEY RLSEL~m~t +100nm from PAD DRE

Mon~tor l~ft vector on RSI amp FDAIF 16 67 RTOGOLATLONG (Vre1=1000fps)

(lnm 010 01deg)SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOlfflMon~tor altimeter

Go To EARTHLANDING pg _I4L5__

-45-

56 EARTHLANDING

90K STEAM PRESS - PEGGED50K CABIN PRESS REL vIv (2) - BOOSTENTRY

SECS PYRO ARM (2) - ARM

40K(90K + 63s)

CM UNSTABLE RCS CMD - OFF ~ 40K APEX COVER JETT PG-PUSH DROGUE DEPLOY PG - PUSH (2 secafter apex cover Jett)

30K ELS LOGIC - ON (up)ELS - AUTO

24K RCS hsable (auto)(90K+92s) RCS CMD - OFF

Apex cover Jett (auto)APEX COVER JETT PB - PUSH

(WAIT 2 SECS)Drogue parachutes deployed (auto)

DROGUE DEPLOY PB - PUSH~

If Drogues FallELS - ~ ~Stablllze CM 5K MAIN DPLY PB - PUSHELS - AUTO

235K Cabln Pressure lncreaslng (Drogues + 50s)If not lncreaSlng by 17K CABIN PRESS REL vlv (RR) - DUMP

-46-

10K Maln parachutes deployedMAIN DEPLOY PB - PUSH (wlthln 1 sec)VHF ANT - RECYVHF AMA - SIMPLEXVHF BCN - ONCABIN PRESS REL v1v (2) - CLOSEDIRECT 02 vlv - OPENCM RCS LOGIC - on (up)CM PRPLNT - DUMP (burn audlb1e)Monltor CM ReS 1amp2 for He press decrease

NO BURN or PRESS DECREASE USE BOTH RHCs DO NOT FIRE PITCH JETS

CM PRPLNT-PURGE (to zero He press)CM RCS He DUMP PB - PUSH RHC (2) - 30 sees NO PITCH k

STRUT LOCKS (2) - UNLOCK

cb FLT amp PL BAT BUS ABampBAT C (3) - closecb FLT amp PLT MNA amp B (2) - opencb ECS RAD HTR OVLD (2) - opencb SPS PampY (4) - open

3K CABIN PRESS REL v1v (RH) - DUMP (after purgecompleted)

FLOOD Lts - POST LDGCM RCS PRPLNT (2) - OFFROT CONTR PWR DIRECT (2) - OFF

800 CAB PRESS RELF vlv - CLOSE (latch off)MN BUS TIE (2) - OFF

AFTER LANDINGcb MAIN REL PYRO (2) - closeMAIN RELEASE - on(up)

Go to POSTLANDING pg _47L-__

I

2

3

-47-

57 POSTLANDING

STABILIZATION VENTILATION COMMUNICATIONS

DIRECT 02 vlv - CLOSE

Stablllzation after landlngELS - AUTO (verlfy)cb MAIN REL PYRO (2) - close (venfy)MAIN RELEASE - on (up) (verlfy)S~CS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb BAT RLY BUS (2) - open

No contact w1th recovery forcesVHF AM AampB - off (ctr) ~

VHF AM Rev ONLY - A cb PL VENT - closecb FLOAT BAG (3) - closecb UPRIGHT SYS COMPRESS (2) - closeIf Stable II

FLOAT BAG(3)-FILL t1ll 2 m1n afterupr1ght then - OFF

VHF AM AlB amp BCN - OFF whlle lnvertedIf Stable I

After 10 M1n Coollng Per1odFLOAT BAG (3) - FILL 7 mln then OFF

Post Stab1lizat1on And Ventllat10nPL BCN LT - BCN LT LOWPL VENT vlv - UNLOCK (Pull)Remove PL VENT Exh CoverPL VENT - HIGH or LOWPL DYE MARKER - ON (swlmmer comm)Release foots traps and_restralntscb MNA BAT BUS A amp BAT C (2) - opencb MNB BAT BUS B amp BAT C (2) - opencb FLT amp PL BAT C - opencb PYRO A SEQ A - opencb PYRO B SEQ B - open

EACH HR - CHECK DC VOLTSgt 275 V If Notmiddot cb FLT amp PL-BAT BUS AampB (2) -open cb FLT amp PL BAT C (1) - open GO TO LOW POWER CHECKLIST

Unstow and lnstall PLV DISTRIB DUCTDeploy grappllng hook and 11ne 1f req

4

-48-

Post Landing Communlcatl0nsVHF ANT-RECY (venfy)VHF BCN - ON (verlfy)

If no contact ~lth recovery forcesperform VHF BEACON Check

MONITOR VHF BEACON transmlSSlonnth VHF AM B Rcvr andor Su)vlval

TransceiverkVHF Beacon not operatlng ~connect Surv~val TranscelVer to antcable behlnd VHF ant access pnland place radio ln BCN mode

LOW POHER CHECKLISTVHF BCN - OFFVHF AM (3) - RCVFLOOD Lts - OFFVHF AM AampB - off (ctr)VHF AM RCV ONLY - A (venfy)COUCH LIGHTS - OFFPOSTLANDING VENT SYS mlnlmlze useSURV RADIO - plug mto VHF BCN ANT cableconn behind VHF ant acess pnl amp turn radloon l-n BCN mode

EGRESS PROCEDURES

CMPCDRLMPCDR

CMPCDRCMP

LMPLl1PCDR

STABLE IDlsconnect Umblll-calsNeck darn onCenter couch - 270 0 positionArmrests stowedConnect raft to SIC l-f desl-red wlth

green lanyardConnect raft ~hl-te lanyards to SUltS amp

lnflate water wlngs when eXltl-ngHATCH PISTON PRESS vlv - PRESS (Outbd)Slde Hatch openedPL VENT - OFFcb Pnl 250 (all) - openEgress with 11feraftPut hardware klt outEgress

or CDIPALL

CMF

CDRCMF

CDR

LMF

CMFCMP LMFCMP

UlP

CDR

-49-

STABLE IIcb CREW STA AUDIO (3) - openD~sconnect umb~1~ca1s

Release foots trapsRelease restra~nt harnessCouch seat pans (3) - 170 0 pos1t10nArm rests stowedSurv1va1 k~ts removed from stowageConnect life raft ma~n1~ne to CDR or SicConnect f~rst wh~te lanyard from

11fe raft to suitConnect th~rd wh~te lanyard from

l~fe raft to SU1tConnect rucksacks together to yellow

lanyard on raft bagPRESSURE EQUALIZATION vlv - OPENRemove and stow fwd hatchEX1t feet f1rst w1th rucksacks when clear

of siC 1nflate water w1ngs and raftExit feet f1rst when clear of SiC

1nflate water w1ngsEX1t feet f1rst when clear of sic

1nflate water w1ngs

-50-

60 TLI ABORTS

TLI Aborts are conta~ned ~n the ESD s~nce the bulk of the funct~ons

concern entry preparat20ns and performance Th~s allows a s2nglesource of procedures for procedure rev2ew val~dat~on checkout andtra~n~ng These procedures ~ncorporate TLI preparat20ns as found ~n

reference 6 w~th the TLI Abort Procedures and these t~e 2nto normallunar return Entry Procedures found ~n sect20n 5 The guidel~nes

for th~s cont2ngency are spec2f2ed 2n reference 7

In2t2al preparat~ons for TLI pos2t20n the necessary system sW2tches2n add~t~on to perform~ng an EMS ~V test and a GDC al~gnment Afterthe DET ~s set for mon2tor2ng TB6 the CMP ~ncreases the 12ght levelof the LEB DSKY to max~mum and returns to the h2s couch Th2s 2Sdone so that the LEB DSKY can be observed ~n the event sunl~ght orreflect20ns wash out the ma2n d2splay panel DSKY dur2ng cr2t2calmaneuvers The crew then straps ~n and prepares for mon2tor~ng TB6as 2nd2cated by the SII SEP L~te The t2mes se~uence of procedures2S keyed on th~s d~splay and ~ncludes the DET START funct~on andSIVB IGNITION Dur2ng the burn the crew mon2tors the FDAIs foratt~tude excurs20ns and abnormal rates report~ng status checks toM~ss2on Control at d2screet t~mes dur2ng the maneuver Upon SIVBSHUTDOWN the eMP records the DSKY d~splayed performance parametersand awa2ts ground conf2rmat~on

The rat~onal for TLI aborts ~s descr~bed 2n reference 7 A summar2shyzat20n 2S extracted to prov2de background and gu2de12nes 2n th2sdocument The abort procedures cover aborts 10 m2nutes after conshyt2ngent SIVE shutdown and aborts 90 m2nutes after normal SIVE shutshydown t2me

The 10 m~nute TLI abort ~s des2gned to be used dur~ng TLI ~n theevent a spacecraft problem develops Wh2Ch can result 2n catastrophe2f ~mmed~ate act~on 2S not taken If the s~tuat20n perm~ts the crewshould always allow the SIVB to complete TLI at wh~ch t~me the groundand crew can perform a malfunct~on analys~s to determ~ne ~f an abort~s adv~sable If a fa~lure occurs that necess2tates the shutdown ofthe SIVB and the ~u~ck return of the crew to earth th~s abort ~s

des~gned to be as ~nsens~t~ve to execut~on errors as poss~ble andst21l be targeted to m2dcorr2dor The burn att~tude w~th the f~ed

hor~zon reference ~s a constant value for any shutdown t~me Theburn durat~on 2S a funct20n of shutdown t2me and 2S ava21able fromcrew charts S~nce the pr~mary purpose of th~s abort ~s to returnto earth as qU2ckly as poss2ble there are no restr2ct20ns as toland~ng locat~on However ~f the t~me to EI is greater than abouttwo hours a midcourse correct20n should be ant~c~pated

The 90 m2nute TLI abort 2S to be used 2f a cr2t2cal subsystem malshyfunct~on ~s determ2ned and the dec2s~on to abort ~s made after the

-51-

TLI cutoff and before TLI cutoff plus approxlmately 80 m1nutesTh1S allows suff1c1ent separatlon and procedural t1me to set upfor the SPS deorb1t burn performed at about TLI + 90 Note thatgenerally the deorb1t burns w1ll be performed a fe11 m1nutes beforeTLI + 90 accord1ng to crew charts shown In reference 8 The no-comm except10n requ1res that 90 m1nutes be the 1nput t1me of 19n1shytlon for P-37 (onboard return-to-earth abort program) so that onshyboard calculatlons can correspond w1th ground calculat10ns to computethe CM land1ng p01nt Th1S TLI abort lS des1gned so that returnfl1ght t1me does not exceed 18 hours and abort ~V does not exceed7000 fps ThlS abort can be performed uSlng chart ~Vs and attltudesand the earths hor1zon serves as a suff1c1ent reference The maneushyver lS targeted to ach1eve the mldcorr1dor entry target Ilne andtlmed to result 1n a deslgnated recovery area

It 1S ObV10US for abort deC1S1ons early 1n the TLI + 90 m1nute t1meshyframe that a GampN SPS burn should be performed In order to keep theTLI abort procedures cons1stent and w1th emphasls on slmpl1c1ty theprocedures here reflect a SCS SPS abort burn to cover the full abortdec1s1on t1meframe

A m1dcourse correct1on for corr1dor control after a TLI abort may bedeS1red 1f the SPS burn d1d not meet expectat1ons The TLIabortprocedures 1n th1S sect10n adapt to the normal lunar return tlmel1neand procedures pr10r to the f1nal MCC

-52-

61 TLI PREPARATION PROCEDURES

GET = 150

CRO AOS(___)

CRO LOS( )(22142)

5100

Don Helmets amp Gloves

XLUNAR - INJECT (verify)EDS PWR - on (venfy)EMS FUNC - OFF (verlfy)EMS MODE - STBYEMS FUNC - IW SETVHF RNGEMS MODE - NORMALSet ~V indo to +15868 fpsEMS FUMC - ~V Test

SPS THRUST Lt - onoff (10 sec)~V lnd stops at -01 to -415

EMS MODE - STBYEMS FUMC - ~V SETVHF RNGSet ~VC

EMS FUNC---~~V=----

GDC ALIGNFDAI Select - liZcb SECS LOGIC (Z) - close (verify)cb SECS ARM (Z) - closeSECS LOGIC (Z) - on (up)MSFN Conflrm GO for PYRO ARM (If pass)SECS PYRO ARM (Z) - on (up)TRANS CONTROL PWR - ONROT CONTR PWR NORMAL (Z) - ACDC(verlfy)ROT CONTR PWR DIRECT (Z) - MNAMNBLV INnGPI - SIISIVB (venfy)LV GUID - IU (venfy)cb DIRECT ULLAGE (Z) - closedSet EVENT TIMER to 5100Begin MONITOR For TB6

CMP to Couch

TB 6 - SII SEP Lt on (TIG-9 mln 38 sec)KEY V83E

SET ORDEALFDAI Z ORB RATE at 180 0 0SII SEP Lt out (38 sec later)Start DET COUNTING UPSC CaNT - SCS (verify)MONITOR LV TANK PRESS

~P lt 36 psid (OXID gt FUEL)~P lt Z6 psid (FUEL gt OXID)

EMERGENCY CSMLV SEP UP TLM CM - BLOCK (verify)UP TLM IU - BLOCK (venfy)

-53-

+45degPY))0middot sec PY

lOK nmltHAlt25K nm

Two phas~ng mnvrs two SPS mnvrs to circular~ze at 150 nmearth orb~t

CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ssion 4K nmltHAltlOK nm CSM amp1M - Two phasing mnvrs two SPS mnvrs to circularize at 150 nm earth orb~t CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ss~on

CSM amp 1M - Two phas~ng mnvrs APS burn todepletion th~rd phasing mnvrSPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn tosem~sync orb~t

25K nmltHAlt40K nm CSM amp 1M - Two phasmg mnvrs APS burn to depletion third phas~ng mnvr SPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn to sem~sync orbit HA)40K nm DPS ava~l - DPS LOll circularize with SPS

DPS not ava~l - Lunar flyby or CSM only to lunar orbit (if reqd gtV lt4000 fps)

V37E 47E (check b~as) Record -=--rshy(Limit 98 fpsmm)

( 1fps)tVXYZN62EVIHDOTHPAD (fpsfpslnm)MONITOR VI ( ) at ECO

SCS TVC SERVO PWR 1 - ACIMNA2 - OFF

TAPE RCDR - CMD RESETHBREMS MODE - NORMAL

SIr SEP Lt - ONTLI Inhib~t S~gnals w~11 not be honored after 5942

SIVB ULLAGE BeginsSII SEP Lt - off (TIG - 18 sec)SIVB FUEL LEADSIVB ULLAGE d~scont~nues

LV ENG I Lt - onSIVB IGNITION ( GETI)LV ENG I Lt - off - -shyMONITOR THRUST amp ATTITUDEMONITOR LV TANK PRESSSIVE ECO (Lt on) (BEGIN TB7)

EMER SIVE CUTOFF AT 6 SEC PAST BURN TIME IF VI ATTAINEDTHC CCW ampNEUTRAL IN 1 SEC or SIISIVB sW - LV STAGEPremature Shutdown HAlt4K nm CSM amp 1M -

5700

58205836

F 16 835800

F 16 62

5838594259525955595900000002SUNRISE(___)

HAW AOS(__=_) KEY VERB (freeze d~splay)

SIVB ATT HOLD 20 sec amp BEGIN VENTINGSIVB NNVR TO ORB RT (HDS DN) (3middot sec)

Record VI -c---HDOT _

HPAD _

KEY RLSEF 16 62

F 16 83

HAW LOS(__=-)

KEYmiddotRLSE~VXYZ (lfps)

Record ~VX---_

~vy

WZ--

AVC---_

TAPE RCDR - off (ctr)EMS MODE - STBYEMS FUNC - OFFSECS PYRO ARM (2) - SAFE

PRO

BURN STATUS REPORT

____--~TIG

BT------VGX____-R

-----P----_Y

REMARKS

_____VI

______--HDOT______--H______---AVC______---FUEL_______OXID

_______UNBAL

F 3708=00 OOEGOS AOS CMP TO LEB

(-=-=-)

0000

0003

0005

0014

0100

-55-

62 TLI 10 MIN ABORTSECS LOGIC (2) - on (up)SECS PYRO ARM (2) - ARM

TRANS CONTR - CGH (4 sec) amp +XDET RESET (verlfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS GMD-ON

TRANS GONTR - neutral then +X for10 sec

SIVBGPI s~ - GPIExcesslve rates 6V THRUST A - NORMAL SPS THRUST - DIRECT When rates damped 6V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

TRANS CONTR +X - OFFV37E OOE

PITGH UP to LOGAL VERT (+X axlSto~ard the earth)

RATE - LOWBMAG MODE (3) - ATTIRATE 2EDS PHR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SEGS ARM (2) - opencb EDS (3) - open

TRANS CONTR -X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (180deg)P (199deg)Y (0deg)

RETRO UPDATEGETI _

JV _VG

Jtb ---GET 400K _

05G _GET DROGUE _

ENTRY P _R _

Y_--

0945

-56-

ALIGN HORIZ ON RET +1 MKGMBL CHECK (T11lle Pentattlng)MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conflnn)cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FUMC - JV SETVHF RNGSET JV from chartE~S FUMC - JVEMS fODE - NOIDlAL

lV THRUST A - NORMALV37E 47E (THRUST fONITOR)

F 16 83 lVXYZ (1 fps)

0950

1000

NOTE For aborts durlng 1st mln of TLIKEY V82E F 16 44 (HaHpTff)Burn untll Hp lt 19NM

TRANS CONTR +X

THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN JV reqdJV THRUST (2) - OFFReport cutoff

cb SPS P2 Y2- closeGfBL MTRS (4) - OFF (LMP Confinn)TRANS CONT PWR - OFFTVC SERVO PWR (2) - OFFMN BUS TIE (2) - OFFcb SPS P1amp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREIf est time to EIltOl5500 omlt fCC andenter the SUPERCIRC CKLIST as early as pos-slb1e Pg ~2~3~ __If est time to EI)Ol5500 anticlpate afCC Enter the ENTRY PREP CKLIST at step 9pg 18

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

-2tl C

l I W gt- ~-4

z laquo I I- 0 -6

l- I J u gt- ~-8

z w w -10

~_ONSANT

9O

VER

SHO

OT

BOU

ND

ARY

LIF

TV

EC

TOR

OR

IEN

TATI

ON

LIN

E

SH

ALL

OW

TAR

GE

TLI

NE

STE

EP

TAR

GE

TLI

NE 12

gU

ND

ERSH

OO

TBO

UN

DAR

Y

RE

EN

TRY

CO

RR

IDO

R

I ~ I

-12 24

26

28

30

32

34

RE

EN

TRY

VE

LOC

ITY

VE

1-F

TS

EC

Ch

art

1

36

3B

6-i

~

5CM

CC

ON

ST

NT

DR

VI z gt

~

I4

0 Cl W

I

gtamp

J+

-I

-

J Cl z

2U

l z 0_bull

bull-1

+-

u ubullbull

~r

U

)

2829

JOn

J23

33

43

5IN

ER

TIA

LR

EE

NTR

YV

ELO

CIT

YA

T4

00

00

0fl

VE

I-F

TS

EC

Ch

art

2

J63

73

8X

03

-i- rtREQUIRED PITCH GIMBAL ANG LETO OBTAIN HOR-IZON AT 317

DEGREES IN wiiiiDOW

260

z~I- ~ i5 24000

1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

-I

-1-

NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

I LU HD~-

LUHD

lt0 120UJ0

~

80 HOLD PRESENT TRIMgt LU HD013

~Y~HOIgtlt

TOP OF WINDOWa 40to

31 7 SCRIBEaaI

80 TTOM OF WINDOWi= 0

0--ltoa

-40t-z

~~~Uw w u lt0 -80

HOLO PRESENT TRIlJCl

LOHU0 lt0

J gt -120 HOLD 059 TRIMlt0 z

LDHUlt0 FIELD OF VI S10 NLDHU LIFT-DOWNHEADS -UPLUHD LIFT-UP HEADS-DOWN

~~H~-160 q - P63 LIMITI- NOrE-VALIO ONLY FO~t~--

LUNAR RETURN VELOCITY

plusmnl8020 244middot 8 12 16

TIME TO 400K FT ALTITUDE-MIN

4

P37

LONG

ITUD

ECO

RREC

TION

TOOB

TAIN

1350

NM

ENTR

YRA

NGE

Ugt

UJ

cgt

3z 0 I- u U

J0

0

0

2I

U~

UJ

cgt

I

gtI- U

gt z 0 J ltJ

1 -0

340

344

348

352

356

364

368

x10

3

CMC

INER

TIAL

VELO

CITY

AT40

0KAL

TITU

DE-

FTS

EC

Ch

art

5

I l I

o

20 100 -40

-10

-50

30

-20

--

+

-BB

A+

lrBB

A

=----

-----

t~I

AB

SA_

-04

0A

AV

Z=

-()4

D_

+

j

+

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tfJ i~

plusmniff

--d~~tj

h-

Ir

at

it

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60--

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2030

NOTE

40

NO

MIN

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RET

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90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 11: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

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40 EARTH ORBITAL DEORBIT AND ENTRY TECHNIQUES

As outl~ned ~n reference 5 a nom~nal PGNCS entry from earth orb~t ~s

based on a preparat~on t~me of 2 hours and 40 m~nutes ~nclud~ng 2n~ght passes Th~s t~me ~ncludes approx~mately 20 minutes before thef~rst n~ght pass after the CMC update and PAD data have been rece2vedTh~s t~e also 2ncludes approx2mately 20 m2nutes after the secondn~ght pass to allow suffic~ent t2me to prepare for retrof2re after theIMU f2ne a12gnment It has been determ2ned coarse a12gnment accuracy~s adequate for retrof~re and entry and undoubtedly other funct20nscould be om2tted depend2ng on the c2rcumstances for the dec2s20n toreenter Descr2bed here2n are the nom2nal earth oro2tal entry proshycedures w2th pert2nent comments on system va12dat20n for real timeacceptance dec~s20ns

After the entry dec~s~on is made the crew transfers the PGNCS fromthe standby to the operate mode and rece~ves a CMe update w~th P27Next the maneuver PAD update ~s v02ced up and the 2n~t~al entry mode~s determ~ned During the ~n~tial n~ght pass the IMU or2entat~on ~s

estab12shed uS2ng P51 star s~ght2ngs to obta2n a REFSMMAT The preshyferred or~entat~on opt20n ~n P52 2S then selected to coarse a12gn theIMU uS2ng the des2red entry REFSMMAT determ2ned by MGG-H The GOO ~s

now al~gned to the IMU 2n preparat~on for an IMUSes dr~ft check Ifthe GOO ~nd~cates the ses dr2ft rate exceeds 10 degrees per hour ~n

any ax~s the check ~s repeated on the other BMAGs to estaol~sh if theGOO or Just the single set 2S unusuable Var20us sytem checks as 12sted2n sect20n 51 are performed as necessary cons2stent w2th the t2me12ned2ctates of the maJor act2v2t2es Included 2n these checks are the EMSself-tests and the dV counter test The latter requ2res the spacecraftbe placed ~n dr2ft2ng fl2ght w~th the funct20n sW2tch 2n the dV pos2t~on

If the counter reg2sters a change of more than 25 feet per second w2th2n100 seconds the scroll and counter are unre12able for mon2tor2ng thedeorb2t burn and entry rang2ng If the EMS self-test fails and t2medoes not allow further analysis a 5555 ERE entry 1S planned as thePGNGS backup entry mode After complet2on of these checks the entryPAD lS prov1ded by MeG-H The crew then selects the external dVprogram P30 and the appropr2ate deorb1t tbrust1ng program p40 or P41Dur2ng th2s per2od wh2ch 2ncludes the f1nal n2ght pass P52 may beselected to ver2fy the IMU a12gnment Since the retro att2tude hasbeen computed so that a w2ndow mark c01nc2des w2th the hor2zon atGETI th2s serves as the conclus2ve check on the PGNCS At 5 m2nutesbefore retrofire the att2tude check 1S made by ver1fY2ng that the 12degree scr~be 12ne ~s w2th2n 3 degrees of the hor2zon If not thePGNeS has fa2led and the ses 2S used for att2tude reference and the

V counter for burn durat~on control S2nce the ses att~tude wasa12gned to the IMU a real~gnment ~s necessary This ~s accompl~shed

by manually maneuver2ng the spacecraft to ma~nta1n the 24 degree wlodowmark on the hor2zon and releas1ng the GOO a12gn button at TIG - 2 m2nutes

-14-

Upon complet~on of the burn the tN res~duals are burned to W~th~n

02 feet per second If the PGNCS ~V counter or est~mated burnduration are ~n d~sagreement ~t must be estab1~shed whether suff~shy

c~ent veloc~ty has been suppl~ed to put the land~ng po~nt in thefootpr~nt The PGNCS data w~ll be used ~f ~t ~s conf~rmed by oneother source if not the ~V counter w~11 be used ~f ~t ~s conf~rmed

by the burn durat~on t~me If add~tional ~V ~s necessary the data~s ava~lable to the crew on an onboard chart found ~n Sect~on 80

Post burn entry preparat~on requ~res EMS ~n~t~al~zation RSI al~gnshy

ment and pre-separat~on funct~ons The crew then selects the ~n~t~al

entry program P61 and records the d~sp1ays as a check aga~nst PADdata Upon complet~on of these checks P62 ~s entered The crewmanually or~ents the spacecraft to the separat~on attitude and yaws450 to ~nsure aga~nst possible CM 8M recontact After separat~on

the spacecraft ~s maneuvered to the reentry tr~m att~tude wh~ch

places the hor~zon on the 3170 w~ndow mark at EI Shortly thereshyafter ~n P62 the entry DAP is act~vated and P63 in~t~ated Dur~ng

th~s t~e MCC-H has computed a postburn update and ~t ~s vo~ced tothe crew ~f d~fferent from preburn values The EMS scroll and rangecounter w~ll be adJusted accord~ngly ~f t~me perm~ts A f~nal PGNCScheck pr~or to 05g may be mon~tored at th~s t~e w~th the CMC modein free and the manual att~tude p~tch ~n acceleration command wh~le

the hor~zon reference ~s held the p~tch error needle w~ll decreaseto zero as EI ~s reached At RET 005g the EMS mode sw~tch ~s

turned to manual the entry 005-g sw~tch and EMS roll sw~tch areturned on and the spacecraft control sw~tched to CMC to beg~n DAPcontrol At the PGNCS 005-g ~ndicatwn the program change fromP63 to P64 ~s mon~tored and the t~e vo~ce recorded At th~s t~me

the EMS range counter check ~s made dur~ng the 10 second per~od

follow~ng EMS 005g Dur~ng th~s per~od the counter should countdown 40 + 10 naut~cal m~les At PGNCS 02-g ~nd~cation the changefrom P64-to P67 ~s monitored and the ~splay may be held by key~ngVERB ~n order to record the init~al downrange error d~splay andcompare ~t to the PAD value The PGNCS has fa~led ~f the two do notagree w~th~n + 100 naut~cal m~les In the event P67 has not appearedwhen both the-g-meter and the scroll ~nd~cate greater than 05g thePGNCS has sim~lar~ly fa~led In e~ther fa~lure the SCS is used foratt~tude reference w~th an EMS entry If the checks agree the crewrema~ns w~th automat~c DAP for the rema~nder of the entry

The entry phase ~s essentially over when the relat~ve velocity ofthe spacecraft decreases to less than 1000 feet per second Th~s

~s ~nd~cated ~n P67 when RTGO lat~tude and long~tude are d~splayed

S~nce very l~ttle rang~ng capab~l~ty exists after th~s pOint thespacecraft is or~ented either full l~ft up or down depending onRTGO negat~ve or pos~t~ve and the crew prepares for the earth land~ng

phase

-15-

41 TYP~cal Retrof~re and Entry Sequence of Events

Dec~s~on to reenter

P27 (CMC update)

Retrof~re PAD update

Entry mode dec~s~on

P51 (IMU or~entat~on determlnatlon) durlng f~rst dark per~od

P52 (IMU coarse allgnment)

EMS checks

Entry PAD update

P30 (external AV)

p40 (SPS thrust)

P52 (IMU f~ne al~gnment) durlng second dark per~od

p40 (SPS thrust)

Ign~t~on att~tude check

Retroflre

P61

P62

CMSM separat~on

P63

Postburn PAD update

Entry attltude check

p64 (beg~n DAP control at O05g)

P67 (PGNCS gono go check at O2g)

42

Retrof~re

and

En

try

Alt

ern

atlv

es

Sys

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fa~lure

PGNC

S

PGNC

San

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S

PGNC

San

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Fal

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Fal

lure

aft

er

Fal

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-3m~ns)

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bu

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SCS

bu

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GET

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----

--

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-17-

5 0 DETAILED ENTRY PROCEDURES

In order to comblne slmilar procedures that are common to lunar returnentrles and earth orblt entrles the followlng procedures are dlvldedlnto categorles that allow a mlnlmum of dupllClty ThlS provldes asmaller tralnlng package and more closely resembles the onboard crewcheckllst when comparlson lS necessary

51 Entry Preparatlons for Superclucular and Earth Orbltal Entrles

1~e entry preparatlons are comblned In these procedures andsteps pecullar to elther superclrcular or earth orbltal entrlesare labeled accordlngly The tlme llstlngs In thlS sectlon areappllcable to only superclrcular entries Slnce the earth orbltalentry tlmellne lS a functlon of several varlables as descrlbedIn sectlon 40 and reference 5

-18-51 (Contlnued)

VEHICLE PREPARATION

l-

2

3

4

5

6 -0600h

7 -0535h

8

9

10 -0430h

INITIAL STOWAGE COMPLETED

CMC amp ISS START UP

SCS POWER UP

p51 - IMU ORIENTATION

LOAD DAPV48E 11102 01111 PRO ERO PRO

LAST MCC DECISION

NO COMM - P52 amp NAV SIGHTINGSNOMINAL - P2337 ONBOARD COMPARISON

DON MAE WESTS amp FOOT RESTRAINTS

VHF AM A - SIMPLEX

P 27 (SV REFSMMAT) MNVRamp ENTRY pAD UPDATES

11 -0415h P52 - IMU REALIGN(___) (OPTION 1)

12 P37 (NO COMM ONLY)

13

14

ECS CKS02 SUPPLY REFILLECS Monitor CkEVAP H20 CONT (2) vlvs - AUTOSUIT HEAT EXCH SEC GLY - FLOW

EPS CKS 1 3 4 (5 If reqd)

15 SPS CK (If req d)

16

17

18

RCS CKSSM RCS MOUlt CkCM RCS MOUlt Ck

CampW SYS CK

CMC SELF CK

19

20 -0345h

-03l5h-0300h

21

22

22A

-19-

DSKY COND LT TEST

MIDCOURSE MANEUVERP30 - EXT rVP404l - SPSRCS THRUSTINGMIDCOURSE (17) BURN

NO COMM NAV SIGHTINGS

ffiVR TO ENTRY ATT (Superc1rc only)V62E

V49E

22B F 06 22 DESIRED FINAL GMBL ANGLESLOAD ENTRY ATT PAD ANGLESPRO

22C F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) SC CONT - CMC

BMAG MODE (3) - RATE 2CMC MODE - AUTO

PRO(~N) SC CONT - SCS

MNVR to 22E

22D 06 18 AUTO MNVR TO FDAI RPY ANGLES

22E F 50 18 REQUEST TRIM(TRIM) Go to 22C(BYPASS) ENTR

23 -200hr BORESIGHT amp SXT STAR CHECKOPT MODE - CMCOPT ZERO - OFF

V41 N91E

F 21 92 SHAFT TRUNLoad SXTS angles

41 OPTICS DRIVE

CHECK SXT STAROPT ZERO - ZERO

CHECK BORESIGHT STAR (If ava11)

24 -0135h

25(___)

26

27 -0115h

-20-

P52 - lMU REALIGNRecord gyro torqu~ng anglesRp~----

YIf-7gt-Lno--re-c-ycle PS2If conflrmed use SCS for EMS entry

GDC ALIGNIf drlft gtLOohr change ratesource

FINAL STOWAGEOPTICS (except for hybrid)ORDEALGLY TO RAD SEC - BYPASS (verlfy)CooL pnl lnstalledY-Y struts (2) extendedStow Data Box R-12

EMS CHECKEMS FUNC - OFFcb EMS (2) - closeEMS MODE - STBYEMS FUNC - EMS TEST 1 (walt 5 sec)EMS MODE - NORMAL (walt 10 sec)

Check ind lts - offRANGE lnd - 00Slew halr1ine over notch

In self-test patternEMS FUNC - EMS TEST 2 (walt 10 sec)

05G It - on (all others out)EMS FUNC - EMS TEST 3

05G It - onRSI Lower It - on (10 sec Qater)Set RANGE counter to 58 nm+OO

EMS FUNC - EMS TEST 405G It - on (all others out)G-V trace w~thin pattern to lwr rt

corner 9GRANGE lnd counts down to 0+02

EMS FUNC - EMS TEST 505G It - onRSI upper lt - on (10 sec later)RANGE md - 00SCrlbe traces vertlcal llne 9g to

022+01ALIGN SCROLL TO ENTRY PATTERN (on

37K ft sec hne)EMS FUNC - RNG SET

G-V scroll assy traces vert llne022g to 0+01

EMS MODE - STBY

28

29

30 -OllOh

-21-

~V TEST (Deorb~t only)EMS FUNC - ~V SETVHF RNGSET ~V ~nd to 15868 fpsEMS MODE - NORMALEMS FUNC - ~V TEST

SPS THRUST LT - onoff (10 sec)~V ~nd stops at -01 to -415

EMS MODE - STBY

PRIMARY WATER EVAP ACTIVATIONGLY EVAP H20 FLOW - AUTOGLY EVAP STH PRESS - AUTOPRI ECS GLY PUMP - ACI

CM RCS PREHEATNote If sys test mtr 5cd6abcd

all read 39 vdc (28degF) or moreom~t preheat

cb RCS LOGIC (2) - closeCM RCS LOGIC - ONUP T1M CM - BLOCK (ver~fy)

cb CM RCS HTRS (2) - closeCM RCS HTRS - ON (LMP Conf~rm)

(20 mlU or III lowest rdg lS39 vdc) (Moultor Maufpress for press drop)

31 (___) FINAL GDC DRIFT CK (If req I d)If drlft gtlOohr Suspect GDC Do not

use RSI amp FDAI 2

32 -OO5Om

33

34

35

TERM CM RCS PREHEATUP TLM CM - BLOCK (venfy)CM RCS HTRS - OFFCM RCS LOGIC - OFF

SYSTEMS TEST PANEL CONFIGURATIONSYS TEST METER - 4BRNDZ XPNDR - OPERATECM RCS HTRS - OFFWASTE H20 DUMP - OFFURINE DUMP - OFF

LEB LIGHTING - OFF

SEC WATER EVAP ACTIVATIONGLY To RAD SEC vlv - BYPASSSEC COOL EVAP - EVAPSEC COOL PUMP - AC2

36

37

38 -OO45m

-22-

PYRO BATT CKcb PYRO A SEQ A - close (ver~fy)

cb PRYO B SEQ B - close (verify)DC IND - PYRO BAT A(B)

~If PYRO BAT A(B) lt 35 vdc cb PYRO A(B) seq A(B) - open~

PYRO A(B)BAT BUS A(B)TO PYRO~MN BUS TIE - close

cb MNA BAT C - closecb MNB BAT C - closeDC IND - MNBPNL 8 - All cbs closed except

PL VENT - open (ver~fy)

FLOAT BAG (3) - open (ver~fy)

DOCKING PROBE (2) - open (verlfy)EDS BAT (3) - open (ver~fy)

CM ReS HTRS (2) - open

CM RCS ACTIVATIONcb SECS ARM (2) - close (verlfy)cb SECS LOGIC (2) - close (verlfy)SECS LOGIC (2) - ONMSFN conflrm GO for PYRO ARM(~f poss)SECS PYRO ARM (2) - ARMCM RCS PRPLNT 1amp2 - ONCM RCS PRESS - ONRCS Ind sw - eMl then 2

He PRESS 3700-4400 pSlaMANF PRESS 287-302 pSla

SECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFF

P27 amp ENTRY PAD UPDATEGo To Entry Checkllst

Superclrc - pg ~2~3 _Hybnd - pg -----2~9L-__Normal Deorblt - pg __3L5L- _

-23-

52 SUPERCIRCULAR ENTRY

1 SET DET (up to ET)

2

3

4

5

3000(-30-00)

EMS INITIALIZATIONSET RNG TO PAD DATA RNGEMS FUNC - Vo SETSlew Scroll to Pad Data VIOEMS FUNC - ENTRY

RS I ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on (up)GDC ALIGN PB - PUSH amp HOLDYAW Tw - Pos~t~on RSI thru

45deg amp back to LIFT UPGDC ALIGN PB - ReleaseEMS ROLL - OFFA1~gn CDC to lMU

CM RCS RING A CKRCS TRNFR - CMcb CM RCS LOGIC MNB - openAUTO RCS SEL MNB (6) - OFFSC CONT - SCSTest R~ng A ThrustersSC CONT - CMCRCS TRNFR - SMAUTO RCS SEL (12) - MNAMNB

(hftoff conflg)cb CM RCS LOGIC MNB - close

OPTICS PWR - OFFCMP to COUCH

MN BUS TIE (2) - ONTAPE RCDR - REWIND

6 35middot0Om(-25middot 00)

-24-

SEPARATION CK LISTTVC SERVO PWR 1 - AClMNAcb ELS (2) - close (ver1fy)PRIM GLY TO RAn - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY vlv - OFFCAB PRESS REL vlv (2) - NORMGMBL MTRS (4) - STARTABORT SYS PRPLNT - RCS CMD (venfy)SM RCS PRIM PRPLNT (4) - ONVHF 11M (AampB) - OFFHI GAIN ANT PWR - OFFFC PUMPS (3) - OFFVer1fy s1ugle SU1t compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - 10101cb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2) - opencb HTRS OVLD (2) - openPOT H20 RTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANSEC COOL EVAP - RESETSEC COOL PUMP - off (etr)

MtiVR TO CMSM SEP P R ATTSC CONT - SCSCMC MODE - FREEMNVR TO PAD ATTR (0deg)PY----W)

-25-

SUPERCIRCULAR ENTRY (Cont~nued)

1

4100m(-1900)

P61 - ENTRY PREP

V37E 61E

k 05 09 01427 - ROLL REVERSED 05 09 01426 - IMU UNSAT ~

2 F 06 61 IMPACT LAT LONG HDS UPDN (+-)PRO (010

fps +00001)

3 F 06 60 GMAXVPREDGAMMA EIRecord

GMAXV400K----

GAMMA EI _PRO

(01deg fpsOldeg)

4 F 06 63 RTOGO (lnm) PAD _VIO (fps) PAD _TFE(m~n-sec)

Compare w~th ~M~SFN==C~f~o-r~P~GNS GONO GOIf NO COMM Set RTOGO amp VIO In EMS

amp lnltla11ze(ACCEPT) PRO(RECALC) V32E To 4

5 F 50 25

4300m

(-1700)

45 oOm(-1500)

500Om(-1000)

6 F 06 61

-26-

P62 - CMSM SEP amp PRE-ENTRY MNVRCAUTION Call No EXT Verbs In P62

00041 REQUEST CMSM SEPSC CONT - SCSFREE

COMPARE PITCH ATT WITH PAD DATA ---0=-

(W~thLU 5deg)YAW - 45deg OUT-OF-PLANE (LEFT)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTIRATE 2MN BUS TIE (2) - ON (ver~fy)

PRIM GLY TO RAD - BYPASS (verlfy)CM RCS LOGIC - ON (venfy)SECS LOGIC (2) - on (up)SECS PYRO ARM - ARMCMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 ps~a

CM RCS LOGIC - OFFSECS PYRO ARM (2) - SAFEMonltor VMAB

If lt25 vdc go to EMERGPOWERDOWN pg E6-l

AUTO RCS SEL AC ROLL (4) - OFFAUTO RCS SEL CM 2(6)-OFFAUTO RCS SEL CM 1(6)-MNAYAW back to 0degPITCH TO HORIZ TRACK ATT

ROLL - 0deg (LIFT UP)PITCH - 400K Horiz Mark (317deg)YAW - 0deg

ATT DB - MAXMAN ATT PITCH - ACCEL CMDEMS DATA - Ver~fy

EMS FliNC - ENTRY (ver~fy)

EMS MODE - NORMALcb SPS PampY (4) - openMAINT HORIZ TRK

PRO (Act ENTRY DAP)

IMPACT LATLONGHDSDN (01deg01deg-00001)PRO

7 POSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axis beyond 45deg of Vel vector)

8 06 64

58middot00m(-0200)

9

05G tlme(+0 )

(--=---)

06 68

-27-

P63 - ENTRY INIT

GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PIJR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRmDHORIZ CKPltch error needle goes toward

zero approachlng OSG tlmeMAN ATT (PITCH) - RATE CMD

If CMC lS GOBMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS I

FLY BETA If CMC NO GO ilt

1 SC CaNT - SCS I

FLY EMS k

p64 - ENTRY POST 05G

RTOGO AT 05G AGREES HITH EMS-venfyHORIZ CK05G Lt - ON (EMS START)

No EMS START wlthln 3 sec ~ EMS MODE - BACKUP VHF RNG c

05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds Llft DN

NNVR Llft DNEMS GONO GO

G-V Plot wlthln IlmltsRng ctr dwn 60plusmn7 durlng 10 sec

perlodMonltor G-meter for

convergence wlth pad data (Do)(Vlt27K fps) Go to 13

-28-

P65 - ENTRY - UP CONT (Vgt27K fps)

10 F 16 69 BETA (01middot) _DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT lt~ SC CONT - SCS FLY EMS

PRO

11 06 68 BETAVIHDOT (OIdegfpsfps)(VltV1+500 fps amp RnOT Neg) Go To 13

P66 - ENTRY - BALLISTIC (D(DL)

12 06 22 DESIRED GMBL ANGLES RPYMoultor horlz +12middot of 317middot mark

P67 - ENTRY - FINAL PHASE (02G)

13 06 66 BETACRSRNG ERRDNRNG ERR(010 1um 1um)

KEY VERBRecord DNRNG ERR _KEY RLSEMoultor l~ft vector ou RSI amp FDAI

16 67 RTOGOLATLONG (Vrel=1000fps)(lumOldegOldeg)

SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOWNMonitor a1t~meter

Go To EARTHLANDING pg ---4L5 _

-29-

53 GampN HYBRID DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL tV1 V37E 30E

2 F 06 33 GETI(ACCEPT) PRO (hrm~n Olsec)(REJECT) LOAD DESIRED GETI

3 F 06 81 tVXYZ (LV) (lfps)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

4 F 06 42 HAHPtV (lnm lfps)Record tV

(ACCEPT) PRO(REJECT) Reselect P30 or P27 Load new paramo

5 F 16 45 MTFIMGA (marksm~n-secOlO)

MGA -00002 ~f k

k lMU not al~gned

SET DETPRO

6

7

8

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (Pull)PLSS 02 vlv - FILL02 8M SUPPLY vlv - OFFCAB PRESS REL vlv (2) - NORMcb ELS (2) - closecb SECS ARM (2) - closecb SECS LOGIC (2) - close (ver~fy)

AUTO RCS SEL CM (12) - MNA or ~ffiB

(hftoff conhg)ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM (AampB) - OFF

CMP to Couch

9

10

11

-30-

MNVR TO PAD BURN ATTLOAD DAPBMAG MODE (3) - RATE 2SC CONT - CMCAUTOATT DB - MINMAN ATT (3) - RATE CMD

v62E

v49E

12 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLES

PRO

13 F 50 18 REQ MNVR TO FDAI RPY ANGLES (01deg)(AUTO) PRO(MAN) SC CONT - SCS

BMAG MODE (3) - RATE 2MNVR To 15

14 06 18 AUTO MNVR TO FDAI RPY ANGLES (01deg)

15 F 50 18 REQ TRIM TO FDAI RPY ANGLES (01deg)(TRIM) Go to 13(ByPASS) ENTR

16

17

CHECK BORESIGHT amp SKT STARSOPT MODE - CMCOPT ZERO - OFF

v41 N91E

18 F 21 92 SHAFTTRUN (01deg 001deg)Load SXTS angles

19 41 OPTICS DRIVECheck SKT STAR

OPT ZERO - ZEROCheck BORESIGHT STAR (~f ava~l)

20 V25 N17E (01deg)Load Pad Data GMBL Angles

for CM BURN ATTATT SETtw - SET

to PAD DATA GMBL ANGLESfor CM BURN ATT

21

22

-31-

PHR REDUCTIONHGA PHR - OFFFC PUMPS (3) - OFFVerify s~ngle su~t compr oper loads

balancedFC 2 MN AampB - OFFS BD PiR AMP - LOWcb ECS RAD CONTHTR (2) - opencb HASTE H20URINE DUMP HTRS(2)- opencb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANMN BUS TIE (2) - ONTVC SERVO PHR 1 - AC1MNAGMBL MTR (4) - START

p41 - RCS THRUSTINGV37E 41E

23 F 50 18 REQ MNVR TO LCL HORIZ (HDS ON)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CMCAUTOPRO To 24

(gtfANDAP) BMAG MODE (3) - RATE 2SC CONT - CMCHOLD

V62EMNVR To 25

24 06 18 AUTO MNVR TO FDAI RPY

25 F 50 18 REQ TRIM TO LCL HORIZ (01deg)ALIGN SC ROLL

(AUTO TRIM) PRO To 24(BYPASS) ATT DB - MIN

RATE - LOHMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTlRATE 2

ENTR

550Om26 06 85

59middot2527

-32-

VGXYZ (1fps)RECHECK BORESIGHT STARTRANS CONIR PWR - on (up)EMS MODE - STBY (ver~fy)

EMS FliNC - bV SETVHF RNGSET (IV for SM BURN _EMS FliNC - bVS BD ANT - OMNI CSECS LOGIC (2) - ONMSFN conhrm Go for PYRO ARMSECS PYRO ARM (2) - ARMCM RCS LOGIC - ON (ver~fy)

DSKY BLANKS

593028 16 85 VG XYZ (AVE G ON) (lfps)

RHCs amp THC - ARMEDLIMIT CYCLE - OFFTAPE RCDR - CMD RESETHBREMS MODE - NORMAL

000029 F 16 85 REQ NULL VG XYZ (lfps)

BURN EMS bV CTR TO ZERORESET DET amp COUNT UP

If SM ONLY burn go to step 32THC - LOCKEDSC CaNT - SCSFREERATE - HIGHPRIM GLY To RAD - BYPASS (ver~fy)

MN BUS TIE (2) - ON (ver~fy)

CMSM SEP (2) - on (up)CSMLM FNL SEP (2) - on (up) (verify)CampW MODE - CMRCS TRNFR - CMCM RCS LOGIC - OFF

Momtor VM ABIf lt25 vdc go to EMERGPOWER DOWN Pg E6-l

V63E

If CMC NO GO FDAI SOURCE - ATT FDAI SEL - 1 or 2 ATT SET - GDC

SET

-33-

~Uili ATT PITCH - ACCEL CMDFDAI SCALE - 55MNVR TO CM BURN ATT (NULL ERR NEEDLES)

R 0degPY --00--

30

31

CM RCS BURNRHC III-ContJnuous PJtch DownRHC HZ-Module PJtch to null needlesBURN VGZ TO ZERO

If only 1 RHC Pulse + P=5deg from retro att MaJnta~n rates lt3degsec

BURN COMPLETION ATllV CTR= or DET= _

V8ZE

32 F 16 44 HAHPTFF (1nmffiJn-sec)Check HP-

If gt Pad data contJnue burnuntJ1 lt Pad

PRO

33 F 16 85 VGXYZ (Ups)Read VG resJduals to MSFN

(HYBRID) PRO to 34(SM ONLY BURN)

PROF 37 ODE

EI-1500 V37E 47EF 16 83 twx Y Z (Ups)

SC CONT - SCSFREEMAN ATT (PITCH) - RATE CMDRATE - HIGHPRIM GLY To RAD - BYPASS (verJfy)MN BUS TIE (2) - ON (verJfy)CMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verJfy)Campl MODE - CMRCS TRNFR - CMCM ReS LOGIC - OFFSECS PYRO ~I (2) - SAFE

-34-

PROMonitor VMAB

If lt25 vdc go to EMERGPOWER DOWN

34 F 37 OOEPCM BIT RATE - LOWATT DB - MAXEMS MODE - STBYEMS FUNC - OFF

Go To EARTH ORBIT ENTRY pg _--40-__

-36-

8 SPS THRUSTING PREPCYCLE CRYO FANSSPS GAGING - ACI (ver~fy)

PUG MODE - NORM (venfy)BMAG MODE (3) - RATE 2tv CG - CSMCMC MODE - FREEAUTO RCS SEL (16) - MNA or HNB

(hftoff conbg)SC CONT - CMCAUTO

9 MNVR TO PAD BURN ATTV62E

10 V49E

11 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLESPRO

12 F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) PRO(HAN) SC CONT - ses

MNVR to 14

06 18 AUTO MNVR TO FDAI RPY ANGLES13

14 F 50 18 REO TRIH TO FDAI RPY ANGLES(TRIM) Go to 12(BYPASS) ENTR

15 BORESIGHT STAR CHECK

16 V37E 40EOPT PWR - OFF

17 F 50 18 REQUEST MNVR TO FDAI RPY ANGLES (01deg)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CHCAUTOPRO to 18

(MANDAP) BMAG HODE (3) - RATE 2SC CONT - CMCHOLDMNVR to 19

(HANseS) se eONT - sesMNVR to 19

-35-

54 NORMAL DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL ~V

1 V37E 30E

2 F 06 33 GETI (hrm~nOlsec)

(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

3 F 06 81 ~VXYZ (LV)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

( lfps)

4 F 06 42 HAHP~V (1nmlfps)Record W

(ACCEPT) PRO -----(REJECT) Rese1ect P30 or P27 Load new pa~am

5 F 16 45 MTFIMGA (marksmln-secOldeg)MGA -00002 If ~ lMU not a1~gned

SET DETPRO

6

7

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY v1v - OFFCAB PRESS REL v1v (2) - NORMcb ELS (2) - close (verify)cb SECS ARM (2) - close (ver~fy)

cb SECS LOGIC (2) - close (verlfy)AUTO RCS SEL CM (12) - ~mA or MNB

(l~ftoff conf~g)

ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM AampB - off (ctr)

18

-37-

06 18 AUTO MNVR TO FDAI RPY ANGLES (01 0)

19 l 50 18 REOUEST TRIM MNVR TOALIGN SIC ROLLGDC ALIGN

FDAI RPY ANGLES(010

)

+54-00m(-06-00)

TIG-5mJn

5500m(-0500)

TVC CHECK amp PREPcb STAB CONT SYS (all) - closecb SPS (12) - closeATT DB - MINRATE - LOl~

LIMIT CYCLE - ONMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE 2ROT CONTR PWR DIRECT (2) - OFFSCS TVC (2) - RATE CMD

If SCS SCS TVC (2) - AUTO SC CONT - SCS ~

TVC GMBL DRIVE PampY - AUTOMN BUS TIE (2) - ONTVC SERVO PWR 1 - AC1MNA

2 - AC2MNBTRANS CONTR PWR - ONROT CONTR PWR NORMAL 2 - ACRHC 2 - ARMED

HORIZ CHK - HorJz on 12deg wJndmlmark (LJffiJt +3 0 PNGCS GONO GO)

If NO GO set tw 180 0 180deg0 0

Track horJz wJth 24deg wJndow markAt TIG-2 mJn Ahgn GDC

PRIMARY TVC CHECKGMBL MOT P1-Y1 -STARTON(LMP confJrm)

If SCS verJfy Thumbwheel TrJmTHC - CWVenfy NO MTVC

SEC TVC CHECKGHBL MOT P2-Y2 -STARTON(LMP confJrm)SET GPI TRIHVenfy MTVCTHC NEUTRALGPI returns to 00 (CMC) or trJm (SCS)ROT CONT Pl~ NORM 2 - ACDC

(TRIM) Go to step 17(BYPASS) BMAG MODE(3) - ATTIRATE2 (ver1fy)

ENTR

-38-

20 F SO 25 00204 GMBL TEST OPTION(ACCEPT) SC CONT - GMC (ver~fy)

PROMonitor GPI Response

0020-2000020-200Tr~m

TEST FAIL SC CONT - SCS SCS TVC (2) - AUTO

(REJECT) ENTR

21 06 40 TFIVG~VM (m~n-sec1fps)

PROG ALM - TIG s1~pped

V5N9E 01703

KEY RLSE To 21 ROT CONTR PWR DIRECT (2) - MNABSPS He v1vs (2) - AUTO (ver~fy)

LIMIT CYCLE - OFFFDAI SCALE - SOIScb SPS P2Y2 - open (for cr~t burn)

5800(-02 00)

5925(-0035)

59middot 30(-0030)

06 40

59XX(-OOXX)

AV THRUST A(B) - NORMALTHC - ARMEDRlIC (2) - ARMEDTAPE RCDR - GID RESETHBR

DSKY BLANKS

(AVE G ON)EMS MODE - NORMAL

TFIVG~VM (m~n-seclfps)

CHECK PIPA BIAS lt2fps for 5 sec

ULLAGE AS REQ

IF NO ULLAGE DIR ULLAGE PB - PUSH~

CONTROL ATT WRlIC MONITOR AVM (R3) COUNTING UP

5955(-0005)

F 99 40 ENG ON ENABLE REQUEST(AUTO IGN) PRO AT TFI gt0 sec(BYPASS IGN) ENTR to 24

22 0000 IGN

-39-

If SCS - THRUST ON PB - PUSH

06 40 TFCVG~VM (m~n-seclfpslfps)

~F 97 40 SPS Thrust fall ~

~(RESTART) PRO To IGN (RECYCLE) ENTR To TIG-05 sec

SPS THRUST LITE - ONMONITOR THRUSTING

Pc 95-105 pSlaEMS COUNTING DOWNSPS IN3 v1vs (4) - OPENSPS He v1vs tb (2) - graySPS FUELOXID PRESS - 175-195 pSlaPUGS - BALANCED

PROG ALARM V5N9E 01407 VG INCTHC - CW FLY MTVC

ECOEMER SPS CUTOFF J

AV THRUST (2) - OFF

23 F 16 40 TFC(STATIC)VG~VM (mln-seclfps)~V THRUST AB - OFF

SPS IN3 v1vs (4) - CLOSEDSPS He tb (2) - bp

cb SPS P2Y2 - closed (verlfy)TVC SERVO PHR - AC1MNA (venfy)TVC SERVO PWR 2 - OFF

PRO

24 F 16 85 VG XYZ(CM) CUps)NULL RESIDUALSRECORD ~V CTR amp RESIDUALS I1VCEMS FUNC - OFF VGXEMS MODE - STBY VGYBMAG MODE (3) - RATE 2ATT DB - MAX VGZTRANS CONT PHR - OFF

PRO

25 F 37 V82E

26 F 16 44 HAHPTFF (lnmm~n-sec)

R3-59B59 HP gt494 nmPRO

27 F 37 OOE

-40-

55 EARTH ORBIT ENTRY

1 Venfy CMSMR __

P_shyY_-

SEP ATT(180deg)

(0deg )

2

3

4

EMS INITIALIZATIONEMS FUNC - RNG SETSET RNG TO PAD DATA RNGEMS FUNC - VA SETSlew scroll to pad data VIOEMS FUNC - ENTRY

RSI ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on(up)GDC ALIGN PB - PUSH amp HOLDYAW tw - Pos1tion RSI thru 45deg amp

back to LIFl UPGDC ALIGN PB - RELEASEEMS ROLL - OFFAl1gn GDC to lMU

PWR REDUCT (Norm Deorb Only)HGA PWR - OFFFC PUMPS (3) - OFFVer1fy s1ngle suit compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - Lowcb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2)-openlOb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MAN

-41-

P61 - ENTRY PREP

5 V37E 61E05 09 01427 - ROLL REVERSED05 09 01426 - IMU UNSAT

6 F 06 61 IMPACT LAT LONG liDS UPDN (+-)(01 0

010

+00001)

PRO

PAD VALUESLATLON==G------liDS UP DN _

7 F 06 60 GMAXV400KGAMMA EIRecord

GMAXV400K----GAMMA EI _

PRO

8 F 06 63 RTOGO (1nm) PAD _VIa (fps) PADTFE (mln-sec) ----Compare wlth MSFN for PGNS GONO GONO COMM SET RTOGO amp VIO IN EMS amp

INITIALIZE(ACCEPT) PRO(RECALC) V32E to 8

-42-

P62 - CMSM SEP amp PRE-ENTRY MNVR

9 F 50 25 00041 REQUEST CMSM SEPSC CONT - SCSFREEYAW - 45deg out-of-plane (left for RCS

nght for SPS)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE2PRIM GLY to RAD - BYPASS (verlfy)SECS LOGIC (2) - on (up)MSFN conflrm GO for PYRO ARMSECS PYRO ARM - ARMMN BUS TIE (2) - ON (verlfy)CMSM SEF (2) - ONCSMLM FNl SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 pSlaCM RCS LOGIC - OFFSECS PYRO ARM - SAFEMonltor VMAB

If lt25vdc go to EMERG POWERDOWN Pg E6-1AUTO RCS SEL AlC ROLL (4) - OFFAUTO RCS SEL CM 2(6) - OFFAUTO RCS SEL CM 1(6) - MNA or MNBYAW back to 00

PITCH TO ENTRY ATTROLL 0deg (LIFT UP)PITCH - HORIZ on 317deg MARK (400K)YAW 00

ATT DB - MAXMAN ATT (PITCH) - ACCEL CMDEMS DATA - VerifyEMS FUNC - ENTRY (verlfy)EMS MODE - NORMALMAINTAIN HORIZ TRK

PRO (Act ENTRY DAP)

10 F 06 61 IMPACT LAT LONG HDSDN(010 010 -00001)

PRO

11 FOSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axlS beyond 45deg of Vel vector)

-43-

P63 - ENTRY INIT

12 06 64 GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PWR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRHORIZ CKP~tch error needle goes toward

zero approach~ng 05G t~me

MAN ATT (PITCH) - RATE CMDIf CMC ~s GO

BMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS FLY BETA If CMC NO GO ~

SC CONT - SCS~

FLY EMS RCS Deorh Roll HDS UPTRACK HORIZ w~th 29deg w~ndow mk

P64 - ENTRY POST 05G

13

05G t=elt+0___)

06 68

RTOGO AT 05G AGREES WITH EMS - venfyHORIZ CK05E Lt - on (EMS start)

No EMS start w~th~n 3 secsEMS MODE - BACKUP VHF RNG 05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds L~ft DN

NNVR L~ft DNEMS GONO GO

G-V Plot w~th~n llm~ts

Rng ctr dwn 60 + 7 durlng 10 sec per~od

Mon~tor G-meter forconvergence wlth pad data (Do)

(Vlt27K fps) Go To 17

-44-

P65 - ENTRY - UP CONT (Vgt27K fps)

14 F 16 69 BETA (01deg)DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT~

SC CONT - SCS FLY EMS

PRO

15 06 68 BElA VI HOOT (01deg fpsfps)(VltVL +500 fps amp RDOT Neg) Go To 17

p66 - ENTRY - BALLISTIC (DltDL)

16 06 22 DESIRED GMBL ANGLES RPY (01deg)Mon~tor hor~z +12deg of 317deg mark

P67 - ENTRY - FINAL PHASE (02G)

17 0666 BETACRSRNG ERRDNRNG ERR (Oldeglnmlnm)KEY VERBRecord DNRNG ERR _KEY RLSEL~m~t +100nm from PAD DRE

Mon~tor l~ft vector on RSI amp FDAIF 16 67 RTOGOLATLONG (Vre1=1000fps)

(lnm 010 01deg)SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOlfflMon~tor altimeter

Go To EARTHLANDING pg _I4L5__

-45-

56 EARTHLANDING

90K STEAM PRESS - PEGGED50K CABIN PRESS REL vIv (2) - BOOSTENTRY

SECS PYRO ARM (2) - ARM

40K(90K + 63s)

CM UNSTABLE RCS CMD - OFF ~ 40K APEX COVER JETT PG-PUSH DROGUE DEPLOY PG - PUSH (2 secafter apex cover Jett)

30K ELS LOGIC - ON (up)ELS - AUTO

24K RCS hsable (auto)(90K+92s) RCS CMD - OFF

Apex cover Jett (auto)APEX COVER JETT PB - PUSH

(WAIT 2 SECS)Drogue parachutes deployed (auto)

DROGUE DEPLOY PB - PUSH~

If Drogues FallELS - ~ ~Stablllze CM 5K MAIN DPLY PB - PUSHELS - AUTO

235K Cabln Pressure lncreaslng (Drogues + 50s)If not lncreaSlng by 17K CABIN PRESS REL vlv (RR) - DUMP

-46-

10K Maln parachutes deployedMAIN DEPLOY PB - PUSH (wlthln 1 sec)VHF ANT - RECYVHF AMA - SIMPLEXVHF BCN - ONCABIN PRESS REL v1v (2) - CLOSEDIRECT 02 vlv - OPENCM RCS LOGIC - on (up)CM PRPLNT - DUMP (burn audlb1e)Monltor CM ReS 1amp2 for He press decrease

NO BURN or PRESS DECREASE USE BOTH RHCs DO NOT FIRE PITCH JETS

CM PRPLNT-PURGE (to zero He press)CM RCS He DUMP PB - PUSH RHC (2) - 30 sees NO PITCH k

STRUT LOCKS (2) - UNLOCK

cb FLT amp PL BAT BUS ABampBAT C (3) - closecb FLT amp PLT MNA amp B (2) - opencb ECS RAD HTR OVLD (2) - opencb SPS PampY (4) - open

3K CABIN PRESS REL v1v (RH) - DUMP (after purgecompleted)

FLOOD Lts - POST LDGCM RCS PRPLNT (2) - OFFROT CONTR PWR DIRECT (2) - OFF

800 CAB PRESS RELF vlv - CLOSE (latch off)MN BUS TIE (2) - OFF

AFTER LANDINGcb MAIN REL PYRO (2) - closeMAIN RELEASE - on(up)

Go to POSTLANDING pg _47L-__

I

2

3

-47-

57 POSTLANDING

STABILIZATION VENTILATION COMMUNICATIONS

DIRECT 02 vlv - CLOSE

Stablllzation after landlngELS - AUTO (verlfy)cb MAIN REL PYRO (2) - close (venfy)MAIN RELEASE - on (up) (verlfy)S~CS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb BAT RLY BUS (2) - open

No contact w1th recovery forcesVHF AM AampB - off (ctr) ~

VHF AM Rev ONLY - A cb PL VENT - closecb FLOAT BAG (3) - closecb UPRIGHT SYS COMPRESS (2) - closeIf Stable II

FLOAT BAG(3)-FILL t1ll 2 m1n afterupr1ght then - OFF

VHF AM AlB amp BCN - OFF whlle lnvertedIf Stable I

After 10 M1n Coollng Per1odFLOAT BAG (3) - FILL 7 mln then OFF

Post Stab1lizat1on And Ventllat10nPL BCN LT - BCN LT LOWPL VENT vlv - UNLOCK (Pull)Remove PL VENT Exh CoverPL VENT - HIGH or LOWPL DYE MARKER - ON (swlmmer comm)Release foots traps and_restralntscb MNA BAT BUS A amp BAT C (2) - opencb MNB BAT BUS B amp BAT C (2) - opencb FLT amp PL BAT C - opencb PYRO A SEQ A - opencb PYRO B SEQ B - open

EACH HR - CHECK DC VOLTSgt 275 V If Notmiddot cb FLT amp PL-BAT BUS AampB (2) -open cb FLT amp PL BAT C (1) - open GO TO LOW POWER CHECKLIST

Unstow and lnstall PLV DISTRIB DUCTDeploy grappllng hook and 11ne 1f req

4

-48-

Post Landing Communlcatl0nsVHF ANT-RECY (venfy)VHF BCN - ON (verlfy)

If no contact ~lth recovery forcesperform VHF BEACON Check

MONITOR VHF BEACON transmlSSlonnth VHF AM B Rcvr andor Su)vlval

TransceiverkVHF Beacon not operatlng ~connect Surv~val TranscelVer to antcable behlnd VHF ant access pnland place radio ln BCN mode

LOW POHER CHECKLISTVHF BCN - OFFVHF AM (3) - RCVFLOOD Lts - OFFVHF AM AampB - off (ctr)VHF AM RCV ONLY - A (venfy)COUCH LIGHTS - OFFPOSTLANDING VENT SYS mlnlmlze useSURV RADIO - plug mto VHF BCN ANT cableconn behind VHF ant acess pnl amp turn radloon l-n BCN mode

EGRESS PROCEDURES

CMPCDRLMPCDR

CMPCDRCMP

LMPLl1PCDR

STABLE IDlsconnect Umblll-calsNeck darn onCenter couch - 270 0 positionArmrests stowedConnect raft to SIC l-f desl-red wlth

green lanyardConnect raft ~hl-te lanyards to SUltS amp

lnflate water wlngs when eXltl-ngHATCH PISTON PRESS vlv - PRESS (Outbd)Slde Hatch openedPL VENT - OFFcb Pnl 250 (all) - openEgress with 11feraftPut hardware klt outEgress

or CDIPALL

CMF

CDRCMF

CDR

LMF

CMFCMP LMFCMP

UlP

CDR

-49-

STABLE IIcb CREW STA AUDIO (3) - openD~sconnect umb~1~ca1s

Release foots trapsRelease restra~nt harnessCouch seat pans (3) - 170 0 pos1t10nArm rests stowedSurv1va1 k~ts removed from stowageConnect life raft ma~n1~ne to CDR or SicConnect f~rst wh~te lanyard from

11fe raft to suitConnect th~rd wh~te lanyard from

l~fe raft to SU1tConnect rucksacks together to yellow

lanyard on raft bagPRESSURE EQUALIZATION vlv - OPENRemove and stow fwd hatchEX1t feet f1rst w1th rucksacks when clear

of siC 1nflate water w1ngs and raftExit feet f1rst when clear of SiC

1nflate water w1ngsEX1t feet f1rst when clear of sic

1nflate water w1ngs

-50-

60 TLI ABORTS

TLI Aborts are conta~ned ~n the ESD s~nce the bulk of the funct~ons

concern entry preparat20ns and performance Th~s allows a s2nglesource of procedures for procedure rev2ew val~dat~on checkout andtra~n~ng These procedures ~ncorporate TLI preparat20ns as found ~n

reference 6 w~th the TLI Abort Procedures and these t~e 2nto normallunar return Entry Procedures found ~n sect20n 5 The guidel~nes

for th~s cont2ngency are spec2f2ed 2n reference 7

In2t2al preparat~ons for TLI pos2t20n the necessary system sW2tches2n add~t~on to perform~ng an EMS ~V test and a GDC al~gnment Afterthe DET ~s set for mon2tor2ng TB6 the CMP ~ncreases the 12ght levelof the LEB DSKY to max~mum and returns to the h2s couch Th2s 2Sdone so that the LEB DSKY can be observed ~n the event sunl~ght orreflect20ns wash out the ma2n d2splay panel DSKY dur2ng cr2t2calmaneuvers The crew then straps ~n and prepares for mon2tor~ng TB6as 2nd2cated by the SII SEP L~te The t2mes se~uence of procedures2S keyed on th~s d~splay and ~ncludes the DET START funct~on andSIVB IGNITION Dur2ng the burn the crew mon2tors the FDAIs foratt~tude excurs20ns and abnormal rates report~ng status checks toM~ss2on Control at d2screet t~mes dur2ng the maneuver Upon SIVBSHUTDOWN the eMP records the DSKY d~splayed performance parametersand awa2ts ground conf2rmat~on

The rat~onal for TLI aborts ~s descr~bed 2n reference 7 A summar2shyzat20n 2S extracted to prov2de background and gu2de12nes 2n th2sdocument The abort procedures cover aborts 10 m2nutes after conshyt2ngent SIVE shutdown and aborts 90 m2nutes after normal SIVE shutshydown t2me

The 10 m~nute TLI abort ~s des2gned to be used dur~ng TLI ~n theevent a spacecraft problem develops Wh2Ch can result 2n catastrophe2f ~mmed~ate act~on 2S not taken If the s~tuat20n perm~ts the crewshould always allow the SIVB to complete TLI at wh~ch t~me the groundand crew can perform a malfunct~on analys~s to determ~ne ~f an abort~s adv~sable If a fa~lure occurs that necess2tates the shutdown ofthe SIVB and the ~u~ck return of the crew to earth th~s abort ~s

des~gned to be as ~nsens~t~ve to execut~on errors as poss~ble andst21l be targeted to m2dcorr2dor The burn att~tude w~th the f~ed

hor~zon reference ~s a constant value for any shutdown t~me Theburn durat~on 2S a funct20n of shutdown t2me and 2S ava21able fromcrew charts S~nce the pr~mary purpose of th~s abort ~s to returnto earth as qU2ckly as poss2ble there are no restr2ct20ns as toland~ng locat~on However ~f the t~me to EI is greater than abouttwo hours a midcourse correct20n should be ant~c~pated

The 90 m2nute TLI abort 2S to be used 2f a cr2t2cal subsystem malshyfunct~on ~s determ2ned and the dec2s~on to abort ~s made after the

-51-

TLI cutoff and before TLI cutoff plus approxlmately 80 m1nutesTh1S allows suff1c1ent separatlon and procedural t1me to set upfor the SPS deorb1t burn performed at about TLI + 90 Note thatgenerally the deorb1t burns w1ll be performed a fe11 m1nutes beforeTLI + 90 accord1ng to crew charts shown In reference 8 The no-comm except10n requ1res that 90 m1nutes be the 1nput t1me of 19n1shytlon for P-37 (onboard return-to-earth abort program) so that onshyboard calculatlons can correspond w1th ground calculat10ns to computethe CM land1ng p01nt Th1S TLI abort lS des1gned so that returnfl1ght t1me does not exceed 18 hours and abort ~V does not exceed7000 fps ThlS abort can be performed uSlng chart ~Vs and attltudesand the earths hor1zon serves as a suff1c1ent reference The maneushyver lS targeted to ach1eve the mldcorr1dor entry target Ilne andtlmed to result 1n a deslgnated recovery area

It 1S ObV10US for abort deC1S1ons early 1n the TLI + 90 m1nute t1meshyframe that a GampN SPS burn should be performed In order to keep theTLI abort procedures cons1stent and w1th emphasls on slmpl1c1ty theprocedures here reflect a SCS SPS abort burn to cover the full abortdec1s1on t1meframe

A m1dcourse correct1on for corr1dor control after a TLI abort may bedeS1red 1f the SPS burn d1d not meet expectat1ons The TLIabortprocedures 1n th1S sect10n adapt to the normal lunar return tlmel1neand procedures pr10r to the f1nal MCC

-52-

61 TLI PREPARATION PROCEDURES

GET = 150

CRO AOS(___)

CRO LOS( )(22142)

5100

Don Helmets amp Gloves

XLUNAR - INJECT (verify)EDS PWR - on (venfy)EMS FUNC - OFF (verlfy)EMS MODE - STBYEMS FUNC - IW SETVHF RNGEMS MODE - NORMALSet ~V indo to +15868 fpsEMS FUMC - ~V Test

SPS THRUST Lt - onoff (10 sec)~V lnd stops at -01 to -415

EMS MODE - STBYEMS FUMC - ~V SETVHF RNGSet ~VC

EMS FUNC---~~V=----

GDC ALIGNFDAI Select - liZcb SECS LOGIC (Z) - close (verify)cb SECS ARM (Z) - closeSECS LOGIC (Z) - on (up)MSFN Conflrm GO for PYRO ARM (If pass)SECS PYRO ARM (Z) - on (up)TRANS CONTROL PWR - ONROT CONTR PWR NORMAL (Z) - ACDC(verlfy)ROT CONTR PWR DIRECT (Z) - MNAMNBLV INnGPI - SIISIVB (venfy)LV GUID - IU (venfy)cb DIRECT ULLAGE (Z) - closedSet EVENT TIMER to 5100Begin MONITOR For TB6

CMP to Couch

TB 6 - SII SEP Lt on (TIG-9 mln 38 sec)KEY V83E

SET ORDEALFDAI Z ORB RATE at 180 0 0SII SEP Lt out (38 sec later)Start DET COUNTING UPSC CaNT - SCS (verify)MONITOR LV TANK PRESS

~P lt 36 psid (OXID gt FUEL)~P lt Z6 psid (FUEL gt OXID)

EMERGENCY CSMLV SEP UP TLM CM - BLOCK (verify)UP TLM IU - BLOCK (venfy)

-53-

+45degPY))0middot sec PY

lOK nmltHAlt25K nm

Two phas~ng mnvrs two SPS mnvrs to circular~ze at 150 nmearth orb~t

CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ssion 4K nmltHAltlOK nm CSM amp1M - Two phasing mnvrs two SPS mnvrs to circularize at 150 nm earth orb~t CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ss~on

CSM amp 1M - Two phas~ng mnvrs APS burn todepletion th~rd phasing mnvrSPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn tosem~sync orb~t

25K nmltHAlt40K nm CSM amp 1M - Two phasmg mnvrs APS burn to depletion third phas~ng mnvr SPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn to sem~sync orbit HA)40K nm DPS ava~l - DPS LOll circularize with SPS

DPS not ava~l - Lunar flyby or CSM only to lunar orbit (if reqd gtV lt4000 fps)

V37E 47E (check b~as) Record -=--rshy(Limit 98 fpsmm)

( 1fps)tVXYZN62EVIHDOTHPAD (fpsfpslnm)MONITOR VI ( ) at ECO

SCS TVC SERVO PWR 1 - ACIMNA2 - OFF

TAPE RCDR - CMD RESETHBREMS MODE - NORMAL

SIr SEP Lt - ONTLI Inhib~t S~gnals w~11 not be honored after 5942

SIVB ULLAGE BeginsSII SEP Lt - off (TIG - 18 sec)SIVB FUEL LEADSIVB ULLAGE d~scont~nues

LV ENG I Lt - onSIVB IGNITION ( GETI)LV ENG I Lt - off - -shyMONITOR THRUST amp ATTITUDEMONITOR LV TANK PRESSSIVE ECO (Lt on) (BEGIN TB7)

EMER SIVE CUTOFF AT 6 SEC PAST BURN TIME IF VI ATTAINEDTHC CCW ampNEUTRAL IN 1 SEC or SIISIVB sW - LV STAGEPremature Shutdown HAlt4K nm CSM amp 1M -

5700

58205836

F 16 835800

F 16 62

5838594259525955595900000002SUNRISE(___)

HAW AOS(__=_) KEY VERB (freeze d~splay)

SIVB ATT HOLD 20 sec amp BEGIN VENTINGSIVB NNVR TO ORB RT (HDS DN) (3middot sec)

Record VI -c---HDOT _

HPAD _

KEY RLSEF 16 62

F 16 83

HAW LOS(__=-)

KEYmiddotRLSE~VXYZ (lfps)

Record ~VX---_

~vy

WZ--

AVC---_

TAPE RCDR - off (ctr)EMS MODE - STBYEMS FUNC - OFFSECS PYRO ARM (2) - SAFE

PRO

BURN STATUS REPORT

____--~TIG

BT------VGX____-R

-----P----_Y

REMARKS

_____VI

______--HDOT______--H______---AVC______---FUEL_______OXID

_______UNBAL

F 3708=00 OOEGOS AOS CMP TO LEB

(-=-=-)

0000

0003

0005

0014

0100

-55-

62 TLI 10 MIN ABORTSECS LOGIC (2) - on (up)SECS PYRO ARM (2) - ARM

TRANS CONTR - CGH (4 sec) amp +XDET RESET (verlfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS GMD-ON

TRANS GONTR - neutral then +X for10 sec

SIVBGPI s~ - GPIExcesslve rates 6V THRUST A - NORMAL SPS THRUST - DIRECT When rates damped 6V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

TRANS CONTR +X - OFFV37E OOE

PITGH UP to LOGAL VERT (+X axlSto~ard the earth)

RATE - LOWBMAG MODE (3) - ATTIRATE 2EDS PHR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SEGS ARM (2) - opencb EDS (3) - open

TRANS CONTR -X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (180deg)P (199deg)Y (0deg)

RETRO UPDATEGETI _

JV _VG

Jtb ---GET 400K _

05G _GET DROGUE _

ENTRY P _R _

Y_--

0945

-56-

ALIGN HORIZ ON RET +1 MKGMBL CHECK (T11lle Pentattlng)MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conflnn)cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FUMC - JV SETVHF RNGSET JV from chartE~S FUMC - JVEMS fODE - NOIDlAL

lV THRUST A - NORMALV37E 47E (THRUST fONITOR)

F 16 83 lVXYZ (1 fps)

0950

1000

NOTE For aborts durlng 1st mln of TLIKEY V82E F 16 44 (HaHpTff)Burn untll Hp lt 19NM

TRANS CONTR +X

THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN JV reqdJV THRUST (2) - OFFReport cutoff

cb SPS P2 Y2- closeGfBL MTRS (4) - OFF (LMP Confinn)TRANS CONT PWR - OFFTVC SERVO PWR (2) - OFFMN BUS TIE (2) - OFFcb SPS P1amp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREIf est time to EIltOl5500 omlt fCC andenter the SUPERCIRC CKLIST as early as pos-slb1e Pg ~2~3~ __If est time to EI)Ol5500 anticlpate afCC Enter the ENTRY PREP CKLIST at step 9pg 18

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

-2tl C

l I W gt- ~-4

z laquo I I- 0 -6

l- I J u gt- ~-8

z w w -10

~_ONSANT

9O

VER

SHO

OT

BOU

ND

ARY

LIF

TV

EC

TOR

OR

IEN

TATI

ON

LIN

E

SH

ALL

OW

TAR

GE

TLI

NE

STE

EP

TAR

GE

TLI

NE 12

gU

ND

ERSH

OO

TBO

UN

DAR

Y

RE

EN

TRY

CO

RR

IDO

R

I ~ I

-12 24

26

28

30

32

34

RE

EN

TRY

VE

LOC

ITY

VE

1-F

TS

EC

Ch

art

1

36

3B

6-i

~

5CM

CC

ON

ST

NT

DR

VI z gt

~

I4

0 Cl W

I

gtamp

J+

-I

-

J Cl z

2U

l z 0_bull

bull-1

+-

u ubullbull

~r

U

)

2829

JOn

J23

33

43

5IN

ER

TIA

LR

EE

NTR

YV

ELO

CIT

YA

T4

00

00

0fl

VE

I-F

TS

EC

Ch

art

2

J63

73

8X

03

-i- rtREQUIRED PITCH GIMBAL ANG LETO OBTAIN HOR-IZON AT 317

DEGREES IN wiiiiDOW

260

z~I- ~ i5 24000

1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

-I

-1-

NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

I LU HD~-

LUHD

lt0 120UJ0

~

80 HOLD PRESENT TRIMgt LU HD013

~Y~HOIgtlt

TOP OF WINDOWa 40to

31 7 SCRIBEaaI

80 TTOM OF WINDOWi= 0

0--ltoa

-40t-z

~~~Uw w u lt0 -80

HOLO PRESENT TRIlJCl

LOHU0 lt0

J gt -120 HOLD 059 TRIMlt0 z

LDHUlt0 FIELD OF VI S10 NLDHU LIFT-DOWNHEADS -UPLUHD LIFT-UP HEADS-DOWN

~~H~-160 q - P63 LIMITI- NOrE-VALIO ONLY FO~t~--

LUNAR RETURN VELOCITY

plusmnl8020 244middot 8 12 16

TIME TO 400K FT ALTITUDE-MIN

4

P37

LONG

ITUD

ECO

RREC

TION

TOOB

TAIN

1350

NM

ENTR

YRA

NGE

Ugt

UJ

cgt

3z 0 I- u U

J0

0

0

2I

U~

UJ

cgt

I

gtI- U

gt z 0 J ltJ

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90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 12: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

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40 EARTH ORBITAL DEORBIT AND ENTRY TECHNIQUES

As outl~ned ~n reference 5 a nom~nal PGNCS entry from earth orb~t ~s

based on a preparat~on t~me of 2 hours and 40 m~nutes ~nclud~ng 2n~ght passes Th~s t~me ~ncludes approx~mately 20 minutes before thef~rst n~ght pass after the CMC update and PAD data have been rece2vedTh~s t~e also 2ncludes approx2mately 20 m2nutes after the secondn~ght pass to allow suffic~ent t2me to prepare for retrof2re after theIMU f2ne a12gnment It has been determ2ned coarse a12gnment accuracy~s adequate for retrof~re and entry and undoubtedly other funct20nscould be om2tted depend2ng on the c2rcumstances for the dec2s20n toreenter Descr2bed here2n are the nom2nal earth oro2tal entry proshycedures w2th pert2nent comments on system va12dat20n for real timeacceptance dec~s20ns

After the entry dec~s~on is made the crew transfers the PGNCS fromthe standby to the operate mode and rece~ves a CMe update w~th P27Next the maneuver PAD update ~s v02ced up and the 2n~t~al entry mode~s determ~ned During the ~n~tial n~ght pass the IMU or2entat~on ~s

estab12shed uS2ng P51 star s~ght2ngs to obta2n a REFSMMAT The preshyferred or~entat~on opt20n ~n P52 2S then selected to coarse a12gn theIMU uS2ng the des2red entry REFSMMAT determ2ned by MGG-H The GOO ~s

now al~gned to the IMU 2n preparat~on for an IMUSes dr~ft check Ifthe GOO ~nd~cates the ses dr2ft rate exceeds 10 degrees per hour ~n

any ax~s the check ~s repeated on the other BMAGs to estaol~sh if theGOO or Just the single set 2S unusuable Var20us sytem checks as 12sted2n sect20n 51 are performed as necessary cons2stent w2th the t2me12ned2ctates of the maJor act2v2t2es Included 2n these checks are the EMSself-tests and the dV counter test The latter requ2res the spacecraftbe placed ~n dr2ft2ng fl2ght w~th the funct20n sW2tch 2n the dV pos2t~on

If the counter reg2sters a change of more than 25 feet per second w2th2n100 seconds the scroll and counter are unre12able for mon2tor2ng thedeorb2t burn and entry rang2ng If the EMS self-test fails and t2medoes not allow further analysis a 5555 ERE entry 1S planned as thePGNGS backup entry mode After complet2on of these checks the entryPAD lS prov1ded by MeG-H The crew then selects the external dVprogram P30 and the appropr2ate deorb1t tbrust1ng program p40 or P41Dur2ng th2s per2od wh2ch 2ncludes the f1nal n2ght pass P52 may beselected to ver2fy the IMU a12gnment Since the retro att2tude hasbeen computed so that a w2ndow mark c01nc2des w2th the hor2zon atGETI th2s serves as the conclus2ve check on the PGNCS At 5 m2nutesbefore retrofire the att2tude check 1S made by ver1fY2ng that the 12degree scr~be 12ne ~s w2th2n 3 degrees of the hor2zon If not thePGNeS has fa2led and the ses 2S used for att2tude reference and the

V counter for burn durat~on control S2nce the ses att~tude wasa12gned to the IMU a real~gnment ~s necessary This ~s accompl~shed

by manually maneuver2ng the spacecraft to ma~nta1n the 24 degree wlodowmark on the hor2zon and releas1ng the GOO a12gn button at TIG - 2 m2nutes

-14-

Upon complet~on of the burn the tN res~duals are burned to W~th~n

02 feet per second If the PGNCS ~V counter or est~mated burnduration are ~n d~sagreement ~t must be estab1~shed whether suff~shy

c~ent veloc~ty has been suppl~ed to put the land~ng po~nt in thefootpr~nt The PGNCS data w~ll be used ~f ~t ~s conf~rmed by oneother source if not the ~V counter w~11 be used ~f ~t ~s conf~rmed

by the burn durat~on t~me If add~tional ~V ~s necessary the data~s ava~lable to the crew on an onboard chart found ~n Sect~on 80

Post burn entry preparat~on requ~res EMS ~n~t~al~zation RSI al~gnshy

ment and pre-separat~on funct~ons The crew then selects the ~n~t~al

entry program P61 and records the d~sp1ays as a check aga~nst PADdata Upon complet~on of these checks P62 ~s entered The crewmanually or~ents the spacecraft to the separat~on attitude and yaws450 to ~nsure aga~nst possible CM 8M recontact After separat~on

the spacecraft ~s maneuvered to the reentry tr~m att~tude wh~ch

places the hor~zon on the 3170 w~ndow mark at EI Shortly thereshyafter ~n P62 the entry DAP is act~vated and P63 in~t~ated Dur~ng

th~s t~e MCC-H has computed a postburn update and ~t ~s vo~ced tothe crew ~f d~fferent from preburn values The EMS scroll and rangecounter w~ll be adJusted accord~ngly ~f t~me perm~ts A f~nal PGNCScheck pr~or to 05g may be mon~tored at th~s t~e w~th the CMC modein free and the manual att~tude p~tch ~n acceleration command wh~le

the hor~zon reference ~s held the p~tch error needle w~ll decreaseto zero as EI ~s reached At RET 005g the EMS mode sw~tch ~s

turned to manual the entry 005-g sw~tch and EMS roll sw~tch areturned on and the spacecraft control sw~tched to CMC to beg~n DAPcontrol At the PGNCS 005-g ~ndicatwn the program change fromP63 to P64 ~s mon~tored and the t~e vo~ce recorded At th~s t~me

the EMS range counter check ~s made dur~ng the 10 second per~od

follow~ng EMS 005g Dur~ng th~s per~od the counter should countdown 40 + 10 naut~cal m~les At PGNCS 02-g ~nd~cation the changefrom P64-to P67 ~s monitored and the ~splay may be held by key~ngVERB ~n order to record the init~al downrange error d~splay andcompare ~t to the PAD value The PGNCS has fa~led ~f the two do notagree w~th~n + 100 naut~cal m~les In the event P67 has not appearedwhen both the-g-meter and the scroll ~nd~cate greater than 05g thePGNCS has sim~lar~ly fa~led In e~ther fa~lure the SCS is used foratt~tude reference w~th an EMS entry If the checks agree the crewrema~ns w~th automat~c DAP for the rema~nder of the entry

The entry phase ~s essentially over when the relat~ve velocity ofthe spacecraft decreases to less than 1000 feet per second Th~s

~s ~nd~cated ~n P67 when RTGO lat~tude and long~tude are d~splayed

S~nce very l~ttle rang~ng capab~l~ty exists after th~s pOint thespacecraft is or~ented either full l~ft up or down depending onRTGO negat~ve or pos~t~ve and the crew prepares for the earth land~ng

phase

-15-

41 TYP~cal Retrof~re and Entry Sequence of Events

Dec~s~on to reenter

P27 (CMC update)

Retrof~re PAD update

Entry mode dec~s~on

P51 (IMU or~entat~on determlnatlon) durlng f~rst dark per~od

P52 (IMU coarse allgnment)

EMS checks

Entry PAD update

P30 (external AV)

p40 (SPS thrust)

P52 (IMU f~ne al~gnment) durlng second dark per~od

p40 (SPS thrust)

Ign~t~on att~tude check

Retroflre

P61

P62

CMSM separat~on

P63

Postburn PAD update

Entry attltude check

p64 (beg~n DAP control at O05g)

P67 (PGNCS gono go check at O2g)

42

Retrof~re

and

En

try

Alt

ern

atlv

es

Sys

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fa~lure

PGNC

S

PGNC

San

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PGNC

San

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Fal

lure

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Fal

lure

aft

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-17-

5 0 DETAILED ENTRY PROCEDURES

In order to comblne slmilar procedures that are common to lunar returnentrles and earth orblt entrles the followlng procedures are dlvldedlnto categorles that allow a mlnlmum of dupllClty ThlS provldes asmaller tralnlng package and more closely resembles the onboard crewcheckllst when comparlson lS necessary

51 Entry Preparatlons for Superclucular and Earth Orbltal Entrles

1~e entry preparatlons are comblned In these procedures andsteps pecullar to elther superclrcular or earth orbltal entrlesare labeled accordlngly The tlme llstlngs In thlS sectlon areappllcable to only superclrcular entries Slnce the earth orbltalentry tlmellne lS a functlon of several varlables as descrlbedIn sectlon 40 and reference 5

-18-51 (Contlnued)

VEHICLE PREPARATION

l-

2

3

4

5

6 -0600h

7 -0535h

8

9

10 -0430h

INITIAL STOWAGE COMPLETED

CMC amp ISS START UP

SCS POWER UP

p51 - IMU ORIENTATION

LOAD DAPV48E 11102 01111 PRO ERO PRO

LAST MCC DECISION

NO COMM - P52 amp NAV SIGHTINGSNOMINAL - P2337 ONBOARD COMPARISON

DON MAE WESTS amp FOOT RESTRAINTS

VHF AM A - SIMPLEX

P 27 (SV REFSMMAT) MNVRamp ENTRY pAD UPDATES

11 -0415h P52 - IMU REALIGN(___) (OPTION 1)

12 P37 (NO COMM ONLY)

13

14

ECS CKS02 SUPPLY REFILLECS Monitor CkEVAP H20 CONT (2) vlvs - AUTOSUIT HEAT EXCH SEC GLY - FLOW

EPS CKS 1 3 4 (5 If reqd)

15 SPS CK (If req d)

16

17

18

RCS CKSSM RCS MOUlt CkCM RCS MOUlt Ck

CampW SYS CK

CMC SELF CK

19

20 -0345h

-03l5h-0300h

21

22

22A

-19-

DSKY COND LT TEST

MIDCOURSE MANEUVERP30 - EXT rVP404l - SPSRCS THRUSTINGMIDCOURSE (17) BURN

NO COMM NAV SIGHTINGS

ffiVR TO ENTRY ATT (Superc1rc only)V62E

V49E

22B F 06 22 DESIRED FINAL GMBL ANGLESLOAD ENTRY ATT PAD ANGLESPRO

22C F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) SC CONT - CMC

BMAG MODE (3) - RATE 2CMC MODE - AUTO

PRO(~N) SC CONT - SCS

MNVR to 22E

22D 06 18 AUTO MNVR TO FDAI RPY ANGLES

22E F 50 18 REQUEST TRIM(TRIM) Go to 22C(BYPASS) ENTR

23 -200hr BORESIGHT amp SXT STAR CHECKOPT MODE - CMCOPT ZERO - OFF

V41 N91E

F 21 92 SHAFT TRUNLoad SXTS angles

41 OPTICS DRIVE

CHECK SXT STAROPT ZERO - ZERO

CHECK BORESIGHT STAR (If ava11)

24 -0135h

25(___)

26

27 -0115h

-20-

P52 - lMU REALIGNRecord gyro torqu~ng anglesRp~----

YIf-7gt-Lno--re-c-ycle PS2If conflrmed use SCS for EMS entry

GDC ALIGNIf drlft gtLOohr change ratesource

FINAL STOWAGEOPTICS (except for hybrid)ORDEALGLY TO RAD SEC - BYPASS (verlfy)CooL pnl lnstalledY-Y struts (2) extendedStow Data Box R-12

EMS CHECKEMS FUNC - OFFcb EMS (2) - closeEMS MODE - STBYEMS FUNC - EMS TEST 1 (walt 5 sec)EMS MODE - NORMAL (walt 10 sec)

Check ind lts - offRANGE lnd - 00Slew halr1ine over notch

In self-test patternEMS FUNC - EMS TEST 2 (walt 10 sec)

05G It - on (all others out)EMS FUNC - EMS TEST 3

05G It - onRSI Lower It - on (10 sec Qater)Set RANGE counter to 58 nm+OO

EMS FUNC - EMS TEST 405G It - on (all others out)G-V trace w~thin pattern to lwr rt

corner 9GRANGE lnd counts down to 0+02

EMS FUNC - EMS TEST 505G It - onRSI upper lt - on (10 sec later)RANGE md - 00SCrlbe traces vertlcal llne 9g to

022+01ALIGN SCROLL TO ENTRY PATTERN (on

37K ft sec hne)EMS FUNC - RNG SET

G-V scroll assy traces vert llne022g to 0+01

EMS MODE - STBY

28

29

30 -OllOh

-21-

~V TEST (Deorb~t only)EMS FUNC - ~V SETVHF RNGSET ~V ~nd to 15868 fpsEMS MODE - NORMALEMS FUNC - ~V TEST

SPS THRUST LT - onoff (10 sec)~V ~nd stops at -01 to -415

EMS MODE - STBY

PRIMARY WATER EVAP ACTIVATIONGLY EVAP H20 FLOW - AUTOGLY EVAP STH PRESS - AUTOPRI ECS GLY PUMP - ACI

CM RCS PREHEATNote If sys test mtr 5cd6abcd

all read 39 vdc (28degF) or moreom~t preheat

cb RCS LOGIC (2) - closeCM RCS LOGIC - ONUP T1M CM - BLOCK (ver~fy)

cb CM RCS HTRS (2) - closeCM RCS HTRS - ON (LMP Conf~rm)

(20 mlU or III lowest rdg lS39 vdc) (Moultor Maufpress for press drop)

31 (___) FINAL GDC DRIFT CK (If req I d)If drlft gtlOohr Suspect GDC Do not

use RSI amp FDAI 2

32 -OO5Om

33

34

35

TERM CM RCS PREHEATUP TLM CM - BLOCK (venfy)CM RCS HTRS - OFFCM RCS LOGIC - OFF

SYSTEMS TEST PANEL CONFIGURATIONSYS TEST METER - 4BRNDZ XPNDR - OPERATECM RCS HTRS - OFFWASTE H20 DUMP - OFFURINE DUMP - OFF

LEB LIGHTING - OFF

SEC WATER EVAP ACTIVATIONGLY To RAD SEC vlv - BYPASSSEC COOL EVAP - EVAPSEC COOL PUMP - AC2

36

37

38 -OO45m

-22-

PYRO BATT CKcb PYRO A SEQ A - close (ver~fy)

cb PRYO B SEQ B - close (verify)DC IND - PYRO BAT A(B)

~If PYRO BAT A(B) lt 35 vdc cb PYRO A(B) seq A(B) - open~

PYRO A(B)BAT BUS A(B)TO PYRO~MN BUS TIE - close

cb MNA BAT C - closecb MNB BAT C - closeDC IND - MNBPNL 8 - All cbs closed except

PL VENT - open (ver~fy)

FLOAT BAG (3) - open (ver~fy)

DOCKING PROBE (2) - open (verlfy)EDS BAT (3) - open (ver~fy)

CM ReS HTRS (2) - open

CM RCS ACTIVATIONcb SECS ARM (2) - close (verlfy)cb SECS LOGIC (2) - close (verlfy)SECS LOGIC (2) - ONMSFN conflrm GO for PYRO ARM(~f poss)SECS PYRO ARM (2) - ARMCM RCS PRPLNT 1amp2 - ONCM RCS PRESS - ONRCS Ind sw - eMl then 2

He PRESS 3700-4400 pSlaMANF PRESS 287-302 pSla

SECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFF

P27 amp ENTRY PAD UPDATEGo To Entry Checkllst

Superclrc - pg ~2~3 _Hybnd - pg -----2~9L-__Normal Deorblt - pg __3L5L- _

-23-

52 SUPERCIRCULAR ENTRY

1 SET DET (up to ET)

2

3

4

5

3000(-30-00)

EMS INITIALIZATIONSET RNG TO PAD DATA RNGEMS FUNC - Vo SETSlew Scroll to Pad Data VIOEMS FUNC - ENTRY

RS I ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on (up)GDC ALIGN PB - PUSH amp HOLDYAW Tw - Pos~t~on RSI thru

45deg amp back to LIFT UPGDC ALIGN PB - ReleaseEMS ROLL - OFFA1~gn CDC to lMU

CM RCS RING A CKRCS TRNFR - CMcb CM RCS LOGIC MNB - openAUTO RCS SEL MNB (6) - OFFSC CONT - SCSTest R~ng A ThrustersSC CONT - CMCRCS TRNFR - SMAUTO RCS SEL (12) - MNAMNB

(hftoff conflg)cb CM RCS LOGIC MNB - close

OPTICS PWR - OFFCMP to COUCH

MN BUS TIE (2) - ONTAPE RCDR - REWIND

6 35middot0Om(-25middot 00)

-24-

SEPARATION CK LISTTVC SERVO PWR 1 - AClMNAcb ELS (2) - close (ver1fy)PRIM GLY TO RAn - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY vlv - OFFCAB PRESS REL vlv (2) - NORMGMBL MTRS (4) - STARTABORT SYS PRPLNT - RCS CMD (venfy)SM RCS PRIM PRPLNT (4) - ONVHF 11M (AampB) - OFFHI GAIN ANT PWR - OFFFC PUMPS (3) - OFFVer1fy s1ugle SU1t compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - 10101cb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2) - opencb HTRS OVLD (2) - openPOT H20 RTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANSEC COOL EVAP - RESETSEC COOL PUMP - off (etr)

MtiVR TO CMSM SEP P R ATTSC CONT - SCSCMC MODE - FREEMNVR TO PAD ATTR (0deg)PY----W)

-25-

SUPERCIRCULAR ENTRY (Cont~nued)

1

4100m(-1900)

P61 - ENTRY PREP

V37E 61E

k 05 09 01427 - ROLL REVERSED 05 09 01426 - IMU UNSAT ~

2 F 06 61 IMPACT LAT LONG HDS UPDN (+-)PRO (010

fps +00001)

3 F 06 60 GMAXVPREDGAMMA EIRecord

GMAXV400K----

GAMMA EI _PRO

(01deg fpsOldeg)

4 F 06 63 RTOGO (lnm) PAD _VIO (fps) PAD _TFE(m~n-sec)

Compare w~th ~M~SFN==C~f~o-r~P~GNS GONO GOIf NO COMM Set RTOGO amp VIO In EMS

amp lnltla11ze(ACCEPT) PRO(RECALC) V32E To 4

5 F 50 25

4300m

(-1700)

45 oOm(-1500)

500Om(-1000)

6 F 06 61

-26-

P62 - CMSM SEP amp PRE-ENTRY MNVRCAUTION Call No EXT Verbs In P62

00041 REQUEST CMSM SEPSC CONT - SCSFREE

COMPARE PITCH ATT WITH PAD DATA ---0=-

(W~thLU 5deg)YAW - 45deg OUT-OF-PLANE (LEFT)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTIRATE 2MN BUS TIE (2) - ON (ver~fy)

PRIM GLY TO RAD - BYPASS (verlfy)CM RCS LOGIC - ON (venfy)SECS LOGIC (2) - on (up)SECS PYRO ARM - ARMCMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 ps~a

CM RCS LOGIC - OFFSECS PYRO ARM (2) - SAFEMonltor VMAB

If lt25 vdc go to EMERGPOWERDOWN pg E6-l

AUTO RCS SEL AC ROLL (4) - OFFAUTO RCS SEL CM 2(6)-OFFAUTO RCS SEL CM 1(6)-MNAYAW back to 0degPITCH TO HORIZ TRACK ATT

ROLL - 0deg (LIFT UP)PITCH - 400K Horiz Mark (317deg)YAW - 0deg

ATT DB - MAXMAN ATT PITCH - ACCEL CMDEMS DATA - Ver~fy

EMS FliNC - ENTRY (ver~fy)

EMS MODE - NORMALcb SPS PampY (4) - openMAINT HORIZ TRK

PRO (Act ENTRY DAP)

IMPACT LATLONGHDSDN (01deg01deg-00001)PRO

7 POSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axis beyond 45deg of Vel vector)

8 06 64

58middot00m(-0200)

9

05G tlme(+0 )

(--=---)

06 68

-27-

P63 - ENTRY INIT

GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PIJR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRmDHORIZ CKPltch error needle goes toward

zero approachlng OSG tlmeMAN ATT (PITCH) - RATE CMD

If CMC lS GOBMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS I

FLY BETA If CMC NO GO ilt

1 SC CaNT - SCS I

FLY EMS k

p64 - ENTRY POST 05G

RTOGO AT 05G AGREES HITH EMS-venfyHORIZ CK05G Lt - ON (EMS START)

No EMS START wlthln 3 sec ~ EMS MODE - BACKUP VHF RNG c

05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds Llft DN

NNVR Llft DNEMS GONO GO

G-V Plot wlthln IlmltsRng ctr dwn 60plusmn7 durlng 10 sec

perlodMonltor G-meter for

convergence wlth pad data (Do)(Vlt27K fps) Go to 13

-28-

P65 - ENTRY - UP CONT (Vgt27K fps)

10 F 16 69 BETA (01middot) _DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT lt~ SC CONT - SCS FLY EMS

PRO

11 06 68 BETAVIHDOT (OIdegfpsfps)(VltV1+500 fps amp RnOT Neg) Go To 13

P66 - ENTRY - BALLISTIC (D(DL)

12 06 22 DESIRED GMBL ANGLES RPYMoultor horlz +12middot of 317middot mark

P67 - ENTRY - FINAL PHASE (02G)

13 06 66 BETACRSRNG ERRDNRNG ERR(010 1um 1um)

KEY VERBRecord DNRNG ERR _KEY RLSEMoultor l~ft vector ou RSI amp FDAI

16 67 RTOGOLATLONG (Vrel=1000fps)(lumOldegOldeg)

SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOWNMonitor a1t~meter

Go To EARTHLANDING pg ---4L5 _

-29-

53 GampN HYBRID DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL tV1 V37E 30E

2 F 06 33 GETI(ACCEPT) PRO (hrm~n Olsec)(REJECT) LOAD DESIRED GETI

3 F 06 81 tVXYZ (LV) (lfps)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

4 F 06 42 HAHPtV (lnm lfps)Record tV

(ACCEPT) PRO(REJECT) Reselect P30 or P27 Load new paramo

5 F 16 45 MTFIMGA (marksm~n-secOlO)

MGA -00002 ~f k

k lMU not al~gned

SET DETPRO

6

7

8

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (Pull)PLSS 02 vlv - FILL02 8M SUPPLY vlv - OFFCAB PRESS REL vlv (2) - NORMcb ELS (2) - closecb SECS ARM (2) - closecb SECS LOGIC (2) - close (ver~fy)

AUTO RCS SEL CM (12) - MNA or ~ffiB

(hftoff conhg)ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM (AampB) - OFF

CMP to Couch

9

10

11

-30-

MNVR TO PAD BURN ATTLOAD DAPBMAG MODE (3) - RATE 2SC CONT - CMCAUTOATT DB - MINMAN ATT (3) - RATE CMD

v62E

v49E

12 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLES

PRO

13 F 50 18 REQ MNVR TO FDAI RPY ANGLES (01deg)(AUTO) PRO(MAN) SC CONT - SCS

BMAG MODE (3) - RATE 2MNVR To 15

14 06 18 AUTO MNVR TO FDAI RPY ANGLES (01deg)

15 F 50 18 REQ TRIM TO FDAI RPY ANGLES (01deg)(TRIM) Go to 13(ByPASS) ENTR

16

17

CHECK BORESIGHT amp SKT STARSOPT MODE - CMCOPT ZERO - OFF

v41 N91E

18 F 21 92 SHAFTTRUN (01deg 001deg)Load SXTS angles

19 41 OPTICS DRIVECheck SKT STAR

OPT ZERO - ZEROCheck BORESIGHT STAR (~f ava~l)

20 V25 N17E (01deg)Load Pad Data GMBL Angles

for CM BURN ATTATT SETtw - SET

to PAD DATA GMBL ANGLESfor CM BURN ATT

21

22

-31-

PHR REDUCTIONHGA PHR - OFFFC PUMPS (3) - OFFVerify s~ngle su~t compr oper loads

balancedFC 2 MN AampB - OFFS BD PiR AMP - LOWcb ECS RAD CONTHTR (2) - opencb HASTE H20URINE DUMP HTRS(2)- opencb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANMN BUS TIE (2) - ONTVC SERVO PHR 1 - AC1MNAGMBL MTR (4) - START

p41 - RCS THRUSTINGV37E 41E

23 F 50 18 REQ MNVR TO LCL HORIZ (HDS ON)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CMCAUTOPRO To 24

(gtfANDAP) BMAG MODE (3) - RATE 2SC CONT - CMCHOLD

V62EMNVR To 25

24 06 18 AUTO MNVR TO FDAI RPY

25 F 50 18 REQ TRIM TO LCL HORIZ (01deg)ALIGN SC ROLL

(AUTO TRIM) PRO To 24(BYPASS) ATT DB - MIN

RATE - LOHMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTlRATE 2

ENTR

550Om26 06 85

59middot2527

-32-

VGXYZ (1fps)RECHECK BORESIGHT STARTRANS CONIR PWR - on (up)EMS MODE - STBY (ver~fy)

EMS FliNC - bV SETVHF RNGSET (IV for SM BURN _EMS FliNC - bVS BD ANT - OMNI CSECS LOGIC (2) - ONMSFN conhrm Go for PYRO ARMSECS PYRO ARM (2) - ARMCM RCS LOGIC - ON (ver~fy)

DSKY BLANKS

593028 16 85 VG XYZ (AVE G ON) (lfps)

RHCs amp THC - ARMEDLIMIT CYCLE - OFFTAPE RCDR - CMD RESETHBREMS MODE - NORMAL

000029 F 16 85 REQ NULL VG XYZ (lfps)

BURN EMS bV CTR TO ZERORESET DET amp COUNT UP

If SM ONLY burn go to step 32THC - LOCKEDSC CaNT - SCSFREERATE - HIGHPRIM GLY To RAD - BYPASS (ver~fy)

MN BUS TIE (2) - ON (ver~fy)

CMSM SEP (2) - on (up)CSMLM FNL SEP (2) - on (up) (verify)CampW MODE - CMRCS TRNFR - CMCM RCS LOGIC - OFF

Momtor VM ABIf lt25 vdc go to EMERGPOWER DOWN Pg E6-l

V63E

If CMC NO GO FDAI SOURCE - ATT FDAI SEL - 1 or 2 ATT SET - GDC

SET

-33-

~Uili ATT PITCH - ACCEL CMDFDAI SCALE - 55MNVR TO CM BURN ATT (NULL ERR NEEDLES)

R 0degPY --00--

30

31

CM RCS BURNRHC III-ContJnuous PJtch DownRHC HZ-Module PJtch to null needlesBURN VGZ TO ZERO

If only 1 RHC Pulse + P=5deg from retro att MaJnta~n rates lt3degsec

BURN COMPLETION ATllV CTR= or DET= _

V8ZE

32 F 16 44 HAHPTFF (1nmffiJn-sec)Check HP-

If gt Pad data contJnue burnuntJ1 lt Pad

PRO

33 F 16 85 VGXYZ (Ups)Read VG resJduals to MSFN

(HYBRID) PRO to 34(SM ONLY BURN)

PROF 37 ODE

EI-1500 V37E 47EF 16 83 twx Y Z (Ups)

SC CONT - SCSFREEMAN ATT (PITCH) - RATE CMDRATE - HIGHPRIM GLY To RAD - BYPASS (verJfy)MN BUS TIE (2) - ON (verJfy)CMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verJfy)Campl MODE - CMRCS TRNFR - CMCM ReS LOGIC - OFFSECS PYRO ~I (2) - SAFE

-34-

PROMonitor VMAB

If lt25 vdc go to EMERGPOWER DOWN

34 F 37 OOEPCM BIT RATE - LOWATT DB - MAXEMS MODE - STBYEMS FUNC - OFF

Go To EARTH ORBIT ENTRY pg _--40-__

-36-

8 SPS THRUSTING PREPCYCLE CRYO FANSSPS GAGING - ACI (ver~fy)

PUG MODE - NORM (venfy)BMAG MODE (3) - RATE 2tv CG - CSMCMC MODE - FREEAUTO RCS SEL (16) - MNA or HNB

(hftoff conbg)SC CONT - CMCAUTO

9 MNVR TO PAD BURN ATTV62E

10 V49E

11 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLESPRO

12 F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) PRO(HAN) SC CONT - ses

MNVR to 14

06 18 AUTO MNVR TO FDAI RPY ANGLES13

14 F 50 18 REO TRIH TO FDAI RPY ANGLES(TRIM) Go to 12(BYPASS) ENTR

15 BORESIGHT STAR CHECK

16 V37E 40EOPT PWR - OFF

17 F 50 18 REQUEST MNVR TO FDAI RPY ANGLES (01deg)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CHCAUTOPRO to 18

(MANDAP) BMAG HODE (3) - RATE 2SC CONT - CMCHOLDMNVR to 19

(HANseS) se eONT - sesMNVR to 19

-35-

54 NORMAL DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL ~V

1 V37E 30E

2 F 06 33 GETI (hrm~nOlsec)

(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

3 F 06 81 ~VXYZ (LV)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

( lfps)

4 F 06 42 HAHP~V (1nmlfps)Record W

(ACCEPT) PRO -----(REJECT) Rese1ect P30 or P27 Load new pa~am

5 F 16 45 MTFIMGA (marksmln-secOldeg)MGA -00002 If ~ lMU not a1~gned

SET DETPRO

6

7

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY v1v - OFFCAB PRESS REL v1v (2) - NORMcb ELS (2) - close (verify)cb SECS ARM (2) - close (ver~fy)

cb SECS LOGIC (2) - close (verlfy)AUTO RCS SEL CM (12) - ~mA or MNB

(l~ftoff conf~g)

ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM AampB - off (ctr)

18

-37-

06 18 AUTO MNVR TO FDAI RPY ANGLES (01 0)

19 l 50 18 REOUEST TRIM MNVR TOALIGN SIC ROLLGDC ALIGN

FDAI RPY ANGLES(010

)

+54-00m(-06-00)

TIG-5mJn

5500m(-0500)

TVC CHECK amp PREPcb STAB CONT SYS (all) - closecb SPS (12) - closeATT DB - MINRATE - LOl~

LIMIT CYCLE - ONMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE 2ROT CONTR PWR DIRECT (2) - OFFSCS TVC (2) - RATE CMD

If SCS SCS TVC (2) - AUTO SC CONT - SCS ~

TVC GMBL DRIVE PampY - AUTOMN BUS TIE (2) - ONTVC SERVO PWR 1 - AC1MNA

2 - AC2MNBTRANS CONTR PWR - ONROT CONTR PWR NORMAL 2 - ACRHC 2 - ARMED

HORIZ CHK - HorJz on 12deg wJndmlmark (LJffiJt +3 0 PNGCS GONO GO)

If NO GO set tw 180 0 180deg0 0

Track horJz wJth 24deg wJndow markAt TIG-2 mJn Ahgn GDC

PRIMARY TVC CHECKGMBL MOT P1-Y1 -STARTON(LMP confJrm)

If SCS verJfy Thumbwheel TrJmTHC - CWVenfy NO MTVC

SEC TVC CHECKGHBL MOT P2-Y2 -STARTON(LMP confJrm)SET GPI TRIHVenfy MTVCTHC NEUTRALGPI returns to 00 (CMC) or trJm (SCS)ROT CONT Pl~ NORM 2 - ACDC

(TRIM) Go to step 17(BYPASS) BMAG MODE(3) - ATTIRATE2 (ver1fy)

ENTR

-38-

20 F SO 25 00204 GMBL TEST OPTION(ACCEPT) SC CONT - GMC (ver~fy)

PROMonitor GPI Response

0020-2000020-200Tr~m

TEST FAIL SC CONT - SCS SCS TVC (2) - AUTO

(REJECT) ENTR

21 06 40 TFIVG~VM (m~n-sec1fps)

PROG ALM - TIG s1~pped

V5N9E 01703

KEY RLSE To 21 ROT CONTR PWR DIRECT (2) - MNABSPS He v1vs (2) - AUTO (ver~fy)

LIMIT CYCLE - OFFFDAI SCALE - SOIScb SPS P2Y2 - open (for cr~t burn)

5800(-02 00)

5925(-0035)

59middot 30(-0030)

06 40

59XX(-OOXX)

AV THRUST A(B) - NORMALTHC - ARMEDRlIC (2) - ARMEDTAPE RCDR - GID RESETHBR

DSKY BLANKS

(AVE G ON)EMS MODE - NORMAL

TFIVG~VM (m~n-seclfps)

CHECK PIPA BIAS lt2fps for 5 sec

ULLAGE AS REQ

IF NO ULLAGE DIR ULLAGE PB - PUSH~

CONTROL ATT WRlIC MONITOR AVM (R3) COUNTING UP

5955(-0005)

F 99 40 ENG ON ENABLE REQUEST(AUTO IGN) PRO AT TFI gt0 sec(BYPASS IGN) ENTR to 24

22 0000 IGN

-39-

If SCS - THRUST ON PB - PUSH

06 40 TFCVG~VM (m~n-seclfpslfps)

~F 97 40 SPS Thrust fall ~

~(RESTART) PRO To IGN (RECYCLE) ENTR To TIG-05 sec

SPS THRUST LITE - ONMONITOR THRUSTING

Pc 95-105 pSlaEMS COUNTING DOWNSPS IN3 v1vs (4) - OPENSPS He v1vs tb (2) - graySPS FUELOXID PRESS - 175-195 pSlaPUGS - BALANCED

PROG ALARM V5N9E 01407 VG INCTHC - CW FLY MTVC

ECOEMER SPS CUTOFF J

AV THRUST (2) - OFF

23 F 16 40 TFC(STATIC)VG~VM (mln-seclfps)~V THRUST AB - OFF

SPS IN3 v1vs (4) - CLOSEDSPS He tb (2) - bp

cb SPS P2Y2 - closed (verlfy)TVC SERVO PHR - AC1MNA (venfy)TVC SERVO PWR 2 - OFF

PRO

24 F 16 85 VG XYZ(CM) CUps)NULL RESIDUALSRECORD ~V CTR amp RESIDUALS I1VCEMS FUNC - OFF VGXEMS MODE - STBY VGYBMAG MODE (3) - RATE 2ATT DB - MAX VGZTRANS CONT PHR - OFF

PRO

25 F 37 V82E

26 F 16 44 HAHPTFF (lnmm~n-sec)

R3-59B59 HP gt494 nmPRO

27 F 37 OOE

-40-

55 EARTH ORBIT ENTRY

1 Venfy CMSMR __

P_shyY_-

SEP ATT(180deg)

(0deg )

2

3

4

EMS INITIALIZATIONEMS FUNC - RNG SETSET RNG TO PAD DATA RNGEMS FUNC - VA SETSlew scroll to pad data VIOEMS FUNC - ENTRY

RSI ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on(up)GDC ALIGN PB - PUSH amp HOLDYAW tw - Pos1tion RSI thru 45deg amp

back to LIFl UPGDC ALIGN PB - RELEASEEMS ROLL - OFFAl1gn GDC to lMU

PWR REDUCT (Norm Deorb Only)HGA PWR - OFFFC PUMPS (3) - OFFVer1fy s1ngle suit compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - Lowcb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2)-openlOb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MAN

-41-

P61 - ENTRY PREP

5 V37E 61E05 09 01427 - ROLL REVERSED05 09 01426 - IMU UNSAT

6 F 06 61 IMPACT LAT LONG liDS UPDN (+-)(01 0

010

+00001)

PRO

PAD VALUESLATLON==G------liDS UP DN _

7 F 06 60 GMAXV400KGAMMA EIRecord

GMAXV400K----GAMMA EI _

PRO

8 F 06 63 RTOGO (1nm) PAD _VIa (fps) PADTFE (mln-sec) ----Compare wlth MSFN for PGNS GONO GONO COMM SET RTOGO amp VIO IN EMS amp

INITIALIZE(ACCEPT) PRO(RECALC) V32E to 8

-42-

P62 - CMSM SEP amp PRE-ENTRY MNVR

9 F 50 25 00041 REQUEST CMSM SEPSC CONT - SCSFREEYAW - 45deg out-of-plane (left for RCS

nght for SPS)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE2PRIM GLY to RAD - BYPASS (verlfy)SECS LOGIC (2) - on (up)MSFN conflrm GO for PYRO ARMSECS PYRO ARM - ARMMN BUS TIE (2) - ON (verlfy)CMSM SEF (2) - ONCSMLM FNl SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 pSlaCM RCS LOGIC - OFFSECS PYRO ARM - SAFEMonltor VMAB

If lt25vdc go to EMERG POWERDOWN Pg E6-1AUTO RCS SEL AlC ROLL (4) - OFFAUTO RCS SEL CM 2(6) - OFFAUTO RCS SEL CM 1(6) - MNA or MNBYAW back to 00

PITCH TO ENTRY ATTROLL 0deg (LIFT UP)PITCH - HORIZ on 317deg MARK (400K)YAW 00

ATT DB - MAXMAN ATT (PITCH) - ACCEL CMDEMS DATA - VerifyEMS FUNC - ENTRY (verlfy)EMS MODE - NORMALMAINTAIN HORIZ TRK

PRO (Act ENTRY DAP)

10 F 06 61 IMPACT LAT LONG HDSDN(010 010 -00001)

PRO

11 FOSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axlS beyond 45deg of Vel vector)

-43-

P63 - ENTRY INIT

12 06 64 GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PWR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRHORIZ CKP~tch error needle goes toward

zero approach~ng 05G t~me

MAN ATT (PITCH) - RATE CMDIf CMC ~s GO

BMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS FLY BETA If CMC NO GO ~

SC CONT - SCS~

FLY EMS RCS Deorh Roll HDS UPTRACK HORIZ w~th 29deg w~ndow mk

P64 - ENTRY POST 05G

13

05G t=elt+0___)

06 68

RTOGO AT 05G AGREES WITH EMS - venfyHORIZ CK05E Lt - on (EMS start)

No EMS start w~th~n 3 secsEMS MODE - BACKUP VHF RNG 05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds L~ft DN

NNVR L~ft DNEMS GONO GO

G-V Plot w~th~n llm~ts

Rng ctr dwn 60 + 7 durlng 10 sec per~od

Mon~tor G-meter forconvergence wlth pad data (Do)

(Vlt27K fps) Go To 17

-44-

P65 - ENTRY - UP CONT (Vgt27K fps)

14 F 16 69 BETA (01deg)DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT~

SC CONT - SCS FLY EMS

PRO

15 06 68 BElA VI HOOT (01deg fpsfps)(VltVL +500 fps amp RDOT Neg) Go To 17

p66 - ENTRY - BALLISTIC (DltDL)

16 06 22 DESIRED GMBL ANGLES RPY (01deg)Mon~tor hor~z +12deg of 317deg mark

P67 - ENTRY - FINAL PHASE (02G)

17 0666 BETACRSRNG ERRDNRNG ERR (Oldeglnmlnm)KEY VERBRecord DNRNG ERR _KEY RLSEL~m~t +100nm from PAD DRE

Mon~tor l~ft vector on RSI amp FDAIF 16 67 RTOGOLATLONG (Vre1=1000fps)

(lnm 010 01deg)SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOlfflMon~tor altimeter

Go To EARTHLANDING pg _I4L5__

-45-

56 EARTHLANDING

90K STEAM PRESS - PEGGED50K CABIN PRESS REL vIv (2) - BOOSTENTRY

SECS PYRO ARM (2) - ARM

40K(90K + 63s)

CM UNSTABLE RCS CMD - OFF ~ 40K APEX COVER JETT PG-PUSH DROGUE DEPLOY PG - PUSH (2 secafter apex cover Jett)

30K ELS LOGIC - ON (up)ELS - AUTO

24K RCS hsable (auto)(90K+92s) RCS CMD - OFF

Apex cover Jett (auto)APEX COVER JETT PB - PUSH

(WAIT 2 SECS)Drogue parachutes deployed (auto)

DROGUE DEPLOY PB - PUSH~

If Drogues FallELS - ~ ~Stablllze CM 5K MAIN DPLY PB - PUSHELS - AUTO

235K Cabln Pressure lncreaslng (Drogues + 50s)If not lncreaSlng by 17K CABIN PRESS REL vlv (RR) - DUMP

-46-

10K Maln parachutes deployedMAIN DEPLOY PB - PUSH (wlthln 1 sec)VHF ANT - RECYVHF AMA - SIMPLEXVHF BCN - ONCABIN PRESS REL v1v (2) - CLOSEDIRECT 02 vlv - OPENCM RCS LOGIC - on (up)CM PRPLNT - DUMP (burn audlb1e)Monltor CM ReS 1amp2 for He press decrease

NO BURN or PRESS DECREASE USE BOTH RHCs DO NOT FIRE PITCH JETS

CM PRPLNT-PURGE (to zero He press)CM RCS He DUMP PB - PUSH RHC (2) - 30 sees NO PITCH k

STRUT LOCKS (2) - UNLOCK

cb FLT amp PL BAT BUS ABampBAT C (3) - closecb FLT amp PLT MNA amp B (2) - opencb ECS RAD HTR OVLD (2) - opencb SPS PampY (4) - open

3K CABIN PRESS REL v1v (RH) - DUMP (after purgecompleted)

FLOOD Lts - POST LDGCM RCS PRPLNT (2) - OFFROT CONTR PWR DIRECT (2) - OFF

800 CAB PRESS RELF vlv - CLOSE (latch off)MN BUS TIE (2) - OFF

AFTER LANDINGcb MAIN REL PYRO (2) - closeMAIN RELEASE - on(up)

Go to POSTLANDING pg _47L-__

I

2

3

-47-

57 POSTLANDING

STABILIZATION VENTILATION COMMUNICATIONS

DIRECT 02 vlv - CLOSE

Stablllzation after landlngELS - AUTO (verlfy)cb MAIN REL PYRO (2) - close (venfy)MAIN RELEASE - on (up) (verlfy)S~CS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb BAT RLY BUS (2) - open

No contact w1th recovery forcesVHF AM AampB - off (ctr) ~

VHF AM Rev ONLY - A cb PL VENT - closecb FLOAT BAG (3) - closecb UPRIGHT SYS COMPRESS (2) - closeIf Stable II

FLOAT BAG(3)-FILL t1ll 2 m1n afterupr1ght then - OFF

VHF AM AlB amp BCN - OFF whlle lnvertedIf Stable I

After 10 M1n Coollng Per1odFLOAT BAG (3) - FILL 7 mln then OFF

Post Stab1lizat1on And Ventllat10nPL BCN LT - BCN LT LOWPL VENT vlv - UNLOCK (Pull)Remove PL VENT Exh CoverPL VENT - HIGH or LOWPL DYE MARKER - ON (swlmmer comm)Release foots traps and_restralntscb MNA BAT BUS A amp BAT C (2) - opencb MNB BAT BUS B amp BAT C (2) - opencb FLT amp PL BAT C - opencb PYRO A SEQ A - opencb PYRO B SEQ B - open

EACH HR - CHECK DC VOLTSgt 275 V If Notmiddot cb FLT amp PL-BAT BUS AampB (2) -open cb FLT amp PL BAT C (1) - open GO TO LOW POWER CHECKLIST

Unstow and lnstall PLV DISTRIB DUCTDeploy grappllng hook and 11ne 1f req

4

-48-

Post Landing Communlcatl0nsVHF ANT-RECY (venfy)VHF BCN - ON (verlfy)

If no contact ~lth recovery forcesperform VHF BEACON Check

MONITOR VHF BEACON transmlSSlonnth VHF AM B Rcvr andor Su)vlval

TransceiverkVHF Beacon not operatlng ~connect Surv~val TranscelVer to antcable behlnd VHF ant access pnland place radio ln BCN mode

LOW POHER CHECKLISTVHF BCN - OFFVHF AM (3) - RCVFLOOD Lts - OFFVHF AM AampB - off (ctr)VHF AM RCV ONLY - A (venfy)COUCH LIGHTS - OFFPOSTLANDING VENT SYS mlnlmlze useSURV RADIO - plug mto VHF BCN ANT cableconn behind VHF ant acess pnl amp turn radloon l-n BCN mode

EGRESS PROCEDURES

CMPCDRLMPCDR

CMPCDRCMP

LMPLl1PCDR

STABLE IDlsconnect Umblll-calsNeck darn onCenter couch - 270 0 positionArmrests stowedConnect raft to SIC l-f desl-red wlth

green lanyardConnect raft ~hl-te lanyards to SUltS amp

lnflate water wlngs when eXltl-ngHATCH PISTON PRESS vlv - PRESS (Outbd)Slde Hatch openedPL VENT - OFFcb Pnl 250 (all) - openEgress with 11feraftPut hardware klt outEgress

or CDIPALL

CMF

CDRCMF

CDR

LMF

CMFCMP LMFCMP

UlP

CDR

-49-

STABLE IIcb CREW STA AUDIO (3) - openD~sconnect umb~1~ca1s

Release foots trapsRelease restra~nt harnessCouch seat pans (3) - 170 0 pos1t10nArm rests stowedSurv1va1 k~ts removed from stowageConnect life raft ma~n1~ne to CDR or SicConnect f~rst wh~te lanyard from

11fe raft to suitConnect th~rd wh~te lanyard from

l~fe raft to SU1tConnect rucksacks together to yellow

lanyard on raft bagPRESSURE EQUALIZATION vlv - OPENRemove and stow fwd hatchEX1t feet f1rst w1th rucksacks when clear

of siC 1nflate water w1ngs and raftExit feet f1rst when clear of SiC

1nflate water w1ngsEX1t feet f1rst when clear of sic

1nflate water w1ngs

-50-

60 TLI ABORTS

TLI Aborts are conta~ned ~n the ESD s~nce the bulk of the funct~ons

concern entry preparat20ns and performance Th~s allows a s2nglesource of procedures for procedure rev2ew val~dat~on checkout andtra~n~ng These procedures ~ncorporate TLI preparat20ns as found ~n

reference 6 w~th the TLI Abort Procedures and these t~e 2nto normallunar return Entry Procedures found ~n sect20n 5 The guidel~nes

for th~s cont2ngency are spec2f2ed 2n reference 7

In2t2al preparat~ons for TLI pos2t20n the necessary system sW2tches2n add~t~on to perform~ng an EMS ~V test and a GDC al~gnment Afterthe DET ~s set for mon2tor2ng TB6 the CMP ~ncreases the 12ght levelof the LEB DSKY to max~mum and returns to the h2s couch Th2s 2Sdone so that the LEB DSKY can be observed ~n the event sunl~ght orreflect20ns wash out the ma2n d2splay panel DSKY dur2ng cr2t2calmaneuvers The crew then straps ~n and prepares for mon2tor~ng TB6as 2nd2cated by the SII SEP L~te The t2mes se~uence of procedures2S keyed on th~s d~splay and ~ncludes the DET START funct~on andSIVB IGNITION Dur2ng the burn the crew mon2tors the FDAIs foratt~tude excurs20ns and abnormal rates report~ng status checks toM~ss2on Control at d2screet t~mes dur2ng the maneuver Upon SIVBSHUTDOWN the eMP records the DSKY d~splayed performance parametersand awa2ts ground conf2rmat~on

The rat~onal for TLI aborts ~s descr~bed 2n reference 7 A summar2shyzat20n 2S extracted to prov2de background and gu2de12nes 2n th2sdocument The abort procedures cover aborts 10 m2nutes after conshyt2ngent SIVE shutdown and aborts 90 m2nutes after normal SIVE shutshydown t2me

The 10 m~nute TLI abort ~s des2gned to be used dur~ng TLI ~n theevent a spacecraft problem develops Wh2Ch can result 2n catastrophe2f ~mmed~ate act~on 2S not taken If the s~tuat20n perm~ts the crewshould always allow the SIVB to complete TLI at wh~ch t~me the groundand crew can perform a malfunct~on analys~s to determ~ne ~f an abort~s adv~sable If a fa~lure occurs that necess2tates the shutdown ofthe SIVB and the ~u~ck return of the crew to earth th~s abort ~s

des~gned to be as ~nsens~t~ve to execut~on errors as poss~ble andst21l be targeted to m2dcorr2dor The burn att~tude w~th the f~ed

hor~zon reference ~s a constant value for any shutdown t~me Theburn durat~on 2S a funct20n of shutdown t2me and 2S ava21able fromcrew charts S~nce the pr~mary purpose of th~s abort ~s to returnto earth as qU2ckly as poss2ble there are no restr2ct20ns as toland~ng locat~on However ~f the t~me to EI is greater than abouttwo hours a midcourse correct20n should be ant~c~pated

The 90 m2nute TLI abort 2S to be used 2f a cr2t2cal subsystem malshyfunct~on ~s determ2ned and the dec2s~on to abort ~s made after the

-51-

TLI cutoff and before TLI cutoff plus approxlmately 80 m1nutesTh1S allows suff1c1ent separatlon and procedural t1me to set upfor the SPS deorb1t burn performed at about TLI + 90 Note thatgenerally the deorb1t burns w1ll be performed a fe11 m1nutes beforeTLI + 90 accord1ng to crew charts shown In reference 8 The no-comm except10n requ1res that 90 m1nutes be the 1nput t1me of 19n1shytlon for P-37 (onboard return-to-earth abort program) so that onshyboard calculatlons can correspond w1th ground calculat10ns to computethe CM land1ng p01nt Th1S TLI abort lS des1gned so that returnfl1ght t1me does not exceed 18 hours and abort ~V does not exceed7000 fps ThlS abort can be performed uSlng chart ~Vs and attltudesand the earths hor1zon serves as a suff1c1ent reference The maneushyver lS targeted to ach1eve the mldcorr1dor entry target Ilne andtlmed to result 1n a deslgnated recovery area

It 1S ObV10US for abort deC1S1ons early 1n the TLI + 90 m1nute t1meshyframe that a GampN SPS burn should be performed In order to keep theTLI abort procedures cons1stent and w1th emphasls on slmpl1c1ty theprocedures here reflect a SCS SPS abort burn to cover the full abortdec1s1on t1meframe

A m1dcourse correct1on for corr1dor control after a TLI abort may bedeS1red 1f the SPS burn d1d not meet expectat1ons The TLIabortprocedures 1n th1S sect10n adapt to the normal lunar return tlmel1neand procedures pr10r to the f1nal MCC

-52-

61 TLI PREPARATION PROCEDURES

GET = 150

CRO AOS(___)

CRO LOS( )(22142)

5100

Don Helmets amp Gloves

XLUNAR - INJECT (verify)EDS PWR - on (venfy)EMS FUNC - OFF (verlfy)EMS MODE - STBYEMS FUNC - IW SETVHF RNGEMS MODE - NORMALSet ~V indo to +15868 fpsEMS FUMC - ~V Test

SPS THRUST Lt - onoff (10 sec)~V lnd stops at -01 to -415

EMS MODE - STBYEMS FUMC - ~V SETVHF RNGSet ~VC

EMS FUNC---~~V=----

GDC ALIGNFDAI Select - liZcb SECS LOGIC (Z) - close (verify)cb SECS ARM (Z) - closeSECS LOGIC (Z) - on (up)MSFN Conflrm GO for PYRO ARM (If pass)SECS PYRO ARM (Z) - on (up)TRANS CONTROL PWR - ONROT CONTR PWR NORMAL (Z) - ACDC(verlfy)ROT CONTR PWR DIRECT (Z) - MNAMNBLV INnGPI - SIISIVB (venfy)LV GUID - IU (venfy)cb DIRECT ULLAGE (Z) - closedSet EVENT TIMER to 5100Begin MONITOR For TB6

CMP to Couch

TB 6 - SII SEP Lt on (TIG-9 mln 38 sec)KEY V83E

SET ORDEALFDAI Z ORB RATE at 180 0 0SII SEP Lt out (38 sec later)Start DET COUNTING UPSC CaNT - SCS (verify)MONITOR LV TANK PRESS

~P lt 36 psid (OXID gt FUEL)~P lt Z6 psid (FUEL gt OXID)

EMERGENCY CSMLV SEP UP TLM CM - BLOCK (verify)UP TLM IU - BLOCK (venfy)

-53-

+45degPY))0middot sec PY

lOK nmltHAlt25K nm

Two phas~ng mnvrs two SPS mnvrs to circular~ze at 150 nmearth orb~t

CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ssion 4K nmltHAltlOK nm CSM amp1M - Two phasing mnvrs two SPS mnvrs to circularize at 150 nm earth orb~t CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ss~on

CSM amp 1M - Two phas~ng mnvrs APS burn todepletion th~rd phasing mnvrSPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn tosem~sync orb~t

25K nmltHAlt40K nm CSM amp 1M - Two phasmg mnvrs APS burn to depletion third phas~ng mnvr SPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn to sem~sync orbit HA)40K nm DPS ava~l - DPS LOll circularize with SPS

DPS not ava~l - Lunar flyby or CSM only to lunar orbit (if reqd gtV lt4000 fps)

V37E 47E (check b~as) Record -=--rshy(Limit 98 fpsmm)

( 1fps)tVXYZN62EVIHDOTHPAD (fpsfpslnm)MONITOR VI ( ) at ECO

SCS TVC SERVO PWR 1 - ACIMNA2 - OFF

TAPE RCDR - CMD RESETHBREMS MODE - NORMAL

SIr SEP Lt - ONTLI Inhib~t S~gnals w~11 not be honored after 5942

SIVB ULLAGE BeginsSII SEP Lt - off (TIG - 18 sec)SIVB FUEL LEADSIVB ULLAGE d~scont~nues

LV ENG I Lt - onSIVB IGNITION ( GETI)LV ENG I Lt - off - -shyMONITOR THRUST amp ATTITUDEMONITOR LV TANK PRESSSIVE ECO (Lt on) (BEGIN TB7)

EMER SIVE CUTOFF AT 6 SEC PAST BURN TIME IF VI ATTAINEDTHC CCW ampNEUTRAL IN 1 SEC or SIISIVB sW - LV STAGEPremature Shutdown HAlt4K nm CSM amp 1M -

5700

58205836

F 16 835800

F 16 62

5838594259525955595900000002SUNRISE(___)

HAW AOS(__=_) KEY VERB (freeze d~splay)

SIVB ATT HOLD 20 sec amp BEGIN VENTINGSIVB NNVR TO ORB RT (HDS DN) (3middot sec)

Record VI -c---HDOT _

HPAD _

KEY RLSEF 16 62

F 16 83

HAW LOS(__=-)

KEYmiddotRLSE~VXYZ (lfps)

Record ~VX---_

~vy

WZ--

AVC---_

TAPE RCDR - off (ctr)EMS MODE - STBYEMS FUNC - OFFSECS PYRO ARM (2) - SAFE

PRO

BURN STATUS REPORT

____--~TIG

BT------VGX____-R

-----P----_Y

REMARKS

_____VI

______--HDOT______--H______---AVC______---FUEL_______OXID

_______UNBAL

F 3708=00 OOEGOS AOS CMP TO LEB

(-=-=-)

0000

0003

0005

0014

0100

-55-

62 TLI 10 MIN ABORTSECS LOGIC (2) - on (up)SECS PYRO ARM (2) - ARM

TRANS CONTR - CGH (4 sec) amp +XDET RESET (verlfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS GMD-ON

TRANS GONTR - neutral then +X for10 sec

SIVBGPI s~ - GPIExcesslve rates 6V THRUST A - NORMAL SPS THRUST - DIRECT When rates damped 6V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

TRANS CONTR +X - OFFV37E OOE

PITGH UP to LOGAL VERT (+X axlSto~ard the earth)

RATE - LOWBMAG MODE (3) - ATTIRATE 2EDS PHR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SEGS ARM (2) - opencb EDS (3) - open

TRANS CONTR -X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (180deg)P (199deg)Y (0deg)

RETRO UPDATEGETI _

JV _VG

Jtb ---GET 400K _

05G _GET DROGUE _

ENTRY P _R _

Y_--

0945

-56-

ALIGN HORIZ ON RET +1 MKGMBL CHECK (T11lle Pentattlng)MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conflnn)cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FUMC - JV SETVHF RNGSET JV from chartE~S FUMC - JVEMS fODE - NOIDlAL

lV THRUST A - NORMALV37E 47E (THRUST fONITOR)

F 16 83 lVXYZ (1 fps)

0950

1000

NOTE For aborts durlng 1st mln of TLIKEY V82E F 16 44 (HaHpTff)Burn untll Hp lt 19NM

TRANS CONTR +X

THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN JV reqdJV THRUST (2) - OFFReport cutoff

cb SPS P2 Y2- closeGfBL MTRS (4) - OFF (LMP Confinn)TRANS CONT PWR - OFFTVC SERVO PWR (2) - OFFMN BUS TIE (2) - OFFcb SPS P1amp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREIf est time to EIltOl5500 omlt fCC andenter the SUPERCIRC CKLIST as early as pos-slb1e Pg ~2~3~ __If est time to EI)Ol5500 anticlpate afCC Enter the ENTRY PREP CKLIST at step 9pg 18

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

-2tl C

l I W gt- ~-4

z laquo I I- 0 -6

l- I J u gt- ~-8

z w w -10

~_ONSANT

9O

VER

SHO

OT

BOU

ND

ARY

LIF

TV

EC

TOR

OR

IEN

TATI

ON

LIN

E

SH

ALL

OW

TAR

GE

TLI

NE

STE

EP

TAR

GE

TLI

NE 12

gU

ND

ERSH

OO

TBO

UN

DAR

Y

RE

EN

TRY

CO

RR

IDO

R

I ~ I

-12 24

26

28

30

32

34

RE

EN

TRY

VE

LOC

ITY

VE

1-F

TS

EC

Ch

art

1

36

3B

6-i

~

5CM

CC

ON

ST

NT

DR

VI z gt

~

I4

0 Cl W

I

gtamp

J+

-I

-

J Cl z

2U

l z 0_bull

bull-1

+-

u ubullbull

~r

U

)

2829

JOn

J23

33

43

5IN

ER

TIA

LR

EE

NTR

YV

ELO

CIT

YA

T4

00

00

0fl

VE

I-F

TS

EC

Ch

art

2

J63

73

8X

03

-i- rtREQUIRED PITCH GIMBAL ANG LETO OBTAIN HOR-IZON AT 317

DEGREES IN wiiiiDOW

260

z~I- ~ i5 24000

1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

-I

-1-

NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

I LU HD~-

LUHD

lt0 120UJ0

~

80 HOLD PRESENT TRIMgt LU HD013

~Y~HOIgtlt

TOP OF WINDOWa 40to

31 7 SCRIBEaaI

80 TTOM OF WINDOWi= 0

0--ltoa

-40t-z

~~~Uw w u lt0 -80

HOLO PRESENT TRIlJCl

LOHU0 lt0

J gt -120 HOLD 059 TRIMlt0 z

LDHUlt0 FIELD OF VI S10 NLDHU LIFT-DOWNHEADS -UPLUHD LIFT-UP HEADS-DOWN

~~H~-160 q - P63 LIMITI- NOrE-VALIO ONLY FO~t~--

LUNAR RETURN VELOCITY

plusmnl8020 244middot 8 12 16

TIME TO 400K FT ALTITUDE-MIN

4

P37

LONG

ITUD

ECO

RREC

TION

TOOB

TAIN

1350

NM

ENTR

YRA

NGE

Ugt

UJ

cgt

3z 0 I- u U

J0

0

0

2I

U~

UJ

cgt

I

gtI- U

gt z 0 J ltJ

1 -0

340

344

348

352

356

364

368

x10

3

CMC

INER

TIAL

VELO

CITY

AT40

0KAL

TITU

DE-

FTS

EC

Ch

art

5

I l I

o

20 100 -40

-10

-50

30

-20

--

+

-BB

A+

lrBB

A

=----

-----

t~I

AB

SA_

-04

0A

AV

Z=

-()4

D_

+

j

+

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tfJ i~

plusmniff

--d~~tj

h-

Ir

at

it

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60--

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2030

NOTE

40

NO

MIN

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RET

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90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 13: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

32

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40 EARTH ORBITAL DEORBIT AND ENTRY TECHNIQUES

As outl~ned ~n reference 5 a nom~nal PGNCS entry from earth orb~t ~s

based on a preparat~on t~me of 2 hours and 40 m~nutes ~nclud~ng 2n~ght passes Th~s t~me ~ncludes approx~mately 20 minutes before thef~rst n~ght pass after the CMC update and PAD data have been rece2vedTh~s t~e also 2ncludes approx2mately 20 m2nutes after the secondn~ght pass to allow suffic~ent t2me to prepare for retrof2re after theIMU f2ne a12gnment It has been determ2ned coarse a12gnment accuracy~s adequate for retrof~re and entry and undoubtedly other funct20nscould be om2tted depend2ng on the c2rcumstances for the dec2s20n toreenter Descr2bed here2n are the nom2nal earth oro2tal entry proshycedures w2th pert2nent comments on system va12dat20n for real timeacceptance dec~s20ns

After the entry dec~s~on is made the crew transfers the PGNCS fromthe standby to the operate mode and rece~ves a CMe update w~th P27Next the maneuver PAD update ~s v02ced up and the 2n~t~al entry mode~s determ~ned During the ~n~tial n~ght pass the IMU or2entat~on ~s

estab12shed uS2ng P51 star s~ght2ngs to obta2n a REFSMMAT The preshyferred or~entat~on opt20n ~n P52 2S then selected to coarse a12gn theIMU uS2ng the des2red entry REFSMMAT determ2ned by MGG-H The GOO ~s

now al~gned to the IMU 2n preparat~on for an IMUSes dr~ft check Ifthe GOO ~nd~cates the ses dr2ft rate exceeds 10 degrees per hour ~n

any ax~s the check ~s repeated on the other BMAGs to estaol~sh if theGOO or Just the single set 2S unusuable Var20us sytem checks as 12sted2n sect20n 51 are performed as necessary cons2stent w2th the t2me12ned2ctates of the maJor act2v2t2es Included 2n these checks are the EMSself-tests and the dV counter test The latter requ2res the spacecraftbe placed ~n dr2ft2ng fl2ght w~th the funct20n sW2tch 2n the dV pos2t~on

If the counter reg2sters a change of more than 25 feet per second w2th2n100 seconds the scroll and counter are unre12able for mon2tor2ng thedeorb2t burn and entry rang2ng If the EMS self-test fails and t2medoes not allow further analysis a 5555 ERE entry 1S planned as thePGNGS backup entry mode After complet2on of these checks the entryPAD lS prov1ded by MeG-H The crew then selects the external dVprogram P30 and the appropr2ate deorb1t tbrust1ng program p40 or P41Dur2ng th2s per2od wh2ch 2ncludes the f1nal n2ght pass P52 may beselected to ver2fy the IMU a12gnment Since the retro att2tude hasbeen computed so that a w2ndow mark c01nc2des w2th the hor2zon atGETI th2s serves as the conclus2ve check on the PGNCS At 5 m2nutesbefore retrofire the att2tude check 1S made by ver1fY2ng that the 12degree scr~be 12ne ~s w2th2n 3 degrees of the hor2zon If not thePGNeS has fa2led and the ses 2S used for att2tude reference and the

V counter for burn durat~on control S2nce the ses att~tude wasa12gned to the IMU a real~gnment ~s necessary This ~s accompl~shed

by manually maneuver2ng the spacecraft to ma~nta1n the 24 degree wlodowmark on the hor2zon and releas1ng the GOO a12gn button at TIG - 2 m2nutes

-14-

Upon complet~on of the burn the tN res~duals are burned to W~th~n

02 feet per second If the PGNCS ~V counter or est~mated burnduration are ~n d~sagreement ~t must be estab1~shed whether suff~shy

c~ent veloc~ty has been suppl~ed to put the land~ng po~nt in thefootpr~nt The PGNCS data w~ll be used ~f ~t ~s conf~rmed by oneother source if not the ~V counter w~11 be used ~f ~t ~s conf~rmed

by the burn durat~on t~me If add~tional ~V ~s necessary the data~s ava~lable to the crew on an onboard chart found ~n Sect~on 80

Post burn entry preparat~on requ~res EMS ~n~t~al~zation RSI al~gnshy

ment and pre-separat~on funct~ons The crew then selects the ~n~t~al

entry program P61 and records the d~sp1ays as a check aga~nst PADdata Upon complet~on of these checks P62 ~s entered The crewmanually or~ents the spacecraft to the separat~on attitude and yaws450 to ~nsure aga~nst possible CM 8M recontact After separat~on

the spacecraft ~s maneuvered to the reentry tr~m att~tude wh~ch

places the hor~zon on the 3170 w~ndow mark at EI Shortly thereshyafter ~n P62 the entry DAP is act~vated and P63 in~t~ated Dur~ng

th~s t~e MCC-H has computed a postburn update and ~t ~s vo~ced tothe crew ~f d~fferent from preburn values The EMS scroll and rangecounter w~ll be adJusted accord~ngly ~f t~me perm~ts A f~nal PGNCScheck pr~or to 05g may be mon~tored at th~s t~e w~th the CMC modein free and the manual att~tude p~tch ~n acceleration command wh~le

the hor~zon reference ~s held the p~tch error needle w~ll decreaseto zero as EI ~s reached At RET 005g the EMS mode sw~tch ~s

turned to manual the entry 005-g sw~tch and EMS roll sw~tch areturned on and the spacecraft control sw~tched to CMC to beg~n DAPcontrol At the PGNCS 005-g ~ndicatwn the program change fromP63 to P64 ~s mon~tored and the t~e vo~ce recorded At th~s t~me

the EMS range counter check ~s made dur~ng the 10 second per~od

follow~ng EMS 005g Dur~ng th~s per~od the counter should countdown 40 + 10 naut~cal m~les At PGNCS 02-g ~nd~cation the changefrom P64-to P67 ~s monitored and the ~splay may be held by key~ngVERB ~n order to record the init~al downrange error d~splay andcompare ~t to the PAD value The PGNCS has fa~led ~f the two do notagree w~th~n + 100 naut~cal m~les In the event P67 has not appearedwhen both the-g-meter and the scroll ~nd~cate greater than 05g thePGNCS has sim~lar~ly fa~led In e~ther fa~lure the SCS is used foratt~tude reference w~th an EMS entry If the checks agree the crewrema~ns w~th automat~c DAP for the rema~nder of the entry

The entry phase ~s essentially over when the relat~ve velocity ofthe spacecraft decreases to less than 1000 feet per second Th~s

~s ~nd~cated ~n P67 when RTGO lat~tude and long~tude are d~splayed

S~nce very l~ttle rang~ng capab~l~ty exists after th~s pOint thespacecraft is or~ented either full l~ft up or down depending onRTGO negat~ve or pos~t~ve and the crew prepares for the earth land~ng

phase

-15-

41 TYP~cal Retrof~re and Entry Sequence of Events

Dec~s~on to reenter

P27 (CMC update)

Retrof~re PAD update

Entry mode dec~s~on

P51 (IMU or~entat~on determlnatlon) durlng f~rst dark per~od

P52 (IMU coarse allgnment)

EMS checks

Entry PAD update

P30 (external AV)

p40 (SPS thrust)

P52 (IMU f~ne al~gnment) durlng second dark per~od

p40 (SPS thrust)

Ign~t~on att~tude check

Retroflre

P61

P62

CMSM separat~on

P63

Postburn PAD update

Entry attltude check

p64 (beg~n DAP control at O05g)

P67 (PGNCS gono go check at O2g)

42

Retrof~re

and

En

try

Alt

ern

atlv

es

Sys

tem

fa~lure

PGNC

S

PGNC

San

dEM

S

PGNC

San

dall

onbo

ard

att

ltu

de

refe

ren

ce

Fal

lure

bef

ore

Fal

lure

aft

er

Fal

lure

aft

er

com

mlt

ted

tono

ml-

com

mlt

ted

tono

ml-

com

mlt

ted

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all

lstl

cn

alG

ETI

(bef

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GET

I(a

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try

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GET

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-3m~ns)

del

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GET

I-5

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SCS

bu

rnatnom~nal

SCS

bu

rnat

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GET

an

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Sen

try

GET

Ian

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Sen

try

----

----

--

Del

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Del

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GET

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bu

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dro

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all

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-17-

5 0 DETAILED ENTRY PROCEDURES

In order to comblne slmilar procedures that are common to lunar returnentrles and earth orblt entrles the followlng procedures are dlvldedlnto categorles that allow a mlnlmum of dupllClty ThlS provldes asmaller tralnlng package and more closely resembles the onboard crewcheckllst when comparlson lS necessary

51 Entry Preparatlons for Superclucular and Earth Orbltal Entrles

1~e entry preparatlons are comblned In these procedures andsteps pecullar to elther superclrcular or earth orbltal entrlesare labeled accordlngly The tlme llstlngs In thlS sectlon areappllcable to only superclrcular entries Slnce the earth orbltalentry tlmellne lS a functlon of several varlables as descrlbedIn sectlon 40 and reference 5

-18-51 (Contlnued)

VEHICLE PREPARATION

l-

2

3

4

5

6 -0600h

7 -0535h

8

9

10 -0430h

INITIAL STOWAGE COMPLETED

CMC amp ISS START UP

SCS POWER UP

p51 - IMU ORIENTATION

LOAD DAPV48E 11102 01111 PRO ERO PRO

LAST MCC DECISION

NO COMM - P52 amp NAV SIGHTINGSNOMINAL - P2337 ONBOARD COMPARISON

DON MAE WESTS amp FOOT RESTRAINTS

VHF AM A - SIMPLEX

P 27 (SV REFSMMAT) MNVRamp ENTRY pAD UPDATES

11 -0415h P52 - IMU REALIGN(___) (OPTION 1)

12 P37 (NO COMM ONLY)

13

14

ECS CKS02 SUPPLY REFILLECS Monitor CkEVAP H20 CONT (2) vlvs - AUTOSUIT HEAT EXCH SEC GLY - FLOW

EPS CKS 1 3 4 (5 If reqd)

15 SPS CK (If req d)

16

17

18

RCS CKSSM RCS MOUlt CkCM RCS MOUlt Ck

CampW SYS CK

CMC SELF CK

19

20 -0345h

-03l5h-0300h

21

22

22A

-19-

DSKY COND LT TEST

MIDCOURSE MANEUVERP30 - EXT rVP404l - SPSRCS THRUSTINGMIDCOURSE (17) BURN

NO COMM NAV SIGHTINGS

ffiVR TO ENTRY ATT (Superc1rc only)V62E

V49E

22B F 06 22 DESIRED FINAL GMBL ANGLESLOAD ENTRY ATT PAD ANGLESPRO

22C F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) SC CONT - CMC

BMAG MODE (3) - RATE 2CMC MODE - AUTO

PRO(~N) SC CONT - SCS

MNVR to 22E

22D 06 18 AUTO MNVR TO FDAI RPY ANGLES

22E F 50 18 REQUEST TRIM(TRIM) Go to 22C(BYPASS) ENTR

23 -200hr BORESIGHT amp SXT STAR CHECKOPT MODE - CMCOPT ZERO - OFF

V41 N91E

F 21 92 SHAFT TRUNLoad SXTS angles

41 OPTICS DRIVE

CHECK SXT STAROPT ZERO - ZERO

CHECK BORESIGHT STAR (If ava11)

24 -0135h

25(___)

26

27 -0115h

-20-

P52 - lMU REALIGNRecord gyro torqu~ng anglesRp~----

YIf-7gt-Lno--re-c-ycle PS2If conflrmed use SCS for EMS entry

GDC ALIGNIf drlft gtLOohr change ratesource

FINAL STOWAGEOPTICS (except for hybrid)ORDEALGLY TO RAD SEC - BYPASS (verlfy)CooL pnl lnstalledY-Y struts (2) extendedStow Data Box R-12

EMS CHECKEMS FUNC - OFFcb EMS (2) - closeEMS MODE - STBYEMS FUNC - EMS TEST 1 (walt 5 sec)EMS MODE - NORMAL (walt 10 sec)

Check ind lts - offRANGE lnd - 00Slew halr1ine over notch

In self-test patternEMS FUNC - EMS TEST 2 (walt 10 sec)

05G It - on (all others out)EMS FUNC - EMS TEST 3

05G It - onRSI Lower It - on (10 sec Qater)Set RANGE counter to 58 nm+OO

EMS FUNC - EMS TEST 405G It - on (all others out)G-V trace w~thin pattern to lwr rt

corner 9GRANGE lnd counts down to 0+02

EMS FUNC - EMS TEST 505G It - onRSI upper lt - on (10 sec later)RANGE md - 00SCrlbe traces vertlcal llne 9g to

022+01ALIGN SCROLL TO ENTRY PATTERN (on

37K ft sec hne)EMS FUNC - RNG SET

G-V scroll assy traces vert llne022g to 0+01

EMS MODE - STBY

28

29

30 -OllOh

-21-

~V TEST (Deorb~t only)EMS FUNC - ~V SETVHF RNGSET ~V ~nd to 15868 fpsEMS MODE - NORMALEMS FUNC - ~V TEST

SPS THRUST LT - onoff (10 sec)~V ~nd stops at -01 to -415

EMS MODE - STBY

PRIMARY WATER EVAP ACTIVATIONGLY EVAP H20 FLOW - AUTOGLY EVAP STH PRESS - AUTOPRI ECS GLY PUMP - ACI

CM RCS PREHEATNote If sys test mtr 5cd6abcd

all read 39 vdc (28degF) or moreom~t preheat

cb RCS LOGIC (2) - closeCM RCS LOGIC - ONUP T1M CM - BLOCK (ver~fy)

cb CM RCS HTRS (2) - closeCM RCS HTRS - ON (LMP Conf~rm)

(20 mlU or III lowest rdg lS39 vdc) (Moultor Maufpress for press drop)

31 (___) FINAL GDC DRIFT CK (If req I d)If drlft gtlOohr Suspect GDC Do not

use RSI amp FDAI 2

32 -OO5Om

33

34

35

TERM CM RCS PREHEATUP TLM CM - BLOCK (venfy)CM RCS HTRS - OFFCM RCS LOGIC - OFF

SYSTEMS TEST PANEL CONFIGURATIONSYS TEST METER - 4BRNDZ XPNDR - OPERATECM RCS HTRS - OFFWASTE H20 DUMP - OFFURINE DUMP - OFF

LEB LIGHTING - OFF

SEC WATER EVAP ACTIVATIONGLY To RAD SEC vlv - BYPASSSEC COOL EVAP - EVAPSEC COOL PUMP - AC2

36

37

38 -OO45m

-22-

PYRO BATT CKcb PYRO A SEQ A - close (ver~fy)

cb PRYO B SEQ B - close (verify)DC IND - PYRO BAT A(B)

~If PYRO BAT A(B) lt 35 vdc cb PYRO A(B) seq A(B) - open~

PYRO A(B)BAT BUS A(B)TO PYRO~MN BUS TIE - close

cb MNA BAT C - closecb MNB BAT C - closeDC IND - MNBPNL 8 - All cbs closed except

PL VENT - open (ver~fy)

FLOAT BAG (3) - open (ver~fy)

DOCKING PROBE (2) - open (verlfy)EDS BAT (3) - open (ver~fy)

CM ReS HTRS (2) - open

CM RCS ACTIVATIONcb SECS ARM (2) - close (verlfy)cb SECS LOGIC (2) - close (verlfy)SECS LOGIC (2) - ONMSFN conflrm GO for PYRO ARM(~f poss)SECS PYRO ARM (2) - ARMCM RCS PRPLNT 1amp2 - ONCM RCS PRESS - ONRCS Ind sw - eMl then 2

He PRESS 3700-4400 pSlaMANF PRESS 287-302 pSla

SECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFF

P27 amp ENTRY PAD UPDATEGo To Entry Checkllst

Superclrc - pg ~2~3 _Hybnd - pg -----2~9L-__Normal Deorblt - pg __3L5L- _

-23-

52 SUPERCIRCULAR ENTRY

1 SET DET (up to ET)

2

3

4

5

3000(-30-00)

EMS INITIALIZATIONSET RNG TO PAD DATA RNGEMS FUNC - Vo SETSlew Scroll to Pad Data VIOEMS FUNC - ENTRY

RS I ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on (up)GDC ALIGN PB - PUSH amp HOLDYAW Tw - Pos~t~on RSI thru

45deg amp back to LIFT UPGDC ALIGN PB - ReleaseEMS ROLL - OFFA1~gn CDC to lMU

CM RCS RING A CKRCS TRNFR - CMcb CM RCS LOGIC MNB - openAUTO RCS SEL MNB (6) - OFFSC CONT - SCSTest R~ng A ThrustersSC CONT - CMCRCS TRNFR - SMAUTO RCS SEL (12) - MNAMNB

(hftoff conflg)cb CM RCS LOGIC MNB - close

OPTICS PWR - OFFCMP to COUCH

MN BUS TIE (2) - ONTAPE RCDR - REWIND

6 35middot0Om(-25middot 00)

-24-

SEPARATION CK LISTTVC SERVO PWR 1 - AClMNAcb ELS (2) - close (ver1fy)PRIM GLY TO RAn - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY vlv - OFFCAB PRESS REL vlv (2) - NORMGMBL MTRS (4) - STARTABORT SYS PRPLNT - RCS CMD (venfy)SM RCS PRIM PRPLNT (4) - ONVHF 11M (AampB) - OFFHI GAIN ANT PWR - OFFFC PUMPS (3) - OFFVer1fy s1ugle SU1t compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - 10101cb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2) - opencb HTRS OVLD (2) - openPOT H20 RTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANSEC COOL EVAP - RESETSEC COOL PUMP - off (etr)

MtiVR TO CMSM SEP P R ATTSC CONT - SCSCMC MODE - FREEMNVR TO PAD ATTR (0deg)PY----W)

-25-

SUPERCIRCULAR ENTRY (Cont~nued)

1

4100m(-1900)

P61 - ENTRY PREP

V37E 61E

k 05 09 01427 - ROLL REVERSED 05 09 01426 - IMU UNSAT ~

2 F 06 61 IMPACT LAT LONG HDS UPDN (+-)PRO (010

fps +00001)

3 F 06 60 GMAXVPREDGAMMA EIRecord

GMAXV400K----

GAMMA EI _PRO

(01deg fpsOldeg)

4 F 06 63 RTOGO (lnm) PAD _VIO (fps) PAD _TFE(m~n-sec)

Compare w~th ~M~SFN==C~f~o-r~P~GNS GONO GOIf NO COMM Set RTOGO amp VIO In EMS

amp lnltla11ze(ACCEPT) PRO(RECALC) V32E To 4

5 F 50 25

4300m

(-1700)

45 oOm(-1500)

500Om(-1000)

6 F 06 61

-26-

P62 - CMSM SEP amp PRE-ENTRY MNVRCAUTION Call No EXT Verbs In P62

00041 REQUEST CMSM SEPSC CONT - SCSFREE

COMPARE PITCH ATT WITH PAD DATA ---0=-

(W~thLU 5deg)YAW - 45deg OUT-OF-PLANE (LEFT)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTIRATE 2MN BUS TIE (2) - ON (ver~fy)

PRIM GLY TO RAD - BYPASS (verlfy)CM RCS LOGIC - ON (venfy)SECS LOGIC (2) - on (up)SECS PYRO ARM - ARMCMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 ps~a

CM RCS LOGIC - OFFSECS PYRO ARM (2) - SAFEMonltor VMAB

If lt25 vdc go to EMERGPOWERDOWN pg E6-l

AUTO RCS SEL AC ROLL (4) - OFFAUTO RCS SEL CM 2(6)-OFFAUTO RCS SEL CM 1(6)-MNAYAW back to 0degPITCH TO HORIZ TRACK ATT

ROLL - 0deg (LIFT UP)PITCH - 400K Horiz Mark (317deg)YAW - 0deg

ATT DB - MAXMAN ATT PITCH - ACCEL CMDEMS DATA - Ver~fy

EMS FliNC - ENTRY (ver~fy)

EMS MODE - NORMALcb SPS PampY (4) - openMAINT HORIZ TRK

PRO (Act ENTRY DAP)

IMPACT LATLONGHDSDN (01deg01deg-00001)PRO

7 POSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axis beyond 45deg of Vel vector)

8 06 64

58middot00m(-0200)

9

05G tlme(+0 )

(--=---)

06 68

-27-

P63 - ENTRY INIT

GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PIJR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRmDHORIZ CKPltch error needle goes toward

zero approachlng OSG tlmeMAN ATT (PITCH) - RATE CMD

If CMC lS GOBMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS I

FLY BETA If CMC NO GO ilt

1 SC CaNT - SCS I

FLY EMS k

p64 - ENTRY POST 05G

RTOGO AT 05G AGREES HITH EMS-venfyHORIZ CK05G Lt - ON (EMS START)

No EMS START wlthln 3 sec ~ EMS MODE - BACKUP VHF RNG c

05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds Llft DN

NNVR Llft DNEMS GONO GO

G-V Plot wlthln IlmltsRng ctr dwn 60plusmn7 durlng 10 sec

perlodMonltor G-meter for

convergence wlth pad data (Do)(Vlt27K fps) Go to 13

-28-

P65 - ENTRY - UP CONT (Vgt27K fps)

10 F 16 69 BETA (01middot) _DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT lt~ SC CONT - SCS FLY EMS

PRO

11 06 68 BETAVIHDOT (OIdegfpsfps)(VltV1+500 fps amp RnOT Neg) Go To 13

P66 - ENTRY - BALLISTIC (D(DL)

12 06 22 DESIRED GMBL ANGLES RPYMoultor horlz +12middot of 317middot mark

P67 - ENTRY - FINAL PHASE (02G)

13 06 66 BETACRSRNG ERRDNRNG ERR(010 1um 1um)

KEY VERBRecord DNRNG ERR _KEY RLSEMoultor l~ft vector ou RSI amp FDAI

16 67 RTOGOLATLONG (Vrel=1000fps)(lumOldegOldeg)

SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOWNMonitor a1t~meter

Go To EARTHLANDING pg ---4L5 _

-29-

53 GampN HYBRID DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL tV1 V37E 30E

2 F 06 33 GETI(ACCEPT) PRO (hrm~n Olsec)(REJECT) LOAD DESIRED GETI

3 F 06 81 tVXYZ (LV) (lfps)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

4 F 06 42 HAHPtV (lnm lfps)Record tV

(ACCEPT) PRO(REJECT) Reselect P30 or P27 Load new paramo

5 F 16 45 MTFIMGA (marksm~n-secOlO)

MGA -00002 ~f k

k lMU not al~gned

SET DETPRO

6

7

8

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (Pull)PLSS 02 vlv - FILL02 8M SUPPLY vlv - OFFCAB PRESS REL vlv (2) - NORMcb ELS (2) - closecb SECS ARM (2) - closecb SECS LOGIC (2) - close (ver~fy)

AUTO RCS SEL CM (12) - MNA or ~ffiB

(hftoff conhg)ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM (AampB) - OFF

CMP to Couch

9

10

11

-30-

MNVR TO PAD BURN ATTLOAD DAPBMAG MODE (3) - RATE 2SC CONT - CMCAUTOATT DB - MINMAN ATT (3) - RATE CMD

v62E

v49E

12 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLES

PRO

13 F 50 18 REQ MNVR TO FDAI RPY ANGLES (01deg)(AUTO) PRO(MAN) SC CONT - SCS

BMAG MODE (3) - RATE 2MNVR To 15

14 06 18 AUTO MNVR TO FDAI RPY ANGLES (01deg)

15 F 50 18 REQ TRIM TO FDAI RPY ANGLES (01deg)(TRIM) Go to 13(ByPASS) ENTR

16

17

CHECK BORESIGHT amp SKT STARSOPT MODE - CMCOPT ZERO - OFF

v41 N91E

18 F 21 92 SHAFTTRUN (01deg 001deg)Load SXTS angles

19 41 OPTICS DRIVECheck SKT STAR

OPT ZERO - ZEROCheck BORESIGHT STAR (~f ava~l)

20 V25 N17E (01deg)Load Pad Data GMBL Angles

for CM BURN ATTATT SETtw - SET

to PAD DATA GMBL ANGLESfor CM BURN ATT

21

22

-31-

PHR REDUCTIONHGA PHR - OFFFC PUMPS (3) - OFFVerify s~ngle su~t compr oper loads

balancedFC 2 MN AampB - OFFS BD PiR AMP - LOWcb ECS RAD CONTHTR (2) - opencb HASTE H20URINE DUMP HTRS(2)- opencb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANMN BUS TIE (2) - ONTVC SERVO PHR 1 - AC1MNAGMBL MTR (4) - START

p41 - RCS THRUSTINGV37E 41E

23 F 50 18 REQ MNVR TO LCL HORIZ (HDS ON)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CMCAUTOPRO To 24

(gtfANDAP) BMAG MODE (3) - RATE 2SC CONT - CMCHOLD

V62EMNVR To 25

24 06 18 AUTO MNVR TO FDAI RPY

25 F 50 18 REQ TRIM TO LCL HORIZ (01deg)ALIGN SC ROLL

(AUTO TRIM) PRO To 24(BYPASS) ATT DB - MIN

RATE - LOHMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTlRATE 2

ENTR

550Om26 06 85

59middot2527

-32-

VGXYZ (1fps)RECHECK BORESIGHT STARTRANS CONIR PWR - on (up)EMS MODE - STBY (ver~fy)

EMS FliNC - bV SETVHF RNGSET (IV for SM BURN _EMS FliNC - bVS BD ANT - OMNI CSECS LOGIC (2) - ONMSFN conhrm Go for PYRO ARMSECS PYRO ARM (2) - ARMCM RCS LOGIC - ON (ver~fy)

DSKY BLANKS

593028 16 85 VG XYZ (AVE G ON) (lfps)

RHCs amp THC - ARMEDLIMIT CYCLE - OFFTAPE RCDR - CMD RESETHBREMS MODE - NORMAL

000029 F 16 85 REQ NULL VG XYZ (lfps)

BURN EMS bV CTR TO ZERORESET DET amp COUNT UP

If SM ONLY burn go to step 32THC - LOCKEDSC CaNT - SCSFREERATE - HIGHPRIM GLY To RAD - BYPASS (ver~fy)

MN BUS TIE (2) - ON (ver~fy)

CMSM SEP (2) - on (up)CSMLM FNL SEP (2) - on (up) (verify)CampW MODE - CMRCS TRNFR - CMCM RCS LOGIC - OFF

Momtor VM ABIf lt25 vdc go to EMERGPOWER DOWN Pg E6-l

V63E

If CMC NO GO FDAI SOURCE - ATT FDAI SEL - 1 or 2 ATT SET - GDC

SET

-33-

~Uili ATT PITCH - ACCEL CMDFDAI SCALE - 55MNVR TO CM BURN ATT (NULL ERR NEEDLES)

R 0degPY --00--

30

31

CM RCS BURNRHC III-ContJnuous PJtch DownRHC HZ-Module PJtch to null needlesBURN VGZ TO ZERO

If only 1 RHC Pulse + P=5deg from retro att MaJnta~n rates lt3degsec

BURN COMPLETION ATllV CTR= or DET= _

V8ZE

32 F 16 44 HAHPTFF (1nmffiJn-sec)Check HP-

If gt Pad data contJnue burnuntJ1 lt Pad

PRO

33 F 16 85 VGXYZ (Ups)Read VG resJduals to MSFN

(HYBRID) PRO to 34(SM ONLY BURN)

PROF 37 ODE

EI-1500 V37E 47EF 16 83 twx Y Z (Ups)

SC CONT - SCSFREEMAN ATT (PITCH) - RATE CMDRATE - HIGHPRIM GLY To RAD - BYPASS (verJfy)MN BUS TIE (2) - ON (verJfy)CMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verJfy)Campl MODE - CMRCS TRNFR - CMCM ReS LOGIC - OFFSECS PYRO ~I (2) - SAFE

-34-

PROMonitor VMAB

If lt25 vdc go to EMERGPOWER DOWN

34 F 37 OOEPCM BIT RATE - LOWATT DB - MAXEMS MODE - STBYEMS FUNC - OFF

Go To EARTH ORBIT ENTRY pg _--40-__

-36-

8 SPS THRUSTING PREPCYCLE CRYO FANSSPS GAGING - ACI (ver~fy)

PUG MODE - NORM (venfy)BMAG MODE (3) - RATE 2tv CG - CSMCMC MODE - FREEAUTO RCS SEL (16) - MNA or HNB

(hftoff conbg)SC CONT - CMCAUTO

9 MNVR TO PAD BURN ATTV62E

10 V49E

11 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLESPRO

12 F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) PRO(HAN) SC CONT - ses

MNVR to 14

06 18 AUTO MNVR TO FDAI RPY ANGLES13

14 F 50 18 REO TRIH TO FDAI RPY ANGLES(TRIM) Go to 12(BYPASS) ENTR

15 BORESIGHT STAR CHECK

16 V37E 40EOPT PWR - OFF

17 F 50 18 REQUEST MNVR TO FDAI RPY ANGLES (01deg)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CHCAUTOPRO to 18

(MANDAP) BMAG HODE (3) - RATE 2SC CONT - CMCHOLDMNVR to 19

(HANseS) se eONT - sesMNVR to 19

-35-

54 NORMAL DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL ~V

1 V37E 30E

2 F 06 33 GETI (hrm~nOlsec)

(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

3 F 06 81 ~VXYZ (LV)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

( lfps)

4 F 06 42 HAHP~V (1nmlfps)Record W

(ACCEPT) PRO -----(REJECT) Rese1ect P30 or P27 Load new pa~am

5 F 16 45 MTFIMGA (marksmln-secOldeg)MGA -00002 If ~ lMU not a1~gned

SET DETPRO

6

7

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY v1v - OFFCAB PRESS REL v1v (2) - NORMcb ELS (2) - close (verify)cb SECS ARM (2) - close (ver~fy)

cb SECS LOGIC (2) - close (verlfy)AUTO RCS SEL CM (12) - ~mA or MNB

(l~ftoff conf~g)

ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM AampB - off (ctr)

18

-37-

06 18 AUTO MNVR TO FDAI RPY ANGLES (01 0)

19 l 50 18 REOUEST TRIM MNVR TOALIGN SIC ROLLGDC ALIGN

FDAI RPY ANGLES(010

)

+54-00m(-06-00)

TIG-5mJn

5500m(-0500)

TVC CHECK amp PREPcb STAB CONT SYS (all) - closecb SPS (12) - closeATT DB - MINRATE - LOl~

LIMIT CYCLE - ONMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE 2ROT CONTR PWR DIRECT (2) - OFFSCS TVC (2) - RATE CMD

If SCS SCS TVC (2) - AUTO SC CONT - SCS ~

TVC GMBL DRIVE PampY - AUTOMN BUS TIE (2) - ONTVC SERVO PWR 1 - AC1MNA

2 - AC2MNBTRANS CONTR PWR - ONROT CONTR PWR NORMAL 2 - ACRHC 2 - ARMED

HORIZ CHK - HorJz on 12deg wJndmlmark (LJffiJt +3 0 PNGCS GONO GO)

If NO GO set tw 180 0 180deg0 0

Track horJz wJth 24deg wJndow markAt TIG-2 mJn Ahgn GDC

PRIMARY TVC CHECKGMBL MOT P1-Y1 -STARTON(LMP confJrm)

If SCS verJfy Thumbwheel TrJmTHC - CWVenfy NO MTVC

SEC TVC CHECKGHBL MOT P2-Y2 -STARTON(LMP confJrm)SET GPI TRIHVenfy MTVCTHC NEUTRALGPI returns to 00 (CMC) or trJm (SCS)ROT CONT Pl~ NORM 2 - ACDC

(TRIM) Go to step 17(BYPASS) BMAG MODE(3) - ATTIRATE2 (ver1fy)

ENTR

-38-

20 F SO 25 00204 GMBL TEST OPTION(ACCEPT) SC CONT - GMC (ver~fy)

PROMonitor GPI Response

0020-2000020-200Tr~m

TEST FAIL SC CONT - SCS SCS TVC (2) - AUTO

(REJECT) ENTR

21 06 40 TFIVG~VM (m~n-sec1fps)

PROG ALM - TIG s1~pped

V5N9E 01703

KEY RLSE To 21 ROT CONTR PWR DIRECT (2) - MNABSPS He v1vs (2) - AUTO (ver~fy)

LIMIT CYCLE - OFFFDAI SCALE - SOIScb SPS P2Y2 - open (for cr~t burn)

5800(-02 00)

5925(-0035)

59middot 30(-0030)

06 40

59XX(-OOXX)

AV THRUST A(B) - NORMALTHC - ARMEDRlIC (2) - ARMEDTAPE RCDR - GID RESETHBR

DSKY BLANKS

(AVE G ON)EMS MODE - NORMAL

TFIVG~VM (m~n-seclfps)

CHECK PIPA BIAS lt2fps for 5 sec

ULLAGE AS REQ

IF NO ULLAGE DIR ULLAGE PB - PUSH~

CONTROL ATT WRlIC MONITOR AVM (R3) COUNTING UP

5955(-0005)

F 99 40 ENG ON ENABLE REQUEST(AUTO IGN) PRO AT TFI gt0 sec(BYPASS IGN) ENTR to 24

22 0000 IGN

-39-

If SCS - THRUST ON PB - PUSH

06 40 TFCVG~VM (m~n-seclfpslfps)

~F 97 40 SPS Thrust fall ~

~(RESTART) PRO To IGN (RECYCLE) ENTR To TIG-05 sec

SPS THRUST LITE - ONMONITOR THRUSTING

Pc 95-105 pSlaEMS COUNTING DOWNSPS IN3 v1vs (4) - OPENSPS He v1vs tb (2) - graySPS FUELOXID PRESS - 175-195 pSlaPUGS - BALANCED

PROG ALARM V5N9E 01407 VG INCTHC - CW FLY MTVC

ECOEMER SPS CUTOFF J

AV THRUST (2) - OFF

23 F 16 40 TFC(STATIC)VG~VM (mln-seclfps)~V THRUST AB - OFF

SPS IN3 v1vs (4) - CLOSEDSPS He tb (2) - bp

cb SPS P2Y2 - closed (verlfy)TVC SERVO PHR - AC1MNA (venfy)TVC SERVO PWR 2 - OFF

PRO

24 F 16 85 VG XYZ(CM) CUps)NULL RESIDUALSRECORD ~V CTR amp RESIDUALS I1VCEMS FUNC - OFF VGXEMS MODE - STBY VGYBMAG MODE (3) - RATE 2ATT DB - MAX VGZTRANS CONT PHR - OFF

PRO

25 F 37 V82E

26 F 16 44 HAHPTFF (lnmm~n-sec)

R3-59B59 HP gt494 nmPRO

27 F 37 OOE

-40-

55 EARTH ORBIT ENTRY

1 Venfy CMSMR __

P_shyY_-

SEP ATT(180deg)

(0deg )

2

3

4

EMS INITIALIZATIONEMS FUNC - RNG SETSET RNG TO PAD DATA RNGEMS FUNC - VA SETSlew scroll to pad data VIOEMS FUNC - ENTRY

RSI ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on(up)GDC ALIGN PB - PUSH amp HOLDYAW tw - Pos1tion RSI thru 45deg amp

back to LIFl UPGDC ALIGN PB - RELEASEEMS ROLL - OFFAl1gn GDC to lMU

PWR REDUCT (Norm Deorb Only)HGA PWR - OFFFC PUMPS (3) - OFFVer1fy s1ngle suit compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - Lowcb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2)-openlOb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MAN

-41-

P61 - ENTRY PREP

5 V37E 61E05 09 01427 - ROLL REVERSED05 09 01426 - IMU UNSAT

6 F 06 61 IMPACT LAT LONG liDS UPDN (+-)(01 0

010

+00001)

PRO

PAD VALUESLATLON==G------liDS UP DN _

7 F 06 60 GMAXV400KGAMMA EIRecord

GMAXV400K----GAMMA EI _

PRO

8 F 06 63 RTOGO (1nm) PAD _VIa (fps) PADTFE (mln-sec) ----Compare wlth MSFN for PGNS GONO GONO COMM SET RTOGO amp VIO IN EMS amp

INITIALIZE(ACCEPT) PRO(RECALC) V32E to 8

-42-

P62 - CMSM SEP amp PRE-ENTRY MNVR

9 F 50 25 00041 REQUEST CMSM SEPSC CONT - SCSFREEYAW - 45deg out-of-plane (left for RCS

nght for SPS)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE2PRIM GLY to RAD - BYPASS (verlfy)SECS LOGIC (2) - on (up)MSFN conflrm GO for PYRO ARMSECS PYRO ARM - ARMMN BUS TIE (2) - ON (verlfy)CMSM SEF (2) - ONCSMLM FNl SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 pSlaCM RCS LOGIC - OFFSECS PYRO ARM - SAFEMonltor VMAB

If lt25vdc go to EMERG POWERDOWN Pg E6-1AUTO RCS SEL AlC ROLL (4) - OFFAUTO RCS SEL CM 2(6) - OFFAUTO RCS SEL CM 1(6) - MNA or MNBYAW back to 00

PITCH TO ENTRY ATTROLL 0deg (LIFT UP)PITCH - HORIZ on 317deg MARK (400K)YAW 00

ATT DB - MAXMAN ATT (PITCH) - ACCEL CMDEMS DATA - VerifyEMS FUNC - ENTRY (verlfy)EMS MODE - NORMALMAINTAIN HORIZ TRK

PRO (Act ENTRY DAP)

10 F 06 61 IMPACT LAT LONG HDSDN(010 010 -00001)

PRO

11 FOSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axlS beyond 45deg of Vel vector)

-43-

P63 - ENTRY INIT

12 06 64 GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PWR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRHORIZ CKP~tch error needle goes toward

zero approach~ng 05G t~me

MAN ATT (PITCH) - RATE CMDIf CMC ~s GO

BMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS FLY BETA If CMC NO GO ~

SC CONT - SCS~

FLY EMS RCS Deorh Roll HDS UPTRACK HORIZ w~th 29deg w~ndow mk

P64 - ENTRY POST 05G

13

05G t=elt+0___)

06 68

RTOGO AT 05G AGREES WITH EMS - venfyHORIZ CK05E Lt - on (EMS start)

No EMS start w~th~n 3 secsEMS MODE - BACKUP VHF RNG 05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds L~ft DN

NNVR L~ft DNEMS GONO GO

G-V Plot w~th~n llm~ts

Rng ctr dwn 60 + 7 durlng 10 sec per~od

Mon~tor G-meter forconvergence wlth pad data (Do)

(Vlt27K fps) Go To 17

-44-

P65 - ENTRY - UP CONT (Vgt27K fps)

14 F 16 69 BETA (01deg)DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT~

SC CONT - SCS FLY EMS

PRO

15 06 68 BElA VI HOOT (01deg fpsfps)(VltVL +500 fps amp RDOT Neg) Go To 17

p66 - ENTRY - BALLISTIC (DltDL)

16 06 22 DESIRED GMBL ANGLES RPY (01deg)Mon~tor hor~z +12deg of 317deg mark

P67 - ENTRY - FINAL PHASE (02G)

17 0666 BETACRSRNG ERRDNRNG ERR (Oldeglnmlnm)KEY VERBRecord DNRNG ERR _KEY RLSEL~m~t +100nm from PAD DRE

Mon~tor l~ft vector on RSI amp FDAIF 16 67 RTOGOLATLONG (Vre1=1000fps)

(lnm 010 01deg)SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOlfflMon~tor altimeter

Go To EARTHLANDING pg _I4L5__

-45-

56 EARTHLANDING

90K STEAM PRESS - PEGGED50K CABIN PRESS REL vIv (2) - BOOSTENTRY

SECS PYRO ARM (2) - ARM

40K(90K + 63s)

CM UNSTABLE RCS CMD - OFF ~ 40K APEX COVER JETT PG-PUSH DROGUE DEPLOY PG - PUSH (2 secafter apex cover Jett)

30K ELS LOGIC - ON (up)ELS - AUTO

24K RCS hsable (auto)(90K+92s) RCS CMD - OFF

Apex cover Jett (auto)APEX COVER JETT PB - PUSH

(WAIT 2 SECS)Drogue parachutes deployed (auto)

DROGUE DEPLOY PB - PUSH~

If Drogues FallELS - ~ ~Stablllze CM 5K MAIN DPLY PB - PUSHELS - AUTO

235K Cabln Pressure lncreaslng (Drogues + 50s)If not lncreaSlng by 17K CABIN PRESS REL vlv (RR) - DUMP

-46-

10K Maln parachutes deployedMAIN DEPLOY PB - PUSH (wlthln 1 sec)VHF ANT - RECYVHF AMA - SIMPLEXVHF BCN - ONCABIN PRESS REL v1v (2) - CLOSEDIRECT 02 vlv - OPENCM RCS LOGIC - on (up)CM PRPLNT - DUMP (burn audlb1e)Monltor CM ReS 1amp2 for He press decrease

NO BURN or PRESS DECREASE USE BOTH RHCs DO NOT FIRE PITCH JETS

CM PRPLNT-PURGE (to zero He press)CM RCS He DUMP PB - PUSH RHC (2) - 30 sees NO PITCH k

STRUT LOCKS (2) - UNLOCK

cb FLT amp PL BAT BUS ABampBAT C (3) - closecb FLT amp PLT MNA amp B (2) - opencb ECS RAD HTR OVLD (2) - opencb SPS PampY (4) - open

3K CABIN PRESS REL v1v (RH) - DUMP (after purgecompleted)

FLOOD Lts - POST LDGCM RCS PRPLNT (2) - OFFROT CONTR PWR DIRECT (2) - OFF

800 CAB PRESS RELF vlv - CLOSE (latch off)MN BUS TIE (2) - OFF

AFTER LANDINGcb MAIN REL PYRO (2) - closeMAIN RELEASE - on(up)

Go to POSTLANDING pg _47L-__

I

2

3

-47-

57 POSTLANDING

STABILIZATION VENTILATION COMMUNICATIONS

DIRECT 02 vlv - CLOSE

Stablllzation after landlngELS - AUTO (verlfy)cb MAIN REL PYRO (2) - close (venfy)MAIN RELEASE - on (up) (verlfy)S~CS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb BAT RLY BUS (2) - open

No contact w1th recovery forcesVHF AM AampB - off (ctr) ~

VHF AM Rev ONLY - A cb PL VENT - closecb FLOAT BAG (3) - closecb UPRIGHT SYS COMPRESS (2) - closeIf Stable II

FLOAT BAG(3)-FILL t1ll 2 m1n afterupr1ght then - OFF

VHF AM AlB amp BCN - OFF whlle lnvertedIf Stable I

After 10 M1n Coollng Per1odFLOAT BAG (3) - FILL 7 mln then OFF

Post Stab1lizat1on And Ventllat10nPL BCN LT - BCN LT LOWPL VENT vlv - UNLOCK (Pull)Remove PL VENT Exh CoverPL VENT - HIGH or LOWPL DYE MARKER - ON (swlmmer comm)Release foots traps and_restralntscb MNA BAT BUS A amp BAT C (2) - opencb MNB BAT BUS B amp BAT C (2) - opencb FLT amp PL BAT C - opencb PYRO A SEQ A - opencb PYRO B SEQ B - open

EACH HR - CHECK DC VOLTSgt 275 V If Notmiddot cb FLT amp PL-BAT BUS AampB (2) -open cb FLT amp PL BAT C (1) - open GO TO LOW POWER CHECKLIST

Unstow and lnstall PLV DISTRIB DUCTDeploy grappllng hook and 11ne 1f req

4

-48-

Post Landing Communlcatl0nsVHF ANT-RECY (venfy)VHF BCN - ON (verlfy)

If no contact ~lth recovery forcesperform VHF BEACON Check

MONITOR VHF BEACON transmlSSlonnth VHF AM B Rcvr andor Su)vlval

TransceiverkVHF Beacon not operatlng ~connect Surv~val TranscelVer to antcable behlnd VHF ant access pnland place radio ln BCN mode

LOW POHER CHECKLISTVHF BCN - OFFVHF AM (3) - RCVFLOOD Lts - OFFVHF AM AampB - off (ctr)VHF AM RCV ONLY - A (venfy)COUCH LIGHTS - OFFPOSTLANDING VENT SYS mlnlmlze useSURV RADIO - plug mto VHF BCN ANT cableconn behind VHF ant acess pnl amp turn radloon l-n BCN mode

EGRESS PROCEDURES

CMPCDRLMPCDR

CMPCDRCMP

LMPLl1PCDR

STABLE IDlsconnect Umblll-calsNeck darn onCenter couch - 270 0 positionArmrests stowedConnect raft to SIC l-f desl-red wlth

green lanyardConnect raft ~hl-te lanyards to SUltS amp

lnflate water wlngs when eXltl-ngHATCH PISTON PRESS vlv - PRESS (Outbd)Slde Hatch openedPL VENT - OFFcb Pnl 250 (all) - openEgress with 11feraftPut hardware klt outEgress

or CDIPALL

CMF

CDRCMF

CDR

LMF

CMFCMP LMFCMP

UlP

CDR

-49-

STABLE IIcb CREW STA AUDIO (3) - openD~sconnect umb~1~ca1s

Release foots trapsRelease restra~nt harnessCouch seat pans (3) - 170 0 pos1t10nArm rests stowedSurv1va1 k~ts removed from stowageConnect life raft ma~n1~ne to CDR or SicConnect f~rst wh~te lanyard from

11fe raft to suitConnect th~rd wh~te lanyard from

l~fe raft to SU1tConnect rucksacks together to yellow

lanyard on raft bagPRESSURE EQUALIZATION vlv - OPENRemove and stow fwd hatchEX1t feet f1rst w1th rucksacks when clear

of siC 1nflate water w1ngs and raftExit feet f1rst when clear of SiC

1nflate water w1ngsEX1t feet f1rst when clear of sic

1nflate water w1ngs

-50-

60 TLI ABORTS

TLI Aborts are conta~ned ~n the ESD s~nce the bulk of the funct~ons

concern entry preparat20ns and performance Th~s allows a s2nglesource of procedures for procedure rev2ew val~dat~on checkout andtra~n~ng These procedures ~ncorporate TLI preparat20ns as found ~n

reference 6 w~th the TLI Abort Procedures and these t~e 2nto normallunar return Entry Procedures found ~n sect20n 5 The guidel~nes

for th~s cont2ngency are spec2f2ed 2n reference 7

In2t2al preparat~ons for TLI pos2t20n the necessary system sW2tches2n add~t~on to perform~ng an EMS ~V test and a GDC al~gnment Afterthe DET ~s set for mon2tor2ng TB6 the CMP ~ncreases the 12ght levelof the LEB DSKY to max~mum and returns to the h2s couch Th2s 2Sdone so that the LEB DSKY can be observed ~n the event sunl~ght orreflect20ns wash out the ma2n d2splay panel DSKY dur2ng cr2t2calmaneuvers The crew then straps ~n and prepares for mon2tor~ng TB6as 2nd2cated by the SII SEP L~te The t2mes se~uence of procedures2S keyed on th~s d~splay and ~ncludes the DET START funct~on andSIVB IGNITION Dur2ng the burn the crew mon2tors the FDAIs foratt~tude excurs20ns and abnormal rates report~ng status checks toM~ss2on Control at d2screet t~mes dur2ng the maneuver Upon SIVBSHUTDOWN the eMP records the DSKY d~splayed performance parametersand awa2ts ground conf2rmat~on

The rat~onal for TLI aborts ~s descr~bed 2n reference 7 A summar2shyzat20n 2S extracted to prov2de background and gu2de12nes 2n th2sdocument The abort procedures cover aborts 10 m2nutes after conshyt2ngent SIVE shutdown and aborts 90 m2nutes after normal SIVE shutshydown t2me

The 10 m~nute TLI abort ~s des2gned to be used dur~ng TLI ~n theevent a spacecraft problem develops Wh2Ch can result 2n catastrophe2f ~mmed~ate act~on 2S not taken If the s~tuat20n perm~ts the crewshould always allow the SIVB to complete TLI at wh~ch t~me the groundand crew can perform a malfunct~on analys~s to determ~ne ~f an abort~s adv~sable If a fa~lure occurs that necess2tates the shutdown ofthe SIVB and the ~u~ck return of the crew to earth th~s abort ~s

des~gned to be as ~nsens~t~ve to execut~on errors as poss~ble andst21l be targeted to m2dcorr2dor The burn att~tude w~th the f~ed

hor~zon reference ~s a constant value for any shutdown t~me Theburn durat~on 2S a funct20n of shutdown t2me and 2S ava21able fromcrew charts S~nce the pr~mary purpose of th~s abort ~s to returnto earth as qU2ckly as poss2ble there are no restr2ct20ns as toland~ng locat~on However ~f the t~me to EI is greater than abouttwo hours a midcourse correct20n should be ant~c~pated

The 90 m2nute TLI abort 2S to be used 2f a cr2t2cal subsystem malshyfunct~on ~s determ2ned and the dec2s~on to abort ~s made after the

-51-

TLI cutoff and before TLI cutoff plus approxlmately 80 m1nutesTh1S allows suff1c1ent separatlon and procedural t1me to set upfor the SPS deorb1t burn performed at about TLI + 90 Note thatgenerally the deorb1t burns w1ll be performed a fe11 m1nutes beforeTLI + 90 accord1ng to crew charts shown In reference 8 The no-comm except10n requ1res that 90 m1nutes be the 1nput t1me of 19n1shytlon for P-37 (onboard return-to-earth abort program) so that onshyboard calculatlons can correspond w1th ground calculat10ns to computethe CM land1ng p01nt Th1S TLI abort lS des1gned so that returnfl1ght t1me does not exceed 18 hours and abort ~V does not exceed7000 fps ThlS abort can be performed uSlng chart ~Vs and attltudesand the earths hor1zon serves as a suff1c1ent reference The maneushyver lS targeted to ach1eve the mldcorr1dor entry target Ilne andtlmed to result 1n a deslgnated recovery area

It 1S ObV10US for abort deC1S1ons early 1n the TLI + 90 m1nute t1meshyframe that a GampN SPS burn should be performed In order to keep theTLI abort procedures cons1stent and w1th emphasls on slmpl1c1ty theprocedures here reflect a SCS SPS abort burn to cover the full abortdec1s1on t1meframe

A m1dcourse correct1on for corr1dor control after a TLI abort may bedeS1red 1f the SPS burn d1d not meet expectat1ons The TLIabortprocedures 1n th1S sect10n adapt to the normal lunar return tlmel1neand procedures pr10r to the f1nal MCC

-52-

61 TLI PREPARATION PROCEDURES

GET = 150

CRO AOS(___)

CRO LOS( )(22142)

5100

Don Helmets amp Gloves

XLUNAR - INJECT (verify)EDS PWR - on (venfy)EMS FUNC - OFF (verlfy)EMS MODE - STBYEMS FUNC - IW SETVHF RNGEMS MODE - NORMALSet ~V indo to +15868 fpsEMS FUMC - ~V Test

SPS THRUST Lt - onoff (10 sec)~V lnd stops at -01 to -415

EMS MODE - STBYEMS FUMC - ~V SETVHF RNGSet ~VC

EMS FUNC---~~V=----

GDC ALIGNFDAI Select - liZcb SECS LOGIC (Z) - close (verify)cb SECS ARM (Z) - closeSECS LOGIC (Z) - on (up)MSFN Conflrm GO for PYRO ARM (If pass)SECS PYRO ARM (Z) - on (up)TRANS CONTROL PWR - ONROT CONTR PWR NORMAL (Z) - ACDC(verlfy)ROT CONTR PWR DIRECT (Z) - MNAMNBLV INnGPI - SIISIVB (venfy)LV GUID - IU (venfy)cb DIRECT ULLAGE (Z) - closedSet EVENT TIMER to 5100Begin MONITOR For TB6

CMP to Couch

TB 6 - SII SEP Lt on (TIG-9 mln 38 sec)KEY V83E

SET ORDEALFDAI Z ORB RATE at 180 0 0SII SEP Lt out (38 sec later)Start DET COUNTING UPSC CaNT - SCS (verify)MONITOR LV TANK PRESS

~P lt 36 psid (OXID gt FUEL)~P lt Z6 psid (FUEL gt OXID)

EMERGENCY CSMLV SEP UP TLM CM - BLOCK (verify)UP TLM IU - BLOCK (venfy)

-53-

+45degPY))0middot sec PY

lOK nmltHAlt25K nm

Two phas~ng mnvrs two SPS mnvrs to circular~ze at 150 nmearth orb~t

CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ssion 4K nmltHAltlOK nm CSM amp1M - Two phasing mnvrs two SPS mnvrs to circularize at 150 nm earth orb~t CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ss~on

CSM amp 1M - Two phas~ng mnvrs APS burn todepletion th~rd phasing mnvrSPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn tosem~sync orb~t

25K nmltHAlt40K nm CSM amp 1M - Two phasmg mnvrs APS burn to depletion third phas~ng mnvr SPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn to sem~sync orbit HA)40K nm DPS ava~l - DPS LOll circularize with SPS

DPS not ava~l - Lunar flyby or CSM only to lunar orbit (if reqd gtV lt4000 fps)

V37E 47E (check b~as) Record -=--rshy(Limit 98 fpsmm)

( 1fps)tVXYZN62EVIHDOTHPAD (fpsfpslnm)MONITOR VI ( ) at ECO

SCS TVC SERVO PWR 1 - ACIMNA2 - OFF

TAPE RCDR - CMD RESETHBREMS MODE - NORMAL

SIr SEP Lt - ONTLI Inhib~t S~gnals w~11 not be honored after 5942

SIVB ULLAGE BeginsSII SEP Lt - off (TIG - 18 sec)SIVB FUEL LEADSIVB ULLAGE d~scont~nues

LV ENG I Lt - onSIVB IGNITION ( GETI)LV ENG I Lt - off - -shyMONITOR THRUST amp ATTITUDEMONITOR LV TANK PRESSSIVE ECO (Lt on) (BEGIN TB7)

EMER SIVE CUTOFF AT 6 SEC PAST BURN TIME IF VI ATTAINEDTHC CCW ampNEUTRAL IN 1 SEC or SIISIVB sW - LV STAGEPremature Shutdown HAlt4K nm CSM amp 1M -

5700

58205836

F 16 835800

F 16 62

5838594259525955595900000002SUNRISE(___)

HAW AOS(__=_) KEY VERB (freeze d~splay)

SIVB ATT HOLD 20 sec amp BEGIN VENTINGSIVB NNVR TO ORB RT (HDS DN) (3middot sec)

Record VI -c---HDOT _

HPAD _

KEY RLSEF 16 62

F 16 83

HAW LOS(__=-)

KEYmiddotRLSE~VXYZ (lfps)

Record ~VX---_

~vy

WZ--

AVC---_

TAPE RCDR - off (ctr)EMS MODE - STBYEMS FUNC - OFFSECS PYRO ARM (2) - SAFE

PRO

BURN STATUS REPORT

____--~TIG

BT------VGX____-R

-----P----_Y

REMARKS

_____VI

______--HDOT______--H______---AVC______---FUEL_______OXID

_______UNBAL

F 3708=00 OOEGOS AOS CMP TO LEB

(-=-=-)

0000

0003

0005

0014

0100

-55-

62 TLI 10 MIN ABORTSECS LOGIC (2) - on (up)SECS PYRO ARM (2) - ARM

TRANS CONTR - CGH (4 sec) amp +XDET RESET (verlfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS GMD-ON

TRANS GONTR - neutral then +X for10 sec

SIVBGPI s~ - GPIExcesslve rates 6V THRUST A - NORMAL SPS THRUST - DIRECT When rates damped 6V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

TRANS CONTR +X - OFFV37E OOE

PITGH UP to LOGAL VERT (+X axlSto~ard the earth)

RATE - LOWBMAG MODE (3) - ATTIRATE 2EDS PHR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SEGS ARM (2) - opencb EDS (3) - open

TRANS CONTR -X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (180deg)P (199deg)Y (0deg)

RETRO UPDATEGETI _

JV _VG

Jtb ---GET 400K _

05G _GET DROGUE _

ENTRY P _R _

Y_--

0945

-56-

ALIGN HORIZ ON RET +1 MKGMBL CHECK (T11lle Pentattlng)MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conflnn)cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FUMC - JV SETVHF RNGSET JV from chartE~S FUMC - JVEMS fODE - NOIDlAL

lV THRUST A - NORMALV37E 47E (THRUST fONITOR)

F 16 83 lVXYZ (1 fps)

0950

1000

NOTE For aborts durlng 1st mln of TLIKEY V82E F 16 44 (HaHpTff)Burn untll Hp lt 19NM

TRANS CONTR +X

THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN JV reqdJV THRUST (2) - OFFReport cutoff

cb SPS P2 Y2- closeGfBL MTRS (4) - OFF (LMP Confinn)TRANS CONT PWR - OFFTVC SERVO PWR (2) - OFFMN BUS TIE (2) - OFFcb SPS P1amp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREIf est time to EIltOl5500 omlt fCC andenter the SUPERCIRC CKLIST as early as pos-slb1e Pg ~2~3~ __If est time to EI)Ol5500 anticlpate afCC Enter the ENTRY PREP CKLIST at step 9pg 18

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

-2tl C

l I W gt- ~-4

z laquo I I- 0 -6

l- I J u gt- ~-8

z w w -10

~_ONSANT

9O

VER

SHO

OT

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LIF

TV

EC

TOR

OR

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TATI

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LIN

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SH

ALL

OW

TAR

GE

TLI

NE

STE

EP

TAR

GE

TLI

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gU

ND

ERSH

OO

TBO

UN

DAR

Y

RE

EN

TRY

CO

RR

IDO

R

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26

28

30

32

34

RE

EN

TRY

VE

LOC

ITY

VE

1-F

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6-i

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CC

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73

8X

03

-i- rtREQUIRED PITCH GIMBAL ANG LETO OBTAIN HOR-IZON AT 317

DEGREES IN wiiiiDOW

260

z~I- ~ i5 24000

1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

-I

-1-

NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

I LU HD~-

LUHD

lt0 120UJ0

~

80 HOLD PRESENT TRIMgt LU HD013

~Y~HOIgtlt

TOP OF WINDOWa 40to

31 7 SCRIBEaaI

80 TTOM OF WINDOWi= 0

0--ltoa

-40t-z

~~~Uw w u lt0 -80

HOLO PRESENT TRIlJCl

LOHU0 lt0

J gt -120 HOLD 059 TRIMlt0 z

LDHUlt0 FIELD OF VI S10 NLDHU LIFT-DOWNHEADS -UPLUHD LIFT-UP HEADS-DOWN

~~H~-160 q - P63 LIMITI- NOrE-VALIO ONLY FO~t~--

LUNAR RETURN VELOCITY

plusmnl8020 244middot 8 12 16

TIME TO 400K FT ALTITUDE-MIN

4

P37

LONG

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344

348

352

356

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320

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-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 14: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

32

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-13-

40 EARTH ORBITAL DEORBIT AND ENTRY TECHNIQUES

As outl~ned ~n reference 5 a nom~nal PGNCS entry from earth orb~t ~s

based on a preparat~on t~me of 2 hours and 40 m~nutes ~nclud~ng 2n~ght passes Th~s t~me ~ncludes approx~mately 20 minutes before thef~rst n~ght pass after the CMC update and PAD data have been rece2vedTh~s t~e also 2ncludes approx2mately 20 m2nutes after the secondn~ght pass to allow suffic~ent t2me to prepare for retrof2re after theIMU f2ne a12gnment It has been determ2ned coarse a12gnment accuracy~s adequate for retrof~re and entry and undoubtedly other funct20nscould be om2tted depend2ng on the c2rcumstances for the dec2s20n toreenter Descr2bed here2n are the nom2nal earth oro2tal entry proshycedures w2th pert2nent comments on system va12dat20n for real timeacceptance dec~s20ns

After the entry dec~s~on is made the crew transfers the PGNCS fromthe standby to the operate mode and rece~ves a CMe update w~th P27Next the maneuver PAD update ~s v02ced up and the 2n~t~al entry mode~s determ~ned During the ~n~tial n~ght pass the IMU or2entat~on ~s

estab12shed uS2ng P51 star s~ght2ngs to obta2n a REFSMMAT The preshyferred or~entat~on opt20n ~n P52 2S then selected to coarse a12gn theIMU uS2ng the des2red entry REFSMMAT determ2ned by MGG-H The GOO ~s

now al~gned to the IMU 2n preparat~on for an IMUSes dr~ft check Ifthe GOO ~nd~cates the ses dr2ft rate exceeds 10 degrees per hour ~n

any ax~s the check ~s repeated on the other BMAGs to estaol~sh if theGOO or Just the single set 2S unusuable Var20us sytem checks as 12sted2n sect20n 51 are performed as necessary cons2stent w2th the t2me12ned2ctates of the maJor act2v2t2es Included 2n these checks are the EMSself-tests and the dV counter test The latter requ2res the spacecraftbe placed ~n dr2ft2ng fl2ght w~th the funct20n sW2tch 2n the dV pos2t~on

If the counter reg2sters a change of more than 25 feet per second w2th2n100 seconds the scroll and counter are unre12able for mon2tor2ng thedeorb2t burn and entry rang2ng If the EMS self-test fails and t2medoes not allow further analysis a 5555 ERE entry 1S planned as thePGNGS backup entry mode After complet2on of these checks the entryPAD lS prov1ded by MeG-H The crew then selects the external dVprogram P30 and the appropr2ate deorb1t tbrust1ng program p40 or P41Dur2ng th2s per2od wh2ch 2ncludes the f1nal n2ght pass P52 may beselected to ver2fy the IMU a12gnment Since the retro att2tude hasbeen computed so that a w2ndow mark c01nc2des w2th the hor2zon atGETI th2s serves as the conclus2ve check on the PGNCS At 5 m2nutesbefore retrofire the att2tude check 1S made by ver1fY2ng that the 12degree scr~be 12ne ~s w2th2n 3 degrees of the hor2zon If not thePGNeS has fa2led and the ses 2S used for att2tude reference and the

V counter for burn durat~on control S2nce the ses att~tude wasa12gned to the IMU a real~gnment ~s necessary This ~s accompl~shed

by manually maneuver2ng the spacecraft to ma~nta1n the 24 degree wlodowmark on the hor2zon and releas1ng the GOO a12gn button at TIG - 2 m2nutes

-14-

Upon complet~on of the burn the tN res~duals are burned to W~th~n

02 feet per second If the PGNCS ~V counter or est~mated burnduration are ~n d~sagreement ~t must be estab1~shed whether suff~shy

c~ent veloc~ty has been suppl~ed to put the land~ng po~nt in thefootpr~nt The PGNCS data w~ll be used ~f ~t ~s conf~rmed by oneother source if not the ~V counter w~11 be used ~f ~t ~s conf~rmed

by the burn durat~on t~me If add~tional ~V ~s necessary the data~s ava~lable to the crew on an onboard chart found ~n Sect~on 80

Post burn entry preparat~on requ~res EMS ~n~t~al~zation RSI al~gnshy

ment and pre-separat~on funct~ons The crew then selects the ~n~t~al

entry program P61 and records the d~sp1ays as a check aga~nst PADdata Upon complet~on of these checks P62 ~s entered The crewmanually or~ents the spacecraft to the separat~on attitude and yaws450 to ~nsure aga~nst possible CM 8M recontact After separat~on

the spacecraft ~s maneuvered to the reentry tr~m att~tude wh~ch

places the hor~zon on the 3170 w~ndow mark at EI Shortly thereshyafter ~n P62 the entry DAP is act~vated and P63 in~t~ated Dur~ng

th~s t~e MCC-H has computed a postburn update and ~t ~s vo~ced tothe crew ~f d~fferent from preburn values The EMS scroll and rangecounter w~ll be adJusted accord~ngly ~f t~me perm~ts A f~nal PGNCScheck pr~or to 05g may be mon~tored at th~s t~e w~th the CMC modein free and the manual att~tude p~tch ~n acceleration command wh~le

the hor~zon reference ~s held the p~tch error needle w~ll decreaseto zero as EI ~s reached At RET 005g the EMS mode sw~tch ~s

turned to manual the entry 005-g sw~tch and EMS roll sw~tch areturned on and the spacecraft control sw~tched to CMC to beg~n DAPcontrol At the PGNCS 005-g ~ndicatwn the program change fromP63 to P64 ~s mon~tored and the t~e vo~ce recorded At th~s t~me

the EMS range counter check ~s made dur~ng the 10 second per~od

follow~ng EMS 005g Dur~ng th~s per~od the counter should countdown 40 + 10 naut~cal m~les At PGNCS 02-g ~nd~cation the changefrom P64-to P67 ~s monitored and the ~splay may be held by key~ngVERB ~n order to record the init~al downrange error d~splay andcompare ~t to the PAD value The PGNCS has fa~led ~f the two do notagree w~th~n + 100 naut~cal m~les In the event P67 has not appearedwhen both the-g-meter and the scroll ~nd~cate greater than 05g thePGNCS has sim~lar~ly fa~led In e~ther fa~lure the SCS is used foratt~tude reference w~th an EMS entry If the checks agree the crewrema~ns w~th automat~c DAP for the rema~nder of the entry

The entry phase ~s essentially over when the relat~ve velocity ofthe spacecraft decreases to less than 1000 feet per second Th~s

~s ~nd~cated ~n P67 when RTGO lat~tude and long~tude are d~splayed

S~nce very l~ttle rang~ng capab~l~ty exists after th~s pOint thespacecraft is or~ented either full l~ft up or down depending onRTGO negat~ve or pos~t~ve and the crew prepares for the earth land~ng

phase

-15-

41 TYP~cal Retrof~re and Entry Sequence of Events

Dec~s~on to reenter

P27 (CMC update)

Retrof~re PAD update

Entry mode dec~s~on

P51 (IMU or~entat~on determlnatlon) durlng f~rst dark per~od

P52 (IMU coarse allgnment)

EMS checks

Entry PAD update

P30 (external AV)

p40 (SPS thrust)

P52 (IMU f~ne al~gnment) durlng second dark per~od

p40 (SPS thrust)

Ign~t~on att~tude check

Retroflre

P61

P62

CMSM separat~on

P63

Postburn PAD update

Entry attltude check

p64 (beg~n DAP control at O05g)

P67 (PGNCS gono go check at O2g)

42

Retrof~re

and

En

try

Alt

ern

atlv

es

Sys

tem

fa~lure

PGNC

S

PGNC

San

dEM

S

PGNC

San

dall

onbo

ard

att

ltu

de

refe

ren

ce

Fal

lure

bef

ore

Fal

lure

aft

er

Fal

lure

aft

er

com

mlt

ted

tono

ml-

com

mlt

ted

tono

ml-

com

mlt

ted

tob

all

lstl

cn

alG

ETI

(bef

ore

nal

GET

I(a

fter

reen

try

(aft

er

nom

GET

I-3

mln

s)no

mG

ETI

-3m~ns)

del

ayed

GET

I-5

mln

s)

SCS

bu

rnatnom~nal

SCS

bu

rnat

nom

lnal

GET

an

dEM

Sen

try

GET

Ian

dEM

Sen

try

----

----

--

Del

ay

GET

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8b

urn

at

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for

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rnan

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555

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urn

and

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90

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try

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entr

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Del

ay

GET

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rH

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onm

onlt

orbu

rnHor~zon

mo

nlt

or

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0

hor~zonmon~tor

bu

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dro

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gb

all

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can

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all

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gball~st~c

entr

y

-17-

5 0 DETAILED ENTRY PROCEDURES

In order to comblne slmilar procedures that are common to lunar returnentrles and earth orblt entrles the followlng procedures are dlvldedlnto categorles that allow a mlnlmum of dupllClty ThlS provldes asmaller tralnlng package and more closely resembles the onboard crewcheckllst when comparlson lS necessary

51 Entry Preparatlons for Superclucular and Earth Orbltal Entrles

1~e entry preparatlons are comblned In these procedures andsteps pecullar to elther superclrcular or earth orbltal entrlesare labeled accordlngly The tlme llstlngs In thlS sectlon areappllcable to only superclrcular entries Slnce the earth orbltalentry tlmellne lS a functlon of several varlables as descrlbedIn sectlon 40 and reference 5

-18-51 (Contlnued)

VEHICLE PREPARATION

l-

2

3

4

5

6 -0600h

7 -0535h

8

9

10 -0430h

INITIAL STOWAGE COMPLETED

CMC amp ISS START UP

SCS POWER UP

p51 - IMU ORIENTATION

LOAD DAPV48E 11102 01111 PRO ERO PRO

LAST MCC DECISION

NO COMM - P52 amp NAV SIGHTINGSNOMINAL - P2337 ONBOARD COMPARISON

DON MAE WESTS amp FOOT RESTRAINTS

VHF AM A - SIMPLEX

P 27 (SV REFSMMAT) MNVRamp ENTRY pAD UPDATES

11 -0415h P52 - IMU REALIGN(___) (OPTION 1)

12 P37 (NO COMM ONLY)

13

14

ECS CKS02 SUPPLY REFILLECS Monitor CkEVAP H20 CONT (2) vlvs - AUTOSUIT HEAT EXCH SEC GLY - FLOW

EPS CKS 1 3 4 (5 If reqd)

15 SPS CK (If req d)

16

17

18

RCS CKSSM RCS MOUlt CkCM RCS MOUlt Ck

CampW SYS CK

CMC SELF CK

19

20 -0345h

-03l5h-0300h

21

22

22A

-19-

DSKY COND LT TEST

MIDCOURSE MANEUVERP30 - EXT rVP404l - SPSRCS THRUSTINGMIDCOURSE (17) BURN

NO COMM NAV SIGHTINGS

ffiVR TO ENTRY ATT (Superc1rc only)V62E

V49E

22B F 06 22 DESIRED FINAL GMBL ANGLESLOAD ENTRY ATT PAD ANGLESPRO

22C F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) SC CONT - CMC

BMAG MODE (3) - RATE 2CMC MODE - AUTO

PRO(~N) SC CONT - SCS

MNVR to 22E

22D 06 18 AUTO MNVR TO FDAI RPY ANGLES

22E F 50 18 REQUEST TRIM(TRIM) Go to 22C(BYPASS) ENTR

23 -200hr BORESIGHT amp SXT STAR CHECKOPT MODE - CMCOPT ZERO - OFF

V41 N91E

F 21 92 SHAFT TRUNLoad SXTS angles

41 OPTICS DRIVE

CHECK SXT STAROPT ZERO - ZERO

CHECK BORESIGHT STAR (If ava11)

24 -0135h

25(___)

26

27 -0115h

-20-

P52 - lMU REALIGNRecord gyro torqu~ng anglesRp~----

YIf-7gt-Lno--re-c-ycle PS2If conflrmed use SCS for EMS entry

GDC ALIGNIf drlft gtLOohr change ratesource

FINAL STOWAGEOPTICS (except for hybrid)ORDEALGLY TO RAD SEC - BYPASS (verlfy)CooL pnl lnstalledY-Y struts (2) extendedStow Data Box R-12

EMS CHECKEMS FUNC - OFFcb EMS (2) - closeEMS MODE - STBYEMS FUNC - EMS TEST 1 (walt 5 sec)EMS MODE - NORMAL (walt 10 sec)

Check ind lts - offRANGE lnd - 00Slew halr1ine over notch

In self-test patternEMS FUNC - EMS TEST 2 (walt 10 sec)

05G It - on (all others out)EMS FUNC - EMS TEST 3

05G It - onRSI Lower It - on (10 sec Qater)Set RANGE counter to 58 nm+OO

EMS FUNC - EMS TEST 405G It - on (all others out)G-V trace w~thin pattern to lwr rt

corner 9GRANGE lnd counts down to 0+02

EMS FUNC - EMS TEST 505G It - onRSI upper lt - on (10 sec later)RANGE md - 00SCrlbe traces vertlcal llne 9g to

022+01ALIGN SCROLL TO ENTRY PATTERN (on

37K ft sec hne)EMS FUNC - RNG SET

G-V scroll assy traces vert llne022g to 0+01

EMS MODE - STBY

28

29

30 -OllOh

-21-

~V TEST (Deorb~t only)EMS FUNC - ~V SETVHF RNGSET ~V ~nd to 15868 fpsEMS MODE - NORMALEMS FUNC - ~V TEST

SPS THRUST LT - onoff (10 sec)~V ~nd stops at -01 to -415

EMS MODE - STBY

PRIMARY WATER EVAP ACTIVATIONGLY EVAP H20 FLOW - AUTOGLY EVAP STH PRESS - AUTOPRI ECS GLY PUMP - ACI

CM RCS PREHEATNote If sys test mtr 5cd6abcd

all read 39 vdc (28degF) or moreom~t preheat

cb RCS LOGIC (2) - closeCM RCS LOGIC - ONUP T1M CM - BLOCK (ver~fy)

cb CM RCS HTRS (2) - closeCM RCS HTRS - ON (LMP Conf~rm)

(20 mlU or III lowest rdg lS39 vdc) (Moultor Maufpress for press drop)

31 (___) FINAL GDC DRIFT CK (If req I d)If drlft gtlOohr Suspect GDC Do not

use RSI amp FDAI 2

32 -OO5Om

33

34

35

TERM CM RCS PREHEATUP TLM CM - BLOCK (venfy)CM RCS HTRS - OFFCM RCS LOGIC - OFF

SYSTEMS TEST PANEL CONFIGURATIONSYS TEST METER - 4BRNDZ XPNDR - OPERATECM RCS HTRS - OFFWASTE H20 DUMP - OFFURINE DUMP - OFF

LEB LIGHTING - OFF

SEC WATER EVAP ACTIVATIONGLY To RAD SEC vlv - BYPASSSEC COOL EVAP - EVAPSEC COOL PUMP - AC2

36

37

38 -OO45m

-22-

PYRO BATT CKcb PYRO A SEQ A - close (ver~fy)

cb PRYO B SEQ B - close (verify)DC IND - PYRO BAT A(B)

~If PYRO BAT A(B) lt 35 vdc cb PYRO A(B) seq A(B) - open~

PYRO A(B)BAT BUS A(B)TO PYRO~MN BUS TIE - close

cb MNA BAT C - closecb MNB BAT C - closeDC IND - MNBPNL 8 - All cbs closed except

PL VENT - open (ver~fy)

FLOAT BAG (3) - open (ver~fy)

DOCKING PROBE (2) - open (verlfy)EDS BAT (3) - open (ver~fy)

CM ReS HTRS (2) - open

CM RCS ACTIVATIONcb SECS ARM (2) - close (verlfy)cb SECS LOGIC (2) - close (verlfy)SECS LOGIC (2) - ONMSFN conflrm GO for PYRO ARM(~f poss)SECS PYRO ARM (2) - ARMCM RCS PRPLNT 1amp2 - ONCM RCS PRESS - ONRCS Ind sw - eMl then 2

He PRESS 3700-4400 pSlaMANF PRESS 287-302 pSla

SECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFF

P27 amp ENTRY PAD UPDATEGo To Entry Checkllst

Superclrc - pg ~2~3 _Hybnd - pg -----2~9L-__Normal Deorblt - pg __3L5L- _

-23-

52 SUPERCIRCULAR ENTRY

1 SET DET (up to ET)

2

3

4

5

3000(-30-00)

EMS INITIALIZATIONSET RNG TO PAD DATA RNGEMS FUNC - Vo SETSlew Scroll to Pad Data VIOEMS FUNC - ENTRY

RS I ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on (up)GDC ALIGN PB - PUSH amp HOLDYAW Tw - Pos~t~on RSI thru

45deg amp back to LIFT UPGDC ALIGN PB - ReleaseEMS ROLL - OFFA1~gn CDC to lMU

CM RCS RING A CKRCS TRNFR - CMcb CM RCS LOGIC MNB - openAUTO RCS SEL MNB (6) - OFFSC CONT - SCSTest R~ng A ThrustersSC CONT - CMCRCS TRNFR - SMAUTO RCS SEL (12) - MNAMNB

(hftoff conflg)cb CM RCS LOGIC MNB - close

OPTICS PWR - OFFCMP to COUCH

MN BUS TIE (2) - ONTAPE RCDR - REWIND

6 35middot0Om(-25middot 00)

-24-

SEPARATION CK LISTTVC SERVO PWR 1 - AClMNAcb ELS (2) - close (ver1fy)PRIM GLY TO RAn - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY vlv - OFFCAB PRESS REL vlv (2) - NORMGMBL MTRS (4) - STARTABORT SYS PRPLNT - RCS CMD (venfy)SM RCS PRIM PRPLNT (4) - ONVHF 11M (AampB) - OFFHI GAIN ANT PWR - OFFFC PUMPS (3) - OFFVer1fy s1ugle SU1t compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - 10101cb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2) - opencb HTRS OVLD (2) - openPOT H20 RTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANSEC COOL EVAP - RESETSEC COOL PUMP - off (etr)

MtiVR TO CMSM SEP P R ATTSC CONT - SCSCMC MODE - FREEMNVR TO PAD ATTR (0deg)PY----W)

-25-

SUPERCIRCULAR ENTRY (Cont~nued)

1

4100m(-1900)

P61 - ENTRY PREP

V37E 61E

k 05 09 01427 - ROLL REVERSED 05 09 01426 - IMU UNSAT ~

2 F 06 61 IMPACT LAT LONG HDS UPDN (+-)PRO (010

fps +00001)

3 F 06 60 GMAXVPREDGAMMA EIRecord

GMAXV400K----

GAMMA EI _PRO

(01deg fpsOldeg)

4 F 06 63 RTOGO (lnm) PAD _VIO (fps) PAD _TFE(m~n-sec)

Compare w~th ~M~SFN==C~f~o-r~P~GNS GONO GOIf NO COMM Set RTOGO amp VIO In EMS

amp lnltla11ze(ACCEPT) PRO(RECALC) V32E To 4

5 F 50 25

4300m

(-1700)

45 oOm(-1500)

500Om(-1000)

6 F 06 61

-26-

P62 - CMSM SEP amp PRE-ENTRY MNVRCAUTION Call No EXT Verbs In P62

00041 REQUEST CMSM SEPSC CONT - SCSFREE

COMPARE PITCH ATT WITH PAD DATA ---0=-

(W~thLU 5deg)YAW - 45deg OUT-OF-PLANE (LEFT)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTIRATE 2MN BUS TIE (2) - ON (ver~fy)

PRIM GLY TO RAD - BYPASS (verlfy)CM RCS LOGIC - ON (venfy)SECS LOGIC (2) - on (up)SECS PYRO ARM - ARMCMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 ps~a

CM RCS LOGIC - OFFSECS PYRO ARM (2) - SAFEMonltor VMAB

If lt25 vdc go to EMERGPOWERDOWN pg E6-l

AUTO RCS SEL AC ROLL (4) - OFFAUTO RCS SEL CM 2(6)-OFFAUTO RCS SEL CM 1(6)-MNAYAW back to 0degPITCH TO HORIZ TRACK ATT

ROLL - 0deg (LIFT UP)PITCH - 400K Horiz Mark (317deg)YAW - 0deg

ATT DB - MAXMAN ATT PITCH - ACCEL CMDEMS DATA - Ver~fy

EMS FliNC - ENTRY (ver~fy)

EMS MODE - NORMALcb SPS PampY (4) - openMAINT HORIZ TRK

PRO (Act ENTRY DAP)

IMPACT LATLONGHDSDN (01deg01deg-00001)PRO

7 POSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axis beyond 45deg of Vel vector)

8 06 64

58middot00m(-0200)

9

05G tlme(+0 )

(--=---)

06 68

-27-

P63 - ENTRY INIT

GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PIJR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRmDHORIZ CKPltch error needle goes toward

zero approachlng OSG tlmeMAN ATT (PITCH) - RATE CMD

If CMC lS GOBMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS I

FLY BETA If CMC NO GO ilt

1 SC CaNT - SCS I

FLY EMS k

p64 - ENTRY POST 05G

RTOGO AT 05G AGREES HITH EMS-venfyHORIZ CK05G Lt - ON (EMS START)

No EMS START wlthln 3 sec ~ EMS MODE - BACKUP VHF RNG c

05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds Llft DN

NNVR Llft DNEMS GONO GO

G-V Plot wlthln IlmltsRng ctr dwn 60plusmn7 durlng 10 sec

perlodMonltor G-meter for

convergence wlth pad data (Do)(Vlt27K fps) Go to 13

-28-

P65 - ENTRY - UP CONT (Vgt27K fps)

10 F 16 69 BETA (01middot) _DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT lt~ SC CONT - SCS FLY EMS

PRO

11 06 68 BETAVIHDOT (OIdegfpsfps)(VltV1+500 fps amp RnOT Neg) Go To 13

P66 - ENTRY - BALLISTIC (D(DL)

12 06 22 DESIRED GMBL ANGLES RPYMoultor horlz +12middot of 317middot mark

P67 - ENTRY - FINAL PHASE (02G)

13 06 66 BETACRSRNG ERRDNRNG ERR(010 1um 1um)

KEY VERBRecord DNRNG ERR _KEY RLSEMoultor l~ft vector ou RSI amp FDAI

16 67 RTOGOLATLONG (Vrel=1000fps)(lumOldegOldeg)

SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOWNMonitor a1t~meter

Go To EARTHLANDING pg ---4L5 _

-29-

53 GampN HYBRID DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL tV1 V37E 30E

2 F 06 33 GETI(ACCEPT) PRO (hrm~n Olsec)(REJECT) LOAD DESIRED GETI

3 F 06 81 tVXYZ (LV) (lfps)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

4 F 06 42 HAHPtV (lnm lfps)Record tV

(ACCEPT) PRO(REJECT) Reselect P30 or P27 Load new paramo

5 F 16 45 MTFIMGA (marksm~n-secOlO)

MGA -00002 ~f k

k lMU not al~gned

SET DETPRO

6

7

8

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (Pull)PLSS 02 vlv - FILL02 8M SUPPLY vlv - OFFCAB PRESS REL vlv (2) - NORMcb ELS (2) - closecb SECS ARM (2) - closecb SECS LOGIC (2) - close (ver~fy)

AUTO RCS SEL CM (12) - MNA or ~ffiB

(hftoff conhg)ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM (AampB) - OFF

CMP to Couch

9

10

11

-30-

MNVR TO PAD BURN ATTLOAD DAPBMAG MODE (3) - RATE 2SC CONT - CMCAUTOATT DB - MINMAN ATT (3) - RATE CMD

v62E

v49E

12 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLES

PRO

13 F 50 18 REQ MNVR TO FDAI RPY ANGLES (01deg)(AUTO) PRO(MAN) SC CONT - SCS

BMAG MODE (3) - RATE 2MNVR To 15

14 06 18 AUTO MNVR TO FDAI RPY ANGLES (01deg)

15 F 50 18 REQ TRIM TO FDAI RPY ANGLES (01deg)(TRIM) Go to 13(ByPASS) ENTR

16

17

CHECK BORESIGHT amp SKT STARSOPT MODE - CMCOPT ZERO - OFF

v41 N91E

18 F 21 92 SHAFTTRUN (01deg 001deg)Load SXTS angles

19 41 OPTICS DRIVECheck SKT STAR

OPT ZERO - ZEROCheck BORESIGHT STAR (~f ava~l)

20 V25 N17E (01deg)Load Pad Data GMBL Angles

for CM BURN ATTATT SETtw - SET

to PAD DATA GMBL ANGLESfor CM BURN ATT

21

22

-31-

PHR REDUCTIONHGA PHR - OFFFC PUMPS (3) - OFFVerify s~ngle su~t compr oper loads

balancedFC 2 MN AampB - OFFS BD PiR AMP - LOWcb ECS RAD CONTHTR (2) - opencb HASTE H20URINE DUMP HTRS(2)- opencb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANMN BUS TIE (2) - ONTVC SERVO PHR 1 - AC1MNAGMBL MTR (4) - START

p41 - RCS THRUSTINGV37E 41E

23 F 50 18 REQ MNVR TO LCL HORIZ (HDS ON)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CMCAUTOPRO To 24

(gtfANDAP) BMAG MODE (3) - RATE 2SC CONT - CMCHOLD

V62EMNVR To 25

24 06 18 AUTO MNVR TO FDAI RPY

25 F 50 18 REQ TRIM TO LCL HORIZ (01deg)ALIGN SC ROLL

(AUTO TRIM) PRO To 24(BYPASS) ATT DB - MIN

RATE - LOHMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTlRATE 2

ENTR

550Om26 06 85

59middot2527

-32-

VGXYZ (1fps)RECHECK BORESIGHT STARTRANS CONIR PWR - on (up)EMS MODE - STBY (ver~fy)

EMS FliNC - bV SETVHF RNGSET (IV for SM BURN _EMS FliNC - bVS BD ANT - OMNI CSECS LOGIC (2) - ONMSFN conhrm Go for PYRO ARMSECS PYRO ARM (2) - ARMCM RCS LOGIC - ON (ver~fy)

DSKY BLANKS

593028 16 85 VG XYZ (AVE G ON) (lfps)

RHCs amp THC - ARMEDLIMIT CYCLE - OFFTAPE RCDR - CMD RESETHBREMS MODE - NORMAL

000029 F 16 85 REQ NULL VG XYZ (lfps)

BURN EMS bV CTR TO ZERORESET DET amp COUNT UP

If SM ONLY burn go to step 32THC - LOCKEDSC CaNT - SCSFREERATE - HIGHPRIM GLY To RAD - BYPASS (ver~fy)

MN BUS TIE (2) - ON (ver~fy)

CMSM SEP (2) - on (up)CSMLM FNL SEP (2) - on (up) (verify)CampW MODE - CMRCS TRNFR - CMCM RCS LOGIC - OFF

Momtor VM ABIf lt25 vdc go to EMERGPOWER DOWN Pg E6-l

V63E

If CMC NO GO FDAI SOURCE - ATT FDAI SEL - 1 or 2 ATT SET - GDC

SET

-33-

~Uili ATT PITCH - ACCEL CMDFDAI SCALE - 55MNVR TO CM BURN ATT (NULL ERR NEEDLES)

R 0degPY --00--

30

31

CM RCS BURNRHC III-ContJnuous PJtch DownRHC HZ-Module PJtch to null needlesBURN VGZ TO ZERO

If only 1 RHC Pulse + P=5deg from retro att MaJnta~n rates lt3degsec

BURN COMPLETION ATllV CTR= or DET= _

V8ZE

32 F 16 44 HAHPTFF (1nmffiJn-sec)Check HP-

If gt Pad data contJnue burnuntJ1 lt Pad

PRO

33 F 16 85 VGXYZ (Ups)Read VG resJduals to MSFN

(HYBRID) PRO to 34(SM ONLY BURN)

PROF 37 ODE

EI-1500 V37E 47EF 16 83 twx Y Z (Ups)

SC CONT - SCSFREEMAN ATT (PITCH) - RATE CMDRATE - HIGHPRIM GLY To RAD - BYPASS (verJfy)MN BUS TIE (2) - ON (verJfy)CMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verJfy)Campl MODE - CMRCS TRNFR - CMCM ReS LOGIC - OFFSECS PYRO ~I (2) - SAFE

-34-

PROMonitor VMAB

If lt25 vdc go to EMERGPOWER DOWN

34 F 37 OOEPCM BIT RATE - LOWATT DB - MAXEMS MODE - STBYEMS FUNC - OFF

Go To EARTH ORBIT ENTRY pg _--40-__

-36-

8 SPS THRUSTING PREPCYCLE CRYO FANSSPS GAGING - ACI (ver~fy)

PUG MODE - NORM (venfy)BMAG MODE (3) - RATE 2tv CG - CSMCMC MODE - FREEAUTO RCS SEL (16) - MNA or HNB

(hftoff conbg)SC CONT - CMCAUTO

9 MNVR TO PAD BURN ATTV62E

10 V49E

11 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLESPRO

12 F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) PRO(HAN) SC CONT - ses

MNVR to 14

06 18 AUTO MNVR TO FDAI RPY ANGLES13

14 F 50 18 REO TRIH TO FDAI RPY ANGLES(TRIM) Go to 12(BYPASS) ENTR

15 BORESIGHT STAR CHECK

16 V37E 40EOPT PWR - OFF

17 F 50 18 REQUEST MNVR TO FDAI RPY ANGLES (01deg)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CHCAUTOPRO to 18

(MANDAP) BMAG HODE (3) - RATE 2SC CONT - CMCHOLDMNVR to 19

(HANseS) se eONT - sesMNVR to 19

-35-

54 NORMAL DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL ~V

1 V37E 30E

2 F 06 33 GETI (hrm~nOlsec)

(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

3 F 06 81 ~VXYZ (LV)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

( lfps)

4 F 06 42 HAHP~V (1nmlfps)Record W

(ACCEPT) PRO -----(REJECT) Rese1ect P30 or P27 Load new pa~am

5 F 16 45 MTFIMGA (marksmln-secOldeg)MGA -00002 If ~ lMU not a1~gned

SET DETPRO

6

7

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY v1v - OFFCAB PRESS REL v1v (2) - NORMcb ELS (2) - close (verify)cb SECS ARM (2) - close (ver~fy)

cb SECS LOGIC (2) - close (verlfy)AUTO RCS SEL CM (12) - ~mA or MNB

(l~ftoff conf~g)

ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM AampB - off (ctr)

18

-37-

06 18 AUTO MNVR TO FDAI RPY ANGLES (01 0)

19 l 50 18 REOUEST TRIM MNVR TOALIGN SIC ROLLGDC ALIGN

FDAI RPY ANGLES(010

)

+54-00m(-06-00)

TIG-5mJn

5500m(-0500)

TVC CHECK amp PREPcb STAB CONT SYS (all) - closecb SPS (12) - closeATT DB - MINRATE - LOl~

LIMIT CYCLE - ONMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE 2ROT CONTR PWR DIRECT (2) - OFFSCS TVC (2) - RATE CMD

If SCS SCS TVC (2) - AUTO SC CONT - SCS ~

TVC GMBL DRIVE PampY - AUTOMN BUS TIE (2) - ONTVC SERVO PWR 1 - AC1MNA

2 - AC2MNBTRANS CONTR PWR - ONROT CONTR PWR NORMAL 2 - ACRHC 2 - ARMED

HORIZ CHK - HorJz on 12deg wJndmlmark (LJffiJt +3 0 PNGCS GONO GO)

If NO GO set tw 180 0 180deg0 0

Track horJz wJth 24deg wJndow markAt TIG-2 mJn Ahgn GDC

PRIMARY TVC CHECKGMBL MOT P1-Y1 -STARTON(LMP confJrm)

If SCS verJfy Thumbwheel TrJmTHC - CWVenfy NO MTVC

SEC TVC CHECKGHBL MOT P2-Y2 -STARTON(LMP confJrm)SET GPI TRIHVenfy MTVCTHC NEUTRALGPI returns to 00 (CMC) or trJm (SCS)ROT CONT Pl~ NORM 2 - ACDC

(TRIM) Go to step 17(BYPASS) BMAG MODE(3) - ATTIRATE2 (ver1fy)

ENTR

-38-

20 F SO 25 00204 GMBL TEST OPTION(ACCEPT) SC CONT - GMC (ver~fy)

PROMonitor GPI Response

0020-2000020-200Tr~m

TEST FAIL SC CONT - SCS SCS TVC (2) - AUTO

(REJECT) ENTR

21 06 40 TFIVG~VM (m~n-sec1fps)

PROG ALM - TIG s1~pped

V5N9E 01703

KEY RLSE To 21 ROT CONTR PWR DIRECT (2) - MNABSPS He v1vs (2) - AUTO (ver~fy)

LIMIT CYCLE - OFFFDAI SCALE - SOIScb SPS P2Y2 - open (for cr~t burn)

5800(-02 00)

5925(-0035)

59middot 30(-0030)

06 40

59XX(-OOXX)

AV THRUST A(B) - NORMALTHC - ARMEDRlIC (2) - ARMEDTAPE RCDR - GID RESETHBR

DSKY BLANKS

(AVE G ON)EMS MODE - NORMAL

TFIVG~VM (m~n-seclfps)

CHECK PIPA BIAS lt2fps for 5 sec

ULLAGE AS REQ

IF NO ULLAGE DIR ULLAGE PB - PUSH~

CONTROL ATT WRlIC MONITOR AVM (R3) COUNTING UP

5955(-0005)

F 99 40 ENG ON ENABLE REQUEST(AUTO IGN) PRO AT TFI gt0 sec(BYPASS IGN) ENTR to 24

22 0000 IGN

-39-

If SCS - THRUST ON PB - PUSH

06 40 TFCVG~VM (m~n-seclfpslfps)

~F 97 40 SPS Thrust fall ~

~(RESTART) PRO To IGN (RECYCLE) ENTR To TIG-05 sec

SPS THRUST LITE - ONMONITOR THRUSTING

Pc 95-105 pSlaEMS COUNTING DOWNSPS IN3 v1vs (4) - OPENSPS He v1vs tb (2) - graySPS FUELOXID PRESS - 175-195 pSlaPUGS - BALANCED

PROG ALARM V5N9E 01407 VG INCTHC - CW FLY MTVC

ECOEMER SPS CUTOFF J

AV THRUST (2) - OFF

23 F 16 40 TFC(STATIC)VG~VM (mln-seclfps)~V THRUST AB - OFF

SPS IN3 v1vs (4) - CLOSEDSPS He tb (2) - bp

cb SPS P2Y2 - closed (verlfy)TVC SERVO PHR - AC1MNA (venfy)TVC SERVO PWR 2 - OFF

PRO

24 F 16 85 VG XYZ(CM) CUps)NULL RESIDUALSRECORD ~V CTR amp RESIDUALS I1VCEMS FUNC - OFF VGXEMS MODE - STBY VGYBMAG MODE (3) - RATE 2ATT DB - MAX VGZTRANS CONT PHR - OFF

PRO

25 F 37 V82E

26 F 16 44 HAHPTFF (lnmm~n-sec)

R3-59B59 HP gt494 nmPRO

27 F 37 OOE

-40-

55 EARTH ORBIT ENTRY

1 Venfy CMSMR __

P_shyY_-

SEP ATT(180deg)

(0deg )

2

3

4

EMS INITIALIZATIONEMS FUNC - RNG SETSET RNG TO PAD DATA RNGEMS FUNC - VA SETSlew scroll to pad data VIOEMS FUNC - ENTRY

RSI ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on(up)GDC ALIGN PB - PUSH amp HOLDYAW tw - Pos1tion RSI thru 45deg amp

back to LIFl UPGDC ALIGN PB - RELEASEEMS ROLL - OFFAl1gn GDC to lMU

PWR REDUCT (Norm Deorb Only)HGA PWR - OFFFC PUMPS (3) - OFFVer1fy s1ngle suit compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - Lowcb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2)-openlOb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MAN

-41-

P61 - ENTRY PREP

5 V37E 61E05 09 01427 - ROLL REVERSED05 09 01426 - IMU UNSAT

6 F 06 61 IMPACT LAT LONG liDS UPDN (+-)(01 0

010

+00001)

PRO

PAD VALUESLATLON==G------liDS UP DN _

7 F 06 60 GMAXV400KGAMMA EIRecord

GMAXV400K----GAMMA EI _

PRO

8 F 06 63 RTOGO (1nm) PAD _VIa (fps) PADTFE (mln-sec) ----Compare wlth MSFN for PGNS GONO GONO COMM SET RTOGO amp VIO IN EMS amp

INITIALIZE(ACCEPT) PRO(RECALC) V32E to 8

-42-

P62 - CMSM SEP amp PRE-ENTRY MNVR

9 F 50 25 00041 REQUEST CMSM SEPSC CONT - SCSFREEYAW - 45deg out-of-plane (left for RCS

nght for SPS)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE2PRIM GLY to RAD - BYPASS (verlfy)SECS LOGIC (2) - on (up)MSFN conflrm GO for PYRO ARMSECS PYRO ARM - ARMMN BUS TIE (2) - ON (verlfy)CMSM SEF (2) - ONCSMLM FNl SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 pSlaCM RCS LOGIC - OFFSECS PYRO ARM - SAFEMonltor VMAB

If lt25vdc go to EMERG POWERDOWN Pg E6-1AUTO RCS SEL AlC ROLL (4) - OFFAUTO RCS SEL CM 2(6) - OFFAUTO RCS SEL CM 1(6) - MNA or MNBYAW back to 00

PITCH TO ENTRY ATTROLL 0deg (LIFT UP)PITCH - HORIZ on 317deg MARK (400K)YAW 00

ATT DB - MAXMAN ATT (PITCH) - ACCEL CMDEMS DATA - VerifyEMS FUNC - ENTRY (verlfy)EMS MODE - NORMALMAINTAIN HORIZ TRK

PRO (Act ENTRY DAP)

10 F 06 61 IMPACT LAT LONG HDSDN(010 010 -00001)

PRO

11 FOSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axlS beyond 45deg of Vel vector)

-43-

P63 - ENTRY INIT

12 06 64 GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PWR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRHORIZ CKP~tch error needle goes toward

zero approach~ng 05G t~me

MAN ATT (PITCH) - RATE CMDIf CMC ~s GO

BMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS FLY BETA If CMC NO GO ~

SC CONT - SCS~

FLY EMS RCS Deorh Roll HDS UPTRACK HORIZ w~th 29deg w~ndow mk

P64 - ENTRY POST 05G

13

05G t=elt+0___)

06 68

RTOGO AT 05G AGREES WITH EMS - venfyHORIZ CK05E Lt - on (EMS start)

No EMS start w~th~n 3 secsEMS MODE - BACKUP VHF RNG 05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds L~ft DN

NNVR L~ft DNEMS GONO GO

G-V Plot w~th~n llm~ts

Rng ctr dwn 60 + 7 durlng 10 sec per~od

Mon~tor G-meter forconvergence wlth pad data (Do)

(Vlt27K fps) Go To 17

-44-

P65 - ENTRY - UP CONT (Vgt27K fps)

14 F 16 69 BETA (01deg)DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT~

SC CONT - SCS FLY EMS

PRO

15 06 68 BElA VI HOOT (01deg fpsfps)(VltVL +500 fps amp RDOT Neg) Go To 17

p66 - ENTRY - BALLISTIC (DltDL)

16 06 22 DESIRED GMBL ANGLES RPY (01deg)Mon~tor hor~z +12deg of 317deg mark

P67 - ENTRY - FINAL PHASE (02G)

17 0666 BETACRSRNG ERRDNRNG ERR (Oldeglnmlnm)KEY VERBRecord DNRNG ERR _KEY RLSEL~m~t +100nm from PAD DRE

Mon~tor l~ft vector on RSI amp FDAIF 16 67 RTOGOLATLONG (Vre1=1000fps)

(lnm 010 01deg)SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOlfflMon~tor altimeter

Go To EARTHLANDING pg _I4L5__

-45-

56 EARTHLANDING

90K STEAM PRESS - PEGGED50K CABIN PRESS REL vIv (2) - BOOSTENTRY

SECS PYRO ARM (2) - ARM

40K(90K + 63s)

CM UNSTABLE RCS CMD - OFF ~ 40K APEX COVER JETT PG-PUSH DROGUE DEPLOY PG - PUSH (2 secafter apex cover Jett)

30K ELS LOGIC - ON (up)ELS - AUTO

24K RCS hsable (auto)(90K+92s) RCS CMD - OFF

Apex cover Jett (auto)APEX COVER JETT PB - PUSH

(WAIT 2 SECS)Drogue parachutes deployed (auto)

DROGUE DEPLOY PB - PUSH~

If Drogues FallELS - ~ ~Stablllze CM 5K MAIN DPLY PB - PUSHELS - AUTO

235K Cabln Pressure lncreaslng (Drogues + 50s)If not lncreaSlng by 17K CABIN PRESS REL vlv (RR) - DUMP

-46-

10K Maln parachutes deployedMAIN DEPLOY PB - PUSH (wlthln 1 sec)VHF ANT - RECYVHF AMA - SIMPLEXVHF BCN - ONCABIN PRESS REL v1v (2) - CLOSEDIRECT 02 vlv - OPENCM RCS LOGIC - on (up)CM PRPLNT - DUMP (burn audlb1e)Monltor CM ReS 1amp2 for He press decrease

NO BURN or PRESS DECREASE USE BOTH RHCs DO NOT FIRE PITCH JETS

CM PRPLNT-PURGE (to zero He press)CM RCS He DUMP PB - PUSH RHC (2) - 30 sees NO PITCH k

STRUT LOCKS (2) - UNLOCK

cb FLT amp PL BAT BUS ABampBAT C (3) - closecb FLT amp PLT MNA amp B (2) - opencb ECS RAD HTR OVLD (2) - opencb SPS PampY (4) - open

3K CABIN PRESS REL v1v (RH) - DUMP (after purgecompleted)

FLOOD Lts - POST LDGCM RCS PRPLNT (2) - OFFROT CONTR PWR DIRECT (2) - OFF

800 CAB PRESS RELF vlv - CLOSE (latch off)MN BUS TIE (2) - OFF

AFTER LANDINGcb MAIN REL PYRO (2) - closeMAIN RELEASE - on(up)

Go to POSTLANDING pg _47L-__

I

2

3

-47-

57 POSTLANDING

STABILIZATION VENTILATION COMMUNICATIONS

DIRECT 02 vlv - CLOSE

Stablllzation after landlngELS - AUTO (verlfy)cb MAIN REL PYRO (2) - close (venfy)MAIN RELEASE - on (up) (verlfy)S~CS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb BAT RLY BUS (2) - open

No contact w1th recovery forcesVHF AM AampB - off (ctr) ~

VHF AM Rev ONLY - A cb PL VENT - closecb FLOAT BAG (3) - closecb UPRIGHT SYS COMPRESS (2) - closeIf Stable II

FLOAT BAG(3)-FILL t1ll 2 m1n afterupr1ght then - OFF

VHF AM AlB amp BCN - OFF whlle lnvertedIf Stable I

After 10 M1n Coollng Per1odFLOAT BAG (3) - FILL 7 mln then OFF

Post Stab1lizat1on And Ventllat10nPL BCN LT - BCN LT LOWPL VENT vlv - UNLOCK (Pull)Remove PL VENT Exh CoverPL VENT - HIGH or LOWPL DYE MARKER - ON (swlmmer comm)Release foots traps and_restralntscb MNA BAT BUS A amp BAT C (2) - opencb MNB BAT BUS B amp BAT C (2) - opencb FLT amp PL BAT C - opencb PYRO A SEQ A - opencb PYRO B SEQ B - open

EACH HR - CHECK DC VOLTSgt 275 V If Notmiddot cb FLT amp PL-BAT BUS AampB (2) -open cb FLT amp PL BAT C (1) - open GO TO LOW POWER CHECKLIST

Unstow and lnstall PLV DISTRIB DUCTDeploy grappllng hook and 11ne 1f req

4

-48-

Post Landing Communlcatl0nsVHF ANT-RECY (venfy)VHF BCN - ON (verlfy)

If no contact ~lth recovery forcesperform VHF BEACON Check

MONITOR VHF BEACON transmlSSlonnth VHF AM B Rcvr andor Su)vlval

TransceiverkVHF Beacon not operatlng ~connect Surv~val TranscelVer to antcable behlnd VHF ant access pnland place radio ln BCN mode

LOW POHER CHECKLISTVHF BCN - OFFVHF AM (3) - RCVFLOOD Lts - OFFVHF AM AampB - off (ctr)VHF AM RCV ONLY - A (venfy)COUCH LIGHTS - OFFPOSTLANDING VENT SYS mlnlmlze useSURV RADIO - plug mto VHF BCN ANT cableconn behind VHF ant acess pnl amp turn radloon l-n BCN mode

EGRESS PROCEDURES

CMPCDRLMPCDR

CMPCDRCMP

LMPLl1PCDR

STABLE IDlsconnect Umblll-calsNeck darn onCenter couch - 270 0 positionArmrests stowedConnect raft to SIC l-f desl-red wlth

green lanyardConnect raft ~hl-te lanyards to SUltS amp

lnflate water wlngs when eXltl-ngHATCH PISTON PRESS vlv - PRESS (Outbd)Slde Hatch openedPL VENT - OFFcb Pnl 250 (all) - openEgress with 11feraftPut hardware klt outEgress

or CDIPALL

CMF

CDRCMF

CDR

LMF

CMFCMP LMFCMP

UlP

CDR

-49-

STABLE IIcb CREW STA AUDIO (3) - openD~sconnect umb~1~ca1s

Release foots trapsRelease restra~nt harnessCouch seat pans (3) - 170 0 pos1t10nArm rests stowedSurv1va1 k~ts removed from stowageConnect life raft ma~n1~ne to CDR or SicConnect f~rst wh~te lanyard from

11fe raft to suitConnect th~rd wh~te lanyard from

l~fe raft to SU1tConnect rucksacks together to yellow

lanyard on raft bagPRESSURE EQUALIZATION vlv - OPENRemove and stow fwd hatchEX1t feet f1rst w1th rucksacks when clear

of siC 1nflate water w1ngs and raftExit feet f1rst when clear of SiC

1nflate water w1ngsEX1t feet f1rst when clear of sic

1nflate water w1ngs

-50-

60 TLI ABORTS

TLI Aborts are conta~ned ~n the ESD s~nce the bulk of the funct~ons

concern entry preparat20ns and performance Th~s allows a s2nglesource of procedures for procedure rev2ew val~dat~on checkout andtra~n~ng These procedures ~ncorporate TLI preparat20ns as found ~n

reference 6 w~th the TLI Abort Procedures and these t~e 2nto normallunar return Entry Procedures found ~n sect20n 5 The guidel~nes

for th~s cont2ngency are spec2f2ed 2n reference 7

In2t2al preparat~ons for TLI pos2t20n the necessary system sW2tches2n add~t~on to perform~ng an EMS ~V test and a GDC al~gnment Afterthe DET ~s set for mon2tor2ng TB6 the CMP ~ncreases the 12ght levelof the LEB DSKY to max~mum and returns to the h2s couch Th2s 2Sdone so that the LEB DSKY can be observed ~n the event sunl~ght orreflect20ns wash out the ma2n d2splay panel DSKY dur2ng cr2t2calmaneuvers The crew then straps ~n and prepares for mon2tor~ng TB6as 2nd2cated by the SII SEP L~te The t2mes se~uence of procedures2S keyed on th~s d~splay and ~ncludes the DET START funct~on andSIVB IGNITION Dur2ng the burn the crew mon2tors the FDAIs foratt~tude excurs20ns and abnormal rates report~ng status checks toM~ss2on Control at d2screet t~mes dur2ng the maneuver Upon SIVBSHUTDOWN the eMP records the DSKY d~splayed performance parametersand awa2ts ground conf2rmat~on

The rat~onal for TLI aborts ~s descr~bed 2n reference 7 A summar2shyzat20n 2S extracted to prov2de background and gu2de12nes 2n th2sdocument The abort procedures cover aborts 10 m2nutes after conshyt2ngent SIVE shutdown and aborts 90 m2nutes after normal SIVE shutshydown t2me

The 10 m~nute TLI abort ~s des2gned to be used dur~ng TLI ~n theevent a spacecraft problem develops Wh2Ch can result 2n catastrophe2f ~mmed~ate act~on 2S not taken If the s~tuat20n perm~ts the crewshould always allow the SIVB to complete TLI at wh~ch t~me the groundand crew can perform a malfunct~on analys~s to determ~ne ~f an abort~s adv~sable If a fa~lure occurs that necess2tates the shutdown ofthe SIVB and the ~u~ck return of the crew to earth th~s abort ~s

des~gned to be as ~nsens~t~ve to execut~on errors as poss~ble andst21l be targeted to m2dcorr2dor The burn att~tude w~th the f~ed

hor~zon reference ~s a constant value for any shutdown t~me Theburn durat~on 2S a funct20n of shutdown t2me and 2S ava21able fromcrew charts S~nce the pr~mary purpose of th~s abort ~s to returnto earth as qU2ckly as poss2ble there are no restr2ct20ns as toland~ng locat~on However ~f the t~me to EI is greater than abouttwo hours a midcourse correct20n should be ant~c~pated

The 90 m2nute TLI abort 2S to be used 2f a cr2t2cal subsystem malshyfunct~on ~s determ2ned and the dec2s~on to abort ~s made after the

-51-

TLI cutoff and before TLI cutoff plus approxlmately 80 m1nutesTh1S allows suff1c1ent separatlon and procedural t1me to set upfor the SPS deorb1t burn performed at about TLI + 90 Note thatgenerally the deorb1t burns w1ll be performed a fe11 m1nutes beforeTLI + 90 accord1ng to crew charts shown In reference 8 The no-comm except10n requ1res that 90 m1nutes be the 1nput t1me of 19n1shytlon for P-37 (onboard return-to-earth abort program) so that onshyboard calculatlons can correspond w1th ground calculat10ns to computethe CM land1ng p01nt Th1S TLI abort lS des1gned so that returnfl1ght t1me does not exceed 18 hours and abort ~V does not exceed7000 fps ThlS abort can be performed uSlng chart ~Vs and attltudesand the earths hor1zon serves as a suff1c1ent reference The maneushyver lS targeted to ach1eve the mldcorr1dor entry target Ilne andtlmed to result 1n a deslgnated recovery area

It 1S ObV10US for abort deC1S1ons early 1n the TLI + 90 m1nute t1meshyframe that a GampN SPS burn should be performed In order to keep theTLI abort procedures cons1stent and w1th emphasls on slmpl1c1ty theprocedures here reflect a SCS SPS abort burn to cover the full abortdec1s1on t1meframe

A m1dcourse correct1on for corr1dor control after a TLI abort may bedeS1red 1f the SPS burn d1d not meet expectat1ons The TLIabortprocedures 1n th1S sect10n adapt to the normal lunar return tlmel1neand procedures pr10r to the f1nal MCC

-52-

61 TLI PREPARATION PROCEDURES

GET = 150

CRO AOS(___)

CRO LOS( )(22142)

5100

Don Helmets amp Gloves

XLUNAR - INJECT (verify)EDS PWR - on (venfy)EMS FUNC - OFF (verlfy)EMS MODE - STBYEMS FUNC - IW SETVHF RNGEMS MODE - NORMALSet ~V indo to +15868 fpsEMS FUMC - ~V Test

SPS THRUST Lt - onoff (10 sec)~V lnd stops at -01 to -415

EMS MODE - STBYEMS FUMC - ~V SETVHF RNGSet ~VC

EMS FUNC---~~V=----

GDC ALIGNFDAI Select - liZcb SECS LOGIC (Z) - close (verify)cb SECS ARM (Z) - closeSECS LOGIC (Z) - on (up)MSFN Conflrm GO for PYRO ARM (If pass)SECS PYRO ARM (Z) - on (up)TRANS CONTROL PWR - ONROT CONTR PWR NORMAL (Z) - ACDC(verlfy)ROT CONTR PWR DIRECT (Z) - MNAMNBLV INnGPI - SIISIVB (venfy)LV GUID - IU (venfy)cb DIRECT ULLAGE (Z) - closedSet EVENT TIMER to 5100Begin MONITOR For TB6

CMP to Couch

TB 6 - SII SEP Lt on (TIG-9 mln 38 sec)KEY V83E

SET ORDEALFDAI Z ORB RATE at 180 0 0SII SEP Lt out (38 sec later)Start DET COUNTING UPSC CaNT - SCS (verify)MONITOR LV TANK PRESS

~P lt 36 psid (OXID gt FUEL)~P lt Z6 psid (FUEL gt OXID)

EMERGENCY CSMLV SEP UP TLM CM - BLOCK (verify)UP TLM IU - BLOCK (venfy)

-53-

+45degPY))0middot sec PY

lOK nmltHAlt25K nm

Two phas~ng mnvrs two SPS mnvrs to circular~ze at 150 nmearth orb~t

CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ssion 4K nmltHAltlOK nm CSM amp1M - Two phasing mnvrs two SPS mnvrs to circularize at 150 nm earth orb~t CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ss~on

CSM amp 1M - Two phas~ng mnvrs APS burn todepletion th~rd phasing mnvrSPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn tosem~sync orb~t

25K nmltHAlt40K nm CSM amp 1M - Two phasmg mnvrs APS burn to depletion third phas~ng mnvr SPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn to sem~sync orbit HA)40K nm DPS ava~l - DPS LOll circularize with SPS

DPS not ava~l - Lunar flyby or CSM only to lunar orbit (if reqd gtV lt4000 fps)

V37E 47E (check b~as) Record -=--rshy(Limit 98 fpsmm)

( 1fps)tVXYZN62EVIHDOTHPAD (fpsfpslnm)MONITOR VI ( ) at ECO

SCS TVC SERVO PWR 1 - ACIMNA2 - OFF

TAPE RCDR - CMD RESETHBREMS MODE - NORMAL

SIr SEP Lt - ONTLI Inhib~t S~gnals w~11 not be honored after 5942

SIVB ULLAGE BeginsSII SEP Lt - off (TIG - 18 sec)SIVB FUEL LEADSIVB ULLAGE d~scont~nues

LV ENG I Lt - onSIVB IGNITION ( GETI)LV ENG I Lt - off - -shyMONITOR THRUST amp ATTITUDEMONITOR LV TANK PRESSSIVE ECO (Lt on) (BEGIN TB7)

EMER SIVE CUTOFF AT 6 SEC PAST BURN TIME IF VI ATTAINEDTHC CCW ampNEUTRAL IN 1 SEC or SIISIVB sW - LV STAGEPremature Shutdown HAlt4K nm CSM amp 1M -

5700

58205836

F 16 835800

F 16 62

5838594259525955595900000002SUNRISE(___)

HAW AOS(__=_) KEY VERB (freeze d~splay)

SIVB ATT HOLD 20 sec amp BEGIN VENTINGSIVB NNVR TO ORB RT (HDS DN) (3middot sec)

Record VI -c---HDOT _

HPAD _

KEY RLSEF 16 62

F 16 83

HAW LOS(__=-)

KEYmiddotRLSE~VXYZ (lfps)

Record ~VX---_

~vy

WZ--

AVC---_

TAPE RCDR - off (ctr)EMS MODE - STBYEMS FUNC - OFFSECS PYRO ARM (2) - SAFE

PRO

BURN STATUS REPORT

____--~TIG

BT------VGX____-R

-----P----_Y

REMARKS

_____VI

______--HDOT______--H______---AVC______---FUEL_______OXID

_______UNBAL

F 3708=00 OOEGOS AOS CMP TO LEB

(-=-=-)

0000

0003

0005

0014

0100

-55-

62 TLI 10 MIN ABORTSECS LOGIC (2) - on (up)SECS PYRO ARM (2) - ARM

TRANS CONTR - CGH (4 sec) amp +XDET RESET (verlfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS GMD-ON

TRANS GONTR - neutral then +X for10 sec

SIVBGPI s~ - GPIExcesslve rates 6V THRUST A - NORMAL SPS THRUST - DIRECT When rates damped 6V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

TRANS CONTR +X - OFFV37E OOE

PITGH UP to LOGAL VERT (+X axlSto~ard the earth)

RATE - LOWBMAG MODE (3) - ATTIRATE 2EDS PHR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SEGS ARM (2) - opencb EDS (3) - open

TRANS CONTR -X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (180deg)P (199deg)Y (0deg)

RETRO UPDATEGETI _

JV _VG

Jtb ---GET 400K _

05G _GET DROGUE _

ENTRY P _R _

Y_--

0945

-56-

ALIGN HORIZ ON RET +1 MKGMBL CHECK (T11lle Pentattlng)MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conflnn)cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FUMC - JV SETVHF RNGSET JV from chartE~S FUMC - JVEMS fODE - NOIDlAL

lV THRUST A - NORMALV37E 47E (THRUST fONITOR)

F 16 83 lVXYZ (1 fps)

0950

1000

NOTE For aborts durlng 1st mln of TLIKEY V82E F 16 44 (HaHpTff)Burn untll Hp lt 19NM

TRANS CONTR +X

THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN JV reqdJV THRUST (2) - OFFReport cutoff

cb SPS P2 Y2- closeGfBL MTRS (4) - OFF (LMP Confinn)TRANS CONT PWR - OFFTVC SERVO PWR (2) - OFFMN BUS TIE (2) - OFFcb SPS P1amp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREIf est time to EIltOl5500 omlt fCC andenter the SUPERCIRC CKLIST as early as pos-slb1e Pg ~2~3~ __If est time to EI)Ol5500 anticlpate afCC Enter the ENTRY PREP CKLIST at step 9pg 18

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

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-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 15: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

33

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40 EARTH ORBITAL DEORBIT AND ENTRY TECHNIQUES

As outl~ned ~n reference 5 a nom~nal PGNCS entry from earth orb~t ~s

based on a preparat~on t~me of 2 hours and 40 m~nutes ~nclud~ng 2n~ght passes Th~s t~me ~ncludes approx~mately 20 minutes before thef~rst n~ght pass after the CMC update and PAD data have been rece2vedTh~s t~e also 2ncludes approx2mately 20 m2nutes after the secondn~ght pass to allow suffic~ent t2me to prepare for retrof2re after theIMU f2ne a12gnment It has been determ2ned coarse a12gnment accuracy~s adequate for retrof~re and entry and undoubtedly other funct20nscould be om2tted depend2ng on the c2rcumstances for the dec2s20n toreenter Descr2bed here2n are the nom2nal earth oro2tal entry proshycedures w2th pert2nent comments on system va12dat20n for real timeacceptance dec~s20ns

After the entry dec~s~on is made the crew transfers the PGNCS fromthe standby to the operate mode and rece~ves a CMe update w~th P27Next the maneuver PAD update ~s v02ced up and the 2n~t~al entry mode~s determ~ned During the ~n~tial n~ght pass the IMU or2entat~on ~s

estab12shed uS2ng P51 star s~ght2ngs to obta2n a REFSMMAT The preshyferred or~entat~on opt20n ~n P52 2S then selected to coarse a12gn theIMU uS2ng the des2red entry REFSMMAT determ2ned by MGG-H The GOO ~s

now al~gned to the IMU 2n preparat~on for an IMUSes dr~ft check Ifthe GOO ~nd~cates the ses dr2ft rate exceeds 10 degrees per hour ~n

any ax~s the check ~s repeated on the other BMAGs to estaol~sh if theGOO or Just the single set 2S unusuable Var20us sytem checks as 12sted2n sect20n 51 are performed as necessary cons2stent w2th the t2me12ned2ctates of the maJor act2v2t2es Included 2n these checks are the EMSself-tests and the dV counter test The latter requ2res the spacecraftbe placed ~n dr2ft2ng fl2ght w~th the funct20n sW2tch 2n the dV pos2t~on

If the counter reg2sters a change of more than 25 feet per second w2th2n100 seconds the scroll and counter are unre12able for mon2tor2ng thedeorb2t burn and entry rang2ng If the EMS self-test fails and t2medoes not allow further analysis a 5555 ERE entry 1S planned as thePGNGS backup entry mode After complet2on of these checks the entryPAD lS prov1ded by MeG-H The crew then selects the external dVprogram P30 and the appropr2ate deorb1t tbrust1ng program p40 or P41Dur2ng th2s per2od wh2ch 2ncludes the f1nal n2ght pass P52 may beselected to ver2fy the IMU a12gnment Since the retro att2tude hasbeen computed so that a w2ndow mark c01nc2des w2th the hor2zon atGETI th2s serves as the conclus2ve check on the PGNCS At 5 m2nutesbefore retrofire the att2tude check 1S made by ver1fY2ng that the 12degree scr~be 12ne ~s w2th2n 3 degrees of the hor2zon If not thePGNeS has fa2led and the ses 2S used for att2tude reference and the

V counter for burn durat~on control S2nce the ses att~tude wasa12gned to the IMU a real~gnment ~s necessary This ~s accompl~shed

by manually maneuver2ng the spacecraft to ma~nta1n the 24 degree wlodowmark on the hor2zon and releas1ng the GOO a12gn button at TIG - 2 m2nutes

-14-

Upon complet~on of the burn the tN res~duals are burned to W~th~n

02 feet per second If the PGNCS ~V counter or est~mated burnduration are ~n d~sagreement ~t must be estab1~shed whether suff~shy

c~ent veloc~ty has been suppl~ed to put the land~ng po~nt in thefootpr~nt The PGNCS data w~ll be used ~f ~t ~s conf~rmed by oneother source if not the ~V counter w~11 be used ~f ~t ~s conf~rmed

by the burn durat~on t~me If add~tional ~V ~s necessary the data~s ava~lable to the crew on an onboard chart found ~n Sect~on 80

Post burn entry preparat~on requ~res EMS ~n~t~al~zation RSI al~gnshy

ment and pre-separat~on funct~ons The crew then selects the ~n~t~al

entry program P61 and records the d~sp1ays as a check aga~nst PADdata Upon complet~on of these checks P62 ~s entered The crewmanually or~ents the spacecraft to the separat~on attitude and yaws450 to ~nsure aga~nst possible CM 8M recontact After separat~on

the spacecraft ~s maneuvered to the reentry tr~m att~tude wh~ch

places the hor~zon on the 3170 w~ndow mark at EI Shortly thereshyafter ~n P62 the entry DAP is act~vated and P63 in~t~ated Dur~ng

th~s t~e MCC-H has computed a postburn update and ~t ~s vo~ced tothe crew ~f d~fferent from preburn values The EMS scroll and rangecounter w~ll be adJusted accord~ngly ~f t~me perm~ts A f~nal PGNCScheck pr~or to 05g may be mon~tored at th~s t~e w~th the CMC modein free and the manual att~tude p~tch ~n acceleration command wh~le

the hor~zon reference ~s held the p~tch error needle w~ll decreaseto zero as EI ~s reached At RET 005g the EMS mode sw~tch ~s

turned to manual the entry 005-g sw~tch and EMS roll sw~tch areturned on and the spacecraft control sw~tched to CMC to beg~n DAPcontrol At the PGNCS 005-g ~ndicatwn the program change fromP63 to P64 ~s mon~tored and the t~e vo~ce recorded At th~s t~me

the EMS range counter check ~s made dur~ng the 10 second per~od

follow~ng EMS 005g Dur~ng th~s per~od the counter should countdown 40 + 10 naut~cal m~les At PGNCS 02-g ~nd~cation the changefrom P64-to P67 ~s monitored and the ~splay may be held by key~ngVERB ~n order to record the init~al downrange error d~splay andcompare ~t to the PAD value The PGNCS has fa~led ~f the two do notagree w~th~n + 100 naut~cal m~les In the event P67 has not appearedwhen both the-g-meter and the scroll ~nd~cate greater than 05g thePGNCS has sim~lar~ly fa~led In e~ther fa~lure the SCS is used foratt~tude reference w~th an EMS entry If the checks agree the crewrema~ns w~th automat~c DAP for the rema~nder of the entry

The entry phase ~s essentially over when the relat~ve velocity ofthe spacecraft decreases to less than 1000 feet per second Th~s

~s ~nd~cated ~n P67 when RTGO lat~tude and long~tude are d~splayed

S~nce very l~ttle rang~ng capab~l~ty exists after th~s pOint thespacecraft is or~ented either full l~ft up or down depending onRTGO negat~ve or pos~t~ve and the crew prepares for the earth land~ng

phase

-15-

41 TYP~cal Retrof~re and Entry Sequence of Events

Dec~s~on to reenter

P27 (CMC update)

Retrof~re PAD update

Entry mode dec~s~on

P51 (IMU or~entat~on determlnatlon) durlng f~rst dark per~od

P52 (IMU coarse allgnment)

EMS checks

Entry PAD update

P30 (external AV)

p40 (SPS thrust)

P52 (IMU f~ne al~gnment) durlng second dark per~od

p40 (SPS thrust)

Ign~t~on att~tude check

Retroflre

P61

P62

CMSM separat~on

P63

Postburn PAD update

Entry attltude check

p64 (beg~n DAP control at O05g)

P67 (PGNCS gono go check at O2g)

42

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-17-

5 0 DETAILED ENTRY PROCEDURES

In order to comblne slmilar procedures that are common to lunar returnentrles and earth orblt entrles the followlng procedures are dlvldedlnto categorles that allow a mlnlmum of dupllClty ThlS provldes asmaller tralnlng package and more closely resembles the onboard crewcheckllst when comparlson lS necessary

51 Entry Preparatlons for Superclucular and Earth Orbltal Entrles

1~e entry preparatlons are comblned In these procedures andsteps pecullar to elther superclrcular or earth orbltal entrlesare labeled accordlngly The tlme llstlngs In thlS sectlon areappllcable to only superclrcular entries Slnce the earth orbltalentry tlmellne lS a functlon of several varlables as descrlbedIn sectlon 40 and reference 5

-18-51 (Contlnued)

VEHICLE PREPARATION

l-

2

3

4

5

6 -0600h

7 -0535h

8

9

10 -0430h

INITIAL STOWAGE COMPLETED

CMC amp ISS START UP

SCS POWER UP

p51 - IMU ORIENTATION

LOAD DAPV48E 11102 01111 PRO ERO PRO

LAST MCC DECISION

NO COMM - P52 amp NAV SIGHTINGSNOMINAL - P2337 ONBOARD COMPARISON

DON MAE WESTS amp FOOT RESTRAINTS

VHF AM A - SIMPLEX

P 27 (SV REFSMMAT) MNVRamp ENTRY pAD UPDATES

11 -0415h P52 - IMU REALIGN(___) (OPTION 1)

12 P37 (NO COMM ONLY)

13

14

ECS CKS02 SUPPLY REFILLECS Monitor CkEVAP H20 CONT (2) vlvs - AUTOSUIT HEAT EXCH SEC GLY - FLOW

EPS CKS 1 3 4 (5 If reqd)

15 SPS CK (If req d)

16

17

18

RCS CKSSM RCS MOUlt CkCM RCS MOUlt Ck

CampW SYS CK

CMC SELF CK

19

20 -0345h

-03l5h-0300h

21

22

22A

-19-

DSKY COND LT TEST

MIDCOURSE MANEUVERP30 - EXT rVP404l - SPSRCS THRUSTINGMIDCOURSE (17) BURN

NO COMM NAV SIGHTINGS

ffiVR TO ENTRY ATT (Superc1rc only)V62E

V49E

22B F 06 22 DESIRED FINAL GMBL ANGLESLOAD ENTRY ATT PAD ANGLESPRO

22C F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) SC CONT - CMC

BMAG MODE (3) - RATE 2CMC MODE - AUTO

PRO(~N) SC CONT - SCS

MNVR to 22E

22D 06 18 AUTO MNVR TO FDAI RPY ANGLES

22E F 50 18 REQUEST TRIM(TRIM) Go to 22C(BYPASS) ENTR

23 -200hr BORESIGHT amp SXT STAR CHECKOPT MODE - CMCOPT ZERO - OFF

V41 N91E

F 21 92 SHAFT TRUNLoad SXTS angles

41 OPTICS DRIVE

CHECK SXT STAROPT ZERO - ZERO

CHECK BORESIGHT STAR (If ava11)

24 -0135h

25(___)

26

27 -0115h

-20-

P52 - lMU REALIGNRecord gyro torqu~ng anglesRp~----

YIf-7gt-Lno--re-c-ycle PS2If conflrmed use SCS for EMS entry

GDC ALIGNIf drlft gtLOohr change ratesource

FINAL STOWAGEOPTICS (except for hybrid)ORDEALGLY TO RAD SEC - BYPASS (verlfy)CooL pnl lnstalledY-Y struts (2) extendedStow Data Box R-12

EMS CHECKEMS FUNC - OFFcb EMS (2) - closeEMS MODE - STBYEMS FUNC - EMS TEST 1 (walt 5 sec)EMS MODE - NORMAL (walt 10 sec)

Check ind lts - offRANGE lnd - 00Slew halr1ine over notch

In self-test patternEMS FUNC - EMS TEST 2 (walt 10 sec)

05G It - on (all others out)EMS FUNC - EMS TEST 3

05G It - onRSI Lower It - on (10 sec Qater)Set RANGE counter to 58 nm+OO

EMS FUNC - EMS TEST 405G It - on (all others out)G-V trace w~thin pattern to lwr rt

corner 9GRANGE lnd counts down to 0+02

EMS FUNC - EMS TEST 505G It - onRSI upper lt - on (10 sec later)RANGE md - 00SCrlbe traces vertlcal llne 9g to

022+01ALIGN SCROLL TO ENTRY PATTERN (on

37K ft sec hne)EMS FUNC - RNG SET

G-V scroll assy traces vert llne022g to 0+01

EMS MODE - STBY

28

29

30 -OllOh

-21-

~V TEST (Deorb~t only)EMS FUNC - ~V SETVHF RNGSET ~V ~nd to 15868 fpsEMS MODE - NORMALEMS FUNC - ~V TEST

SPS THRUST LT - onoff (10 sec)~V ~nd stops at -01 to -415

EMS MODE - STBY

PRIMARY WATER EVAP ACTIVATIONGLY EVAP H20 FLOW - AUTOGLY EVAP STH PRESS - AUTOPRI ECS GLY PUMP - ACI

CM RCS PREHEATNote If sys test mtr 5cd6abcd

all read 39 vdc (28degF) or moreom~t preheat

cb RCS LOGIC (2) - closeCM RCS LOGIC - ONUP T1M CM - BLOCK (ver~fy)

cb CM RCS HTRS (2) - closeCM RCS HTRS - ON (LMP Conf~rm)

(20 mlU or III lowest rdg lS39 vdc) (Moultor Maufpress for press drop)

31 (___) FINAL GDC DRIFT CK (If req I d)If drlft gtlOohr Suspect GDC Do not

use RSI amp FDAI 2

32 -OO5Om

33

34

35

TERM CM RCS PREHEATUP TLM CM - BLOCK (venfy)CM RCS HTRS - OFFCM RCS LOGIC - OFF

SYSTEMS TEST PANEL CONFIGURATIONSYS TEST METER - 4BRNDZ XPNDR - OPERATECM RCS HTRS - OFFWASTE H20 DUMP - OFFURINE DUMP - OFF

LEB LIGHTING - OFF

SEC WATER EVAP ACTIVATIONGLY To RAD SEC vlv - BYPASSSEC COOL EVAP - EVAPSEC COOL PUMP - AC2

36

37

38 -OO45m

-22-

PYRO BATT CKcb PYRO A SEQ A - close (ver~fy)

cb PRYO B SEQ B - close (verify)DC IND - PYRO BAT A(B)

~If PYRO BAT A(B) lt 35 vdc cb PYRO A(B) seq A(B) - open~

PYRO A(B)BAT BUS A(B)TO PYRO~MN BUS TIE - close

cb MNA BAT C - closecb MNB BAT C - closeDC IND - MNBPNL 8 - All cbs closed except

PL VENT - open (ver~fy)

FLOAT BAG (3) - open (ver~fy)

DOCKING PROBE (2) - open (verlfy)EDS BAT (3) - open (ver~fy)

CM ReS HTRS (2) - open

CM RCS ACTIVATIONcb SECS ARM (2) - close (verlfy)cb SECS LOGIC (2) - close (verlfy)SECS LOGIC (2) - ONMSFN conflrm GO for PYRO ARM(~f poss)SECS PYRO ARM (2) - ARMCM RCS PRPLNT 1amp2 - ONCM RCS PRESS - ONRCS Ind sw - eMl then 2

He PRESS 3700-4400 pSlaMANF PRESS 287-302 pSla

SECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFF

P27 amp ENTRY PAD UPDATEGo To Entry Checkllst

Superclrc - pg ~2~3 _Hybnd - pg -----2~9L-__Normal Deorblt - pg __3L5L- _

-23-

52 SUPERCIRCULAR ENTRY

1 SET DET (up to ET)

2

3

4

5

3000(-30-00)

EMS INITIALIZATIONSET RNG TO PAD DATA RNGEMS FUNC - Vo SETSlew Scroll to Pad Data VIOEMS FUNC - ENTRY

RS I ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on (up)GDC ALIGN PB - PUSH amp HOLDYAW Tw - Pos~t~on RSI thru

45deg amp back to LIFT UPGDC ALIGN PB - ReleaseEMS ROLL - OFFA1~gn CDC to lMU

CM RCS RING A CKRCS TRNFR - CMcb CM RCS LOGIC MNB - openAUTO RCS SEL MNB (6) - OFFSC CONT - SCSTest R~ng A ThrustersSC CONT - CMCRCS TRNFR - SMAUTO RCS SEL (12) - MNAMNB

(hftoff conflg)cb CM RCS LOGIC MNB - close

OPTICS PWR - OFFCMP to COUCH

MN BUS TIE (2) - ONTAPE RCDR - REWIND

6 35middot0Om(-25middot 00)

-24-

SEPARATION CK LISTTVC SERVO PWR 1 - AClMNAcb ELS (2) - close (ver1fy)PRIM GLY TO RAn - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY vlv - OFFCAB PRESS REL vlv (2) - NORMGMBL MTRS (4) - STARTABORT SYS PRPLNT - RCS CMD (venfy)SM RCS PRIM PRPLNT (4) - ONVHF 11M (AampB) - OFFHI GAIN ANT PWR - OFFFC PUMPS (3) - OFFVer1fy s1ugle SU1t compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - 10101cb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2) - opencb HTRS OVLD (2) - openPOT H20 RTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANSEC COOL EVAP - RESETSEC COOL PUMP - off (etr)

MtiVR TO CMSM SEP P R ATTSC CONT - SCSCMC MODE - FREEMNVR TO PAD ATTR (0deg)PY----W)

-25-

SUPERCIRCULAR ENTRY (Cont~nued)

1

4100m(-1900)

P61 - ENTRY PREP

V37E 61E

k 05 09 01427 - ROLL REVERSED 05 09 01426 - IMU UNSAT ~

2 F 06 61 IMPACT LAT LONG HDS UPDN (+-)PRO (010

fps +00001)

3 F 06 60 GMAXVPREDGAMMA EIRecord

GMAXV400K----

GAMMA EI _PRO

(01deg fpsOldeg)

4 F 06 63 RTOGO (lnm) PAD _VIO (fps) PAD _TFE(m~n-sec)

Compare w~th ~M~SFN==C~f~o-r~P~GNS GONO GOIf NO COMM Set RTOGO amp VIO In EMS

amp lnltla11ze(ACCEPT) PRO(RECALC) V32E To 4

5 F 50 25

4300m

(-1700)

45 oOm(-1500)

500Om(-1000)

6 F 06 61

-26-

P62 - CMSM SEP amp PRE-ENTRY MNVRCAUTION Call No EXT Verbs In P62

00041 REQUEST CMSM SEPSC CONT - SCSFREE

COMPARE PITCH ATT WITH PAD DATA ---0=-

(W~thLU 5deg)YAW - 45deg OUT-OF-PLANE (LEFT)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTIRATE 2MN BUS TIE (2) - ON (ver~fy)

PRIM GLY TO RAD - BYPASS (verlfy)CM RCS LOGIC - ON (venfy)SECS LOGIC (2) - on (up)SECS PYRO ARM - ARMCMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 ps~a

CM RCS LOGIC - OFFSECS PYRO ARM (2) - SAFEMonltor VMAB

If lt25 vdc go to EMERGPOWERDOWN pg E6-l

AUTO RCS SEL AC ROLL (4) - OFFAUTO RCS SEL CM 2(6)-OFFAUTO RCS SEL CM 1(6)-MNAYAW back to 0degPITCH TO HORIZ TRACK ATT

ROLL - 0deg (LIFT UP)PITCH - 400K Horiz Mark (317deg)YAW - 0deg

ATT DB - MAXMAN ATT PITCH - ACCEL CMDEMS DATA - Ver~fy

EMS FliNC - ENTRY (ver~fy)

EMS MODE - NORMALcb SPS PampY (4) - openMAINT HORIZ TRK

PRO (Act ENTRY DAP)

IMPACT LATLONGHDSDN (01deg01deg-00001)PRO

7 POSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axis beyond 45deg of Vel vector)

8 06 64

58middot00m(-0200)

9

05G tlme(+0 )

(--=---)

06 68

-27-

P63 - ENTRY INIT

GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PIJR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRmDHORIZ CKPltch error needle goes toward

zero approachlng OSG tlmeMAN ATT (PITCH) - RATE CMD

If CMC lS GOBMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS I

FLY BETA If CMC NO GO ilt

1 SC CaNT - SCS I

FLY EMS k

p64 - ENTRY POST 05G

RTOGO AT 05G AGREES HITH EMS-venfyHORIZ CK05G Lt - ON (EMS START)

No EMS START wlthln 3 sec ~ EMS MODE - BACKUP VHF RNG c

05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds Llft DN

NNVR Llft DNEMS GONO GO

G-V Plot wlthln IlmltsRng ctr dwn 60plusmn7 durlng 10 sec

perlodMonltor G-meter for

convergence wlth pad data (Do)(Vlt27K fps) Go to 13

-28-

P65 - ENTRY - UP CONT (Vgt27K fps)

10 F 16 69 BETA (01middot) _DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT lt~ SC CONT - SCS FLY EMS

PRO

11 06 68 BETAVIHDOT (OIdegfpsfps)(VltV1+500 fps amp RnOT Neg) Go To 13

P66 - ENTRY - BALLISTIC (D(DL)

12 06 22 DESIRED GMBL ANGLES RPYMoultor horlz +12middot of 317middot mark

P67 - ENTRY - FINAL PHASE (02G)

13 06 66 BETACRSRNG ERRDNRNG ERR(010 1um 1um)

KEY VERBRecord DNRNG ERR _KEY RLSEMoultor l~ft vector ou RSI amp FDAI

16 67 RTOGOLATLONG (Vrel=1000fps)(lumOldegOldeg)

SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOWNMonitor a1t~meter

Go To EARTHLANDING pg ---4L5 _

-29-

53 GampN HYBRID DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL tV1 V37E 30E

2 F 06 33 GETI(ACCEPT) PRO (hrm~n Olsec)(REJECT) LOAD DESIRED GETI

3 F 06 81 tVXYZ (LV) (lfps)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

4 F 06 42 HAHPtV (lnm lfps)Record tV

(ACCEPT) PRO(REJECT) Reselect P30 or P27 Load new paramo

5 F 16 45 MTFIMGA (marksm~n-secOlO)

MGA -00002 ~f k

k lMU not al~gned

SET DETPRO

6

7

8

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (Pull)PLSS 02 vlv - FILL02 8M SUPPLY vlv - OFFCAB PRESS REL vlv (2) - NORMcb ELS (2) - closecb SECS ARM (2) - closecb SECS LOGIC (2) - close (ver~fy)

AUTO RCS SEL CM (12) - MNA or ~ffiB

(hftoff conhg)ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM (AampB) - OFF

CMP to Couch

9

10

11

-30-

MNVR TO PAD BURN ATTLOAD DAPBMAG MODE (3) - RATE 2SC CONT - CMCAUTOATT DB - MINMAN ATT (3) - RATE CMD

v62E

v49E

12 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLES

PRO

13 F 50 18 REQ MNVR TO FDAI RPY ANGLES (01deg)(AUTO) PRO(MAN) SC CONT - SCS

BMAG MODE (3) - RATE 2MNVR To 15

14 06 18 AUTO MNVR TO FDAI RPY ANGLES (01deg)

15 F 50 18 REQ TRIM TO FDAI RPY ANGLES (01deg)(TRIM) Go to 13(ByPASS) ENTR

16

17

CHECK BORESIGHT amp SKT STARSOPT MODE - CMCOPT ZERO - OFF

v41 N91E

18 F 21 92 SHAFTTRUN (01deg 001deg)Load SXTS angles

19 41 OPTICS DRIVECheck SKT STAR

OPT ZERO - ZEROCheck BORESIGHT STAR (~f ava~l)

20 V25 N17E (01deg)Load Pad Data GMBL Angles

for CM BURN ATTATT SETtw - SET

to PAD DATA GMBL ANGLESfor CM BURN ATT

21

22

-31-

PHR REDUCTIONHGA PHR - OFFFC PUMPS (3) - OFFVerify s~ngle su~t compr oper loads

balancedFC 2 MN AampB - OFFS BD PiR AMP - LOWcb ECS RAD CONTHTR (2) - opencb HASTE H20URINE DUMP HTRS(2)- opencb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANMN BUS TIE (2) - ONTVC SERVO PHR 1 - AC1MNAGMBL MTR (4) - START

p41 - RCS THRUSTINGV37E 41E

23 F 50 18 REQ MNVR TO LCL HORIZ (HDS ON)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CMCAUTOPRO To 24

(gtfANDAP) BMAG MODE (3) - RATE 2SC CONT - CMCHOLD

V62EMNVR To 25

24 06 18 AUTO MNVR TO FDAI RPY

25 F 50 18 REQ TRIM TO LCL HORIZ (01deg)ALIGN SC ROLL

(AUTO TRIM) PRO To 24(BYPASS) ATT DB - MIN

RATE - LOHMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTlRATE 2

ENTR

550Om26 06 85

59middot2527

-32-

VGXYZ (1fps)RECHECK BORESIGHT STARTRANS CONIR PWR - on (up)EMS MODE - STBY (ver~fy)

EMS FliNC - bV SETVHF RNGSET (IV for SM BURN _EMS FliNC - bVS BD ANT - OMNI CSECS LOGIC (2) - ONMSFN conhrm Go for PYRO ARMSECS PYRO ARM (2) - ARMCM RCS LOGIC - ON (ver~fy)

DSKY BLANKS

593028 16 85 VG XYZ (AVE G ON) (lfps)

RHCs amp THC - ARMEDLIMIT CYCLE - OFFTAPE RCDR - CMD RESETHBREMS MODE - NORMAL

000029 F 16 85 REQ NULL VG XYZ (lfps)

BURN EMS bV CTR TO ZERORESET DET amp COUNT UP

If SM ONLY burn go to step 32THC - LOCKEDSC CaNT - SCSFREERATE - HIGHPRIM GLY To RAD - BYPASS (ver~fy)

MN BUS TIE (2) - ON (ver~fy)

CMSM SEP (2) - on (up)CSMLM FNL SEP (2) - on (up) (verify)CampW MODE - CMRCS TRNFR - CMCM RCS LOGIC - OFF

Momtor VM ABIf lt25 vdc go to EMERGPOWER DOWN Pg E6-l

V63E

If CMC NO GO FDAI SOURCE - ATT FDAI SEL - 1 or 2 ATT SET - GDC

SET

-33-

~Uili ATT PITCH - ACCEL CMDFDAI SCALE - 55MNVR TO CM BURN ATT (NULL ERR NEEDLES)

R 0degPY --00--

30

31

CM RCS BURNRHC III-ContJnuous PJtch DownRHC HZ-Module PJtch to null needlesBURN VGZ TO ZERO

If only 1 RHC Pulse + P=5deg from retro att MaJnta~n rates lt3degsec

BURN COMPLETION ATllV CTR= or DET= _

V8ZE

32 F 16 44 HAHPTFF (1nmffiJn-sec)Check HP-

If gt Pad data contJnue burnuntJ1 lt Pad

PRO

33 F 16 85 VGXYZ (Ups)Read VG resJduals to MSFN

(HYBRID) PRO to 34(SM ONLY BURN)

PROF 37 ODE

EI-1500 V37E 47EF 16 83 twx Y Z (Ups)

SC CONT - SCSFREEMAN ATT (PITCH) - RATE CMDRATE - HIGHPRIM GLY To RAD - BYPASS (verJfy)MN BUS TIE (2) - ON (verJfy)CMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verJfy)Campl MODE - CMRCS TRNFR - CMCM ReS LOGIC - OFFSECS PYRO ~I (2) - SAFE

-34-

PROMonitor VMAB

If lt25 vdc go to EMERGPOWER DOWN

34 F 37 OOEPCM BIT RATE - LOWATT DB - MAXEMS MODE - STBYEMS FUNC - OFF

Go To EARTH ORBIT ENTRY pg _--40-__

-36-

8 SPS THRUSTING PREPCYCLE CRYO FANSSPS GAGING - ACI (ver~fy)

PUG MODE - NORM (venfy)BMAG MODE (3) - RATE 2tv CG - CSMCMC MODE - FREEAUTO RCS SEL (16) - MNA or HNB

(hftoff conbg)SC CONT - CMCAUTO

9 MNVR TO PAD BURN ATTV62E

10 V49E

11 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLESPRO

12 F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) PRO(HAN) SC CONT - ses

MNVR to 14

06 18 AUTO MNVR TO FDAI RPY ANGLES13

14 F 50 18 REO TRIH TO FDAI RPY ANGLES(TRIM) Go to 12(BYPASS) ENTR

15 BORESIGHT STAR CHECK

16 V37E 40EOPT PWR - OFF

17 F 50 18 REQUEST MNVR TO FDAI RPY ANGLES (01deg)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CHCAUTOPRO to 18

(MANDAP) BMAG HODE (3) - RATE 2SC CONT - CMCHOLDMNVR to 19

(HANseS) se eONT - sesMNVR to 19

-35-

54 NORMAL DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL ~V

1 V37E 30E

2 F 06 33 GETI (hrm~nOlsec)

(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

3 F 06 81 ~VXYZ (LV)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

( lfps)

4 F 06 42 HAHP~V (1nmlfps)Record W

(ACCEPT) PRO -----(REJECT) Rese1ect P30 or P27 Load new pa~am

5 F 16 45 MTFIMGA (marksmln-secOldeg)MGA -00002 If ~ lMU not a1~gned

SET DETPRO

6

7

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY v1v - OFFCAB PRESS REL v1v (2) - NORMcb ELS (2) - close (verify)cb SECS ARM (2) - close (ver~fy)

cb SECS LOGIC (2) - close (verlfy)AUTO RCS SEL CM (12) - ~mA or MNB

(l~ftoff conf~g)

ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM AampB - off (ctr)

18

-37-

06 18 AUTO MNVR TO FDAI RPY ANGLES (01 0)

19 l 50 18 REOUEST TRIM MNVR TOALIGN SIC ROLLGDC ALIGN

FDAI RPY ANGLES(010

)

+54-00m(-06-00)

TIG-5mJn

5500m(-0500)

TVC CHECK amp PREPcb STAB CONT SYS (all) - closecb SPS (12) - closeATT DB - MINRATE - LOl~

LIMIT CYCLE - ONMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE 2ROT CONTR PWR DIRECT (2) - OFFSCS TVC (2) - RATE CMD

If SCS SCS TVC (2) - AUTO SC CONT - SCS ~

TVC GMBL DRIVE PampY - AUTOMN BUS TIE (2) - ONTVC SERVO PWR 1 - AC1MNA

2 - AC2MNBTRANS CONTR PWR - ONROT CONTR PWR NORMAL 2 - ACRHC 2 - ARMED

HORIZ CHK - HorJz on 12deg wJndmlmark (LJffiJt +3 0 PNGCS GONO GO)

If NO GO set tw 180 0 180deg0 0

Track horJz wJth 24deg wJndow markAt TIG-2 mJn Ahgn GDC

PRIMARY TVC CHECKGMBL MOT P1-Y1 -STARTON(LMP confJrm)

If SCS verJfy Thumbwheel TrJmTHC - CWVenfy NO MTVC

SEC TVC CHECKGHBL MOT P2-Y2 -STARTON(LMP confJrm)SET GPI TRIHVenfy MTVCTHC NEUTRALGPI returns to 00 (CMC) or trJm (SCS)ROT CONT Pl~ NORM 2 - ACDC

(TRIM) Go to step 17(BYPASS) BMAG MODE(3) - ATTIRATE2 (ver1fy)

ENTR

-38-

20 F SO 25 00204 GMBL TEST OPTION(ACCEPT) SC CONT - GMC (ver~fy)

PROMonitor GPI Response

0020-2000020-200Tr~m

TEST FAIL SC CONT - SCS SCS TVC (2) - AUTO

(REJECT) ENTR

21 06 40 TFIVG~VM (m~n-sec1fps)

PROG ALM - TIG s1~pped

V5N9E 01703

KEY RLSE To 21 ROT CONTR PWR DIRECT (2) - MNABSPS He v1vs (2) - AUTO (ver~fy)

LIMIT CYCLE - OFFFDAI SCALE - SOIScb SPS P2Y2 - open (for cr~t burn)

5800(-02 00)

5925(-0035)

59middot 30(-0030)

06 40

59XX(-OOXX)

AV THRUST A(B) - NORMALTHC - ARMEDRlIC (2) - ARMEDTAPE RCDR - GID RESETHBR

DSKY BLANKS

(AVE G ON)EMS MODE - NORMAL

TFIVG~VM (m~n-seclfps)

CHECK PIPA BIAS lt2fps for 5 sec

ULLAGE AS REQ

IF NO ULLAGE DIR ULLAGE PB - PUSH~

CONTROL ATT WRlIC MONITOR AVM (R3) COUNTING UP

5955(-0005)

F 99 40 ENG ON ENABLE REQUEST(AUTO IGN) PRO AT TFI gt0 sec(BYPASS IGN) ENTR to 24

22 0000 IGN

-39-

If SCS - THRUST ON PB - PUSH

06 40 TFCVG~VM (m~n-seclfpslfps)

~F 97 40 SPS Thrust fall ~

~(RESTART) PRO To IGN (RECYCLE) ENTR To TIG-05 sec

SPS THRUST LITE - ONMONITOR THRUSTING

Pc 95-105 pSlaEMS COUNTING DOWNSPS IN3 v1vs (4) - OPENSPS He v1vs tb (2) - graySPS FUELOXID PRESS - 175-195 pSlaPUGS - BALANCED

PROG ALARM V5N9E 01407 VG INCTHC - CW FLY MTVC

ECOEMER SPS CUTOFF J

AV THRUST (2) - OFF

23 F 16 40 TFC(STATIC)VG~VM (mln-seclfps)~V THRUST AB - OFF

SPS IN3 v1vs (4) - CLOSEDSPS He tb (2) - bp

cb SPS P2Y2 - closed (verlfy)TVC SERVO PHR - AC1MNA (venfy)TVC SERVO PWR 2 - OFF

PRO

24 F 16 85 VG XYZ(CM) CUps)NULL RESIDUALSRECORD ~V CTR amp RESIDUALS I1VCEMS FUNC - OFF VGXEMS MODE - STBY VGYBMAG MODE (3) - RATE 2ATT DB - MAX VGZTRANS CONT PHR - OFF

PRO

25 F 37 V82E

26 F 16 44 HAHPTFF (lnmm~n-sec)

R3-59B59 HP gt494 nmPRO

27 F 37 OOE

-40-

55 EARTH ORBIT ENTRY

1 Venfy CMSMR __

P_shyY_-

SEP ATT(180deg)

(0deg )

2

3

4

EMS INITIALIZATIONEMS FUNC - RNG SETSET RNG TO PAD DATA RNGEMS FUNC - VA SETSlew scroll to pad data VIOEMS FUNC - ENTRY

RSI ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on(up)GDC ALIGN PB - PUSH amp HOLDYAW tw - Pos1tion RSI thru 45deg amp

back to LIFl UPGDC ALIGN PB - RELEASEEMS ROLL - OFFAl1gn GDC to lMU

PWR REDUCT (Norm Deorb Only)HGA PWR - OFFFC PUMPS (3) - OFFVer1fy s1ngle suit compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - Lowcb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2)-openlOb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MAN

-41-

P61 - ENTRY PREP

5 V37E 61E05 09 01427 - ROLL REVERSED05 09 01426 - IMU UNSAT

6 F 06 61 IMPACT LAT LONG liDS UPDN (+-)(01 0

010

+00001)

PRO

PAD VALUESLATLON==G------liDS UP DN _

7 F 06 60 GMAXV400KGAMMA EIRecord

GMAXV400K----GAMMA EI _

PRO

8 F 06 63 RTOGO (1nm) PAD _VIa (fps) PADTFE (mln-sec) ----Compare wlth MSFN for PGNS GONO GONO COMM SET RTOGO amp VIO IN EMS amp

INITIALIZE(ACCEPT) PRO(RECALC) V32E to 8

-42-

P62 - CMSM SEP amp PRE-ENTRY MNVR

9 F 50 25 00041 REQUEST CMSM SEPSC CONT - SCSFREEYAW - 45deg out-of-plane (left for RCS

nght for SPS)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE2PRIM GLY to RAD - BYPASS (verlfy)SECS LOGIC (2) - on (up)MSFN conflrm GO for PYRO ARMSECS PYRO ARM - ARMMN BUS TIE (2) - ON (verlfy)CMSM SEF (2) - ONCSMLM FNl SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 pSlaCM RCS LOGIC - OFFSECS PYRO ARM - SAFEMonltor VMAB

If lt25vdc go to EMERG POWERDOWN Pg E6-1AUTO RCS SEL AlC ROLL (4) - OFFAUTO RCS SEL CM 2(6) - OFFAUTO RCS SEL CM 1(6) - MNA or MNBYAW back to 00

PITCH TO ENTRY ATTROLL 0deg (LIFT UP)PITCH - HORIZ on 317deg MARK (400K)YAW 00

ATT DB - MAXMAN ATT (PITCH) - ACCEL CMDEMS DATA - VerifyEMS FUNC - ENTRY (verlfy)EMS MODE - NORMALMAINTAIN HORIZ TRK

PRO (Act ENTRY DAP)

10 F 06 61 IMPACT LAT LONG HDSDN(010 010 -00001)

PRO

11 FOSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axlS beyond 45deg of Vel vector)

-43-

P63 - ENTRY INIT

12 06 64 GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PWR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRHORIZ CKP~tch error needle goes toward

zero approach~ng 05G t~me

MAN ATT (PITCH) - RATE CMDIf CMC ~s GO

BMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS FLY BETA If CMC NO GO ~

SC CONT - SCS~

FLY EMS RCS Deorh Roll HDS UPTRACK HORIZ w~th 29deg w~ndow mk

P64 - ENTRY POST 05G

13

05G t=elt+0___)

06 68

RTOGO AT 05G AGREES WITH EMS - venfyHORIZ CK05E Lt - on (EMS start)

No EMS start w~th~n 3 secsEMS MODE - BACKUP VHF RNG 05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds L~ft DN

NNVR L~ft DNEMS GONO GO

G-V Plot w~th~n llm~ts

Rng ctr dwn 60 + 7 durlng 10 sec per~od

Mon~tor G-meter forconvergence wlth pad data (Do)

(Vlt27K fps) Go To 17

-44-

P65 - ENTRY - UP CONT (Vgt27K fps)

14 F 16 69 BETA (01deg)DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT~

SC CONT - SCS FLY EMS

PRO

15 06 68 BElA VI HOOT (01deg fpsfps)(VltVL +500 fps amp RDOT Neg) Go To 17

p66 - ENTRY - BALLISTIC (DltDL)

16 06 22 DESIRED GMBL ANGLES RPY (01deg)Mon~tor hor~z +12deg of 317deg mark

P67 - ENTRY - FINAL PHASE (02G)

17 0666 BETACRSRNG ERRDNRNG ERR (Oldeglnmlnm)KEY VERBRecord DNRNG ERR _KEY RLSEL~m~t +100nm from PAD DRE

Mon~tor l~ft vector on RSI amp FDAIF 16 67 RTOGOLATLONG (Vre1=1000fps)

(lnm 010 01deg)SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOlfflMon~tor altimeter

Go To EARTHLANDING pg _I4L5__

-45-

56 EARTHLANDING

90K STEAM PRESS - PEGGED50K CABIN PRESS REL vIv (2) - BOOSTENTRY

SECS PYRO ARM (2) - ARM

40K(90K + 63s)

CM UNSTABLE RCS CMD - OFF ~ 40K APEX COVER JETT PG-PUSH DROGUE DEPLOY PG - PUSH (2 secafter apex cover Jett)

30K ELS LOGIC - ON (up)ELS - AUTO

24K RCS hsable (auto)(90K+92s) RCS CMD - OFF

Apex cover Jett (auto)APEX COVER JETT PB - PUSH

(WAIT 2 SECS)Drogue parachutes deployed (auto)

DROGUE DEPLOY PB - PUSH~

If Drogues FallELS - ~ ~Stablllze CM 5K MAIN DPLY PB - PUSHELS - AUTO

235K Cabln Pressure lncreaslng (Drogues + 50s)If not lncreaSlng by 17K CABIN PRESS REL vlv (RR) - DUMP

-46-

10K Maln parachutes deployedMAIN DEPLOY PB - PUSH (wlthln 1 sec)VHF ANT - RECYVHF AMA - SIMPLEXVHF BCN - ONCABIN PRESS REL v1v (2) - CLOSEDIRECT 02 vlv - OPENCM RCS LOGIC - on (up)CM PRPLNT - DUMP (burn audlb1e)Monltor CM ReS 1amp2 for He press decrease

NO BURN or PRESS DECREASE USE BOTH RHCs DO NOT FIRE PITCH JETS

CM PRPLNT-PURGE (to zero He press)CM RCS He DUMP PB - PUSH RHC (2) - 30 sees NO PITCH k

STRUT LOCKS (2) - UNLOCK

cb FLT amp PL BAT BUS ABampBAT C (3) - closecb FLT amp PLT MNA amp B (2) - opencb ECS RAD HTR OVLD (2) - opencb SPS PampY (4) - open

3K CABIN PRESS REL v1v (RH) - DUMP (after purgecompleted)

FLOOD Lts - POST LDGCM RCS PRPLNT (2) - OFFROT CONTR PWR DIRECT (2) - OFF

800 CAB PRESS RELF vlv - CLOSE (latch off)MN BUS TIE (2) - OFF

AFTER LANDINGcb MAIN REL PYRO (2) - closeMAIN RELEASE - on(up)

Go to POSTLANDING pg _47L-__

I

2

3

-47-

57 POSTLANDING

STABILIZATION VENTILATION COMMUNICATIONS

DIRECT 02 vlv - CLOSE

Stablllzation after landlngELS - AUTO (verlfy)cb MAIN REL PYRO (2) - close (venfy)MAIN RELEASE - on (up) (verlfy)S~CS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb BAT RLY BUS (2) - open

No contact w1th recovery forcesVHF AM AampB - off (ctr) ~

VHF AM Rev ONLY - A cb PL VENT - closecb FLOAT BAG (3) - closecb UPRIGHT SYS COMPRESS (2) - closeIf Stable II

FLOAT BAG(3)-FILL t1ll 2 m1n afterupr1ght then - OFF

VHF AM AlB amp BCN - OFF whlle lnvertedIf Stable I

After 10 M1n Coollng Per1odFLOAT BAG (3) - FILL 7 mln then OFF

Post Stab1lizat1on And Ventllat10nPL BCN LT - BCN LT LOWPL VENT vlv - UNLOCK (Pull)Remove PL VENT Exh CoverPL VENT - HIGH or LOWPL DYE MARKER - ON (swlmmer comm)Release foots traps and_restralntscb MNA BAT BUS A amp BAT C (2) - opencb MNB BAT BUS B amp BAT C (2) - opencb FLT amp PL BAT C - opencb PYRO A SEQ A - opencb PYRO B SEQ B - open

EACH HR - CHECK DC VOLTSgt 275 V If Notmiddot cb FLT amp PL-BAT BUS AampB (2) -open cb FLT amp PL BAT C (1) - open GO TO LOW POWER CHECKLIST

Unstow and lnstall PLV DISTRIB DUCTDeploy grappllng hook and 11ne 1f req

4

-48-

Post Landing Communlcatl0nsVHF ANT-RECY (venfy)VHF BCN - ON (verlfy)

If no contact ~lth recovery forcesperform VHF BEACON Check

MONITOR VHF BEACON transmlSSlonnth VHF AM B Rcvr andor Su)vlval

TransceiverkVHF Beacon not operatlng ~connect Surv~val TranscelVer to antcable behlnd VHF ant access pnland place radio ln BCN mode

LOW POHER CHECKLISTVHF BCN - OFFVHF AM (3) - RCVFLOOD Lts - OFFVHF AM AampB - off (ctr)VHF AM RCV ONLY - A (venfy)COUCH LIGHTS - OFFPOSTLANDING VENT SYS mlnlmlze useSURV RADIO - plug mto VHF BCN ANT cableconn behind VHF ant acess pnl amp turn radloon l-n BCN mode

EGRESS PROCEDURES

CMPCDRLMPCDR

CMPCDRCMP

LMPLl1PCDR

STABLE IDlsconnect Umblll-calsNeck darn onCenter couch - 270 0 positionArmrests stowedConnect raft to SIC l-f desl-red wlth

green lanyardConnect raft ~hl-te lanyards to SUltS amp

lnflate water wlngs when eXltl-ngHATCH PISTON PRESS vlv - PRESS (Outbd)Slde Hatch openedPL VENT - OFFcb Pnl 250 (all) - openEgress with 11feraftPut hardware klt outEgress

or CDIPALL

CMF

CDRCMF

CDR

LMF

CMFCMP LMFCMP

UlP

CDR

-49-

STABLE IIcb CREW STA AUDIO (3) - openD~sconnect umb~1~ca1s

Release foots trapsRelease restra~nt harnessCouch seat pans (3) - 170 0 pos1t10nArm rests stowedSurv1va1 k~ts removed from stowageConnect life raft ma~n1~ne to CDR or SicConnect f~rst wh~te lanyard from

11fe raft to suitConnect th~rd wh~te lanyard from

l~fe raft to SU1tConnect rucksacks together to yellow

lanyard on raft bagPRESSURE EQUALIZATION vlv - OPENRemove and stow fwd hatchEX1t feet f1rst w1th rucksacks when clear

of siC 1nflate water w1ngs and raftExit feet f1rst when clear of SiC

1nflate water w1ngsEX1t feet f1rst when clear of sic

1nflate water w1ngs

-50-

60 TLI ABORTS

TLI Aborts are conta~ned ~n the ESD s~nce the bulk of the funct~ons

concern entry preparat20ns and performance Th~s allows a s2nglesource of procedures for procedure rev2ew val~dat~on checkout andtra~n~ng These procedures ~ncorporate TLI preparat20ns as found ~n

reference 6 w~th the TLI Abort Procedures and these t~e 2nto normallunar return Entry Procedures found ~n sect20n 5 The guidel~nes

for th~s cont2ngency are spec2f2ed 2n reference 7

In2t2al preparat~ons for TLI pos2t20n the necessary system sW2tches2n add~t~on to perform~ng an EMS ~V test and a GDC al~gnment Afterthe DET ~s set for mon2tor2ng TB6 the CMP ~ncreases the 12ght levelof the LEB DSKY to max~mum and returns to the h2s couch Th2s 2Sdone so that the LEB DSKY can be observed ~n the event sunl~ght orreflect20ns wash out the ma2n d2splay panel DSKY dur2ng cr2t2calmaneuvers The crew then straps ~n and prepares for mon2tor~ng TB6as 2nd2cated by the SII SEP L~te The t2mes se~uence of procedures2S keyed on th~s d~splay and ~ncludes the DET START funct~on andSIVB IGNITION Dur2ng the burn the crew mon2tors the FDAIs foratt~tude excurs20ns and abnormal rates report~ng status checks toM~ss2on Control at d2screet t~mes dur2ng the maneuver Upon SIVBSHUTDOWN the eMP records the DSKY d~splayed performance parametersand awa2ts ground conf2rmat~on

The rat~onal for TLI aborts ~s descr~bed 2n reference 7 A summar2shyzat20n 2S extracted to prov2de background and gu2de12nes 2n th2sdocument The abort procedures cover aborts 10 m2nutes after conshyt2ngent SIVE shutdown and aborts 90 m2nutes after normal SIVE shutshydown t2me

The 10 m~nute TLI abort ~s des2gned to be used dur~ng TLI ~n theevent a spacecraft problem develops Wh2Ch can result 2n catastrophe2f ~mmed~ate act~on 2S not taken If the s~tuat20n perm~ts the crewshould always allow the SIVB to complete TLI at wh~ch t~me the groundand crew can perform a malfunct~on analys~s to determ~ne ~f an abort~s adv~sable If a fa~lure occurs that necess2tates the shutdown ofthe SIVB and the ~u~ck return of the crew to earth th~s abort ~s

des~gned to be as ~nsens~t~ve to execut~on errors as poss~ble andst21l be targeted to m2dcorr2dor The burn att~tude w~th the f~ed

hor~zon reference ~s a constant value for any shutdown t~me Theburn durat~on 2S a funct20n of shutdown t2me and 2S ava21able fromcrew charts S~nce the pr~mary purpose of th~s abort ~s to returnto earth as qU2ckly as poss2ble there are no restr2ct20ns as toland~ng locat~on However ~f the t~me to EI is greater than abouttwo hours a midcourse correct20n should be ant~c~pated

The 90 m2nute TLI abort 2S to be used 2f a cr2t2cal subsystem malshyfunct~on ~s determ2ned and the dec2s~on to abort ~s made after the

-51-

TLI cutoff and before TLI cutoff plus approxlmately 80 m1nutesTh1S allows suff1c1ent separatlon and procedural t1me to set upfor the SPS deorb1t burn performed at about TLI + 90 Note thatgenerally the deorb1t burns w1ll be performed a fe11 m1nutes beforeTLI + 90 accord1ng to crew charts shown In reference 8 The no-comm except10n requ1res that 90 m1nutes be the 1nput t1me of 19n1shytlon for P-37 (onboard return-to-earth abort program) so that onshyboard calculatlons can correspond w1th ground calculat10ns to computethe CM land1ng p01nt Th1S TLI abort lS des1gned so that returnfl1ght t1me does not exceed 18 hours and abort ~V does not exceed7000 fps ThlS abort can be performed uSlng chart ~Vs and attltudesand the earths hor1zon serves as a suff1c1ent reference The maneushyver lS targeted to ach1eve the mldcorr1dor entry target Ilne andtlmed to result 1n a deslgnated recovery area

It 1S ObV10US for abort deC1S1ons early 1n the TLI + 90 m1nute t1meshyframe that a GampN SPS burn should be performed In order to keep theTLI abort procedures cons1stent and w1th emphasls on slmpl1c1ty theprocedures here reflect a SCS SPS abort burn to cover the full abortdec1s1on t1meframe

A m1dcourse correct1on for corr1dor control after a TLI abort may bedeS1red 1f the SPS burn d1d not meet expectat1ons The TLIabortprocedures 1n th1S sect10n adapt to the normal lunar return tlmel1neand procedures pr10r to the f1nal MCC

-52-

61 TLI PREPARATION PROCEDURES

GET = 150

CRO AOS(___)

CRO LOS( )(22142)

5100

Don Helmets amp Gloves

XLUNAR - INJECT (verify)EDS PWR - on (venfy)EMS FUNC - OFF (verlfy)EMS MODE - STBYEMS FUNC - IW SETVHF RNGEMS MODE - NORMALSet ~V indo to +15868 fpsEMS FUMC - ~V Test

SPS THRUST Lt - onoff (10 sec)~V lnd stops at -01 to -415

EMS MODE - STBYEMS FUMC - ~V SETVHF RNGSet ~VC

EMS FUNC---~~V=----

GDC ALIGNFDAI Select - liZcb SECS LOGIC (Z) - close (verify)cb SECS ARM (Z) - closeSECS LOGIC (Z) - on (up)MSFN Conflrm GO for PYRO ARM (If pass)SECS PYRO ARM (Z) - on (up)TRANS CONTROL PWR - ONROT CONTR PWR NORMAL (Z) - ACDC(verlfy)ROT CONTR PWR DIRECT (Z) - MNAMNBLV INnGPI - SIISIVB (venfy)LV GUID - IU (venfy)cb DIRECT ULLAGE (Z) - closedSet EVENT TIMER to 5100Begin MONITOR For TB6

CMP to Couch

TB 6 - SII SEP Lt on (TIG-9 mln 38 sec)KEY V83E

SET ORDEALFDAI Z ORB RATE at 180 0 0SII SEP Lt out (38 sec later)Start DET COUNTING UPSC CaNT - SCS (verify)MONITOR LV TANK PRESS

~P lt 36 psid (OXID gt FUEL)~P lt Z6 psid (FUEL gt OXID)

EMERGENCY CSMLV SEP UP TLM CM - BLOCK (verify)UP TLM IU - BLOCK (venfy)

-53-

+45degPY))0middot sec PY

lOK nmltHAlt25K nm

Two phas~ng mnvrs two SPS mnvrs to circular~ze at 150 nmearth orb~t

CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ssion 4K nmltHAltlOK nm CSM amp1M - Two phasing mnvrs two SPS mnvrs to circularize at 150 nm earth orb~t CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ss~on

CSM amp 1M - Two phas~ng mnvrs APS burn todepletion th~rd phasing mnvrSPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn tosem~sync orb~t

25K nmltHAlt40K nm CSM amp 1M - Two phasmg mnvrs APS burn to depletion third phas~ng mnvr SPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn to sem~sync orbit HA)40K nm DPS ava~l - DPS LOll circularize with SPS

DPS not ava~l - Lunar flyby or CSM only to lunar orbit (if reqd gtV lt4000 fps)

V37E 47E (check b~as) Record -=--rshy(Limit 98 fpsmm)

( 1fps)tVXYZN62EVIHDOTHPAD (fpsfpslnm)MONITOR VI ( ) at ECO

SCS TVC SERVO PWR 1 - ACIMNA2 - OFF

TAPE RCDR - CMD RESETHBREMS MODE - NORMAL

SIr SEP Lt - ONTLI Inhib~t S~gnals w~11 not be honored after 5942

SIVB ULLAGE BeginsSII SEP Lt - off (TIG - 18 sec)SIVB FUEL LEADSIVB ULLAGE d~scont~nues

LV ENG I Lt - onSIVB IGNITION ( GETI)LV ENG I Lt - off - -shyMONITOR THRUST amp ATTITUDEMONITOR LV TANK PRESSSIVE ECO (Lt on) (BEGIN TB7)

EMER SIVE CUTOFF AT 6 SEC PAST BURN TIME IF VI ATTAINEDTHC CCW ampNEUTRAL IN 1 SEC or SIISIVB sW - LV STAGEPremature Shutdown HAlt4K nm CSM amp 1M -

5700

58205836

F 16 835800

F 16 62

5838594259525955595900000002SUNRISE(___)

HAW AOS(__=_) KEY VERB (freeze d~splay)

SIVB ATT HOLD 20 sec amp BEGIN VENTINGSIVB NNVR TO ORB RT (HDS DN) (3middot sec)

Record VI -c---HDOT _

HPAD _

KEY RLSEF 16 62

F 16 83

HAW LOS(__=-)

KEYmiddotRLSE~VXYZ (lfps)

Record ~VX---_

~vy

WZ--

AVC---_

TAPE RCDR - off (ctr)EMS MODE - STBYEMS FUNC - OFFSECS PYRO ARM (2) - SAFE

PRO

BURN STATUS REPORT

____--~TIG

BT------VGX____-R

-----P----_Y

REMARKS

_____VI

______--HDOT______--H______---AVC______---FUEL_______OXID

_______UNBAL

F 3708=00 OOEGOS AOS CMP TO LEB

(-=-=-)

0000

0003

0005

0014

0100

-55-

62 TLI 10 MIN ABORTSECS LOGIC (2) - on (up)SECS PYRO ARM (2) - ARM

TRANS CONTR - CGH (4 sec) amp +XDET RESET (verlfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS GMD-ON

TRANS GONTR - neutral then +X for10 sec

SIVBGPI s~ - GPIExcesslve rates 6V THRUST A - NORMAL SPS THRUST - DIRECT When rates damped 6V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

TRANS CONTR +X - OFFV37E OOE

PITGH UP to LOGAL VERT (+X axlSto~ard the earth)

RATE - LOWBMAG MODE (3) - ATTIRATE 2EDS PHR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SEGS ARM (2) - opencb EDS (3) - open

TRANS CONTR -X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (180deg)P (199deg)Y (0deg)

RETRO UPDATEGETI _

JV _VG

Jtb ---GET 400K _

05G _GET DROGUE _

ENTRY P _R _

Y_--

0945

-56-

ALIGN HORIZ ON RET +1 MKGMBL CHECK (T11lle Pentattlng)MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conflnn)cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FUMC - JV SETVHF RNGSET JV from chartE~S FUMC - JVEMS fODE - NOIDlAL

lV THRUST A - NORMALV37E 47E (THRUST fONITOR)

F 16 83 lVXYZ (1 fps)

0950

1000

NOTE For aborts durlng 1st mln of TLIKEY V82E F 16 44 (HaHpTff)Burn untll Hp lt 19NM

TRANS CONTR +X

THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN JV reqdJV THRUST (2) - OFFReport cutoff

cb SPS P2 Y2- closeGfBL MTRS (4) - OFF (LMP Confinn)TRANS CONT PWR - OFFTVC SERVO PWR (2) - OFFMN BUS TIE (2) - OFFcb SPS P1amp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREIf est time to EIltOl5500 omlt fCC andenter the SUPERCIRC CKLIST as early as pos-slb1e Pg ~2~3~ __If est time to EI)Ol5500 anticlpate afCC Enter the ENTRY PREP CKLIST at step 9pg 18

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

-2tl C

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-i- rtREQUIRED PITCH GIMBAL ANG LETO OBTAIN HOR-IZON AT 317

DEGREES IN wiiiiDOW

260

z~I- ~ i5 24000

1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

-I

-1-

NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

I LU HD~-

LUHD

lt0 120UJ0

~

80 HOLD PRESENT TRIMgt LU HD013

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TOP OF WINDOWa 40to

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80 TTOM OF WINDOWi= 0

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HOLO PRESENT TRIlJCl

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~~H~-160 q - P63 LIMITI- NOrE-VALIO ONLY FO~t~--

LUNAR RETURN VELOCITY

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TIME TO 400K FT ALTITUDE-MIN

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-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 16: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

-13-

40 EARTH ORBITAL DEORBIT AND ENTRY TECHNIQUES

As outl~ned ~n reference 5 a nom~nal PGNCS entry from earth orb~t ~s

based on a preparat~on t~me of 2 hours and 40 m~nutes ~nclud~ng 2n~ght passes Th~s t~me ~ncludes approx~mately 20 minutes before thef~rst n~ght pass after the CMC update and PAD data have been rece2vedTh~s t~e also 2ncludes approx2mately 20 m2nutes after the secondn~ght pass to allow suffic~ent t2me to prepare for retrof2re after theIMU f2ne a12gnment It has been determ2ned coarse a12gnment accuracy~s adequate for retrof~re and entry and undoubtedly other funct20nscould be om2tted depend2ng on the c2rcumstances for the dec2s20n toreenter Descr2bed here2n are the nom2nal earth oro2tal entry proshycedures w2th pert2nent comments on system va12dat20n for real timeacceptance dec~s20ns

After the entry dec~s~on is made the crew transfers the PGNCS fromthe standby to the operate mode and rece~ves a CMe update w~th P27Next the maneuver PAD update ~s v02ced up and the 2n~t~al entry mode~s determ~ned During the ~n~tial n~ght pass the IMU or2entat~on ~s

estab12shed uS2ng P51 star s~ght2ngs to obta2n a REFSMMAT The preshyferred or~entat~on opt20n ~n P52 2S then selected to coarse a12gn theIMU uS2ng the des2red entry REFSMMAT determ2ned by MGG-H The GOO ~s

now al~gned to the IMU 2n preparat~on for an IMUSes dr~ft check Ifthe GOO ~nd~cates the ses dr2ft rate exceeds 10 degrees per hour ~n

any ax~s the check ~s repeated on the other BMAGs to estaol~sh if theGOO or Just the single set 2S unusuable Var20us sytem checks as 12sted2n sect20n 51 are performed as necessary cons2stent w2th the t2me12ned2ctates of the maJor act2v2t2es Included 2n these checks are the EMSself-tests and the dV counter test The latter requ2res the spacecraftbe placed ~n dr2ft2ng fl2ght w~th the funct20n sW2tch 2n the dV pos2t~on

If the counter reg2sters a change of more than 25 feet per second w2th2n100 seconds the scroll and counter are unre12able for mon2tor2ng thedeorb2t burn and entry rang2ng If the EMS self-test fails and t2medoes not allow further analysis a 5555 ERE entry 1S planned as thePGNGS backup entry mode After complet2on of these checks the entryPAD lS prov1ded by MeG-H The crew then selects the external dVprogram P30 and the appropr2ate deorb1t tbrust1ng program p40 or P41Dur2ng th2s per2od wh2ch 2ncludes the f1nal n2ght pass P52 may beselected to ver2fy the IMU a12gnment Since the retro att2tude hasbeen computed so that a w2ndow mark c01nc2des w2th the hor2zon atGETI th2s serves as the conclus2ve check on the PGNCS At 5 m2nutesbefore retrofire the att2tude check 1S made by ver1fY2ng that the 12degree scr~be 12ne ~s w2th2n 3 degrees of the hor2zon If not thePGNeS has fa2led and the ses 2S used for att2tude reference and the

V counter for burn durat~on control S2nce the ses att~tude wasa12gned to the IMU a real~gnment ~s necessary This ~s accompl~shed

by manually maneuver2ng the spacecraft to ma~nta1n the 24 degree wlodowmark on the hor2zon and releas1ng the GOO a12gn button at TIG - 2 m2nutes

-14-

Upon complet~on of the burn the tN res~duals are burned to W~th~n

02 feet per second If the PGNCS ~V counter or est~mated burnduration are ~n d~sagreement ~t must be estab1~shed whether suff~shy

c~ent veloc~ty has been suppl~ed to put the land~ng po~nt in thefootpr~nt The PGNCS data w~ll be used ~f ~t ~s conf~rmed by oneother source if not the ~V counter w~11 be used ~f ~t ~s conf~rmed

by the burn durat~on t~me If add~tional ~V ~s necessary the data~s ava~lable to the crew on an onboard chart found ~n Sect~on 80

Post burn entry preparat~on requ~res EMS ~n~t~al~zation RSI al~gnshy

ment and pre-separat~on funct~ons The crew then selects the ~n~t~al

entry program P61 and records the d~sp1ays as a check aga~nst PADdata Upon complet~on of these checks P62 ~s entered The crewmanually or~ents the spacecraft to the separat~on attitude and yaws450 to ~nsure aga~nst possible CM 8M recontact After separat~on

the spacecraft ~s maneuvered to the reentry tr~m att~tude wh~ch

places the hor~zon on the 3170 w~ndow mark at EI Shortly thereshyafter ~n P62 the entry DAP is act~vated and P63 in~t~ated Dur~ng

th~s t~e MCC-H has computed a postburn update and ~t ~s vo~ced tothe crew ~f d~fferent from preburn values The EMS scroll and rangecounter w~ll be adJusted accord~ngly ~f t~me perm~ts A f~nal PGNCScheck pr~or to 05g may be mon~tored at th~s t~e w~th the CMC modein free and the manual att~tude p~tch ~n acceleration command wh~le

the hor~zon reference ~s held the p~tch error needle w~ll decreaseto zero as EI ~s reached At RET 005g the EMS mode sw~tch ~s

turned to manual the entry 005-g sw~tch and EMS roll sw~tch areturned on and the spacecraft control sw~tched to CMC to beg~n DAPcontrol At the PGNCS 005-g ~ndicatwn the program change fromP63 to P64 ~s mon~tored and the t~e vo~ce recorded At th~s t~me

the EMS range counter check ~s made dur~ng the 10 second per~od

follow~ng EMS 005g Dur~ng th~s per~od the counter should countdown 40 + 10 naut~cal m~les At PGNCS 02-g ~nd~cation the changefrom P64-to P67 ~s monitored and the ~splay may be held by key~ngVERB ~n order to record the init~al downrange error d~splay andcompare ~t to the PAD value The PGNCS has fa~led ~f the two do notagree w~th~n + 100 naut~cal m~les In the event P67 has not appearedwhen both the-g-meter and the scroll ~nd~cate greater than 05g thePGNCS has sim~lar~ly fa~led In e~ther fa~lure the SCS is used foratt~tude reference w~th an EMS entry If the checks agree the crewrema~ns w~th automat~c DAP for the rema~nder of the entry

The entry phase ~s essentially over when the relat~ve velocity ofthe spacecraft decreases to less than 1000 feet per second Th~s

~s ~nd~cated ~n P67 when RTGO lat~tude and long~tude are d~splayed

S~nce very l~ttle rang~ng capab~l~ty exists after th~s pOint thespacecraft is or~ented either full l~ft up or down depending onRTGO negat~ve or pos~t~ve and the crew prepares for the earth land~ng

phase

-15-

41 TYP~cal Retrof~re and Entry Sequence of Events

Dec~s~on to reenter

P27 (CMC update)

Retrof~re PAD update

Entry mode dec~s~on

P51 (IMU or~entat~on determlnatlon) durlng f~rst dark per~od

P52 (IMU coarse allgnment)

EMS checks

Entry PAD update

P30 (external AV)

p40 (SPS thrust)

P52 (IMU f~ne al~gnment) durlng second dark per~od

p40 (SPS thrust)

Ign~t~on att~tude check

Retroflre

P61

P62

CMSM separat~on

P63

Postburn PAD update

Entry attltude check

p64 (beg~n DAP control at O05g)

P67 (PGNCS gono go check at O2g)

42

Retrof~re

and

En

try

Alt

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Sys

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-17-

5 0 DETAILED ENTRY PROCEDURES

In order to comblne slmilar procedures that are common to lunar returnentrles and earth orblt entrles the followlng procedures are dlvldedlnto categorles that allow a mlnlmum of dupllClty ThlS provldes asmaller tralnlng package and more closely resembles the onboard crewcheckllst when comparlson lS necessary

51 Entry Preparatlons for Superclucular and Earth Orbltal Entrles

1~e entry preparatlons are comblned In these procedures andsteps pecullar to elther superclrcular or earth orbltal entrlesare labeled accordlngly The tlme llstlngs In thlS sectlon areappllcable to only superclrcular entries Slnce the earth orbltalentry tlmellne lS a functlon of several varlables as descrlbedIn sectlon 40 and reference 5

-18-51 (Contlnued)

VEHICLE PREPARATION

l-

2

3

4

5

6 -0600h

7 -0535h

8

9

10 -0430h

INITIAL STOWAGE COMPLETED

CMC amp ISS START UP

SCS POWER UP

p51 - IMU ORIENTATION

LOAD DAPV48E 11102 01111 PRO ERO PRO

LAST MCC DECISION

NO COMM - P52 amp NAV SIGHTINGSNOMINAL - P2337 ONBOARD COMPARISON

DON MAE WESTS amp FOOT RESTRAINTS

VHF AM A - SIMPLEX

P 27 (SV REFSMMAT) MNVRamp ENTRY pAD UPDATES

11 -0415h P52 - IMU REALIGN(___) (OPTION 1)

12 P37 (NO COMM ONLY)

13

14

ECS CKS02 SUPPLY REFILLECS Monitor CkEVAP H20 CONT (2) vlvs - AUTOSUIT HEAT EXCH SEC GLY - FLOW

EPS CKS 1 3 4 (5 If reqd)

15 SPS CK (If req d)

16

17

18

RCS CKSSM RCS MOUlt CkCM RCS MOUlt Ck

CampW SYS CK

CMC SELF CK

19

20 -0345h

-03l5h-0300h

21

22

22A

-19-

DSKY COND LT TEST

MIDCOURSE MANEUVERP30 - EXT rVP404l - SPSRCS THRUSTINGMIDCOURSE (17) BURN

NO COMM NAV SIGHTINGS

ffiVR TO ENTRY ATT (Superc1rc only)V62E

V49E

22B F 06 22 DESIRED FINAL GMBL ANGLESLOAD ENTRY ATT PAD ANGLESPRO

22C F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) SC CONT - CMC

BMAG MODE (3) - RATE 2CMC MODE - AUTO

PRO(~N) SC CONT - SCS

MNVR to 22E

22D 06 18 AUTO MNVR TO FDAI RPY ANGLES

22E F 50 18 REQUEST TRIM(TRIM) Go to 22C(BYPASS) ENTR

23 -200hr BORESIGHT amp SXT STAR CHECKOPT MODE - CMCOPT ZERO - OFF

V41 N91E

F 21 92 SHAFT TRUNLoad SXTS angles

41 OPTICS DRIVE

CHECK SXT STAROPT ZERO - ZERO

CHECK BORESIGHT STAR (If ava11)

24 -0135h

25(___)

26

27 -0115h

-20-

P52 - lMU REALIGNRecord gyro torqu~ng anglesRp~----

YIf-7gt-Lno--re-c-ycle PS2If conflrmed use SCS for EMS entry

GDC ALIGNIf drlft gtLOohr change ratesource

FINAL STOWAGEOPTICS (except for hybrid)ORDEALGLY TO RAD SEC - BYPASS (verlfy)CooL pnl lnstalledY-Y struts (2) extendedStow Data Box R-12

EMS CHECKEMS FUNC - OFFcb EMS (2) - closeEMS MODE - STBYEMS FUNC - EMS TEST 1 (walt 5 sec)EMS MODE - NORMAL (walt 10 sec)

Check ind lts - offRANGE lnd - 00Slew halr1ine over notch

In self-test patternEMS FUNC - EMS TEST 2 (walt 10 sec)

05G It - on (all others out)EMS FUNC - EMS TEST 3

05G It - onRSI Lower It - on (10 sec Qater)Set RANGE counter to 58 nm+OO

EMS FUNC - EMS TEST 405G It - on (all others out)G-V trace w~thin pattern to lwr rt

corner 9GRANGE lnd counts down to 0+02

EMS FUNC - EMS TEST 505G It - onRSI upper lt - on (10 sec later)RANGE md - 00SCrlbe traces vertlcal llne 9g to

022+01ALIGN SCROLL TO ENTRY PATTERN (on

37K ft sec hne)EMS FUNC - RNG SET

G-V scroll assy traces vert llne022g to 0+01

EMS MODE - STBY

28

29

30 -OllOh

-21-

~V TEST (Deorb~t only)EMS FUNC - ~V SETVHF RNGSET ~V ~nd to 15868 fpsEMS MODE - NORMALEMS FUNC - ~V TEST

SPS THRUST LT - onoff (10 sec)~V ~nd stops at -01 to -415

EMS MODE - STBY

PRIMARY WATER EVAP ACTIVATIONGLY EVAP H20 FLOW - AUTOGLY EVAP STH PRESS - AUTOPRI ECS GLY PUMP - ACI

CM RCS PREHEATNote If sys test mtr 5cd6abcd

all read 39 vdc (28degF) or moreom~t preheat

cb RCS LOGIC (2) - closeCM RCS LOGIC - ONUP T1M CM - BLOCK (ver~fy)

cb CM RCS HTRS (2) - closeCM RCS HTRS - ON (LMP Conf~rm)

(20 mlU or III lowest rdg lS39 vdc) (Moultor Maufpress for press drop)

31 (___) FINAL GDC DRIFT CK (If req I d)If drlft gtlOohr Suspect GDC Do not

use RSI amp FDAI 2

32 -OO5Om

33

34

35

TERM CM RCS PREHEATUP TLM CM - BLOCK (venfy)CM RCS HTRS - OFFCM RCS LOGIC - OFF

SYSTEMS TEST PANEL CONFIGURATIONSYS TEST METER - 4BRNDZ XPNDR - OPERATECM RCS HTRS - OFFWASTE H20 DUMP - OFFURINE DUMP - OFF

LEB LIGHTING - OFF

SEC WATER EVAP ACTIVATIONGLY To RAD SEC vlv - BYPASSSEC COOL EVAP - EVAPSEC COOL PUMP - AC2

36

37

38 -OO45m

-22-

PYRO BATT CKcb PYRO A SEQ A - close (ver~fy)

cb PRYO B SEQ B - close (verify)DC IND - PYRO BAT A(B)

~If PYRO BAT A(B) lt 35 vdc cb PYRO A(B) seq A(B) - open~

PYRO A(B)BAT BUS A(B)TO PYRO~MN BUS TIE - close

cb MNA BAT C - closecb MNB BAT C - closeDC IND - MNBPNL 8 - All cbs closed except

PL VENT - open (ver~fy)

FLOAT BAG (3) - open (ver~fy)

DOCKING PROBE (2) - open (verlfy)EDS BAT (3) - open (ver~fy)

CM ReS HTRS (2) - open

CM RCS ACTIVATIONcb SECS ARM (2) - close (verlfy)cb SECS LOGIC (2) - close (verlfy)SECS LOGIC (2) - ONMSFN conflrm GO for PYRO ARM(~f poss)SECS PYRO ARM (2) - ARMCM RCS PRPLNT 1amp2 - ONCM RCS PRESS - ONRCS Ind sw - eMl then 2

He PRESS 3700-4400 pSlaMANF PRESS 287-302 pSla

SECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFF

P27 amp ENTRY PAD UPDATEGo To Entry Checkllst

Superclrc - pg ~2~3 _Hybnd - pg -----2~9L-__Normal Deorblt - pg __3L5L- _

-23-

52 SUPERCIRCULAR ENTRY

1 SET DET (up to ET)

2

3

4

5

3000(-30-00)

EMS INITIALIZATIONSET RNG TO PAD DATA RNGEMS FUNC - Vo SETSlew Scroll to Pad Data VIOEMS FUNC - ENTRY

RS I ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on (up)GDC ALIGN PB - PUSH amp HOLDYAW Tw - Pos~t~on RSI thru

45deg amp back to LIFT UPGDC ALIGN PB - ReleaseEMS ROLL - OFFA1~gn CDC to lMU

CM RCS RING A CKRCS TRNFR - CMcb CM RCS LOGIC MNB - openAUTO RCS SEL MNB (6) - OFFSC CONT - SCSTest R~ng A ThrustersSC CONT - CMCRCS TRNFR - SMAUTO RCS SEL (12) - MNAMNB

(hftoff conflg)cb CM RCS LOGIC MNB - close

OPTICS PWR - OFFCMP to COUCH

MN BUS TIE (2) - ONTAPE RCDR - REWIND

6 35middot0Om(-25middot 00)

-24-

SEPARATION CK LISTTVC SERVO PWR 1 - AClMNAcb ELS (2) - close (ver1fy)PRIM GLY TO RAn - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY vlv - OFFCAB PRESS REL vlv (2) - NORMGMBL MTRS (4) - STARTABORT SYS PRPLNT - RCS CMD (venfy)SM RCS PRIM PRPLNT (4) - ONVHF 11M (AampB) - OFFHI GAIN ANT PWR - OFFFC PUMPS (3) - OFFVer1fy s1ugle SU1t compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - 10101cb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2) - opencb HTRS OVLD (2) - openPOT H20 RTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANSEC COOL EVAP - RESETSEC COOL PUMP - off (etr)

MtiVR TO CMSM SEP P R ATTSC CONT - SCSCMC MODE - FREEMNVR TO PAD ATTR (0deg)PY----W)

-25-

SUPERCIRCULAR ENTRY (Cont~nued)

1

4100m(-1900)

P61 - ENTRY PREP

V37E 61E

k 05 09 01427 - ROLL REVERSED 05 09 01426 - IMU UNSAT ~

2 F 06 61 IMPACT LAT LONG HDS UPDN (+-)PRO (010

fps +00001)

3 F 06 60 GMAXVPREDGAMMA EIRecord

GMAXV400K----

GAMMA EI _PRO

(01deg fpsOldeg)

4 F 06 63 RTOGO (lnm) PAD _VIO (fps) PAD _TFE(m~n-sec)

Compare w~th ~M~SFN==C~f~o-r~P~GNS GONO GOIf NO COMM Set RTOGO amp VIO In EMS

amp lnltla11ze(ACCEPT) PRO(RECALC) V32E To 4

5 F 50 25

4300m

(-1700)

45 oOm(-1500)

500Om(-1000)

6 F 06 61

-26-

P62 - CMSM SEP amp PRE-ENTRY MNVRCAUTION Call No EXT Verbs In P62

00041 REQUEST CMSM SEPSC CONT - SCSFREE

COMPARE PITCH ATT WITH PAD DATA ---0=-

(W~thLU 5deg)YAW - 45deg OUT-OF-PLANE (LEFT)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTIRATE 2MN BUS TIE (2) - ON (ver~fy)

PRIM GLY TO RAD - BYPASS (verlfy)CM RCS LOGIC - ON (venfy)SECS LOGIC (2) - on (up)SECS PYRO ARM - ARMCMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 ps~a

CM RCS LOGIC - OFFSECS PYRO ARM (2) - SAFEMonltor VMAB

If lt25 vdc go to EMERGPOWERDOWN pg E6-l

AUTO RCS SEL AC ROLL (4) - OFFAUTO RCS SEL CM 2(6)-OFFAUTO RCS SEL CM 1(6)-MNAYAW back to 0degPITCH TO HORIZ TRACK ATT

ROLL - 0deg (LIFT UP)PITCH - 400K Horiz Mark (317deg)YAW - 0deg

ATT DB - MAXMAN ATT PITCH - ACCEL CMDEMS DATA - Ver~fy

EMS FliNC - ENTRY (ver~fy)

EMS MODE - NORMALcb SPS PampY (4) - openMAINT HORIZ TRK

PRO (Act ENTRY DAP)

IMPACT LATLONGHDSDN (01deg01deg-00001)PRO

7 POSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axis beyond 45deg of Vel vector)

8 06 64

58middot00m(-0200)

9

05G tlme(+0 )

(--=---)

06 68

-27-

P63 - ENTRY INIT

GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PIJR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRmDHORIZ CKPltch error needle goes toward

zero approachlng OSG tlmeMAN ATT (PITCH) - RATE CMD

If CMC lS GOBMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS I

FLY BETA If CMC NO GO ilt

1 SC CaNT - SCS I

FLY EMS k

p64 - ENTRY POST 05G

RTOGO AT 05G AGREES HITH EMS-venfyHORIZ CK05G Lt - ON (EMS START)

No EMS START wlthln 3 sec ~ EMS MODE - BACKUP VHF RNG c

05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds Llft DN

NNVR Llft DNEMS GONO GO

G-V Plot wlthln IlmltsRng ctr dwn 60plusmn7 durlng 10 sec

perlodMonltor G-meter for

convergence wlth pad data (Do)(Vlt27K fps) Go to 13

-28-

P65 - ENTRY - UP CONT (Vgt27K fps)

10 F 16 69 BETA (01middot) _DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT lt~ SC CONT - SCS FLY EMS

PRO

11 06 68 BETAVIHDOT (OIdegfpsfps)(VltV1+500 fps amp RnOT Neg) Go To 13

P66 - ENTRY - BALLISTIC (D(DL)

12 06 22 DESIRED GMBL ANGLES RPYMoultor horlz +12middot of 317middot mark

P67 - ENTRY - FINAL PHASE (02G)

13 06 66 BETACRSRNG ERRDNRNG ERR(010 1um 1um)

KEY VERBRecord DNRNG ERR _KEY RLSEMoultor l~ft vector ou RSI amp FDAI

16 67 RTOGOLATLONG (Vrel=1000fps)(lumOldegOldeg)

SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOWNMonitor a1t~meter

Go To EARTHLANDING pg ---4L5 _

-29-

53 GampN HYBRID DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL tV1 V37E 30E

2 F 06 33 GETI(ACCEPT) PRO (hrm~n Olsec)(REJECT) LOAD DESIRED GETI

3 F 06 81 tVXYZ (LV) (lfps)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

4 F 06 42 HAHPtV (lnm lfps)Record tV

(ACCEPT) PRO(REJECT) Reselect P30 or P27 Load new paramo

5 F 16 45 MTFIMGA (marksm~n-secOlO)

MGA -00002 ~f k

k lMU not al~gned

SET DETPRO

6

7

8

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (Pull)PLSS 02 vlv - FILL02 8M SUPPLY vlv - OFFCAB PRESS REL vlv (2) - NORMcb ELS (2) - closecb SECS ARM (2) - closecb SECS LOGIC (2) - close (ver~fy)

AUTO RCS SEL CM (12) - MNA or ~ffiB

(hftoff conhg)ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM (AampB) - OFF

CMP to Couch

9

10

11

-30-

MNVR TO PAD BURN ATTLOAD DAPBMAG MODE (3) - RATE 2SC CONT - CMCAUTOATT DB - MINMAN ATT (3) - RATE CMD

v62E

v49E

12 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLES

PRO

13 F 50 18 REQ MNVR TO FDAI RPY ANGLES (01deg)(AUTO) PRO(MAN) SC CONT - SCS

BMAG MODE (3) - RATE 2MNVR To 15

14 06 18 AUTO MNVR TO FDAI RPY ANGLES (01deg)

15 F 50 18 REQ TRIM TO FDAI RPY ANGLES (01deg)(TRIM) Go to 13(ByPASS) ENTR

16

17

CHECK BORESIGHT amp SKT STARSOPT MODE - CMCOPT ZERO - OFF

v41 N91E

18 F 21 92 SHAFTTRUN (01deg 001deg)Load SXTS angles

19 41 OPTICS DRIVECheck SKT STAR

OPT ZERO - ZEROCheck BORESIGHT STAR (~f ava~l)

20 V25 N17E (01deg)Load Pad Data GMBL Angles

for CM BURN ATTATT SETtw - SET

to PAD DATA GMBL ANGLESfor CM BURN ATT

21

22

-31-

PHR REDUCTIONHGA PHR - OFFFC PUMPS (3) - OFFVerify s~ngle su~t compr oper loads

balancedFC 2 MN AampB - OFFS BD PiR AMP - LOWcb ECS RAD CONTHTR (2) - opencb HASTE H20URINE DUMP HTRS(2)- opencb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANMN BUS TIE (2) - ONTVC SERVO PHR 1 - AC1MNAGMBL MTR (4) - START

p41 - RCS THRUSTINGV37E 41E

23 F 50 18 REQ MNVR TO LCL HORIZ (HDS ON)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CMCAUTOPRO To 24

(gtfANDAP) BMAG MODE (3) - RATE 2SC CONT - CMCHOLD

V62EMNVR To 25

24 06 18 AUTO MNVR TO FDAI RPY

25 F 50 18 REQ TRIM TO LCL HORIZ (01deg)ALIGN SC ROLL

(AUTO TRIM) PRO To 24(BYPASS) ATT DB - MIN

RATE - LOHMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTlRATE 2

ENTR

550Om26 06 85

59middot2527

-32-

VGXYZ (1fps)RECHECK BORESIGHT STARTRANS CONIR PWR - on (up)EMS MODE - STBY (ver~fy)

EMS FliNC - bV SETVHF RNGSET (IV for SM BURN _EMS FliNC - bVS BD ANT - OMNI CSECS LOGIC (2) - ONMSFN conhrm Go for PYRO ARMSECS PYRO ARM (2) - ARMCM RCS LOGIC - ON (ver~fy)

DSKY BLANKS

593028 16 85 VG XYZ (AVE G ON) (lfps)

RHCs amp THC - ARMEDLIMIT CYCLE - OFFTAPE RCDR - CMD RESETHBREMS MODE - NORMAL

000029 F 16 85 REQ NULL VG XYZ (lfps)

BURN EMS bV CTR TO ZERORESET DET amp COUNT UP

If SM ONLY burn go to step 32THC - LOCKEDSC CaNT - SCSFREERATE - HIGHPRIM GLY To RAD - BYPASS (ver~fy)

MN BUS TIE (2) - ON (ver~fy)

CMSM SEP (2) - on (up)CSMLM FNL SEP (2) - on (up) (verify)CampW MODE - CMRCS TRNFR - CMCM RCS LOGIC - OFF

Momtor VM ABIf lt25 vdc go to EMERGPOWER DOWN Pg E6-l

V63E

If CMC NO GO FDAI SOURCE - ATT FDAI SEL - 1 or 2 ATT SET - GDC

SET

-33-

~Uili ATT PITCH - ACCEL CMDFDAI SCALE - 55MNVR TO CM BURN ATT (NULL ERR NEEDLES)

R 0degPY --00--

30

31

CM RCS BURNRHC III-ContJnuous PJtch DownRHC HZ-Module PJtch to null needlesBURN VGZ TO ZERO

If only 1 RHC Pulse + P=5deg from retro att MaJnta~n rates lt3degsec

BURN COMPLETION ATllV CTR= or DET= _

V8ZE

32 F 16 44 HAHPTFF (1nmffiJn-sec)Check HP-

If gt Pad data contJnue burnuntJ1 lt Pad

PRO

33 F 16 85 VGXYZ (Ups)Read VG resJduals to MSFN

(HYBRID) PRO to 34(SM ONLY BURN)

PROF 37 ODE

EI-1500 V37E 47EF 16 83 twx Y Z (Ups)

SC CONT - SCSFREEMAN ATT (PITCH) - RATE CMDRATE - HIGHPRIM GLY To RAD - BYPASS (verJfy)MN BUS TIE (2) - ON (verJfy)CMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verJfy)Campl MODE - CMRCS TRNFR - CMCM ReS LOGIC - OFFSECS PYRO ~I (2) - SAFE

-34-

PROMonitor VMAB

If lt25 vdc go to EMERGPOWER DOWN

34 F 37 OOEPCM BIT RATE - LOWATT DB - MAXEMS MODE - STBYEMS FUNC - OFF

Go To EARTH ORBIT ENTRY pg _--40-__

-36-

8 SPS THRUSTING PREPCYCLE CRYO FANSSPS GAGING - ACI (ver~fy)

PUG MODE - NORM (venfy)BMAG MODE (3) - RATE 2tv CG - CSMCMC MODE - FREEAUTO RCS SEL (16) - MNA or HNB

(hftoff conbg)SC CONT - CMCAUTO

9 MNVR TO PAD BURN ATTV62E

10 V49E

11 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLESPRO

12 F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) PRO(HAN) SC CONT - ses

MNVR to 14

06 18 AUTO MNVR TO FDAI RPY ANGLES13

14 F 50 18 REO TRIH TO FDAI RPY ANGLES(TRIM) Go to 12(BYPASS) ENTR

15 BORESIGHT STAR CHECK

16 V37E 40EOPT PWR - OFF

17 F 50 18 REQUEST MNVR TO FDAI RPY ANGLES (01deg)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CHCAUTOPRO to 18

(MANDAP) BMAG HODE (3) - RATE 2SC CONT - CMCHOLDMNVR to 19

(HANseS) se eONT - sesMNVR to 19

-35-

54 NORMAL DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL ~V

1 V37E 30E

2 F 06 33 GETI (hrm~nOlsec)

(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

3 F 06 81 ~VXYZ (LV)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

( lfps)

4 F 06 42 HAHP~V (1nmlfps)Record W

(ACCEPT) PRO -----(REJECT) Rese1ect P30 or P27 Load new pa~am

5 F 16 45 MTFIMGA (marksmln-secOldeg)MGA -00002 If ~ lMU not a1~gned

SET DETPRO

6

7

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY v1v - OFFCAB PRESS REL v1v (2) - NORMcb ELS (2) - close (verify)cb SECS ARM (2) - close (ver~fy)

cb SECS LOGIC (2) - close (verlfy)AUTO RCS SEL CM (12) - ~mA or MNB

(l~ftoff conf~g)

ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM AampB - off (ctr)

18

-37-

06 18 AUTO MNVR TO FDAI RPY ANGLES (01 0)

19 l 50 18 REOUEST TRIM MNVR TOALIGN SIC ROLLGDC ALIGN

FDAI RPY ANGLES(010

)

+54-00m(-06-00)

TIG-5mJn

5500m(-0500)

TVC CHECK amp PREPcb STAB CONT SYS (all) - closecb SPS (12) - closeATT DB - MINRATE - LOl~

LIMIT CYCLE - ONMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE 2ROT CONTR PWR DIRECT (2) - OFFSCS TVC (2) - RATE CMD

If SCS SCS TVC (2) - AUTO SC CONT - SCS ~

TVC GMBL DRIVE PampY - AUTOMN BUS TIE (2) - ONTVC SERVO PWR 1 - AC1MNA

2 - AC2MNBTRANS CONTR PWR - ONROT CONTR PWR NORMAL 2 - ACRHC 2 - ARMED

HORIZ CHK - HorJz on 12deg wJndmlmark (LJffiJt +3 0 PNGCS GONO GO)

If NO GO set tw 180 0 180deg0 0

Track horJz wJth 24deg wJndow markAt TIG-2 mJn Ahgn GDC

PRIMARY TVC CHECKGMBL MOT P1-Y1 -STARTON(LMP confJrm)

If SCS verJfy Thumbwheel TrJmTHC - CWVenfy NO MTVC

SEC TVC CHECKGHBL MOT P2-Y2 -STARTON(LMP confJrm)SET GPI TRIHVenfy MTVCTHC NEUTRALGPI returns to 00 (CMC) or trJm (SCS)ROT CONT Pl~ NORM 2 - ACDC

(TRIM) Go to step 17(BYPASS) BMAG MODE(3) - ATTIRATE2 (ver1fy)

ENTR

-38-

20 F SO 25 00204 GMBL TEST OPTION(ACCEPT) SC CONT - GMC (ver~fy)

PROMonitor GPI Response

0020-2000020-200Tr~m

TEST FAIL SC CONT - SCS SCS TVC (2) - AUTO

(REJECT) ENTR

21 06 40 TFIVG~VM (m~n-sec1fps)

PROG ALM - TIG s1~pped

V5N9E 01703

KEY RLSE To 21 ROT CONTR PWR DIRECT (2) - MNABSPS He v1vs (2) - AUTO (ver~fy)

LIMIT CYCLE - OFFFDAI SCALE - SOIScb SPS P2Y2 - open (for cr~t burn)

5800(-02 00)

5925(-0035)

59middot 30(-0030)

06 40

59XX(-OOXX)

AV THRUST A(B) - NORMALTHC - ARMEDRlIC (2) - ARMEDTAPE RCDR - GID RESETHBR

DSKY BLANKS

(AVE G ON)EMS MODE - NORMAL

TFIVG~VM (m~n-seclfps)

CHECK PIPA BIAS lt2fps for 5 sec

ULLAGE AS REQ

IF NO ULLAGE DIR ULLAGE PB - PUSH~

CONTROL ATT WRlIC MONITOR AVM (R3) COUNTING UP

5955(-0005)

F 99 40 ENG ON ENABLE REQUEST(AUTO IGN) PRO AT TFI gt0 sec(BYPASS IGN) ENTR to 24

22 0000 IGN

-39-

If SCS - THRUST ON PB - PUSH

06 40 TFCVG~VM (m~n-seclfpslfps)

~F 97 40 SPS Thrust fall ~

~(RESTART) PRO To IGN (RECYCLE) ENTR To TIG-05 sec

SPS THRUST LITE - ONMONITOR THRUSTING

Pc 95-105 pSlaEMS COUNTING DOWNSPS IN3 v1vs (4) - OPENSPS He v1vs tb (2) - graySPS FUELOXID PRESS - 175-195 pSlaPUGS - BALANCED

PROG ALARM V5N9E 01407 VG INCTHC - CW FLY MTVC

ECOEMER SPS CUTOFF J

AV THRUST (2) - OFF

23 F 16 40 TFC(STATIC)VG~VM (mln-seclfps)~V THRUST AB - OFF

SPS IN3 v1vs (4) - CLOSEDSPS He tb (2) - bp

cb SPS P2Y2 - closed (verlfy)TVC SERVO PHR - AC1MNA (venfy)TVC SERVO PWR 2 - OFF

PRO

24 F 16 85 VG XYZ(CM) CUps)NULL RESIDUALSRECORD ~V CTR amp RESIDUALS I1VCEMS FUNC - OFF VGXEMS MODE - STBY VGYBMAG MODE (3) - RATE 2ATT DB - MAX VGZTRANS CONT PHR - OFF

PRO

25 F 37 V82E

26 F 16 44 HAHPTFF (lnmm~n-sec)

R3-59B59 HP gt494 nmPRO

27 F 37 OOE

-40-

55 EARTH ORBIT ENTRY

1 Venfy CMSMR __

P_shyY_-

SEP ATT(180deg)

(0deg )

2

3

4

EMS INITIALIZATIONEMS FUNC - RNG SETSET RNG TO PAD DATA RNGEMS FUNC - VA SETSlew scroll to pad data VIOEMS FUNC - ENTRY

RSI ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on(up)GDC ALIGN PB - PUSH amp HOLDYAW tw - Pos1tion RSI thru 45deg amp

back to LIFl UPGDC ALIGN PB - RELEASEEMS ROLL - OFFAl1gn GDC to lMU

PWR REDUCT (Norm Deorb Only)HGA PWR - OFFFC PUMPS (3) - OFFVer1fy s1ngle suit compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - Lowcb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2)-openlOb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MAN

-41-

P61 - ENTRY PREP

5 V37E 61E05 09 01427 - ROLL REVERSED05 09 01426 - IMU UNSAT

6 F 06 61 IMPACT LAT LONG liDS UPDN (+-)(01 0

010

+00001)

PRO

PAD VALUESLATLON==G------liDS UP DN _

7 F 06 60 GMAXV400KGAMMA EIRecord

GMAXV400K----GAMMA EI _

PRO

8 F 06 63 RTOGO (1nm) PAD _VIa (fps) PADTFE (mln-sec) ----Compare wlth MSFN for PGNS GONO GONO COMM SET RTOGO amp VIO IN EMS amp

INITIALIZE(ACCEPT) PRO(RECALC) V32E to 8

-42-

P62 - CMSM SEP amp PRE-ENTRY MNVR

9 F 50 25 00041 REQUEST CMSM SEPSC CONT - SCSFREEYAW - 45deg out-of-plane (left for RCS

nght for SPS)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE2PRIM GLY to RAD - BYPASS (verlfy)SECS LOGIC (2) - on (up)MSFN conflrm GO for PYRO ARMSECS PYRO ARM - ARMMN BUS TIE (2) - ON (verlfy)CMSM SEF (2) - ONCSMLM FNl SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 pSlaCM RCS LOGIC - OFFSECS PYRO ARM - SAFEMonltor VMAB

If lt25vdc go to EMERG POWERDOWN Pg E6-1AUTO RCS SEL AlC ROLL (4) - OFFAUTO RCS SEL CM 2(6) - OFFAUTO RCS SEL CM 1(6) - MNA or MNBYAW back to 00

PITCH TO ENTRY ATTROLL 0deg (LIFT UP)PITCH - HORIZ on 317deg MARK (400K)YAW 00

ATT DB - MAXMAN ATT (PITCH) - ACCEL CMDEMS DATA - VerifyEMS FUNC - ENTRY (verlfy)EMS MODE - NORMALMAINTAIN HORIZ TRK

PRO (Act ENTRY DAP)

10 F 06 61 IMPACT LAT LONG HDSDN(010 010 -00001)

PRO

11 FOSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axlS beyond 45deg of Vel vector)

-43-

P63 - ENTRY INIT

12 06 64 GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PWR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRHORIZ CKP~tch error needle goes toward

zero approach~ng 05G t~me

MAN ATT (PITCH) - RATE CMDIf CMC ~s GO

BMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS FLY BETA If CMC NO GO ~

SC CONT - SCS~

FLY EMS RCS Deorh Roll HDS UPTRACK HORIZ w~th 29deg w~ndow mk

P64 - ENTRY POST 05G

13

05G t=elt+0___)

06 68

RTOGO AT 05G AGREES WITH EMS - venfyHORIZ CK05E Lt - on (EMS start)

No EMS start w~th~n 3 secsEMS MODE - BACKUP VHF RNG 05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds L~ft DN

NNVR L~ft DNEMS GONO GO

G-V Plot w~th~n llm~ts

Rng ctr dwn 60 + 7 durlng 10 sec per~od

Mon~tor G-meter forconvergence wlth pad data (Do)

(Vlt27K fps) Go To 17

-44-

P65 - ENTRY - UP CONT (Vgt27K fps)

14 F 16 69 BETA (01deg)DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT~

SC CONT - SCS FLY EMS

PRO

15 06 68 BElA VI HOOT (01deg fpsfps)(VltVL +500 fps amp RDOT Neg) Go To 17

p66 - ENTRY - BALLISTIC (DltDL)

16 06 22 DESIRED GMBL ANGLES RPY (01deg)Mon~tor hor~z +12deg of 317deg mark

P67 - ENTRY - FINAL PHASE (02G)

17 0666 BETACRSRNG ERRDNRNG ERR (Oldeglnmlnm)KEY VERBRecord DNRNG ERR _KEY RLSEL~m~t +100nm from PAD DRE

Mon~tor l~ft vector on RSI amp FDAIF 16 67 RTOGOLATLONG (Vre1=1000fps)

(lnm 010 01deg)SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOlfflMon~tor altimeter

Go To EARTHLANDING pg _I4L5__

-45-

56 EARTHLANDING

90K STEAM PRESS - PEGGED50K CABIN PRESS REL vIv (2) - BOOSTENTRY

SECS PYRO ARM (2) - ARM

40K(90K + 63s)

CM UNSTABLE RCS CMD - OFF ~ 40K APEX COVER JETT PG-PUSH DROGUE DEPLOY PG - PUSH (2 secafter apex cover Jett)

30K ELS LOGIC - ON (up)ELS - AUTO

24K RCS hsable (auto)(90K+92s) RCS CMD - OFF

Apex cover Jett (auto)APEX COVER JETT PB - PUSH

(WAIT 2 SECS)Drogue parachutes deployed (auto)

DROGUE DEPLOY PB - PUSH~

If Drogues FallELS - ~ ~Stablllze CM 5K MAIN DPLY PB - PUSHELS - AUTO

235K Cabln Pressure lncreaslng (Drogues + 50s)If not lncreaSlng by 17K CABIN PRESS REL vlv (RR) - DUMP

-46-

10K Maln parachutes deployedMAIN DEPLOY PB - PUSH (wlthln 1 sec)VHF ANT - RECYVHF AMA - SIMPLEXVHF BCN - ONCABIN PRESS REL v1v (2) - CLOSEDIRECT 02 vlv - OPENCM RCS LOGIC - on (up)CM PRPLNT - DUMP (burn audlb1e)Monltor CM ReS 1amp2 for He press decrease

NO BURN or PRESS DECREASE USE BOTH RHCs DO NOT FIRE PITCH JETS

CM PRPLNT-PURGE (to zero He press)CM RCS He DUMP PB - PUSH RHC (2) - 30 sees NO PITCH k

STRUT LOCKS (2) - UNLOCK

cb FLT amp PL BAT BUS ABampBAT C (3) - closecb FLT amp PLT MNA amp B (2) - opencb ECS RAD HTR OVLD (2) - opencb SPS PampY (4) - open

3K CABIN PRESS REL v1v (RH) - DUMP (after purgecompleted)

FLOOD Lts - POST LDGCM RCS PRPLNT (2) - OFFROT CONTR PWR DIRECT (2) - OFF

800 CAB PRESS RELF vlv - CLOSE (latch off)MN BUS TIE (2) - OFF

AFTER LANDINGcb MAIN REL PYRO (2) - closeMAIN RELEASE - on(up)

Go to POSTLANDING pg _47L-__

I

2

3

-47-

57 POSTLANDING

STABILIZATION VENTILATION COMMUNICATIONS

DIRECT 02 vlv - CLOSE

Stablllzation after landlngELS - AUTO (verlfy)cb MAIN REL PYRO (2) - close (venfy)MAIN RELEASE - on (up) (verlfy)S~CS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb BAT RLY BUS (2) - open

No contact w1th recovery forcesVHF AM AampB - off (ctr) ~

VHF AM Rev ONLY - A cb PL VENT - closecb FLOAT BAG (3) - closecb UPRIGHT SYS COMPRESS (2) - closeIf Stable II

FLOAT BAG(3)-FILL t1ll 2 m1n afterupr1ght then - OFF

VHF AM AlB amp BCN - OFF whlle lnvertedIf Stable I

After 10 M1n Coollng Per1odFLOAT BAG (3) - FILL 7 mln then OFF

Post Stab1lizat1on And Ventllat10nPL BCN LT - BCN LT LOWPL VENT vlv - UNLOCK (Pull)Remove PL VENT Exh CoverPL VENT - HIGH or LOWPL DYE MARKER - ON (swlmmer comm)Release foots traps and_restralntscb MNA BAT BUS A amp BAT C (2) - opencb MNB BAT BUS B amp BAT C (2) - opencb FLT amp PL BAT C - opencb PYRO A SEQ A - opencb PYRO B SEQ B - open

EACH HR - CHECK DC VOLTSgt 275 V If Notmiddot cb FLT amp PL-BAT BUS AampB (2) -open cb FLT amp PL BAT C (1) - open GO TO LOW POWER CHECKLIST

Unstow and lnstall PLV DISTRIB DUCTDeploy grappllng hook and 11ne 1f req

4

-48-

Post Landing Communlcatl0nsVHF ANT-RECY (venfy)VHF BCN - ON (verlfy)

If no contact ~lth recovery forcesperform VHF BEACON Check

MONITOR VHF BEACON transmlSSlonnth VHF AM B Rcvr andor Su)vlval

TransceiverkVHF Beacon not operatlng ~connect Surv~val TranscelVer to antcable behlnd VHF ant access pnland place radio ln BCN mode

LOW POHER CHECKLISTVHF BCN - OFFVHF AM (3) - RCVFLOOD Lts - OFFVHF AM AampB - off (ctr)VHF AM RCV ONLY - A (venfy)COUCH LIGHTS - OFFPOSTLANDING VENT SYS mlnlmlze useSURV RADIO - plug mto VHF BCN ANT cableconn behind VHF ant acess pnl amp turn radloon l-n BCN mode

EGRESS PROCEDURES

CMPCDRLMPCDR

CMPCDRCMP

LMPLl1PCDR

STABLE IDlsconnect Umblll-calsNeck darn onCenter couch - 270 0 positionArmrests stowedConnect raft to SIC l-f desl-red wlth

green lanyardConnect raft ~hl-te lanyards to SUltS amp

lnflate water wlngs when eXltl-ngHATCH PISTON PRESS vlv - PRESS (Outbd)Slde Hatch openedPL VENT - OFFcb Pnl 250 (all) - openEgress with 11feraftPut hardware klt outEgress

or CDIPALL

CMF

CDRCMF

CDR

LMF

CMFCMP LMFCMP

UlP

CDR

-49-

STABLE IIcb CREW STA AUDIO (3) - openD~sconnect umb~1~ca1s

Release foots trapsRelease restra~nt harnessCouch seat pans (3) - 170 0 pos1t10nArm rests stowedSurv1va1 k~ts removed from stowageConnect life raft ma~n1~ne to CDR or SicConnect f~rst wh~te lanyard from

11fe raft to suitConnect th~rd wh~te lanyard from

l~fe raft to SU1tConnect rucksacks together to yellow

lanyard on raft bagPRESSURE EQUALIZATION vlv - OPENRemove and stow fwd hatchEX1t feet f1rst w1th rucksacks when clear

of siC 1nflate water w1ngs and raftExit feet f1rst when clear of SiC

1nflate water w1ngsEX1t feet f1rst when clear of sic

1nflate water w1ngs

-50-

60 TLI ABORTS

TLI Aborts are conta~ned ~n the ESD s~nce the bulk of the funct~ons

concern entry preparat20ns and performance Th~s allows a s2nglesource of procedures for procedure rev2ew val~dat~on checkout andtra~n~ng These procedures ~ncorporate TLI preparat20ns as found ~n

reference 6 w~th the TLI Abort Procedures and these t~e 2nto normallunar return Entry Procedures found ~n sect20n 5 The guidel~nes

for th~s cont2ngency are spec2f2ed 2n reference 7

In2t2al preparat~ons for TLI pos2t20n the necessary system sW2tches2n add~t~on to perform~ng an EMS ~V test and a GDC al~gnment Afterthe DET ~s set for mon2tor2ng TB6 the CMP ~ncreases the 12ght levelof the LEB DSKY to max~mum and returns to the h2s couch Th2s 2Sdone so that the LEB DSKY can be observed ~n the event sunl~ght orreflect20ns wash out the ma2n d2splay panel DSKY dur2ng cr2t2calmaneuvers The crew then straps ~n and prepares for mon2tor~ng TB6as 2nd2cated by the SII SEP L~te The t2mes se~uence of procedures2S keyed on th~s d~splay and ~ncludes the DET START funct~on andSIVB IGNITION Dur2ng the burn the crew mon2tors the FDAIs foratt~tude excurs20ns and abnormal rates report~ng status checks toM~ss2on Control at d2screet t~mes dur2ng the maneuver Upon SIVBSHUTDOWN the eMP records the DSKY d~splayed performance parametersand awa2ts ground conf2rmat~on

The rat~onal for TLI aborts ~s descr~bed 2n reference 7 A summar2shyzat20n 2S extracted to prov2de background and gu2de12nes 2n th2sdocument The abort procedures cover aborts 10 m2nutes after conshyt2ngent SIVE shutdown and aborts 90 m2nutes after normal SIVE shutshydown t2me

The 10 m~nute TLI abort ~s des2gned to be used dur~ng TLI ~n theevent a spacecraft problem develops Wh2Ch can result 2n catastrophe2f ~mmed~ate act~on 2S not taken If the s~tuat20n perm~ts the crewshould always allow the SIVB to complete TLI at wh~ch t~me the groundand crew can perform a malfunct~on analys~s to determ~ne ~f an abort~s adv~sable If a fa~lure occurs that necess2tates the shutdown ofthe SIVB and the ~u~ck return of the crew to earth th~s abort ~s

des~gned to be as ~nsens~t~ve to execut~on errors as poss~ble andst21l be targeted to m2dcorr2dor The burn att~tude w~th the f~ed

hor~zon reference ~s a constant value for any shutdown t~me Theburn durat~on 2S a funct20n of shutdown t2me and 2S ava21able fromcrew charts S~nce the pr~mary purpose of th~s abort ~s to returnto earth as qU2ckly as poss2ble there are no restr2ct20ns as toland~ng locat~on However ~f the t~me to EI is greater than abouttwo hours a midcourse correct20n should be ant~c~pated

The 90 m2nute TLI abort 2S to be used 2f a cr2t2cal subsystem malshyfunct~on ~s determ2ned and the dec2s~on to abort ~s made after the

-51-

TLI cutoff and before TLI cutoff plus approxlmately 80 m1nutesTh1S allows suff1c1ent separatlon and procedural t1me to set upfor the SPS deorb1t burn performed at about TLI + 90 Note thatgenerally the deorb1t burns w1ll be performed a fe11 m1nutes beforeTLI + 90 accord1ng to crew charts shown In reference 8 The no-comm except10n requ1res that 90 m1nutes be the 1nput t1me of 19n1shytlon for P-37 (onboard return-to-earth abort program) so that onshyboard calculatlons can correspond w1th ground calculat10ns to computethe CM land1ng p01nt Th1S TLI abort lS des1gned so that returnfl1ght t1me does not exceed 18 hours and abort ~V does not exceed7000 fps ThlS abort can be performed uSlng chart ~Vs and attltudesand the earths hor1zon serves as a suff1c1ent reference The maneushyver lS targeted to ach1eve the mldcorr1dor entry target Ilne andtlmed to result 1n a deslgnated recovery area

It 1S ObV10US for abort deC1S1ons early 1n the TLI + 90 m1nute t1meshyframe that a GampN SPS burn should be performed In order to keep theTLI abort procedures cons1stent and w1th emphasls on slmpl1c1ty theprocedures here reflect a SCS SPS abort burn to cover the full abortdec1s1on t1meframe

A m1dcourse correct1on for corr1dor control after a TLI abort may bedeS1red 1f the SPS burn d1d not meet expectat1ons The TLIabortprocedures 1n th1S sect10n adapt to the normal lunar return tlmel1neand procedures pr10r to the f1nal MCC

-52-

61 TLI PREPARATION PROCEDURES

GET = 150

CRO AOS(___)

CRO LOS( )(22142)

5100

Don Helmets amp Gloves

XLUNAR - INJECT (verify)EDS PWR - on (venfy)EMS FUNC - OFF (verlfy)EMS MODE - STBYEMS FUNC - IW SETVHF RNGEMS MODE - NORMALSet ~V indo to +15868 fpsEMS FUMC - ~V Test

SPS THRUST Lt - onoff (10 sec)~V lnd stops at -01 to -415

EMS MODE - STBYEMS FUMC - ~V SETVHF RNGSet ~VC

EMS FUNC---~~V=----

GDC ALIGNFDAI Select - liZcb SECS LOGIC (Z) - close (verify)cb SECS ARM (Z) - closeSECS LOGIC (Z) - on (up)MSFN Conflrm GO for PYRO ARM (If pass)SECS PYRO ARM (Z) - on (up)TRANS CONTROL PWR - ONROT CONTR PWR NORMAL (Z) - ACDC(verlfy)ROT CONTR PWR DIRECT (Z) - MNAMNBLV INnGPI - SIISIVB (venfy)LV GUID - IU (venfy)cb DIRECT ULLAGE (Z) - closedSet EVENT TIMER to 5100Begin MONITOR For TB6

CMP to Couch

TB 6 - SII SEP Lt on (TIG-9 mln 38 sec)KEY V83E

SET ORDEALFDAI Z ORB RATE at 180 0 0SII SEP Lt out (38 sec later)Start DET COUNTING UPSC CaNT - SCS (verify)MONITOR LV TANK PRESS

~P lt 36 psid (OXID gt FUEL)~P lt Z6 psid (FUEL gt OXID)

EMERGENCY CSMLV SEP UP TLM CM - BLOCK (verify)UP TLM IU - BLOCK (venfy)

-53-

+45degPY))0middot sec PY

lOK nmltHAlt25K nm

Two phas~ng mnvrs two SPS mnvrs to circular~ze at 150 nmearth orb~t

CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ssion 4K nmltHAltlOK nm CSM amp1M - Two phasing mnvrs two SPS mnvrs to circularize at 150 nm earth orb~t CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ss~on

CSM amp 1M - Two phas~ng mnvrs APS burn todepletion th~rd phasing mnvrSPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn tosem~sync orb~t

25K nmltHAlt40K nm CSM amp 1M - Two phasmg mnvrs APS burn to depletion third phas~ng mnvr SPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn to sem~sync orbit HA)40K nm DPS ava~l - DPS LOll circularize with SPS

DPS not ava~l - Lunar flyby or CSM only to lunar orbit (if reqd gtV lt4000 fps)

V37E 47E (check b~as) Record -=--rshy(Limit 98 fpsmm)

( 1fps)tVXYZN62EVIHDOTHPAD (fpsfpslnm)MONITOR VI ( ) at ECO

SCS TVC SERVO PWR 1 - ACIMNA2 - OFF

TAPE RCDR - CMD RESETHBREMS MODE - NORMAL

SIr SEP Lt - ONTLI Inhib~t S~gnals w~11 not be honored after 5942

SIVB ULLAGE BeginsSII SEP Lt - off (TIG - 18 sec)SIVB FUEL LEADSIVB ULLAGE d~scont~nues

LV ENG I Lt - onSIVB IGNITION ( GETI)LV ENG I Lt - off - -shyMONITOR THRUST amp ATTITUDEMONITOR LV TANK PRESSSIVE ECO (Lt on) (BEGIN TB7)

EMER SIVE CUTOFF AT 6 SEC PAST BURN TIME IF VI ATTAINEDTHC CCW ampNEUTRAL IN 1 SEC or SIISIVB sW - LV STAGEPremature Shutdown HAlt4K nm CSM amp 1M -

5700

58205836

F 16 835800

F 16 62

5838594259525955595900000002SUNRISE(___)

HAW AOS(__=_) KEY VERB (freeze d~splay)

SIVB ATT HOLD 20 sec amp BEGIN VENTINGSIVB NNVR TO ORB RT (HDS DN) (3middot sec)

Record VI -c---HDOT _

HPAD _

KEY RLSEF 16 62

F 16 83

HAW LOS(__=-)

KEYmiddotRLSE~VXYZ (lfps)

Record ~VX---_

~vy

WZ--

AVC---_

TAPE RCDR - off (ctr)EMS MODE - STBYEMS FUNC - OFFSECS PYRO ARM (2) - SAFE

PRO

BURN STATUS REPORT

____--~TIG

BT------VGX____-R

-----P----_Y

REMARKS

_____VI

______--HDOT______--H______---AVC______---FUEL_______OXID

_______UNBAL

F 3708=00 OOEGOS AOS CMP TO LEB

(-=-=-)

0000

0003

0005

0014

0100

-55-

62 TLI 10 MIN ABORTSECS LOGIC (2) - on (up)SECS PYRO ARM (2) - ARM

TRANS CONTR - CGH (4 sec) amp +XDET RESET (verlfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS GMD-ON

TRANS GONTR - neutral then +X for10 sec

SIVBGPI s~ - GPIExcesslve rates 6V THRUST A - NORMAL SPS THRUST - DIRECT When rates damped 6V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

TRANS CONTR +X - OFFV37E OOE

PITGH UP to LOGAL VERT (+X axlSto~ard the earth)

RATE - LOWBMAG MODE (3) - ATTIRATE 2EDS PHR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SEGS ARM (2) - opencb EDS (3) - open

TRANS CONTR -X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (180deg)P (199deg)Y (0deg)

RETRO UPDATEGETI _

JV _VG

Jtb ---GET 400K _

05G _GET DROGUE _

ENTRY P _R _

Y_--

0945

-56-

ALIGN HORIZ ON RET +1 MKGMBL CHECK (T11lle Pentattlng)MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conflnn)cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FUMC - JV SETVHF RNGSET JV from chartE~S FUMC - JVEMS fODE - NOIDlAL

lV THRUST A - NORMALV37E 47E (THRUST fONITOR)

F 16 83 lVXYZ (1 fps)

0950

1000

NOTE For aborts durlng 1st mln of TLIKEY V82E F 16 44 (HaHpTff)Burn untll Hp lt 19NM

TRANS CONTR +X

THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN JV reqdJV THRUST (2) - OFFReport cutoff

cb SPS P2 Y2- closeGfBL MTRS (4) - OFF (LMP Confinn)TRANS CONT PWR - OFFTVC SERVO PWR (2) - OFFMN BUS TIE (2) - OFFcb SPS P1amp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREIf est time to EIltOl5500 omlt fCC andenter the SUPERCIRC CKLIST as early as pos-slb1e Pg ~2~3~ __If est time to EI)Ol5500 anticlpate afCC Enter the ENTRY PREP CKLIST at step 9pg 18

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

-2tl C

l I W gt- ~-4

z laquo I I- 0 -6

l- I J u gt- ~-8

z w w -10

~_ONSANT

9O

VER

SHO

OT

BOU

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LIF

TV

EC

TOR

OR

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TATI

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LIN

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SH

ALL

OW

TAR

GE

TLI

NE

STE

EP

TAR

GE

TLI

NE 12

gU

ND

ERSH

OO

TBO

UN

DAR

Y

RE

EN

TRY

CO

RR

IDO

R

I ~ I

-12 24

26

28

30

32

34

RE

EN

TRY

VE

LOC

ITY

VE

1-F

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3B

6-i

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CC

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8X

03

-i- rtREQUIRED PITCH GIMBAL ANG LETO OBTAIN HOR-IZON AT 317

DEGREES IN wiiiiDOW

260

z~I- ~ i5 24000

1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

-I

-1-

NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

I LU HD~-

LUHD

lt0 120UJ0

~

80 HOLD PRESENT TRIMgt LU HD013

~Y~HOIgtlt

TOP OF WINDOWa 40to

31 7 SCRIBEaaI

80 TTOM OF WINDOWi= 0

0--ltoa

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~~~Uw w u lt0 -80

HOLO PRESENT TRIlJCl

LOHU0 lt0

J gt -120 HOLD 059 TRIMlt0 z

LDHUlt0 FIELD OF VI S10 NLDHU LIFT-DOWNHEADS -UPLUHD LIFT-UP HEADS-DOWN

~~H~-160 q - P63 LIMITI- NOrE-VALIO ONLY FO~t~--

LUNAR RETURN VELOCITY

plusmnl8020 244middot 8 12 16

TIME TO 400K FT ALTITUDE-MIN

4

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-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 17: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

-14-

Upon complet~on of the burn the tN res~duals are burned to W~th~n

02 feet per second If the PGNCS ~V counter or est~mated burnduration are ~n d~sagreement ~t must be estab1~shed whether suff~shy

c~ent veloc~ty has been suppl~ed to put the land~ng po~nt in thefootpr~nt The PGNCS data w~ll be used ~f ~t ~s conf~rmed by oneother source if not the ~V counter w~11 be used ~f ~t ~s conf~rmed

by the burn durat~on t~me If add~tional ~V ~s necessary the data~s ava~lable to the crew on an onboard chart found ~n Sect~on 80

Post burn entry preparat~on requ~res EMS ~n~t~al~zation RSI al~gnshy

ment and pre-separat~on funct~ons The crew then selects the ~n~t~al

entry program P61 and records the d~sp1ays as a check aga~nst PADdata Upon complet~on of these checks P62 ~s entered The crewmanually or~ents the spacecraft to the separat~on attitude and yaws450 to ~nsure aga~nst possible CM 8M recontact After separat~on

the spacecraft ~s maneuvered to the reentry tr~m att~tude wh~ch

places the hor~zon on the 3170 w~ndow mark at EI Shortly thereshyafter ~n P62 the entry DAP is act~vated and P63 in~t~ated Dur~ng

th~s t~e MCC-H has computed a postburn update and ~t ~s vo~ced tothe crew ~f d~fferent from preburn values The EMS scroll and rangecounter w~ll be adJusted accord~ngly ~f t~me perm~ts A f~nal PGNCScheck pr~or to 05g may be mon~tored at th~s t~e w~th the CMC modein free and the manual att~tude p~tch ~n acceleration command wh~le

the hor~zon reference ~s held the p~tch error needle w~ll decreaseto zero as EI ~s reached At RET 005g the EMS mode sw~tch ~s

turned to manual the entry 005-g sw~tch and EMS roll sw~tch areturned on and the spacecraft control sw~tched to CMC to beg~n DAPcontrol At the PGNCS 005-g ~ndicatwn the program change fromP63 to P64 ~s mon~tored and the t~e vo~ce recorded At th~s t~me

the EMS range counter check ~s made dur~ng the 10 second per~od

follow~ng EMS 005g Dur~ng th~s per~od the counter should countdown 40 + 10 naut~cal m~les At PGNCS 02-g ~nd~cation the changefrom P64-to P67 ~s monitored and the ~splay may be held by key~ngVERB ~n order to record the init~al downrange error d~splay andcompare ~t to the PAD value The PGNCS has fa~led ~f the two do notagree w~th~n + 100 naut~cal m~les In the event P67 has not appearedwhen both the-g-meter and the scroll ~nd~cate greater than 05g thePGNCS has sim~lar~ly fa~led In e~ther fa~lure the SCS is used foratt~tude reference w~th an EMS entry If the checks agree the crewrema~ns w~th automat~c DAP for the rema~nder of the entry

The entry phase ~s essentially over when the relat~ve velocity ofthe spacecraft decreases to less than 1000 feet per second Th~s

~s ~nd~cated ~n P67 when RTGO lat~tude and long~tude are d~splayed

S~nce very l~ttle rang~ng capab~l~ty exists after th~s pOint thespacecraft is or~ented either full l~ft up or down depending onRTGO negat~ve or pos~t~ve and the crew prepares for the earth land~ng

phase

-15-

41 TYP~cal Retrof~re and Entry Sequence of Events

Dec~s~on to reenter

P27 (CMC update)

Retrof~re PAD update

Entry mode dec~s~on

P51 (IMU or~entat~on determlnatlon) durlng f~rst dark per~od

P52 (IMU coarse allgnment)

EMS checks

Entry PAD update

P30 (external AV)

p40 (SPS thrust)

P52 (IMU f~ne al~gnment) durlng second dark per~od

p40 (SPS thrust)

Ign~t~on att~tude check

Retroflre

P61

P62

CMSM separat~on

P63

Postburn PAD update

Entry attltude check

p64 (beg~n DAP control at O05g)

P67 (PGNCS gono go check at O2g)

42

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and

En

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Alt

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-17-

5 0 DETAILED ENTRY PROCEDURES

In order to comblne slmilar procedures that are common to lunar returnentrles and earth orblt entrles the followlng procedures are dlvldedlnto categorles that allow a mlnlmum of dupllClty ThlS provldes asmaller tralnlng package and more closely resembles the onboard crewcheckllst when comparlson lS necessary

51 Entry Preparatlons for Superclucular and Earth Orbltal Entrles

1~e entry preparatlons are comblned In these procedures andsteps pecullar to elther superclrcular or earth orbltal entrlesare labeled accordlngly The tlme llstlngs In thlS sectlon areappllcable to only superclrcular entries Slnce the earth orbltalentry tlmellne lS a functlon of several varlables as descrlbedIn sectlon 40 and reference 5

-18-51 (Contlnued)

VEHICLE PREPARATION

l-

2

3

4

5

6 -0600h

7 -0535h

8

9

10 -0430h

INITIAL STOWAGE COMPLETED

CMC amp ISS START UP

SCS POWER UP

p51 - IMU ORIENTATION

LOAD DAPV48E 11102 01111 PRO ERO PRO

LAST MCC DECISION

NO COMM - P52 amp NAV SIGHTINGSNOMINAL - P2337 ONBOARD COMPARISON

DON MAE WESTS amp FOOT RESTRAINTS

VHF AM A - SIMPLEX

P 27 (SV REFSMMAT) MNVRamp ENTRY pAD UPDATES

11 -0415h P52 - IMU REALIGN(___) (OPTION 1)

12 P37 (NO COMM ONLY)

13

14

ECS CKS02 SUPPLY REFILLECS Monitor CkEVAP H20 CONT (2) vlvs - AUTOSUIT HEAT EXCH SEC GLY - FLOW

EPS CKS 1 3 4 (5 If reqd)

15 SPS CK (If req d)

16

17

18

RCS CKSSM RCS MOUlt CkCM RCS MOUlt Ck

CampW SYS CK

CMC SELF CK

19

20 -0345h

-03l5h-0300h

21

22

22A

-19-

DSKY COND LT TEST

MIDCOURSE MANEUVERP30 - EXT rVP404l - SPSRCS THRUSTINGMIDCOURSE (17) BURN

NO COMM NAV SIGHTINGS

ffiVR TO ENTRY ATT (Superc1rc only)V62E

V49E

22B F 06 22 DESIRED FINAL GMBL ANGLESLOAD ENTRY ATT PAD ANGLESPRO

22C F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) SC CONT - CMC

BMAG MODE (3) - RATE 2CMC MODE - AUTO

PRO(~N) SC CONT - SCS

MNVR to 22E

22D 06 18 AUTO MNVR TO FDAI RPY ANGLES

22E F 50 18 REQUEST TRIM(TRIM) Go to 22C(BYPASS) ENTR

23 -200hr BORESIGHT amp SXT STAR CHECKOPT MODE - CMCOPT ZERO - OFF

V41 N91E

F 21 92 SHAFT TRUNLoad SXTS angles

41 OPTICS DRIVE

CHECK SXT STAROPT ZERO - ZERO

CHECK BORESIGHT STAR (If ava11)

24 -0135h

25(___)

26

27 -0115h

-20-

P52 - lMU REALIGNRecord gyro torqu~ng anglesRp~----

YIf-7gt-Lno--re-c-ycle PS2If conflrmed use SCS for EMS entry

GDC ALIGNIf drlft gtLOohr change ratesource

FINAL STOWAGEOPTICS (except for hybrid)ORDEALGLY TO RAD SEC - BYPASS (verlfy)CooL pnl lnstalledY-Y struts (2) extendedStow Data Box R-12

EMS CHECKEMS FUNC - OFFcb EMS (2) - closeEMS MODE - STBYEMS FUNC - EMS TEST 1 (walt 5 sec)EMS MODE - NORMAL (walt 10 sec)

Check ind lts - offRANGE lnd - 00Slew halr1ine over notch

In self-test patternEMS FUNC - EMS TEST 2 (walt 10 sec)

05G It - on (all others out)EMS FUNC - EMS TEST 3

05G It - onRSI Lower It - on (10 sec Qater)Set RANGE counter to 58 nm+OO

EMS FUNC - EMS TEST 405G It - on (all others out)G-V trace w~thin pattern to lwr rt

corner 9GRANGE lnd counts down to 0+02

EMS FUNC - EMS TEST 505G It - onRSI upper lt - on (10 sec later)RANGE md - 00SCrlbe traces vertlcal llne 9g to

022+01ALIGN SCROLL TO ENTRY PATTERN (on

37K ft sec hne)EMS FUNC - RNG SET

G-V scroll assy traces vert llne022g to 0+01

EMS MODE - STBY

28

29

30 -OllOh

-21-

~V TEST (Deorb~t only)EMS FUNC - ~V SETVHF RNGSET ~V ~nd to 15868 fpsEMS MODE - NORMALEMS FUNC - ~V TEST

SPS THRUST LT - onoff (10 sec)~V ~nd stops at -01 to -415

EMS MODE - STBY

PRIMARY WATER EVAP ACTIVATIONGLY EVAP H20 FLOW - AUTOGLY EVAP STH PRESS - AUTOPRI ECS GLY PUMP - ACI

CM RCS PREHEATNote If sys test mtr 5cd6abcd

all read 39 vdc (28degF) or moreom~t preheat

cb RCS LOGIC (2) - closeCM RCS LOGIC - ONUP T1M CM - BLOCK (ver~fy)

cb CM RCS HTRS (2) - closeCM RCS HTRS - ON (LMP Conf~rm)

(20 mlU or III lowest rdg lS39 vdc) (Moultor Maufpress for press drop)

31 (___) FINAL GDC DRIFT CK (If req I d)If drlft gtlOohr Suspect GDC Do not

use RSI amp FDAI 2

32 -OO5Om

33

34

35

TERM CM RCS PREHEATUP TLM CM - BLOCK (venfy)CM RCS HTRS - OFFCM RCS LOGIC - OFF

SYSTEMS TEST PANEL CONFIGURATIONSYS TEST METER - 4BRNDZ XPNDR - OPERATECM RCS HTRS - OFFWASTE H20 DUMP - OFFURINE DUMP - OFF

LEB LIGHTING - OFF

SEC WATER EVAP ACTIVATIONGLY To RAD SEC vlv - BYPASSSEC COOL EVAP - EVAPSEC COOL PUMP - AC2

36

37

38 -OO45m

-22-

PYRO BATT CKcb PYRO A SEQ A - close (ver~fy)

cb PRYO B SEQ B - close (verify)DC IND - PYRO BAT A(B)

~If PYRO BAT A(B) lt 35 vdc cb PYRO A(B) seq A(B) - open~

PYRO A(B)BAT BUS A(B)TO PYRO~MN BUS TIE - close

cb MNA BAT C - closecb MNB BAT C - closeDC IND - MNBPNL 8 - All cbs closed except

PL VENT - open (ver~fy)

FLOAT BAG (3) - open (ver~fy)

DOCKING PROBE (2) - open (verlfy)EDS BAT (3) - open (ver~fy)

CM ReS HTRS (2) - open

CM RCS ACTIVATIONcb SECS ARM (2) - close (verlfy)cb SECS LOGIC (2) - close (verlfy)SECS LOGIC (2) - ONMSFN conflrm GO for PYRO ARM(~f poss)SECS PYRO ARM (2) - ARMCM RCS PRPLNT 1amp2 - ONCM RCS PRESS - ONRCS Ind sw - eMl then 2

He PRESS 3700-4400 pSlaMANF PRESS 287-302 pSla

SECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFF

P27 amp ENTRY PAD UPDATEGo To Entry Checkllst

Superclrc - pg ~2~3 _Hybnd - pg -----2~9L-__Normal Deorblt - pg __3L5L- _

-23-

52 SUPERCIRCULAR ENTRY

1 SET DET (up to ET)

2

3

4

5

3000(-30-00)

EMS INITIALIZATIONSET RNG TO PAD DATA RNGEMS FUNC - Vo SETSlew Scroll to Pad Data VIOEMS FUNC - ENTRY

RS I ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on (up)GDC ALIGN PB - PUSH amp HOLDYAW Tw - Pos~t~on RSI thru

45deg amp back to LIFT UPGDC ALIGN PB - ReleaseEMS ROLL - OFFA1~gn CDC to lMU

CM RCS RING A CKRCS TRNFR - CMcb CM RCS LOGIC MNB - openAUTO RCS SEL MNB (6) - OFFSC CONT - SCSTest R~ng A ThrustersSC CONT - CMCRCS TRNFR - SMAUTO RCS SEL (12) - MNAMNB

(hftoff conflg)cb CM RCS LOGIC MNB - close

OPTICS PWR - OFFCMP to COUCH

MN BUS TIE (2) - ONTAPE RCDR - REWIND

6 35middot0Om(-25middot 00)

-24-

SEPARATION CK LISTTVC SERVO PWR 1 - AClMNAcb ELS (2) - close (ver1fy)PRIM GLY TO RAn - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY vlv - OFFCAB PRESS REL vlv (2) - NORMGMBL MTRS (4) - STARTABORT SYS PRPLNT - RCS CMD (venfy)SM RCS PRIM PRPLNT (4) - ONVHF 11M (AampB) - OFFHI GAIN ANT PWR - OFFFC PUMPS (3) - OFFVer1fy s1ugle SU1t compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - 10101cb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2) - opencb HTRS OVLD (2) - openPOT H20 RTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANSEC COOL EVAP - RESETSEC COOL PUMP - off (etr)

MtiVR TO CMSM SEP P R ATTSC CONT - SCSCMC MODE - FREEMNVR TO PAD ATTR (0deg)PY----W)

-25-

SUPERCIRCULAR ENTRY (Cont~nued)

1

4100m(-1900)

P61 - ENTRY PREP

V37E 61E

k 05 09 01427 - ROLL REVERSED 05 09 01426 - IMU UNSAT ~

2 F 06 61 IMPACT LAT LONG HDS UPDN (+-)PRO (010

fps +00001)

3 F 06 60 GMAXVPREDGAMMA EIRecord

GMAXV400K----

GAMMA EI _PRO

(01deg fpsOldeg)

4 F 06 63 RTOGO (lnm) PAD _VIO (fps) PAD _TFE(m~n-sec)

Compare w~th ~M~SFN==C~f~o-r~P~GNS GONO GOIf NO COMM Set RTOGO amp VIO In EMS

amp lnltla11ze(ACCEPT) PRO(RECALC) V32E To 4

5 F 50 25

4300m

(-1700)

45 oOm(-1500)

500Om(-1000)

6 F 06 61

-26-

P62 - CMSM SEP amp PRE-ENTRY MNVRCAUTION Call No EXT Verbs In P62

00041 REQUEST CMSM SEPSC CONT - SCSFREE

COMPARE PITCH ATT WITH PAD DATA ---0=-

(W~thLU 5deg)YAW - 45deg OUT-OF-PLANE (LEFT)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTIRATE 2MN BUS TIE (2) - ON (ver~fy)

PRIM GLY TO RAD - BYPASS (verlfy)CM RCS LOGIC - ON (venfy)SECS LOGIC (2) - on (up)SECS PYRO ARM - ARMCMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 ps~a

CM RCS LOGIC - OFFSECS PYRO ARM (2) - SAFEMonltor VMAB

If lt25 vdc go to EMERGPOWERDOWN pg E6-l

AUTO RCS SEL AC ROLL (4) - OFFAUTO RCS SEL CM 2(6)-OFFAUTO RCS SEL CM 1(6)-MNAYAW back to 0degPITCH TO HORIZ TRACK ATT

ROLL - 0deg (LIFT UP)PITCH - 400K Horiz Mark (317deg)YAW - 0deg

ATT DB - MAXMAN ATT PITCH - ACCEL CMDEMS DATA - Ver~fy

EMS FliNC - ENTRY (ver~fy)

EMS MODE - NORMALcb SPS PampY (4) - openMAINT HORIZ TRK

PRO (Act ENTRY DAP)

IMPACT LATLONGHDSDN (01deg01deg-00001)PRO

7 POSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axis beyond 45deg of Vel vector)

8 06 64

58middot00m(-0200)

9

05G tlme(+0 )

(--=---)

06 68

-27-

P63 - ENTRY INIT

GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PIJR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRmDHORIZ CKPltch error needle goes toward

zero approachlng OSG tlmeMAN ATT (PITCH) - RATE CMD

If CMC lS GOBMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS I

FLY BETA If CMC NO GO ilt

1 SC CaNT - SCS I

FLY EMS k

p64 - ENTRY POST 05G

RTOGO AT 05G AGREES HITH EMS-venfyHORIZ CK05G Lt - ON (EMS START)

No EMS START wlthln 3 sec ~ EMS MODE - BACKUP VHF RNG c

05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds Llft DN

NNVR Llft DNEMS GONO GO

G-V Plot wlthln IlmltsRng ctr dwn 60plusmn7 durlng 10 sec

perlodMonltor G-meter for

convergence wlth pad data (Do)(Vlt27K fps) Go to 13

-28-

P65 - ENTRY - UP CONT (Vgt27K fps)

10 F 16 69 BETA (01middot) _DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT lt~ SC CONT - SCS FLY EMS

PRO

11 06 68 BETAVIHDOT (OIdegfpsfps)(VltV1+500 fps amp RnOT Neg) Go To 13

P66 - ENTRY - BALLISTIC (D(DL)

12 06 22 DESIRED GMBL ANGLES RPYMoultor horlz +12middot of 317middot mark

P67 - ENTRY - FINAL PHASE (02G)

13 06 66 BETACRSRNG ERRDNRNG ERR(010 1um 1um)

KEY VERBRecord DNRNG ERR _KEY RLSEMoultor l~ft vector ou RSI amp FDAI

16 67 RTOGOLATLONG (Vrel=1000fps)(lumOldegOldeg)

SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOWNMonitor a1t~meter

Go To EARTHLANDING pg ---4L5 _

-29-

53 GampN HYBRID DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL tV1 V37E 30E

2 F 06 33 GETI(ACCEPT) PRO (hrm~n Olsec)(REJECT) LOAD DESIRED GETI

3 F 06 81 tVXYZ (LV) (lfps)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

4 F 06 42 HAHPtV (lnm lfps)Record tV

(ACCEPT) PRO(REJECT) Reselect P30 or P27 Load new paramo

5 F 16 45 MTFIMGA (marksm~n-secOlO)

MGA -00002 ~f k

k lMU not al~gned

SET DETPRO

6

7

8

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (Pull)PLSS 02 vlv - FILL02 8M SUPPLY vlv - OFFCAB PRESS REL vlv (2) - NORMcb ELS (2) - closecb SECS ARM (2) - closecb SECS LOGIC (2) - close (ver~fy)

AUTO RCS SEL CM (12) - MNA or ~ffiB

(hftoff conhg)ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM (AampB) - OFF

CMP to Couch

9

10

11

-30-

MNVR TO PAD BURN ATTLOAD DAPBMAG MODE (3) - RATE 2SC CONT - CMCAUTOATT DB - MINMAN ATT (3) - RATE CMD

v62E

v49E

12 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLES

PRO

13 F 50 18 REQ MNVR TO FDAI RPY ANGLES (01deg)(AUTO) PRO(MAN) SC CONT - SCS

BMAG MODE (3) - RATE 2MNVR To 15

14 06 18 AUTO MNVR TO FDAI RPY ANGLES (01deg)

15 F 50 18 REQ TRIM TO FDAI RPY ANGLES (01deg)(TRIM) Go to 13(ByPASS) ENTR

16

17

CHECK BORESIGHT amp SKT STARSOPT MODE - CMCOPT ZERO - OFF

v41 N91E

18 F 21 92 SHAFTTRUN (01deg 001deg)Load SXTS angles

19 41 OPTICS DRIVECheck SKT STAR

OPT ZERO - ZEROCheck BORESIGHT STAR (~f ava~l)

20 V25 N17E (01deg)Load Pad Data GMBL Angles

for CM BURN ATTATT SETtw - SET

to PAD DATA GMBL ANGLESfor CM BURN ATT

21

22

-31-

PHR REDUCTIONHGA PHR - OFFFC PUMPS (3) - OFFVerify s~ngle su~t compr oper loads

balancedFC 2 MN AampB - OFFS BD PiR AMP - LOWcb ECS RAD CONTHTR (2) - opencb HASTE H20URINE DUMP HTRS(2)- opencb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANMN BUS TIE (2) - ONTVC SERVO PHR 1 - AC1MNAGMBL MTR (4) - START

p41 - RCS THRUSTINGV37E 41E

23 F 50 18 REQ MNVR TO LCL HORIZ (HDS ON)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CMCAUTOPRO To 24

(gtfANDAP) BMAG MODE (3) - RATE 2SC CONT - CMCHOLD

V62EMNVR To 25

24 06 18 AUTO MNVR TO FDAI RPY

25 F 50 18 REQ TRIM TO LCL HORIZ (01deg)ALIGN SC ROLL

(AUTO TRIM) PRO To 24(BYPASS) ATT DB - MIN

RATE - LOHMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTlRATE 2

ENTR

550Om26 06 85

59middot2527

-32-

VGXYZ (1fps)RECHECK BORESIGHT STARTRANS CONIR PWR - on (up)EMS MODE - STBY (ver~fy)

EMS FliNC - bV SETVHF RNGSET (IV for SM BURN _EMS FliNC - bVS BD ANT - OMNI CSECS LOGIC (2) - ONMSFN conhrm Go for PYRO ARMSECS PYRO ARM (2) - ARMCM RCS LOGIC - ON (ver~fy)

DSKY BLANKS

593028 16 85 VG XYZ (AVE G ON) (lfps)

RHCs amp THC - ARMEDLIMIT CYCLE - OFFTAPE RCDR - CMD RESETHBREMS MODE - NORMAL

000029 F 16 85 REQ NULL VG XYZ (lfps)

BURN EMS bV CTR TO ZERORESET DET amp COUNT UP

If SM ONLY burn go to step 32THC - LOCKEDSC CaNT - SCSFREERATE - HIGHPRIM GLY To RAD - BYPASS (ver~fy)

MN BUS TIE (2) - ON (ver~fy)

CMSM SEP (2) - on (up)CSMLM FNL SEP (2) - on (up) (verify)CampW MODE - CMRCS TRNFR - CMCM RCS LOGIC - OFF

Momtor VM ABIf lt25 vdc go to EMERGPOWER DOWN Pg E6-l

V63E

If CMC NO GO FDAI SOURCE - ATT FDAI SEL - 1 or 2 ATT SET - GDC

SET

-33-

~Uili ATT PITCH - ACCEL CMDFDAI SCALE - 55MNVR TO CM BURN ATT (NULL ERR NEEDLES)

R 0degPY --00--

30

31

CM RCS BURNRHC III-ContJnuous PJtch DownRHC HZ-Module PJtch to null needlesBURN VGZ TO ZERO

If only 1 RHC Pulse + P=5deg from retro att MaJnta~n rates lt3degsec

BURN COMPLETION ATllV CTR= or DET= _

V8ZE

32 F 16 44 HAHPTFF (1nmffiJn-sec)Check HP-

If gt Pad data contJnue burnuntJ1 lt Pad

PRO

33 F 16 85 VGXYZ (Ups)Read VG resJduals to MSFN

(HYBRID) PRO to 34(SM ONLY BURN)

PROF 37 ODE

EI-1500 V37E 47EF 16 83 twx Y Z (Ups)

SC CONT - SCSFREEMAN ATT (PITCH) - RATE CMDRATE - HIGHPRIM GLY To RAD - BYPASS (verJfy)MN BUS TIE (2) - ON (verJfy)CMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verJfy)Campl MODE - CMRCS TRNFR - CMCM ReS LOGIC - OFFSECS PYRO ~I (2) - SAFE

-34-

PROMonitor VMAB

If lt25 vdc go to EMERGPOWER DOWN

34 F 37 OOEPCM BIT RATE - LOWATT DB - MAXEMS MODE - STBYEMS FUNC - OFF

Go To EARTH ORBIT ENTRY pg _--40-__

-36-

8 SPS THRUSTING PREPCYCLE CRYO FANSSPS GAGING - ACI (ver~fy)

PUG MODE - NORM (venfy)BMAG MODE (3) - RATE 2tv CG - CSMCMC MODE - FREEAUTO RCS SEL (16) - MNA or HNB

(hftoff conbg)SC CONT - CMCAUTO

9 MNVR TO PAD BURN ATTV62E

10 V49E

11 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLESPRO

12 F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) PRO(HAN) SC CONT - ses

MNVR to 14

06 18 AUTO MNVR TO FDAI RPY ANGLES13

14 F 50 18 REO TRIH TO FDAI RPY ANGLES(TRIM) Go to 12(BYPASS) ENTR

15 BORESIGHT STAR CHECK

16 V37E 40EOPT PWR - OFF

17 F 50 18 REQUEST MNVR TO FDAI RPY ANGLES (01deg)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CHCAUTOPRO to 18

(MANDAP) BMAG HODE (3) - RATE 2SC CONT - CMCHOLDMNVR to 19

(HANseS) se eONT - sesMNVR to 19

-35-

54 NORMAL DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL ~V

1 V37E 30E

2 F 06 33 GETI (hrm~nOlsec)

(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

3 F 06 81 ~VXYZ (LV)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

( lfps)

4 F 06 42 HAHP~V (1nmlfps)Record W

(ACCEPT) PRO -----(REJECT) Rese1ect P30 or P27 Load new pa~am

5 F 16 45 MTFIMGA (marksmln-secOldeg)MGA -00002 If ~ lMU not a1~gned

SET DETPRO

6

7

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY v1v - OFFCAB PRESS REL v1v (2) - NORMcb ELS (2) - close (verify)cb SECS ARM (2) - close (ver~fy)

cb SECS LOGIC (2) - close (verlfy)AUTO RCS SEL CM (12) - ~mA or MNB

(l~ftoff conf~g)

ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM AampB - off (ctr)

18

-37-

06 18 AUTO MNVR TO FDAI RPY ANGLES (01 0)

19 l 50 18 REOUEST TRIM MNVR TOALIGN SIC ROLLGDC ALIGN

FDAI RPY ANGLES(010

)

+54-00m(-06-00)

TIG-5mJn

5500m(-0500)

TVC CHECK amp PREPcb STAB CONT SYS (all) - closecb SPS (12) - closeATT DB - MINRATE - LOl~

LIMIT CYCLE - ONMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE 2ROT CONTR PWR DIRECT (2) - OFFSCS TVC (2) - RATE CMD

If SCS SCS TVC (2) - AUTO SC CONT - SCS ~

TVC GMBL DRIVE PampY - AUTOMN BUS TIE (2) - ONTVC SERVO PWR 1 - AC1MNA

2 - AC2MNBTRANS CONTR PWR - ONROT CONTR PWR NORMAL 2 - ACRHC 2 - ARMED

HORIZ CHK - HorJz on 12deg wJndmlmark (LJffiJt +3 0 PNGCS GONO GO)

If NO GO set tw 180 0 180deg0 0

Track horJz wJth 24deg wJndow markAt TIG-2 mJn Ahgn GDC

PRIMARY TVC CHECKGMBL MOT P1-Y1 -STARTON(LMP confJrm)

If SCS verJfy Thumbwheel TrJmTHC - CWVenfy NO MTVC

SEC TVC CHECKGHBL MOT P2-Y2 -STARTON(LMP confJrm)SET GPI TRIHVenfy MTVCTHC NEUTRALGPI returns to 00 (CMC) or trJm (SCS)ROT CONT Pl~ NORM 2 - ACDC

(TRIM) Go to step 17(BYPASS) BMAG MODE(3) - ATTIRATE2 (ver1fy)

ENTR

-38-

20 F SO 25 00204 GMBL TEST OPTION(ACCEPT) SC CONT - GMC (ver~fy)

PROMonitor GPI Response

0020-2000020-200Tr~m

TEST FAIL SC CONT - SCS SCS TVC (2) - AUTO

(REJECT) ENTR

21 06 40 TFIVG~VM (m~n-sec1fps)

PROG ALM - TIG s1~pped

V5N9E 01703

KEY RLSE To 21 ROT CONTR PWR DIRECT (2) - MNABSPS He v1vs (2) - AUTO (ver~fy)

LIMIT CYCLE - OFFFDAI SCALE - SOIScb SPS P2Y2 - open (for cr~t burn)

5800(-02 00)

5925(-0035)

59middot 30(-0030)

06 40

59XX(-OOXX)

AV THRUST A(B) - NORMALTHC - ARMEDRlIC (2) - ARMEDTAPE RCDR - GID RESETHBR

DSKY BLANKS

(AVE G ON)EMS MODE - NORMAL

TFIVG~VM (m~n-seclfps)

CHECK PIPA BIAS lt2fps for 5 sec

ULLAGE AS REQ

IF NO ULLAGE DIR ULLAGE PB - PUSH~

CONTROL ATT WRlIC MONITOR AVM (R3) COUNTING UP

5955(-0005)

F 99 40 ENG ON ENABLE REQUEST(AUTO IGN) PRO AT TFI gt0 sec(BYPASS IGN) ENTR to 24

22 0000 IGN

-39-

If SCS - THRUST ON PB - PUSH

06 40 TFCVG~VM (m~n-seclfpslfps)

~F 97 40 SPS Thrust fall ~

~(RESTART) PRO To IGN (RECYCLE) ENTR To TIG-05 sec

SPS THRUST LITE - ONMONITOR THRUSTING

Pc 95-105 pSlaEMS COUNTING DOWNSPS IN3 v1vs (4) - OPENSPS He v1vs tb (2) - graySPS FUELOXID PRESS - 175-195 pSlaPUGS - BALANCED

PROG ALARM V5N9E 01407 VG INCTHC - CW FLY MTVC

ECOEMER SPS CUTOFF J

AV THRUST (2) - OFF

23 F 16 40 TFC(STATIC)VG~VM (mln-seclfps)~V THRUST AB - OFF

SPS IN3 v1vs (4) - CLOSEDSPS He tb (2) - bp

cb SPS P2Y2 - closed (verlfy)TVC SERVO PHR - AC1MNA (venfy)TVC SERVO PWR 2 - OFF

PRO

24 F 16 85 VG XYZ(CM) CUps)NULL RESIDUALSRECORD ~V CTR amp RESIDUALS I1VCEMS FUNC - OFF VGXEMS MODE - STBY VGYBMAG MODE (3) - RATE 2ATT DB - MAX VGZTRANS CONT PHR - OFF

PRO

25 F 37 V82E

26 F 16 44 HAHPTFF (lnmm~n-sec)

R3-59B59 HP gt494 nmPRO

27 F 37 OOE

-40-

55 EARTH ORBIT ENTRY

1 Venfy CMSMR __

P_shyY_-

SEP ATT(180deg)

(0deg )

2

3

4

EMS INITIALIZATIONEMS FUNC - RNG SETSET RNG TO PAD DATA RNGEMS FUNC - VA SETSlew scroll to pad data VIOEMS FUNC - ENTRY

RSI ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on(up)GDC ALIGN PB - PUSH amp HOLDYAW tw - Pos1tion RSI thru 45deg amp

back to LIFl UPGDC ALIGN PB - RELEASEEMS ROLL - OFFAl1gn GDC to lMU

PWR REDUCT (Norm Deorb Only)HGA PWR - OFFFC PUMPS (3) - OFFVer1fy s1ngle suit compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - Lowcb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2)-openlOb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MAN

-41-

P61 - ENTRY PREP

5 V37E 61E05 09 01427 - ROLL REVERSED05 09 01426 - IMU UNSAT

6 F 06 61 IMPACT LAT LONG liDS UPDN (+-)(01 0

010

+00001)

PRO

PAD VALUESLATLON==G------liDS UP DN _

7 F 06 60 GMAXV400KGAMMA EIRecord

GMAXV400K----GAMMA EI _

PRO

8 F 06 63 RTOGO (1nm) PAD _VIa (fps) PADTFE (mln-sec) ----Compare wlth MSFN for PGNS GONO GONO COMM SET RTOGO amp VIO IN EMS amp

INITIALIZE(ACCEPT) PRO(RECALC) V32E to 8

-42-

P62 - CMSM SEP amp PRE-ENTRY MNVR

9 F 50 25 00041 REQUEST CMSM SEPSC CONT - SCSFREEYAW - 45deg out-of-plane (left for RCS

nght for SPS)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE2PRIM GLY to RAD - BYPASS (verlfy)SECS LOGIC (2) - on (up)MSFN conflrm GO for PYRO ARMSECS PYRO ARM - ARMMN BUS TIE (2) - ON (verlfy)CMSM SEF (2) - ONCSMLM FNl SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 pSlaCM RCS LOGIC - OFFSECS PYRO ARM - SAFEMonltor VMAB

If lt25vdc go to EMERG POWERDOWN Pg E6-1AUTO RCS SEL AlC ROLL (4) - OFFAUTO RCS SEL CM 2(6) - OFFAUTO RCS SEL CM 1(6) - MNA or MNBYAW back to 00

PITCH TO ENTRY ATTROLL 0deg (LIFT UP)PITCH - HORIZ on 317deg MARK (400K)YAW 00

ATT DB - MAXMAN ATT (PITCH) - ACCEL CMDEMS DATA - VerifyEMS FUNC - ENTRY (verlfy)EMS MODE - NORMALMAINTAIN HORIZ TRK

PRO (Act ENTRY DAP)

10 F 06 61 IMPACT LAT LONG HDSDN(010 010 -00001)

PRO

11 FOSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axlS beyond 45deg of Vel vector)

-43-

P63 - ENTRY INIT

12 06 64 GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PWR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRHORIZ CKP~tch error needle goes toward

zero approach~ng 05G t~me

MAN ATT (PITCH) - RATE CMDIf CMC ~s GO

BMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS FLY BETA If CMC NO GO ~

SC CONT - SCS~

FLY EMS RCS Deorh Roll HDS UPTRACK HORIZ w~th 29deg w~ndow mk

P64 - ENTRY POST 05G

13

05G t=elt+0___)

06 68

RTOGO AT 05G AGREES WITH EMS - venfyHORIZ CK05E Lt - on (EMS start)

No EMS start w~th~n 3 secsEMS MODE - BACKUP VHF RNG 05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds L~ft DN

NNVR L~ft DNEMS GONO GO

G-V Plot w~th~n llm~ts

Rng ctr dwn 60 + 7 durlng 10 sec per~od

Mon~tor G-meter forconvergence wlth pad data (Do)

(Vlt27K fps) Go To 17

-44-

P65 - ENTRY - UP CONT (Vgt27K fps)

14 F 16 69 BETA (01deg)DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT~

SC CONT - SCS FLY EMS

PRO

15 06 68 BElA VI HOOT (01deg fpsfps)(VltVL +500 fps amp RDOT Neg) Go To 17

p66 - ENTRY - BALLISTIC (DltDL)

16 06 22 DESIRED GMBL ANGLES RPY (01deg)Mon~tor hor~z +12deg of 317deg mark

P67 - ENTRY - FINAL PHASE (02G)

17 0666 BETACRSRNG ERRDNRNG ERR (Oldeglnmlnm)KEY VERBRecord DNRNG ERR _KEY RLSEL~m~t +100nm from PAD DRE

Mon~tor l~ft vector on RSI amp FDAIF 16 67 RTOGOLATLONG (Vre1=1000fps)

(lnm 010 01deg)SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOlfflMon~tor altimeter

Go To EARTHLANDING pg _I4L5__

-45-

56 EARTHLANDING

90K STEAM PRESS - PEGGED50K CABIN PRESS REL vIv (2) - BOOSTENTRY

SECS PYRO ARM (2) - ARM

40K(90K + 63s)

CM UNSTABLE RCS CMD - OFF ~ 40K APEX COVER JETT PG-PUSH DROGUE DEPLOY PG - PUSH (2 secafter apex cover Jett)

30K ELS LOGIC - ON (up)ELS - AUTO

24K RCS hsable (auto)(90K+92s) RCS CMD - OFF

Apex cover Jett (auto)APEX COVER JETT PB - PUSH

(WAIT 2 SECS)Drogue parachutes deployed (auto)

DROGUE DEPLOY PB - PUSH~

If Drogues FallELS - ~ ~Stablllze CM 5K MAIN DPLY PB - PUSHELS - AUTO

235K Cabln Pressure lncreaslng (Drogues + 50s)If not lncreaSlng by 17K CABIN PRESS REL vlv (RR) - DUMP

-46-

10K Maln parachutes deployedMAIN DEPLOY PB - PUSH (wlthln 1 sec)VHF ANT - RECYVHF AMA - SIMPLEXVHF BCN - ONCABIN PRESS REL v1v (2) - CLOSEDIRECT 02 vlv - OPENCM RCS LOGIC - on (up)CM PRPLNT - DUMP (burn audlb1e)Monltor CM ReS 1amp2 for He press decrease

NO BURN or PRESS DECREASE USE BOTH RHCs DO NOT FIRE PITCH JETS

CM PRPLNT-PURGE (to zero He press)CM RCS He DUMP PB - PUSH RHC (2) - 30 sees NO PITCH k

STRUT LOCKS (2) - UNLOCK

cb FLT amp PL BAT BUS ABampBAT C (3) - closecb FLT amp PLT MNA amp B (2) - opencb ECS RAD HTR OVLD (2) - opencb SPS PampY (4) - open

3K CABIN PRESS REL v1v (RH) - DUMP (after purgecompleted)

FLOOD Lts - POST LDGCM RCS PRPLNT (2) - OFFROT CONTR PWR DIRECT (2) - OFF

800 CAB PRESS RELF vlv - CLOSE (latch off)MN BUS TIE (2) - OFF

AFTER LANDINGcb MAIN REL PYRO (2) - closeMAIN RELEASE - on(up)

Go to POSTLANDING pg _47L-__

I

2

3

-47-

57 POSTLANDING

STABILIZATION VENTILATION COMMUNICATIONS

DIRECT 02 vlv - CLOSE

Stablllzation after landlngELS - AUTO (verlfy)cb MAIN REL PYRO (2) - close (venfy)MAIN RELEASE - on (up) (verlfy)S~CS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb BAT RLY BUS (2) - open

No contact w1th recovery forcesVHF AM AampB - off (ctr) ~

VHF AM Rev ONLY - A cb PL VENT - closecb FLOAT BAG (3) - closecb UPRIGHT SYS COMPRESS (2) - closeIf Stable II

FLOAT BAG(3)-FILL t1ll 2 m1n afterupr1ght then - OFF

VHF AM AlB amp BCN - OFF whlle lnvertedIf Stable I

After 10 M1n Coollng Per1odFLOAT BAG (3) - FILL 7 mln then OFF

Post Stab1lizat1on And Ventllat10nPL BCN LT - BCN LT LOWPL VENT vlv - UNLOCK (Pull)Remove PL VENT Exh CoverPL VENT - HIGH or LOWPL DYE MARKER - ON (swlmmer comm)Release foots traps and_restralntscb MNA BAT BUS A amp BAT C (2) - opencb MNB BAT BUS B amp BAT C (2) - opencb FLT amp PL BAT C - opencb PYRO A SEQ A - opencb PYRO B SEQ B - open

EACH HR - CHECK DC VOLTSgt 275 V If Notmiddot cb FLT amp PL-BAT BUS AampB (2) -open cb FLT amp PL BAT C (1) - open GO TO LOW POWER CHECKLIST

Unstow and lnstall PLV DISTRIB DUCTDeploy grappllng hook and 11ne 1f req

4

-48-

Post Landing Communlcatl0nsVHF ANT-RECY (venfy)VHF BCN - ON (verlfy)

If no contact ~lth recovery forcesperform VHF BEACON Check

MONITOR VHF BEACON transmlSSlonnth VHF AM B Rcvr andor Su)vlval

TransceiverkVHF Beacon not operatlng ~connect Surv~val TranscelVer to antcable behlnd VHF ant access pnland place radio ln BCN mode

LOW POHER CHECKLISTVHF BCN - OFFVHF AM (3) - RCVFLOOD Lts - OFFVHF AM AampB - off (ctr)VHF AM RCV ONLY - A (venfy)COUCH LIGHTS - OFFPOSTLANDING VENT SYS mlnlmlze useSURV RADIO - plug mto VHF BCN ANT cableconn behind VHF ant acess pnl amp turn radloon l-n BCN mode

EGRESS PROCEDURES

CMPCDRLMPCDR

CMPCDRCMP

LMPLl1PCDR

STABLE IDlsconnect Umblll-calsNeck darn onCenter couch - 270 0 positionArmrests stowedConnect raft to SIC l-f desl-red wlth

green lanyardConnect raft ~hl-te lanyards to SUltS amp

lnflate water wlngs when eXltl-ngHATCH PISTON PRESS vlv - PRESS (Outbd)Slde Hatch openedPL VENT - OFFcb Pnl 250 (all) - openEgress with 11feraftPut hardware klt outEgress

or CDIPALL

CMF

CDRCMF

CDR

LMF

CMFCMP LMFCMP

UlP

CDR

-49-

STABLE IIcb CREW STA AUDIO (3) - openD~sconnect umb~1~ca1s

Release foots trapsRelease restra~nt harnessCouch seat pans (3) - 170 0 pos1t10nArm rests stowedSurv1va1 k~ts removed from stowageConnect life raft ma~n1~ne to CDR or SicConnect f~rst wh~te lanyard from

11fe raft to suitConnect th~rd wh~te lanyard from

l~fe raft to SU1tConnect rucksacks together to yellow

lanyard on raft bagPRESSURE EQUALIZATION vlv - OPENRemove and stow fwd hatchEX1t feet f1rst w1th rucksacks when clear

of siC 1nflate water w1ngs and raftExit feet f1rst when clear of SiC

1nflate water w1ngsEX1t feet f1rst when clear of sic

1nflate water w1ngs

-50-

60 TLI ABORTS

TLI Aborts are conta~ned ~n the ESD s~nce the bulk of the funct~ons

concern entry preparat20ns and performance Th~s allows a s2nglesource of procedures for procedure rev2ew val~dat~on checkout andtra~n~ng These procedures ~ncorporate TLI preparat20ns as found ~n

reference 6 w~th the TLI Abort Procedures and these t~e 2nto normallunar return Entry Procedures found ~n sect20n 5 The guidel~nes

for th~s cont2ngency are spec2f2ed 2n reference 7

In2t2al preparat~ons for TLI pos2t20n the necessary system sW2tches2n add~t~on to perform~ng an EMS ~V test and a GDC al~gnment Afterthe DET ~s set for mon2tor2ng TB6 the CMP ~ncreases the 12ght levelof the LEB DSKY to max~mum and returns to the h2s couch Th2s 2Sdone so that the LEB DSKY can be observed ~n the event sunl~ght orreflect20ns wash out the ma2n d2splay panel DSKY dur2ng cr2t2calmaneuvers The crew then straps ~n and prepares for mon2tor~ng TB6as 2nd2cated by the SII SEP L~te The t2mes se~uence of procedures2S keyed on th~s d~splay and ~ncludes the DET START funct~on andSIVB IGNITION Dur2ng the burn the crew mon2tors the FDAIs foratt~tude excurs20ns and abnormal rates report~ng status checks toM~ss2on Control at d2screet t~mes dur2ng the maneuver Upon SIVBSHUTDOWN the eMP records the DSKY d~splayed performance parametersand awa2ts ground conf2rmat~on

The rat~onal for TLI aborts ~s descr~bed 2n reference 7 A summar2shyzat20n 2S extracted to prov2de background and gu2de12nes 2n th2sdocument The abort procedures cover aborts 10 m2nutes after conshyt2ngent SIVE shutdown and aborts 90 m2nutes after normal SIVE shutshydown t2me

The 10 m~nute TLI abort ~s des2gned to be used dur~ng TLI ~n theevent a spacecraft problem develops Wh2Ch can result 2n catastrophe2f ~mmed~ate act~on 2S not taken If the s~tuat20n perm~ts the crewshould always allow the SIVB to complete TLI at wh~ch t~me the groundand crew can perform a malfunct~on analys~s to determ~ne ~f an abort~s adv~sable If a fa~lure occurs that necess2tates the shutdown ofthe SIVB and the ~u~ck return of the crew to earth th~s abort ~s

des~gned to be as ~nsens~t~ve to execut~on errors as poss~ble andst21l be targeted to m2dcorr2dor The burn att~tude w~th the f~ed

hor~zon reference ~s a constant value for any shutdown t~me Theburn durat~on 2S a funct20n of shutdown t2me and 2S ava21able fromcrew charts S~nce the pr~mary purpose of th~s abort ~s to returnto earth as qU2ckly as poss2ble there are no restr2ct20ns as toland~ng locat~on However ~f the t~me to EI is greater than abouttwo hours a midcourse correct20n should be ant~c~pated

The 90 m2nute TLI abort 2S to be used 2f a cr2t2cal subsystem malshyfunct~on ~s determ2ned and the dec2s~on to abort ~s made after the

-51-

TLI cutoff and before TLI cutoff plus approxlmately 80 m1nutesTh1S allows suff1c1ent separatlon and procedural t1me to set upfor the SPS deorb1t burn performed at about TLI + 90 Note thatgenerally the deorb1t burns w1ll be performed a fe11 m1nutes beforeTLI + 90 accord1ng to crew charts shown In reference 8 The no-comm except10n requ1res that 90 m1nutes be the 1nput t1me of 19n1shytlon for P-37 (onboard return-to-earth abort program) so that onshyboard calculatlons can correspond w1th ground calculat10ns to computethe CM land1ng p01nt Th1S TLI abort lS des1gned so that returnfl1ght t1me does not exceed 18 hours and abort ~V does not exceed7000 fps ThlS abort can be performed uSlng chart ~Vs and attltudesand the earths hor1zon serves as a suff1c1ent reference The maneushyver lS targeted to ach1eve the mldcorr1dor entry target Ilne andtlmed to result 1n a deslgnated recovery area

It 1S ObV10US for abort deC1S1ons early 1n the TLI + 90 m1nute t1meshyframe that a GampN SPS burn should be performed In order to keep theTLI abort procedures cons1stent and w1th emphasls on slmpl1c1ty theprocedures here reflect a SCS SPS abort burn to cover the full abortdec1s1on t1meframe

A m1dcourse correct1on for corr1dor control after a TLI abort may bedeS1red 1f the SPS burn d1d not meet expectat1ons The TLIabortprocedures 1n th1S sect10n adapt to the normal lunar return tlmel1neand procedures pr10r to the f1nal MCC

-52-

61 TLI PREPARATION PROCEDURES

GET = 150

CRO AOS(___)

CRO LOS( )(22142)

5100

Don Helmets amp Gloves

XLUNAR - INJECT (verify)EDS PWR - on (venfy)EMS FUNC - OFF (verlfy)EMS MODE - STBYEMS FUNC - IW SETVHF RNGEMS MODE - NORMALSet ~V indo to +15868 fpsEMS FUMC - ~V Test

SPS THRUST Lt - onoff (10 sec)~V lnd stops at -01 to -415

EMS MODE - STBYEMS FUMC - ~V SETVHF RNGSet ~VC

EMS FUNC---~~V=----

GDC ALIGNFDAI Select - liZcb SECS LOGIC (Z) - close (verify)cb SECS ARM (Z) - closeSECS LOGIC (Z) - on (up)MSFN Conflrm GO for PYRO ARM (If pass)SECS PYRO ARM (Z) - on (up)TRANS CONTROL PWR - ONROT CONTR PWR NORMAL (Z) - ACDC(verlfy)ROT CONTR PWR DIRECT (Z) - MNAMNBLV INnGPI - SIISIVB (venfy)LV GUID - IU (venfy)cb DIRECT ULLAGE (Z) - closedSet EVENT TIMER to 5100Begin MONITOR For TB6

CMP to Couch

TB 6 - SII SEP Lt on (TIG-9 mln 38 sec)KEY V83E

SET ORDEALFDAI Z ORB RATE at 180 0 0SII SEP Lt out (38 sec later)Start DET COUNTING UPSC CaNT - SCS (verify)MONITOR LV TANK PRESS

~P lt 36 psid (OXID gt FUEL)~P lt Z6 psid (FUEL gt OXID)

EMERGENCY CSMLV SEP UP TLM CM - BLOCK (verify)UP TLM IU - BLOCK (venfy)

-53-

+45degPY))0middot sec PY

lOK nmltHAlt25K nm

Two phas~ng mnvrs two SPS mnvrs to circular~ze at 150 nmearth orb~t

CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ssion 4K nmltHAltlOK nm CSM amp1M - Two phasing mnvrs two SPS mnvrs to circularize at 150 nm earth orb~t CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ss~on

CSM amp 1M - Two phas~ng mnvrs APS burn todepletion th~rd phasing mnvrSPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn tosem~sync orb~t

25K nmltHAlt40K nm CSM amp 1M - Two phasmg mnvrs APS burn to depletion third phas~ng mnvr SPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn to sem~sync orbit HA)40K nm DPS ava~l - DPS LOll circularize with SPS

DPS not ava~l - Lunar flyby or CSM only to lunar orbit (if reqd gtV lt4000 fps)

V37E 47E (check b~as) Record -=--rshy(Limit 98 fpsmm)

( 1fps)tVXYZN62EVIHDOTHPAD (fpsfpslnm)MONITOR VI ( ) at ECO

SCS TVC SERVO PWR 1 - ACIMNA2 - OFF

TAPE RCDR - CMD RESETHBREMS MODE - NORMAL

SIr SEP Lt - ONTLI Inhib~t S~gnals w~11 not be honored after 5942

SIVB ULLAGE BeginsSII SEP Lt - off (TIG - 18 sec)SIVB FUEL LEADSIVB ULLAGE d~scont~nues

LV ENG I Lt - onSIVB IGNITION ( GETI)LV ENG I Lt - off - -shyMONITOR THRUST amp ATTITUDEMONITOR LV TANK PRESSSIVE ECO (Lt on) (BEGIN TB7)

EMER SIVE CUTOFF AT 6 SEC PAST BURN TIME IF VI ATTAINEDTHC CCW ampNEUTRAL IN 1 SEC or SIISIVB sW - LV STAGEPremature Shutdown HAlt4K nm CSM amp 1M -

5700

58205836

F 16 835800

F 16 62

5838594259525955595900000002SUNRISE(___)

HAW AOS(__=_) KEY VERB (freeze d~splay)

SIVB ATT HOLD 20 sec amp BEGIN VENTINGSIVB NNVR TO ORB RT (HDS DN) (3middot sec)

Record VI -c---HDOT _

HPAD _

KEY RLSEF 16 62

F 16 83

HAW LOS(__=-)

KEYmiddotRLSE~VXYZ (lfps)

Record ~VX---_

~vy

WZ--

AVC---_

TAPE RCDR - off (ctr)EMS MODE - STBYEMS FUNC - OFFSECS PYRO ARM (2) - SAFE

PRO

BURN STATUS REPORT

____--~TIG

BT------VGX____-R

-----P----_Y

REMARKS

_____VI

______--HDOT______--H______---AVC______---FUEL_______OXID

_______UNBAL

F 3708=00 OOEGOS AOS CMP TO LEB

(-=-=-)

0000

0003

0005

0014

0100

-55-

62 TLI 10 MIN ABORTSECS LOGIC (2) - on (up)SECS PYRO ARM (2) - ARM

TRANS CONTR - CGH (4 sec) amp +XDET RESET (verlfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS GMD-ON

TRANS GONTR - neutral then +X for10 sec

SIVBGPI s~ - GPIExcesslve rates 6V THRUST A - NORMAL SPS THRUST - DIRECT When rates damped 6V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

TRANS CONTR +X - OFFV37E OOE

PITGH UP to LOGAL VERT (+X axlSto~ard the earth)

RATE - LOWBMAG MODE (3) - ATTIRATE 2EDS PHR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SEGS ARM (2) - opencb EDS (3) - open

TRANS CONTR -X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (180deg)P (199deg)Y (0deg)

RETRO UPDATEGETI _

JV _VG

Jtb ---GET 400K _

05G _GET DROGUE _

ENTRY P _R _

Y_--

0945

-56-

ALIGN HORIZ ON RET +1 MKGMBL CHECK (T11lle Pentattlng)MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conflnn)cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FUMC - JV SETVHF RNGSET JV from chartE~S FUMC - JVEMS fODE - NOIDlAL

lV THRUST A - NORMALV37E 47E (THRUST fONITOR)

F 16 83 lVXYZ (1 fps)

0950

1000

NOTE For aborts durlng 1st mln of TLIKEY V82E F 16 44 (HaHpTff)Burn untll Hp lt 19NM

TRANS CONTR +X

THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN JV reqdJV THRUST (2) - OFFReport cutoff

cb SPS P2 Y2- closeGfBL MTRS (4) - OFF (LMP Confinn)TRANS CONT PWR - OFFTVC SERVO PWR (2) - OFFMN BUS TIE (2) - OFFcb SPS P1amp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREIf est time to EIltOl5500 omlt fCC andenter the SUPERCIRC CKLIST as early as pos-slb1e Pg ~2~3~ __If est time to EI)Ol5500 anticlpate afCC Enter the ENTRY PREP CKLIST at step 9pg 18

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

-2tl C

l I W gt- ~-4

z laquo I I- 0 -6

l- I J u gt- ~-8

z w w -10

~_ONSANT

9O

VER

SHO

OT

BOU

ND

ARY

LIF

TV

EC

TOR

OR

IEN

TATI

ON

LIN

E

SH

ALL

OW

TAR

GE

TLI

NE

STE

EP

TAR

GE

TLI

NE 12

gU

ND

ERSH

OO

TBO

UN

DAR

Y

RE

EN

TRY

CO

RR

IDO

R

I ~ I

-12 24

26

28

30

32

34

RE

EN

TRY

VE

LOC

ITY

VE

1-F

TS

EC

Ch

art

1

36

3B

6-i

~

5CM

CC

ON

ST

NT

DR

VI z gt

~

I4

0 Cl W

I

gtamp

J+

-I

-

J Cl z

2U

l z 0_bull

bull-1

+-

u ubullbull

~r

U

)

2829

JOn

J23

33

43

5IN

ER

TIA

LR

EE

NTR

YV

ELO

CIT

YA

T4

00

00

0fl

VE

I-F

TS

EC

Ch

art

2

J63

73

8X

03

-i- rtREQUIRED PITCH GIMBAL ANG LETO OBTAIN HOR-IZON AT 317

DEGREES IN wiiiiDOW

260

z~I- ~ i5 24000

1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

-I

-1-

NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

I LU HD~-

LUHD

lt0 120UJ0

~

80 HOLD PRESENT TRIMgt LU HD013

~Y~HOIgtlt

TOP OF WINDOWa 40to

31 7 SCRIBEaaI

80 TTOM OF WINDOWi= 0

0--ltoa

-40t-z

~~~Uw w u lt0 -80

HOLO PRESENT TRIlJCl

LOHU0 lt0

J gt -120 HOLD 059 TRIMlt0 z

LDHUlt0 FIELD OF VI S10 NLDHU LIFT-DOWNHEADS -UPLUHD LIFT-UP HEADS-DOWN

~~H~-160 q - P63 LIMITI- NOrE-VALIO ONLY FO~t~--

LUNAR RETURN VELOCITY

plusmnl8020 244middot 8 12 16

TIME TO 400K FT ALTITUDE-MIN

4

P37

LONG

ITUD

ECO

RREC

TION

TOOB

TAIN

1350

NM

ENTR

YRA

NGE

Ugt

UJ

cgt

3z 0 I- u U

J0

0

0

2I

U~

UJ

cgt

I

gtI- U

gt z 0 J ltJ

1 -0

340

344

348

352

356

364

368

x10

3

CMC

INER

TIAL

VELO

CITY

AT40

0KAL

TITU

DE-

FTS

EC

Ch

art

5

I l I

o

20 100 -40

-10

-50

30

-20

--

+

-BB

A+

lrBB

A

=----

-----

t~I

AB

SA_

-04

0A

AV

Z=

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D_

+

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plusmniff

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60--

--1-

-0

2030

NOTE

40

NO

MIN

AL

RET

RB

=22

MIN

30

-40

-50

---------O

VE

RB

UR

N---------I------U

ND

ER

BU

RN

------I

~30

-20

-tD

010

20

AA

VX

FTS

EC

-60

Ch

art

6

1000

0 90

00 70

00 60

00 i50

00 iMl

OO ilOO

O i20

00 10

00 o

040

120

200

EMS

6V-

FTS

EC

240

320

400

440

520

S-IV

BeO

RN-

NSE

C

105

0

I 1- I

I

LAUN

CHAZ

IMUT

H

72r

rr

ml

lJ8

ilLIG

gtEA

ilt1t

1I0R

IZON

+rmr)lfl~

GIM

BAL

ANGL

E

ROLL

=IS

OPI

TCH

=199

YAW

0

TLI

-10

MIN

ABO

RTLA

UNCH

DEC

21

1968

400050

z =gt co23

0on 3

~7 X ampJ V

gt ~ 6

2627

~B

~n

_n

INER

TIAL

VELO

CITY

ATAB

ORT

IS-IV

BC

UTO

FF)middot

FTIS

EC34

3536

Xllf

Ch

art

7

7

1000

0i

0-00

EMS

V-F

TSE

C90

0080

0070

0060

0050

0040

0030

0020

0010

000

II

II

II

II

S-IV

BBU

RNTI

ME

-M

INSE

Cll-

41)

120

200

241)

320

400

441)

520

TlI

-I0

MIN

ABOR

TlA

UNCH

-DE

C21

19

68

lAUN

CHA

ZIM

UTH

lllJ

72I ~ I

Z526

27~

~bull

DX

~IN

ERTI

ALVE

LOCI

TYAT

ABOR

T(5

-IVB

CU

TaF

l-

FTlS

EC

Ch

art

8

34l6

Xla

3

-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 18: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

-15-

41 TYP~cal Retrof~re and Entry Sequence of Events

Dec~s~on to reenter

P27 (CMC update)

Retrof~re PAD update

Entry mode dec~s~on

P51 (IMU or~entat~on determlnatlon) durlng f~rst dark per~od

P52 (IMU coarse allgnment)

EMS checks

Entry PAD update

P30 (external AV)

p40 (SPS thrust)

P52 (IMU f~ne al~gnment) durlng second dark per~od

p40 (SPS thrust)

Ign~t~on att~tude check

Retroflre

P61

P62

CMSM separat~on

P63

Postburn PAD update

Entry attltude check

p64 (beg~n DAP control at O05g)

P67 (PGNCS gono go check at O2g)

42

Retrof~re

and

En

try

Alt

ern

atlv

es

Sys

tem

fa~lure

PGNC

S

PGNC

San

dEM

S

PGNC

San

dall

onbo

ard

att

ltu

de

refe

ren

ce

Fal

lure

bef

ore

Fal

lure

aft

er

Fal

lure

aft

er

com

mlt

ted

tono

ml-

com

mlt

ted

tono

ml-

com

mlt

ted

tob

all

lstl

cn

alG

ETI

(bef

ore

nal

GET

I(a

fter

reen

try

(aft

er

nom

GET

I-3

mln

s)no

mG

ETI

-3m~ns)

del

ayed

GET

I-5

mln

s)

SCS

bu

rnatnom~nal

SCS

bu

rnat

nom

lnal

GET

an

dEM

Sen

try

GET

Ian

dEM

Sen

try

----

----

--

Del

ay

GET

Ifo

rSC

S8C

8b

urn

at

nom

lnal

Del

ayG

ETI

for

8C8

bu

rnan

d(9

09

0)

GET

Ian

d(5

555

)b

urn

and

(90

90

)BR

Eball~stlc

entr

yBR

Een

try

BRBballlst~c

entr

y1

Del

ay

GET

Ifo

rH

orlz

onm

onlt

orbu

rnHor~zon

mo

nlt

or

bu

rnt-

0

hor~zonmon~tor

bu

rnan

dro

llln

gb

all

lstl

can

dro

llln

gb

all

lstl

cI

and

roll

lng

ball~stlc

entr

yen

try

entr

y

If

VO

lce

com

mun

lcat

lons

fall

p

roce

edw~th

nom

lnal

GET

Ian

dus

e(5

555

)BR

Een

try

If

VO

lce

commun~cat~ons

fall

p

roce

edw~th

nom~nal

GET

Ian

du

sero

llln

gball~st~c

entr

y

-17-

5 0 DETAILED ENTRY PROCEDURES

In order to comblne slmilar procedures that are common to lunar returnentrles and earth orblt entrles the followlng procedures are dlvldedlnto categorles that allow a mlnlmum of dupllClty ThlS provldes asmaller tralnlng package and more closely resembles the onboard crewcheckllst when comparlson lS necessary

51 Entry Preparatlons for Superclucular and Earth Orbltal Entrles

1~e entry preparatlons are comblned In these procedures andsteps pecullar to elther superclrcular or earth orbltal entrlesare labeled accordlngly The tlme llstlngs In thlS sectlon areappllcable to only superclrcular entries Slnce the earth orbltalentry tlmellne lS a functlon of several varlables as descrlbedIn sectlon 40 and reference 5

-18-51 (Contlnued)

VEHICLE PREPARATION

l-

2

3

4

5

6 -0600h

7 -0535h

8

9

10 -0430h

INITIAL STOWAGE COMPLETED

CMC amp ISS START UP

SCS POWER UP

p51 - IMU ORIENTATION

LOAD DAPV48E 11102 01111 PRO ERO PRO

LAST MCC DECISION

NO COMM - P52 amp NAV SIGHTINGSNOMINAL - P2337 ONBOARD COMPARISON

DON MAE WESTS amp FOOT RESTRAINTS

VHF AM A - SIMPLEX

P 27 (SV REFSMMAT) MNVRamp ENTRY pAD UPDATES

11 -0415h P52 - IMU REALIGN(___) (OPTION 1)

12 P37 (NO COMM ONLY)

13

14

ECS CKS02 SUPPLY REFILLECS Monitor CkEVAP H20 CONT (2) vlvs - AUTOSUIT HEAT EXCH SEC GLY - FLOW

EPS CKS 1 3 4 (5 If reqd)

15 SPS CK (If req d)

16

17

18

RCS CKSSM RCS MOUlt CkCM RCS MOUlt Ck

CampW SYS CK

CMC SELF CK

19

20 -0345h

-03l5h-0300h

21

22

22A

-19-

DSKY COND LT TEST

MIDCOURSE MANEUVERP30 - EXT rVP404l - SPSRCS THRUSTINGMIDCOURSE (17) BURN

NO COMM NAV SIGHTINGS

ffiVR TO ENTRY ATT (Superc1rc only)V62E

V49E

22B F 06 22 DESIRED FINAL GMBL ANGLESLOAD ENTRY ATT PAD ANGLESPRO

22C F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) SC CONT - CMC

BMAG MODE (3) - RATE 2CMC MODE - AUTO

PRO(~N) SC CONT - SCS

MNVR to 22E

22D 06 18 AUTO MNVR TO FDAI RPY ANGLES

22E F 50 18 REQUEST TRIM(TRIM) Go to 22C(BYPASS) ENTR

23 -200hr BORESIGHT amp SXT STAR CHECKOPT MODE - CMCOPT ZERO - OFF

V41 N91E

F 21 92 SHAFT TRUNLoad SXTS angles

41 OPTICS DRIVE

CHECK SXT STAROPT ZERO - ZERO

CHECK BORESIGHT STAR (If ava11)

24 -0135h

25(___)

26

27 -0115h

-20-

P52 - lMU REALIGNRecord gyro torqu~ng anglesRp~----

YIf-7gt-Lno--re-c-ycle PS2If conflrmed use SCS for EMS entry

GDC ALIGNIf drlft gtLOohr change ratesource

FINAL STOWAGEOPTICS (except for hybrid)ORDEALGLY TO RAD SEC - BYPASS (verlfy)CooL pnl lnstalledY-Y struts (2) extendedStow Data Box R-12

EMS CHECKEMS FUNC - OFFcb EMS (2) - closeEMS MODE - STBYEMS FUNC - EMS TEST 1 (walt 5 sec)EMS MODE - NORMAL (walt 10 sec)

Check ind lts - offRANGE lnd - 00Slew halr1ine over notch

In self-test patternEMS FUNC - EMS TEST 2 (walt 10 sec)

05G It - on (all others out)EMS FUNC - EMS TEST 3

05G It - onRSI Lower It - on (10 sec Qater)Set RANGE counter to 58 nm+OO

EMS FUNC - EMS TEST 405G It - on (all others out)G-V trace w~thin pattern to lwr rt

corner 9GRANGE lnd counts down to 0+02

EMS FUNC - EMS TEST 505G It - onRSI upper lt - on (10 sec later)RANGE md - 00SCrlbe traces vertlcal llne 9g to

022+01ALIGN SCROLL TO ENTRY PATTERN (on

37K ft sec hne)EMS FUNC - RNG SET

G-V scroll assy traces vert llne022g to 0+01

EMS MODE - STBY

28

29

30 -OllOh

-21-

~V TEST (Deorb~t only)EMS FUNC - ~V SETVHF RNGSET ~V ~nd to 15868 fpsEMS MODE - NORMALEMS FUNC - ~V TEST

SPS THRUST LT - onoff (10 sec)~V ~nd stops at -01 to -415

EMS MODE - STBY

PRIMARY WATER EVAP ACTIVATIONGLY EVAP H20 FLOW - AUTOGLY EVAP STH PRESS - AUTOPRI ECS GLY PUMP - ACI

CM RCS PREHEATNote If sys test mtr 5cd6abcd

all read 39 vdc (28degF) or moreom~t preheat

cb RCS LOGIC (2) - closeCM RCS LOGIC - ONUP T1M CM - BLOCK (ver~fy)

cb CM RCS HTRS (2) - closeCM RCS HTRS - ON (LMP Conf~rm)

(20 mlU or III lowest rdg lS39 vdc) (Moultor Maufpress for press drop)

31 (___) FINAL GDC DRIFT CK (If req I d)If drlft gtlOohr Suspect GDC Do not

use RSI amp FDAI 2

32 -OO5Om

33

34

35

TERM CM RCS PREHEATUP TLM CM - BLOCK (venfy)CM RCS HTRS - OFFCM RCS LOGIC - OFF

SYSTEMS TEST PANEL CONFIGURATIONSYS TEST METER - 4BRNDZ XPNDR - OPERATECM RCS HTRS - OFFWASTE H20 DUMP - OFFURINE DUMP - OFF

LEB LIGHTING - OFF

SEC WATER EVAP ACTIVATIONGLY To RAD SEC vlv - BYPASSSEC COOL EVAP - EVAPSEC COOL PUMP - AC2

36

37

38 -OO45m

-22-

PYRO BATT CKcb PYRO A SEQ A - close (ver~fy)

cb PRYO B SEQ B - close (verify)DC IND - PYRO BAT A(B)

~If PYRO BAT A(B) lt 35 vdc cb PYRO A(B) seq A(B) - open~

PYRO A(B)BAT BUS A(B)TO PYRO~MN BUS TIE - close

cb MNA BAT C - closecb MNB BAT C - closeDC IND - MNBPNL 8 - All cbs closed except

PL VENT - open (ver~fy)

FLOAT BAG (3) - open (ver~fy)

DOCKING PROBE (2) - open (verlfy)EDS BAT (3) - open (ver~fy)

CM ReS HTRS (2) - open

CM RCS ACTIVATIONcb SECS ARM (2) - close (verlfy)cb SECS LOGIC (2) - close (verlfy)SECS LOGIC (2) - ONMSFN conflrm GO for PYRO ARM(~f poss)SECS PYRO ARM (2) - ARMCM RCS PRPLNT 1amp2 - ONCM RCS PRESS - ONRCS Ind sw - eMl then 2

He PRESS 3700-4400 pSlaMANF PRESS 287-302 pSla

SECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFF

P27 amp ENTRY PAD UPDATEGo To Entry Checkllst

Superclrc - pg ~2~3 _Hybnd - pg -----2~9L-__Normal Deorblt - pg __3L5L- _

-23-

52 SUPERCIRCULAR ENTRY

1 SET DET (up to ET)

2

3

4

5

3000(-30-00)

EMS INITIALIZATIONSET RNG TO PAD DATA RNGEMS FUNC - Vo SETSlew Scroll to Pad Data VIOEMS FUNC - ENTRY

RS I ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on (up)GDC ALIGN PB - PUSH amp HOLDYAW Tw - Pos~t~on RSI thru

45deg amp back to LIFT UPGDC ALIGN PB - ReleaseEMS ROLL - OFFA1~gn CDC to lMU

CM RCS RING A CKRCS TRNFR - CMcb CM RCS LOGIC MNB - openAUTO RCS SEL MNB (6) - OFFSC CONT - SCSTest R~ng A ThrustersSC CONT - CMCRCS TRNFR - SMAUTO RCS SEL (12) - MNAMNB

(hftoff conflg)cb CM RCS LOGIC MNB - close

OPTICS PWR - OFFCMP to COUCH

MN BUS TIE (2) - ONTAPE RCDR - REWIND

6 35middot0Om(-25middot 00)

-24-

SEPARATION CK LISTTVC SERVO PWR 1 - AClMNAcb ELS (2) - close (ver1fy)PRIM GLY TO RAn - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY vlv - OFFCAB PRESS REL vlv (2) - NORMGMBL MTRS (4) - STARTABORT SYS PRPLNT - RCS CMD (venfy)SM RCS PRIM PRPLNT (4) - ONVHF 11M (AampB) - OFFHI GAIN ANT PWR - OFFFC PUMPS (3) - OFFVer1fy s1ugle SU1t compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - 10101cb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2) - opencb HTRS OVLD (2) - openPOT H20 RTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANSEC COOL EVAP - RESETSEC COOL PUMP - off (etr)

MtiVR TO CMSM SEP P R ATTSC CONT - SCSCMC MODE - FREEMNVR TO PAD ATTR (0deg)PY----W)

-25-

SUPERCIRCULAR ENTRY (Cont~nued)

1

4100m(-1900)

P61 - ENTRY PREP

V37E 61E

k 05 09 01427 - ROLL REVERSED 05 09 01426 - IMU UNSAT ~

2 F 06 61 IMPACT LAT LONG HDS UPDN (+-)PRO (010

fps +00001)

3 F 06 60 GMAXVPREDGAMMA EIRecord

GMAXV400K----

GAMMA EI _PRO

(01deg fpsOldeg)

4 F 06 63 RTOGO (lnm) PAD _VIO (fps) PAD _TFE(m~n-sec)

Compare w~th ~M~SFN==C~f~o-r~P~GNS GONO GOIf NO COMM Set RTOGO amp VIO In EMS

amp lnltla11ze(ACCEPT) PRO(RECALC) V32E To 4

5 F 50 25

4300m

(-1700)

45 oOm(-1500)

500Om(-1000)

6 F 06 61

-26-

P62 - CMSM SEP amp PRE-ENTRY MNVRCAUTION Call No EXT Verbs In P62

00041 REQUEST CMSM SEPSC CONT - SCSFREE

COMPARE PITCH ATT WITH PAD DATA ---0=-

(W~thLU 5deg)YAW - 45deg OUT-OF-PLANE (LEFT)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTIRATE 2MN BUS TIE (2) - ON (ver~fy)

PRIM GLY TO RAD - BYPASS (verlfy)CM RCS LOGIC - ON (venfy)SECS LOGIC (2) - on (up)SECS PYRO ARM - ARMCMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 ps~a

CM RCS LOGIC - OFFSECS PYRO ARM (2) - SAFEMonltor VMAB

If lt25 vdc go to EMERGPOWERDOWN pg E6-l

AUTO RCS SEL AC ROLL (4) - OFFAUTO RCS SEL CM 2(6)-OFFAUTO RCS SEL CM 1(6)-MNAYAW back to 0degPITCH TO HORIZ TRACK ATT

ROLL - 0deg (LIFT UP)PITCH - 400K Horiz Mark (317deg)YAW - 0deg

ATT DB - MAXMAN ATT PITCH - ACCEL CMDEMS DATA - Ver~fy

EMS FliNC - ENTRY (ver~fy)

EMS MODE - NORMALcb SPS PampY (4) - openMAINT HORIZ TRK

PRO (Act ENTRY DAP)

IMPACT LATLONGHDSDN (01deg01deg-00001)PRO

7 POSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axis beyond 45deg of Vel vector)

8 06 64

58middot00m(-0200)

9

05G tlme(+0 )

(--=---)

06 68

-27-

P63 - ENTRY INIT

GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PIJR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRmDHORIZ CKPltch error needle goes toward

zero approachlng OSG tlmeMAN ATT (PITCH) - RATE CMD

If CMC lS GOBMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS I

FLY BETA If CMC NO GO ilt

1 SC CaNT - SCS I

FLY EMS k

p64 - ENTRY POST 05G

RTOGO AT 05G AGREES HITH EMS-venfyHORIZ CK05G Lt - ON (EMS START)

No EMS START wlthln 3 sec ~ EMS MODE - BACKUP VHF RNG c

05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds Llft DN

NNVR Llft DNEMS GONO GO

G-V Plot wlthln IlmltsRng ctr dwn 60plusmn7 durlng 10 sec

perlodMonltor G-meter for

convergence wlth pad data (Do)(Vlt27K fps) Go to 13

-28-

P65 - ENTRY - UP CONT (Vgt27K fps)

10 F 16 69 BETA (01middot) _DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT lt~ SC CONT - SCS FLY EMS

PRO

11 06 68 BETAVIHDOT (OIdegfpsfps)(VltV1+500 fps amp RnOT Neg) Go To 13

P66 - ENTRY - BALLISTIC (D(DL)

12 06 22 DESIRED GMBL ANGLES RPYMoultor horlz +12middot of 317middot mark

P67 - ENTRY - FINAL PHASE (02G)

13 06 66 BETACRSRNG ERRDNRNG ERR(010 1um 1um)

KEY VERBRecord DNRNG ERR _KEY RLSEMoultor l~ft vector ou RSI amp FDAI

16 67 RTOGOLATLONG (Vrel=1000fps)(lumOldegOldeg)

SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOWNMonitor a1t~meter

Go To EARTHLANDING pg ---4L5 _

-29-

53 GampN HYBRID DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL tV1 V37E 30E

2 F 06 33 GETI(ACCEPT) PRO (hrm~n Olsec)(REJECT) LOAD DESIRED GETI

3 F 06 81 tVXYZ (LV) (lfps)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

4 F 06 42 HAHPtV (lnm lfps)Record tV

(ACCEPT) PRO(REJECT) Reselect P30 or P27 Load new paramo

5 F 16 45 MTFIMGA (marksm~n-secOlO)

MGA -00002 ~f k

k lMU not al~gned

SET DETPRO

6

7

8

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (Pull)PLSS 02 vlv - FILL02 8M SUPPLY vlv - OFFCAB PRESS REL vlv (2) - NORMcb ELS (2) - closecb SECS ARM (2) - closecb SECS LOGIC (2) - close (ver~fy)

AUTO RCS SEL CM (12) - MNA or ~ffiB

(hftoff conhg)ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM (AampB) - OFF

CMP to Couch

9

10

11

-30-

MNVR TO PAD BURN ATTLOAD DAPBMAG MODE (3) - RATE 2SC CONT - CMCAUTOATT DB - MINMAN ATT (3) - RATE CMD

v62E

v49E

12 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLES

PRO

13 F 50 18 REQ MNVR TO FDAI RPY ANGLES (01deg)(AUTO) PRO(MAN) SC CONT - SCS

BMAG MODE (3) - RATE 2MNVR To 15

14 06 18 AUTO MNVR TO FDAI RPY ANGLES (01deg)

15 F 50 18 REQ TRIM TO FDAI RPY ANGLES (01deg)(TRIM) Go to 13(ByPASS) ENTR

16

17

CHECK BORESIGHT amp SKT STARSOPT MODE - CMCOPT ZERO - OFF

v41 N91E

18 F 21 92 SHAFTTRUN (01deg 001deg)Load SXTS angles

19 41 OPTICS DRIVECheck SKT STAR

OPT ZERO - ZEROCheck BORESIGHT STAR (~f ava~l)

20 V25 N17E (01deg)Load Pad Data GMBL Angles

for CM BURN ATTATT SETtw - SET

to PAD DATA GMBL ANGLESfor CM BURN ATT

21

22

-31-

PHR REDUCTIONHGA PHR - OFFFC PUMPS (3) - OFFVerify s~ngle su~t compr oper loads

balancedFC 2 MN AampB - OFFS BD PiR AMP - LOWcb ECS RAD CONTHTR (2) - opencb HASTE H20URINE DUMP HTRS(2)- opencb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANMN BUS TIE (2) - ONTVC SERVO PHR 1 - AC1MNAGMBL MTR (4) - START

p41 - RCS THRUSTINGV37E 41E

23 F 50 18 REQ MNVR TO LCL HORIZ (HDS ON)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CMCAUTOPRO To 24

(gtfANDAP) BMAG MODE (3) - RATE 2SC CONT - CMCHOLD

V62EMNVR To 25

24 06 18 AUTO MNVR TO FDAI RPY

25 F 50 18 REQ TRIM TO LCL HORIZ (01deg)ALIGN SC ROLL

(AUTO TRIM) PRO To 24(BYPASS) ATT DB - MIN

RATE - LOHMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTlRATE 2

ENTR

550Om26 06 85

59middot2527

-32-

VGXYZ (1fps)RECHECK BORESIGHT STARTRANS CONIR PWR - on (up)EMS MODE - STBY (ver~fy)

EMS FliNC - bV SETVHF RNGSET (IV for SM BURN _EMS FliNC - bVS BD ANT - OMNI CSECS LOGIC (2) - ONMSFN conhrm Go for PYRO ARMSECS PYRO ARM (2) - ARMCM RCS LOGIC - ON (ver~fy)

DSKY BLANKS

593028 16 85 VG XYZ (AVE G ON) (lfps)

RHCs amp THC - ARMEDLIMIT CYCLE - OFFTAPE RCDR - CMD RESETHBREMS MODE - NORMAL

000029 F 16 85 REQ NULL VG XYZ (lfps)

BURN EMS bV CTR TO ZERORESET DET amp COUNT UP

If SM ONLY burn go to step 32THC - LOCKEDSC CaNT - SCSFREERATE - HIGHPRIM GLY To RAD - BYPASS (ver~fy)

MN BUS TIE (2) - ON (ver~fy)

CMSM SEP (2) - on (up)CSMLM FNL SEP (2) - on (up) (verify)CampW MODE - CMRCS TRNFR - CMCM RCS LOGIC - OFF

Momtor VM ABIf lt25 vdc go to EMERGPOWER DOWN Pg E6-l

V63E

If CMC NO GO FDAI SOURCE - ATT FDAI SEL - 1 or 2 ATT SET - GDC

SET

-33-

~Uili ATT PITCH - ACCEL CMDFDAI SCALE - 55MNVR TO CM BURN ATT (NULL ERR NEEDLES)

R 0degPY --00--

30

31

CM RCS BURNRHC III-ContJnuous PJtch DownRHC HZ-Module PJtch to null needlesBURN VGZ TO ZERO

If only 1 RHC Pulse + P=5deg from retro att MaJnta~n rates lt3degsec

BURN COMPLETION ATllV CTR= or DET= _

V8ZE

32 F 16 44 HAHPTFF (1nmffiJn-sec)Check HP-

If gt Pad data contJnue burnuntJ1 lt Pad

PRO

33 F 16 85 VGXYZ (Ups)Read VG resJduals to MSFN

(HYBRID) PRO to 34(SM ONLY BURN)

PROF 37 ODE

EI-1500 V37E 47EF 16 83 twx Y Z (Ups)

SC CONT - SCSFREEMAN ATT (PITCH) - RATE CMDRATE - HIGHPRIM GLY To RAD - BYPASS (verJfy)MN BUS TIE (2) - ON (verJfy)CMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verJfy)Campl MODE - CMRCS TRNFR - CMCM ReS LOGIC - OFFSECS PYRO ~I (2) - SAFE

-34-

PROMonitor VMAB

If lt25 vdc go to EMERGPOWER DOWN

34 F 37 OOEPCM BIT RATE - LOWATT DB - MAXEMS MODE - STBYEMS FUNC - OFF

Go To EARTH ORBIT ENTRY pg _--40-__

-36-

8 SPS THRUSTING PREPCYCLE CRYO FANSSPS GAGING - ACI (ver~fy)

PUG MODE - NORM (venfy)BMAG MODE (3) - RATE 2tv CG - CSMCMC MODE - FREEAUTO RCS SEL (16) - MNA or HNB

(hftoff conbg)SC CONT - CMCAUTO

9 MNVR TO PAD BURN ATTV62E

10 V49E

11 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLESPRO

12 F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) PRO(HAN) SC CONT - ses

MNVR to 14

06 18 AUTO MNVR TO FDAI RPY ANGLES13

14 F 50 18 REO TRIH TO FDAI RPY ANGLES(TRIM) Go to 12(BYPASS) ENTR

15 BORESIGHT STAR CHECK

16 V37E 40EOPT PWR - OFF

17 F 50 18 REQUEST MNVR TO FDAI RPY ANGLES (01deg)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CHCAUTOPRO to 18

(MANDAP) BMAG HODE (3) - RATE 2SC CONT - CMCHOLDMNVR to 19

(HANseS) se eONT - sesMNVR to 19

-35-

54 NORMAL DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL ~V

1 V37E 30E

2 F 06 33 GETI (hrm~nOlsec)

(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

3 F 06 81 ~VXYZ (LV)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

( lfps)

4 F 06 42 HAHP~V (1nmlfps)Record W

(ACCEPT) PRO -----(REJECT) Rese1ect P30 or P27 Load new pa~am

5 F 16 45 MTFIMGA (marksmln-secOldeg)MGA -00002 If ~ lMU not a1~gned

SET DETPRO

6

7

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY v1v - OFFCAB PRESS REL v1v (2) - NORMcb ELS (2) - close (verify)cb SECS ARM (2) - close (ver~fy)

cb SECS LOGIC (2) - close (verlfy)AUTO RCS SEL CM (12) - ~mA or MNB

(l~ftoff conf~g)

ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM AampB - off (ctr)

18

-37-

06 18 AUTO MNVR TO FDAI RPY ANGLES (01 0)

19 l 50 18 REOUEST TRIM MNVR TOALIGN SIC ROLLGDC ALIGN

FDAI RPY ANGLES(010

)

+54-00m(-06-00)

TIG-5mJn

5500m(-0500)

TVC CHECK amp PREPcb STAB CONT SYS (all) - closecb SPS (12) - closeATT DB - MINRATE - LOl~

LIMIT CYCLE - ONMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE 2ROT CONTR PWR DIRECT (2) - OFFSCS TVC (2) - RATE CMD

If SCS SCS TVC (2) - AUTO SC CONT - SCS ~

TVC GMBL DRIVE PampY - AUTOMN BUS TIE (2) - ONTVC SERVO PWR 1 - AC1MNA

2 - AC2MNBTRANS CONTR PWR - ONROT CONTR PWR NORMAL 2 - ACRHC 2 - ARMED

HORIZ CHK - HorJz on 12deg wJndmlmark (LJffiJt +3 0 PNGCS GONO GO)

If NO GO set tw 180 0 180deg0 0

Track horJz wJth 24deg wJndow markAt TIG-2 mJn Ahgn GDC

PRIMARY TVC CHECKGMBL MOT P1-Y1 -STARTON(LMP confJrm)

If SCS verJfy Thumbwheel TrJmTHC - CWVenfy NO MTVC

SEC TVC CHECKGHBL MOT P2-Y2 -STARTON(LMP confJrm)SET GPI TRIHVenfy MTVCTHC NEUTRALGPI returns to 00 (CMC) or trJm (SCS)ROT CONT Pl~ NORM 2 - ACDC

(TRIM) Go to step 17(BYPASS) BMAG MODE(3) - ATTIRATE2 (ver1fy)

ENTR

-38-

20 F SO 25 00204 GMBL TEST OPTION(ACCEPT) SC CONT - GMC (ver~fy)

PROMonitor GPI Response

0020-2000020-200Tr~m

TEST FAIL SC CONT - SCS SCS TVC (2) - AUTO

(REJECT) ENTR

21 06 40 TFIVG~VM (m~n-sec1fps)

PROG ALM - TIG s1~pped

V5N9E 01703

KEY RLSE To 21 ROT CONTR PWR DIRECT (2) - MNABSPS He v1vs (2) - AUTO (ver~fy)

LIMIT CYCLE - OFFFDAI SCALE - SOIScb SPS P2Y2 - open (for cr~t burn)

5800(-02 00)

5925(-0035)

59middot 30(-0030)

06 40

59XX(-OOXX)

AV THRUST A(B) - NORMALTHC - ARMEDRlIC (2) - ARMEDTAPE RCDR - GID RESETHBR

DSKY BLANKS

(AVE G ON)EMS MODE - NORMAL

TFIVG~VM (m~n-seclfps)

CHECK PIPA BIAS lt2fps for 5 sec

ULLAGE AS REQ

IF NO ULLAGE DIR ULLAGE PB - PUSH~

CONTROL ATT WRlIC MONITOR AVM (R3) COUNTING UP

5955(-0005)

F 99 40 ENG ON ENABLE REQUEST(AUTO IGN) PRO AT TFI gt0 sec(BYPASS IGN) ENTR to 24

22 0000 IGN

-39-

If SCS - THRUST ON PB - PUSH

06 40 TFCVG~VM (m~n-seclfpslfps)

~F 97 40 SPS Thrust fall ~

~(RESTART) PRO To IGN (RECYCLE) ENTR To TIG-05 sec

SPS THRUST LITE - ONMONITOR THRUSTING

Pc 95-105 pSlaEMS COUNTING DOWNSPS IN3 v1vs (4) - OPENSPS He v1vs tb (2) - graySPS FUELOXID PRESS - 175-195 pSlaPUGS - BALANCED

PROG ALARM V5N9E 01407 VG INCTHC - CW FLY MTVC

ECOEMER SPS CUTOFF J

AV THRUST (2) - OFF

23 F 16 40 TFC(STATIC)VG~VM (mln-seclfps)~V THRUST AB - OFF

SPS IN3 v1vs (4) - CLOSEDSPS He tb (2) - bp

cb SPS P2Y2 - closed (verlfy)TVC SERVO PHR - AC1MNA (venfy)TVC SERVO PWR 2 - OFF

PRO

24 F 16 85 VG XYZ(CM) CUps)NULL RESIDUALSRECORD ~V CTR amp RESIDUALS I1VCEMS FUNC - OFF VGXEMS MODE - STBY VGYBMAG MODE (3) - RATE 2ATT DB - MAX VGZTRANS CONT PHR - OFF

PRO

25 F 37 V82E

26 F 16 44 HAHPTFF (lnmm~n-sec)

R3-59B59 HP gt494 nmPRO

27 F 37 OOE

-40-

55 EARTH ORBIT ENTRY

1 Venfy CMSMR __

P_shyY_-

SEP ATT(180deg)

(0deg )

2

3

4

EMS INITIALIZATIONEMS FUNC - RNG SETSET RNG TO PAD DATA RNGEMS FUNC - VA SETSlew scroll to pad data VIOEMS FUNC - ENTRY

RSI ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on(up)GDC ALIGN PB - PUSH amp HOLDYAW tw - Pos1tion RSI thru 45deg amp

back to LIFl UPGDC ALIGN PB - RELEASEEMS ROLL - OFFAl1gn GDC to lMU

PWR REDUCT (Norm Deorb Only)HGA PWR - OFFFC PUMPS (3) - OFFVer1fy s1ngle suit compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - Lowcb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2)-openlOb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MAN

-41-

P61 - ENTRY PREP

5 V37E 61E05 09 01427 - ROLL REVERSED05 09 01426 - IMU UNSAT

6 F 06 61 IMPACT LAT LONG liDS UPDN (+-)(01 0

010

+00001)

PRO

PAD VALUESLATLON==G------liDS UP DN _

7 F 06 60 GMAXV400KGAMMA EIRecord

GMAXV400K----GAMMA EI _

PRO

8 F 06 63 RTOGO (1nm) PAD _VIa (fps) PADTFE (mln-sec) ----Compare wlth MSFN for PGNS GONO GONO COMM SET RTOGO amp VIO IN EMS amp

INITIALIZE(ACCEPT) PRO(RECALC) V32E to 8

-42-

P62 - CMSM SEP amp PRE-ENTRY MNVR

9 F 50 25 00041 REQUEST CMSM SEPSC CONT - SCSFREEYAW - 45deg out-of-plane (left for RCS

nght for SPS)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE2PRIM GLY to RAD - BYPASS (verlfy)SECS LOGIC (2) - on (up)MSFN conflrm GO for PYRO ARMSECS PYRO ARM - ARMMN BUS TIE (2) - ON (verlfy)CMSM SEF (2) - ONCSMLM FNl SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 pSlaCM RCS LOGIC - OFFSECS PYRO ARM - SAFEMonltor VMAB

If lt25vdc go to EMERG POWERDOWN Pg E6-1AUTO RCS SEL AlC ROLL (4) - OFFAUTO RCS SEL CM 2(6) - OFFAUTO RCS SEL CM 1(6) - MNA or MNBYAW back to 00

PITCH TO ENTRY ATTROLL 0deg (LIFT UP)PITCH - HORIZ on 317deg MARK (400K)YAW 00

ATT DB - MAXMAN ATT (PITCH) - ACCEL CMDEMS DATA - VerifyEMS FUNC - ENTRY (verlfy)EMS MODE - NORMALMAINTAIN HORIZ TRK

PRO (Act ENTRY DAP)

10 F 06 61 IMPACT LAT LONG HDSDN(010 010 -00001)

PRO

11 FOSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axlS beyond 45deg of Vel vector)

-43-

P63 - ENTRY INIT

12 06 64 GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PWR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRHORIZ CKP~tch error needle goes toward

zero approach~ng 05G t~me

MAN ATT (PITCH) - RATE CMDIf CMC ~s GO

BMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS FLY BETA If CMC NO GO ~

SC CONT - SCS~

FLY EMS RCS Deorh Roll HDS UPTRACK HORIZ w~th 29deg w~ndow mk

P64 - ENTRY POST 05G

13

05G t=elt+0___)

06 68

RTOGO AT 05G AGREES WITH EMS - venfyHORIZ CK05E Lt - on (EMS start)

No EMS start w~th~n 3 secsEMS MODE - BACKUP VHF RNG 05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds L~ft DN

NNVR L~ft DNEMS GONO GO

G-V Plot w~th~n llm~ts

Rng ctr dwn 60 + 7 durlng 10 sec per~od

Mon~tor G-meter forconvergence wlth pad data (Do)

(Vlt27K fps) Go To 17

-44-

P65 - ENTRY - UP CONT (Vgt27K fps)

14 F 16 69 BETA (01deg)DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT~

SC CONT - SCS FLY EMS

PRO

15 06 68 BElA VI HOOT (01deg fpsfps)(VltVL +500 fps amp RDOT Neg) Go To 17

p66 - ENTRY - BALLISTIC (DltDL)

16 06 22 DESIRED GMBL ANGLES RPY (01deg)Mon~tor hor~z +12deg of 317deg mark

P67 - ENTRY - FINAL PHASE (02G)

17 0666 BETACRSRNG ERRDNRNG ERR (Oldeglnmlnm)KEY VERBRecord DNRNG ERR _KEY RLSEL~m~t +100nm from PAD DRE

Mon~tor l~ft vector on RSI amp FDAIF 16 67 RTOGOLATLONG (Vre1=1000fps)

(lnm 010 01deg)SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOlfflMon~tor altimeter

Go To EARTHLANDING pg _I4L5__

-45-

56 EARTHLANDING

90K STEAM PRESS - PEGGED50K CABIN PRESS REL vIv (2) - BOOSTENTRY

SECS PYRO ARM (2) - ARM

40K(90K + 63s)

CM UNSTABLE RCS CMD - OFF ~ 40K APEX COVER JETT PG-PUSH DROGUE DEPLOY PG - PUSH (2 secafter apex cover Jett)

30K ELS LOGIC - ON (up)ELS - AUTO

24K RCS hsable (auto)(90K+92s) RCS CMD - OFF

Apex cover Jett (auto)APEX COVER JETT PB - PUSH

(WAIT 2 SECS)Drogue parachutes deployed (auto)

DROGUE DEPLOY PB - PUSH~

If Drogues FallELS - ~ ~Stablllze CM 5K MAIN DPLY PB - PUSHELS - AUTO

235K Cabln Pressure lncreaslng (Drogues + 50s)If not lncreaSlng by 17K CABIN PRESS REL vlv (RR) - DUMP

-46-

10K Maln parachutes deployedMAIN DEPLOY PB - PUSH (wlthln 1 sec)VHF ANT - RECYVHF AMA - SIMPLEXVHF BCN - ONCABIN PRESS REL v1v (2) - CLOSEDIRECT 02 vlv - OPENCM RCS LOGIC - on (up)CM PRPLNT - DUMP (burn audlb1e)Monltor CM ReS 1amp2 for He press decrease

NO BURN or PRESS DECREASE USE BOTH RHCs DO NOT FIRE PITCH JETS

CM PRPLNT-PURGE (to zero He press)CM RCS He DUMP PB - PUSH RHC (2) - 30 sees NO PITCH k

STRUT LOCKS (2) - UNLOCK

cb FLT amp PL BAT BUS ABampBAT C (3) - closecb FLT amp PLT MNA amp B (2) - opencb ECS RAD HTR OVLD (2) - opencb SPS PampY (4) - open

3K CABIN PRESS REL v1v (RH) - DUMP (after purgecompleted)

FLOOD Lts - POST LDGCM RCS PRPLNT (2) - OFFROT CONTR PWR DIRECT (2) - OFF

800 CAB PRESS RELF vlv - CLOSE (latch off)MN BUS TIE (2) - OFF

AFTER LANDINGcb MAIN REL PYRO (2) - closeMAIN RELEASE - on(up)

Go to POSTLANDING pg _47L-__

I

2

3

-47-

57 POSTLANDING

STABILIZATION VENTILATION COMMUNICATIONS

DIRECT 02 vlv - CLOSE

Stablllzation after landlngELS - AUTO (verlfy)cb MAIN REL PYRO (2) - close (venfy)MAIN RELEASE - on (up) (verlfy)S~CS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb BAT RLY BUS (2) - open

No contact w1th recovery forcesVHF AM AampB - off (ctr) ~

VHF AM Rev ONLY - A cb PL VENT - closecb FLOAT BAG (3) - closecb UPRIGHT SYS COMPRESS (2) - closeIf Stable II

FLOAT BAG(3)-FILL t1ll 2 m1n afterupr1ght then - OFF

VHF AM AlB amp BCN - OFF whlle lnvertedIf Stable I

After 10 M1n Coollng Per1odFLOAT BAG (3) - FILL 7 mln then OFF

Post Stab1lizat1on And Ventllat10nPL BCN LT - BCN LT LOWPL VENT vlv - UNLOCK (Pull)Remove PL VENT Exh CoverPL VENT - HIGH or LOWPL DYE MARKER - ON (swlmmer comm)Release foots traps and_restralntscb MNA BAT BUS A amp BAT C (2) - opencb MNB BAT BUS B amp BAT C (2) - opencb FLT amp PL BAT C - opencb PYRO A SEQ A - opencb PYRO B SEQ B - open

EACH HR - CHECK DC VOLTSgt 275 V If Notmiddot cb FLT amp PL-BAT BUS AampB (2) -open cb FLT amp PL BAT C (1) - open GO TO LOW POWER CHECKLIST

Unstow and lnstall PLV DISTRIB DUCTDeploy grappllng hook and 11ne 1f req

4

-48-

Post Landing Communlcatl0nsVHF ANT-RECY (venfy)VHF BCN - ON (verlfy)

If no contact ~lth recovery forcesperform VHF BEACON Check

MONITOR VHF BEACON transmlSSlonnth VHF AM B Rcvr andor Su)vlval

TransceiverkVHF Beacon not operatlng ~connect Surv~val TranscelVer to antcable behlnd VHF ant access pnland place radio ln BCN mode

LOW POHER CHECKLISTVHF BCN - OFFVHF AM (3) - RCVFLOOD Lts - OFFVHF AM AampB - off (ctr)VHF AM RCV ONLY - A (venfy)COUCH LIGHTS - OFFPOSTLANDING VENT SYS mlnlmlze useSURV RADIO - plug mto VHF BCN ANT cableconn behind VHF ant acess pnl amp turn radloon l-n BCN mode

EGRESS PROCEDURES

CMPCDRLMPCDR

CMPCDRCMP

LMPLl1PCDR

STABLE IDlsconnect Umblll-calsNeck darn onCenter couch - 270 0 positionArmrests stowedConnect raft to SIC l-f desl-red wlth

green lanyardConnect raft ~hl-te lanyards to SUltS amp

lnflate water wlngs when eXltl-ngHATCH PISTON PRESS vlv - PRESS (Outbd)Slde Hatch openedPL VENT - OFFcb Pnl 250 (all) - openEgress with 11feraftPut hardware klt outEgress

or CDIPALL

CMF

CDRCMF

CDR

LMF

CMFCMP LMFCMP

UlP

CDR

-49-

STABLE IIcb CREW STA AUDIO (3) - openD~sconnect umb~1~ca1s

Release foots trapsRelease restra~nt harnessCouch seat pans (3) - 170 0 pos1t10nArm rests stowedSurv1va1 k~ts removed from stowageConnect life raft ma~n1~ne to CDR or SicConnect f~rst wh~te lanyard from

11fe raft to suitConnect th~rd wh~te lanyard from

l~fe raft to SU1tConnect rucksacks together to yellow

lanyard on raft bagPRESSURE EQUALIZATION vlv - OPENRemove and stow fwd hatchEX1t feet f1rst w1th rucksacks when clear

of siC 1nflate water w1ngs and raftExit feet f1rst when clear of SiC

1nflate water w1ngsEX1t feet f1rst when clear of sic

1nflate water w1ngs

-50-

60 TLI ABORTS

TLI Aborts are conta~ned ~n the ESD s~nce the bulk of the funct~ons

concern entry preparat20ns and performance Th~s allows a s2nglesource of procedures for procedure rev2ew val~dat~on checkout andtra~n~ng These procedures ~ncorporate TLI preparat20ns as found ~n

reference 6 w~th the TLI Abort Procedures and these t~e 2nto normallunar return Entry Procedures found ~n sect20n 5 The guidel~nes

for th~s cont2ngency are spec2f2ed 2n reference 7

In2t2al preparat~ons for TLI pos2t20n the necessary system sW2tches2n add~t~on to perform~ng an EMS ~V test and a GDC al~gnment Afterthe DET ~s set for mon2tor2ng TB6 the CMP ~ncreases the 12ght levelof the LEB DSKY to max~mum and returns to the h2s couch Th2s 2Sdone so that the LEB DSKY can be observed ~n the event sunl~ght orreflect20ns wash out the ma2n d2splay panel DSKY dur2ng cr2t2calmaneuvers The crew then straps ~n and prepares for mon2tor~ng TB6as 2nd2cated by the SII SEP L~te The t2mes se~uence of procedures2S keyed on th~s d~splay and ~ncludes the DET START funct~on andSIVB IGNITION Dur2ng the burn the crew mon2tors the FDAIs foratt~tude excurs20ns and abnormal rates report~ng status checks toM~ss2on Control at d2screet t~mes dur2ng the maneuver Upon SIVBSHUTDOWN the eMP records the DSKY d~splayed performance parametersand awa2ts ground conf2rmat~on

The rat~onal for TLI aborts ~s descr~bed 2n reference 7 A summar2shyzat20n 2S extracted to prov2de background and gu2de12nes 2n th2sdocument The abort procedures cover aborts 10 m2nutes after conshyt2ngent SIVE shutdown and aborts 90 m2nutes after normal SIVE shutshydown t2me

The 10 m~nute TLI abort ~s des2gned to be used dur~ng TLI ~n theevent a spacecraft problem develops Wh2Ch can result 2n catastrophe2f ~mmed~ate act~on 2S not taken If the s~tuat20n perm~ts the crewshould always allow the SIVB to complete TLI at wh~ch t~me the groundand crew can perform a malfunct~on analys~s to determ~ne ~f an abort~s adv~sable If a fa~lure occurs that necess2tates the shutdown ofthe SIVB and the ~u~ck return of the crew to earth th~s abort ~s

des~gned to be as ~nsens~t~ve to execut~on errors as poss~ble andst21l be targeted to m2dcorr2dor The burn att~tude w~th the f~ed

hor~zon reference ~s a constant value for any shutdown t~me Theburn durat~on 2S a funct20n of shutdown t2me and 2S ava21able fromcrew charts S~nce the pr~mary purpose of th~s abort ~s to returnto earth as qU2ckly as poss2ble there are no restr2ct20ns as toland~ng locat~on However ~f the t~me to EI is greater than abouttwo hours a midcourse correct20n should be ant~c~pated

The 90 m2nute TLI abort 2S to be used 2f a cr2t2cal subsystem malshyfunct~on ~s determ2ned and the dec2s~on to abort ~s made after the

-51-

TLI cutoff and before TLI cutoff plus approxlmately 80 m1nutesTh1S allows suff1c1ent separatlon and procedural t1me to set upfor the SPS deorb1t burn performed at about TLI + 90 Note thatgenerally the deorb1t burns w1ll be performed a fe11 m1nutes beforeTLI + 90 accord1ng to crew charts shown In reference 8 The no-comm except10n requ1res that 90 m1nutes be the 1nput t1me of 19n1shytlon for P-37 (onboard return-to-earth abort program) so that onshyboard calculatlons can correspond w1th ground calculat10ns to computethe CM land1ng p01nt Th1S TLI abort lS des1gned so that returnfl1ght t1me does not exceed 18 hours and abort ~V does not exceed7000 fps ThlS abort can be performed uSlng chart ~Vs and attltudesand the earths hor1zon serves as a suff1c1ent reference The maneushyver lS targeted to ach1eve the mldcorr1dor entry target Ilne andtlmed to result 1n a deslgnated recovery area

It 1S ObV10US for abort deC1S1ons early 1n the TLI + 90 m1nute t1meshyframe that a GampN SPS burn should be performed In order to keep theTLI abort procedures cons1stent and w1th emphasls on slmpl1c1ty theprocedures here reflect a SCS SPS abort burn to cover the full abortdec1s1on t1meframe

A m1dcourse correct1on for corr1dor control after a TLI abort may bedeS1red 1f the SPS burn d1d not meet expectat1ons The TLIabortprocedures 1n th1S sect10n adapt to the normal lunar return tlmel1neand procedures pr10r to the f1nal MCC

-52-

61 TLI PREPARATION PROCEDURES

GET = 150

CRO AOS(___)

CRO LOS( )(22142)

5100

Don Helmets amp Gloves

XLUNAR - INJECT (verify)EDS PWR - on (venfy)EMS FUNC - OFF (verlfy)EMS MODE - STBYEMS FUNC - IW SETVHF RNGEMS MODE - NORMALSet ~V indo to +15868 fpsEMS FUMC - ~V Test

SPS THRUST Lt - onoff (10 sec)~V lnd stops at -01 to -415

EMS MODE - STBYEMS FUMC - ~V SETVHF RNGSet ~VC

EMS FUNC---~~V=----

GDC ALIGNFDAI Select - liZcb SECS LOGIC (Z) - close (verify)cb SECS ARM (Z) - closeSECS LOGIC (Z) - on (up)MSFN Conflrm GO for PYRO ARM (If pass)SECS PYRO ARM (Z) - on (up)TRANS CONTROL PWR - ONROT CONTR PWR NORMAL (Z) - ACDC(verlfy)ROT CONTR PWR DIRECT (Z) - MNAMNBLV INnGPI - SIISIVB (venfy)LV GUID - IU (venfy)cb DIRECT ULLAGE (Z) - closedSet EVENT TIMER to 5100Begin MONITOR For TB6

CMP to Couch

TB 6 - SII SEP Lt on (TIG-9 mln 38 sec)KEY V83E

SET ORDEALFDAI Z ORB RATE at 180 0 0SII SEP Lt out (38 sec later)Start DET COUNTING UPSC CaNT - SCS (verify)MONITOR LV TANK PRESS

~P lt 36 psid (OXID gt FUEL)~P lt Z6 psid (FUEL gt OXID)

EMERGENCY CSMLV SEP UP TLM CM - BLOCK (verify)UP TLM IU - BLOCK (venfy)

-53-

+45degPY))0middot sec PY

lOK nmltHAlt25K nm

Two phas~ng mnvrs two SPS mnvrs to circular~ze at 150 nmearth orb~t

CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ssion 4K nmltHAltlOK nm CSM amp1M - Two phasing mnvrs two SPS mnvrs to circularize at 150 nm earth orb~t CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ss~on

CSM amp 1M - Two phas~ng mnvrs APS burn todepletion th~rd phasing mnvrSPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn tosem~sync orb~t

25K nmltHAlt40K nm CSM amp 1M - Two phasmg mnvrs APS burn to depletion third phas~ng mnvr SPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn to sem~sync orbit HA)40K nm DPS ava~l - DPS LOll circularize with SPS

DPS not ava~l - Lunar flyby or CSM only to lunar orbit (if reqd gtV lt4000 fps)

V37E 47E (check b~as) Record -=--rshy(Limit 98 fpsmm)

( 1fps)tVXYZN62EVIHDOTHPAD (fpsfpslnm)MONITOR VI ( ) at ECO

SCS TVC SERVO PWR 1 - ACIMNA2 - OFF

TAPE RCDR - CMD RESETHBREMS MODE - NORMAL

SIr SEP Lt - ONTLI Inhib~t S~gnals w~11 not be honored after 5942

SIVB ULLAGE BeginsSII SEP Lt - off (TIG - 18 sec)SIVB FUEL LEADSIVB ULLAGE d~scont~nues

LV ENG I Lt - onSIVB IGNITION ( GETI)LV ENG I Lt - off - -shyMONITOR THRUST amp ATTITUDEMONITOR LV TANK PRESSSIVE ECO (Lt on) (BEGIN TB7)

EMER SIVE CUTOFF AT 6 SEC PAST BURN TIME IF VI ATTAINEDTHC CCW ampNEUTRAL IN 1 SEC or SIISIVB sW - LV STAGEPremature Shutdown HAlt4K nm CSM amp 1M -

5700

58205836

F 16 835800

F 16 62

5838594259525955595900000002SUNRISE(___)

HAW AOS(__=_) KEY VERB (freeze d~splay)

SIVB ATT HOLD 20 sec amp BEGIN VENTINGSIVB NNVR TO ORB RT (HDS DN) (3middot sec)

Record VI -c---HDOT _

HPAD _

KEY RLSEF 16 62

F 16 83

HAW LOS(__=-)

KEYmiddotRLSE~VXYZ (lfps)

Record ~VX---_

~vy

WZ--

AVC---_

TAPE RCDR - off (ctr)EMS MODE - STBYEMS FUNC - OFFSECS PYRO ARM (2) - SAFE

PRO

BURN STATUS REPORT

____--~TIG

BT------VGX____-R

-----P----_Y

REMARKS

_____VI

______--HDOT______--H______---AVC______---FUEL_______OXID

_______UNBAL

F 3708=00 OOEGOS AOS CMP TO LEB

(-=-=-)

0000

0003

0005

0014

0100

-55-

62 TLI 10 MIN ABORTSECS LOGIC (2) - on (up)SECS PYRO ARM (2) - ARM

TRANS CONTR - CGH (4 sec) amp +XDET RESET (verlfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS GMD-ON

TRANS GONTR - neutral then +X for10 sec

SIVBGPI s~ - GPIExcesslve rates 6V THRUST A - NORMAL SPS THRUST - DIRECT When rates damped 6V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

TRANS CONTR +X - OFFV37E OOE

PITGH UP to LOGAL VERT (+X axlSto~ard the earth)

RATE - LOWBMAG MODE (3) - ATTIRATE 2EDS PHR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SEGS ARM (2) - opencb EDS (3) - open

TRANS CONTR -X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (180deg)P (199deg)Y (0deg)

RETRO UPDATEGETI _

JV _VG

Jtb ---GET 400K _

05G _GET DROGUE _

ENTRY P _R _

Y_--

0945

-56-

ALIGN HORIZ ON RET +1 MKGMBL CHECK (T11lle Pentattlng)MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conflnn)cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FUMC - JV SETVHF RNGSET JV from chartE~S FUMC - JVEMS fODE - NOIDlAL

lV THRUST A - NORMALV37E 47E (THRUST fONITOR)

F 16 83 lVXYZ (1 fps)

0950

1000

NOTE For aborts durlng 1st mln of TLIKEY V82E F 16 44 (HaHpTff)Burn untll Hp lt 19NM

TRANS CONTR +X

THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN JV reqdJV THRUST (2) - OFFReport cutoff

cb SPS P2 Y2- closeGfBL MTRS (4) - OFF (LMP Confinn)TRANS CONT PWR - OFFTVC SERVO PWR (2) - OFFMN BUS TIE (2) - OFFcb SPS P1amp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREIf est time to EIltOl5500 omlt fCC andenter the SUPERCIRC CKLIST as early as pos-slb1e Pg ~2~3~ __If est time to EI)Ol5500 anticlpate afCC Enter the ENTRY PREP CKLIST at step 9pg 18

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

-2tl C

l I W gt- ~-4

z laquo I I- 0 -6

l- I J u gt- ~-8

z w w -10

~_ONSANT

9O

VER

SHO

OT

BOU

ND

ARY

LIF

TV

EC

TOR

OR

IEN

TATI

ON

LIN

E

SH

ALL

OW

TAR

GE

TLI

NE

STE

EP

TAR

GE

TLI

NE 12

gU

ND

ERSH

OO

TBO

UN

DAR

Y

RE

EN

TRY

CO

RR

IDO

R

I ~ I

-12 24

26

28

30

32

34

RE

EN

TRY

VE

LOC

ITY

VE

1-F

TS

EC

Ch

art

1

36

3B

6-i

~

5CM

CC

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bull-1

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43

5IN

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LR

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73

8X

03

-i- rtREQUIRED PITCH GIMBAL ANG LETO OBTAIN HOR-IZON AT 317

DEGREES IN wiiiiDOW

260

z~I- ~ i5 24000

1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

-I

-1-

NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

I LU HD~-

LUHD

lt0 120UJ0

~

80 HOLD PRESENT TRIMgt LU HD013

~Y~HOIgtlt

TOP OF WINDOWa 40to

31 7 SCRIBEaaI

80 TTOM OF WINDOWi= 0

0--ltoa

-40t-z

~~~Uw w u lt0 -80

HOLO PRESENT TRIlJCl

LOHU0 lt0

J gt -120 HOLD 059 TRIMlt0 z

LDHUlt0 FIELD OF VI S10 NLDHU LIFT-DOWNHEADS -UPLUHD LIFT-UP HEADS-DOWN

~~H~-160 q - P63 LIMITI- NOrE-VALIO ONLY FO~t~--

LUNAR RETURN VELOCITY

plusmnl8020 244middot 8 12 16

TIME TO 400K FT ALTITUDE-MIN

4

P37

LONG

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1350

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340

344

348

352

356

364

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120

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320

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IS-IV

BC

UTO

FF)middot

FTIS

EC34

3536

Xllf

Ch

art

7

7

1000

0i

0-00

EMS

V-F

TSE

C90

0080

0070

0060

0050

0040

0030

0020

0010

000

II

II

II

II

S-IV

BBU

RNTI

ME

-M

INSE

Cll-

41)

120

200

241)

320

400

441)

520

TlI

-I0

MIN

ABOR

TlA

UNCH

-DE

C21

19

68

lAUN

CHA

ZIM

UTH

lllJ

72I ~ I

Z526

27~

~bull

DX

~IN

ERTI

ALVE

LOCI

TYAT

ABOR

T(5

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CU

TaF

l-

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EC

Ch

art

8

34l6

Xla

3

-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 19: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

42

Retrof~re

and

En

try

Alt

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atlv

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Sys

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fa~lure

PGNC

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PGNC

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PGNC

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Fal

lure

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lure

aft

er

Fal

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com

mlt

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com

mlt

ted

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ml-

com

mlt

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all

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-3m~ns)

del

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GET

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bu

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SCS

bu

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GET

an

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try

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--

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Del

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for

8C8

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Ian

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all

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-17-

5 0 DETAILED ENTRY PROCEDURES

In order to comblne slmilar procedures that are common to lunar returnentrles and earth orblt entrles the followlng procedures are dlvldedlnto categorles that allow a mlnlmum of dupllClty ThlS provldes asmaller tralnlng package and more closely resembles the onboard crewcheckllst when comparlson lS necessary

51 Entry Preparatlons for Superclucular and Earth Orbltal Entrles

1~e entry preparatlons are comblned In these procedures andsteps pecullar to elther superclrcular or earth orbltal entrlesare labeled accordlngly The tlme llstlngs In thlS sectlon areappllcable to only superclrcular entries Slnce the earth orbltalentry tlmellne lS a functlon of several varlables as descrlbedIn sectlon 40 and reference 5

-18-51 (Contlnued)

VEHICLE PREPARATION

l-

2

3

4

5

6 -0600h

7 -0535h

8

9

10 -0430h

INITIAL STOWAGE COMPLETED

CMC amp ISS START UP

SCS POWER UP

p51 - IMU ORIENTATION

LOAD DAPV48E 11102 01111 PRO ERO PRO

LAST MCC DECISION

NO COMM - P52 amp NAV SIGHTINGSNOMINAL - P2337 ONBOARD COMPARISON

DON MAE WESTS amp FOOT RESTRAINTS

VHF AM A - SIMPLEX

P 27 (SV REFSMMAT) MNVRamp ENTRY pAD UPDATES

11 -0415h P52 - IMU REALIGN(___) (OPTION 1)

12 P37 (NO COMM ONLY)

13

14

ECS CKS02 SUPPLY REFILLECS Monitor CkEVAP H20 CONT (2) vlvs - AUTOSUIT HEAT EXCH SEC GLY - FLOW

EPS CKS 1 3 4 (5 If reqd)

15 SPS CK (If req d)

16

17

18

RCS CKSSM RCS MOUlt CkCM RCS MOUlt Ck

CampW SYS CK

CMC SELF CK

19

20 -0345h

-03l5h-0300h

21

22

22A

-19-

DSKY COND LT TEST

MIDCOURSE MANEUVERP30 - EXT rVP404l - SPSRCS THRUSTINGMIDCOURSE (17) BURN

NO COMM NAV SIGHTINGS

ffiVR TO ENTRY ATT (Superc1rc only)V62E

V49E

22B F 06 22 DESIRED FINAL GMBL ANGLESLOAD ENTRY ATT PAD ANGLESPRO

22C F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) SC CONT - CMC

BMAG MODE (3) - RATE 2CMC MODE - AUTO

PRO(~N) SC CONT - SCS

MNVR to 22E

22D 06 18 AUTO MNVR TO FDAI RPY ANGLES

22E F 50 18 REQUEST TRIM(TRIM) Go to 22C(BYPASS) ENTR

23 -200hr BORESIGHT amp SXT STAR CHECKOPT MODE - CMCOPT ZERO - OFF

V41 N91E

F 21 92 SHAFT TRUNLoad SXTS angles

41 OPTICS DRIVE

CHECK SXT STAROPT ZERO - ZERO

CHECK BORESIGHT STAR (If ava11)

24 -0135h

25(___)

26

27 -0115h

-20-

P52 - lMU REALIGNRecord gyro torqu~ng anglesRp~----

YIf-7gt-Lno--re-c-ycle PS2If conflrmed use SCS for EMS entry

GDC ALIGNIf drlft gtLOohr change ratesource

FINAL STOWAGEOPTICS (except for hybrid)ORDEALGLY TO RAD SEC - BYPASS (verlfy)CooL pnl lnstalledY-Y struts (2) extendedStow Data Box R-12

EMS CHECKEMS FUNC - OFFcb EMS (2) - closeEMS MODE - STBYEMS FUNC - EMS TEST 1 (walt 5 sec)EMS MODE - NORMAL (walt 10 sec)

Check ind lts - offRANGE lnd - 00Slew halr1ine over notch

In self-test patternEMS FUNC - EMS TEST 2 (walt 10 sec)

05G It - on (all others out)EMS FUNC - EMS TEST 3

05G It - onRSI Lower It - on (10 sec Qater)Set RANGE counter to 58 nm+OO

EMS FUNC - EMS TEST 405G It - on (all others out)G-V trace w~thin pattern to lwr rt

corner 9GRANGE lnd counts down to 0+02

EMS FUNC - EMS TEST 505G It - onRSI upper lt - on (10 sec later)RANGE md - 00SCrlbe traces vertlcal llne 9g to

022+01ALIGN SCROLL TO ENTRY PATTERN (on

37K ft sec hne)EMS FUNC - RNG SET

G-V scroll assy traces vert llne022g to 0+01

EMS MODE - STBY

28

29

30 -OllOh

-21-

~V TEST (Deorb~t only)EMS FUNC - ~V SETVHF RNGSET ~V ~nd to 15868 fpsEMS MODE - NORMALEMS FUNC - ~V TEST

SPS THRUST LT - onoff (10 sec)~V ~nd stops at -01 to -415

EMS MODE - STBY

PRIMARY WATER EVAP ACTIVATIONGLY EVAP H20 FLOW - AUTOGLY EVAP STH PRESS - AUTOPRI ECS GLY PUMP - ACI

CM RCS PREHEATNote If sys test mtr 5cd6abcd

all read 39 vdc (28degF) or moreom~t preheat

cb RCS LOGIC (2) - closeCM RCS LOGIC - ONUP T1M CM - BLOCK (ver~fy)

cb CM RCS HTRS (2) - closeCM RCS HTRS - ON (LMP Conf~rm)

(20 mlU or III lowest rdg lS39 vdc) (Moultor Maufpress for press drop)

31 (___) FINAL GDC DRIFT CK (If req I d)If drlft gtlOohr Suspect GDC Do not

use RSI amp FDAI 2

32 -OO5Om

33

34

35

TERM CM RCS PREHEATUP TLM CM - BLOCK (venfy)CM RCS HTRS - OFFCM RCS LOGIC - OFF

SYSTEMS TEST PANEL CONFIGURATIONSYS TEST METER - 4BRNDZ XPNDR - OPERATECM RCS HTRS - OFFWASTE H20 DUMP - OFFURINE DUMP - OFF

LEB LIGHTING - OFF

SEC WATER EVAP ACTIVATIONGLY To RAD SEC vlv - BYPASSSEC COOL EVAP - EVAPSEC COOL PUMP - AC2

36

37

38 -OO45m

-22-

PYRO BATT CKcb PYRO A SEQ A - close (ver~fy)

cb PRYO B SEQ B - close (verify)DC IND - PYRO BAT A(B)

~If PYRO BAT A(B) lt 35 vdc cb PYRO A(B) seq A(B) - open~

PYRO A(B)BAT BUS A(B)TO PYRO~MN BUS TIE - close

cb MNA BAT C - closecb MNB BAT C - closeDC IND - MNBPNL 8 - All cbs closed except

PL VENT - open (ver~fy)

FLOAT BAG (3) - open (ver~fy)

DOCKING PROBE (2) - open (verlfy)EDS BAT (3) - open (ver~fy)

CM ReS HTRS (2) - open

CM RCS ACTIVATIONcb SECS ARM (2) - close (verlfy)cb SECS LOGIC (2) - close (verlfy)SECS LOGIC (2) - ONMSFN conflrm GO for PYRO ARM(~f poss)SECS PYRO ARM (2) - ARMCM RCS PRPLNT 1amp2 - ONCM RCS PRESS - ONRCS Ind sw - eMl then 2

He PRESS 3700-4400 pSlaMANF PRESS 287-302 pSla

SECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFF

P27 amp ENTRY PAD UPDATEGo To Entry Checkllst

Superclrc - pg ~2~3 _Hybnd - pg -----2~9L-__Normal Deorblt - pg __3L5L- _

-23-

52 SUPERCIRCULAR ENTRY

1 SET DET (up to ET)

2

3

4

5

3000(-30-00)

EMS INITIALIZATIONSET RNG TO PAD DATA RNGEMS FUNC - Vo SETSlew Scroll to Pad Data VIOEMS FUNC - ENTRY

RS I ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on (up)GDC ALIGN PB - PUSH amp HOLDYAW Tw - Pos~t~on RSI thru

45deg amp back to LIFT UPGDC ALIGN PB - ReleaseEMS ROLL - OFFA1~gn CDC to lMU

CM RCS RING A CKRCS TRNFR - CMcb CM RCS LOGIC MNB - openAUTO RCS SEL MNB (6) - OFFSC CONT - SCSTest R~ng A ThrustersSC CONT - CMCRCS TRNFR - SMAUTO RCS SEL (12) - MNAMNB

(hftoff conflg)cb CM RCS LOGIC MNB - close

OPTICS PWR - OFFCMP to COUCH

MN BUS TIE (2) - ONTAPE RCDR - REWIND

6 35middot0Om(-25middot 00)

-24-

SEPARATION CK LISTTVC SERVO PWR 1 - AClMNAcb ELS (2) - close (ver1fy)PRIM GLY TO RAn - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY vlv - OFFCAB PRESS REL vlv (2) - NORMGMBL MTRS (4) - STARTABORT SYS PRPLNT - RCS CMD (venfy)SM RCS PRIM PRPLNT (4) - ONVHF 11M (AampB) - OFFHI GAIN ANT PWR - OFFFC PUMPS (3) - OFFVer1fy s1ugle SU1t compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - 10101cb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2) - opencb HTRS OVLD (2) - openPOT H20 RTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANSEC COOL EVAP - RESETSEC COOL PUMP - off (etr)

MtiVR TO CMSM SEP P R ATTSC CONT - SCSCMC MODE - FREEMNVR TO PAD ATTR (0deg)PY----W)

-25-

SUPERCIRCULAR ENTRY (Cont~nued)

1

4100m(-1900)

P61 - ENTRY PREP

V37E 61E

k 05 09 01427 - ROLL REVERSED 05 09 01426 - IMU UNSAT ~

2 F 06 61 IMPACT LAT LONG HDS UPDN (+-)PRO (010

fps +00001)

3 F 06 60 GMAXVPREDGAMMA EIRecord

GMAXV400K----

GAMMA EI _PRO

(01deg fpsOldeg)

4 F 06 63 RTOGO (lnm) PAD _VIO (fps) PAD _TFE(m~n-sec)

Compare w~th ~M~SFN==C~f~o-r~P~GNS GONO GOIf NO COMM Set RTOGO amp VIO In EMS

amp lnltla11ze(ACCEPT) PRO(RECALC) V32E To 4

5 F 50 25

4300m

(-1700)

45 oOm(-1500)

500Om(-1000)

6 F 06 61

-26-

P62 - CMSM SEP amp PRE-ENTRY MNVRCAUTION Call No EXT Verbs In P62

00041 REQUEST CMSM SEPSC CONT - SCSFREE

COMPARE PITCH ATT WITH PAD DATA ---0=-

(W~thLU 5deg)YAW - 45deg OUT-OF-PLANE (LEFT)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTIRATE 2MN BUS TIE (2) - ON (ver~fy)

PRIM GLY TO RAD - BYPASS (verlfy)CM RCS LOGIC - ON (venfy)SECS LOGIC (2) - on (up)SECS PYRO ARM - ARMCMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 ps~a

CM RCS LOGIC - OFFSECS PYRO ARM (2) - SAFEMonltor VMAB

If lt25 vdc go to EMERGPOWERDOWN pg E6-l

AUTO RCS SEL AC ROLL (4) - OFFAUTO RCS SEL CM 2(6)-OFFAUTO RCS SEL CM 1(6)-MNAYAW back to 0degPITCH TO HORIZ TRACK ATT

ROLL - 0deg (LIFT UP)PITCH - 400K Horiz Mark (317deg)YAW - 0deg

ATT DB - MAXMAN ATT PITCH - ACCEL CMDEMS DATA - Ver~fy

EMS FliNC - ENTRY (ver~fy)

EMS MODE - NORMALcb SPS PampY (4) - openMAINT HORIZ TRK

PRO (Act ENTRY DAP)

IMPACT LATLONGHDSDN (01deg01deg-00001)PRO

7 POSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axis beyond 45deg of Vel vector)

8 06 64

58middot00m(-0200)

9

05G tlme(+0 )

(--=---)

06 68

-27-

P63 - ENTRY INIT

GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PIJR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRmDHORIZ CKPltch error needle goes toward

zero approachlng OSG tlmeMAN ATT (PITCH) - RATE CMD

If CMC lS GOBMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS I

FLY BETA If CMC NO GO ilt

1 SC CaNT - SCS I

FLY EMS k

p64 - ENTRY POST 05G

RTOGO AT 05G AGREES HITH EMS-venfyHORIZ CK05G Lt - ON (EMS START)

No EMS START wlthln 3 sec ~ EMS MODE - BACKUP VHF RNG c

05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds Llft DN

NNVR Llft DNEMS GONO GO

G-V Plot wlthln IlmltsRng ctr dwn 60plusmn7 durlng 10 sec

perlodMonltor G-meter for

convergence wlth pad data (Do)(Vlt27K fps) Go to 13

-28-

P65 - ENTRY - UP CONT (Vgt27K fps)

10 F 16 69 BETA (01middot) _DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT lt~ SC CONT - SCS FLY EMS

PRO

11 06 68 BETAVIHDOT (OIdegfpsfps)(VltV1+500 fps amp RnOT Neg) Go To 13

P66 - ENTRY - BALLISTIC (D(DL)

12 06 22 DESIRED GMBL ANGLES RPYMoultor horlz +12middot of 317middot mark

P67 - ENTRY - FINAL PHASE (02G)

13 06 66 BETACRSRNG ERRDNRNG ERR(010 1um 1um)

KEY VERBRecord DNRNG ERR _KEY RLSEMoultor l~ft vector ou RSI amp FDAI

16 67 RTOGOLATLONG (Vrel=1000fps)(lumOldegOldeg)

SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOWNMonitor a1t~meter

Go To EARTHLANDING pg ---4L5 _

-29-

53 GampN HYBRID DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL tV1 V37E 30E

2 F 06 33 GETI(ACCEPT) PRO (hrm~n Olsec)(REJECT) LOAD DESIRED GETI

3 F 06 81 tVXYZ (LV) (lfps)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

4 F 06 42 HAHPtV (lnm lfps)Record tV

(ACCEPT) PRO(REJECT) Reselect P30 or P27 Load new paramo

5 F 16 45 MTFIMGA (marksm~n-secOlO)

MGA -00002 ~f k

k lMU not al~gned

SET DETPRO

6

7

8

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (Pull)PLSS 02 vlv - FILL02 8M SUPPLY vlv - OFFCAB PRESS REL vlv (2) - NORMcb ELS (2) - closecb SECS ARM (2) - closecb SECS LOGIC (2) - close (ver~fy)

AUTO RCS SEL CM (12) - MNA or ~ffiB

(hftoff conhg)ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM (AampB) - OFF

CMP to Couch

9

10

11

-30-

MNVR TO PAD BURN ATTLOAD DAPBMAG MODE (3) - RATE 2SC CONT - CMCAUTOATT DB - MINMAN ATT (3) - RATE CMD

v62E

v49E

12 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLES

PRO

13 F 50 18 REQ MNVR TO FDAI RPY ANGLES (01deg)(AUTO) PRO(MAN) SC CONT - SCS

BMAG MODE (3) - RATE 2MNVR To 15

14 06 18 AUTO MNVR TO FDAI RPY ANGLES (01deg)

15 F 50 18 REQ TRIM TO FDAI RPY ANGLES (01deg)(TRIM) Go to 13(ByPASS) ENTR

16

17

CHECK BORESIGHT amp SKT STARSOPT MODE - CMCOPT ZERO - OFF

v41 N91E

18 F 21 92 SHAFTTRUN (01deg 001deg)Load SXTS angles

19 41 OPTICS DRIVECheck SKT STAR

OPT ZERO - ZEROCheck BORESIGHT STAR (~f ava~l)

20 V25 N17E (01deg)Load Pad Data GMBL Angles

for CM BURN ATTATT SETtw - SET

to PAD DATA GMBL ANGLESfor CM BURN ATT

21

22

-31-

PHR REDUCTIONHGA PHR - OFFFC PUMPS (3) - OFFVerify s~ngle su~t compr oper loads

balancedFC 2 MN AampB - OFFS BD PiR AMP - LOWcb ECS RAD CONTHTR (2) - opencb HASTE H20URINE DUMP HTRS(2)- opencb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANMN BUS TIE (2) - ONTVC SERVO PHR 1 - AC1MNAGMBL MTR (4) - START

p41 - RCS THRUSTINGV37E 41E

23 F 50 18 REQ MNVR TO LCL HORIZ (HDS ON)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CMCAUTOPRO To 24

(gtfANDAP) BMAG MODE (3) - RATE 2SC CONT - CMCHOLD

V62EMNVR To 25

24 06 18 AUTO MNVR TO FDAI RPY

25 F 50 18 REQ TRIM TO LCL HORIZ (01deg)ALIGN SC ROLL

(AUTO TRIM) PRO To 24(BYPASS) ATT DB - MIN

RATE - LOHMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTlRATE 2

ENTR

550Om26 06 85

59middot2527

-32-

VGXYZ (1fps)RECHECK BORESIGHT STARTRANS CONIR PWR - on (up)EMS MODE - STBY (ver~fy)

EMS FliNC - bV SETVHF RNGSET (IV for SM BURN _EMS FliNC - bVS BD ANT - OMNI CSECS LOGIC (2) - ONMSFN conhrm Go for PYRO ARMSECS PYRO ARM (2) - ARMCM RCS LOGIC - ON (ver~fy)

DSKY BLANKS

593028 16 85 VG XYZ (AVE G ON) (lfps)

RHCs amp THC - ARMEDLIMIT CYCLE - OFFTAPE RCDR - CMD RESETHBREMS MODE - NORMAL

000029 F 16 85 REQ NULL VG XYZ (lfps)

BURN EMS bV CTR TO ZERORESET DET amp COUNT UP

If SM ONLY burn go to step 32THC - LOCKEDSC CaNT - SCSFREERATE - HIGHPRIM GLY To RAD - BYPASS (ver~fy)

MN BUS TIE (2) - ON (ver~fy)

CMSM SEP (2) - on (up)CSMLM FNL SEP (2) - on (up) (verify)CampW MODE - CMRCS TRNFR - CMCM RCS LOGIC - OFF

Momtor VM ABIf lt25 vdc go to EMERGPOWER DOWN Pg E6-l

V63E

If CMC NO GO FDAI SOURCE - ATT FDAI SEL - 1 or 2 ATT SET - GDC

SET

-33-

~Uili ATT PITCH - ACCEL CMDFDAI SCALE - 55MNVR TO CM BURN ATT (NULL ERR NEEDLES)

R 0degPY --00--

30

31

CM RCS BURNRHC III-ContJnuous PJtch DownRHC HZ-Module PJtch to null needlesBURN VGZ TO ZERO

If only 1 RHC Pulse + P=5deg from retro att MaJnta~n rates lt3degsec

BURN COMPLETION ATllV CTR= or DET= _

V8ZE

32 F 16 44 HAHPTFF (1nmffiJn-sec)Check HP-

If gt Pad data contJnue burnuntJ1 lt Pad

PRO

33 F 16 85 VGXYZ (Ups)Read VG resJduals to MSFN

(HYBRID) PRO to 34(SM ONLY BURN)

PROF 37 ODE

EI-1500 V37E 47EF 16 83 twx Y Z (Ups)

SC CONT - SCSFREEMAN ATT (PITCH) - RATE CMDRATE - HIGHPRIM GLY To RAD - BYPASS (verJfy)MN BUS TIE (2) - ON (verJfy)CMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verJfy)Campl MODE - CMRCS TRNFR - CMCM ReS LOGIC - OFFSECS PYRO ~I (2) - SAFE

-34-

PROMonitor VMAB

If lt25 vdc go to EMERGPOWER DOWN

34 F 37 OOEPCM BIT RATE - LOWATT DB - MAXEMS MODE - STBYEMS FUNC - OFF

Go To EARTH ORBIT ENTRY pg _--40-__

-36-

8 SPS THRUSTING PREPCYCLE CRYO FANSSPS GAGING - ACI (ver~fy)

PUG MODE - NORM (venfy)BMAG MODE (3) - RATE 2tv CG - CSMCMC MODE - FREEAUTO RCS SEL (16) - MNA or HNB

(hftoff conbg)SC CONT - CMCAUTO

9 MNVR TO PAD BURN ATTV62E

10 V49E

11 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLESPRO

12 F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) PRO(HAN) SC CONT - ses

MNVR to 14

06 18 AUTO MNVR TO FDAI RPY ANGLES13

14 F 50 18 REO TRIH TO FDAI RPY ANGLES(TRIM) Go to 12(BYPASS) ENTR

15 BORESIGHT STAR CHECK

16 V37E 40EOPT PWR - OFF

17 F 50 18 REQUEST MNVR TO FDAI RPY ANGLES (01deg)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CHCAUTOPRO to 18

(MANDAP) BMAG HODE (3) - RATE 2SC CONT - CMCHOLDMNVR to 19

(HANseS) se eONT - sesMNVR to 19

-35-

54 NORMAL DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL ~V

1 V37E 30E

2 F 06 33 GETI (hrm~nOlsec)

(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

3 F 06 81 ~VXYZ (LV)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

( lfps)

4 F 06 42 HAHP~V (1nmlfps)Record W

(ACCEPT) PRO -----(REJECT) Rese1ect P30 or P27 Load new pa~am

5 F 16 45 MTFIMGA (marksmln-secOldeg)MGA -00002 If ~ lMU not a1~gned

SET DETPRO

6

7

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY v1v - OFFCAB PRESS REL v1v (2) - NORMcb ELS (2) - close (verify)cb SECS ARM (2) - close (ver~fy)

cb SECS LOGIC (2) - close (verlfy)AUTO RCS SEL CM (12) - ~mA or MNB

(l~ftoff conf~g)

ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM AampB - off (ctr)

18

-37-

06 18 AUTO MNVR TO FDAI RPY ANGLES (01 0)

19 l 50 18 REOUEST TRIM MNVR TOALIGN SIC ROLLGDC ALIGN

FDAI RPY ANGLES(010

)

+54-00m(-06-00)

TIG-5mJn

5500m(-0500)

TVC CHECK amp PREPcb STAB CONT SYS (all) - closecb SPS (12) - closeATT DB - MINRATE - LOl~

LIMIT CYCLE - ONMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE 2ROT CONTR PWR DIRECT (2) - OFFSCS TVC (2) - RATE CMD

If SCS SCS TVC (2) - AUTO SC CONT - SCS ~

TVC GMBL DRIVE PampY - AUTOMN BUS TIE (2) - ONTVC SERVO PWR 1 - AC1MNA

2 - AC2MNBTRANS CONTR PWR - ONROT CONTR PWR NORMAL 2 - ACRHC 2 - ARMED

HORIZ CHK - HorJz on 12deg wJndmlmark (LJffiJt +3 0 PNGCS GONO GO)

If NO GO set tw 180 0 180deg0 0

Track horJz wJth 24deg wJndow markAt TIG-2 mJn Ahgn GDC

PRIMARY TVC CHECKGMBL MOT P1-Y1 -STARTON(LMP confJrm)

If SCS verJfy Thumbwheel TrJmTHC - CWVenfy NO MTVC

SEC TVC CHECKGHBL MOT P2-Y2 -STARTON(LMP confJrm)SET GPI TRIHVenfy MTVCTHC NEUTRALGPI returns to 00 (CMC) or trJm (SCS)ROT CONT Pl~ NORM 2 - ACDC

(TRIM) Go to step 17(BYPASS) BMAG MODE(3) - ATTIRATE2 (ver1fy)

ENTR

-38-

20 F SO 25 00204 GMBL TEST OPTION(ACCEPT) SC CONT - GMC (ver~fy)

PROMonitor GPI Response

0020-2000020-200Tr~m

TEST FAIL SC CONT - SCS SCS TVC (2) - AUTO

(REJECT) ENTR

21 06 40 TFIVG~VM (m~n-sec1fps)

PROG ALM - TIG s1~pped

V5N9E 01703

KEY RLSE To 21 ROT CONTR PWR DIRECT (2) - MNABSPS He v1vs (2) - AUTO (ver~fy)

LIMIT CYCLE - OFFFDAI SCALE - SOIScb SPS P2Y2 - open (for cr~t burn)

5800(-02 00)

5925(-0035)

59middot 30(-0030)

06 40

59XX(-OOXX)

AV THRUST A(B) - NORMALTHC - ARMEDRlIC (2) - ARMEDTAPE RCDR - GID RESETHBR

DSKY BLANKS

(AVE G ON)EMS MODE - NORMAL

TFIVG~VM (m~n-seclfps)

CHECK PIPA BIAS lt2fps for 5 sec

ULLAGE AS REQ

IF NO ULLAGE DIR ULLAGE PB - PUSH~

CONTROL ATT WRlIC MONITOR AVM (R3) COUNTING UP

5955(-0005)

F 99 40 ENG ON ENABLE REQUEST(AUTO IGN) PRO AT TFI gt0 sec(BYPASS IGN) ENTR to 24

22 0000 IGN

-39-

If SCS - THRUST ON PB - PUSH

06 40 TFCVG~VM (m~n-seclfpslfps)

~F 97 40 SPS Thrust fall ~

~(RESTART) PRO To IGN (RECYCLE) ENTR To TIG-05 sec

SPS THRUST LITE - ONMONITOR THRUSTING

Pc 95-105 pSlaEMS COUNTING DOWNSPS IN3 v1vs (4) - OPENSPS He v1vs tb (2) - graySPS FUELOXID PRESS - 175-195 pSlaPUGS - BALANCED

PROG ALARM V5N9E 01407 VG INCTHC - CW FLY MTVC

ECOEMER SPS CUTOFF J

AV THRUST (2) - OFF

23 F 16 40 TFC(STATIC)VG~VM (mln-seclfps)~V THRUST AB - OFF

SPS IN3 v1vs (4) - CLOSEDSPS He tb (2) - bp

cb SPS P2Y2 - closed (verlfy)TVC SERVO PHR - AC1MNA (venfy)TVC SERVO PWR 2 - OFF

PRO

24 F 16 85 VG XYZ(CM) CUps)NULL RESIDUALSRECORD ~V CTR amp RESIDUALS I1VCEMS FUNC - OFF VGXEMS MODE - STBY VGYBMAG MODE (3) - RATE 2ATT DB - MAX VGZTRANS CONT PHR - OFF

PRO

25 F 37 V82E

26 F 16 44 HAHPTFF (lnmm~n-sec)

R3-59B59 HP gt494 nmPRO

27 F 37 OOE

-40-

55 EARTH ORBIT ENTRY

1 Venfy CMSMR __

P_shyY_-

SEP ATT(180deg)

(0deg )

2

3

4

EMS INITIALIZATIONEMS FUNC - RNG SETSET RNG TO PAD DATA RNGEMS FUNC - VA SETSlew scroll to pad data VIOEMS FUNC - ENTRY

RSI ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on(up)GDC ALIGN PB - PUSH amp HOLDYAW tw - Pos1tion RSI thru 45deg amp

back to LIFl UPGDC ALIGN PB - RELEASEEMS ROLL - OFFAl1gn GDC to lMU

PWR REDUCT (Norm Deorb Only)HGA PWR - OFFFC PUMPS (3) - OFFVer1fy s1ngle suit compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - Lowcb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2)-openlOb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MAN

-41-

P61 - ENTRY PREP

5 V37E 61E05 09 01427 - ROLL REVERSED05 09 01426 - IMU UNSAT

6 F 06 61 IMPACT LAT LONG liDS UPDN (+-)(01 0

010

+00001)

PRO

PAD VALUESLATLON==G------liDS UP DN _

7 F 06 60 GMAXV400KGAMMA EIRecord

GMAXV400K----GAMMA EI _

PRO

8 F 06 63 RTOGO (1nm) PAD _VIa (fps) PADTFE (mln-sec) ----Compare wlth MSFN for PGNS GONO GONO COMM SET RTOGO amp VIO IN EMS amp

INITIALIZE(ACCEPT) PRO(RECALC) V32E to 8

-42-

P62 - CMSM SEP amp PRE-ENTRY MNVR

9 F 50 25 00041 REQUEST CMSM SEPSC CONT - SCSFREEYAW - 45deg out-of-plane (left for RCS

nght for SPS)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE2PRIM GLY to RAD - BYPASS (verlfy)SECS LOGIC (2) - on (up)MSFN conflrm GO for PYRO ARMSECS PYRO ARM - ARMMN BUS TIE (2) - ON (verlfy)CMSM SEF (2) - ONCSMLM FNl SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 pSlaCM RCS LOGIC - OFFSECS PYRO ARM - SAFEMonltor VMAB

If lt25vdc go to EMERG POWERDOWN Pg E6-1AUTO RCS SEL AlC ROLL (4) - OFFAUTO RCS SEL CM 2(6) - OFFAUTO RCS SEL CM 1(6) - MNA or MNBYAW back to 00

PITCH TO ENTRY ATTROLL 0deg (LIFT UP)PITCH - HORIZ on 317deg MARK (400K)YAW 00

ATT DB - MAXMAN ATT (PITCH) - ACCEL CMDEMS DATA - VerifyEMS FUNC - ENTRY (verlfy)EMS MODE - NORMALMAINTAIN HORIZ TRK

PRO (Act ENTRY DAP)

10 F 06 61 IMPACT LAT LONG HDSDN(010 010 -00001)

PRO

11 FOSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axlS beyond 45deg of Vel vector)

-43-

P63 - ENTRY INIT

12 06 64 GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PWR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRHORIZ CKP~tch error needle goes toward

zero approach~ng 05G t~me

MAN ATT (PITCH) - RATE CMDIf CMC ~s GO

BMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS FLY BETA If CMC NO GO ~

SC CONT - SCS~

FLY EMS RCS Deorh Roll HDS UPTRACK HORIZ w~th 29deg w~ndow mk

P64 - ENTRY POST 05G

13

05G t=elt+0___)

06 68

RTOGO AT 05G AGREES WITH EMS - venfyHORIZ CK05E Lt - on (EMS start)

No EMS start w~th~n 3 secsEMS MODE - BACKUP VHF RNG 05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds L~ft DN

NNVR L~ft DNEMS GONO GO

G-V Plot w~th~n llm~ts

Rng ctr dwn 60 + 7 durlng 10 sec per~od

Mon~tor G-meter forconvergence wlth pad data (Do)

(Vlt27K fps) Go To 17

-44-

P65 - ENTRY - UP CONT (Vgt27K fps)

14 F 16 69 BETA (01deg)DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT~

SC CONT - SCS FLY EMS

PRO

15 06 68 BElA VI HOOT (01deg fpsfps)(VltVL +500 fps amp RDOT Neg) Go To 17

p66 - ENTRY - BALLISTIC (DltDL)

16 06 22 DESIRED GMBL ANGLES RPY (01deg)Mon~tor hor~z +12deg of 317deg mark

P67 - ENTRY - FINAL PHASE (02G)

17 0666 BETACRSRNG ERRDNRNG ERR (Oldeglnmlnm)KEY VERBRecord DNRNG ERR _KEY RLSEL~m~t +100nm from PAD DRE

Mon~tor l~ft vector on RSI amp FDAIF 16 67 RTOGOLATLONG (Vre1=1000fps)

(lnm 010 01deg)SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOlfflMon~tor altimeter

Go To EARTHLANDING pg _I4L5__

-45-

56 EARTHLANDING

90K STEAM PRESS - PEGGED50K CABIN PRESS REL vIv (2) - BOOSTENTRY

SECS PYRO ARM (2) - ARM

40K(90K + 63s)

CM UNSTABLE RCS CMD - OFF ~ 40K APEX COVER JETT PG-PUSH DROGUE DEPLOY PG - PUSH (2 secafter apex cover Jett)

30K ELS LOGIC - ON (up)ELS - AUTO

24K RCS hsable (auto)(90K+92s) RCS CMD - OFF

Apex cover Jett (auto)APEX COVER JETT PB - PUSH

(WAIT 2 SECS)Drogue parachutes deployed (auto)

DROGUE DEPLOY PB - PUSH~

If Drogues FallELS - ~ ~Stablllze CM 5K MAIN DPLY PB - PUSHELS - AUTO

235K Cabln Pressure lncreaslng (Drogues + 50s)If not lncreaSlng by 17K CABIN PRESS REL vlv (RR) - DUMP

-46-

10K Maln parachutes deployedMAIN DEPLOY PB - PUSH (wlthln 1 sec)VHF ANT - RECYVHF AMA - SIMPLEXVHF BCN - ONCABIN PRESS REL v1v (2) - CLOSEDIRECT 02 vlv - OPENCM RCS LOGIC - on (up)CM PRPLNT - DUMP (burn audlb1e)Monltor CM ReS 1amp2 for He press decrease

NO BURN or PRESS DECREASE USE BOTH RHCs DO NOT FIRE PITCH JETS

CM PRPLNT-PURGE (to zero He press)CM RCS He DUMP PB - PUSH RHC (2) - 30 sees NO PITCH k

STRUT LOCKS (2) - UNLOCK

cb FLT amp PL BAT BUS ABampBAT C (3) - closecb FLT amp PLT MNA amp B (2) - opencb ECS RAD HTR OVLD (2) - opencb SPS PampY (4) - open

3K CABIN PRESS REL v1v (RH) - DUMP (after purgecompleted)

FLOOD Lts - POST LDGCM RCS PRPLNT (2) - OFFROT CONTR PWR DIRECT (2) - OFF

800 CAB PRESS RELF vlv - CLOSE (latch off)MN BUS TIE (2) - OFF

AFTER LANDINGcb MAIN REL PYRO (2) - closeMAIN RELEASE - on(up)

Go to POSTLANDING pg _47L-__

I

2

3

-47-

57 POSTLANDING

STABILIZATION VENTILATION COMMUNICATIONS

DIRECT 02 vlv - CLOSE

Stablllzation after landlngELS - AUTO (verlfy)cb MAIN REL PYRO (2) - close (venfy)MAIN RELEASE - on (up) (verlfy)S~CS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb BAT RLY BUS (2) - open

No contact w1th recovery forcesVHF AM AampB - off (ctr) ~

VHF AM Rev ONLY - A cb PL VENT - closecb FLOAT BAG (3) - closecb UPRIGHT SYS COMPRESS (2) - closeIf Stable II

FLOAT BAG(3)-FILL t1ll 2 m1n afterupr1ght then - OFF

VHF AM AlB amp BCN - OFF whlle lnvertedIf Stable I

After 10 M1n Coollng Per1odFLOAT BAG (3) - FILL 7 mln then OFF

Post Stab1lizat1on And Ventllat10nPL BCN LT - BCN LT LOWPL VENT vlv - UNLOCK (Pull)Remove PL VENT Exh CoverPL VENT - HIGH or LOWPL DYE MARKER - ON (swlmmer comm)Release foots traps and_restralntscb MNA BAT BUS A amp BAT C (2) - opencb MNB BAT BUS B amp BAT C (2) - opencb FLT amp PL BAT C - opencb PYRO A SEQ A - opencb PYRO B SEQ B - open

EACH HR - CHECK DC VOLTSgt 275 V If Notmiddot cb FLT amp PL-BAT BUS AampB (2) -open cb FLT amp PL BAT C (1) - open GO TO LOW POWER CHECKLIST

Unstow and lnstall PLV DISTRIB DUCTDeploy grappllng hook and 11ne 1f req

4

-48-

Post Landing Communlcatl0nsVHF ANT-RECY (venfy)VHF BCN - ON (verlfy)

If no contact ~lth recovery forcesperform VHF BEACON Check

MONITOR VHF BEACON transmlSSlonnth VHF AM B Rcvr andor Su)vlval

TransceiverkVHF Beacon not operatlng ~connect Surv~val TranscelVer to antcable behlnd VHF ant access pnland place radio ln BCN mode

LOW POHER CHECKLISTVHF BCN - OFFVHF AM (3) - RCVFLOOD Lts - OFFVHF AM AampB - off (ctr)VHF AM RCV ONLY - A (venfy)COUCH LIGHTS - OFFPOSTLANDING VENT SYS mlnlmlze useSURV RADIO - plug mto VHF BCN ANT cableconn behind VHF ant acess pnl amp turn radloon l-n BCN mode

EGRESS PROCEDURES

CMPCDRLMPCDR

CMPCDRCMP

LMPLl1PCDR

STABLE IDlsconnect Umblll-calsNeck darn onCenter couch - 270 0 positionArmrests stowedConnect raft to SIC l-f desl-red wlth

green lanyardConnect raft ~hl-te lanyards to SUltS amp

lnflate water wlngs when eXltl-ngHATCH PISTON PRESS vlv - PRESS (Outbd)Slde Hatch openedPL VENT - OFFcb Pnl 250 (all) - openEgress with 11feraftPut hardware klt outEgress

or CDIPALL

CMF

CDRCMF

CDR

LMF

CMFCMP LMFCMP

UlP

CDR

-49-

STABLE IIcb CREW STA AUDIO (3) - openD~sconnect umb~1~ca1s

Release foots trapsRelease restra~nt harnessCouch seat pans (3) - 170 0 pos1t10nArm rests stowedSurv1va1 k~ts removed from stowageConnect life raft ma~n1~ne to CDR or SicConnect f~rst wh~te lanyard from

11fe raft to suitConnect th~rd wh~te lanyard from

l~fe raft to SU1tConnect rucksacks together to yellow

lanyard on raft bagPRESSURE EQUALIZATION vlv - OPENRemove and stow fwd hatchEX1t feet f1rst w1th rucksacks when clear

of siC 1nflate water w1ngs and raftExit feet f1rst when clear of SiC

1nflate water w1ngsEX1t feet f1rst when clear of sic

1nflate water w1ngs

-50-

60 TLI ABORTS

TLI Aborts are conta~ned ~n the ESD s~nce the bulk of the funct~ons

concern entry preparat20ns and performance Th~s allows a s2nglesource of procedures for procedure rev2ew val~dat~on checkout andtra~n~ng These procedures ~ncorporate TLI preparat20ns as found ~n

reference 6 w~th the TLI Abort Procedures and these t~e 2nto normallunar return Entry Procedures found ~n sect20n 5 The guidel~nes

for th~s cont2ngency are spec2f2ed 2n reference 7

In2t2al preparat~ons for TLI pos2t20n the necessary system sW2tches2n add~t~on to perform~ng an EMS ~V test and a GDC al~gnment Afterthe DET ~s set for mon2tor2ng TB6 the CMP ~ncreases the 12ght levelof the LEB DSKY to max~mum and returns to the h2s couch Th2s 2Sdone so that the LEB DSKY can be observed ~n the event sunl~ght orreflect20ns wash out the ma2n d2splay panel DSKY dur2ng cr2t2calmaneuvers The crew then straps ~n and prepares for mon2tor~ng TB6as 2nd2cated by the SII SEP L~te The t2mes se~uence of procedures2S keyed on th~s d~splay and ~ncludes the DET START funct~on andSIVB IGNITION Dur2ng the burn the crew mon2tors the FDAIs foratt~tude excurs20ns and abnormal rates report~ng status checks toM~ss2on Control at d2screet t~mes dur2ng the maneuver Upon SIVBSHUTDOWN the eMP records the DSKY d~splayed performance parametersand awa2ts ground conf2rmat~on

The rat~onal for TLI aborts ~s descr~bed 2n reference 7 A summar2shyzat20n 2S extracted to prov2de background and gu2de12nes 2n th2sdocument The abort procedures cover aborts 10 m2nutes after conshyt2ngent SIVE shutdown and aborts 90 m2nutes after normal SIVE shutshydown t2me

The 10 m~nute TLI abort ~s des2gned to be used dur~ng TLI ~n theevent a spacecraft problem develops Wh2Ch can result 2n catastrophe2f ~mmed~ate act~on 2S not taken If the s~tuat20n perm~ts the crewshould always allow the SIVB to complete TLI at wh~ch t~me the groundand crew can perform a malfunct~on analys~s to determ~ne ~f an abort~s adv~sable If a fa~lure occurs that necess2tates the shutdown ofthe SIVB and the ~u~ck return of the crew to earth th~s abort ~s

des~gned to be as ~nsens~t~ve to execut~on errors as poss~ble andst21l be targeted to m2dcorr2dor The burn att~tude w~th the f~ed

hor~zon reference ~s a constant value for any shutdown t~me Theburn durat~on 2S a funct20n of shutdown t2me and 2S ava21able fromcrew charts S~nce the pr~mary purpose of th~s abort ~s to returnto earth as qU2ckly as poss2ble there are no restr2ct20ns as toland~ng locat~on However ~f the t~me to EI is greater than abouttwo hours a midcourse correct20n should be ant~c~pated

The 90 m2nute TLI abort 2S to be used 2f a cr2t2cal subsystem malshyfunct~on ~s determ2ned and the dec2s~on to abort ~s made after the

-51-

TLI cutoff and before TLI cutoff plus approxlmately 80 m1nutesTh1S allows suff1c1ent separatlon and procedural t1me to set upfor the SPS deorb1t burn performed at about TLI + 90 Note thatgenerally the deorb1t burns w1ll be performed a fe11 m1nutes beforeTLI + 90 accord1ng to crew charts shown In reference 8 The no-comm except10n requ1res that 90 m1nutes be the 1nput t1me of 19n1shytlon for P-37 (onboard return-to-earth abort program) so that onshyboard calculatlons can correspond w1th ground calculat10ns to computethe CM land1ng p01nt Th1S TLI abort lS des1gned so that returnfl1ght t1me does not exceed 18 hours and abort ~V does not exceed7000 fps ThlS abort can be performed uSlng chart ~Vs and attltudesand the earths hor1zon serves as a suff1c1ent reference The maneushyver lS targeted to ach1eve the mldcorr1dor entry target Ilne andtlmed to result 1n a deslgnated recovery area

It 1S ObV10US for abort deC1S1ons early 1n the TLI + 90 m1nute t1meshyframe that a GampN SPS burn should be performed In order to keep theTLI abort procedures cons1stent and w1th emphasls on slmpl1c1ty theprocedures here reflect a SCS SPS abort burn to cover the full abortdec1s1on t1meframe

A m1dcourse correct1on for corr1dor control after a TLI abort may bedeS1red 1f the SPS burn d1d not meet expectat1ons The TLIabortprocedures 1n th1S sect10n adapt to the normal lunar return tlmel1neand procedures pr10r to the f1nal MCC

-52-

61 TLI PREPARATION PROCEDURES

GET = 150

CRO AOS(___)

CRO LOS( )(22142)

5100

Don Helmets amp Gloves

XLUNAR - INJECT (verify)EDS PWR - on (venfy)EMS FUNC - OFF (verlfy)EMS MODE - STBYEMS FUNC - IW SETVHF RNGEMS MODE - NORMALSet ~V indo to +15868 fpsEMS FUMC - ~V Test

SPS THRUST Lt - onoff (10 sec)~V lnd stops at -01 to -415

EMS MODE - STBYEMS FUMC - ~V SETVHF RNGSet ~VC

EMS FUNC---~~V=----

GDC ALIGNFDAI Select - liZcb SECS LOGIC (Z) - close (verify)cb SECS ARM (Z) - closeSECS LOGIC (Z) - on (up)MSFN Conflrm GO for PYRO ARM (If pass)SECS PYRO ARM (Z) - on (up)TRANS CONTROL PWR - ONROT CONTR PWR NORMAL (Z) - ACDC(verlfy)ROT CONTR PWR DIRECT (Z) - MNAMNBLV INnGPI - SIISIVB (venfy)LV GUID - IU (venfy)cb DIRECT ULLAGE (Z) - closedSet EVENT TIMER to 5100Begin MONITOR For TB6

CMP to Couch

TB 6 - SII SEP Lt on (TIG-9 mln 38 sec)KEY V83E

SET ORDEALFDAI Z ORB RATE at 180 0 0SII SEP Lt out (38 sec later)Start DET COUNTING UPSC CaNT - SCS (verify)MONITOR LV TANK PRESS

~P lt 36 psid (OXID gt FUEL)~P lt Z6 psid (FUEL gt OXID)

EMERGENCY CSMLV SEP UP TLM CM - BLOCK (verify)UP TLM IU - BLOCK (venfy)

-53-

+45degPY))0middot sec PY

lOK nmltHAlt25K nm

Two phas~ng mnvrs two SPS mnvrs to circular~ze at 150 nmearth orb~t

CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ssion 4K nmltHAltlOK nm CSM amp1M - Two phasing mnvrs two SPS mnvrs to circularize at 150 nm earth orb~t CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ss~on

CSM amp 1M - Two phas~ng mnvrs APS burn todepletion th~rd phasing mnvrSPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn tosem~sync orb~t

25K nmltHAlt40K nm CSM amp 1M - Two phasmg mnvrs APS burn to depletion third phas~ng mnvr SPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn to sem~sync orbit HA)40K nm DPS ava~l - DPS LOll circularize with SPS

DPS not ava~l - Lunar flyby or CSM only to lunar orbit (if reqd gtV lt4000 fps)

V37E 47E (check b~as) Record -=--rshy(Limit 98 fpsmm)

( 1fps)tVXYZN62EVIHDOTHPAD (fpsfpslnm)MONITOR VI ( ) at ECO

SCS TVC SERVO PWR 1 - ACIMNA2 - OFF

TAPE RCDR - CMD RESETHBREMS MODE - NORMAL

SIr SEP Lt - ONTLI Inhib~t S~gnals w~11 not be honored after 5942

SIVB ULLAGE BeginsSII SEP Lt - off (TIG - 18 sec)SIVB FUEL LEADSIVB ULLAGE d~scont~nues

LV ENG I Lt - onSIVB IGNITION ( GETI)LV ENG I Lt - off - -shyMONITOR THRUST amp ATTITUDEMONITOR LV TANK PRESSSIVE ECO (Lt on) (BEGIN TB7)

EMER SIVE CUTOFF AT 6 SEC PAST BURN TIME IF VI ATTAINEDTHC CCW ampNEUTRAL IN 1 SEC or SIISIVB sW - LV STAGEPremature Shutdown HAlt4K nm CSM amp 1M -

5700

58205836

F 16 835800

F 16 62

5838594259525955595900000002SUNRISE(___)

HAW AOS(__=_) KEY VERB (freeze d~splay)

SIVB ATT HOLD 20 sec amp BEGIN VENTINGSIVB NNVR TO ORB RT (HDS DN) (3middot sec)

Record VI -c---HDOT _

HPAD _

KEY RLSEF 16 62

F 16 83

HAW LOS(__=-)

KEYmiddotRLSE~VXYZ (lfps)

Record ~VX---_

~vy

WZ--

AVC---_

TAPE RCDR - off (ctr)EMS MODE - STBYEMS FUNC - OFFSECS PYRO ARM (2) - SAFE

PRO

BURN STATUS REPORT

____--~TIG

BT------VGX____-R

-----P----_Y

REMARKS

_____VI

______--HDOT______--H______---AVC______---FUEL_______OXID

_______UNBAL

F 3708=00 OOEGOS AOS CMP TO LEB

(-=-=-)

0000

0003

0005

0014

0100

-55-

62 TLI 10 MIN ABORTSECS LOGIC (2) - on (up)SECS PYRO ARM (2) - ARM

TRANS CONTR - CGH (4 sec) amp +XDET RESET (verlfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS GMD-ON

TRANS GONTR - neutral then +X for10 sec

SIVBGPI s~ - GPIExcesslve rates 6V THRUST A - NORMAL SPS THRUST - DIRECT When rates damped 6V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

TRANS CONTR +X - OFFV37E OOE

PITGH UP to LOGAL VERT (+X axlSto~ard the earth)

RATE - LOWBMAG MODE (3) - ATTIRATE 2EDS PHR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SEGS ARM (2) - opencb EDS (3) - open

TRANS CONTR -X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (180deg)P (199deg)Y (0deg)

RETRO UPDATEGETI _

JV _VG

Jtb ---GET 400K _

05G _GET DROGUE _

ENTRY P _R _

Y_--

0945

-56-

ALIGN HORIZ ON RET +1 MKGMBL CHECK (T11lle Pentattlng)MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conflnn)cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FUMC - JV SETVHF RNGSET JV from chartE~S FUMC - JVEMS fODE - NOIDlAL

lV THRUST A - NORMALV37E 47E (THRUST fONITOR)

F 16 83 lVXYZ (1 fps)

0950

1000

NOTE For aborts durlng 1st mln of TLIKEY V82E F 16 44 (HaHpTff)Burn untll Hp lt 19NM

TRANS CONTR +X

THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN JV reqdJV THRUST (2) - OFFReport cutoff

cb SPS P2 Y2- closeGfBL MTRS (4) - OFF (LMP Confinn)TRANS CONT PWR - OFFTVC SERVO PWR (2) - OFFMN BUS TIE (2) - OFFcb SPS P1amp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREIf est time to EIltOl5500 omlt fCC andenter the SUPERCIRC CKLIST as early as pos-slb1e Pg ~2~3~ __If est time to EI)Ol5500 anticlpate afCC Enter the ENTRY PREP CKLIST at step 9pg 18

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

-2tl C

l I W gt- ~-4

z laquo I I- 0 -6

l- I J u gt- ~-8

z w w -10

~_ONSANT

9O

VER

SHO

OT

BOU

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LIF

TV

EC

TOR

OR

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TATI

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LIN

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SH

ALL

OW

TAR

GE

TLI

NE

STE

EP

TAR

GE

TLI

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gU

ND

ERSH

OO

TBO

UN

DAR

Y

RE

EN

TRY

CO

RR

IDO

R

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26

28

30

32

34

RE

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TRY

VE

LOC

ITY

VE

1-F

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6-i

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73

8X

03

-i- rtREQUIRED PITCH GIMBAL ANG LETO OBTAIN HOR-IZON AT 317

DEGREES IN wiiiiDOW

260

z~I- ~ i5 24000

1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

-I

-1-

NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

I LU HD~-

LUHD

lt0 120UJ0

~

80 HOLD PRESENT TRIMgt LU HD013

~Y~HOIgtlt

TOP OF WINDOWa 40to

31 7 SCRIBEaaI

80 TTOM OF WINDOWi= 0

0--ltoa

-40t-z

~~~Uw w u lt0 -80

HOLO PRESENT TRIlJCl

LOHU0 lt0

J gt -120 HOLD 059 TRIMlt0 z

LDHUlt0 FIELD OF VI S10 NLDHU LIFT-DOWNHEADS -UPLUHD LIFT-UP HEADS-DOWN

~~H~-160 q - P63 LIMITI- NOrE-VALIO ONLY FO~t~--

LUNAR RETURN VELOCITY

plusmnl8020 244middot 8 12 16

TIME TO 400K FT ALTITUDE-MIN

4

P37

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-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 20: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

-17-

5 0 DETAILED ENTRY PROCEDURES

In order to comblne slmilar procedures that are common to lunar returnentrles and earth orblt entrles the followlng procedures are dlvldedlnto categorles that allow a mlnlmum of dupllClty ThlS provldes asmaller tralnlng package and more closely resembles the onboard crewcheckllst when comparlson lS necessary

51 Entry Preparatlons for Superclucular and Earth Orbltal Entrles

1~e entry preparatlons are comblned In these procedures andsteps pecullar to elther superclrcular or earth orbltal entrlesare labeled accordlngly The tlme llstlngs In thlS sectlon areappllcable to only superclrcular entries Slnce the earth orbltalentry tlmellne lS a functlon of several varlables as descrlbedIn sectlon 40 and reference 5

-18-51 (Contlnued)

VEHICLE PREPARATION

l-

2

3

4

5

6 -0600h

7 -0535h

8

9

10 -0430h

INITIAL STOWAGE COMPLETED

CMC amp ISS START UP

SCS POWER UP

p51 - IMU ORIENTATION

LOAD DAPV48E 11102 01111 PRO ERO PRO

LAST MCC DECISION

NO COMM - P52 amp NAV SIGHTINGSNOMINAL - P2337 ONBOARD COMPARISON

DON MAE WESTS amp FOOT RESTRAINTS

VHF AM A - SIMPLEX

P 27 (SV REFSMMAT) MNVRamp ENTRY pAD UPDATES

11 -0415h P52 - IMU REALIGN(___) (OPTION 1)

12 P37 (NO COMM ONLY)

13

14

ECS CKS02 SUPPLY REFILLECS Monitor CkEVAP H20 CONT (2) vlvs - AUTOSUIT HEAT EXCH SEC GLY - FLOW

EPS CKS 1 3 4 (5 If reqd)

15 SPS CK (If req d)

16

17

18

RCS CKSSM RCS MOUlt CkCM RCS MOUlt Ck

CampW SYS CK

CMC SELF CK

19

20 -0345h

-03l5h-0300h

21

22

22A

-19-

DSKY COND LT TEST

MIDCOURSE MANEUVERP30 - EXT rVP404l - SPSRCS THRUSTINGMIDCOURSE (17) BURN

NO COMM NAV SIGHTINGS

ffiVR TO ENTRY ATT (Superc1rc only)V62E

V49E

22B F 06 22 DESIRED FINAL GMBL ANGLESLOAD ENTRY ATT PAD ANGLESPRO

22C F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) SC CONT - CMC

BMAG MODE (3) - RATE 2CMC MODE - AUTO

PRO(~N) SC CONT - SCS

MNVR to 22E

22D 06 18 AUTO MNVR TO FDAI RPY ANGLES

22E F 50 18 REQUEST TRIM(TRIM) Go to 22C(BYPASS) ENTR

23 -200hr BORESIGHT amp SXT STAR CHECKOPT MODE - CMCOPT ZERO - OFF

V41 N91E

F 21 92 SHAFT TRUNLoad SXTS angles

41 OPTICS DRIVE

CHECK SXT STAROPT ZERO - ZERO

CHECK BORESIGHT STAR (If ava11)

24 -0135h

25(___)

26

27 -0115h

-20-

P52 - lMU REALIGNRecord gyro torqu~ng anglesRp~----

YIf-7gt-Lno--re-c-ycle PS2If conflrmed use SCS for EMS entry

GDC ALIGNIf drlft gtLOohr change ratesource

FINAL STOWAGEOPTICS (except for hybrid)ORDEALGLY TO RAD SEC - BYPASS (verlfy)CooL pnl lnstalledY-Y struts (2) extendedStow Data Box R-12

EMS CHECKEMS FUNC - OFFcb EMS (2) - closeEMS MODE - STBYEMS FUNC - EMS TEST 1 (walt 5 sec)EMS MODE - NORMAL (walt 10 sec)

Check ind lts - offRANGE lnd - 00Slew halr1ine over notch

In self-test patternEMS FUNC - EMS TEST 2 (walt 10 sec)

05G It - on (all others out)EMS FUNC - EMS TEST 3

05G It - onRSI Lower It - on (10 sec Qater)Set RANGE counter to 58 nm+OO

EMS FUNC - EMS TEST 405G It - on (all others out)G-V trace w~thin pattern to lwr rt

corner 9GRANGE lnd counts down to 0+02

EMS FUNC - EMS TEST 505G It - onRSI upper lt - on (10 sec later)RANGE md - 00SCrlbe traces vertlcal llne 9g to

022+01ALIGN SCROLL TO ENTRY PATTERN (on

37K ft sec hne)EMS FUNC - RNG SET

G-V scroll assy traces vert llne022g to 0+01

EMS MODE - STBY

28

29

30 -OllOh

-21-

~V TEST (Deorb~t only)EMS FUNC - ~V SETVHF RNGSET ~V ~nd to 15868 fpsEMS MODE - NORMALEMS FUNC - ~V TEST

SPS THRUST LT - onoff (10 sec)~V ~nd stops at -01 to -415

EMS MODE - STBY

PRIMARY WATER EVAP ACTIVATIONGLY EVAP H20 FLOW - AUTOGLY EVAP STH PRESS - AUTOPRI ECS GLY PUMP - ACI

CM RCS PREHEATNote If sys test mtr 5cd6abcd

all read 39 vdc (28degF) or moreom~t preheat

cb RCS LOGIC (2) - closeCM RCS LOGIC - ONUP T1M CM - BLOCK (ver~fy)

cb CM RCS HTRS (2) - closeCM RCS HTRS - ON (LMP Conf~rm)

(20 mlU or III lowest rdg lS39 vdc) (Moultor Maufpress for press drop)

31 (___) FINAL GDC DRIFT CK (If req I d)If drlft gtlOohr Suspect GDC Do not

use RSI amp FDAI 2

32 -OO5Om

33

34

35

TERM CM RCS PREHEATUP TLM CM - BLOCK (venfy)CM RCS HTRS - OFFCM RCS LOGIC - OFF

SYSTEMS TEST PANEL CONFIGURATIONSYS TEST METER - 4BRNDZ XPNDR - OPERATECM RCS HTRS - OFFWASTE H20 DUMP - OFFURINE DUMP - OFF

LEB LIGHTING - OFF

SEC WATER EVAP ACTIVATIONGLY To RAD SEC vlv - BYPASSSEC COOL EVAP - EVAPSEC COOL PUMP - AC2

36

37

38 -OO45m

-22-

PYRO BATT CKcb PYRO A SEQ A - close (ver~fy)

cb PRYO B SEQ B - close (verify)DC IND - PYRO BAT A(B)

~If PYRO BAT A(B) lt 35 vdc cb PYRO A(B) seq A(B) - open~

PYRO A(B)BAT BUS A(B)TO PYRO~MN BUS TIE - close

cb MNA BAT C - closecb MNB BAT C - closeDC IND - MNBPNL 8 - All cbs closed except

PL VENT - open (ver~fy)

FLOAT BAG (3) - open (ver~fy)

DOCKING PROBE (2) - open (verlfy)EDS BAT (3) - open (ver~fy)

CM ReS HTRS (2) - open

CM RCS ACTIVATIONcb SECS ARM (2) - close (verlfy)cb SECS LOGIC (2) - close (verlfy)SECS LOGIC (2) - ONMSFN conflrm GO for PYRO ARM(~f poss)SECS PYRO ARM (2) - ARMCM RCS PRPLNT 1amp2 - ONCM RCS PRESS - ONRCS Ind sw - eMl then 2

He PRESS 3700-4400 pSlaMANF PRESS 287-302 pSla

SECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFF

P27 amp ENTRY PAD UPDATEGo To Entry Checkllst

Superclrc - pg ~2~3 _Hybnd - pg -----2~9L-__Normal Deorblt - pg __3L5L- _

-23-

52 SUPERCIRCULAR ENTRY

1 SET DET (up to ET)

2

3

4

5

3000(-30-00)

EMS INITIALIZATIONSET RNG TO PAD DATA RNGEMS FUNC - Vo SETSlew Scroll to Pad Data VIOEMS FUNC - ENTRY

RS I ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on (up)GDC ALIGN PB - PUSH amp HOLDYAW Tw - Pos~t~on RSI thru

45deg amp back to LIFT UPGDC ALIGN PB - ReleaseEMS ROLL - OFFA1~gn CDC to lMU

CM RCS RING A CKRCS TRNFR - CMcb CM RCS LOGIC MNB - openAUTO RCS SEL MNB (6) - OFFSC CONT - SCSTest R~ng A ThrustersSC CONT - CMCRCS TRNFR - SMAUTO RCS SEL (12) - MNAMNB

(hftoff conflg)cb CM RCS LOGIC MNB - close

OPTICS PWR - OFFCMP to COUCH

MN BUS TIE (2) - ONTAPE RCDR - REWIND

6 35middot0Om(-25middot 00)

-24-

SEPARATION CK LISTTVC SERVO PWR 1 - AClMNAcb ELS (2) - close (ver1fy)PRIM GLY TO RAn - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY vlv - OFFCAB PRESS REL vlv (2) - NORMGMBL MTRS (4) - STARTABORT SYS PRPLNT - RCS CMD (venfy)SM RCS PRIM PRPLNT (4) - ONVHF 11M (AampB) - OFFHI GAIN ANT PWR - OFFFC PUMPS (3) - OFFVer1fy s1ugle SU1t compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - 10101cb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2) - opencb HTRS OVLD (2) - openPOT H20 RTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANSEC COOL EVAP - RESETSEC COOL PUMP - off (etr)

MtiVR TO CMSM SEP P R ATTSC CONT - SCSCMC MODE - FREEMNVR TO PAD ATTR (0deg)PY----W)

-25-

SUPERCIRCULAR ENTRY (Cont~nued)

1

4100m(-1900)

P61 - ENTRY PREP

V37E 61E

k 05 09 01427 - ROLL REVERSED 05 09 01426 - IMU UNSAT ~

2 F 06 61 IMPACT LAT LONG HDS UPDN (+-)PRO (010

fps +00001)

3 F 06 60 GMAXVPREDGAMMA EIRecord

GMAXV400K----

GAMMA EI _PRO

(01deg fpsOldeg)

4 F 06 63 RTOGO (lnm) PAD _VIO (fps) PAD _TFE(m~n-sec)

Compare w~th ~M~SFN==C~f~o-r~P~GNS GONO GOIf NO COMM Set RTOGO amp VIO In EMS

amp lnltla11ze(ACCEPT) PRO(RECALC) V32E To 4

5 F 50 25

4300m

(-1700)

45 oOm(-1500)

500Om(-1000)

6 F 06 61

-26-

P62 - CMSM SEP amp PRE-ENTRY MNVRCAUTION Call No EXT Verbs In P62

00041 REQUEST CMSM SEPSC CONT - SCSFREE

COMPARE PITCH ATT WITH PAD DATA ---0=-

(W~thLU 5deg)YAW - 45deg OUT-OF-PLANE (LEFT)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTIRATE 2MN BUS TIE (2) - ON (ver~fy)

PRIM GLY TO RAD - BYPASS (verlfy)CM RCS LOGIC - ON (venfy)SECS LOGIC (2) - on (up)SECS PYRO ARM - ARMCMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 ps~a

CM RCS LOGIC - OFFSECS PYRO ARM (2) - SAFEMonltor VMAB

If lt25 vdc go to EMERGPOWERDOWN pg E6-l

AUTO RCS SEL AC ROLL (4) - OFFAUTO RCS SEL CM 2(6)-OFFAUTO RCS SEL CM 1(6)-MNAYAW back to 0degPITCH TO HORIZ TRACK ATT

ROLL - 0deg (LIFT UP)PITCH - 400K Horiz Mark (317deg)YAW - 0deg

ATT DB - MAXMAN ATT PITCH - ACCEL CMDEMS DATA - Ver~fy

EMS FliNC - ENTRY (ver~fy)

EMS MODE - NORMALcb SPS PampY (4) - openMAINT HORIZ TRK

PRO (Act ENTRY DAP)

IMPACT LATLONGHDSDN (01deg01deg-00001)PRO

7 POSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axis beyond 45deg of Vel vector)

8 06 64

58middot00m(-0200)

9

05G tlme(+0 )

(--=---)

06 68

-27-

P63 - ENTRY INIT

GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PIJR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRmDHORIZ CKPltch error needle goes toward

zero approachlng OSG tlmeMAN ATT (PITCH) - RATE CMD

If CMC lS GOBMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS I

FLY BETA If CMC NO GO ilt

1 SC CaNT - SCS I

FLY EMS k

p64 - ENTRY POST 05G

RTOGO AT 05G AGREES HITH EMS-venfyHORIZ CK05G Lt - ON (EMS START)

No EMS START wlthln 3 sec ~ EMS MODE - BACKUP VHF RNG c

05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds Llft DN

NNVR Llft DNEMS GONO GO

G-V Plot wlthln IlmltsRng ctr dwn 60plusmn7 durlng 10 sec

perlodMonltor G-meter for

convergence wlth pad data (Do)(Vlt27K fps) Go to 13

-28-

P65 - ENTRY - UP CONT (Vgt27K fps)

10 F 16 69 BETA (01middot) _DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT lt~ SC CONT - SCS FLY EMS

PRO

11 06 68 BETAVIHDOT (OIdegfpsfps)(VltV1+500 fps amp RnOT Neg) Go To 13

P66 - ENTRY - BALLISTIC (D(DL)

12 06 22 DESIRED GMBL ANGLES RPYMoultor horlz +12middot of 317middot mark

P67 - ENTRY - FINAL PHASE (02G)

13 06 66 BETACRSRNG ERRDNRNG ERR(010 1um 1um)

KEY VERBRecord DNRNG ERR _KEY RLSEMoultor l~ft vector ou RSI amp FDAI

16 67 RTOGOLATLONG (Vrel=1000fps)(lumOldegOldeg)

SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOWNMonitor a1t~meter

Go To EARTHLANDING pg ---4L5 _

-29-

53 GampN HYBRID DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL tV1 V37E 30E

2 F 06 33 GETI(ACCEPT) PRO (hrm~n Olsec)(REJECT) LOAD DESIRED GETI

3 F 06 81 tVXYZ (LV) (lfps)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

4 F 06 42 HAHPtV (lnm lfps)Record tV

(ACCEPT) PRO(REJECT) Reselect P30 or P27 Load new paramo

5 F 16 45 MTFIMGA (marksm~n-secOlO)

MGA -00002 ~f k

k lMU not al~gned

SET DETPRO

6

7

8

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (Pull)PLSS 02 vlv - FILL02 8M SUPPLY vlv - OFFCAB PRESS REL vlv (2) - NORMcb ELS (2) - closecb SECS ARM (2) - closecb SECS LOGIC (2) - close (ver~fy)

AUTO RCS SEL CM (12) - MNA or ~ffiB

(hftoff conhg)ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM (AampB) - OFF

CMP to Couch

9

10

11

-30-

MNVR TO PAD BURN ATTLOAD DAPBMAG MODE (3) - RATE 2SC CONT - CMCAUTOATT DB - MINMAN ATT (3) - RATE CMD

v62E

v49E

12 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLES

PRO

13 F 50 18 REQ MNVR TO FDAI RPY ANGLES (01deg)(AUTO) PRO(MAN) SC CONT - SCS

BMAG MODE (3) - RATE 2MNVR To 15

14 06 18 AUTO MNVR TO FDAI RPY ANGLES (01deg)

15 F 50 18 REQ TRIM TO FDAI RPY ANGLES (01deg)(TRIM) Go to 13(ByPASS) ENTR

16

17

CHECK BORESIGHT amp SKT STARSOPT MODE - CMCOPT ZERO - OFF

v41 N91E

18 F 21 92 SHAFTTRUN (01deg 001deg)Load SXTS angles

19 41 OPTICS DRIVECheck SKT STAR

OPT ZERO - ZEROCheck BORESIGHT STAR (~f ava~l)

20 V25 N17E (01deg)Load Pad Data GMBL Angles

for CM BURN ATTATT SETtw - SET

to PAD DATA GMBL ANGLESfor CM BURN ATT

21

22

-31-

PHR REDUCTIONHGA PHR - OFFFC PUMPS (3) - OFFVerify s~ngle su~t compr oper loads

balancedFC 2 MN AampB - OFFS BD PiR AMP - LOWcb ECS RAD CONTHTR (2) - opencb HASTE H20URINE DUMP HTRS(2)- opencb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANMN BUS TIE (2) - ONTVC SERVO PHR 1 - AC1MNAGMBL MTR (4) - START

p41 - RCS THRUSTINGV37E 41E

23 F 50 18 REQ MNVR TO LCL HORIZ (HDS ON)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CMCAUTOPRO To 24

(gtfANDAP) BMAG MODE (3) - RATE 2SC CONT - CMCHOLD

V62EMNVR To 25

24 06 18 AUTO MNVR TO FDAI RPY

25 F 50 18 REQ TRIM TO LCL HORIZ (01deg)ALIGN SC ROLL

(AUTO TRIM) PRO To 24(BYPASS) ATT DB - MIN

RATE - LOHMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTlRATE 2

ENTR

550Om26 06 85

59middot2527

-32-

VGXYZ (1fps)RECHECK BORESIGHT STARTRANS CONIR PWR - on (up)EMS MODE - STBY (ver~fy)

EMS FliNC - bV SETVHF RNGSET (IV for SM BURN _EMS FliNC - bVS BD ANT - OMNI CSECS LOGIC (2) - ONMSFN conhrm Go for PYRO ARMSECS PYRO ARM (2) - ARMCM RCS LOGIC - ON (ver~fy)

DSKY BLANKS

593028 16 85 VG XYZ (AVE G ON) (lfps)

RHCs amp THC - ARMEDLIMIT CYCLE - OFFTAPE RCDR - CMD RESETHBREMS MODE - NORMAL

000029 F 16 85 REQ NULL VG XYZ (lfps)

BURN EMS bV CTR TO ZERORESET DET amp COUNT UP

If SM ONLY burn go to step 32THC - LOCKEDSC CaNT - SCSFREERATE - HIGHPRIM GLY To RAD - BYPASS (ver~fy)

MN BUS TIE (2) - ON (ver~fy)

CMSM SEP (2) - on (up)CSMLM FNL SEP (2) - on (up) (verify)CampW MODE - CMRCS TRNFR - CMCM RCS LOGIC - OFF

Momtor VM ABIf lt25 vdc go to EMERGPOWER DOWN Pg E6-l

V63E

If CMC NO GO FDAI SOURCE - ATT FDAI SEL - 1 or 2 ATT SET - GDC

SET

-33-

~Uili ATT PITCH - ACCEL CMDFDAI SCALE - 55MNVR TO CM BURN ATT (NULL ERR NEEDLES)

R 0degPY --00--

30

31

CM RCS BURNRHC III-ContJnuous PJtch DownRHC HZ-Module PJtch to null needlesBURN VGZ TO ZERO

If only 1 RHC Pulse + P=5deg from retro att MaJnta~n rates lt3degsec

BURN COMPLETION ATllV CTR= or DET= _

V8ZE

32 F 16 44 HAHPTFF (1nmffiJn-sec)Check HP-

If gt Pad data contJnue burnuntJ1 lt Pad

PRO

33 F 16 85 VGXYZ (Ups)Read VG resJduals to MSFN

(HYBRID) PRO to 34(SM ONLY BURN)

PROF 37 ODE

EI-1500 V37E 47EF 16 83 twx Y Z (Ups)

SC CONT - SCSFREEMAN ATT (PITCH) - RATE CMDRATE - HIGHPRIM GLY To RAD - BYPASS (verJfy)MN BUS TIE (2) - ON (verJfy)CMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verJfy)Campl MODE - CMRCS TRNFR - CMCM ReS LOGIC - OFFSECS PYRO ~I (2) - SAFE

-34-

PROMonitor VMAB

If lt25 vdc go to EMERGPOWER DOWN

34 F 37 OOEPCM BIT RATE - LOWATT DB - MAXEMS MODE - STBYEMS FUNC - OFF

Go To EARTH ORBIT ENTRY pg _--40-__

-36-

8 SPS THRUSTING PREPCYCLE CRYO FANSSPS GAGING - ACI (ver~fy)

PUG MODE - NORM (venfy)BMAG MODE (3) - RATE 2tv CG - CSMCMC MODE - FREEAUTO RCS SEL (16) - MNA or HNB

(hftoff conbg)SC CONT - CMCAUTO

9 MNVR TO PAD BURN ATTV62E

10 V49E

11 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLESPRO

12 F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) PRO(HAN) SC CONT - ses

MNVR to 14

06 18 AUTO MNVR TO FDAI RPY ANGLES13

14 F 50 18 REO TRIH TO FDAI RPY ANGLES(TRIM) Go to 12(BYPASS) ENTR

15 BORESIGHT STAR CHECK

16 V37E 40EOPT PWR - OFF

17 F 50 18 REQUEST MNVR TO FDAI RPY ANGLES (01deg)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CHCAUTOPRO to 18

(MANDAP) BMAG HODE (3) - RATE 2SC CONT - CMCHOLDMNVR to 19

(HANseS) se eONT - sesMNVR to 19

-35-

54 NORMAL DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL ~V

1 V37E 30E

2 F 06 33 GETI (hrm~nOlsec)

(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

3 F 06 81 ~VXYZ (LV)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

( lfps)

4 F 06 42 HAHP~V (1nmlfps)Record W

(ACCEPT) PRO -----(REJECT) Rese1ect P30 or P27 Load new pa~am

5 F 16 45 MTFIMGA (marksmln-secOldeg)MGA -00002 If ~ lMU not a1~gned

SET DETPRO

6

7

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY v1v - OFFCAB PRESS REL v1v (2) - NORMcb ELS (2) - close (verify)cb SECS ARM (2) - close (ver~fy)

cb SECS LOGIC (2) - close (verlfy)AUTO RCS SEL CM (12) - ~mA or MNB

(l~ftoff conf~g)

ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM AampB - off (ctr)

18

-37-

06 18 AUTO MNVR TO FDAI RPY ANGLES (01 0)

19 l 50 18 REOUEST TRIM MNVR TOALIGN SIC ROLLGDC ALIGN

FDAI RPY ANGLES(010

)

+54-00m(-06-00)

TIG-5mJn

5500m(-0500)

TVC CHECK amp PREPcb STAB CONT SYS (all) - closecb SPS (12) - closeATT DB - MINRATE - LOl~

LIMIT CYCLE - ONMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE 2ROT CONTR PWR DIRECT (2) - OFFSCS TVC (2) - RATE CMD

If SCS SCS TVC (2) - AUTO SC CONT - SCS ~

TVC GMBL DRIVE PampY - AUTOMN BUS TIE (2) - ONTVC SERVO PWR 1 - AC1MNA

2 - AC2MNBTRANS CONTR PWR - ONROT CONTR PWR NORMAL 2 - ACRHC 2 - ARMED

HORIZ CHK - HorJz on 12deg wJndmlmark (LJffiJt +3 0 PNGCS GONO GO)

If NO GO set tw 180 0 180deg0 0

Track horJz wJth 24deg wJndow markAt TIG-2 mJn Ahgn GDC

PRIMARY TVC CHECKGMBL MOT P1-Y1 -STARTON(LMP confJrm)

If SCS verJfy Thumbwheel TrJmTHC - CWVenfy NO MTVC

SEC TVC CHECKGHBL MOT P2-Y2 -STARTON(LMP confJrm)SET GPI TRIHVenfy MTVCTHC NEUTRALGPI returns to 00 (CMC) or trJm (SCS)ROT CONT Pl~ NORM 2 - ACDC

(TRIM) Go to step 17(BYPASS) BMAG MODE(3) - ATTIRATE2 (ver1fy)

ENTR

-38-

20 F SO 25 00204 GMBL TEST OPTION(ACCEPT) SC CONT - GMC (ver~fy)

PROMonitor GPI Response

0020-2000020-200Tr~m

TEST FAIL SC CONT - SCS SCS TVC (2) - AUTO

(REJECT) ENTR

21 06 40 TFIVG~VM (m~n-sec1fps)

PROG ALM - TIG s1~pped

V5N9E 01703

KEY RLSE To 21 ROT CONTR PWR DIRECT (2) - MNABSPS He v1vs (2) - AUTO (ver~fy)

LIMIT CYCLE - OFFFDAI SCALE - SOIScb SPS P2Y2 - open (for cr~t burn)

5800(-02 00)

5925(-0035)

59middot 30(-0030)

06 40

59XX(-OOXX)

AV THRUST A(B) - NORMALTHC - ARMEDRlIC (2) - ARMEDTAPE RCDR - GID RESETHBR

DSKY BLANKS

(AVE G ON)EMS MODE - NORMAL

TFIVG~VM (m~n-seclfps)

CHECK PIPA BIAS lt2fps for 5 sec

ULLAGE AS REQ

IF NO ULLAGE DIR ULLAGE PB - PUSH~

CONTROL ATT WRlIC MONITOR AVM (R3) COUNTING UP

5955(-0005)

F 99 40 ENG ON ENABLE REQUEST(AUTO IGN) PRO AT TFI gt0 sec(BYPASS IGN) ENTR to 24

22 0000 IGN

-39-

If SCS - THRUST ON PB - PUSH

06 40 TFCVG~VM (m~n-seclfpslfps)

~F 97 40 SPS Thrust fall ~

~(RESTART) PRO To IGN (RECYCLE) ENTR To TIG-05 sec

SPS THRUST LITE - ONMONITOR THRUSTING

Pc 95-105 pSlaEMS COUNTING DOWNSPS IN3 v1vs (4) - OPENSPS He v1vs tb (2) - graySPS FUELOXID PRESS - 175-195 pSlaPUGS - BALANCED

PROG ALARM V5N9E 01407 VG INCTHC - CW FLY MTVC

ECOEMER SPS CUTOFF J

AV THRUST (2) - OFF

23 F 16 40 TFC(STATIC)VG~VM (mln-seclfps)~V THRUST AB - OFF

SPS IN3 v1vs (4) - CLOSEDSPS He tb (2) - bp

cb SPS P2Y2 - closed (verlfy)TVC SERVO PHR - AC1MNA (venfy)TVC SERVO PWR 2 - OFF

PRO

24 F 16 85 VG XYZ(CM) CUps)NULL RESIDUALSRECORD ~V CTR amp RESIDUALS I1VCEMS FUNC - OFF VGXEMS MODE - STBY VGYBMAG MODE (3) - RATE 2ATT DB - MAX VGZTRANS CONT PHR - OFF

PRO

25 F 37 V82E

26 F 16 44 HAHPTFF (lnmm~n-sec)

R3-59B59 HP gt494 nmPRO

27 F 37 OOE

-40-

55 EARTH ORBIT ENTRY

1 Venfy CMSMR __

P_shyY_-

SEP ATT(180deg)

(0deg )

2

3

4

EMS INITIALIZATIONEMS FUNC - RNG SETSET RNG TO PAD DATA RNGEMS FUNC - VA SETSlew scroll to pad data VIOEMS FUNC - ENTRY

RSI ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on(up)GDC ALIGN PB - PUSH amp HOLDYAW tw - Pos1tion RSI thru 45deg amp

back to LIFl UPGDC ALIGN PB - RELEASEEMS ROLL - OFFAl1gn GDC to lMU

PWR REDUCT (Norm Deorb Only)HGA PWR - OFFFC PUMPS (3) - OFFVer1fy s1ngle suit compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - Lowcb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2)-openlOb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MAN

-41-

P61 - ENTRY PREP

5 V37E 61E05 09 01427 - ROLL REVERSED05 09 01426 - IMU UNSAT

6 F 06 61 IMPACT LAT LONG liDS UPDN (+-)(01 0

010

+00001)

PRO

PAD VALUESLATLON==G------liDS UP DN _

7 F 06 60 GMAXV400KGAMMA EIRecord

GMAXV400K----GAMMA EI _

PRO

8 F 06 63 RTOGO (1nm) PAD _VIa (fps) PADTFE (mln-sec) ----Compare wlth MSFN for PGNS GONO GONO COMM SET RTOGO amp VIO IN EMS amp

INITIALIZE(ACCEPT) PRO(RECALC) V32E to 8

-42-

P62 - CMSM SEP amp PRE-ENTRY MNVR

9 F 50 25 00041 REQUEST CMSM SEPSC CONT - SCSFREEYAW - 45deg out-of-plane (left for RCS

nght for SPS)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE2PRIM GLY to RAD - BYPASS (verlfy)SECS LOGIC (2) - on (up)MSFN conflrm GO for PYRO ARMSECS PYRO ARM - ARMMN BUS TIE (2) - ON (verlfy)CMSM SEF (2) - ONCSMLM FNl SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 pSlaCM RCS LOGIC - OFFSECS PYRO ARM - SAFEMonltor VMAB

If lt25vdc go to EMERG POWERDOWN Pg E6-1AUTO RCS SEL AlC ROLL (4) - OFFAUTO RCS SEL CM 2(6) - OFFAUTO RCS SEL CM 1(6) - MNA or MNBYAW back to 00

PITCH TO ENTRY ATTROLL 0deg (LIFT UP)PITCH - HORIZ on 317deg MARK (400K)YAW 00

ATT DB - MAXMAN ATT (PITCH) - ACCEL CMDEMS DATA - VerifyEMS FUNC - ENTRY (verlfy)EMS MODE - NORMALMAINTAIN HORIZ TRK

PRO (Act ENTRY DAP)

10 F 06 61 IMPACT LAT LONG HDSDN(010 010 -00001)

PRO

11 FOSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axlS beyond 45deg of Vel vector)

-43-

P63 - ENTRY INIT

12 06 64 GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PWR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRHORIZ CKP~tch error needle goes toward

zero approach~ng 05G t~me

MAN ATT (PITCH) - RATE CMDIf CMC ~s GO

BMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS FLY BETA If CMC NO GO ~

SC CONT - SCS~

FLY EMS RCS Deorh Roll HDS UPTRACK HORIZ w~th 29deg w~ndow mk

P64 - ENTRY POST 05G

13

05G t=elt+0___)

06 68

RTOGO AT 05G AGREES WITH EMS - venfyHORIZ CK05E Lt - on (EMS start)

No EMS start w~th~n 3 secsEMS MODE - BACKUP VHF RNG 05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds L~ft DN

NNVR L~ft DNEMS GONO GO

G-V Plot w~th~n llm~ts

Rng ctr dwn 60 + 7 durlng 10 sec per~od

Mon~tor G-meter forconvergence wlth pad data (Do)

(Vlt27K fps) Go To 17

-44-

P65 - ENTRY - UP CONT (Vgt27K fps)

14 F 16 69 BETA (01deg)DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT~

SC CONT - SCS FLY EMS

PRO

15 06 68 BElA VI HOOT (01deg fpsfps)(VltVL +500 fps amp RDOT Neg) Go To 17

p66 - ENTRY - BALLISTIC (DltDL)

16 06 22 DESIRED GMBL ANGLES RPY (01deg)Mon~tor hor~z +12deg of 317deg mark

P67 - ENTRY - FINAL PHASE (02G)

17 0666 BETACRSRNG ERRDNRNG ERR (Oldeglnmlnm)KEY VERBRecord DNRNG ERR _KEY RLSEL~m~t +100nm from PAD DRE

Mon~tor l~ft vector on RSI amp FDAIF 16 67 RTOGOLATLONG (Vre1=1000fps)

(lnm 010 01deg)SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOlfflMon~tor altimeter

Go To EARTHLANDING pg _I4L5__

-45-

56 EARTHLANDING

90K STEAM PRESS - PEGGED50K CABIN PRESS REL vIv (2) - BOOSTENTRY

SECS PYRO ARM (2) - ARM

40K(90K + 63s)

CM UNSTABLE RCS CMD - OFF ~ 40K APEX COVER JETT PG-PUSH DROGUE DEPLOY PG - PUSH (2 secafter apex cover Jett)

30K ELS LOGIC - ON (up)ELS - AUTO

24K RCS hsable (auto)(90K+92s) RCS CMD - OFF

Apex cover Jett (auto)APEX COVER JETT PB - PUSH

(WAIT 2 SECS)Drogue parachutes deployed (auto)

DROGUE DEPLOY PB - PUSH~

If Drogues FallELS - ~ ~Stablllze CM 5K MAIN DPLY PB - PUSHELS - AUTO

235K Cabln Pressure lncreaslng (Drogues + 50s)If not lncreaSlng by 17K CABIN PRESS REL vlv (RR) - DUMP

-46-

10K Maln parachutes deployedMAIN DEPLOY PB - PUSH (wlthln 1 sec)VHF ANT - RECYVHF AMA - SIMPLEXVHF BCN - ONCABIN PRESS REL v1v (2) - CLOSEDIRECT 02 vlv - OPENCM RCS LOGIC - on (up)CM PRPLNT - DUMP (burn audlb1e)Monltor CM ReS 1amp2 for He press decrease

NO BURN or PRESS DECREASE USE BOTH RHCs DO NOT FIRE PITCH JETS

CM PRPLNT-PURGE (to zero He press)CM RCS He DUMP PB - PUSH RHC (2) - 30 sees NO PITCH k

STRUT LOCKS (2) - UNLOCK

cb FLT amp PL BAT BUS ABampBAT C (3) - closecb FLT amp PLT MNA amp B (2) - opencb ECS RAD HTR OVLD (2) - opencb SPS PampY (4) - open

3K CABIN PRESS REL v1v (RH) - DUMP (after purgecompleted)

FLOOD Lts - POST LDGCM RCS PRPLNT (2) - OFFROT CONTR PWR DIRECT (2) - OFF

800 CAB PRESS RELF vlv - CLOSE (latch off)MN BUS TIE (2) - OFF

AFTER LANDINGcb MAIN REL PYRO (2) - closeMAIN RELEASE - on(up)

Go to POSTLANDING pg _47L-__

I

2

3

-47-

57 POSTLANDING

STABILIZATION VENTILATION COMMUNICATIONS

DIRECT 02 vlv - CLOSE

Stablllzation after landlngELS - AUTO (verlfy)cb MAIN REL PYRO (2) - close (venfy)MAIN RELEASE - on (up) (verlfy)S~CS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb BAT RLY BUS (2) - open

No contact w1th recovery forcesVHF AM AampB - off (ctr) ~

VHF AM Rev ONLY - A cb PL VENT - closecb FLOAT BAG (3) - closecb UPRIGHT SYS COMPRESS (2) - closeIf Stable II

FLOAT BAG(3)-FILL t1ll 2 m1n afterupr1ght then - OFF

VHF AM AlB amp BCN - OFF whlle lnvertedIf Stable I

After 10 M1n Coollng Per1odFLOAT BAG (3) - FILL 7 mln then OFF

Post Stab1lizat1on And Ventllat10nPL BCN LT - BCN LT LOWPL VENT vlv - UNLOCK (Pull)Remove PL VENT Exh CoverPL VENT - HIGH or LOWPL DYE MARKER - ON (swlmmer comm)Release foots traps and_restralntscb MNA BAT BUS A amp BAT C (2) - opencb MNB BAT BUS B amp BAT C (2) - opencb FLT amp PL BAT C - opencb PYRO A SEQ A - opencb PYRO B SEQ B - open

EACH HR - CHECK DC VOLTSgt 275 V If Notmiddot cb FLT amp PL-BAT BUS AampB (2) -open cb FLT amp PL BAT C (1) - open GO TO LOW POWER CHECKLIST

Unstow and lnstall PLV DISTRIB DUCTDeploy grappllng hook and 11ne 1f req

4

-48-

Post Landing Communlcatl0nsVHF ANT-RECY (venfy)VHF BCN - ON (verlfy)

If no contact ~lth recovery forcesperform VHF BEACON Check

MONITOR VHF BEACON transmlSSlonnth VHF AM B Rcvr andor Su)vlval

TransceiverkVHF Beacon not operatlng ~connect Surv~val TranscelVer to antcable behlnd VHF ant access pnland place radio ln BCN mode

LOW POHER CHECKLISTVHF BCN - OFFVHF AM (3) - RCVFLOOD Lts - OFFVHF AM AampB - off (ctr)VHF AM RCV ONLY - A (venfy)COUCH LIGHTS - OFFPOSTLANDING VENT SYS mlnlmlze useSURV RADIO - plug mto VHF BCN ANT cableconn behind VHF ant acess pnl amp turn radloon l-n BCN mode

EGRESS PROCEDURES

CMPCDRLMPCDR

CMPCDRCMP

LMPLl1PCDR

STABLE IDlsconnect Umblll-calsNeck darn onCenter couch - 270 0 positionArmrests stowedConnect raft to SIC l-f desl-red wlth

green lanyardConnect raft ~hl-te lanyards to SUltS amp

lnflate water wlngs when eXltl-ngHATCH PISTON PRESS vlv - PRESS (Outbd)Slde Hatch openedPL VENT - OFFcb Pnl 250 (all) - openEgress with 11feraftPut hardware klt outEgress

or CDIPALL

CMF

CDRCMF

CDR

LMF

CMFCMP LMFCMP

UlP

CDR

-49-

STABLE IIcb CREW STA AUDIO (3) - openD~sconnect umb~1~ca1s

Release foots trapsRelease restra~nt harnessCouch seat pans (3) - 170 0 pos1t10nArm rests stowedSurv1va1 k~ts removed from stowageConnect life raft ma~n1~ne to CDR or SicConnect f~rst wh~te lanyard from

11fe raft to suitConnect th~rd wh~te lanyard from

l~fe raft to SU1tConnect rucksacks together to yellow

lanyard on raft bagPRESSURE EQUALIZATION vlv - OPENRemove and stow fwd hatchEX1t feet f1rst w1th rucksacks when clear

of siC 1nflate water w1ngs and raftExit feet f1rst when clear of SiC

1nflate water w1ngsEX1t feet f1rst when clear of sic

1nflate water w1ngs

-50-

60 TLI ABORTS

TLI Aborts are conta~ned ~n the ESD s~nce the bulk of the funct~ons

concern entry preparat20ns and performance Th~s allows a s2nglesource of procedures for procedure rev2ew val~dat~on checkout andtra~n~ng These procedures ~ncorporate TLI preparat20ns as found ~n

reference 6 w~th the TLI Abort Procedures and these t~e 2nto normallunar return Entry Procedures found ~n sect20n 5 The guidel~nes

for th~s cont2ngency are spec2f2ed 2n reference 7

In2t2al preparat~ons for TLI pos2t20n the necessary system sW2tches2n add~t~on to perform~ng an EMS ~V test and a GDC al~gnment Afterthe DET ~s set for mon2tor2ng TB6 the CMP ~ncreases the 12ght levelof the LEB DSKY to max~mum and returns to the h2s couch Th2s 2Sdone so that the LEB DSKY can be observed ~n the event sunl~ght orreflect20ns wash out the ma2n d2splay panel DSKY dur2ng cr2t2calmaneuvers The crew then straps ~n and prepares for mon2tor~ng TB6as 2nd2cated by the SII SEP L~te The t2mes se~uence of procedures2S keyed on th~s d~splay and ~ncludes the DET START funct~on andSIVB IGNITION Dur2ng the burn the crew mon2tors the FDAIs foratt~tude excurs20ns and abnormal rates report~ng status checks toM~ss2on Control at d2screet t~mes dur2ng the maneuver Upon SIVBSHUTDOWN the eMP records the DSKY d~splayed performance parametersand awa2ts ground conf2rmat~on

The rat~onal for TLI aborts ~s descr~bed 2n reference 7 A summar2shyzat20n 2S extracted to prov2de background and gu2de12nes 2n th2sdocument The abort procedures cover aborts 10 m2nutes after conshyt2ngent SIVE shutdown and aborts 90 m2nutes after normal SIVE shutshydown t2me

The 10 m~nute TLI abort ~s des2gned to be used dur~ng TLI ~n theevent a spacecraft problem develops Wh2Ch can result 2n catastrophe2f ~mmed~ate act~on 2S not taken If the s~tuat20n perm~ts the crewshould always allow the SIVB to complete TLI at wh~ch t~me the groundand crew can perform a malfunct~on analys~s to determ~ne ~f an abort~s adv~sable If a fa~lure occurs that necess2tates the shutdown ofthe SIVB and the ~u~ck return of the crew to earth th~s abort ~s

des~gned to be as ~nsens~t~ve to execut~on errors as poss~ble andst21l be targeted to m2dcorr2dor The burn att~tude w~th the f~ed

hor~zon reference ~s a constant value for any shutdown t~me Theburn durat~on 2S a funct20n of shutdown t2me and 2S ava21able fromcrew charts S~nce the pr~mary purpose of th~s abort ~s to returnto earth as qU2ckly as poss2ble there are no restr2ct20ns as toland~ng locat~on However ~f the t~me to EI is greater than abouttwo hours a midcourse correct20n should be ant~c~pated

The 90 m2nute TLI abort 2S to be used 2f a cr2t2cal subsystem malshyfunct~on ~s determ2ned and the dec2s~on to abort ~s made after the

-51-

TLI cutoff and before TLI cutoff plus approxlmately 80 m1nutesTh1S allows suff1c1ent separatlon and procedural t1me to set upfor the SPS deorb1t burn performed at about TLI + 90 Note thatgenerally the deorb1t burns w1ll be performed a fe11 m1nutes beforeTLI + 90 accord1ng to crew charts shown In reference 8 The no-comm except10n requ1res that 90 m1nutes be the 1nput t1me of 19n1shytlon for P-37 (onboard return-to-earth abort program) so that onshyboard calculatlons can correspond w1th ground calculat10ns to computethe CM land1ng p01nt Th1S TLI abort lS des1gned so that returnfl1ght t1me does not exceed 18 hours and abort ~V does not exceed7000 fps ThlS abort can be performed uSlng chart ~Vs and attltudesand the earths hor1zon serves as a suff1c1ent reference The maneushyver lS targeted to ach1eve the mldcorr1dor entry target Ilne andtlmed to result 1n a deslgnated recovery area

It 1S ObV10US for abort deC1S1ons early 1n the TLI + 90 m1nute t1meshyframe that a GampN SPS burn should be performed In order to keep theTLI abort procedures cons1stent and w1th emphasls on slmpl1c1ty theprocedures here reflect a SCS SPS abort burn to cover the full abortdec1s1on t1meframe

A m1dcourse correct1on for corr1dor control after a TLI abort may bedeS1red 1f the SPS burn d1d not meet expectat1ons The TLIabortprocedures 1n th1S sect10n adapt to the normal lunar return tlmel1neand procedures pr10r to the f1nal MCC

-52-

61 TLI PREPARATION PROCEDURES

GET = 150

CRO AOS(___)

CRO LOS( )(22142)

5100

Don Helmets amp Gloves

XLUNAR - INJECT (verify)EDS PWR - on (venfy)EMS FUNC - OFF (verlfy)EMS MODE - STBYEMS FUNC - IW SETVHF RNGEMS MODE - NORMALSet ~V indo to +15868 fpsEMS FUMC - ~V Test

SPS THRUST Lt - onoff (10 sec)~V lnd stops at -01 to -415

EMS MODE - STBYEMS FUMC - ~V SETVHF RNGSet ~VC

EMS FUNC---~~V=----

GDC ALIGNFDAI Select - liZcb SECS LOGIC (Z) - close (verify)cb SECS ARM (Z) - closeSECS LOGIC (Z) - on (up)MSFN Conflrm GO for PYRO ARM (If pass)SECS PYRO ARM (Z) - on (up)TRANS CONTROL PWR - ONROT CONTR PWR NORMAL (Z) - ACDC(verlfy)ROT CONTR PWR DIRECT (Z) - MNAMNBLV INnGPI - SIISIVB (venfy)LV GUID - IU (venfy)cb DIRECT ULLAGE (Z) - closedSet EVENT TIMER to 5100Begin MONITOR For TB6

CMP to Couch

TB 6 - SII SEP Lt on (TIG-9 mln 38 sec)KEY V83E

SET ORDEALFDAI Z ORB RATE at 180 0 0SII SEP Lt out (38 sec later)Start DET COUNTING UPSC CaNT - SCS (verify)MONITOR LV TANK PRESS

~P lt 36 psid (OXID gt FUEL)~P lt Z6 psid (FUEL gt OXID)

EMERGENCY CSMLV SEP UP TLM CM - BLOCK (verify)UP TLM IU - BLOCK (venfy)

-53-

+45degPY))0middot sec PY

lOK nmltHAlt25K nm

Two phas~ng mnvrs two SPS mnvrs to circular~ze at 150 nmearth orb~t

CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ssion 4K nmltHAltlOK nm CSM amp1M - Two phasing mnvrs two SPS mnvrs to circularize at 150 nm earth orb~t CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ss~on

CSM amp 1M - Two phas~ng mnvrs APS burn todepletion th~rd phasing mnvrSPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn tosem~sync orb~t

25K nmltHAlt40K nm CSM amp 1M - Two phasmg mnvrs APS burn to depletion third phas~ng mnvr SPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn to sem~sync orbit HA)40K nm DPS ava~l - DPS LOll circularize with SPS

DPS not ava~l - Lunar flyby or CSM only to lunar orbit (if reqd gtV lt4000 fps)

V37E 47E (check b~as) Record -=--rshy(Limit 98 fpsmm)

( 1fps)tVXYZN62EVIHDOTHPAD (fpsfpslnm)MONITOR VI ( ) at ECO

SCS TVC SERVO PWR 1 - ACIMNA2 - OFF

TAPE RCDR - CMD RESETHBREMS MODE - NORMAL

SIr SEP Lt - ONTLI Inhib~t S~gnals w~11 not be honored after 5942

SIVB ULLAGE BeginsSII SEP Lt - off (TIG - 18 sec)SIVB FUEL LEADSIVB ULLAGE d~scont~nues

LV ENG I Lt - onSIVB IGNITION ( GETI)LV ENG I Lt - off - -shyMONITOR THRUST amp ATTITUDEMONITOR LV TANK PRESSSIVE ECO (Lt on) (BEGIN TB7)

EMER SIVE CUTOFF AT 6 SEC PAST BURN TIME IF VI ATTAINEDTHC CCW ampNEUTRAL IN 1 SEC or SIISIVB sW - LV STAGEPremature Shutdown HAlt4K nm CSM amp 1M -

5700

58205836

F 16 835800

F 16 62

5838594259525955595900000002SUNRISE(___)

HAW AOS(__=_) KEY VERB (freeze d~splay)

SIVB ATT HOLD 20 sec amp BEGIN VENTINGSIVB NNVR TO ORB RT (HDS DN) (3middot sec)

Record VI -c---HDOT _

HPAD _

KEY RLSEF 16 62

F 16 83

HAW LOS(__=-)

KEYmiddotRLSE~VXYZ (lfps)

Record ~VX---_

~vy

WZ--

AVC---_

TAPE RCDR - off (ctr)EMS MODE - STBYEMS FUNC - OFFSECS PYRO ARM (2) - SAFE

PRO

BURN STATUS REPORT

____--~TIG

BT------VGX____-R

-----P----_Y

REMARKS

_____VI

______--HDOT______--H______---AVC______---FUEL_______OXID

_______UNBAL

F 3708=00 OOEGOS AOS CMP TO LEB

(-=-=-)

0000

0003

0005

0014

0100

-55-

62 TLI 10 MIN ABORTSECS LOGIC (2) - on (up)SECS PYRO ARM (2) - ARM

TRANS CONTR - CGH (4 sec) amp +XDET RESET (verlfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS GMD-ON

TRANS GONTR - neutral then +X for10 sec

SIVBGPI s~ - GPIExcesslve rates 6V THRUST A - NORMAL SPS THRUST - DIRECT When rates damped 6V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

TRANS CONTR +X - OFFV37E OOE

PITGH UP to LOGAL VERT (+X axlSto~ard the earth)

RATE - LOWBMAG MODE (3) - ATTIRATE 2EDS PHR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SEGS ARM (2) - opencb EDS (3) - open

TRANS CONTR -X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (180deg)P (199deg)Y (0deg)

RETRO UPDATEGETI _

JV _VG

Jtb ---GET 400K _

05G _GET DROGUE _

ENTRY P _R _

Y_--

0945

-56-

ALIGN HORIZ ON RET +1 MKGMBL CHECK (T11lle Pentattlng)MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conflnn)cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FUMC - JV SETVHF RNGSET JV from chartE~S FUMC - JVEMS fODE - NOIDlAL

lV THRUST A - NORMALV37E 47E (THRUST fONITOR)

F 16 83 lVXYZ (1 fps)

0950

1000

NOTE For aborts durlng 1st mln of TLIKEY V82E F 16 44 (HaHpTff)Burn untll Hp lt 19NM

TRANS CONTR +X

THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN JV reqdJV THRUST (2) - OFFReport cutoff

cb SPS P2 Y2- closeGfBL MTRS (4) - OFF (LMP Confinn)TRANS CONT PWR - OFFTVC SERVO PWR (2) - OFFMN BUS TIE (2) - OFFcb SPS P1amp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREIf est time to EIltOl5500 omlt fCC andenter the SUPERCIRC CKLIST as early as pos-slb1e Pg ~2~3~ __If est time to EI)Ol5500 anticlpate afCC Enter the ENTRY PREP CKLIST at step 9pg 18

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

-2tl C

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UN

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26

28

30

32

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RE

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03

-i- rtREQUIRED PITCH GIMBAL ANG LETO OBTAIN HOR-IZON AT 317

DEGREES IN wiiiiDOW

260

z~I- ~ i5 24000

1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

-I

-1-

NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

I LU HD~-

LUHD

lt0 120UJ0

~

80 HOLD PRESENT TRIMgt LU HD013

~Y~HOIgtlt

TOP OF WINDOWa 40to

31 7 SCRIBEaaI

80 TTOM OF WINDOWi= 0

0--ltoa

-40t-z

~~~Uw w u lt0 -80

HOLO PRESENT TRIlJCl

LOHU0 lt0

J gt -120 HOLD 059 TRIMlt0 z

LDHUlt0 FIELD OF VI S10 NLDHU LIFT-DOWNHEADS -UPLUHD LIFT-UP HEADS-DOWN

~~H~-160 q - P63 LIMITI- NOrE-VALIO ONLY FO~t~--

LUNAR RETURN VELOCITY

plusmnl8020 244middot 8 12 16

TIME TO 400K FT ALTITUDE-MIN

4

P37

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344

348

352

356

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320

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-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 21: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

-18-51 (Contlnued)

VEHICLE PREPARATION

l-

2

3

4

5

6 -0600h

7 -0535h

8

9

10 -0430h

INITIAL STOWAGE COMPLETED

CMC amp ISS START UP

SCS POWER UP

p51 - IMU ORIENTATION

LOAD DAPV48E 11102 01111 PRO ERO PRO

LAST MCC DECISION

NO COMM - P52 amp NAV SIGHTINGSNOMINAL - P2337 ONBOARD COMPARISON

DON MAE WESTS amp FOOT RESTRAINTS

VHF AM A - SIMPLEX

P 27 (SV REFSMMAT) MNVRamp ENTRY pAD UPDATES

11 -0415h P52 - IMU REALIGN(___) (OPTION 1)

12 P37 (NO COMM ONLY)

13

14

ECS CKS02 SUPPLY REFILLECS Monitor CkEVAP H20 CONT (2) vlvs - AUTOSUIT HEAT EXCH SEC GLY - FLOW

EPS CKS 1 3 4 (5 If reqd)

15 SPS CK (If req d)

16

17

18

RCS CKSSM RCS MOUlt CkCM RCS MOUlt Ck

CampW SYS CK

CMC SELF CK

19

20 -0345h

-03l5h-0300h

21

22

22A

-19-

DSKY COND LT TEST

MIDCOURSE MANEUVERP30 - EXT rVP404l - SPSRCS THRUSTINGMIDCOURSE (17) BURN

NO COMM NAV SIGHTINGS

ffiVR TO ENTRY ATT (Superc1rc only)V62E

V49E

22B F 06 22 DESIRED FINAL GMBL ANGLESLOAD ENTRY ATT PAD ANGLESPRO

22C F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) SC CONT - CMC

BMAG MODE (3) - RATE 2CMC MODE - AUTO

PRO(~N) SC CONT - SCS

MNVR to 22E

22D 06 18 AUTO MNVR TO FDAI RPY ANGLES

22E F 50 18 REQUEST TRIM(TRIM) Go to 22C(BYPASS) ENTR

23 -200hr BORESIGHT amp SXT STAR CHECKOPT MODE - CMCOPT ZERO - OFF

V41 N91E

F 21 92 SHAFT TRUNLoad SXTS angles

41 OPTICS DRIVE

CHECK SXT STAROPT ZERO - ZERO

CHECK BORESIGHT STAR (If ava11)

24 -0135h

25(___)

26

27 -0115h

-20-

P52 - lMU REALIGNRecord gyro torqu~ng anglesRp~----

YIf-7gt-Lno--re-c-ycle PS2If conflrmed use SCS for EMS entry

GDC ALIGNIf drlft gtLOohr change ratesource

FINAL STOWAGEOPTICS (except for hybrid)ORDEALGLY TO RAD SEC - BYPASS (verlfy)CooL pnl lnstalledY-Y struts (2) extendedStow Data Box R-12

EMS CHECKEMS FUNC - OFFcb EMS (2) - closeEMS MODE - STBYEMS FUNC - EMS TEST 1 (walt 5 sec)EMS MODE - NORMAL (walt 10 sec)

Check ind lts - offRANGE lnd - 00Slew halr1ine over notch

In self-test patternEMS FUNC - EMS TEST 2 (walt 10 sec)

05G It - on (all others out)EMS FUNC - EMS TEST 3

05G It - onRSI Lower It - on (10 sec Qater)Set RANGE counter to 58 nm+OO

EMS FUNC - EMS TEST 405G It - on (all others out)G-V trace w~thin pattern to lwr rt

corner 9GRANGE lnd counts down to 0+02

EMS FUNC - EMS TEST 505G It - onRSI upper lt - on (10 sec later)RANGE md - 00SCrlbe traces vertlcal llne 9g to

022+01ALIGN SCROLL TO ENTRY PATTERN (on

37K ft sec hne)EMS FUNC - RNG SET

G-V scroll assy traces vert llne022g to 0+01

EMS MODE - STBY

28

29

30 -OllOh

-21-

~V TEST (Deorb~t only)EMS FUNC - ~V SETVHF RNGSET ~V ~nd to 15868 fpsEMS MODE - NORMALEMS FUNC - ~V TEST

SPS THRUST LT - onoff (10 sec)~V ~nd stops at -01 to -415

EMS MODE - STBY

PRIMARY WATER EVAP ACTIVATIONGLY EVAP H20 FLOW - AUTOGLY EVAP STH PRESS - AUTOPRI ECS GLY PUMP - ACI

CM RCS PREHEATNote If sys test mtr 5cd6abcd

all read 39 vdc (28degF) or moreom~t preheat

cb RCS LOGIC (2) - closeCM RCS LOGIC - ONUP T1M CM - BLOCK (ver~fy)

cb CM RCS HTRS (2) - closeCM RCS HTRS - ON (LMP Conf~rm)

(20 mlU or III lowest rdg lS39 vdc) (Moultor Maufpress for press drop)

31 (___) FINAL GDC DRIFT CK (If req I d)If drlft gtlOohr Suspect GDC Do not

use RSI amp FDAI 2

32 -OO5Om

33

34

35

TERM CM RCS PREHEATUP TLM CM - BLOCK (venfy)CM RCS HTRS - OFFCM RCS LOGIC - OFF

SYSTEMS TEST PANEL CONFIGURATIONSYS TEST METER - 4BRNDZ XPNDR - OPERATECM RCS HTRS - OFFWASTE H20 DUMP - OFFURINE DUMP - OFF

LEB LIGHTING - OFF

SEC WATER EVAP ACTIVATIONGLY To RAD SEC vlv - BYPASSSEC COOL EVAP - EVAPSEC COOL PUMP - AC2

36

37

38 -OO45m

-22-

PYRO BATT CKcb PYRO A SEQ A - close (ver~fy)

cb PRYO B SEQ B - close (verify)DC IND - PYRO BAT A(B)

~If PYRO BAT A(B) lt 35 vdc cb PYRO A(B) seq A(B) - open~

PYRO A(B)BAT BUS A(B)TO PYRO~MN BUS TIE - close

cb MNA BAT C - closecb MNB BAT C - closeDC IND - MNBPNL 8 - All cbs closed except

PL VENT - open (ver~fy)

FLOAT BAG (3) - open (ver~fy)

DOCKING PROBE (2) - open (verlfy)EDS BAT (3) - open (ver~fy)

CM ReS HTRS (2) - open

CM RCS ACTIVATIONcb SECS ARM (2) - close (verlfy)cb SECS LOGIC (2) - close (verlfy)SECS LOGIC (2) - ONMSFN conflrm GO for PYRO ARM(~f poss)SECS PYRO ARM (2) - ARMCM RCS PRPLNT 1amp2 - ONCM RCS PRESS - ONRCS Ind sw - eMl then 2

He PRESS 3700-4400 pSlaMANF PRESS 287-302 pSla

SECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFF

P27 amp ENTRY PAD UPDATEGo To Entry Checkllst

Superclrc - pg ~2~3 _Hybnd - pg -----2~9L-__Normal Deorblt - pg __3L5L- _

-23-

52 SUPERCIRCULAR ENTRY

1 SET DET (up to ET)

2

3

4

5

3000(-30-00)

EMS INITIALIZATIONSET RNG TO PAD DATA RNGEMS FUNC - Vo SETSlew Scroll to Pad Data VIOEMS FUNC - ENTRY

RS I ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on (up)GDC ALIGN PB - PUSH amp HOLDYAW Tw - Pos~t~on RSI thru

45deg amp back to LIFT UPGDC ALIGN PB - ReleaseEMS ROLL - OFFA1~gn CDC to lMU

CM RCS RING A CKRCS TRNFR - CMcb CM RCS LOGIC MNB - openAUTO RCS SEL MNB (6) - OFFSC CONT - SCSTest R~ng A ThrustersSC CONT - CMCRCS TRNFR - SMAUTO RCS SEL (12) - MNAMNB

(hftoff conflg)cb CM RCS LOGIC MNB - close

OPTICS PWR - OFFCMP to COUCH

MN BUS TIE (2) - ONTAPE RCDR - REWIND

6 35middot0Om(-25middot 00)

-24-

SEPARATION CK LISTTVC SERVO PWR 1 - AClMNAcb ELS (2) - close (ver1fy)PRIM GLY TO RAn - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY vlv - OFFCAB PRESS REL vlv (2) - NORMGMBL MTRS (4) - STARTABORT SYS PRPLNT - RCS CMD (venfy)SM RCS PRIM PRPLNT (4) - ONVHF 11M (AampB) - OFFHI GAIN ANT PWR - OFFFC PUMPS (3) - OFFVer1fy s1ugle SU1t compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - 10101cb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2) - opencb HTRS OVLD (2) - openPOT H20 RTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANSEC COOL EVAP - RESETSEC COOL PUMP - off (etr)

MtiVR TO CMSM SEP P R ATTSC CONT - SCSCMC MODE - FREEMNVR TO PAD ATTR (0deg)PY----W)

-25-

SUPERCIRCULAR ENTRY (Cont~nued)

1

4100m(-1900)

P61 - ENTRY PREP

V37E 61E

k 05 09 01427 - ROLL REVERSED 05 09 01426 - IMU UNSAT ~

2 F 06 61 IMPACT LAT LONG HDS UPDN (+-)PRO (010

fps +00001)

3 F 06 60 GMAXVPREDGAMMA EIRecord

GMAXV400K----

GAMMA EI _PRO

(01deg fpsOldeg)

4 F 06 63 RTOGO (lnm) PAD _VIO (fps) PAD _TFE(m~n-sec)

Compare w~th ~M~SFN==C~f~o-r~P~GNS GONO GOIf NO COMM Set RTOGO amp VIO In EMS

amp lnltla11ze(ACCEPT) PRO(RECALC) V32E To 4

5 F 50 25

4300m

(-1700)

45 oOm(-1500)

500Om(-1000)

6 F 06 61

-26-

P62 - CMSM SEP amp PRE-ENTRY MNVRCAUTION Call No EXT Verbs In P62

00041 REQUEST CMSM SEPSC CONT - SCSFREE

COMPARE PITCH ATT WITH PAD DATA ---0=-

(W~thLU 5deg)YAW - 45deg OUT-OF-PLANE (LEFT)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTIRATE 2MN BUS TIE (2) - ON (ver~fy)

PRIM GLY TO RAD - BYPASS (verlfy)CM RCS LOGIC - ON (venfy)SECS LOGIC (2) - on (up)SECS PYRO ARM - ARMCMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 ps~a

CM RCS LOGIC - OFFSECS PYRO ARM (2) - SAFEMonltor VMAB

If lt25 vdc go to EMERGPOWERDOWN pg E6-l

AUTO RCS SEL AC ROLL (4) - OFFAUTO RCS SEL CM 2(6)-OFFAUTO RCS SEL CM 1(6)-MNAYAW back to 0degPITCH TO HORIZ TRACK ATT

ROLL - 0deg (LIFT UP)PITCH - 400K Horiz Mark (317deg)YAW - 0deg

ATT DB - MAXMAN ATT PITCH - ACCEL CMDEMS DATA - Ver~fy

EMS FliNC - ENTRY (ver~fy)

EMS MODE - NORMALcb SPS PampY (4) - openMAINT HORIZ TRK

PRO (Act ENTRY DAP)

IMPACT LATLONGHDSDN (01deg01deg-00001)PRO

7 POSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axis beyond 45deg of Vel vector)

8 06 64

58middot00m(-0200)

9

05G tlme(+0 )

(--=---)

06 68

-27-

P63 - ENTRY INIT

GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PIJR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRmDHORIZ CKPltch error needle goes toward

zero approachlng OSG tlmeMAN ATT (PITCH) - RATE CMD

If CMC lS GOBMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS I

FLY BETA If CMC NO GO ilt

1 SC CaNT - SCS I

FLY EMS k

p64 - ENTRY POST 05G

RTOGO AT 05G AGREES HITH EMS-venfyHORIZ CK05G Lt - ON (EMS START)

No EMS START wlthln 3 sec ~ EMS MODE - BACKUP VHF RNG c

05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds Llft DN

NNVR Llft DNEMS GONO GO

G-V Plot wlthln IlmltsRng ctr dwn 60plusmn7 durlng 10 sec

perlodMonltor G-meter for

convergence wlth pad data (Do)(Vlt27K fps) Go to 13

-28-

P65 - ENTRY - UP CONT (Vgt27K fps)

10 F 16 69 BETA (01middot) _DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT lt~ SC CONT - SCS FLY EMS

PRO

11 06 68 BETAVIHDOT (OIdegfpsfps)(VltV1+500 fps amp RnOT Neg) Go To 13

P66 - ENTRY - BALLISTIC (D(DL)

12 06 22 DESIRED GMBL ANGLES RPYMoultor horlz +12middot of 317middot mark

P67 - ENTRY - FINAL PHASE (02G)

13 06 66 BETACRSRNG ERRDNRNG ERR(010 1um 1um)

KEY VERBRecord DNRNG ERR _KEY RLSEMoultor l~ft vector ou RSI amp FDAI

16 67 RTOGOLATLONG (Vrel=1000fps)(lumOldegOldeg)

SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOWNMonitor a1t~meter

Go To EARTHLANDING pg ---4L5 _

-29-

53 GampN HYBRID DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL tV1 V37E 30E

2 F 06 33 GETI(ACCEPT) PRO (hrm~n Olsec)(REJECT) LOAD DESIRED GETI

3 F 06 81 tVXYZ (LV) (lfps)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

4 F 06 42 HAHPtV (lnm lfps)Record tV

(ACCEPT) PRO(REJECT) Reselect P30 or P27 Load new paramo

5 F 16 45 MTFIMGA (marksm~n-secOlO)

MGA -00002 ~f k

k lMU not al~gned

SET DETPRO

6

7

8

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (Pull)PLSS 02 vlv - FILL02 8M SUPPLY vlv - OFFCAB PRESS REL vlv (2) - NORMcb ELS (2) - closecb SECS ARM (2) - closecb SECS LOGIC (2) - close (ver~fy)

AUTO RCS SEL CM (12) - MNA or ~ffiB

(hftoff conhg)ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM (AampB) - OFF

CMP to Couch

9

10

11

-30-

MNVR TO PAD BURN ATTLOAD DAPBMAG MODE (3) - RATE 2SC CONT - CMCAUTOATT DB - MINMAN ATT (3) - RATE CMD

v62E

v49E

12 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLES

PRO

13 F 50 18 REQ MNVR TO FDAI RPY ANGLES (01deg)(AUTO) PRO(MAN) SC CONT - SCS

BMAG MODE (3) - RATE 2MNVR To 15

14 06 18 AUTO MNVR TO FDAI RPY ANGLES (01deg)

15 F 50 18 REQ TRIM TO FDAI RPY ANGLES (01deg)(TRIM) Go to 13(ByPASS) ENTR

16

17

CHECK BORESIGHT amp SKT STARSOPT MODE - CMCOPT ZERO - OFF

v41 N91E

18 F 21 92 SHAFTTRUN (01deg 001deg)Load SXTS angles

19 41 OPTICS DRIVECheck SKT STAR

OPT ZERO - ZEROCheck BORESIGHT STAR (~f ava~l)

20 V25 N17E (01deg)Load Pad Data GMBL Angles

for CM BURN ATTATT SETtw - SET

to PAD DATA GMBL ANGLESfor CM BURN ATT

21

22

-31-

PHR REDUCTIONHGA PHR - OFFFC PUMPS (3) - OFFVerify s~ngle su~t compr oper loads

balancedFC 2 MN AampB - OFFS BD PiR AMP - LOWcb ECS RAD CONTHTR (2) - opencb HASTE H20URINE DUMP HTRS(2)- opencb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANMN BUS TIE (2) - ONTVC SERVO PHR 1 - AC1MNAGMBL MTR (4) - START

p41 - RCS THRUSTINGV37E 41E

23 F 50 18 REQ MNVR TO LCL HORIZ (HDS ON)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CMCAUTOPRO To 24

(gtfANDAP) BMAG MODE (3) - RATE 2SC CONT - CMCHOLD

V62EMNVR To 25

24 06 18 AUTO MNVR TO FDAI RPY

25 F 50 18 REQ TRIM TO LCL HORIZ (01deg)ALIGN SC ROLL

(AUTO TRIM) PRO To 24(BYPASS) ATT DB - MIN

RATE - LOHMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTlRATE 2

ENTR

550Om26 06 85

59middot2527

-32-

VGXYZ (1fps)RECHECK BORESIGHT STARTRANS CONIR PWR - on (up)EMS MODE - STBY (ver~fy)

EMS FliNC - bV SETVHF RNGSET (IV for SM BURN _EMS FliNC - bVS BD ANT - OMNI CSECS LOGIC (2) - ONMSFN conhrm Go for PYRO ARMSECS PYRO ARM (2) - ARMCM RCS LOGIC - ON (ver~fy)

DSKY BLANKS

593028 16 85 VG XYZ (AVE G ON) (lfps)

RHCs amp THC - ARMEDLIMIT CYCLE - OFFTAPE RCDR - CMD RESETHBREMS MODE - NORMAL

000029 F 16 85 REQ NULL VG XYZ (lfps)

BURN EMS bV CTR TO ZERORESET DET amp COUNT UP

If SM ONLY burn go to step 32THC - LOCKEDSC CaNT - SCSFREERATE - HIGHPRIM GLY To RAD - BYPASS (ver~fy)

MN BUS TIE (2) - ON (ver~fy)

CMSM SEP (2) - on (up)CSMLM FNL SEP (2) - on (up) (verify)CampW MODE - CMRCS TRNFR - CMCM RCS LOGIC - OFF

Momtor VM ABIf lt25 vdc go to EMERGPOWER DOWN Pg E6-l

V63E

If CMC NO GO FDAI SOURCE - ATT FDAI SEL - 1 or 2 ATT SET - GDC

SET

-33-

~Uili ATT PITCH - ACCEL CMDFDAI SCALE - 55MNVR TO CM BURN ATT (NULL ERR NEEDLES)

R 0degPY --00--

30

31

CM RCS BURNRHC III-ContJnuous PJtch DownRHC HZ-Module PJtch to null needlesBURN VGZ TO ZERO

If only 1 RHC Pulse + P=5deg from retro att MaJnta~n rates lt3degsec

BURN COMPLETION ATllV CTR= or DET= _

V8ZE

32 F 16 44 HAHPTFF (1nmffiJn-sec)Check HP-

If gt Pad data contJnue burnuntJ1 lt Pad

PRO

33 F 16 85 VGXYZ (Ups)Read VG resJduals to MSFN

(HYBRID) PRO to 34(SM ONLY BURN)

PROF 37 ODE

EI-1500 V37E 47EF 16 83 twx Y Z (Ups)

SC CONT - SCSFREEMAN ATT (PITCH) - RATE CMDRATE - HIGHPRIM GLY To RAD - BYPASS (verJfy)MN BUS TIE (2) - ON (verJfy)CMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verJfy)Campl MODE - CMRCS TRNFR - CMCM ReS LOGIC - OFFSECS PYRO ~I (2) - SAFE

-34-

PROMonitor VMAB

If lt25 vdc go to EMERGPOWER DOWN

34 F 37 OOEPCM BIT RATE - LOWATT DB - MAXEMS MODE - STBYEMS FUNC - OFF

Go To EARTH ORBIT ENTRY pg _--40-__

-36-

8 SPS THRUSTING PREPCYCLE CRYO FANSSPS GAGING - ACI (ver~fy)

PUG MODE - NORM (venfy)BMAG MODE (3) - RATE 2tv CG - CSMCMC MODE - FREEAUTO RCS SEL (16) - MNA or HNB

(hftoff conbg)SC CONT - CMCAUTO

9 MNVR TO PAD BURN ATTV62E

10 V49E

11 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLESPRO

12 F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) PRO(HAN) SC CONT - ses

MNVR to 14

06 18 AUTO MNVR TO FDAI RPY ANGLES13

14 F 50 18 REO TRIH TO FDAI RPY ANGLES(TRIM) Go to 12(BYPASS) ENTR

15 BORESIGHT STAR CHECK

16 V37E 40EOPT PWR - OFF

17 F 50 18 REQUEST MNVR TO FDAI RPY ANGLES (01deg)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CHCAUTOPRO to 18

(MANDAP) BMAG HODE (3) - RATE 2SC CONT - CMCHOLDMNVR to 19

(HANseS) se eONT - sesMNVR to 19

-35-

54 NORMAL DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL ~V

1 V37E 30E

2 F 06 33 GETI (hrm~nOlsec)

(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

3 F 06 81 ~VXYZ (LV)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

( lfps)

4 F 06 42 HAHP~V (1nmlfps)Record W

(ACCEPT) PRO -----(REJECT) Rese1ect P30 or P27 Load new pa~am

5 F 16 45 MTFIMGA (marksmln-secOldeg)MGA -00002 If ~ lMU not a1~gned

SET DETPRO

6

7

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY v1v - OFFCAB PRESS REL v1v (2) - NORMcb ELS (2) - close (verify)cb SECS ARM (2) - close (ver~fy)

cb SECS LOGIC (2) - close (verlfy)AUTO RCS SEL CM (12) - ~mA or MNB

(l~ftoff conf~g)

ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM AampB - off (ctr)

18

-37-

06 18 AUTO MNVR TO FDAI RPY ANGLES (01 0)

19 l 50 18 REOUEST TRIM MNVR TOALIGN SIC ROLLGDC ALIGN

FDAI RPY ANGLES(010

)

+54-00m(-06-00)

TIG-5mJn

5500m(-0500)

TVC CHECK amp PREPcb STAB CONT SYS (all) - closecb SPS (12) - closeATT DB - MINRATE - LOl~

LIMIT CYCLE - ONMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE 2ROT CONTR PWR DIRECT (2) - OFFSCS TVC (2) - RATE CMD

If SCS SCS TVC (2) - AUTO SC CONT - SCS ~

TVC GMBL DRIVE PampY - AUTOMN BUS TIE (2) - ONTVC SERVO PWR 1 - AC1MNA

2 - AC2MNBTRANS CONTR PWR - ONROT CONTR PWR NORMAL 2 - ACRHC 2 - ARMED

HORIZ CHK - HorJz on 12deg wJndmlmark (LJffiJt +3 0 PNGCS GONO GO)

If NO GO set tw 180 0 180deg0 0

Track horJz wJth 24deg wJndow markAt TIG-2 mJn Ahgn GDC

PRIMARY TVC CHECKGMBL MOT P1-Y1 -STARTON(LMP confJrm)

If SCS verJfy Thumbwheel TrJmTHC - CWVenfy NO MTVC

SEC TVC CHECKGHBL MOT P2-Y2 -STARTON(LMP confJrm)SET GPI TRIHVenfy MTVCTHC NEUTRALGPI returns to 00 (CMC) or trJm (SCS)ROT CONT Pl~ NORM 2 - ACDC

(TRIM) Go to step 17(BYPASS) BMAG MODE(3) - ATTIRATE2 (ver1fy)

ENTR

-38-

20 F SO 25 00204 GMBL TEST OPTION(ACCEPT) SC CONT - GMC (ver~fy)

PROMonitor GPI Response

0020-2000020-200Tr~m

TEST FAIL SC CONT - SCS SCS TVC (2) - AUTO

(REJECT) ENTR

21 06 40 TFIVG~VM (m~n-sec1fps)

PROG ALM - TIG s1~pped

V5N9E 01703

KEY RLSE To 21 ROT CONTR PWR DIRECT (2) - MNABSPS He v1vs (2) - AUTO (ver~fy)

LIMIT CYCLE - OFFFDAI SCALE - SOIScb SPS P2Y2 - open (for cr~t burn)

5800(-02 00)

5925(-0035)

59middot 30(-0030)

06 40

59XX(-OOXX)

AV THRUST A(B) - NORMALTHC - ARMEDRlIC (2) - ARMEDTAPE RCDR - GID RESETHBR

DSKY BLANKS

(AVE G ON)EMS MODE - NORMAL

TFIVG~VM (m~n-seclfps)

CHECK PIPA BIAS lt2fps for 5 sec

ULLAGE AS REQ

IF NO ULLAGE DIR ULLAGE PB - PUSH~

CONTROL ATT WRlIC MONITOR AVM (R3) COUNTING UP

5955(-0005)

F 99 40 ENG ON ENABLE REQUEST(AUTO IGN) PRO AT TFI gt0 sec(BYPASS IGN) ENTR to 24

22 0000 IGN

-39-

If SCS - THRUST ON PB - PUSH

06 40 TFCVG~VM (m~n-seclfpslfps)

~F 97 40 SPS Thrust fall ~

~(RESTART) PRO To IGN (RECYCLE) ENTR To TIG-05 sec

SPS THRUST LITE - ONMONITOR THRUSTING

Pc 95-105 pSlaEMS COUNTING DOWNSPS IN3 v1vs (4) - OPENSPS He v1vs tb (2) - graySPS FUELOXID PRESS - 175-195 pSlaPUGS - BALANCED

PROG ALARM V5N9E 01407 VG INCTHC - CW FLY MTVC

ECOEMER SPS CUTOFF J

AV THRUST (2) - OFF

23 F 16 40 TFC(STATIC)VG~VM (mln-seclfps)~V THRUST AB - OFF

SPS IN3 v1vs (4) - CLOSEDSPS He tb (2) - bp

cb SPS P2Y2 - closed (verlfy)TVC SERVO PHR - AC1MNA (venfy)TVC SERVO PWR 2 - OFF

PRO

24 F 16 85 VG XYZ(CM) CUps)NULL RESIDUALSRECORD ~V CTR amp RESIDUALS I1VCEMS FUNC - OFF VGXEMS MODE - STBY VGYBMAG MODE (3) - RATE 2ATT DB - MAX VGZTRANS CONT PHR - OFF

PRO

25 F 37 V82E

26 F 16 44 HAHPTFF (lnmm~n-sec)

R3-59B59 HP gt494 nmPRO

27 F 37 OOE

-40-

55 EARTH ORBIT ENTRY

1 Venfy CMSMR __

P_shyY_-

SEP ATT(180deg)

(0deg )

2

3

4

EMS INITIALIZATIONEMS FUNC - RNG SETSET RNG TO PAD DATA RNGEMS FUNC - VA SETSlew scroll to pad data VIOEMS FUNC - ENTRY

RSI ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on(up)GDC ALIGN PB - PUSH amp HOLDYAW tw - Pos1tion RSI thru 45deg amp

back to LIFl UPGDC ALIGN PB - RELEASEEMS ROLL - OFFAl1gn GDC to lMU

PWR REDUCT (Norm Deorb Only)HGA PWR - OFFFC PUMPS (3) - OFFVer1fy s1ngle suit compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - Lowcb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2)-openlOb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MAN

-41-

P61 - ENTRY PREP

5 V37E 61E05 09 01427 - ROLL REVERSED05 09 01426 - IMU UNSAT

6 F 06 61 IMPACT LAT LONG liDS UPDN (+-)(01 0

010

+00001)

PRO

PAD VALUESLATLON==G------liDS UP DN _

7 F 06 60 GMAXV400KGAMMA EIRecord

GMAXV400K----GAMMA EI _

PRO

8 F 06 63 RTOGO (1nm) PAD _VIa (fps) PADTFE (mln-sec) ----Compare wlth MSFN for PGNS GONO GONO COMM SET RTOGO amp VIO IN EMS amp

INITIALIZE(ACCEPT) PRO(RECALC) V32E to 8

-42-

P62 - CMSM SEP amp PRE-ENTRY MNVR

9 F 50 25 00041 REQUEST CMSM SEPSC CONT - SCSFREEYAW - 45deg out-of-plane (left for RCS

nght for SPS)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE2PRIM GLY to RAD - BYPASS (verlfy)SECS LOGIC (2) - on (up)MSFN conflrm GO for PYRO ARMSECS PYRO ARM - ARMMN BUS TIE (2) - ON (verlfy)CMSM SEF (2) - ONCSMLM FNl SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 pSlaCM RCS LOGIC - OFFSECS PYRO ARM - SAFEMonltor VMAB

If lt25vdc go to EMERG POWERDOWN Pg E6-1AUTO RCS SEL AlC ROLL (4) - OFFAUTO RCS SEL CM 2(6) - OFFAUTO RCS SEL CM 1(6) - MNA or MNBYAW back to 00

PITCH TO ENTRY ATTROLL 0deg (LIFT UP)PITCH - HORIZ on 317deg MARK (400K)YAW 00

ATT DB - MAXMAN ATT (PITCH) - ACCEL CMDEMS DATA - VerifyEMS FUNC - ENTRY (verlfy)EMS MODE - NORMALMAINTAIN HORIZ TRK

PRO (Act ENTRY DAP)

10 F 06 61 IMPACT LAT LONG HDSDN(010 010 -00001)

PRO

11 FOSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axlS beyond 45deg of Vel vector)

-43-

P63 - ENTRY INIT

12 06 64 GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PWR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRHORIZ CKP~tch error needle goes toward

zero approach~ng 05G t~me

MAN ATT (PITCH) - RATE CMDIf CMC ~s GO

BMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS FLY BETA If CMC NO GO ~

SC CONT - SCS~

FLY EMS RCS Deorh Roll HDS UPTRACK HORIZ w~th 29deg w~ndow mk

P64 - ENTRY POST 05G

13

05G t=elt+0___)

06 68

RTOGO AT 05G AGREES WITH EMS - venfyHORIZ CK05E Lt - on (EMS start)

No EMS start w~th~n 3 secsEMS MODE - BACKUP VHF RNG 05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds L~ft DN

NNVR L~ft DNEMS GONO GO

G-V Plot w~th~n llm~ts

Rng ctr dwn 60 + 7 durlng 10 sec per~od

Mon~tor G-meter forconvergence wlth pad data (Do)

(Vlt27K fps) Go To 17

-44-

P65 - ENTRY - UP CONT (Vgt27K fps)

14 F 16 69 BETA (01deg)DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT~

SC CONT - SCS FLY EMS

PRO

15 06 68 BElA VI HOOT (01deg fpsfps)(VltVL +500 fps amp RDOT Neg) Go To 17

p66 - ENTRY - BALLISTIC (DltDL)

16 06 22 DESIRED GMBL ANGLES RPY (01deg)Mon~tor hor~z +12deg of 317deg mark

P67 - ENTRY - FINAL PHASE (02G)

17 0666 BETACRSRNG ERRDNRNG ERR (Oldeglnmlnm)KEY VERBRecord DNRNG ERR _KEY RLSEL~m~t +100nm from PAD DRE

Mon~tor l~ft vector on RSI amp FDAIF 16 67 RTOGOLATLONG (Vre1=1000fps)

(lnm 010 01deg)SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOlfflMon~tor altimeter

Go To EARTHLANDING pg _I4L5__

-45-

56 EARTHLANDING

90K STEAM PRESS - PEGGED50K CABIN PRESS REL vIv (2) - BOOSTENTRY

SECS PYRO ARM (2) - ARM

40K(90K + 63s)

CM UNSTABLE RCS CMD - OFF ~ 40K APEX COVER JETT PG-PUSH DROGUE DEPLOY PG - PUSH (2 secafter apex cover Jett)

30K ELS LOGIC - ON (up)ELS - AUTO

24K RCS hsable (auto)(90K+92s) RCS CMD - OFF

Apex cover Jett (auto)APEX COVER JETT PB - PUSH

(WAIT 2 SECS)Drogue parachutes deployed (auto)

DROGUE DEPLOY PB - PUSH~

If Drogues FallELS - ~ ~Stablllze CM 5K MAIN DPLY PB - PUSHELS - AUTO

235K Cabln Pressure lncreaslng (Drogues + 50s)If not lncreaSlng by 17K CABIN PRESS REL vlv (RR) - DUMP

-46-

10K Maln parachutes deployedMAIN DEPLOY PB - PUSH (wlthln 1 sec)VHF ANT - RECYVHF AMA - SIMPLEXVHF BCN - ONCABIN PRESS REL v1v (2) - CLOSEDIRECT 02 vlv - OPENCM RCS LOGIC - on (up)CM PRPLNT - DUMP (burn audlb1e)Monltor CM ReS 1amp2 for He press decrease

NO BURN or PRESS DECREASE USE BOTH RHCs DO NOT FIRE PITCH JETS

CM PRPLNT-PURGE (to zero He press)CM RCS He DUMP PB - PUSH RHC (2) - 30 sees NO PITCH k

STRUT LOCKS (2) - UNLOCK

cb FLT amp PL BAT BUS ABampBAT C (3) - closecb FLT amp PLT MNA amp B (2) - opencb ECS RAD HTR OVLD (2) - opencb SPS PampY (4) - open

3K CABIN PRESS REL v1v (RH) - DUMP (after purgecompleted)

FLOOD Lts - POST LDGCM RCS PRPLNT (2) - OFFROT CONTR PWR DIRECT (2) - OFF

800 CAB PRESS RELF vlv - CLOSE (latch off)MN BUS TIE (2) - OFF

AFTER LANDINGcb MAIN REL PYRO (2) - closeMAIN RELEASE - on(up)

Go to POSTLANDING pg _47L-__

I

2

3

-47-

57 POSTLANDING

STABILIZATION VENTILATION COMMUNICATIONS

DIRECT 02 vlv - CLOSE

Stablllzation after landlngELS - AUTO (verlfy)cb MAIN REL PYRO (2) - close (venfy)MAIN RELEASE - on (up) (verlfy)S~CS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb BAT RLY BUS (2) - open

No contact w1th recovery forcesVHF AM AampB - off (ctr) ~

VHF AM Rev ONLY - A cb PL VENT - closecb FLOAT BAG (3) - closecb UPRIGHT SYS COMPRESS (2) - closeIf Stable II

FLOAT BAG(3)-FILL t1ll 2 m1n afterupr1ght then - OFF

VHF AM AlB amp BCN - OFF whlle lnvertedIf Stable I

After 10 M1n Coollng Per1odFLOAT BAG (3) - FILL 7 mln then OFF

Post Stab1lizat1on And Ventllat10nPL BCN LT - BCN LT LOWPL VENT vlv - UNLOCK (Pull)Remove PL VENT Exh CoverPL VENT - HIGH or LOWPL DYE MARKER - ON (swlmmer comm)Release foots traps and_restralntscb MNA BAT BUS A amp BAT C (2) - opencb MNB BAT BUS B amp BAT C (2) - opencb FLT amp PL BAT C - opencb PYRO A SEQ A - opencb PYRO B SEQ B - open

EACH HR - CHECK DC VOLTSgt 275 V If Notmiddot cb FLT amp PL-BAT BUS AampB (2) -open cb FLT amp PL BAT C (1) - open GO TO LOW POWER CHECKLIST

Unstow and lnstall PLV DISTRIB DUCTDeploy grappllng hook and 11ne 1f req

4

-48-

Post Landing Communlcatl0nsVHF ANT-RECY (venfy)VHF BCN - ON (verlfy)

If no contact ~lth recovery forcesperform VHF BEACON Check

MONITOR VHF BEACON transmlSSlonnth VHF AM B Rcvr andor Su)vlval

TransceiverkVHF Beacon not operatlng ~connect Surv~val TranscelVer to antcable behlnd VHF ant access pnland place radio ln BCN mode

LOW POHER CHECKLISTVHF BCN - OFFVHF AM (3) - RCVFLOOD Lts - OFFVHF AM AampB - off (ctr)VHF AM RCV ONLY - A (venfy)COUCH LIGHTS - OFFPOSTLANDING VENT SYS mlnlmlze useSURV RADIO - plug mto VHF BCN ANT cableconn behind VHF ant acess pnl amp turn radloon l-n BCN mode

EGRESS PROCEDURES

CMPCDRLMPCDR

CMPCDRCMP

LMPLl1PCDR

STABLE IDlsconnect Umblll-calsNeck darn onCenter couch - 270 0 positionArmrests stowedConnect raft to SIC l-f desl-red wlth

green lanyardConnect raft ~hl-te lanyards to SUltS amp

lnflate water wlngs when eXltl-ngHATCH PISTON PRESS vlv - PRESS (Outbd)Slde Hatch openedPL VENT - OFFcb Pnl 250 (all) - openEgress with 11feraftPut hardware klt outEgress

or CDIPALL

CMF

CDRCMF

CDR

LMF

CMFCMP LMFCMP

UlP

CDR

-49-

STABLE IIcb CREW STA AUDIO (3) - openD~sconnect umb~1~ca1s

Release foots trapsRelease restra~nt harnessCouch seat pans (3) - 170 0 pos1t10nArm rests stowedSurv1va1 k~ts removed from stowageConnect life raft ma~n1~ne to CDR or SicConnect f~rst wh~te lanyard from

11fe raft to suitConnect th~rd wh~te lanyard from

l~fe raft to SU1tConnect rucksacks together to yellow

lanyard on raft bagPRESSURE EQUALIZATION vlv - OPENRemove and stow fwd hatchEX1t feet f1rst w1th rucksacks when clear

of siC 1nflate water w1ngs and raftExit feet f1rst when clear of SiC

1nflate water w1ngsEX1t feet f1rst when clear of sic

1nflate water w1ngs

-50-

60 TLI ABORTS

TLI Aborts are conta~ned ~n the ESD s~nce the bulk of the funct~ons

concern entry preparat20ns and performance Th~s allows a s2nglesource of procedures for procedure rev2ew val~dat~on checkout andtra~n~ng These procedures ~ncorporate TLI preparat20ns as found ~n

reference 6 w~th the TLI Abort Procedures and these t~e 2nto normallunar return Entry Procedures found ~n sect20n 5 The guidel~nes

for th~s cont2ngency are spec2f2ed 2n reference 7

In2t2al preparat~ons for TLI pos2t20n the necessary system sW2tches2n add~t~on to perform~ng an EMS ~V test and a GDC al~gnment Afterthe DET ~s set for mon2tor2ng TB6 the CMP ~ncreases the 12ght levelof the LEB DSKY to max~mum and returns to the h2s couch Th2s 2Sdone so that the LEB DSKY can be observed ~n the event sunl~ght orreflect20ns wash out the ma2n d2splay panel DSKY dur2ng cr2t2calmaneuvers The crew then straps ~n and prepares for mon2tor~ng TB6as 2nd2cated by the SII SEP L~te The t2mes se~uence of procedures2S keyed on th~s d~splay and ~ncludes the DET START funct~on andSIVB IGNITION Dur2ng the burn the crew mon2tors the FDAIs foratt~tude excurs20ns and abnormal rates report~ng status checks toM~ss2on Control at d2screet t~mes dur2ng the maneuver Upon SIVBSHUTDOWN the eMP records the DSKY d~splayed performance parametersand awa2ts ground conf2rmat~on

The rat~onal for TLI aborts ~s descr~bed 2n reference 7 A summar2shyzat20n 2S extracted to prov2de background and gu2de12nes 2n th2sdocument The abort procedures cover aborts 10 m2nutes after conshyt2ngent SIVE shutdown and aborts 90 m2nutes after normal SIVE shutshydown t2me

The 10 m~nute TLI abort ~s des2gned to be used dur~ng TLI ~n theevent a spacecraft problem develops Wh2Ch can result 2n catastrophe2f ~mmed~ate act~on 2S not taken If the s~tuat20n perm~ts the crewshould always allow the SIVB to complete TLI at wh~ch t~me the groundand crew can perform a malfunct~on analys~s to determ~ne ~f an abort~s adv~sable If a fa~lure occurs that necess2tates the shutdown ofthe SIVB and the ~u~ck return of the crew to earth th~s abort ~s

des~gned to be as ~nsens~t~ve to execut~on errors as poss~ble andst21l be targeted to m2dcorr2dor The burn att~tude w~th the f~ed

hor~zon reference ~s a constant value for any shutdown t~me Theburn durat~on 2S a funct20n of shutdown t2me and 2S ava21able fromcrew charts S~nce the pr~mary purpose of th~s abort ~s to returnto earth as qU2ckly as poss2ble there are no restr2ct20ns as toland~ng locat~on However ~f the t~me to EI is greater than abouttwo hours a midcourse correct20n should be ant~c~pated

The 90 m2nute TLI abort 2S to be used 2f a cr2t2cal subsystem malshyfunct~on ~s determ2ned and the dec2s~on to abort ~s made after the

-51-

TLI cutoff and before TLI cutoff plus approxlmately 80 m1nutesTh1S allows suff1c1ent separatlon and procedural t1me to set upfor the SPS deorb1t burn performed at about TLI + 90 Note thatgenerally the deorb1t burns w1ll be performed a fe11 m1nutes beforeTLI + 90 accord1ng to crew charts shown In reference 8 The no-comm except10n requ1res that 90 m1nutes be the 1nput t1me of 19n1shytlon for P-37 (onboard return-to-earth abort program) so that onshyboard calculatlons can correspond w1th ground calculat10ns to computethe CM land1ng p01nt Th1S TLI abort lS des1gned so that returnfl1ght t1me does not exceed 18 hours and abort ~V does not exceed7000 fps ThlS abort can be performed uSlng chart ~Vs and attltudesand the earths hor1zon serves as a suff1c1ent reference The maneushyver lS targeted to ach1eve the mldcorr1dor entry target Ilne andtlmed to result 1n a deslgnated recovery area

It 1S ObV10US for abort deC1S1ons early 1n the TLI + 90 m1nute t1meshyframe that a GampN SPS burn should be performed In order to keep theTLI abort procedures cons1stent and w1th emphasls on slmpl1c1ty theprocedures here reflect a SCS SPS abort burn to cover the full abortdec1s1on t1meframe

A m1dcourse correct1on for corr1dor control after a TLI abort may bedeS1red 1f the SPS burn d1d not meet expectat1ons The TLIabortprocedures 1n th1S sect10n adapt to the normal lunar return tlmel1neand procedures pr10r to the f1nal MCC

-52-

61 TLI PREPARATION PROCEDURES

GET = 150

CRO AOS(___)

CRO LOS( )(22142)

5100

Don Helmets amp Gloves

XLUNAR - INJECT (verify)EDS PWR - on (venfy)EMS FUNC - OFF (verlfy)EMS MODE - STBYEMS FUNC - IW SETVHF RNGEMS MODE - NORMALSet ~V indo to +15868 fpsEMS FUMC - ~V Test

SPS THRUST Lt - onoff (10 sec)~V lnd stops at -01 to -415

EMS MODE - STBYEMS FUMC - ~V SETVHF RNGSet ~VC

EMS FUNC---~~V=----

GDC ALIGNFDAI Select - liZcb SECS LOGIC (Z) - close (verify)cb SECS ARM (Z) - closeSECS LOGIC (Z) - on (up)MSFN Conflrm GO for PYRO ARM (If pass)SECS PYRO ARM (Z) - on (up)TRANS CONTROL PWR - ONROT CONTR PWR NORMAL (Z) - ACDC(verlfy)ROT CONTR PWR DIRECT (Z) - MNAMNBLV INnGPI - SIISIVB (venfy)LV GUID - IU (venfy)cb DIRECT ULLAGE (Z) - closedSet EVENT TIMER to 5100Begin MONITOR For TB6

CMP to Couch

TB 6 - SII SEP Lt on (TIG-9 mln 38 sec)KEY V83E

SET ORDEALFDAI Z ORB RATE at 180 0 0SII SEP Lt out (38 sec later)Start DET COUNTING UPSC CaNT - SCS (verify)MONITOR LV TANK PRESS

~P lt 36 psid (OXID gt FUEL)~P lt Z6 psid (FUEL gt OXID)

EMERGENCY CSMLV SEP UP TLM CM - BLOCK (verify)UP TLM IU - BLOCK (venfy)

-53-

+45degPY))0middot sec PY

lOK nmltHAlt25K nm

Two phas~ng mnvrs two SPS mnvrs to circular~ze at 150 nmearth orb~t

CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ssion 4K nmltHAltlOK nm CSM amp1M - Two phasing mnvrs two SPS mnvrs to circularize at 150 nm earth orb~t CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ss~on

CSM amp 1M - Two phas~ng mnvrs APS burn todepletion th~rd phasing mnvrSPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn tosem~sync orb~t

25K nmltHAlt40K nm CSM amp 1M - Two phasmg mnvrs APS burn to depletion third phas~ng mnvr SPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn to sem~sync orbit HA)40K nm DPS ava~l - DPS LOll circularize with SPS

DPS not ava~l - Lunar flyby or CSM only to lunar orbit (if reqd gtV lt4000 fps)

V37E 47E (check b~as) Record -=--rshy(Limit 98 fpsmm)

( 1fps)tVXYZN62EVIHDOTHPAD (fpsfpslnm)MONITOR VI ( ) at ECO

SCS TVC SERVO PWR 1 - ACIMNA2 - OFF

TAPE RCDR - CMD RESETHBREMS MODE - NORMAL

SIr SEP Lt - ONTLI Inhib~t S~gnals w~11 not be honored after 5942

SIVB ULLAGE BeginsSII SEP Lt - off (TIG - 18 sec)SIVB FUEL LEADSIVB ULLAGE d~scont~nues

LV ENG I Lt - onSIVB IGNITION ( GETI)LV ENG I Lt - off - -shyMONITOR THRUST amp ATTITUDEMONITOR LV TANK PRESSSIVE ECO (Lt on) (BEGIN TB7)

EMER SIVE CUTOFF AT 6 SEC PAST BURN TIME IF VI ATTAINEDTHC CCW ampNEUTRAL IN 1 SEC or SIISIVB sW - LV STAGEPremature Shutdown HAlt4K nm CSM amp 1M -

5700

58205836

F 16 835800

F 16 62

5838594259525955595900000002SUNRISE(___)

HAW AOS(__=_) KEY VERB (freeze d~splay)

SIVB ATT HOLD 20 sec amp BEGIN VENTINGSIVB NNVR TO ORB RT (HDS DN) (3middot sec)

Record VI -c---HDOT _

HPAD _

KEY RLSEF 16 62

F 16 83

HAW LOS(__=-)

KEYmiddotRLSE~VXYZ (lfps)

Record ~VX---_

~vy

WZ--

AVC---_

TAPE RCDR - off (ctr)EMS MODE - STBYEMS FUNC - OFFSECS PYRO ARM (2) - SAFE

PRO

BURN STATUS REPORT

____--~TIG

BT------VGX____-R

-----P----_Y

REMARKS

_____VI

______--HDOT______--H______---AVC______---FUEL_______OXID

_______UNBAL

F 3708=00 OOEGOS AOS CMP TO LEB

(-=-=-)

0000

0003

0005

0014

0100

-55-

62 TLI 10 MIN ABORTSECS LOGIC (2) - on (up)SECS PYRO ARM (2) - ARM

TRANS CONTR - CGH (4 sec) amp +XDET RESET (verlfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS GMD-ON

TRANS GONTR - neutral then +X for10 sec

SIVBGPI s~ - GPIExcesslve rates 6V THRUST A - NORMAL SPS THRUST - DIRECT When rates damped 6V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

TRANS CONTR +X - OFFV37E OOE

PITGH UP to LOGAL VERT (+X axlSto~ard the earth)

RATE - LOWBMAG MODE (3) - ATTIRATE 2EDS PHR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SEGS ARM (2) - opencb EDS (3) - open

TRANS CONTR -X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (180deg)P (199deg)Y (0deg)

RETRO UPDATEGETI _

JV _VG

Jtb ---GET 400K _

05G _GET DROGUE _

ENTRY P _R _

Y_--

0945

-56-

ALIGN HORIZ ON RET +1 MKGMBL CHECK (T11lle Pentattlng)MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conflnn)cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FUMC - JV SETVHF RNGSET JV from chartE~S FUMC - JVEMS fODE - NOIDlAL

lV THRUST A - NORMALV37E 47E (THRUST fONITOR)

F 16 83 lVXYZ (1 fps)

0950

1000

NOTE For aborts durlng 1st mln of TLIKEY V82E F 16 44 (HaHpTff)Burn untll Hp lt 19NM

TRANS CONTR +X

THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN JV reqdJV THRUST (2) - OFFReport cutoff

cb SPS P2 Y2- closeGfBL MTRS (4) - OFF (LMP Confinn)TRANS CONT PWR - OFFTVC SERVO PWR (2) - OFFMN BUS TIE (2) - OFFcb SPS P1amp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREIf est time to EIltOl5500 omlt fCC andenter the SUPERCIRC CKLIST as early as pos-slb1e Pg ~2~3~ __If est time to EI)Ol5500 anticlpate afCC Enter the ENTRY PREP CKLIST at step 9pg 18

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

-2tl C

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28

30

32

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-i- rtREQUIRED PITCH GIMBAL ANG LETO OBTAIN HOR-IZON AT 317

DEGREES IN wiiiiDOW

260

z~I- ~ i5 24000

1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

-I

-1-

NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

I LU HD~-

LUHD

lt0 120UJ0

~

80 HOLD PRESENT TRIMgt LU HD013

~Y~HOIgtlt

TOP OF WINDOWa 40to

31 7 SCRIBEaaI

80 TTOM OF WINDOWi= 0

0--ltoa

-40t-z

~~~Uw w u lt0 -80

HOLO PRESENT TRIlJCl

LOHU0 lt0

J gt -120 HOLD 059 TRIMlt0 z

LDHUlt0 FIELD OF VI S10 NLDHU LIFT-DOWNHEADS -UPLUHD LIFT-UP HEADS-DOWN

~~H~-160 q - P63 LIMITI- NOrE-VALIO ONLY FO~t~--

LUNAR RETURN VELOCITY

plusmnl8020 244middot 8 12 16

TIME TO 400K FT ALTITUDE-MIN

4

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320

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120

200

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320

400

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-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 22: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

19

20 -0345h

-03l5h-0300h

21

22

22A

-19-

DSKY COND LT TEST

MIDCOURSE MANEUVERP30 - EXT rVP404l - SPSRCS THRUSTINGMIDCOURSE (17) BURN

NO COMM NAV SIGHTINGS

ffiVR TO ENTRY ATT (Superc1rc only)V62E

V49E

22B F 06 22 DESIRED FINAL GMBL ANGLESLOAD ENTRY ATT PAD ANGLESPRO

22C F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) SC CONT - CMC

BMAG MODE (3) - RATE 2CMC MODE - AUTO

PRO(~N) SC CONT - SCS

MNVR to 22E

22D 06 18 AUTO MNVR TO FDAI RPY ANGLES

22E F 50 18 REQUEST TRIM(TRIM) Go to 22C(BYPASS) ENTR

23 -200hr BORESIGHT amp SXT STAR CHECKOPT MODE - CMCOPT ZERO - OFF

V41 N91E

F 21 92 SHAFT TRUNLoad SXTS angles

41 OPTICS DRIVE

CHECK SXT STAROPT ZERO - ZERO

CHECK BORESIGHT STAR (If ava11)

24 -0135h

25(___)

26

27 -0115h

-20-

P52 - lMU REALIGNRecord gyro torqu~ng anglesRp~----

YIf-7gt-Lno--re-c-ycle PS2If conflrmed use SCS for EMS entry

GDC ALIGNIf drlft gtLOohr change ratesource

FINAL STOWAGEOPTICS (except for hybrid)ORDEALGLY TO RAD SEC - BYPASS (verlfy)CooL pnl lnstalledY-Y struts (2) extendedStow Data Box R-12

EMS CHECKEMS FUNC - OFFcb EMS (2) - closeEMS MODE - STBYEMS FUNC - EMS TEST 1 (walt 5 sec)EMS MODE - NORMAL (walt 10 sec)

Check ind lts - offRANGE lnd - 00Slew halr1ine over notch

In self-test patternEMS FUNC - EMS TEST 2 (walt 10 sec)

05G It - on (all others out)EMS FUNC - EMS TEST 3

05G It - onRSI Lower It - on (10 sec Qater)Set RANGE counter to 58 nm+OO

EMS FUNC - EMS TEST 405G It - on (all others out)G-V trace w~thin pattern to lwr rt

corner 9GRANGE lnd counts down to 0+02

EMS FUNC - EMS TEST 505G It - onRSI upper lt - on (10 sec later)RANGE md - 00SCrlbe traces vertlcal llne 9g to

022+01ALIGN SCROLL TO ENTRY PATTERN (on

37K ft sec hne)EMS FUNC - RNG SET

G-V scroll assy traces vert llne022g to 0+01

EMS MODE - STBY

28

29

30 -OllOh

-21-

~V TEST (Deorb~t only)EMS FUNC - ~V SETVHF RNGSET ~V ~nd to 15868 fpsEMS MODE - NORMALEMS FUNC - ~V TEST

SPS THRUST LT - onoff (10 sec)~V ~nd stops at -01 to -415

EMS MODE - STBY

PRIMARY WATER EVAP ACTIVATIONGLY EVAP H20 FLOW - AUTOGLY EVAP STH PRESS - AUTOPRI ECS GLY PUMP - ACI

CM RCS PREHEATNote If sys test mtr 5cd6abcd

all read 39 vdc (28degF) or moreom~t preheat

cb RCS LOGIC (2) - closeCM RCS LOGIC - ONUP T1M CM - BLOCK (ver~fy)

cb CM RCS HTRS (2) - closeCM RCS HTRS - ON (LMP Conf~rm)

(20 mlU or III lowest rdg lS39 vdc) (Moultor Maufpress for press drop)

31 (___) FINAL GDC DRIFT CK (If req I d)If drlft gtlOohr Suspect GDC Do not

use RSI amp FDAI 2

32 -OO5Om

33

34

35

TERM CM RCS PREHEATUP TLM CM - BLOCK (venfy)CM RCS HTRS - OFFCM RCS LOGIC - OFF

SYSTEMS TEST PANEL CONFIGURATIONSYS TEST METER - 4BRNDZ XPNDR - OPERATECM RCS HTRS - OFFWASTE H20 DUMP - OFFURINE DUMP - OFF

LEB LIGHTING - OFF

SEC WATER EVAP ACTIVATIONGLY To RAD SEC vlv - BYPASSSEC COOL EVAP - EVAPSEC COOL PUMP - AC2

36

37

38 -OO45m

-22-

PYRO BATT CKcb PYRO A SEQ A - close (ver~fy)

cb PRYO B SEQ B - close (verify)DC IND - PYRO BAT A(B)

~If PYRO BAT A(B) lt 35 vdc cb PYRO A(B) seq A(B) - open~

PYRO A(B)BAT BUS A(B)TO PYRO~MN BUS TIE - close

cb MNA BAT C - closecb MNB BAT C - closeDC IND - MNBPNL 8 - All cbs closed except

PL VENT - open (ver~fy)

FLOAT BAG (3) - open (ver~fy)

DOCKING PROBE (2) - open (verlfy)EDS BAT (3) - open (ver~fy)

CM ReS HTRS (2) - open

CM RCS ACTIVATIONcb SECS ARM (2) - close (verlfy)cb SECS LOGIC (2) - close (verlfy)SECS LOGIC (2) - ONMSFN conflrm GO for PYRO ARM(~f poss)SECS PYRO ARM (2) - ARMCM RCS PRPLNT 1amp2 - ONCM RCS PRESS - ONRCS Ind sw - eMl then 2

He PRESS 3700-4400 pSlaMANF PRESS 287-302 pSla

SECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFF

P27 amp ENTRY PAD UPDATEGo To Entry Checkllst

Superclrc - pg ~2~3 _Hybnd - pg -----2~9L-__Normal Deorblt - pg __3L5L- _

-23-

52 SUPERCIRCULAR ENTRY

1 SET DET (up to ET)

2

3

4

5

3000(-30-00)

EMS INITIALIZATIONSET RNG TO PAD DATA RNGEMS FUNC - Vo SETSlew Scroll to Pad Data VIOEMS FUNC - ENTRY

RS I ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on (up)GDC ALIGN PB - PUSH amp HOLDYAW Tw - Pos~t~on RSI thru

45deg amp back to LIFT UPGDC ALIGN PB - ReleaseEMS ROLL - OFFA1~gn CDC to lMU

CM RCS RING A CKRCS TRNFR - CMcb CM RCS LOGIC MNB - openAUTO RCS SEL MNB (6) - OFFSC CONT - SCSTest R~ng A ThrustersSC CONT - CMCRCS TRNFR - SMAUTO RCS SEL (12) - MNAMNB

(hftoff conflg)cb CM RCS LOGIC MNB - close

OPTICS PWR - OFFCMP to COUCH

MN BUS TIE (2) - ONTAPE RCDR - REWIND

6 35middot0Om(-25middot 00)

-24-

SEPARATION CK LISTTVC SERVO PWR 1 - AClMNAcb ELS (2) - close (ver1fy)PRIM GLY TO RAn - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY vlv - OFFCAB PRESS REL vlv (2) - NORMGMBL MTRS (4) - STARTABORT SYS PRPLNT - RCS CMD (venfy)SM RCS PRIM PRPLNT (4) - ONVHF 11M (AampB) - OFFHI GAIN ANT PWR - OFFFC PUMPS (3) - OFFVer1fy s1ugle SU1t compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - 10101cb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2) - opencb HTRS OVLD (2) - openPOT H20 RTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANSEC COOL EVAP - RESETSEC COOL PUMP - off (etr)

MtiVR TO CMSM SEP P R ATTSC CONT - SCSCMC MODE - FREEMNVR TO PAD ATTR (0deg)PY----W)

-25-

SUPERCIRCULAR ENTRY (Cont~nued)

1

4100m(-1900)

P61 - ENTRY PREP

V37E 61E

k 05 09 01427 - ROLL REVERSED 05 09 01426 - IMU UNSAT ~

2 F 06 61 IMPACT LAT LONG HDS UPDN (+-)PRO (010

fps +00001)

3 F 06 60 GMAXVPREDGAMMA EIRecord

GMAXV400K----

GAMMA EI _PRO

(01deg fpsOldeg)

4 F 06 63 RTOGO (lnm) PAD _VIO (fps) PAD _TFE(m~n-sec)

Compare w~th ~M~SFN==C~f~o-r~P~GNS GONO GOIf NO COMM Set RTOGO amp VIO In EMS

amp lnltla11ze(ACCEPT) PRO(RECALC) V32E To 4

5 F 50 25

4300m

(-1700)

45 oOm(-1500)

500Om(-1000)

6 F 06 61

-26-

P62 - CMSM SEP amp PRE-ENTRY MNVRCAUTION Call No EXT Verbs In P62

00041 REQUEST CMSM SEPSC CONT - SCSFREE

COMPARE PITCH ATT WITH PAD DATA ---0=-

(W~thLU 5deg)YAW - 45deg OUT-OF-PLANE (LEFT)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTIRATE 2MN BUS TIE (2) - ON (ver~fy)

PRIM GLY TO RAD - BYPASS (verlfy)CM RCS LOGIC - ON (venfy)SECS LOGIC (2) - on (up)SECS PYRO ARM - ARMCMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 ps~a

CM RCS LOGIC - OFFSECS PYRO ARM (2) - SAFEMonltor VMAB

If lt25 vdc go to EMERGPOWERDOWN pg E6-l

AUTO RCS SEL AC ROLL (4) - OFFAUTO RCS SEL CM 2(6)-OFFAUTO RCS SEL CM 1(6)-MNAYAW back to 0degPITCH TO HORIZ TRACK ATT

ROLL - 0deg (LIFT UP)PITCH - 400K Horiz Mark (317deg)YAW - 0deg

ATT DB - MAXMAN ATT PITCH - ACCEL CMDEMS DATA - Ver~fy

EMS FliNC - ENTRY (ver~fy)

EMS MODE - NORMALcb SPS PampY (4) - openMAINT HORIZ TRK

PRO (Act ENTRY DAP)

IMPACT LATLONGHDSDN (01deg01deg-00001)PRO

7 POSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axis beyond 45deg of Vel vector)

8 06 64

58middot00m(-0200)

9

05G tlme(+0 )

(--=---)

06 68

-27-

P63 - ENTRY INIT

GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PIJR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRmDHORIZ CKPltch error needle goes toward

zero approachlng OSG tlmeMAN ATT (PITCH) - RATE CMD

If CMC lS GOBMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS I

FLY BETA If CMC NO GO ilt

1 SC CaNT - SCS I

FLY EMS k

p64 - ENTRY POST 05G

RTOGO AT 05G AGREES HITH EMS-venfyHORIZ CK05G Lt - ON (EMS START)

No EMS START wlthln 3 sec ~ EMS MODE - BACKUP VHF RNG c

05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds Llft DN

NNVR Llft DNEMS GONO GO

G-V Plot wlthln IlmltsRng ctr dwn 60plusmn7 durlng 10 sec

perlodMonltor G-meter for

convergence wlth pad data (Do)(Vlt27K fps) Go to 13

-28-

P65 - ENTRY - UP CONT (Vgt27K fps)

10 F 16 69 BETA (01middot) _DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT lt~ SC CONT - SCS FLY EMS

PRO

11 06 68 BETAVIHDOT (OIdegfpsfps)(VltV1+500 fps amp RnOT Neg) Go To 13

P66 - ENTRY - BALLISTIC (D(DL)

12 06 22 DESIRED GMBL ANGLES RPYMoultor horlz +12middot of 317middot mark

P67 - ENTRY - FINAL PHASE (02G)

13 06 66 BETACRSRNG ERRDNRNG ERR(010 1um 1um)

KEY VERBRecord DNRNG ERR _KEY RLSEMoultor l~ft vector ou RSI amp FDAI

16 67 RTOGOLATLONG (Vrel=1000fps)(lumOldegOldeg)

SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOWNMonitor a1t~meter

Go To EARTHLANDING pg ---4L5 _

-29-

53 GampN HYBRID DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL tV1 V37E 30E

2 F 06 33 GETI(ACCEPT) PRO (hrm~n Olsec)(REJECT) LOAD DESIRED GETI

3 F 06 81 tVXYZ (LV) (lfps)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

4 F 06 42 HAHPtV (lnm lfps)Record tV

(ACCEPT) PRO(REJECT) Reselect P30 or P27 Load new paramo

5 F 16 45 MTFIMGA (marksm~n-secOlO)

MGA -00002 ~f k

k lMU not al~gned

SET DETPRO

6

7

8

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (Pull)PLSS 02 vlv - FILL02 8M SUPPLY vlv - OFFCAB PRESS REL vlv (2) - NORMcb ELS (2) - closecb SECS ARM (2) - closecb SECS LOGIC (2) - close (ver~fy)

AUTO RCS SEL CM (12) - MNA or ~ffiB

(hftoff conhg)ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM (AampB) - OFF

CMP to Couch

9

10

11

-30-

MNVR TO PAD BURN ATTLOAD DAPBMAG MODE (3) - RATE 2SC CONT - CMCAUTOATT DB - MINMAN ATT (3) - RATE CMD

v62E

v49E

12 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLES

PRO

13 F 50 18 REQ MNVR TO FDAI RPY ANGLES (01deg)(AUTO) PRO(MAN) SC CONT - SCS

BMAG MODE (3) - RATE 2MNVR To 15

14 06 18 AUTO MNVR TO FDAI RPY ANGLES (01deg)

15 F 50 18 REQ TRIM TO FDAI RPY ANGLES (01deg)(TRIM) Go to 13(ByPASS) ENTR

16

17

CHECK BORESIGHT amp SKT STARSOPT MODE - CMCOPT ZERO - OFF

v41 N91E

18 F 21 92 SHAFTTRUN (01deg 001deg)Load SXTS angles

19 41 OPTICS DRIVECheck SKT STAR

OPT ZERO - ZEROCheck BORESIGHT STAR (~f ava~l)

20 V25 N17E (01deg)Load Pad Data GMBL Angles

for CM BURN ATTATT SETtw - SET

to PAD DATA GMBL ANGLESfor CM BURN ATT

21

22

-31-

PHR REDUCTIONHGA PHR - OFFFC PUMPS (3) - OFFVerify s~ngle su~t compr oper loads

balancedFC 2 MN AampB - OFFS BD PiR AMP - LOWcb ECS RAD CONTHTR (2) - opencb HASTE H20URINE DUMP HTRS(2)- opencb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANMN BUS TIE (2) - ONTVC SERVO PHR 1 - AC1MNAGMBL MTR (4) - START

p41 - RCS THRUSTINGV37E 41E

23 F 50 18 REQ MNVR TO LCL HORIZ (HDS ON)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CMCAUTOPRO To 24

(gtfANDAP) BMAG MODE (3) - RATE 2SC CONT - CMCHOLD

V62EMNVR To 25

24 06 18 AUTO MNVR TO FDAI RPY

25 F 50 18 REQ TRIM TO LCL HORIZ (01deg)ALIGN SC ROLL

(AUTO TRIM) PRO To 24(BYPASS) ATT DB - MIN

RATE - LOHMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTlRATE 2

ENTR

550Om26 06 85

59middot2527

-32-

VGXYZ (1fps)RECHECK BORESIGHT STARTRANS CONIR PWR - on (up)EMS MODE - STBY (ver~fy)

EMS FliNC - bV SETVHF RNGSET (IV for SM BURN _EMS FliNC - bVS BD ANT - OMNI CSECS LOGIC (2) - ONMSFN conhrm Go for PYRO ARMSECS PYRO ARM (2) - ARMCM RCS LOGIC - ON (ver~fy)

DSKY BLANKS

593028 16 85 VG XYZ (AVE G ON) (lfps)

RHCs amp THC - ARMEDLIMIT CYCLE - OFFTAPE RCDR - CMD RESETHBREMS MODE - NORMAL

000029 F 16 85 REQ NULL VG XYZ (lfps)

BURN EMS bV CTR TO ZERORESET DET amp COUNT UP

If SM ONLY burn go to step 32THC - LOCKEDSC CaNT - SCSFREERATE - HIGHPRIM GLY To RAD - BYPASS (ver~fy)

MN BUS TIE (2) - ON (ver~fy)

CMSM SEP (2) - on (up)CSMLM FNL SEP (2) - on (up) (verify)CampW MODE - CMRCS TRNFR - CMCM RCS LOGIC - OFF

Momtor VM ABIf lt25 vdc go to EMERGPOWER DOWN Pg E6-l

V63E

If CMC NO GO FDAI SOURCE - ATT FDAI SEL - 1 or 2 ATT SET - GDC

SET

-33-

~Uili ATT PITCH - ACCEL CMDFDAI SCALE - 55MNVR TO CM BURN ATT (NULL ERR NEEDLES)

R 0degPY --00--

30

31

CM RCS BURNRHC III-ContJnuous PJtch DownRHC HZ-Module PJtch to null needlesBURN VGZ TO ZERO

If only 1 RHC Pulse + P=5deg from retro att MaJnta~n rates lt3degsec

BURN COMPLETION ATllV CTR= or DET= _

V8ZE

32 F 16 44 HAHPTFF (1nmffiJn-sec)Check HP-

If gt Pad data contJnue burnuntJ1 lt Pad

PRO

33 F 16 85 VGXYZ (Ups)Read VG resJduals to MSFN

(HYBRID) PRO to 34(SM ONLY BURN)

PROF 37 ODE

EI-1500 V37E 47EF 16 83 twx Y Z (Ups)

SC CONT - SCSFREEMAN ATT (PITCH) - RATE CMDRATE - HIGHPRIM GLY To RAD - BYPASS (verJfy)MN BUS TIE (2) - ON (verJfy)CMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verJfy)Campl MODE - CMRCS TRNFR - CMCM ReS LOGIC - OFFSECS PYRO ~I (2) - SAFE

-34-

PROMonitor VMAB

If lt25 vdc go to EMERGPOWER DOWN

34 F 37 OOEPCM BIT RATE - LOWATT DB - MAXEMS MODE - STBYEMS FUNC - OFF

Go To EARTH ORBIT ENTRY pg _--40-__

-36-

8 SPS THRUSTING PREPCYCLE CRYO FANSSPS GAGING - ACI (ver~fy)

PUG MODE - NORM (venfy)BMAG MODE (3) - RATE 2tv CG - CSMCMC MODE - FREEAUTO RCS SEL (16) - MNA or HNB

(hftoff conbg)SC CONT - CMCAUTO

9 MNVR TO PAD BURN ATTV62E

10 V49E

11 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLESPRO

12 F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) PRO(HAN) SC CONT - ses

MNVR to 14

06 18 AUTO MNVR TO FDAI RPY ANGLES13

14 F 50 18 REO TRIH TO FDAI RPY ANGLES(TRIM) Go to 12(BYPASS) ENTR

15 BORESIGHT STAR CHECK

16 V37E 40EOPT PWR - OFF

17 F 50 18 REQUEST MNVR TO FDAI RPY ANGLES (01deg)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CHCAUTOPRO to 18

(MANDAP) BMAG HODE (3) - RATE 2SC CONT - CMCHOLDMNVR to 19

(HANseS) se eONT - sesMNVR to 19

-35-

54 NORMAL DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL ~V

1 V37E 30E

2 F 06 33 GETI (hrm~nOlsec)

(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

3 F 06 81 ~VXYZ (LV)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

( lfps)

4 F 06 42 HAHP~V (1nmlfps)Record W

(ACCEPT) PRO -----(REJECT) Rese1ect P30 or P27 Load new pa~am

5 F 16 45 MTFIMGA (marksmln-secOldeg)MGA -00002 If ~ lMU not a1~gned

SET DETPRO

6

7

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY v1v - OFFCAB PRESS REL v1v (2) - NORMcb ELS (2) - close (verify)cb SECS ARM (2) - close (ver~fy)

cb SECS LOGIC (2) - close (verlfy)AUTO RCS SEL CM (12) - ~mA or MNB

(l~ftoff conf~g)

ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM AampB - off (ctr)

18

-37-

06 18 AUTO MNVR TO FDAI RPY ANGLES (01 0)

19 l 50 18 REOUEST TRIM MNVR TOALIGN SIC ROLLGDC ALIGN

FDAI RPY ANGLES(010

)

+54-00m(-06-00)

TIG-5mJn

5500m(-0500)

TVC CHECK amp PREPcb STAB CONT SYS (all) - closecb SPS (12) - closeATT DB - MINRATE - LOl~

LIMIT CYCLE - ONMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE 2ROT CONTR PWR DIRECT (2) - OFFSCS TVC (2) - RATE CMD

If SCS SCS TVC (2) - AUTO SC CONT - SCS ~

TVC GMBL DRIVE PampY - AUTOMN BUS TIE (2) - ONTVC SERVO PWR 1 - AC1MNA

2 - AC2MNBTRANS CONTR PWR - ONROT CONTR PWR NORMAL 2 - ACRHC 2 - ARMED

HORIZ CHK - HorJz on 12deg wJndmlmark (LJffiJt +3 0 PNGCS GONO GO)

If NO GO set tw 180 0 180deg0 0

Track horJz wJth 24deg wJndow markAt TIG-2 mJn Ahgn GDC

PRIMARY TVC CHECKGMBL MOT P1-Y1 -STARTON(LMP confJrm)

If SCS verJfy Thumbwheel TrJmTHC - CWVenfy NO MTVC

SEC TVC CHECKGHBL MOT P2-Y2 -STARTON(LMP confJrm)SET GPI TRIHVenfy MTVCTHC NEUTRALGPI returns to 00 (CMC) or trJm (SCS)ROT CONT Pl~ NORM 2 - ACDC

(TRIM) Go to step 17(BYPASS) BMAG MODE(3) - ATTIRATE2 (ver1fy)

ENTR

-38-

20 F SO 25 00204 GMBL TEST OPTION(ACCEPT) SC CONT - GMC (ver~fy)

PROMonitor GPI Response

0020-2000020-200Tr~m

TEST FAIL SC CONT - SCS SCS TVC (2) - AUTO

(REJECT) ENTR

21 06 40 TFIVG~VM (m~n-sec1fps)

PROG ALM - TIG s1~pped

V5N9E 01703

KEY RLSE To 21 ROT CONTR PWR DIRECT (2) - MNABSPS He v1vs (2) - AUTO (ver~fy)

LIMIT CYCLE - OFFFDAI SCALE - SOIScb SPS P2Y2 - open (for cr~t burn)

5800(-02 00)

5925(-0035)

59middot 30(-0030)

06 40

59XX(-OOXX)

AV THRUST A(B) - NORMALTHC - ARMEDRlIC (2) - ARMEDTAPE RCDR - GID RESETHBR

DSKY BLANKS

(AVE G ON)EMS MODE - NORMAL

TFIVG~VM (m~n-seclfps)

CHECK PIPA BIAS lt2fps for 5 sec

ULLAGE AS REQ

IF NO ULLAGE DIR ULLAGE PB - PUSH~

CONTROL ATT WRlIC MONITOR AVM (R3) COUNTING UP

5955(-0005)

F 99 40 ENG ON ENABLE REQUEST(AUTO IGN) PRO AT TFI gt0 sec(BYPASS IGN) ENTR to 24

22 0000 IGN

-39-

If SCS - THRUST ON PB - PUSH

06 40 TFCVG~VM (m~n-seclfpslfps)

~F 97 40 SPS Thrust fall ~

~(RESTART) PRO To IGN (RECYCLE) ENTR To TIG-05 sec

SPS THRUST LITE - ONMONITOR THRUSTING

Pc 95-105 pSlaEMS COUNTING DOWNSPS IN3 v1vs (4) - OPENSPS He v1vs tb (2) - graySPS FUELOXID PRESS - 175-195 pSlaPUGS - BALANCED

PROG ALARM V5N9E 01407 VG INCTHC - CW FLY MTVC

ECOEMER SPS CUTOFF J

AV THRUST (2) - OFF

23 F 16 40 TFC(STATIC)VG~VM (mln-seclfps)~V THRUST AB - OFF

SPS IN3 v1vs (4) - CLOSEDSPS He tb (2) - bp

cb SPS P2Y2 - closed (verlfy)TVC SERVO PHR - AC1MNA (venfy)TVC SERVO PWR 2 - OFF

PRO

24 F 16 85 VG XYZ(CM) CUps)NULL RESIDUALSRECORD ~V CTR amp RESIDUALS I1VCEMS FUNC - OFF VGXEMS MODE - STBY VGYBMAG MODE (3) - RATE 2ATT DB - MAX VGZTRANS CONT PHR - OFF

PRO

25 F 37 V82E

26 F 16 44 HAHPTFF (lnmm~n-sec)

R3-59B59 HP gt494 nmPRO

27 F 37 OOE

-40-

55 EARTH ORBIT ENTRY

1 Venfy CMSMR __

P_shyY_-

SEP ATT(180deg)

(0deg )

2

3

4

EMS INITIALIZATIONEMS FUNC - RNG SETSET RNG TO PAD DATA RNGEMS FUNC - VA SETSlew scroll to pad data VIOEMS FUNC - ENTRY

RSI ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on(up)GDC ALIGN PB - PUSH amp HOLDYAW tw - Pos1tion RSI thru 45deg amp

back to LIFl UPGDC ALIGN PB - RELEASEEMS ROLL - OFFAl1gn GDC to lMU

PWR REDUCT (Norm Deorb Only)HGA PWR - OFFFC PUMPS (3) - OFFVer1fy s1ngle suit compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - Lowcb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2)-openlOb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MAN

-41-

P61 - ENTRY PREP

5 V37E 61E05 09 01427 - ROLL REVERSED05 09 01426 - IMU UNSAT

6 F 06 61 IMPACT LAT LONG liDS UPDN (+-)(01 0

010

+00001)

PRO

PAD VALUESLATLON==G------liDS UP DN _

7 F 06 60 GMAXV400KGAMMA EIRecord

GMAXV400K----GAMMA EI _

PRO

8 F 06 63 RTOGO (1nm) PAD _VIa (fps) PADTFE (mln-sec) ----Compare wlth MSFN for PGNS GONO GONO COMM SET RTOGO amp VIO IN EMS amp

INITIALIZE(ACCEPT) PRO(RECALC) V32E to 8

-42-

P62 - CMSM SEP amp PRE-ENTRY MNVR

9 F 50 25 00041 REQUEST CMSM SEPSC CONT - SCSFREEYAW - 45deg out-of-plane (left for RCS

nght for SPS)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE2PRIM GLY to RAD - BYPASS (verlfy)SECS LOGIC (2) - on (up)MSFN conflrm GO for PYRO ARMSECS PYRO ARM - ARMMN BUS TIE (2) - ON (verlfy)CMSM SEF (2) - ONCSMLM FNl SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 pSlaCM RCS LOGIC - OFFSECS PYRO ARM - SAFEMonltor VMAB

If lt25vdc go to EMERG POWERDOWN Pg E6-1AUTO RCS SEL AlC ROLL (4) - OFFAUTO RCS SEL CM 2(6) - OFFAUTO RCS SEL CM 1(6) - MNA or MNBYAW back to 00

PITCH TO ENTRY ATTROLL 0deg (LIFT UP)PITCH - HORIZ on 317deg MARK (400K)YAW 00

ATT DB - MAXMAN ATT (PITCH) - ACCEL CMDEMS DATA - VerifyEMS FUNC - ENTRY (verlfy)EMS MODE - NORMALMAINTAIN HORIZ TRK

PRO (Act ENTRY DAP)

10 F 06 61 IMPACT LAT LONG HDSDN(010 010 -00001)

PRO

11 FOSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axlS beyond 45deg of Vel vector)

-43-

P63 - ENTRY INIT

12 06 64 GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PWR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRHORIZ CKP~tch error needle goes toward

zero approach~ng 05G t~me

MAN ATT (PITCH) - RATE CMDIf CMC ~s GO

BMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS FLY BETA If CMC NO GO ~

SC CONT - SCS~

FLY EMS RCS Deorh Roll HDS UPTRACK HORIZ w~th 29deg w~ndow mk

P64 - ENTRY POST 05G

13

05G t=elt+0___)

06 68

RTOGO AT 05G AGREES WITH EMS - venfyHORIZ CK05E Lt - on (EMS start)

No EMS start w~th~n 3 secsEMS MODE - BACKUP VHF RNG 05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds L~ft DN

NNVR L~ft DNEMS GONO GO

G-V Plot w~th~n llm~ts

Rng ctr dwn 60 + 7 durlng 10 sec per~od

Mon~tor G-meter forconvergence wlth pad data (Do)

(Vlt27K fps) Go To 17

-44-

P65 - ENTRY - UP CONT (Vgt27K fps)

14 F 16 69 BETA (01deg)DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT~

SC CONT - SCS FLY EMS

PRO

15 06 68 BElA VI HOOT (01deg fpsfps)(VltVL +500 fps amp RDOT Neg) Go To 17

p66 - ENTRY - BALLISTIC (DltDL)

16 06 22 DESIRED GMBL ANGLES RPY (01deg)Mon~tor hor~z +12deg of 317deg mark

P67 - ENTRY - FINAL PHASE (02G)

17 0666 BETACRSRNG ERRDNRNG ERR (Oldeglnmlnm)KEY VERBRecord DNRNG ERR _KEY RLSEL~m~t +100nm from PAD DRE

Mon~tor l~ft vector on RSI amp FDAIF 16 67 RTOGOLATLONG (Vre1=1000fps)

(lnm 010 01deg)SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOlfflMon~tor altimeter

Go To EARTHLANDING pg _I4L5__

-45-

56 EARTHLANDING

90K STEAM PRESS - PEGGED50K CABIN PRESS REL vIv (2) - BOOSTENTRY

SECS PYRO ARM (2) - ARM

40K(90K + 63s)

CM UNSTABLE RCS CMD - OFF ~ 40K APEX COVER JETT PG-PUSH DROGUE DEPLOY PG - PUSH (2 secafter apex cover Jett)

30K ELS LOGIC - ON (up)ELS - AUTO

24K RCS hsable (auto)(90K+92s) RCS CMD - OFF

Apex cover Jett (auto)APEX COVER JETT PB - PUSH

(WAIT 2 SECS)Drogue parachutes deployed (auto)

DROGUE DEPLOY PB - PUSH~

If Drogues FallELS - ~ ~Stablllze CM 5K MAIN DPLY PB - PUSHELS - AUTO

235K Cabln Pressure lncreaslng (Drogues + 50s)If not lncreaSlng by 17K CABIN PRESS REL vlv (RR) - DUMP

-46-

10K Maln parachutes deployedMAIN DEPLOY PB - PUSH (wlthln 1 sec)VHF ANT - RECYVHF AMA - SIMPLEXVHF BCN - ONCABIN PRESS REL v1v (2) - CLOSEDIRECT 02 vlv - OPENCM RCS LOGIC - on (up)CM PRPLNT - DUMP (burn audlb1e)Monltor CM ReS 1amp2 for He press decrease

NO BURN or PRESS DECREASE USE BOTH RHCs DO NOT FIRE PITCH JETS

CM PRPLNT-PURGE (to zero He press)CM RCS He DUMP PB - PUSH RHC (2) - 30 sees NO PITCH k

STRUT LOCKS (2) - UNLOCK

cb FLT amp PL BAT BUS ABampBAT C (3) - closecb FLT amp PLT MNA amp B (2) - opencb ECS RAD HTR OVLD (2) - opencb SPS PampY (4) - open

3K CABIN PRESS REL v1v (RH) - DUMP (after purgecompleted)

FLOOD Lts - POST LDGCM RCS PRPLNT (2) - OFFROT CONTR PWR DIRECT (2) - OFF

800 CAB PRESS RELF vlv - CLOSE (latch off)MN BUS TIE (2) - OFF

AFTER LANDINGcb MAIN REL PYRO (2) - closeMAIN RELEASE - on(up)

Go to POSTLANDING pg _47L-__

I

2

3

-47-

57 POSTLANDING

STABILIZATION VENTILATION COMMUNICATIONS

DIRECT 02 vlv - CLOSE

Stablllzation after landlngELS - AUTO (verlfy)cb MAIN REL PYRO (2) - close (venfy)MAIN RELEASE - on (up) (verlfy)S~CS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb BAT RLY BUS (2) - open

No contact w1th recovery forcesVHF AM AampB - off (ctr) ~

VHF AM Rev ONLY - A cb PL VENT - closecb FLOAT BAG (3) - closecb UPRIGHT SYS COMPRESS (2) - closeIf Stable II

FLOAT BAG(3)-FILL t1ll 2 m1n afterupr1ght then - OFF

VHF AM AlB amp BCN - OFF whlle lnvertedIf Stable I

After 10 M1n Coollng Per1odFLOAT BAG (3) - FILL 7 mln then OFF

Post Stab1lizat1on And Ventllat10nPL BCN LT - BCN LT LOWPL VENT vlv - UNLOCK (Pull)Remove PL VENT Exh CoverPL VENT - HIGH or LOWPL DYE MARKER - ON (swlmmer comm)Release foots traps and_restralntscb MNA BAT BUS A amp BAT C (2) - opencb MNB BAT BUS B amp BAT C (2) - opencb FLT amp PL BAT C - opencb PYRO A SEQ A - opencb PYRO B SEQ B - open

EACH HR - CHECK DC VOLTSgt 275 V If Notmiddot cb FLT amp PL-BAT BUS AampB (2) -open cb FLT amp PL BAT C (1) - open GO TO LOW POWER CHECKLIST

Unstow and lnstall PLV DISTRIB DUCTDeploy grappllng hook and 11ne 1f req

4

-48-

Post Landing Communlcatl0nsVHF ANT-RECY (venfy)VHF BCN - ON (verlfy)

If no contact ~lth recovery forcesperform VHF BEACON Check

MONITOR VHF BEACON transmlSSlonnth VHF AM B Rcvr andor Su)vlval

TransceiverkVHF Beacon not operatlng ~connect Surv~val TranscelVer to antcable behlnd VHF ant access pnland place radio ln BCN mode

LOW POHER CHECKLISTVHF BCN - OFFVHF AM (3) - RCVFLOOD Lts - OFFVHF AM AampB - off (ctr)VHF AM RCV ONLY - A (venfy)COUCH LIGHTS - OFFPOSTLANDING VENT SYS mlnlmlze useSURV RADIO - plug mto VHF BCN ANT cableconn behind VHF ant acess pnl amp turn radloon l-n BCN mode

EGRESS PROCEDURES

CMPCDRLMPCDR

CMPCDRCMP

LMPLl1PCDR

STABLE IDlsconnect Umblll-calsNeck darn onCenter couch - 270 0 positionArmrests stowedConnect raft to SIC l-f desl-red wlth

green lanyardConnect raft ~hl-te lanyards to SUltS amp

lnflate water wlngs when eXltl-ngHATCH PISTON PRESS vlv - PRESS (Outbd)Slde Hatch openedPL VENT - OFFcb Pnl 250 (all) - openEgress with 11feraftPut hardware klt outEgress

or CDIPALL

CMF

CDRCMF

CDR

LMF

CMFCMP LMFCMP

UlP

CDR

-49-

STABLE IIcb CREW STA AUDIO (3) - openD~sconnect umb~1~ca1s

Release foots trapsRelease restra~nt harnessCouch seat pans (3) - 170 0 pos1t10nArm rests stowedSurv1va1 k~ts removed from stowageConnect life raft ma~n1~ne to CDR or SicConnect f~rst wh~te lanyard from

11fe raft to suitConnect th~rd wh~te lanyard from

l~fe raft to SU1tConnect rucksacks together to yellow

lanyard on raft bagPRESSURE EQUALIZATION vlv - OPENRemove and stow fwd hatchEX1t feet f1rst w1th rucksacks when clear

of siC 1nflate water w1ngs and raftExit feet f1rst when clear of SiC

1nflate water w1ngsEX1t feet f1rst when clear of sic

1nflate water w1ngs

-50-

60 TLI ABORTS

TLI Aborts are conta~ned ~n the ESD s~nce the bulk of the funct~ons

concern entry preparat20ns and performance Th~s allows a s2nglesource of procedures for procedure rev2ew val~dat~on checkout andtra~n~ng These procedures ~ncorporate TLI preparat20ns as found ~n

reference 6 w~th the TLI Abort Procedures and these t~e 2nto normallunar return Entry Procedures found ~n sect20n 5 The guidel~nes

for th~s cont2ngency are spec2f2ed 2n reference 7

In2t2al preparat~ons for TLI pos2t20n the necessary system sW2tches2n add~t~on to perform~ng an EMS ~V test and a GDC al~gnment Afterthe DET ~s set for mon2tor2ng TB6 the CMP ~ncreases the 12ght levelof the LEB DSKY to max~mum and returns to the h2s couch Th2s 2Sdone so that the LEB DSKY can be observed ~n the event sunl~ght orreflect20ns wash out the ma2n d2splay panel DSKY dur2ng cr2t2calmaneuvers The crew then straps ~n and prepares for mon2tor~ng TB6as 2nd2cated by the SII SEP L~te The t2mes se~uence of procedures2S keyed on th~s d~splay and ~ncludes the DET START funct~on andSIVB IGNITION Dur2ng the burn the crew mon2tors the FDAIs foratt~tude excurs20ns and abnormal rates report~ng status checks toM~ss2on Control at d2screet t~mes dur2ng the maneuver Upon SIVBSHUTDOWN the eMP records the DSKY d~splayed performance parametersand awa2ts ground conf2rmat~on

The rat~onal for TLI aborts ~s descr~bed 2n reference 7 A summar2shyzat20n 2S extracted to prov2de background and gu2de12nes 2n th2sdocument The abort procedures cover aborts 10 m2nutes after conshyt2ngent SIVE shutdown and aborts 90 m2nutes after normal SIVE shutshydown t2me

The 10 m~nute TLI abort ~s des2gned to be used dur~ng TLI ~n theevent a spacecraft problem develops Wh2Ch can result 2n catastrophe2f ~mmed~ate act~on 2S not taken If the s~tuat20n perm~ts the crewshould always allow the SIVB to complete TLI at wh~ch t~me the groundand crew can perform a malfunct~on analys~s to determ~ne ~f an abort~s adv~sable If a fa~lure occurs that necess2tates the shutdown ofthe SIVB and the ~u~ck return of the crew to earth th~s abort ~s

des~gned to be as ~nsens~t~ve to execut~on errors as poss~ble andst21l be targeted to m2dcorr2dor The burn att~tude w~th the f~ed

hor~zon reference ~s a constant value for any shutdown t~me Theburn durat~on 2S a funct20n of shutdown t2me and 2S ava21able fromcrew charts S~nce the pr~mary purpose of th~s abort ~s to returnto earth as qU2ckly as poss2ble there are no restr2ct20ns as toland~ng locat~on However ~f the t~me to EI is greater than abouttwo hours a midcourse correct20n should be ant~c~pated

The 90 m2nute TLI abort 2S to be used 2f a cr2t2cal subsystem malshyfunct~on ~s determ2ned and the dec2s~on to abort ~s made after the

-51-

TLI cutoff and before TLI cutoff plus approxlmately 80 m1nutesTh1S allows suff1c1ent separatlon and procedural t1me to set upfor the SPS deorb1t burn performed at about TLI + 90 Note thatgenerally the deorb1t burns w1ll be performed a fe11 m1nutes beforeTLI + 90 accord1ng to crew charts shown In reference 8 The no-comm except10n requ1res that 90 m1nutes be the 1nput t1me of 19n1shytlon for P-37 (onboard return-to-earth abort program) so that onshyboard calculatlons can correspond w1th ground calculat10ns to computethe CM land1ng p01nt Th1S TLI abort lS des1gned so that returnfl1ght t1me does not exceed 18 hours and abort ~V does not exceed7000 fps ThlS abort can be performed uSlng chart ~Vs and attltudesand the earths hor1zon serves as a suff1c1ent reference The maneushyver lS targeted to ach1eve the mldcorr1dor entry target Ilne andtlmed to result 1n a deslgnated recovery area

It 1S ObV10US for abort deC1S1ons early 1n the TLI + 90 m1nute t1meshyframe that a GampN SPS burn should be performed In order to keep theTLI abort procedures cons1stent and w1th emphasls on slmpl1c1ty theprocedures here reflect a SCS SPS abort burn to cover the full abortdec1s1on t1meframe

A m1dcourse correct1on for corr1dor control after a TLI abort may bedeS1red 1f the SPS burn d1d not meet expectat1ons The TLIabortprocedures 1n th1S sect10n adapt to the normal lunar return tlmel1neand procedures pr10r to the f1nal MCC

-52-

61 TLI PREPARATION PROCEDURES

GET = 150

CRO AOS(___)

CRO LOS( )(22142)

5100

Don Helmets amp Gloves

XLUNAR - INJECT (verify)EDS PWR - on (venfy)EMS FUNC - OFF (verlfy)EMS MODE - STBYEMS FUNC - IW SETVHF RNGEMS MODE - NORMALSet ~V indo to +15868 fpsEMS FUMC - ~V Test

SPS THRUST Lt - onoff (10 sec)~V lnd stops at -01 to -415

EMS MODE - STBYEMS FUMC - ~V SETVHF RNGSet ~VC

EMS FUNC---~~V=----

GDC ALIGNFDAI Select - liZcb SECS LOGIC (Z) - close (verify)cb SECS ARM (Z) - closeSECS LOGIC (Z) - on (up)MSFN Conflrm GO for PYRO ARM (If pass)SECS PYRO ARM (Z) - on (up)TRANS CONTROL PWR - ONROT CONTR PWR NORMAL (Z) - ACDC(verlfy)ROT CONTR PWR DIRECT (Z) - MNAMNBLV INnGPI - SIISIVB (venfy)LV GUID - IU (venfy)cb DIRECT ULLAGE (Z) - closedSet EVENT TIMER to 5100Begin MONITOR For TB6

CMP to Couch

TB 6 - SII SEP Lt on (TIG-9 mln 38 sec)KEY V83E

SET ORDEALFDAI Z ORB RATE at 180 0 0SII SEP Lt out (38 sec later)Start DET COUNTING UPSC CaNT - SCS (verify)MONITOR LV TANK PRESS

~P lt 36 psid (OXID gt FUEL)~P lt Z6 psid (FUEL gt OXID)

EMERGENCY CSMLV SEP UP TLM CM - BLOCK (verify)UP TLM IU - BLOCK (venfy)

-53-

+45degPY))0middot sec PY

lOK nmltHAlt25K nm

Two phas~ng mnvrs two SPS mnvrs to circular~ze at 150 nmearth orb~t

CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ssion 4K nmltHAltlOK nm CSM amp1M - Two phasing mnvrs two SPS mnvrs to circularize at 150 nm earth orb~t CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ss~on

CSM amp 1M - Two phas~ng mnvrs APS burn todepletion th~rd phasing mnvrSPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn tosem~sync orb~t

25K nmltHAlt40K nm CSM amp 1M - Two phasmg mnvrs APS burn to depletion third phas~ng mnvr SPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn to sem~sync orbit HA)40K nm DPS ava~l - DPS LOll circularize with SPS

DPS not ava~l - Lunar flyby or CSM only to lunar orbit (if reqd gtV lt4000 fps)

V37E 47E (check b~as) Record -=--rshy(Limit 98 fpsmm)

( 1fps)tVXYZN62EVIHDOTHPAD (fpsfpslnm)MONITOR VI ( ) at ECO

SCS TVC SERVO PWR 1 - ACIMNA2 - OFF

TAPE RCDR - CMD RESETHBREMS MODE - NORMAL

SIr SEP Lt - ONTLI Inhib~t S~gnals w~11 not be honored after 5942

SIVB ULLAGE BeginsSII SEP Lt - off (TIG - 18 sec)SIVB FUEL LEADSIVB ULLAGE d~scont~nues

LV ENG I Lt - onSIVB IGNITION ( GETI)LV ENG I Lt - off - -shyMONITOR THRUST amp ATTITUDEMONITOR LV TANK PRESSSIVE ECO (Lt on) (BEGIN TB7)

EMER SIVE CUTOFF AT 6 SEC PAST BURN TIME IF VI ATTAINEDTHC CCW ampNEUTRAL IN 1 SEC or SIISIVB sW - LV STAGEPremature Shutdown HAlt4K nm CSM amp 1M -

5700

58205836

F 16 835800

F 16 62

5838594259525955595900000002SUNRISE(___)

HAW AOS(__=_) KEY VERB (freeze d~splay)

SIVB ATT HOLD 20 sec amp BEGIN VENTINGSIVB NNVR TO ORB RT (HDS DN) (3middot sec)

Record VI -c---HDOT _

HPAD _

KEY RLSEF 16 62

F 16 83

HAW LOS(__=-)

KEYmiddotRLSE~VXYZ (lfps)

Record ~VX---_

~vy

WZ--

AVC---_

TAPE RCDR - off (ctr)EMS MODE - STBYEMS FUNC - OFFSECS PYRO ARM (2) - SAFE

PRO

BURN STATUS REPORT

____--~TIG

BT------VGX____-R

-----P----_Y

REMARKS

_____VI

______--HDOT______--H______---AVC______---FUEL_______OXID

_______UNBAL

F 3708=00 OOEGOS AOS CMP TO LEB

(-=-=-)

0000

0003

0005

0014

0100

-55-

62 TLI 10 MIN ABORTSECS LOGIC (2) - on (up)SECS PYRO ARM (2) - ARM

TRANS CONTR - CGH (4 sec) amp +XDET RESET (verlfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS GMD-ON

TRANS GONTR - neutral then +X for10 sec

SIVBGPI s~ - GPIExcesslve rates 6V THRUST A - NORMAL SPS THRUST - DIRECT When rates damped 6V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

TRANS CONTR +X - OFFV37E OOE

PITGH UP to LOGAL VERT (+X axlSto~ard the earth)

RATE - LOWBMAG MODE (3) - ATTIRATE 2EDS PHR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SEGS ARM (2) - opencb EDS (3) - open

TRANS CONTR -X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (180deg)P (199deg)Y (0deg)

RETRO UPDATEGETI _

JV _VG

Jtb ---GET 400K _

05G _GET DROGUE _

ENTRY P _R _

Y_--

0945

-56-

ALIGN HORIZ ON RET +1 MKGMBL CHECK (T11lle Pentattlng)MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conflnn)cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FUMC - JV SETVHF RNGSET JV from chartE~S FUMC - JVEMS fODE - NOIDlAL

lV THRUST A - NORMALV37E 47E (THRUST fONITOR)

F 16 83 lVXYZ (1 fps)

0950

1000

NOTE For aborts durlng 1st mln of TLIKEY V82E F 16 44 (HaHpTff)Burn untll Hp lt 19NM

TRANS CONTR +X

THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN JV reqdJV THRUST (2) - OFFReport cutoff

cb SPS P2 Y2- closeGfBL MTRS (4) - OFF (LMP Confinn)TRANS CONT PWR - OFFTVC SERVO PWR (2) - OFFMN BUS TIE (2) - OFFcb SPS P1amp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREIf est time to EIltOl5500 omlt fCC andenter the SUPERCIRC CKLIST as early as pos-slb1e Pg ~2~3~ __If est time to EI)Ol5500 anticlpate afCC Enter the ENTRY PREP CKLIST at step 9pg 18

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

-2tl C

l I W gt- ~-4

z laquo I I- 0 -6

l- I J u gt- ~-8

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STE

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26

28

30

32

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-i- rtREQUIRED PITCH GIMBAL ANG LETO OBTAIN HOR-IZON AT 317

DEGREES IN wiiiiDOW

260

z~I- ~ i5 24000

1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

-I

-1-

NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

I LU HD~-

LUHD

lt0 120UJ0

~

80 HOLD PRESENT TRIMgt LU HD013

~Y~HOIgtlt

TOP OF WINDOWa 40to

31 7 SCRIBEaaI

80 TTOM OF WINDOWi= 0

0--ltoa

-40t-z

~~~Uw w u lt0 -80

HOLO PRESENT TRIlJCl

LOHU0 lt0

J gt -120 HOLD 059 TRIMlt0 z

LDHUlt0 FIELD OF VI S10 NLDHU LIFT-DOWNHEADS -UPLUHD LIFT-UP HEADS-DOWN

~~H~-160 q - P63 LIMITI- NOrE-VALIO ONLY FO~t~--

LUNAR RETURN VELOCITY

plusmnl8020 244middot 8 12 16

TIME TO 400K FT ALTITUDE-MIN

4

P37

LONG

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Cll-

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120

200

241)

320

400

441)

520

TlI

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ABOR

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-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 23: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

24 -0135h

25(___)

26

27 -0115h

-20-

P52 - lMU REALIGNRecord gyro torqu~ng anglesRp~----

YIf-7gt-Lno--re-c-ycle PS2If conflrmed use SCS for EMS entry

GDC ALIGNIf drlft gtLOohr change ratesource

FINAL STOWAGEOPTICS (except for hybrid)ORDEALGLY TO RAD SEC - BYPASS (verlfy)CooL pnl lnstalledY-Y struts (2) extendedStow Data Box R-12

EMS CHECKEMS FUNC - OFFcb EMS (2) - closeEMS MODE - STBYEMS FUNC - EMS TEST 1 (walt 5 sec)EMS MODE - NORMAL (walt 10 sec)

Check ind lts - offRANGE lnd - 00Slew halr1ine over notch

In self-test patternEMS FUNC - EMS TEST 2 (walt 10 sec)

05G It - on (all others out)EMS FUNC - EMS TEST 3

05G It - onRSI Lower It - on (10 sec Qater)Set RANGE counter to 58 nm+OO

EMS FUNC - EMS TEST 405G It - on (all others out)G-V trace w~thin pattern to lwr rt

corner 9GRANGE lnd counts down to 0+02

EMS FUNC - EMS TEST 505G It - onRSI upper lt - on (10 sec later)RANGE md - 00SCrlbe traces vertlcal llne 9g to

022+01ALIGN SCROLL TO ENTRY PATTERN (on

37K ft sec hne)EMS FUNC - RNG SET

G-V scroll assy traces vert llne022g to 0+01

EMS MODE - STBY

28

29

30 -OllOh

-21-

~V TEST (Deorb~t only)EMS FUNC - ~V SETVHF RNGSET ~V ~nd to 15868 fpsEMS MODE - NORMALEMS FUNC - ~V TEST

SPS THRUST LT - onoff (10 sec)~V ~nd stops at -01 to -415

EMS MODE - STBY

PRIMARY WATER EVAP ACTIVATIONGLY EVAP H20 FLOW - AUTOGLY EVAP STH PRESS - AUTOPRI ECS GLY PUMP - ACI

CM RCS PREHEATNote If sys test mtr 5cd6abcd

all read 39 vdc (28degF) or moreom~t preheat

cb RCS LOGIC (2) - closeCM RCS LOGIC - ONUP T1M CM - BLOCK (ver~fy)

cb CM RCS HTRS (2) - closeCM RCS HTRS - ON (LMP Conf~rm)

(20 mlU or III lowest rdg lS39 vdc) (Moultor Maufpress for press drop)

31 (___) FINAL GDC DRIFT CK (If req I d)If drlft gtlOohr Suspect GDC Do not

use RSI amp FDAI 2

32 -OO5Om

33

34

35

TERM CM RCS PREHEATUP TLM CM - BLOCK (venfy)CM RCS HTRS - OFFCM RCS LOGIC - OFF

SYSTEMS TEST PANEL CONFIGURATIONSYS TEST METER - 4BRNDZ XPNDR - OPERATECM RCS HTRS - OFFWASTE H20 DUMP - OFFURINE DUMP - OFF

LEB LIGHTING - OFF

SEC WATER EVAP ACTIVATIONGLY To RAD SEC vlv - BYPASSSEC COOL EVAP - EVAPSEC COOL PUMP - AC2

36

37

38 -OO45m

-22-

PYRO BATT CKcb PYRO A SEQ A - close (ver~fy)

cb PRYO B SEQ B - close (verify)DC IND - PYRO BAT A(B)

~If PYRO BAT A(B) lt 35 vdc cb PYRO A(B) seq A(B) - open~

PYRO A(B)BAT BUS A(B)TO PYRO~MN BUS TIE - close

cb MNA BAT C - closecb MNB BAT C - closeDC IND - MNBPNL 8 - All cbs closed except

PL VENT - open (ver~fy)

FLOAT BAG (3) - open (ver~fy)

DOCKING PROBE (2) - open (verlfy)EDS BAT (3) - open (ver~fy)

CM ReS HTRS (2) - open

CM RCS ACTIVATIONcb SECS ARM (2) - close (verlfy)cb SECS LOGIC (2) - close (verlfy)SECS LOGIC (2) - ONMSFN conflrm GO for PYRO ARM(~f poss)SECS PYRO ARM (2) - ARMCM RCS PRPLNT 1amp2 - ONCM RCS PRESS - ONRCS Ind sw - eMl then 2

He PRESS 3700-4400 pSlaMANF PRESS 287-302 pSla

SECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFF

P27 amp ENTRY PAD UPDATEGo To Entry Checkllst

Superclrc - pg ~2~3 _Hybnd - pg -----2~9L-__Normal Deorblt - pg __3L5L- _

-23-

52 SUPERCIRCULAR ENTRY

1 SET DET (up to ET)

2

3

4

5

3000(-30-00)

EMS INITIALIZATIONSET RNG TO PAD DATA RNGEMS FUNC - Vo SETSlew Scroll to Pad Data VIOEMS FUNC - ENTRY

RS I ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on (up)GDC ALIGN PB - PUSH amp HOLDYAW Tw - Pos~t~on RSI thru

45deg amp back to LIFT UPGDC ALIGN PB - ReleaseEMS ROLL - OFFA1~gn CDC to lMU

CM RCS RING A CKRCS TRNFR - CMcb CM RCS LOGIC MNB - openAUTO RCS SEL MNB (6) - OFFSC CONT - SCSTest R~ng A ThrustersSC CONT - CMCRCS TRNFR - SMAUTO RCS SEL (12) - MNAMNB

(hftoff conflg)cb CM RCS LOGIC MNB - close

OPTICS PWR - OFFCMP to COUCH

MN BUS TIE (2) - ONTAPE RCDR - REWIND

6 35middot0Om(-25middot 00)

-24-

SEPARATION CK LISTTVC SERVO PWR 1 - AClMNAcb ELS (2) - close (ver1fy)PRIM GLY TO RAn - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY vlv - OFFCAB PRESS REL vlv (2) - NORMGMBL MTRS (4) - STARTABORT SYS PRPLNT - RCS CMD (venfy)SM RCS PRIM PRPLNT (4) - ONVHF 11M (AampB) - OFFHI GAIN ANT PWR - OFFFC PUMPS (3) - OFFVer1fy s1ugle SU1t compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - 10101cb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2) - opencb HTRS OVLD (2) - openPOT H20 RTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANSEC COOL EVAP - RESETSEC COOL PUMP - off (etr)

MtiVR TO CMSM SEP P R ATTSC CONT - SCSCMC MODE - FREEMNVR TO PAD ATTR (0deg)PY----W)

-25-

SUPERCIRCULAR ENTRY (Cont~nued)

1

4100m(-1900)

P61 - ENTRY PREP

V37E 61E

k 05 09 01427 - ROLL REVERSED 05 09 01426 - IMU UNSAT ~

2 F 06 61 IMPACT LAT LONG HDS UPDN (+-)PRO (010

fps +00001)

3 F 06 60 GMAXVPREDGAMMA EIRecord

GMAXV400K----

GAMMA EI _PRO

(01deg fpsOldeg)

4 F 06 63 RTOGO (lnm) PAD _VIO (fps) PAD _TFE(m~n-sec)

Compare w~th ~M~SFN==C~f~o-r~P~GNS GONO GOIf NO COMM Set RTOGO amp VIO In EMS

amp lnltla11ze(ACCEPT) PRO(RECALC) V32E To 4

5 F 50 25

4300m

(-1700)

45 oOm(-1500)

500Om(-1000)

6 F 06 61

-26-

P62 - CMSM SEP amp PRE-ENTRY MNVRCAUTION Call No EXT Verbs In P62

00041 REQUEST CMSM SEPSC CONT - SCSFREE

COMPARE PITCH ATT WITH PAD DATA ---0=-

(W~thLU 5deg)YAW - 45deg OUT-OF-PLANE (LEFT)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTIRATE 2MN BUS TIE (2) - ON (ver~fy)

PRIM GLY TO RAD - BYPASS (verlfy)CM RCS LOGIC - ON (venfy)SECS LOGIC (2) - on (up)SECS PYRO ARM - ARMCMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 ps~a

CM RCS LOGIC - OFFSECS PYRO ARM (2) - SAFEMonltor VMAB

If lt25 vdc go to EMERGPOWERDOWN pg E6-l

AUTO RCS SEL AC ROLL (4) - OFFAUTO RCS SEL CM 2(6)-OFFAUTO RCS SEL CM 1(6)-MNAYAW back to 0degPITCH TO HORIZ TRACK ATT

ROLL - 0deg (LIFT UP)PITCH - 400K Horiz Mark (317deg)YAW - 0deg

ATT DB - MAXMAN ATT PITCH - ACCEL CMDEMS DATA - Ver~fy

EMS FliNC - ENTRY (ver~fy)

EMS MODE - NORMALcb SPS PampY (4) - openMAINT HORIZ TRK

PRO (Act ENTRY DAP)

IMPACT LATLONGHDSDN (01deg01deg-00001)PRO

7 POSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axis beyond 45deg of Vel vector)

8 06 64

58middot00m(-0200)

9

05G tlme(+0 )

(--=---)

06 68

-27-

P63 - ENTRY INIT

GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PIJR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRmDHORIZ CKPltch error needle goes toward

zero approachlng OSG tlmeMAN ATT (PITCH) - RATE CMD

If CMC lS GOBMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS I

FLY BETA If CMC NO GO ilt

1 SC CaNT - SCS I

FLY EMS k

p64 - ENTRY POST 05G

RTOGO AT 05G AGREES HITH EMS-venfyHORIZ CK05G Lt - ON (EMS START)

No EMS START wlthln 3 sec ~ EMS MODE - BACKUP VHF RNG c

05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds Llft DN

NNVR Llft DNEMS GONO GO

G-V Plot wlthln IlmltsRng ctr dwn 60plusmn7 durlng 10 sec

perlodMonltor G-meter for

convergence wlth pad data (Do)(Vlt27K fps) Go to 13

-28-

P65 - ENTRY - UP CONT (Vgt27K fps)

10 F 16 69 BETA (01middot) _DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT lt~ SC CONT - SCS FLY EMS

PRO

11 06 68 BETAVIHDOT (OIdegfpsfps)(VltV1+500 fps amp RnOT Neg) Go To 13

P66 - ENTRY - BALLISTIC (D(DL)

12 06 22 DESIRED GMBL ANGLES RPYMoultor horlz +12middot of 317middot mark

P67 - ENTRY - FINAL PHASE (02G)

13 06 66 BETACRSRNG ERRDNRNG ERR(010 1um 1um)

KEY VERBRecord DNRNG ERR _KEY RLSEMoultor l~ft vector ou RSI amp FDAI

16 67 RTOGOLATLONG (Vrel=1000fps)(lumOldegOldeg)

SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOWNMonitor a1t~meter

Go To EARTHLANDING pg ---4L5 _

-29-

53 GampN HYBRID DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL tV1 V37E 30E

2 F 06 33 GETI(ACCEPT) PRO (hrm~n Olsec)(REJECT) LOAD DESIRED GETI

3 F 06 81 tVXYZ (LV) (lfps)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

4 F 06 42 HAHPtV (lnm lfps)Record tV

(ACCEPT) PRO(REJECT) Reselect P30 or P27 Load new paramo

5 F 16 45 MTFIMGA (marksm~n-secOlO)

MGA -00002 ~f k

k lMU not al~gned

SET DETPRO

6

7

8

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (Pull)PLSS 02 vlv - FILL02 8M SUPPLY vlv - OFFCAB PRESS REL vlv (2) - NORMcb ELS (2) - closecb SECS ARM (2) - closecb SECS LOGIC (2) - close (ver~fy)

AUTO RCS SEL CM (12) - MNA or ~ffiB

(hftoff conhg)ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM (AampB) - OFF

CMP to Couch

9

10

11

-30-

MNVR TO PAD BURN ATTLOAD DAPBMAG MODE (3) - RATE 2SC CONT - CMCAUTOATT DB - MINMAN ATT (3) - RATE CMD

v62E

v49E

12 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLES

PRO

13 F 50 18 REQ MNVR TO FDAI RPY ANGLES (01deg)(AUTO) PRO(MAN) SC CONT - SCS

BMAG MODE (3) - RATE 2MNVR To 15

14 06 18 AUTO MNVR TO FDAI RPY ANGLES (01deg)

15 F 50 18 REQ TRIM TO FDAI RPY ANGLES (01deg)(TRIM) Go to 13(ByPASS) ENTR

16

17

CHECK BORESIGHT amp SKT STARSOPT MODE - CMCOPT ZERO - OFF

v41 N91E

18 F 21 92 SHAFTTRUN (01deg 001deg)Load SXTS angles

19 41 OPTICS DRIVECheck SKT STAR

OPT ZERO - ZEROCheck BORESIGHT STAR (~f ava~l)

20 V25 N17E (01deg)Load Pad Data GMBL Angles

for CM BURN ATTATT SETtw - SET

to PAD DATA GMBL ANGLESfor CM BURN ATT

21

22

-31-

PHR REDUCTIONHGA PHR - OFFFC PUMPS (3) - OFFVerify s~ngle su~t compr oper loads

balancedFC 2 MN AampB - OFFS BD PiR AMP - LOWcb ECS RAD CONTHTR (2) - opencb HASTE H20URINE DUMP HTRS(2)- opencb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANMN BUS TIE (2) - ONTVC SERVO PHR 1 - AC1MNAGMBL MTR (4) - START

p41 - RCS THRUSTINGV37E 41E

23 F 50 18 REQ MNVR TO LCL HORIZ (HDS ON)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CMCAUTOPRO To 24

(gtfANDAP) BMAG MODE (3) - RATE 2SC CONT - CMCHOLD

V62EMNVR To 25

24 06 18 AUTO MNVR TO FDAI RPY

25 F 50 18 REQ TRIM TO LCL HORIZ (01deg)ALIGN SC ROLL

(AUTO TRIM) PRO To 24(BYPASS) ATT DB - MIN

RATE - LOHMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTlRATE 2

ENTR

550Om26 06 85

59middot2527

-32-

VGXYZ (1fps)RECHECK BORESIGHT STARTRANS CONIR PWR - on (up)EMS MODE - STBY (ver~fy)

EMS FliNC - bV SETVHF RNGSET (IV for SM BURN _EMS FliNC - bVS BD ANT - OMNI CSECS LOGIC (2) - ONMSFN conhrm Go for PYRO ARMSECS PYRO ARM (2) - ARMCM RCS LOGIC - ON (ver~fy)

DSKY BLANKS

593028 16 85 VG XYZ (AVE G ON) (lfps)

RHCs amp THC - ARMEDLIMIT CYCLE - OFFTAPE RCDR - CMD RESETHBREMS MODE - NORMAL

000029 F 16 85 REQ NULL VG XYZ (lfps)

BURN EMS bV CTR TO ZERORESET DET amp COUNT UP

If SM ONLY burn go to step 32THC - LOCKEDSC CaNT - SCSFREERATE - HIGHPRIM GLY To RAD - BYPASS (ver~fy)

MN BUS TIE (2) - ON (ver~fy)

CMSM SEP (2) - on (up)CSMLM FNL SEP (2) - on (up) (verify)CampW MODE - CMRCS TRNFR - CMCM RCS LOGIC - OFF

Momtor VM ABIf lt25 vdc go to EMERGPOWER DOWN Pg E6-l

V63E

If CMC NO GO FDAI SOURCE - ATT FDAI SEL - 1 or 2 ATT SET - GDC

SET

-33-

~Uili ATT PITCH - ACCEL CMDFDAI SCALE - 55MNVR TO CM BURN ATT (NULL ERR NEEDLES)

R 0degPY --00--

30

31

CM RCS BURNRHC III-ContJnuous PJtch DownRHC HZ-Module PJtch to null needlesBURN VGZ TO ZERO

If only 1 RHC Pulse + P=5deg from retro att MaJnta~n rates lt3degsec

BURN COMPLETION ATllV CTR= or DET= _

V8ZE

32 F 16 44 HAHPTFF (1nmffiJn-sec)Check HP-

If gt Pad data contJnue burnuntJ1 lt Pad

PRO

33 F 16 85 VGXYZ (Ups)Read VG resJduals to MSFN

(HYBRID) PRO to 34(SM ONLY BURN)

PROF 37 ODE

EI-1500 V37E 47EF 16 83 twx Y Z (Ups)

SC CONT - SCSFREEMAN ATT (PITCH) - RATE CMDRATE - HIGHPRIM GLY To RAD - BYPASS (verJfy)MN BUS TIE (2) - ON (verJfy)CMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verJfy)Campl MODE - CMRCS TRNFR - CMCM ReS LOGIC - OFFSECS PYRO ~I (2) - SAFE

-34-

PROMonitor VMAB

If lt25 vdc go to EMERGPOWER DOWN

34 F 37 OOEPCM BIT RATE - LOWATT DB - MAXEMS MODE - STBYEMS FUNC - OFF

Go To EARTH ORBIT ENTRY pg _--40-__

-36-

8 SPS THRUSTING PREPCYCLE CRYO FANSSPS GAGING - ACI (ver~fy)

PUG MODE - NORM (venfy)BMAG MODE (3) - RATE 2tv CG - CSMCMC MODE - FREEAUTO RCS SEL (16) - MNA or HNB

(hftoff conbg)SC CONT - CMCAUTO

9 MNVR TO PAD BURN ATTV62E

10 V49E

11 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLESPRO

12 F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) PRO(HAN) SC CONT - ses

MNVR to 14

06 18 AUTO MNVR TO FDAI RPY ANGLES13

14 F 50 18 REO TRIH TO FDAI RPY ANGLES(TRIM) Go to 12(BYPASS) ENTR

15 BORESIGHT STAR CHECK

16 V37E 40EOPT PWR - OFF

17 F 50 18 REQUEST MNVR TO FDAI RPY ANGLES (01deg)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CHCAUTOPRO to 18

(MANDAP) BMAG HODE (3) - RATE 2SC CONT - CMCHOLDMNVR to 19

(HANseS) se eONT - sesMNVR to 19

-35-

54 NORMAL DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL ~V

1 V37E 30E

2 F 06 33 GETI (hrm~nOlsec)

(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

3 F 06 81 ~VXYZ (LV)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

( lfps)

4 F 06 42 HAHP~V (1nmlfps)Record W

(ACCEPT) PRO -----(REJECT) Rese1ect P30 or P27 Load new pa~am

5 F 16 45 MTFIMGA (marksmln-secOldeg)MGA -00002 If ~ lMU not a1~gned

SET DETPRO

6

7

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY v1v - OFFCAB PRESS REL v1v (2) - NORMcb ELS (2) - close (verify)cb SECS ARM (2) - close (ver~fy)

cb SECS LOGIC (2) - close (verlfy)AUTO RCS SEL CM (12) - ~mA or MNB

(l~ftoff conf~g)

ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM AampB - off (ctr)

18

-37-

06 18 AUTO MNVR TO FDAI RPY ANGLES (01 0)

19 l 50 18 REOUEST TRIM MNVR TOALIGN SIC ROLLGDC ALIGN

FDAI RPY ANGLES(010

)

+54-00m(-06-00)

TIG-5mJn

5500m(-0500)

TVC CHECK amp PREPcb STAB CONT SYS (all) - closecb SPS (12) - closeATT DB - MINRATE - LOl~

LIMIT CYCLE - ONMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE 2ROT CONTR PWR DIRECT (2) - OFFSCS TVC (2) - RATE CMD

If SCS SCS TVC (2) - AUTO SC CONT - SCS ~

TVC GMBL DRIVE PampY - AUTOMN BUS TIE (2) - ONTVC SERVO PWR 1 - AC1MNA

2 - AC2MNBTRANS CONTR PWR - ONROT CONTR PWR NORMAL 2 - ACRHC 2 - ARMED

HORIZ CHK - HorJz on 12deg wJndmlmark (LJffiJt +3 0 PNGCS GONO GO)

If NO GO set tw 180 0 180deg0 0

Track horJz wJth 24deg wJndow markAt TIG-2 mJn Ahgn GDC

PRIMARY TVC CHECKGMBL MOT P1-Y1 -STARTON(LMP confJrm)

If SCS verJfy Thumbwheel TrJmTHC - CWVenfy NO MTVC

SEC TVC CHECKGHBL MOT P2-Y2 -STARTON(LMP confJrm)SET GPI TRIHVenfy MTVCTHC NEUTRALGPI returns to 00 (CMC) or trJm (SCS)ROT CONT Pl~ NORM 2 - ACDC

(TRIM) Go to step 17(BYPASS) BMAG MODE(3) - ATTIRATE2 (ver1fy)

ENTR

-38-

20 F SO 25 00204 GMBL TEST OPTION(ACCEPT) SC CONT - GMC (ver~fy)

PROMonitor GPI Response

0020-2000020-200Tr~m

TEST FAIL SC CONT - SCS SCS TVC (2) - AUTO

(REJECT) ENTR

21 06 40 TFIVG~VM (m~n-sec1fps)

PROG ALM - TIG s1~pped

V5N9E 01703

KEY RLSE To 21 ROT CONTR PWR DIRECT (2) - MNABSPS He v1vs (2) - AUTO (ver~fy)

LIMIT CYCLE - OFFFDAI SCALE - SOIScb SPS P2Y2 - open (for cr~t burn)

5800(-02 00)

5925(-0035)

59middot 30(-0030)

06 40

59XX(-OOXX)

AV THRUST A(B) - NORMALTHC - ARMEDRlIC (2) - ARMEDTAPE RCDR - GID RESETHBR

DSKY BLANKS

(AVE G ON)EMS MODE - NORMAL

TFIVG~VM (m~n-seclfps)

CHECK PIPA BIAS lt2fps for 5 sec

ULLAGE AS REQ

IF NO ULLAGE DIR ULLAGE PB - PUSH~

CONTROL ATT WRlIC MONITOR AVM (R3) COUNTING UP

5955(-0005)

F 99 40 ENG ON ENABLE REQUEST(AUTO IGN) PRO AT TFI gt0 sec(BYPASS IGN) ENTR to 24

22 0000 IGN

-39-

If SCS - THRUST ON PB - PUSH

06 40 TFCVG~VM (m~n-seclfpslfps)

~F 97 40 SPS Thrust fall ~

~(RESTART) PRO To IGN (RECYCLE) ENTR To TIG-05 sec

SPS THRUST LITE - ONMONITOR THRUSTING

Pc 95-105 pSlaEMS COUNTING DOWNSPS IN3 v1vs (4) - OPENSPS He v1vs tb (2) - graySPS FUELOXID PRESS - 175-195 pSlaPUGS - BALANCED

PROG ALARM V5N9E 01407 VG INCTHC - CW FLY MTVC

ECOEMER SPS CUTOFF J

AV THRUST (2) - OFF

23 F 16 40 TFC(STATIC)VG~VM (mln-seclfps)~V THRUST AB - OFF

SPS IN3 v1vs (4) - CLOSEDSPS He tb (2) - bp

cb SPS P2Y2 - closed (verlfy)TVC SERVO PHR - AC1MNA (venfy)TVC SERVO PWR 2 - OFF

PRO

24 F 16 85 VG XYZ(CM) CUps)NULL RESIDUALSRECORD ~V CTR amp RESIDUALS I1VCEMS FUNC - OFF VGXEMS MODE - STBY VGYBMAG MODE (3) - RATE 2ATT DB - MAX VGZTRANS CONT PHR - OFF

PRO

25 F 37 V82E

26 F 16 44 HAHPTFF (lnmm~n-sec)

R3-59B59 HP gt494 nmPRO

27 F 37 OOE

-40-

55 EARTH ORBIT ENTRY

1 Venfy CMSMR __

P_shyY_-

SEP ATT(180deg)

(0deg )

2

3

4

EMS INITIALIZATIONEMS FUNC - RNG SETSET RNG TO PAD DATA RNGEMS FUNC - VA SETSlew scroll to pad data VIOEMS FUNC - ENTRY

RSI ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on(up)GDC ALIGN PB - PUSH amp HOLDYAW tw - Pos1tion RSI thru 45deg amp

back to LIFl UPGDC ALIGN PB - RELEASEEMS ROLL - OFFAl1gn GDC to lMU

PWR REDUCT (Norm Deorb Only)HGA PWR - OFFFC PUMPS (3) - OFFVer1fy s1ngle suit compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - Lowcb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2)-openlOb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MAN

-41-

P61 - ENTRY PREP

5 V37E 61E05 09 01427 - ROLL REVERSED05 09 01426 - IMU UNSAT

6 F 06 61 IMPACT LAT LONG liDS UPDN (+-)(01 0

010

+00001)

PRO

PAD VALUESLATLON==G------liDS UP DN _

7 F 06 60 GMAXV400KGAMMA EIRecord

GMAXV400K----GAMMA EI _

PRO

8 F 06 63 RTOGO (1nm) PAD _VIa (fps) PADTFE (mln-sec) ----Compare wlth MSFN for PGNS GONO GONO COMM SET RTOGO amp VIO IN EMS amp

INITIALIZE(ACCEPT) PRO(RECALC) V32E to 8

-42-

P62 - CMSM SEP amp PRE-ENTRY MNVR

9 F 50 25 00041 REQUEST CMSM SEPSC CONT - SCSFREEYAW - 45deg out-of-plane (left for RCS

nght for SPS)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE2PRIM GLY to RAD - BYPASS (verlfy)SECS LOGIC (2) - on (up)MSFN conflrm GO for PYRO ARMSECS PYRO ARM - ARMMN BUS TIE (2) - ON (verlfy)CMSM SEF (2) - ONCSMLM FNl SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 pSlaCM RCS LOGIC - OFFSECS PYRO ARM - SAFEMonltor VMAB

If lt25vdc go to EMERG POWERDOWN Pg E6-1AUTO RCS SEL AlC ROLL (4) - OFFAUTO RCS SEL CM 2(6) - OFFAUTO RCS SEL CM 1(6) - MNA or MNBYAW back to 00

PITCH TO ENTRY ATTROLL 0deg (LIFT UP)PITCH - HORIZ on 317deg MARK (400K)YAW 00

ATT DB - MAXMAN ATT (PITCH) - ACCEL CMDEMS DATA - VerifyEMS FUNC - ENTRY (verlfy)EMS MODE - NORMALMAINTAIN HORIZ TRK

PRO (Act ENTRY DAP)

10 F 06 61 IMPACT LAT LONG HDSDN(010 010 -00001)

PRO

11 FOSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axlS beyond 45deg of Vel vector)

-43-

P63 - ENTRY INIT

12 06 64 GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PWR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRHORIZ CKP~tch error needle goes toward

zero approach~ng 05G t~me

MAN ATT (PITCH) - RATE CMDIf CMC ~s GO

BMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS FLY BETA If CMC NO GO ~

SC CONT - SCS~

FLY EMS RCS Deorh Roll HDS UPTRACK HORIZ w~th 29deg w~ndow mk

P64 - ENTRY POST 05G

13

05G t=elt+0___)

06 68

RTOGO AT 05G AGREES WITH EMS - venfyHORIZ CK05E Lt - on (EMS start)

No EMS start w~th~n 3 secsEMS MODE - BACKUP VHF RNG 05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds L~ft DN

NNVR L~ft DNEMS GONO GO

G-V Plot w~th~n llm~ts

Rng ctr dwn 60 + 7 durlng 10 sec per~od

Mon~tor G-meter forconvergence wlth pad data (Do)

(Vlt27K fps) Go To 17

-44-

P65 - ENTRY - UP CONT (Vgt27K fps)

14 F 16 69 BETA (01deg)DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT~

SC CONT - SCS FLY EMS

PRO

15 06 68 BElA VI HOOT (01deg fpsfps)(VltVL +500 fps amp RDOT Neg) Go To 17

p66 - ENTRY - BALLISTIC (DltDL)

16 06 22 DESIRED GMBL ANGLES RPY (01deg)Mon~tor hor~z +12deg of 317deg mark

P67 - ENTRY - FINAL PHASE (02G)

17 0666 BETACRSRNG ERRDNRNG ERR (Oldeglnmlnm)KEY VERBRecord DNRNG ERR _KEY RLSEL~m~t +100nm from PAD DRE

Mon~tor l~ft vector on RSI amp FDAIF 16 67 RTOGOLATLONG (Vre1=1000fps)

(lnm 010 01deg)SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOlfflMon~tor altimeter

Go To EARTHLANDING pg _I4L5__

-45-

56 EARTHLANDING

90K STEAM PRESS - PEGGED50K CABIN PRESS REL vIv (2) - BOOSTENTRY

SECS PYRO ARM (2) - ARM

40K(90K + 63s)

CM UNSTABLE RCS CMD - OFF ~ 40K APEX COVER JETT PG-PUSH DROGUE DEPLOY PG - PUSH (2 secafter apex cover Jett)

30K ELS LOGIC - ON (up)ELS - AUTO

24K RCS hsable (auto)(90K+92s) RCS CMD - OFF

Apex cover Jett (auto)APEX COVER JETT PB - PUSH

(WAIT 2 SECS)Drogue parachutes deployed (auto)

DROGUE DEPLOY PB - PUSH~

If Drogues FallELS - ~ ~Stablllze CM 5K MAIN DPLY PB - PUSHELS - AUTO

235K Cabln Pressure lncreaslng (Drogues + 50s)If not lncreaSlng by 17K CABIN PRESS REL vlv (RR) - DUMP

-46-

10K Maln parachutes deployedMAIN DEPLOY PB - PUSH (wlthln 1 sec)VHF ANT - RECYVHF AMA - SIMPLEXVHF BCN - ONCABIN PRESS REL v1v (2) - CLOSEDIRECT 02 vlv - OPENCM RCS LOGIC - on (up)CM PRPLNT - DUMP (burn audlb1e)Monltor CM ReS 1amp2 for He press decrease

NO BURN or PRESS DECREASE USE BOTH RHCs DO NOT FIRE PITCH JETS

CM PRPLNT-PURGE (to zero He press)CM RCS He DUMP PB - PUSH RHC (2) - 30 sees NO PITCH k

STRUT LOCKS (2) - UNLOCK

cb FLT amp PL BAT BUS ABampBAT C (3) - closecb FLT amp PLT MNA amp B (2) - opencb ECS RAD HTR OVLD (2) - opencb SPS PampY (4) - open

3K CABIN PRESS REL v1v (RH) - DUMP (after purgecompleted)

FLOOD Lts - POST LDGCM RCS PRPLNT (2) - OFFROT CONTR PWR DIRECT (2) - OFF

800 CAB PRESS RELF vlv - CLOSE (latch off)MN BUS TIE (2) - OFF

AFTER LANDINGcb MAIN REL PYRO (2) - closeMAIN RELEASE - on(up)

Go to POSTLANDING pg _47L-__

I

2

3

-47-

57 POSTLANDING

STABILIZATION VENTILATION COMMUNICATIONS

DIRECT 02 vlv - CLOSE

Stablllzation after landlngELS - AUTO (verlfy)cb MAIN REL PYRO (2) - close (venfy)MAIN RELEASE - on (up) (verlfy)S~CS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb BAT RLY BUS (2) - open

No contact w1th recovery forcesVHF AM AampB - off (ctr) ~

VHF AM Rev ONLY - A cb PL VENT - closecb FLOAT BAG (3) - closecb UPRIGHT SYS COMPRESS (2) - closeIf Stable II

FLOAT BAG(3)-FILL t1ll 2 m1n afterupr1ght then - OFF

VHF AM AlB amp BCN - OFF whlle lnvertedIf Stable I

After 10 M1n Coollng Per1odFLOAT BAG (3) - FILL 7 mln then OFF

Post Stab1lizat1on And Ventllat10nPL BCN LT - BCN LT LOWPL VENT vlv - UNLOCK (Pull)Remove PL VENT Exh CoverPL VENT - HIGH or LOWPL DYE MARKER - ON (swlmmer comm)Release foots traps and_restralntscb MNA BAT BUS A amp BAT C (2) - opencb MNB BAT BUS B amp BAT C (2) - opencb FLT amp PL BAT C - opencb PYRO A SEQ A - opencb PYRO B SEQ B - open

EACH HR - CHECK DC VOLTSgt 275 V If Notmiddot cb FLT amp PL-BAT BUS AampB (2) -open cb FLT amp PL BAT C (1) - open GO TO LOW POWER CHECKLIST

Unstow and lnstall PLV DISTRIB DUCTDeploy grappllng hook and 11ne 1f req

4

-48-

Post Landing Communlcatl0nsVHF ANT-RECY (venfy)VHF BCN - ON (verlfy)

If no contact ~lth recovery forcesperform VHF BEACON Check

MONITOR VHF BEACON transmlSSlonnth VHF AM B Rcvr andor Su)vlval

TransceiverkVHF Beacon not operatlng ~connect Surv~val TranscelVer to antcable behlnd VHF ant access pnland place radio ln BCN mode

LOW POHER CHECKLISTVHF BCN - OFFVHF AM (3) - RCVFLOOD Lts - OFFVHF AM AampB - off (ctr)VHF AM RCV ONLY - A (venfy)COUCH LIGHTS - OFFPOSTLANDING VENT SYS mlnlmlze useSURV RADIO - plug mto VHF BCN ANT cableconn behind VHF ant acess pnl amp turn radloon l-n BCN mode

EGRESS PROCEDURES

CMPCDRLMPCDR

CMPCDRCMP

LMPLl1PCDR

STABLE IDlsconnect Umblll-calsNeck darn onCenter couch - 270 0 positionArmrests stowedConnect raft to SIC l-f desl-red wlth

green lanyardConnect raft ~hl-te lanyards to SUltS amp

lnflate water wlngs when eXltl-ngHATCH PISTON PRESS vlv - PRESS (Outbd)Slde Hatch openedPL VENT - OFFcb Pnl 250 (all) - openEgress with 11feraftPut hardware klt outEgress

or CDIPALL

CMF

CDRCMF

CDR

LMF

CMFCMP LMFCMP

UlP

CDR

-49-

STABLE IIcb CREW STA AUDIO (3) - openD~sconnect umb~1~ca1s

Release foots trapsRelease restra~nt harnessCouch seat pans (3) - 170 0 pos1t10nArm rests stowedSurv1va1 k~ts removed from stowageConnect life raft ma~n1~ne to CDR or SicConnect f~rst wh~te lanyard from

11fe raft to suitConnect th~rd wh~te lanyard from

l~fe raft to SU1tConnect rucksacks together to yellow

lanyard on raft bagPRESSURE EQUALIZATION vlv - OPENRemove and stow fwd hatchEX1t feet f1rst w1th rucksacks when clear

of siC 1nflate water w1ngs and raftExit feet f1rst when clear of SiC

1nflate water w1ngsEX1t feet f1rst when clear of sic

1nflate water w1ngs

-50-

60 TLI ABORTS

TLI Aborts are conta~ned ~n the ESD s~nce the bulk of the funct~ons

concern entry preparat20ns and performance Th~s allows a s2nglesource of procedures for procedure rev2ew val~dat~on checkout andtra~n~ng These procedures ~ncorporate TLI preparat20ns as found ~n

reference 6 w~th the TLI Abort Procedures and these t~e 2nto normallunar return Entry Procedures found ~n sect20n 5 The guidel~nes

for th~s cont2ngency are spec2f2ed 2n reference 7

In2t2al preparat~ons for TLI pos2t20n the necessary system sW2tches2n add~t~on to perform~ng an EMS ~V test and a GDC al~gnment Afterthe DET ~s set for mon2tor2ng TB6 the CMP ~ncreases the 12ght levelof the LEB DSKY to max~mum and returns to the h2s couch Th2s 2Sdone so that the LEB DSKY can be observed ~n the event sunl~ght orreflect20ns wash out the ma2n d2splay panel DSKY dur2ng cr2t2calmaneuvers The crew then straps ~n and prepares for mon2tor~ng TB6as 2nd2cated by the SII SEP L~te The t2mes se~uence of procedures2S keyed on th~s d~splay and ~ncludes the DET START funct~on andSIVB IGNITION Dur2ng the burn the crew mon2tors the FDAIs foratt~tude excurs20ns and abnormal rates report~ng status checks toM~ss2on Control at d2screet t~mes dur2ng the maneuver Upon SIVBSHUTDOWN the eMP records the DSKY d~splayed performance parametersand awa2ts ground conf2rmat~on

The rat~onal for TLI aborts ~s descr~bed 2n reference 7 A summar2shyzat20n 2S extracted to prov2de background and gu2de12nes 2n th2sdocument The abort procedures cover aborts 10 m2nutes after conshyt2ngent SIVE shutdown and aborts 90 m2nutes after normal SIVE shutshydown t2me

The 10 m~nute TLI abort ~s des2gned to be used dur~ng TLI ~n theevent a spacecraft problem develops Wh2Ch can result 2n catastrophe2f ~mmed~ate act~on 2S not taken If the s~tuat20n perm~ts the crewshould always allow the SIVB to complete TLI at wh~ch t~me the groundand crew can perform a malfunct~on analys~s to determ~ne ~f an abort~s adv~sable If a fa~lure occurs that necess2tates the shutdown ofthe SIVB and the ~u~ck return of the crew to earth th~s abort ~s

des~gned to be as ~nsens~t~ve to execut~on errors as poss~ble andst21l be targeted to m2dcorr2dor The burn att~tude w~th the f~ed

hor~zon reference ~s a constant value for any shutdown t~me Theburn durat~on 2S a funct20n of shutdown t2me and 2S ava21able fromcrew charts S~nce the pr~mary purpose of th~s abort ~s to returnto earth as qU2ckly as poss2ble there are no restr2ct20ns as toland~ng locat~on However ~f the t~me to EI is greater than abouttwo hours a midcourse correct20n should be ant~c~pated

The 90 m2nute TLI abort 2S to be used 2f a cr2t2cal subsystem malshyfunct~on ~s determ2ned and the dec2s~on to abort ~s made after the

-51-

TLI cutoff and before TLI cutoff plus approxlmately 80 m1nutesTh1S allows suff1c1ent separatlon and procedural t1me to set upfor the SPS deorb1t burn performed at about TLI + 90 Note thatgenerally the deorb1t burns w1ll be performed a fe11 m1nutes beforeTLI + 90 accord1ng to crew charts shown In reference 8 The no-comm except10n requ1res that 90 m1nutes be the 1nput t1me of 19n1shytlon for P-37 (onboard return-to-earth abort program) so that onshyboard calculatlons can correspond w1th ground calculat10ns to computethe CM land1ng p01nt Th1S TLI abort lS des1gned so that returnfl1ght t1me does not exceed 18 hours and abort ~V does not exceed7000 fps ThlS abort can be performed uSlng chart ~Vs and attltudesand the earths hor1zon serves as a suff1c1ent reference The maneushyver lS targeted to ach1eve the mldcorr1dor entry target Ilne andtlmed to result 1n a deslgnated recovery area

It 1S ObV10US for abort deC1S1ons early 1n the TLI + 90 m1nute t1meshyframe that a GampN SPS burn should be performed In order to keep theTLI abort procedures cons1stent and w1th emphasls on slmpl1c1ty theprocedures here reflect a SCS SPS abort burn to cover the full abortdec1s1on t1meframe

A m1dcourse correct1on for corr1dor control after a TLI abort may bedeS1red 1f the SPS burn d1d not meet expectat1ons The TLIabortprocedures 1n th1S sect10n adapt to the normal lunar return tlmel1neand procedures pr10r to the f1nal MCC

-52-

61 TLI PREPARATION PROCEDURES

GET = 150

CRO AOS(___)

CRO LOS( )(22142)

5100

Don Helmets amp Gloves

XLUNAR - INJECT (verify)EDS PWR - on (venfy)EMS FUNC - OFF (verlfy)EMS MODE - STBYEMS FUNC - IW SETVHF RNGEMS MODE - NORMALSet ~V indo to +15868 fpsEMS FUMC - ~V Test

SPS THRUST Lt - onoff (10 sec)~V lnd stops at -01 to -415

EMS MODE - STBYEMS FUMC - ~V SETVHF RNGSet ~VC

EMS FUNC---~~V=----

GDC ALIGNFDAI Select - liZcb SECS LOGIC (Z) - close (verify)cb SECS ARM (Z) - closeSECS LOGIC (Z) - on (up)MSFN Conflrm GO for PYRO ARM (If pass)SECS PYRO ARM (Z) - on (up)TRANS CONTROL PWR - ONROT CONTR PWR NORMAL (Z) - ACDC(verlfy)ROT CONTR PWR DIRECT (Z) - MNAMNBLV INnGPI - SIISIVB (venfy)LV GUID - IU (venfy)cb DIRECT ULLAGE (Z) - closedSet EVENT TIMER to 5100Begin MONITOR For TB6

CMP to Couch

TB 6 - SII SEP Lt on (TIG-9 mln 38 sec)KEY V83E

SET ORDEALFDAI Z ORB RATE at 180 0 0SII SEP Lt out (38 sec later)Start DET COUNTING UPSC CaNT - SCS (verify)MONITOR LV TANK PRESS

~P lt 36 psid (OXID gt FUEL)~P lt Z6 psid (FUEL gt OXID)

EMERGENCY CSMLV SEP UP TLM CM - BLOCK (verify)UP TLM IU - BLOCK (venfy)

-53-

+45degPY))0middot sec PY

lOK nmltHAlt25K nm

Two phas~ng mnvrs two SPS mnvrs to circular~ze at 150 nmearth orb~t

CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ssion 4K nmltHAltlOK nm CSM amp1M - Two phasing mnvrs two SPS mnvrs to circularize at 150 nm earth orb~t CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ss~on

CSM amp 1M - Two phas~ng mnvrs APS burn todepletion th~rd phasing mnvrSPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn tosem~sync orb~t

25K nmltHAlt40K nm CSM amp 1M - Two phasmg mnvrs APS burn to depletion third phas~ng mnvr SPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn to sem~sync orbit HA)40K nm DPS ava~l - DPS LOll circularize with SPS

DPS not ava~l - Lunar flyby or CSM only to lunar orbit (if reqd gtV lt4000 fps)

V37E 47E (check b~as) Record -=--rshy(Limit 98 fpsmm)

( 1fps)tVXYZN62EVIHDOTHPAD (fpsfpslnm)MONITOR VI ( ) at ECO

SCS TVC SERVO PWR 1 - ACIMNA2 - OFF

TAPE RCDR - CMD RESETHBREMS MODE - NORMAL

SIr SEP Lt - ONTLI Inhib~t S~gnals w~11 not be honored after 5942

SIVB ULLAGE BeginsSII SEP Lt - off (TIG - 18 sec)SIVB FUEL LEADSIVB ULLAGE d~scont~nues

LV ENG I Lt - onSIVB IGNITION ( GETI)LV ENG I Lt - off - -shyMONITOR THRUST amp ATTITUDEMONITOR LV TANK PRESSSIVE ECO (Lt on) (BEGIN TB7)

EMER SIVE CUTOFF AT 6 SEC PAST BURN TIME IF VI ATTAINEDTHC CCW ampNEUTRAL IN 1 SEC or SIISIVB sW - LV STAGEPremature Shutdown HAlt4K nm CSM amp 1M -

5700

58205836

F 16 835800

F 16 62

5838594259525955595900000002SUNRISE(___)

HAW AOS(__=_) KEY VERB (freeze d~splay)

SIVB ATT HOLD 20 sec amp BEGIN VENTINGSIVB NNVR TO ORB RT (HDS DN) (3middot sec)

Record VI -c---HDOT _

HPAD _

KEY RLSEF 16 62

F 16 83

HAW LOS(__=-)

KEYmiddotRLSE~VXYZ (lfps)

Record ~VX---_

~vy

WZ--

AVC---_

TAPE RCDR - off (ctr)EMS MODE - STBYEMS FUNC - OFFSECS PYRO ARM (2) - SAFE

PRO

BURN STATUS REPORT

____--~TIG

BT------VGX____-R

-----P----_Y

REMARKS

_____VI

______--HDOT______--H______---AVC______---FUEL_______OXID

_______UNBAL

F 3708=00 OOEGOS AOS CMP TO LEB

(-=-=-)

0000

0003

0005

0014

0100

-55-

62 TLI 10 MIN ABORTSECS LOGIC (2) - on (up)SECS PYRO ARM (2) - ARM

TRANS CONTR - CGH (4 sec) amp +XDET RESET (verlfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS GMD-ON

TRANS GONTR - neutral then +X for10 sec

SIVBGPI s~ - GPIExcesslve rates 6V THRUST A - NORMAL SPS THRUST - DIRECT When rates damped 6V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

TRANS CONTR +X - OFFV37E OOE

PITGH UP to LOGAL VERT (+X axlSto~ard the earth)

RATE - LOWBMAG MODE (3) - ATTIRATE 2EDS PHR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SEGS ARM (2) - opencb EDS (3) - open

TRANS CONTR -X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (180deg)P (199deg)Y (0deg)

RETRO UPDATEGETI _

JV _VG

Jtb ---GET 400K _

05G _GET DROGUE _

ENTRY P _R _

Y_--

0945

-56-

ALIGN HORIZ ON RET +1 MKGMBL CHECK (T11lle Pentattlng)MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conflnn)cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FUMC - JV SETVHF RNGSET JV from chartE~S FUMC - JVEMS fODE - NOIDlAL

lV THRUST A - NORMALV37E 47E (THRUST fONITOR)

F 16 83 lVXYZ (1 fps)

0950

1000

NOTE For aborts durlng 1st mln of TLIKEY V82E F 16 44 (HaHpTff)Burn untll Hp lt 19NM

TRANS CONTR +X

THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN JV reqdJV THRUST (2) - OFFReport cutoff

cb SPS P2 Y2- closeGfBL MTRS (4) - OFF (LMP Confinn)TRANS CONT PWR - OFFTVC SERVO PWR (2) - OFFMN BUS TIE (2) - OFFcb SPS P1amp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREIf est time to EIltOl5500 omlt fCC andenter the SUPERCIRC CKLIST as early as pos-slb1e Pg ~2~3~ __If est time to EI)Ol5500 anticlpate afCC Enter the ENTRY PREP CKLIST at step 9pg 18

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

-2tl C

l I W gt- ~-4

z laquo I I- 0 -6

l- I J u gt- ~-8

z w w -10

~_ONSANT

9O

VER

SHO

OT

BOU

ND

ARY

LIF

TV

EC

TOR

OR

IEN

TATI

ON

LIN

E

SH

ALL

OW

TAR

GE

TLI

NE

STE

EP

TAR

GE

TLI

NE 12

gU

ND

ERSH

OO

TBO

UN

DAR

Y

RE

EN

TRY

CO

RR

IDO

R

I ~ I

-12 24

26

28

30

32

34

RE

EN

TRY

VE

LOC

ITY

VE

1-F

TS

EC

Ch

art

1

36

3B

6-i

~

5CM

CC

ON

ST

NT

DR

VI z gt

~

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gtamp

J+

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bull-1

+-

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~r

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2829

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33

43

5IN

ER

TIA

LR

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NTR

YV

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00

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VE

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EC

Ch

art

2

J63

73

8X

03

-i- rtREQUIRED PITCH GIMBAL ANG LETO OBTAIN HOR-IZON AT 317

DEGREES IN wiiiiDOW

260

z~I- ~ i5 24000

1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

-I

-1-

NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

I LU HD~-

LUHD

lt0 120UJ0

~

80 HOLD PRESENT TRIMgt LU HD013

~Y~HOIgtlt

TOP OF WINDOWa 40to

31 7 SCRIBEaaI

80 TTOM OF WINDOWi= 0

0--ltoa

-40t-z

~~~Uw w u lt0 -80

HOLO PRESENT TRIlJCl

LOHU0 lt0

J gt -120 HOLD 059 TRIMlt0 z

LDHUlt0 FIELD OF VI S10 NLDHU LIFT-DOWNHEADS -UPLUHD LIFT-UP HEADS-DOWN

~~H~-160 q - P63 LIMITI- NOrE-VALIO ONLY FO~t~--

LUNAR RETURN VELOCITY

plusmnl8020 244middot 8 12 16

TIME TO 400K FT ALTITUDE-MIN

4

P37

LONG

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TOOB

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1350

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340

344

348

352

356

364

368

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NO

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AA

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-60

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0 90

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120

200

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240

320

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TCH

=199

YAW

0

TLI

-10

MIN

ABO

RTLA

UNCH

DEC

21

1968

400050

z =gt co23

0on 3

~7 X ampJ V

gt ~ 6

2627

~B

~n

_n

INER

TIAL

VELO

CITY

ATAB

ORT

IS-IV

BC

UTO

FF)middot

FTIS

EC34

3536

Xllf

Ch

art

7

7

1000

0i

0-00

EMS

V-F

TSE

C90

0080

0070

0060

0050

0040

0030

0020

0010

000

II

II

II

II

S-IV

BBU

RNTI

ME

-M

INSE

Cll-

41)

120

200

241)

320

400

441)

520

TlI

-I0

MIN

ABOR

TlA

UNCH

-DE

C21

19

68

lAUN

CHA

ZIM

UTH

lllJ

72I ~ I

Z526

27~

~bull

DX

~IN

ERTI

ALVE

LOCI

TYAT

ABOR

T(5

-IVB

CU

TaF

l-

FTlS

EC

Ch

art

8

34l6

Xla

3

-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 24: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

28

29

30 -OllOh

-21-

~V TEST (Deorb~t only)EMS FUNC - ~V SETVHF RNGSET ~V ~nd to 15868 fpsEMS MODE - NORMALEMS FUNC - ~V TEST

SPS THRUST LT - onoff (10 sec)~V ~nd stops at -01 to -415

EMS MODE - STBY

PRIMARY WATER EVAP ACTIVATIONGLY EVAP H20 FLOW - AUTOGLY EVAP STH PRESS - AUTOPRI ECS GLY PUMP - ACI

CM RCS PREHEATNote If sys test mtr 5cd6abcd

all read 39 vdc (28degF) or moreom~t preheat

cb RCS LOGIC (2) - closeCM RCS LOGIC - ONUP T1M CM - BLOCK (ver~fy)

cb CM RCS HTRS (2) - closeCM RCS HTRS - ON (LMP Conf~rm)

(20 mlU or III lowest rdg lS39 vdc) (Moultor Maufpress for press drop)

31 (___) FINAL GDC DRIFT CK (If req I d)If drlft gtlOohr Suspect GDC Do not

use RSI amp FDAI 2

32 -OO5Om

33

34

35

TERM CM RCS PREHEATUP TLM CM - BLOCK (venfy)CM RCS HTRS - OFFCM RCS LOGIC - OFF

SYSTEMS TEST PANEL CONFIGURATIONSYS TEST METER - 4BRNDZ XPNDR - OPERATECM RCS HTRS - OFFWASTE H20 DUMP - OFFURINE DUMP - OFF

LEB LIGHTING - OFF

SEC WATER EVAP ACTIVATIONGLY To RAD SEC vlv - BYPASSSEC COOL EVAP - EVAPSEC COOL PUMP - AC2

36

37

38 -OO45m

-22-

PYRO BATT CKcb PYRO A SEQ A - close (ver~fy)

cb PRYO B SEQ B - close (verify)DC IND - PYRO BAT A(B)

~If PYRO BAT A(B) lt 35 vdc cb PYRO A(B) seq A(B) - open~

PYRO A(B)BAT BUS A(B)TO PYRO~MN BUS TIE - close

cb MNA BAT C - closecb MNB BAT C - closeDC IND - MNBPNL 8 - All cbs closed except

PL VENT - open (ver~fy)

FLOAT BAG (3) - open (ver~fy)

DOCKING PROBE (2) - open (verlfy)EDS BAT (3) - open (ver~fy)

CM ReS HTRS (2) - open

CM RCS ACTIVATIONcb SECS ARM (2) - close (verlfy)cb SECS LOGIC (2) - close (verlfy)SECS LOGIC (2) - ONMSFN conflrm GO for PYRO ARM(~f poss)SECS PYRO ARM (2) - ARMCM RCS PRPLNT 1amp2 - ONCM RCS PRESS - ONRCS Ind sw - eMl then 2

He PRESS 3700-4400 pSlaMANF PRESS 287-302 pSla

SECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFF

P27 amp ENTRY PAD UPDATEGo To Entry Checkllst

Superclrc - pg ~2~3 _Hybnd - pg -----2~9L-__Normal Deorblt - pg __3L5L- _

-23-

52 SUPERCIRCULAR ENTRY

1 SET DET (up to ET)

2

3

4

5

3000(-30-00)

EMS INITIALIZATIONSET RNG TO PAD DATA RNGEMS FUNC - Vo SETSlew Scroll to Pad Data VIOEMS FUNC - ENTRY

RS I ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on (up)GDC ALIGN PB - PUSH amp HOLDYAW Tw - Pos~t~on RSI thru

45deg amp back to LIFT UPGDC ALIGN PB - ReleaseEMS ROLL - OFFA1~gn CDC to lMU

CM RCS RING A CKRCS TRNFR - CMcb CM RCS LOGIC MNB - openAUTO RCS SEL MNB (6) - OFFSC CONT - SCSTest R~ng A ThrustersSC CONT - CMCRCS TRNFR - SMAUTO RCS SEL (12) - MNAMNB

(hftoff conflg)cb CM RCS LOGIC MNB - close

OPTICS PWR - OFFCMP to COUCH

MN BUS TIE (2) - ONTAPE RCDR - REWIND

6 35middot0Om(-25middot 00)

-24-

SEPARATION CK LISTTVC SERVO PWR 1 - AClMNAcb ELS (2) - close (ver1fy)PRIM GLY TO RAn - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY vlv - OFFCAB PRESS REL vlv (2) - NORMGMBL MTRS (4) - STARTABORT SYS PRPLNT - RCS CMD (venfy)SM RCS PRIM PRPLNT (4) - ONVHF 11M (AampB) - OFFHI GAIN ANT PWR - OFFFC PUMPS (3) - OFFVer1fy s1ugle SU1t compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - 10101cb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2) - opencb HTRS OVLD (2) - openPOT H20 RTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANSEC COOL EVAP - RESETSEC COOL PUMP - off (etr)

MtiVR TO CMSM SEP P R ATTSC CONT - SCSCMC MODE - FREEMNVR TO PAD ATTR (0deg)PY----W)

-25-

SUPERCIRCULAR ENTRY (Cont~nued)

1

4100m(-1900)

P61 - ENTRY PREP

V37E 61E

k 05 09 01427 - ROLL REVERSED 05 09 01426 - IMU UNSAT ~

2 F 06 61 IMPACT LAT LONG HDS UPDN (+-)PRO (010

fps +00001)

3 F 06 60 GMAXVPREDGAMMA EIRecord

GMAXV400K----

GAMMA EI _PRO

(01deg fpsOldeg)

4 F 06 63 RTOGO (lnm) PAD _VIO (fps) PAD _TFE(m~n-sec)

Compare w~th ~M~SFN==C~f~o-r~P~GNS GONO GOIf NO COMM Set RTOGO amp VIO In EMS

amp lnltla11ze(ACCEPT) PRO(RECALC) V32E To 4

5 F 50 25

4300m

(-1700)

45 oOm(-1500)

500Om(-1000)

6 F 06 61

-26-

P62 - CMSM SEP amp PRE-ENTRY MNVRCAUTION Call No EXT Verbs In P62

00041 REQUEST CMSM SEPSC CONT - SCSFREE

COMPARE PITCH ATT WITH PAD DATA ---0=-

(W~thLU 5deg)YAW - 45deg OUT-OF-PLANE (LEFT)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTIRATE 2MN BUS TIE (2) - ON (ver~fy)

PRIM GLY TO RAD - BYPASS (verlfy)CM RCS LOGIC - ON (venfy)SECS LOGIC (2) - on (up)SECS PYRO ARM - ARMCMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 ps~a

CM RCS LOGIC - OFFSECS PYRO ARM (2) - SAFEMonltor VMAB

If lt25 vdc go to EMERGPOWERDOWN pg E6-l

AUTO RCS SEL AC ROLL (4) - OFFAUTO RCS SEL CM 2(6)-OFFAUTO RCS SEL CM 1(6)-MNAYAW back to 0degPITCH TO HORIZ TRACK ATT

ROLL - 0deg (LIFT UP)PITCH - 400K Horiz Mark (317deg)YAW - 0deg

ATT DB - MAXMAN ATT PITCH - ACCEL CMDEMS DATA - Ver~fy

EMS FliNC - ENTRY (ver~fy)

EMS MODE - NORMALcb SPS PampY (4) - openMAINT HORIZ TRK

PRO (Act ENTRY DAP)

IMPACT LATLONGHDSDN (01deg01deg-00001)PRO

7 POSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axis beyond 45deg of Vel vector)

8 06 64

58middot00m(-0200)

9

05G tlme(+0 )

(--=---)

06 68

-27-

P63 - ENTRY INIT

GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PIJR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRmDHORIZ CKPltch error needle goes toward

zero approachlng OSG tlmeMAN ATT (PITCH) - RATE CMD

If CMC lS GOBMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS I

FLY BETA If CMC NO GO ilt

1 SC CaNT - SCS I

FLY EMS k

p64 - ENTRY POST 05G

RTOGO AT 05G AGREES HITH EMS-venfyHORIZ CK05G Lt - ON (EMS START)

No EMS START wlthln 3 sec ~ EMS MODE - BACKUP VHF RNG c

05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds Llft DN

NNVR Llft DNEMS GONO GO

G-V Plot wlthln IlmltsRng ctr dwn 60plusmn7 durlng 10 sec

perlodMonltor G-meter for

convergence wlth pad data (Do)(Vlt27K fps) Go to 13

-28-

P65 - ENTRY - UP CONT (Vgt27K fps)

10 F 16 69 BETA (01middot) _DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT lt~ SC CONT - SCS FLY EMS

PRO

11 06 68 BETAVIHDOT (OIdegfpsfps)(VltV1+500 fps amp RnOT Neg) Go To 13

P66 - ENTRY - BALLISTIC (D(DL)

12 06 22 DESIRED GMBL ANGLES RPYMoultor horlz +12middot of 317middot mark

P67 - ENTRY - FINAL PHASE (02G)

13 06 66 BETACRSRNG ERRDNRNG ERR(010 1um 1um)

KEY VERBRecord DNRNG ERR _KEY RLSEMoultor l~ft vector ou RSI amp FDAI

16 67 RTOGOLATLONG (Vrel=1000fps)(lumOldegOldeg)

SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOWNMonitor a1t~meter

Go To EARTHLANDING pg ---4L5 _

-29-

53 GampN HYBRID DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL tV1 V37E 30E

2 F 06 33 GETI(ACCEPT) PRO (hrm~n Olsec)(REJECT) LOAD DESIRED GETI

3 F 06 81 tVXYZ (LV) (lfps)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

4 F 06 42 HAHPtV (lnm lfps)Record tV

(ACCEPT) PRO(REJECT) Reselect P30 or P27 Load new paramo

5 F 16 45 MTFIMGA (marksm~n-secOlO)

MGA -00002 ~f k

k lMU not al~gned

SET DETPRO

6

7

8

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (Pull)PLSS 02 vlv - FILL02 8M SUPPLY vlv - OFFCAB PRESS REL vlv (2) - NORMcb ELS (2) - closecb SECS ARM (2) - closecb SECS LOGIC (2) - close (ver~fy)

AUTO RCS SEL CM (12) - MNA or ~ffiB

(hftoff conhg)ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM (AampB) - OFF

CMP to Couch

9

10

11

-30-

MNVR TO PAD BURN ATTLOAD DAPBMAG MODE (3) - RATE 2SC CONT - CMCAUTOATT DB - MINMAN ATT (3) - RATE CMD

v62E

v49E

12 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLES

PRO

13 F 50 18 REQ MNVR TO FDAI RPY ANGLES (01deg)(AUTO) PRO(MAN) SC CONT - SCS

BMAG MODE (3) - RATE 2MNVR To 15

14 06 18 AUTO MNVR TO FDAI RPY ANGLES (01deg)

15 F 50 18 REQ TRIM TO FDAI RPY ANGLES (01deg)(TRIM) Go to 13(ByPASS) ENTR

16

17

CHECK BORESIGHT amp SKT STARSOPT MODE - CMCOPT ZERO - OFF

v41 N91E

18 F 21 92 SHAFTTRUN (01deg 001deg)Load SXTS angles

19 41 OPTICS DRIVECheck SKT STAR

OPT ZERO - ZEROCheck BORESIGHT STAR (~f ava~l)

20 V25 N17E (01deg)Load Pad Data GMBL Angles

for CM BURN ATTATT SETtw - SET

to PAD DATA GMBL ANGLESfor CM BURN ATT

21

22

-31-

PHR REDUCTIONHGA PHR - OFFFC PUMPS (3) - OFFVerify s~ngle su~t compr oper loads

balancedFC 2 MN AampB - OFFS BD PiR AMP - LOWcb ECS RAD CONTHTR (2) - opencb HASTE H20URINE DUMP HTRS(2)- opencb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANMN BUS TIE (2) - ONTVC SERVO PHR 1 - AC1MNAGMBL MTR (4) - START

p41 - RCS THRUSTINGV37E 41E

23 F 50 18 REQ MNVR TO LCL HORIZ (HDS ON)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CMCAUTOPRO To 24

(gtfANDAP) BMAG MODE (3) - RATE 2SC CONT - CMCHOLD

V62EMNVR To 25

24 06 18 AUTO MNVR TO FDAI RPY

25 F 50 18 REQ TRIM TO LCL HORIZ (01deg)ALIGN SC ROLL

(AUTO TRIM) PRO To 24(BYPASS) ATT DB - MIN

RATE - LOHMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTlRATE 2

ENTR

550Om26 06 85

59middot2527

-32-

VGXYZ (1fps)RECHECK BORESIGHT STARTRANS CONIR PWR - on (up)EMS MODE - STBY (ver~fy)

EMS FliNC - bV SETVHF RNGSET (IV for SM BURN _EMS FliNC - bVS BD ANT - OMNI CSECS LOGIC (2) - ONMSFN conhrm Go for PYRO ARMSECS PYRO ARM (2) - ARMCM RCS LOGIC - ON (ver~fy)

DSKY BLANKS

593028 16 85 VG XYZ (AVE G ON) (lfps)

RHCs amp THC - ARMEDLIMIT CYCLE - OFFTAPE RCDR - CMD RESETHBREMS MODE - NORMAL

000029 F 16 85 REQ NULL VG XYZ (lfps)

BURN EMS bV CTR TO ZERORESET DET amp COUNT UP

If SM ONLY burn go to step 32THC - LOCKEDSC CaNT - SCSFREERATE - HIGHPRIM GLY To RAD - BYPASS (ver~fy)

MN BUS TIE (2) - ON (ver~fy)

CMSM SEP (2) - on (up)CSMLM FNL SEP (2) - on (up) (verify)CampW MODE - CMRCS TRNFR - CMCM RCS LOGIC - OFF

Momtor VM ABIf lt25 vdc go to EMERGPOWER DOWN Pg E6-l

V63E

If CMC NO GO FDAI SOURCE - ATT FDAI SEL - 1 or 2 ATT SET - GDC

SET

-33-

~Uili ATT PITCH - ACCEL CMDFDAI SCALE - 55MNVR TO CM BURN ATT (NULL ERR NEEDLES)

R 0degPY --00--

30

31

CM RCS BURNRHC III-ContJnuous PJtch DownRHC HZ-Module PJtch to null needlesBURN VGZ TO ZERO

If only 1 RHC Pulse + P=5deg from retro att MaJnta~n rates lt3degsec

BURN COMPLETION ATllV CTR= or DET= _

V8ZE

32 F 16 44 HAHPTFF (1nmffiJn-sec)Check HP-

If gt Pad data contJnue burnuntJ1 lt Pad

PRO

33 F 16 85 VGXYZ (Ups)Read VG resJduals to MSFN

(HYBRID) PRO to 34(SM ONLY BURN)

PROF 37 ODE

EI-1500 V37E 47EF 16 83 twx Y Z (Ups)

SC CONT - SCSFREEMAN ATT (PITCH) - RATE CMDRATE - HIGHPRIM GLY To RAD - BYPASS (verJfy)MN BUS TIE (2) - ON (verJfy)CMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verJfy)Campl MODE - CMRCS TRNFR - CMCM ReS LOGIC - OFFSECS PYRO ~I (2) - SAFE

-34-

PROMonitor VMAB

If lt25 vdc go to EMERGPOWER DOWN

34 F 37 OOEPCM BIT RATE - LOWATT DB - MAXEMS MODE - STBYEMS FUNC - OFF

Go To EARTH ORBIT ENTRY pg _--40-__

-36-

8 SPS THRUSTING PREPCYCLE CRYO FANSSPS GAGING - ACI (ver~fy)

PUG MODE - NORM (venfy)BMAG MODE (3) - RATE 2tv CG - CSMCMC MODE - FREEAUTO RCS SEL (16) - MNA or HNB

(hftoff conbg)SC CONT - CMCAUTO

9 MNVR TO PAD BURN ATTV62E

10 V49E

11 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLESPRO

12 F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) PRO(HAN) SC CONT - ses

MNVR to 14

06 18 AUTO MNVR TO FDAI RPY ANGLES13

14 F 50 18 REO TRIH TO FDAI RPY ANGLES(TRIM) Go to 12(BYPASS) ENTR

15 BORESIGHT STAR CHECK

16 V37E 40EOPT PWR - OFF

17 F 50 18 REQUEST MNVR TO FDAI RPY ANGLES (01deg)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CHCAUTOPRO to 18

(MANDAP) BMAG HODE (3) - RATE 2SC CONT - CMCHOLDMNVR to 19

(HANseS) se eONT - sesMNVR to 19

-35-

54 NORMAL DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL ~V

1 V37E 30E

2 F 06 33 GETI (hrm~nOlsec)

(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

3 F 06 81 ~VXYZ (LV)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

( lfps)

4 F 06 42 HAHP~V (1nmlfps)Record W

(ACCEPT) PRO -----(REJECT) Rese1ect P30 or P27 Load new pa~am

5 F 16 45 MTFIMGA (marksmln-secOldeg)MGA -00002 If ~ lMU not a1~gned

SET DETPRO

6

7

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY v1v - OFFCAB PRESS REL v1v (2) - NORMcb ELS (2) - close (verify)cb SECS ARM (2) - close (ver~fy)

cb SECS LOGIC (2) - close (verlfy)AUTO RCS SEL CM (12) - ~mA or MNB

(l~ftoff conf~g)

ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM AampB - off (ctr)

18

-37-

06 18 AUTO MNVR TO FDAI RPY ANGLES (01 0)

19 l 50 18 REOUEST TRIM MNVR TOALIGN SIC ROLLGDC ALIGN

FDAI RPY ANGLES(010

)

+54-00m(-06-00)

TIG-5mJn

5500m(-0500)

TVC CHECK amp PREPcb STAB CONT SYS (all) - closecb SPS (12) - closeATT DB - MINRATE - LOl~

LIMIT CYCLE - ONMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE 2ROT CONTR PWR DIRECT (2) - OFFSCS TVC (2) - RATE CMD

If SCS SCS TVC (2) - AUTO SC CONT - SCS ~

TVC GMBL DRIVE PampY - AUTOMN BUS TIE (2) - ONTVC SERVO PWR 1 - AC1MNA

2 - AC2MNBTRANS CONTR PWR - ONROT CONTR PWR NORMAL 2 - ACRHC 2 - ARMED

HORIZ CHK - HorJz on 12deg wJndmlmark (LJffiJt +3 0 PNGCS GONO GO)

If NO GO set tw 180 0 180deg0 0

Track horJz wJth 24deg wJndow markAt TIG-2 mJn Ahgn GDC

PRIMARY TVC CHECKGMBL MOT P1-Y1 -STARTON(LMP confJrm)

If SCS verJfy Thumbwheel TrJmTHC - CWVenfy NO MTVC

SEC TVC CHECKGHBL MOT P2-Y2 -STARTON(LMP confJrm)SET GPI TRIHVenfy MTVCTHC NEUTRALGPI returns to 00 (CMC) or trJm (SCS)ROT CONT Pl~ NORM 2 - ACDC

(TRIM) Go to step 17(BYPASS) BMAG MODE(3) - ATTIRATE2 (ver1fy)

ENTR

-38-

20 F SO 25 00204 GMBL TEST OPTION(ACCEPT) SC CONT - GMC (ver~fy)

PROMonitor GPI Response

0020-2000020-200Tr~m

TEST FAIL SC CONT - SCS SCS TVC (2) - AUTO

(REJECT) ENTR

21 06 40 TFIVG~VM (m~n-sec1fps)

PROG ALM - TIG s1~pped

V5N9E 01703

KEY RLSE To 21 ROT CONTR PWR DIRECT (2) - MNABSPS He v1vs (2) - AUTO (ver~fy)

LIMIT CYCLE - OFFFDAI SCALE - SOIScb SPS P2Y2 - open (for cr~t burn)

5800(-02 00)

5925(-0035)

59middot 30(-0030)

06 40

59XX(-OOXX)

AV THRUST A(B) - NORMALTHC - ARMEDRlIC (2) - ARMEDTAPE RCDR - GID RESETHBR

DSKY BLANKS

(AVE G ON)EMS MODE - NORMAL

TFIVG~VM (m~n-seclfps)

CHECK PIPA BIAS lt2fps for 5 sec

ULLAGE AS REQ

IF NO ULLAGE DIR ULLAGE PB - PUSH~

CONTROL ATT WRlIC MONITOR AVM (R3) COUNTING UP

5955(-0005)

F 99 40 ENG ON ENABLE REQUEST(AUTO IGN) PRO AT TFI gt0 sec(BYPASS IGN) ENTR to 24

22 0000 IGN

-39-

If SCS - THRUST ON PB - PUSH

06 40 TFCVG~VM (m~n-seclfpslfps)

~F 97 40 SPS Thrust fall ~

~(RESTART) PRO To IGN (RECYCLE) ENTR To TIG-05 sec

SPS THRUST LITE - ONMONITOR THRUSTING

Pc 95-105 pSlaEMS COUNTING DOWNSPS IN3 v1vs (4) - OPENSPS He v1vs tb (2) - graySPS FUELOXID PRESS - 175-195 pSlaPUGS - BALANCED

PROG ALARM V5N9E 01407 VG INCTHC - CW FLY MTVC

ECOEMER SPS CUTOFF J

AV THRUST (2) - OFF

23 F 16 40 TFC(STATIC)VG~VM (mln-seclfps)~V THRUST AB - OFF

SPS IN3 v1vs (4) - CLOSEDSPS He tb (2) - bp

cb SPS P2Y2 - closed (verlfy)TVC SERVO PHR - AC1MNA (venfy)TVC SERVO PWR 2 - OFF

PRO

24 F 16 85 VG XYZ(CM) CUps)NULL RESIDUALSRECORD ~V CTR amp RESIDUALS I1VCEMS FUNC - OFF VGXEMS MODE - STBY VGYBMAG MODE (3) - RATE 2ATT DB - MAX VGZTRANS CONT PHR - OFF

PRO

25 F 37 V82E

26 F 16 44 HAHPTFF (lnmm~n-sec)

R3-59B59 HP gt494 nmPRO

27 F 37 OOE

-40-

55 EARTH ORBIT ENTRY

1 Venfy CMSMR __

P_shyY_-

SEP ATT(180deg)

(0deg )

2

3

4

EMS INITIALIZATIONEMS FUNC - RNG SETSET RNG TO PAD DATA RNGEMS FUNC - VA SETSlew scroll to pad data VIOEMS FUNC - ENTRY

RSI ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on(up)GDC ALIGN PB - PUSH amp HOLDYAW tw - Pos1tion RSI thru 45deg amp

back to LIFl UPGDC ALIGN PB - RELEASEEMS ROLL - OFFAl1gn GDC to lMU

PWR REDUCT (Norm Deorb Only)HGA PWR - OFFFC PUMPS (3) - OFFVer1fy s1ngle suit compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - Lowcb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2)-openlOb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MAN

-41-

P61 - ENTRY PREP

5 V37E 61E05 09 01427 - ROLL REVERSED05 09 01426 - IMU UNSAT

6 F 06 61 IMPACT LAT LONG liDS UPDN (+-)(01 0

010

+00001)

PRO

PAD VALUESLATLON==G------liDS UP DN _

7 F 06 60 GMAXV400KGAMMA EIRecord

GMAXV400K----GAMMA EI _

PRO

8 F 06 63 RTOGO (1nm) PAD _VIa (fps) PADTFE (mln-sec) ----Compare wlth MSFN for PGNS GONO GONO COMM SET RTOGO amp VIO IN EMS amp

INITIALIZE(ACCEPT) PRO(RECALC) V32E to 8

-42-

P62 - CMSM SEP amp PRE-ENTRY MNVR

9 F 50 25 00041 REQUEST CMSM SEPSC CONT - SCSFREEYAW - 45deg out-of-plane (left for RCS

nght for SPS)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE2PRIM GLY to RAD - BYPASS (verlfy)SECS LOGIC (2) - on (up)MSFN conflrm GO for PYRO ARMSECS PYRO ARM - ARMMN BUS TIE (2) - ON (verlfy)CMSM SEF (2) - ONCSMLM FNl SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 pSlaCM RCS LOGIC - OFFSECS PYRO ARM - SAFEMonltor VMAB

If lt25vdc go to EMERG POWERDOWN Pg E6-1AUTO RCS SEL AlC ROLL (4) - OFFAUTO RCS SEL CM 2(6) - OFFAUTO RCS SEL CM 1(6) - MNA or MNBYAW back to 00

PITCH TO ENTRY ATTROLL 0deg (LIFT UP)PITCH - HORIZ on 317deg MARK (400K)YAW 00

ATT DB - MAXMAN ATT (PITCH) - ACCEL CMDEMS DATA - VerifyEMS FUNC - ENTRY (verlfy)EMS MODE - NORMALMAINTAIN HORIZ TRK

PRO (Act ENTRY DAP)

10 F 06 61 IMPACT LAT LONG HDSDN(010 010 -00001)

PRO

11 FOSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axlS beyond 45deg of Vel vector)

-43-

P63 - ENTRY INIT

12 06 64 GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PWR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRHORIZ CKP~tch error needle goes toward

zero approach~ng 05G t~me

MAN ATT (PITCH) - RATE CMDIf CMC ~s GO

BMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS FLY BETA If CMC NO GO ~

SC CONT - SCS~

FLY EMS RCS Deorh Roll HDS UPTRACK HORIZ w~th 29deg w~ndow mk

P64 - ENTRY POST 05G

13

05G t=elt+0___)

06 68

RTOGO AT 05G AGREES WITH EMS - venfyHORIZ CK05E Lt - on (EMS start)

No EMS start w~th~n 3 secsEMS MODE - BACKUP VHF RNG 05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds L~ft DN

NNVR L~ft DNEMS GONO GO

G-V Plot w~th~n llm~ts

Rng ctr dwn 60 + 7 durlng 10 sec per~od

Mon~tor G-meter forconvergence wlth pad data (Do)

(Vlt27K fps) Go To 17

-44-

P65 - ENTRY - UP CONT (Vgt27K fps)

14 F 16 69 BETA (01deg)DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT~

SC CONT - SCS FLY EMS

PRO

15 06 68 BElA VI HOOT (01deg fpsfps)(VltVL +500 fps amp RDOT Neg) Go To 17

p66 - ENTRY - BALLISTIC (DltDL)

16 06 22 DESIRED GMBL ANGLES RPY (01deg)Mon~tor hor~z +12deg of 317deg mark

P67 - ENTRY - FINAL PHASE (02G)

17 0666 BETACRSRNG ERRDNRNG ERR (Oldeglnmlnm)KEY VERBRecord DNRNG ERR _KEY RLSEL~m~t +100nm from PAD DRE

Mon~tor l~ft vector on RSI amp FDAIF 16 67 RTOGOLATLONG (Vre1=1000fps)

(lnm 010 01deg)SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOlfflMon~tor altimeter

Go To EARTHLANDING pg _I4L5__

-45-

56 EARTHLANDING

90K STEAM PRESS - PEGGED50K CABIN PRESS REL vIv (2) - BOOSTENTRY

SECS PYRO ARM (2) - ARM

40K(90K + 63s)

CM UNSTABLE RCS CMD - OFF ~ 40K APEX COVER JETT PG-PUSH DROGUE DEPLOY PG - PUSH (2 secafter apex cover Jett)

30K ELS LOGIC - ON (up)ELS - AUTO

24K RCS hsable (auto)(90K+92s) RCS CMD - OFF

Apex cover Jett (auto)APEX COVER JETT PB - PUSH

(WAIT 2 SECS)Drogue parachutes deployed (auto)

DROGUE DEPLOY PB - PUSH~

If Drogues FallELS - ~ ~Stablllze CM 5K MAIN DPLY PB - PUSHELS - AUTO

235K Cabln Pressure lncreaslng (Drogues + 50s)If not lncreaSlng by 17K CABIN PRESS REL vlv (RR) - DUMP

-46-

10K Maln parachutes deployedMAIN DEPLOY PB - PUSH (wlthln 1 sec)VHF ANT - RECYVHF AMA - SIMPLEXVHF BCN - ONCABIN PRESS REL v1v (2) - CLOSEDIRECT 02 vlv - OPENCM RCS LOGIC - on (up)CM PRPLNT - DUMP (burn audlb1e)Monltor CM ReS 1amp2 for He press decrease

NO BURN or PRESS DECREASE USE BOTH RHCs DO NOT FIRE PITCH JETS

CM PRPLNT-PURGE (to zero He press)CM RCS He DUMP PB - PUSH RHC (2) - 30 sees NO PITCH k

STRUT LOCKS (2) - UNLOCK

cb FLT amp PL BAT BUS ABampBAT C (3) - closecb FLT amp PLT MNA amp B (2) - opencb ECS RAD HTR OVLD (2) - opencb SPS PampY (4) - open

3K CABIN PRESS REL v1v (RH) - DUMP (after purgecompleted)

FLOOD Lts - POST LDGCM RCS PRPLNT (2) - OFFROT CONTR PWR DIRECT (2) - OFF

800 CAB PRESS RELF vlv - CLOSE (latch off)MN BUS TIE (2) - OFF

AFTER LANDINGcb MAIN REL PYRO (2) - closeMAIN RELEASE - on(up)

Go to POSTLANDING pg _47L-__

I

2

3

-47-

57 POSTLANDING

STABILIZATION VENTILATION COMMUNICATIONS

DIRECT 02 vlv - CLOSE

Stablllzation after landlngELS - AUTO (verlfy)cb MAIN REL PYRO (2) - close (venfy)MAIN RELEASE - on (up) (verlfy)S~CS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb BAT RLY BUS (2) - open

No contact w1th recovery forcesVHF AM AampB - off (ctr) ~

VHF AM Rev ONLY - A cb PL VENT - closecb FLOAT BAG (3) - closecb UPRIGHT SYS COMPRESS (2) - closeIf Stable II

FLOAT BAG(3)-FILL t1ll 2 m1n afterupr1ght then - OFF

VHF AM AlB amp BCN - OFF whlle lnvertedIf Stable I

After 10 M1n Coollng Per1odFLOAT BAG (3) - FILL 7 mln then OFF

Post Stab1lizat1on And Ventllat10nPL BCN LT - BCN LT LOWPL VENT vlv - UNLOCK (Pull)Remove PL VENT Exh CoverPL VENT - HIGH or LOWPL DYE MARKER - ON (swlmmer comm)Release foots traps and_restralntscb MNA BAT BUS A amp BAT C (2) - opencb MNB BAT BUS B amp BAT C (2) - opencb FLT amp PL BAT C - opencb PYRO A SEQ A - opencb PYRO B SEQ B - open

EACH HR - CHECK DC VOLTSgt 275 V If Notmiddot cb FLT amp PL-BAT BUS AampB (2) -open cb FLT amp PL BAT C (1) - open GO TO LOW POWER CHECKLIST

Unstow and lnstall PLV DISTRIB DUCTDeploy grappllng hook and 11ne 1f req

4

-48-

Post Landing Communlcatl0nsVHF ANT-RECY (venfy)VHF BCN - ON (verlfy)

If no contact ~lth recovery forcesperform VHF BEACON Check

MONITOR VHF BEACON transmlSSlonnth VHF AM B Rcvr andor Su)vlval

TransceiverkVHF Beacon not operatlng ~connect Surv~val TranscelVer to antcable behlnd VHF ant access pnland place radio ln BCN mode

LOW POHER CHECKLISTVHF BCN - OFFVHF AM (3) - RCVFLOOD Lts - OFFVHF AM AampB - off (ctr)VHF AM RCV ONLY - A (venfy)COUCH LIGHTS - OFFPOSTLANDING VENT SYS mlnlmlze useSURV RADIO - plug mto VHF BCN ANT cableconn behind VHF ant acess pnl amp turn radloon l-n BCN mode

EGRESS PROCEDURES

CMPCDRLMPCDR

CMPCDRCMP

LMPLl1PCDR

STABLE IDlsconnect Umblll-calsNeck darn onCenter couch - 270 0 positionArmrests stowedConnect raft to SIC l-f desl-red wlth

green lanyardConnect raft ~hl-te lanyards to SUltS amp

lnflate water wlngs when eXltl-ngHATCH PISTON PRESS vlv - PRESS (Outbd)Slde Hatch openedPL VENT - OFFcb Pnl 250 (all) - openEgress with 11feraftPut hardware klt outEgress

or CDIPALL

CMF

CDRCMF

CDR

LMF

CMFCMP LMFCMP

UlP

CDR

-49-

STABLE IIcb CREW STA AUDIO (3) - openD~sconnect umb~1~ca1s

Release foots trapsRelease restra~nt harnessCouch seat pans (3) - 170 0 pos1t10nArm rests stowedSurv1va1 k~ts removed from stowageConnect life raft ma~n1~ne to CDR or SicConnect f~rst wh~te lanyard from

11fe raft to suitConnect th~rd wh~te lanyard from

l~fe raft to SU1tConnect rucksacks together to yellow

lanyard on raft bagPRESSURE EQUALIZATION vlv - OPENRemove and stow fwd hatchEX1t feet f1rst w1th rucksacks when clear

of siC 1nflate water w1ngs and raftExit feet f1rst when clear of SiC

1nflate water w1ngsEX1t feet f1rst when clear of sic

1nflate water w1ngs

-50-

60 TLI ABORTS

TLI Aborts are conta~ned ~n the ESD s~nce the bulk of the funct~ons

concern entry preparat20ns and performance Th~s allows a s2nglesource of procedures for procedure rev2ew val~dat~on checkout andtra~n~ng These procedures ~ncorporate TLI preparat20ns as found ~n

reference 6 w~th the TLI Abort Procedures and these t~e 2nto normallunar return Entry Procedures found ~n sect20n 5 The guidel~nes

for th~s cont2ngency are spec2f2ed 2n reference 7

In2t2al preparat~ons for TLI pos2t20n the necessary system sW2tches2n add~t~on to perform~ng an EMS ~V test and a GDC al~gnment Afterthe DET ~s set for mon2tor2ng TB6 the CMP ~ncreases the 12ght levelof the LEB DSKY to max~mum and returns to the h2s couch Th2s 2Sdone so that the LEB DSKY can be observed ~n the event sunl~ght orreflect20ns wash out the ma2n d2splay panel DSKY dur2ng cr2t2calmaneuvers The crew then straps ~n and prepares for mon2tor~ng TB6as 2nd2cated by the SII SEP L~te The t2mes se~uence of procedures2S keyed on th~s d~splay and ~ncludes the DET START funct~on andSIVB IGNITION Dur2ng the burn the crew mon2tors the FDAIs foratt~tude excurs20ns and abnormal rates report~ng status checks toM~ss2on Control at d2screet t~mes dur2ng the maneuver Upon SIVBSHUTDOWN the eMP records the DSKY d~splayed performance parametersand awa2ts ground conf2rmat~on

The rat~onal for TLI aborts ~s descr~bed 2n reference 7 A summar2shyzat20n 2S extracted to prov2de background and gu2de12nes 2n th2sdocument The abort procedures cover aborts 10 m2nutes after conshyt2ngent SIVE shutdown and aborts 90 m2nutes after normal SIVE shutshydown t2me

The 10 m~nute TLI abort ~s des2gned to be used dur~ng TLI ~n theevent a spacecraft problem develops Wh2Ch can result 2n catastrophe2f ~mmed~ate act~on 2S not taken If the s~tuat20n perm~ts the crewshould always allow the SIVB to complete TLI at wh~ch t~me the groundand crew can perform a malfunct~on analys~s to determ~ne ~f an abort~s adv~sable If a fa~lure occurs that necess2tates the shutdown ofthe SIVB and the ~u~ck return of the crew to earth th~s abort ~s

des~gned to be as ~nsens~t~ve to execut~on errors as poss~ble andst21l be targeted to m2dcorr2dor The burn att~tude w~th the f~ed

hor~zon reference ~s a constant value for any shutdown t~me Theburn durat~on 2S a funct20n of shutdown t2me and 2S ava21able fromcrew charts S~nce the pr~mary purpose of th~s abort ~s to returnto earth as qU2ckly as poss2ble there are no restr2ct20ns as toland~ng locat~on However ~f the t~me to EI is greater than abouttwo hours a midcourse correct20n should be ant~c~pated

The 90 m2nute TLI abort 2S to be used 2f a cr2t2cal subsystem malshyfunct~on ~s determ2ned and the dec2s~on to abort ~s made after the

-51-

TLI cutoff and before TLI cutoff plus approxlmately 80 m1nutesTh1S allows suff1c1ent separatlon and procedural t1me to set upfor the SPS deorb1t burn performed at about TLI + 90 Note thatgenerally the deorb1t burns w1ll be performed a fe11 m1nutes beforeTLI + 90 accord1ng to crew charts shown In reference 8 The no-comm except10n requ1res that 90 m1nutes be the 1nput t1me of 19n1shytlon for P-37 (onboard return-to-earth abort program) so that onshyboard calculatlons can correspond w1th ground calculat10ns to computethe CM land1ng p01nt Th1S TLI abort lS des1gned so that returnfl1ght t1me does not exceed 18 hours and abort ~V does not exceed7000 fps ThlS abort can be performed uSlng chart ~Vs and attltudesand the earths hor1zon serves as a suff1c1ent reference The maneushyver lS targeted to ach1eve the mldcorr1dor entry target Ilne andtlmed to result 1n a deslgnated recovery area

It 1S ObV10US for abort deC1S1ons early 1n the TLI + 90 m1nute t1meshyframe that a GampN SPS burn should be performed In order to keep theTLI abort procedures cons1stent and w1th emphasls on slmpl1c1ty theprocedures here reflect a SCS SPS abort burn to cover the full abortdec1s1on t1meframe

A m1dcourse correct1on for corr1dor control after a TLI abort may bedeS1red 1f the SPS burn d1d not meet expectat1ons The TLIabortprocedures 1n th1S sect10n adapt to the normal lunar return tlmel1neand procedures pr10r to the f1nal MCC

-52-

61 TLI PREPARATION PROCEDURES

GET = 150

CRO AOS(___)

CRO LOS( )(22142)

5100

Don Helmets amp Gloves

XLUNAR - INJECT (verify)EDS PWR - on (venfy)EMS FUNC - OFF (verlfy)EMS MODE - STBYEMS FUNC - IW SETVHF RNGEMS MODE - NORMALSet ~V indo to +15868 fpsEMS FUMC - ~V Test

SPS THRUST Lt - onoff (10 sec)~V lnd stops at -01 to -415

EMS MODE - STBYEMS FUMC - ~V SETVHF RNGSet ~VC

EMS FUNC---~~V=----

GDC ALIGNFDAI Select - liZcb SECS LOGIC (Z) - close (verify)cb SECS ARM (Z) - closeSECS LOGIC (Z) - on (up)MSFN Conflrm GO for PYRO ARM (If pass)SECS PYRO ARM (Z) - on (up)TRANS CONTROL PWR - ONROT CONTR PWR NORMAL (Z) - ACDC(verlfy)ROT CONTR PWR DIRECT (Z) - MNAMNBLV INnGPI - SIISIVB (venfy)LV GUID - IU (venfy)cb DIRECT ULLAGE (Z) - closedSet EVENT TIMER to 5100Begin MONITOR For TB6

CMP to Couch

TB 6 - SII SEP Lt on (TIG-9 mln 38 sec)KEY V83E

SET ORDEALFDAI Z ORB RATE at 180 0 0SII SEP Lt out (38 sec later)Start DET COUNTING UPSC CaNT - SCS (verify)MONITOR LV TANK PRESS

~P lt 36 psid (OXID gt FUEL)~P lt Z6 psid (FUEL gt OXID)

EMERGENCY CSMLV SEP UP TLM CM - BLOCK (verify)UP TLM IU - BLOCK (venfy)

-53-

+45degPY))0middot sec PY

lOK nmltHAlt25K nm

Two phas~ng mnvrs two SPS mnvrs to circular~ze at 150 nmearth orb~t

CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ssion 4K nmltHAltlOK nm CSM amp1M - Two phasing mnvrs two SPS mnvrs to circularize at 150 nm earth orb~t CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ss~on

CSM amp 1M - Two phas~ng mnvrs APS burn todepletion th~rd phasing mnvrSPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn tosem~sync orb~t

25K nmltHAlt40K nm CSM amp 1M - Two phasmg mnvrs APS burn to depletion third phas~ng mnvr SPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn to sem~sync orbit HA)40K nm DPS ava~l - DPS LOll circularize with SPS

DPS not ava~l - Lunar flyby or CSM only to lunar orbit (if reqd gtV lt4000 fps)

V37E 47E (check b~as) Record -=--rshy(Limit 98 fpsmm)

( 1fps)tVXYZN62EVIHDOTHPAD (fpsfpslnm)MONITOR VI ( ) at ECO

SCS TVC SERVO PWR 1 - ACIMNA2 - OFF

TAPE RCDR - CMD RESETHBREMS MODE - NORMAL

SIr SEP Lt - ONTLI Inhib~t S~gnals w~11 not be honored after 5942

SIVB ULLAGE BeginsSII SEP Lt - off (TIG - 18 sec)SIVB FUEL LEADSIVB ULLAGE d~scont~nues

LV ENG I Lt - onSIVB IGNITION ( GETI)LV ENG I Lt - off - -shyMONITOR THRUST amp ATTITUDEMONITOR LV TANK PRESSSIVE ECO (Lt on) (BEGIN TB7)

EMER SIVE CUTOFF AT 6 SEC PAST BURN TIME IF VI ATTAINEDTHC CCW ampNEUTRAL IN 1 SEC or SIISIVB sW - LV STAGEPremature Shutdown HAlt4K nm CSM amp 1M -

5700

58205836

F 16 835800

F 16 62

5838594259525955595900000002SUNRISE(___)

HAW AOS(__=_) KEY VERB (freeze d~splay)

SIVB ATT HOLD 20 sec amp BEGIN VENTINGSIVB NNVR TO ORB RT (HDS DN) (3middot sec)

Record VI -c---HDOT _

HPAD _

KEY RLSEF 16 62

F 16 83

HAW LOS(__=-)

KEYmiddotRLSE~VXYZ (lfps)

Record ~VX---_

~vy

WZ--

AVC---_

TAPE RCDR - off (ctr)EMS MODE - STBYEMS FUNC - OFFSECS PYRO ARM (2) - SAFE

PRO

BURN STATUS REPORT

____--~TIG

BT------VGX____-R

-----P----_Y

REMARKS

_____VI

______--HDOT______--H______---AVC______---FUEL_______OXID

_______UNBAL

F 3708=00 OOEGOS AOS CMP TO LEB

(-=-=-)

0000

0003

0005

0014

0100

-55-

62 TLI 10 MIN ABORTSECS LOGIC (2) - on (up)SECS PYRO ARM (2) - ARM

TRANS CONTR - CGH (4 sec) amp +XDET RESET (verlfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS GMD-ON

TRANS GONTR - neutral then +X for10 sec

SIVBGPI s~ - GPIExcesslve rates 6V THRUST A - NORMAL SPS THRUST - DIRECT When rates damped 6V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

TRANS CONTR +X - OFFV37E OOE

PITGH UP to LOGAL VERT (+X axlSto~ard the earth)

RATE - LOWBMAG MODE (3) - ATTIRATE 2EDS PHR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SEGS ARM (2) - opencb EDS (3) - open

TRANS CONTR -X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (180deg)P (199deg)Y (0deg)

RETRO UPDATEGETI _

JV _VG

Jtb ---GET 400K _

05G _GET DROGUE _

ENTRY P _R _

Y_--

0945

-56-

ALIGN HORIZ ON RET +1 MKGMBL CHECK (T11lle Pentattlng)MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conflnn)cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FUMC - JV SETVHF RNGSET JV from chartE~S FUMC - JVEMS fODE - NOIDlAL

lV THRUST A - NORMALV37E 47E (THRUST fONITOR)

F 16 83 lVXYZ (1 fps)

0950

1000

NOTE For aborts durlng 1st mln of TLIKEY V82E F 16 44 (HaHpTff)Burn untll Hp lt 19NM

TRANS CONTR +X

THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN JV reqdJV THRUST (2) - OFFReport cutoff

cb SPS P2 Y2- closeGfBL MTRS (4) - OFF (LMP Confinn)TRANS CONT PWR - OFFTVC SERVO PWR (2) - OFFMN BUS TIE (2) - OFFcb SPS P1amp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREIf est time to EIltOl5500 omlt fCC andenter the SUPERCIRC CKLIST as early as pos-slb1e Pg ~2~3~ __If est time to EI)Ol5500 anticlpate afCC Enter the ENTRY PREP CKLIST at step 9pg 18

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

-2tl C

l I W gt- ~-4

z laquo I I- 0 -6

l- I J u gt- ~-8

z w w -10

~_ONSANT

9O

VER

SHO

OT

BOU

ND

ARY

LIF

TV

EC

TOR

OR

IEN

TATI

ON

LIN

E

SH

ALL

OW

TAR

GE

TLI

NE

STE

EP

TAR

GE

TLI

NE 12

gU

ND

ERSH

OO

TBO

UN

DAR

Y

RE

EN

TRY

CO

RR

IDO

R

I ~ I

-12 24

26

28

30

32

34

RE

EN

TRY

VE

LOC

ITY

VE

1-F

TS

EC

Ch

art

1

36

3B

6-i

~

5CM

CC

ON

ST

NT

DR

VI z gt

~

I4

0 Cl W

I

gtamp

J+

-I

-

J Cl z

2U

l z 0_bull

bull-1

+-

u ubullbull

~r

U

)

2829

JOn

J23

33

43

5IN

ER

TIA

LR

EE

NTR

YV

ELO

CIT

YA

T4

00

00

0fl

VE

I-F

TS

EC

Ch

art

2

J63

73

8X

03

-i- rtREQUIRED PITCH GIMBAL ANG LETO OBTAIN HOR-IZON AT 317

DEGREES IN wiiiiDOW

260

z~I- ~ i5 24000

1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

-I

-1-

NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

I LU HD~-

LUHD

lt0 120UJ0

~

80 HOLD PRESENT TRIMgt LU HD013

~Y~HOIgtlt

TOP OF WINDOWa 40to

31 7 SCRIBEaaI

80 TTOM OF WINDOWi= 0

0--ltoa

-40t-z

~~~Uw w u lt0 -80

HOLO PRESENT TRIlJCl

LOHU0 lt0

J gt -120 HOLD 059 TRIMlt0 z

LDHUlt0 FIELD OF VI S10 NLDHU LIFT-DOWNHEADS -UPLUHD LIFT-UP HEADS-DOWN

~~H~-160 q - P63 LIMITI- NOrE-VALIO ONLY FO~t~--

LUNAR RETURN VELOCITY

plusmnl8020 244middot 8 12 16

TIME TO 400K FT ALTITUDE-MIN

4

P37

LONG

ITUD

ECO

RREC

TION

TOOB

TAIN

1350

NM

ENTR

YRA

NGE

Ugt

UJ

cgt

3z 0 I- u U

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0

0

2I

U~

UJ

cgt

I

gtI- U

gt z 0 J ltJ

1 -0

340

344

348

352

356

364

368

x10

3

CMC

INER

TIAL

VELO

CITY

AT40

0KAL

TITU

DE-

FTS

EC

Ch

art

5

I l I

o

20 100 -40

-10

-50

30

-20

--

+

-BB

A+

lrBB

A

=----

-----

t~I

AB

SA_

-04

0A

AV

Z=

-()4

D_

+

j

+

-

tfJ i~

plusmniff

--d~~tj

h-

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at

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-I

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-

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_-_

l

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60--

--1-

-0

2030

NOTE

40

NO

MIN

AL

RET

RB

=22

MIN

30

-40

-50

---------O

VE

RB

UR

N---------I------U

ND

ER

BU

RN

------I

~30

-20

-tD

010

20

AA

VX

FTS

EC

-60

Ch

art

6

1000

0 90

00 70

00 60

00 i50

00 iMl

OO ilOO

O i20

00 10

00 o

040

120

200

EMS

6V-

FTS

EC

240

320

400

440

520

S-IV

BeO

RN-

NSE

C

105

0

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LAUN

CHAZ

IMUT

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72r

rr

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BAL

ANGL

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ROLL

=IS

OPI

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YAW

0

TLI

-10

MIN

ABO

RTLA

UNCH

DEC

21

1968

400050

z =gt co23

0on 3

~7 X ampJ V

gt ~ 6

2627

~B

~n

_n

INER

TIAL

VELO

CITY

ATAB

ORT

IS-IV

BC

UTO

FF)middot

FTIS

EC34

3536

Xllf

Ch

art

7

7

1000

0i

0-00

EMS

V-F

TSE

C90

0080

0070

0060

0050

0040

0030

0020

0010

000

II

II

II

II

S-IV

BBU

RNTI

ME

-M

INSE

Cll-

41)

120

200

241)

320

400

441)

520

TlI

-I0

MIN

ABOR

TlA

UNCH

-DE

C21

19

68

lAUN

CHA

ZIM

UTH

lllJ

72I ~ I

Z526

27~

~bull

DX

~IN

ERTI

ALVE

LOCI

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T(5

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CU

TaF

l-

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Ch

art

8

34l6

Xla

3

-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 25: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

36

37

38 -OO45m

-22-

PYRO BATT CKcb PYRO A SEQ A - close (ver~fy)

cb PRYO B SEQ B - close (verify)DC IND - PYRO BAT A(B)

~If PYRO BAT A(B) lt 35 vdc cb PYRO A(B) seq A(B) - open~

PYRO A(B)BAT BUS A(B)TO PYRO~MN BUS TIE - close

cb MNA BAT C - closecb MNB BAT C - closeDC IND - MNBPNL 8 - All cbs closed except

PL VENT - open (ver~fy)

FLOAT BAG (3) - open (ver~fy)

DOCKING PROBE (2) - open (verlfy)EDS BAT (3) - open (ver~fy)

CM ReS HTRS (2) - open

CM RCS ACTIVATIONcb SECS ARM (2) - close (verlfy)cb SECS LOGIC (2) - close (verlfy)SECS LOGIC (2) - ONMSFN conflrm GO for PYRO ARM(~f poss)SECS PYRO ARM (2) - ARMCM RCS PRPLNT 1amp2 - ONCM RCS PRESS - ONRCS Ind sw - eMl then 2

He PRESS 3700-4400 pSlaMANF PRESS 287-302 pSla

SECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFF

P27 amp ENTRY PAD UPDATEGo To Entry Checkllst

Superclrc - pg ~2~3 _Hybnd - pg -----2~9L-__Normal Deorblt - pg __3L5L- _

-23-

52 SUPERCIRCULAR ENTRY

1 SET DET (up to ET)

2

3

4

5

3000(-30-00)

EMS INITIALIZATIONSET RNG TO PAD DATA RNGEMS FUNC - Vo SETSlew Scroll to Pad Data VIOEMS FUNC - ENTRY

RS I ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on (up)GDC ALIGN PB - PUSH amp HOLDYAW Tw - Pos~t~on RSI thru

45deg amp back to LIFT UPGDC ALIGN PB - ReleaseEMS ROLL - OFFA1~gn CDC to lMU

CM RCS RING A CKRCS TRNFR - CMcb CM RCS LOGIC MNB - openAUTO RCS SEL MNB (6) - OFFSC CONT - SCSTest R~ng A ThrustersSC CONT - CMCRCS TRNFR - SMAUTO RCS SEL (12) - MNAMNB

(hftoff conflg)cb CM RCS LOGIC MNB - close

OPTICS PWR - OFFCMP to COUCH

MN BUS TIE (2) - ONTAPE RCDR - REWIND

6 35middot0Om(-25middot 00)

-24-

SEPARATION CK LISTTVC SERVO PWR 1 - AClMNAcb ELS (2) - close (ver1fy)PRIM GLY TO RAn - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY vlv - OFFCAB PRESS REL vlv (2) - NORMGMBL MTRS (4) - STARTABORT SYS PRPLNT - RCS CMD (venfy)SM RCS PRIM PRPLNT (4) - ONVHF 11M (AampB) - OFFHI GAIN ANT PWR - OFFFC PUMPS (3) - OFFVer1fy s1ugle SU1t compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - 10101cb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2) - opencb HTRS OVLD (2) - openPOT H20 RTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANSEC COOL EVAP - RESETSEC COOL PUMP - off (etr)

MtiVR TO CMSM SEP P R ATTSC CONT - SCSCMC MODE - FREEMNVR TO PAD ATTR (0deg)PY----W)

-25-

SUPERCIRCULAR ENTRY (Cont~nued)

1

4100m(-1900)

P61 - ENTRY PREP

V37E 61E

k 05 09 01427 - ROLL REVERSED 05 09 01426 - IMU UNSAT ~

2 F 06 61 IMPACT LAT LONG HDS UPDN (+-)PRO (010

fps +00001)

3 F 06 60 GMAXVPREDGAMMA EIRecord

GMAXV400K----

GAMMA EI _PRO

(01deg fpsOldeg)

4 F 06 63 RTOGO (lnm) PAD _VIO (fps) PAD _TFE(m~n-sec)

Compare w~th ~M~SFN==C~f~o-r~P~GNS GONO GOIf NO COMM Set RTOGO amp VIO In EMS

amp lnltla11ze(ACCEPT) PRO(RECALC) V32E To 4

5 F 50 25

4300m

(-1700)

45 oOm(-1500)

500Om(-1000)

6 F 06 61

-26-

P62 - CMSM SEP amp PRE-ENTRY MNVRCAUTION Call No EXT Verbs In P62

00041 REQUEST CMSM SEPSC CONT - SCSFREE

COMPARE PITCH ATT WITH PAD DATA ---0=-

(W~thLU 5deg)YAW - 45deg OUT-OF-PLANE (LEFT)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTIRATE 2MN BUS TIE (2) - ON (ver~fy)

PRIM GLY TO RAD - BYPASS (verlfy)CM RCS LOGIC - ON (venfy)SECS LOGIC (2) - on (up)SECS PYRO ARM - ARMCMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 ps~a

CM RCS LOGIC - OFFSECS PYRO ARM (2) - SAFEMonltor VMAB

If lt25 vdc go to EMERGPOWERDOWN pg E6-l

AUTO RCS SEL AC ROLL (4) - OFFAUTO RCS SEL CM 2(6)-OFFAUTO RCS SEL CM 1(6)-MNAYAW back to 0degPITCH TO HORIZ TRACK ATT

ROLL - 0deg (LIFT UP)PITCH - 400K Horiz Mark (317deg)YAW - 0deg

ATT DB - MAXMAN ATT PITCH - ACCEL CMDEMS DATA - Ver~fy

EMS FliNC - ENTRY (ver~fy)

EMS MODE - NORMALcb SPS PampY (4) - openMAINT HORIZ TRK

PRO (Act ENTRY DAP)

IMPACT LATLONGHDSDN (01deg01deg-00001)PRO

7 POSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axis beyond 45deg of Vel vector)

8 06 64

58middot00m(-0200)

9

05G tlme(+0 )

(--=---)

06 68

-27-

P63 - ENTRY INIT

GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PIJR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRmDHORIZ CKPltch error needle goes toward

zero approachlng OSG tlmeMAN ATT (PITCH) - RATE CMD

If CMC lS GOBMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS I

FLY BETA If CMC NO GO ilt

1 SC CaNT - SCS I

FLY EMS k

p64 - ENTRY POST 05G

RTOGO AT 05G AGREES HITH EMS-venfyHORIZ CK05G Lt - ON (EMS START)

No EMS START wlthln 3 sec ~ EMS MODE - BACKUP VHF RNG c

05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds Llft DN

NNVR Llft DNEMS GONO GO

G-V Plot wlthln IlmltsRng ctr dwn 60plusmn7 durlng 10 sec

perlodMonltor G-meter for

convergence wlth pad data (Do)(Vlt27K fps) Go to 13

-28-

P65 - ENTRY - UP CONT (Vgt27K fps)

10 F 16 69 BETA (01middot) _DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT lt~ SC CONT - SCS FLY EMS

PRO

11 06 68 BETAVIHDOT (OIdegfpsfps)(VltV1+500 fps amp RnOT Neg) Go To 13

P66 - ENTRY - BALLISTIC (D(DL)

12 06 22 DESIRED GMBL ANGLES RPYMoultor horlz +12middot of 317middot mark

P67 - ENTRY - FINAL PHASE (02G)

13 06 66 BETACRSRNG ERRDNRNG ERR(010 1um 1um)

KEY VERBRecord DNRNG ERR _KEY RLSEMoultor l~ft vector ou RSI amp FDAI

16 67 RTOGOLATLONG (Vrel=1000fps)(lumOldegOldeg)

SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOWNMonitor a1t~meter

Go To EARTHLANDING pg ---4L5 _

-29-

53 GampN HYBRID DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL tV1 V37E 30E

2 F 06 33 GETI(ACCEPT) PRO (hrm~n Olsec)(REJECT) LOAD DESIRED GETI

3 F 06 81 tVXYZ (LV) (lfps)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

4 F 06 42 HAHPtV (lnm lfps)Record tV

(ACCEPT) PRO(REJECT) Reselect P30 or P27 Load new paramo

5 F 16 45 MTFIMGA (marksm~n-secOlO)

MGA -00002 ~f k

k lMU not al~gned

SET DETPRO

6

7

8

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (Pull)PLSS 02 vlv - FILL02 8M SUPPLY vlv - OFFCAB PRESS REL vlv (2) - NORMcb ELS (2) - closecb SECS ARM (2) - closecb SECS LOGIC (2) - close (ver~fy)

AUTO RCS SEL CM (12) - MNA or ~ffiB

(hftoff conhg)ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM (AampB) - OFF

CMP to Couch

9

10

11

-30-

MNVR TO PAD BURN ATTLOAD DAPBMAG MODE (3) - RATE 2SC CONT - CMCAUTOATT DB - MINMAN ATT (3) - RATE CMD

v62E

v49E

12 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLES

PRO

13 F 50 18 REQ MNVR TO FDAI RPY ANGLES (01deg)(AUTO) PRO(MAN) SC CONT - SCS

BMAG MODE (3) - RATE 2MNVR To 15

14 06 18 AUTO MNVR TO FDAI RPY ANGLES (01deg)

15 F 50 18 REQ TRIM TO FDAI RPY ANGLES (01deg)(TRIM) Go to 13(ByPASS) ENTR

16

17

CHECK BORESIGHT amp SKT STARSOPT MODE - CMCOPT ZERO - OFF

v41 N91E

18 F 21 92 SHAFTTRUN (01deg 001deg)Load SXTS angles

19 41 OPTICS DRIVECheck SKT STAR

OPT ZERO - ZEROCheck BORESIGHT STAR (~f ava~l)

20 V25 N17E (01deg)Load Pad Data GMBL Angles

for CM BURN ATTATT SETtw - SET

to PAD DATA GMBL ANGLESfor CM BURN ATT

21

22

-31-

PHR REDUCTIONHGA PHR - OFFFC PUMPS (3) - OFFVerify s~ngle su~t compr oper loads

balancedFC 2 MN AampB - OFFS BD PiR AMP - LOWcb ECS RAD CONTHTR (2) - opencb HASTE H20URINE DUMP HTRS(2)- opencb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANMN BUS TIE (2) - ONTVC SERVO PHR 1 - AC1MNAGMBL MTR (4) - START

p41 - RCS THRUSTINGV37E 41E

23 F 50 18 REQ MNVR TO LCL HORIZ (HDS ON)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CMCAUTOPRO To 24

(gtfANDAP) BMAG MODE (3) - RATE 2SC CONT - CMCHOLD

V62EMNVR To 25

24 06 18 AUTO MNVR TO FDAI RPY

25 F 50 18 REQ TRIM TO LCL HORIZ (01deg)ALIGN SC ROLL

(AUTO TRIM) PRO To 24(BYPASS) ATT DB - MIN

RATE - LOHMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTlRATE 2

ENTR

550Om26 06 85

59middot2527

-32-

VGXYZ (1fps)RECHECK BORESIGHT STARTRANS CONIR PWR - on (up)EMS MODE - STBY (ver~fy)

EMS FliNC - bV SETVHF RNGSET (IV for SM BURN _EMS FliNC - bVS BD ANT - OMNI CSECS LOGIC (2) - ONMSFN conhrm Go for PYRO ARMSECS PYRO ARM (2) - ARMCM RCS LOGIC - ON (ver~fy)

DSKY BLANKS

593028 16 85 VG XYZ (AVE G ON) (lfps)

RHCs amp THC - ARMEDLIMIT CYCLE - OFFTAPE RCDR - CMD RESETHBREMS MODE - NORMAL

000029 F 16 85 REQ NULL VG XYZ (lfps)

BURN EMS bV CTR TO ZERORESET DET amp COUNT UP

If SM ONLY burn go to step 32THC - LOCKEDSC CaNT - SCSFREERATE - HIGHPRIM GLY To RAD - BYPASS (ver~fy)

MN BUS TIE (2) - ON (ver~fy)

CMSM SEP (2) - on (up)CSMLM FNL SEP (2) - on (up) (verify)CampW MODE - CMRCS TRNFR - CMCM RCS LOGIC - OFF

Momtor VM ABIf lt25 vdc go to EMERGPOWER DOWN Pg E6-l

V63E

If CMC NO GO FDAI SOURCE - ATT FDAI SEL - 1 or 2 ATT SET - GDC

SET

-33-

~Uili ATT PITCH - ACCEL CMDFDAI SCALE - 55MNVR TO CM BURN ATT (NULL ERR NEEDLES)

R 0degPY --00--

30

31

CM RCS BURNRHC III-ContJnuous PJtch DownRHC HZ-Module PJtch to null needlesBURN VGZ TO ZERO

If only 1 RHC Pulse + P=5deg from retro att MaJnta~n rates lt3degsec

BURN COMPLETION ATllV CTR= or DET= _

V8ZE

32 F 16 44 HAHPTFF (1nmffiJn-sec)Check HP-

If gt Pad data contJnue burnuntJ1 lt Pad

PRO

33 F 16 85 VGXYZ (Ups)Read VG resJduals to MSFN

(HYBRID) PRO to 34(SM ONLY BURN)

PROF 37 ODE

EI-1500 V37E 47EF 16 83 twx Y Z (Ups)

SC CONT - SCSFREEMAN ATT (PITCH) - RATE CMDRATE - HIGHPRIM GLY To RAD - BYPASS (verJfy)MN BUS TIE (2) - ON (verJfy)CMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verJfy)Campl MODE - CMRCS TRNFR - CMCM ReS LOGIC - OFFSECS PYRO ~I (2) - SAFE

-34-

PROMonitor VMAB

If lt25 vdc go to EMERGPOWER DOWN

34 F 37 OOEPCM BIT RATE - LOWATT DB - MAXEMS MODE - STBYEMS FUNC - OFF

Go To EARTH ORBIT ENTRY pg _--40-__

-36-

8 SPS THRUSTING PREPCYCLE CRYO FANSSPS GAGING - ACI (ver~fy)

PUG MODE - NORM (venfy)BMAG MODE (3) - RATE 2tv CG - CSMCMC MODE - FREEAUTO RCS SEL (16) - MNA or HNB

(hftoff conbg)SC CONT - CMCAUTO

9 MNVR TO PAD BURN ATTV62E

10 V49E

11 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLESPRO

12 F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) PRO(HAN) SC CONT - ses

MNVR to 14

06 18 AUTO MNVR TO FDAI RPY ANGLES13

14 F 50 18 REO TRIH TO FDAI RPY ANGLES(TRIM) Go to 12(BYPASS) ENTR

15 BORESIGHT STAR CHECK

16 V37E 40EOPT PWR - OFF

17 F 50 18 REQUEST MNVR TO FDAI RPY ANGLES (01deg)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CHCAUTOPRO to 18

(MANDAP) BMAG HODE (3) - RATE 2SC CONT - CMCHOLDMNVR to 19

(HANseS) se eONT - sesMNVR to 19

-35-

54 NORMAL DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL ~V

1 V37E 30E

2 F 06 33 GETI (hrm~nOlsec)

(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

3 F 06 81 ~VXYZ (LV)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

( lfps)

4 F 06 42 HAHP~V (1nmlfps)Record W

(ACCEPT) PRO -----(REJECT) Rese1ect P30 or P27 Load new pa~am

5 F 16 45 MTFIMGA (marksmln-secOldeg)MGA -00002 If ~ lMU not a1~gned

SET DETPRO

6

7

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY v1v - OFFCAB PRESS REL v1v (2) - NORMcb ELS (2) - close (verify)cb SECS ARM (2) - close (ver~fy)

cb SECS LOGIC (2) - close (verlfy)AUTO RCS SEL CM (12) - ~mA or MNB

(l~ftoff conf~g)

ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM AampB - off (ctr)

18

-37-

06 18 AUTO MNVR TO FDAI RPY ANGLES (01 0)

19 l 50 18 REOUEST TRIM MNVR TOALIGN SIC ROLLGDC ALIGN

FDAI RPY ANGLES(010

)

+54-00m(-06-00)

TIG-5mJn

5500m(-0500)

TVC CHECK amp PREPcb STAB CONT SYS (all) - closecb SPS (12) - closeATT DB - MINRATE - LOl~

LIMIT CYCLE - ONMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE 2ROT CONTR PWR DIRECT (2) - OFFSCS TVC (2) - RATE CMD

If SCS SCS TVC (2) - AUTO SC CONT - SCS ~

TVC GMBL DRIVE PampY - AUTOMN BUS TIE (2) - ONTVC SERVO PWR 1 - AC1MNA

2 - AC2MNBTRANS CONTR PWR - ONROT CONTR PWR NORMAL 2 - ACRHC 2 - ARMED

HORIZ CHK - HorJz on 12deg wJndmlmark (LJffiJt +3 0 PNGCS GONO GO)

If NO GO set tw 180 0 180deg0 0

Track horJz wJth 24deg wJndow markAt TIG-2 mJn Ahgn GDC

PRIMARY TVC CHECKGMBL MOT P1-Y1 -STARTON(LMP confJrm)

If SCS verJfy Thumbwheel TrJmTHC - CWVenfy NO MTVC

SEC TVC CHECKGHBL MOT P2-Y2 -STARTON(LMP confJrm)SET GPI TRIHVenfy MTVCTHC NEUTRALGPI returns to 00 (CMC) or trJm (SCS)ROT CONT Pl~ NORM 2 - ACDC

(TRIM) Go to step 17(BYPASS) BMAG MODE(3) - ATTIRATE2 (ver1fy)

ENTR

-38-

20 F SO 25 00204 GMBL TEST OPTION(ACCEPT) SC CONT - GMC (ver~fy)

PROMonitor GPI Response

0020-2000020-200Tr~m

TEST FAIL SC CONT - SCS SCS TVC (2) - AUTO

(REJECT) ENTR

21 06 40 TFIVG~VM (m~n-sec1fps)

PROG ALM - TIG s1~pped

V5N9E 01703

KEY RLSE To 21 ROT CONTR PWR DIRECT (2) - MNABSPS He v1vs (2) - AUTO (ver~fy)

LIMIT CYCLE - OFFFDAI SCALE - SOIScb SPS P2Y2 - open (for cr~t burn)

5800(-02 00)

5925(-0035)

59middot 30(-0030)

06 40

59XX(-OOXX)

AV THRUST A(B) - NORMALTHC - ARMEDRlIC (2) - ARMEDTAPE RCDR - GID RESETHBR

DSKY BLANKS

(AVE G ON)EMS MODE - NORMAL

TFIVG~VM (m~n-seclfps)

CHECK PIPA BIAS lt2fps for 5 sec

ULLAGE AS REQ

IF NO ULLAGE DIR ULLAGE PB - PUSH~

CONTROL ATT WRlIC MONITOR AVM (R3) COUNTING UP

5955(-0005)

F 99 40 ENG ON ENABLE REQUEST(AUTO IGN) PRO AT TFI gt0 sec(BYPASS IGN) ENTR to 24

22 0000 IGN

-39-

If SCS - THRUST ON PB - PUSH

06 40 TFCVG~VM (m~n-seclfpslfps)

~F 97 40 SPS Thrust fall ~

~(RESTART) PRO To IGN (RECYCLE) ENTR To TIG-05 sec

SPS THRUST LITE - ONMONITOR THRUSTING

Pc 95-105 pSlaEMS COUNTING DOWNSPS IN3 v1vs (4) - OPENSPS He v1vs tb (2) - graySPS FUELOXID PRESS - 175-195 pSlaPUGS - BALANCED

PROG ALARM V5N9E 01407 VG INCTHC - CW FLY MTVC

ECOEMER SPS CUTOFF J

AV THRUST (2) - OFF

23 F 16 40 TFC(STATIC)VG~VM (mln-seclfps)~V THRUST AB - OFF

SPS IN3 v1vs (4) - CLOSEDSPS He tb (2) - bp

cb SPS P2Y2 - closed (verlfy)TVC SERVO PHR - AC1MNA (venfy)TVC SERVO PWR 2 - OFF

PRO

24 F 16 85 VG XYZ(CM) CUps)NULL RESIDUALSRECORD ~V CTR amp RESIDUALS I1VCEMS FUNC - OFF VGXEMS MODE - STBY VGYBMAG MODE (3) - RATE 2ATT DB - MAX VGZTRANS CONT PHR - OFF

PRO

25 F 37 V82E

26 F 16 44 HAHPTFF (lnmm~n-sec)

R3-59B59 HP gt494 nmPRO

27 F 37 OOE

-40-

55 EARTH ORBIT ENTRY

1 Venfy CMSMR __

P_shyY_-

SEP ATT(180deg)

(0deg )

2

3

4

EMS INITIALIZATIONEMS FUNC - RNG SETSET RNG TO PAD DATA RNGEMS FUNC - VA SETSlew scroll to pad data VIOEMS FUNC - ENTRY

RSI ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on(up)GDC ALIGN PB - PUSH amp HOLDYAW tw - Pos1tion RSI thru 45deg amp

back to LIFl UPGDC ALIGN PB - RELEASEEMS ROLL - OFFAl1gn GDC to lMU

PWR REDUCT (Norm Deorb Only)HGA PWR - OFFFC PUMPS (3) - OFFVer1fy s1ngle suit compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - Lowcb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2)-openlOb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MAN

-41-

P61 - ENTRY PREP

5 V37E 61E05 09 01427 - ROLL REVERSED05 09 01426 - IMU UNSAT

6 F 06 61 IMPACT LAT LONG liDS UPDN (+-)(01 0

010

+00001)

PRO

PAD VALUESLATLON==G------liDS UP DN _

7 F 06 60 GMAXV400KGAMMA EIRecord

GMAXV400K----GAMMA EI _

PRO

8 F 06 63 RTOGO (1nm) PAD _VIa (fps) PADTFE (mln-sec) ----Compare wlth MSFN for PGNS GONO GONO COMM SET RTOGO amp VIO IN EMS amp

INITIALIZE(ACCEPT) PRO(RECALC) V32E to 8

-42-

P62 - CMSM SEP amp PRE-ENTRY MNVR

9 F 50 25 00041 REQUEST CMSM SEPSC CONT - SCSFREEYAW - 45deg out-of-plane (left for RCS

nght for SPS)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE2PRIM GLY to RAD - BYPASS (verlfy)SECS LOGIC (2) - on (up)MSFN conflrm GO for PYRO ARMSECS PYRO ARM - ARMMN BUS TIE (2) - ON (verlfy)CMSM SEF (2) - ONCSMLM FNl SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 pSlaCM RCS LOGIC - OFFSECS PYRO ARM - SAFEMonltor VMAB

If lt25vdc go to EMERG POWERDOWN Pg E6-1AUTO RCS SEL AlC ROLL (4) - OFFAUTO RCS SEL CM 2(6) - OFFAUTO RCS SEL CM 1(6) - MNA or MNBYAW back to 00

PITCH TO ENTRY ATTROLL 0deg (LIFT UP)PITCH - HORIZ on 317deg MARK (400K)YAW 00

ATT DB - MAXMAN ATT (PITCH) - ACCEL CMDEMS DATA - VerifyEMS FUNC - ENTRY (verlfy)EMS MODE - NORMALMAINTAIN HORIZ TRK

PRO (Act ENTRY DAP)

10 F 06 61 IMPACT LAT LONG HDSDN(010 010 -00001)

PRO

11 FOSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axlS beyond 45deg of Vel vector)

-43-

P63 - ENTRY INIT

12 06 64 GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PWR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRHORIZ CKP~tch error needle goes toward

zero approach~ng 05G t~me

MAN ATT (PITCH) - RATE CMDIf CMC ~s GO

BMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS FLY BETA If CMC NO GO ~

SC CONT - SCS~

FLY EMS RCS Deorh Roll HDS UPTRACK HORIZ w~th 29deg w~ndow mk

P64 - ENTRY POST 05G

13

05G t=elt+0___)

06 68

RTOGO AT 05G AGREES WITH EMS - venfyHORIZ CK05E Lt - on (EMS start)

No EMS start w~th~n 3 secsEMS MODE - BACKUP VHF RNG 05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds L~ft DN

NNVR L~ft DNEMS GONO GO

G-V Plot w~th~n llm~ts

Rng ctr dwn 60 + 7 durlng 10 sec per~od

Mon~tor G-meter forconvergence wlth pad data (Do)

(Vlt27K fps) Go To 17

-44-

P65 - ENTRY - UP CONT (Vgt27K fps)

14 F 16 69 BETA (01deg)DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT~

SC CONT - SCS FLY EMS

PRO

15 06 68 BElA VI HOOT (01deg fpsfps)(VltVL +500 fps amp RDOT Neg) Go To 17

p66 - ENTRY - BALLISTIC (DltDL)

16 06 22 DESIRED GMBL ANGLES RPY (01deg)Mon~tor hor~z +12deg of 317deg mark

P67 - ENTRY - FINAL PHASE (02G)

17 0666 BETACRSRNG ERRDNRNG ERR (Oldeglnmlnm)KEY VERBRecord DNRNG ERR _KEY RLSEL~m~t +100nm from PAD DRE

Mon~tor l~ft vector on RSI amp FDAIF 16 67 RTOGOLATLONG (Vre1=1000fps)

(lnm 010 01deg)SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOlfflMon~tor altimeter

Go To EARTHLANDING pg _I4L5__

-45-

56 EARTHLANDING

90K STEAM PRESS - PEGGED50K CABIN PRESS REL vIv (2) - BOOSTENTRY

SECS PYRO ARM (2) - ARM

40K(90K + 63s)

CM UNSTABLE RCS CMD - OFF ~ 40K APEX COVER JETT PG-PUSH DROGUE DEPLOY PG - PUSH (2 secafter apex cover Jett)

30K ELS LOGIC - ON (up)ELS - AUTO

24K RCS hsable (auto)(90K+92s) RCS CMD - OFF

Apex cover Jett (auto)APEX COVER JETT PB - PUSH

(WAIT 2 SECS)Drogue parachutes deployed (auto)

DROGUE DEPLOY PB - PUSH~

If Drogues FallELS - ~ ~Stablllze CM 5K MAIN DPLY PB - PUSHELS - AUTO

235K Cabln Pressure lncreaslng (Drogues + 50s)If not lncreaSlng by 17K CABIN PRESS REL vlv (RR) - DUMP

-46-

10K Maln parachutes deployedMAIN DEPLOY PB - PUSH (wlthln 1 sec)VHF ANT - RECYVHF AMA - SIMPLEXVHF BCN - ONCABIN PRESS REL v1v (2) - CLOSEDIRECT 02 vlv - OPENCM RCS LOGIC - on (up)CM PRPLNT - DUMP (burn audlb1e)Monltor CM ReS 1amp2 for He press decrease

NO BURN or PRESS DECREASE USE BOTH RHCs DO NOT FIRE PITCH JETS

CM PRPLNT-PURGE (to zero He press)CM RCS He DUMP PB - PUSH RHC (2) - 30 sees NO PITCH k

STRUT LOCKS (2) - UNLOCK

cb FLT amp PL BAT BUS ABampBAT C (3) - closecb FLT amp PLT MNA amp B (2) - opencb ECS RAD HTR OVLD (2) - opencb SPS PampY (4) - open

3K CABIN PRESS REL v1v (RH) - DUMP (after purgecompleted)

FLOOD Lts - POST LDGCM RCS PRPLNT (2) - OFFROT CONTR PWR DIRECT (2) - OFF

800 CAB PRESS RELF vlv - CLOSE (latch off)MN BUS TIE (2) - OFF

AFTER LANDINGcb MAIN REL PYRO (2) - closeMAIN RELEASE - on(up)

Go to POSTLANDING pg _47L-__

I

2

3

-47-

57 POSTLANDING

STABILIZATION VENTILATION COMMUNICATIONS

DIRECT 02 vlv - CLOSE

Stablllzation after landlngELS - AUTO (verlfy)cb MAIN REL PYRO (2) - close (venfy)MAIN RELEASE - on (up) (verlfy)S~CS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb BAT RLY BUS (2) - open

No contact w1th recovery forcesVHF AM AampB - off (ctr) ~

VHF AM Rev ONLY - A cb PL VENT - closecb FLOAT BAG (3) - closecb UPRIGHT SYS COMPRESS (2) - closeIf Stable II

FLOAT BAG(3)-FILL t1ll 2 m1n afterupr1ght then - OFF

VHF AM AlB amp BCN - OFF whlle lnvertedIf Stable I

After 10 M1n Coollng Per1odFLOAT BAG (3) - FILL 7 mln then OFF

Post Stab1lizat1on And Ventllat10nPL BCN LT - BCN LT LOWPL VENT vlv - UNLOCK (Pull)Remove PL VENT Exh CoverPL VENT - HIGH or LOWPL DYE MARKER - ON (swlmmer comm)Release foots traps and_restralntscb MNA BAT BUS A amp BAT C (2) - opencb MNB BAT BUS B amp BAT C (2) - opencb FLT amp PL BAT C - opencb PYRO A SEQ A - opencb PYRO B SEQ B - open

EACH HR - CHECK DC VOLTSgt 275 V If Notmiddot cb FLT amp PL-BAT BUS AampB (2) -open cb FLT amp PL BAT C (1) - open GO TO LOW POWER CHECKLIST

Unstow and lnstall PLV DISTRIB DUCTDeploy grappllng hook and 11ne 1f req

4

-48-

Post Landing Communlcatl0nsVHF ANT-RECY (venfy)VHF BCN - ON (verlfy)

If no contact ~lth recovery forcesperform VHF BEACON Check

MONITOR VHF BEACON transmlSSlonnth VHF AM B Rcvr andor Su)vlval

TransceiverkVHF Beacon not operatlng ~connect Surv~val TranscelVer to antcable behlnd VHF ant access pnland place radio ln BCN mode

LOW POHER CHECKLISTVHF BCN - OFFVHF AM (3) - RCVFLOOD Lts - OFFVHF AM AampB - off (ctr)VHF AM RCV ONLY - A (venfy)COUCH LIGHTS - OFFPOSTLANDING VENT SYS mlnlmlze useSURV RADIO - plug mto VHF BCN ANT cableconn behind VHF ant acess pnl amp turn radloon l-n BCN mode

EGRESS PROCEDURES

CMPCDRLMPCDR

CMPCDRCMP

LMPLl1PCDR

STABLE IDlsconnect Umblll-calsNeck darn onCenter couch - 270 0 positionArmrests stowedConnect raft to SIC l-f desl-red wlth

green lanyardConnect raft ~hl-te lanyards to SUltS amp

lnflate water wlngs when eXltl-ngHATCH PISTON PRESS vlv - PRESS (Outbd)Slde Hatch openedPL VENT - OFFcb Pnl 250 (all) - openEgress with 11feraftPut hardware klt outEgress

or CDIPALL

CMF

CDRCMF

CDR

LMF

CMFCMP LMFCMP

UlP

CDR

-49-

STABLE IIcb CREW STA AUDIO (3) - openD~sconnect umb~1~ca1s

Release foots trapsRelease restra~nt harnessCouch seat pans (3) - 170 0 pos1t10nArm rests stowedSurv1va1 k~ts removed from stowageConnect life raft ma~n1~ne to CDR or SicConnect f~rst wh~te lanyard from

11fe raft to suitConnect th~rd wh~te lanyard from

l~fe raft to SU1tConnect rucksacks together to yellow

lanyard on raft bagPRESSURE EQUALIZATION vlv - OPENRemove and stow fwd hatchEX1t feet f1rst w1th rucksacks when clear

of siC 1nflate water w1ngs and raftExit feet f1rst when clear of SiC

1nflate water w1ngsEX1t feet f1rst when clear of sic

1nflate water w1ngs

-50-

60 TLI ABORTS

TLI Aborts are conta~ned ~n the ESD s~nce the bulk of the funct~ons

concern entry preparat20ns and performance Th~s allows a s2nglesource of procedures for procedure rev2ew val~dat~on checkout andtra~n~ng These procedures ~ncorporate TLI preparat20ns as found ~n

reference 6 w~th the TLI Abort Procedures and these t~e 2nto normallunar return Entry Procedures found ~n sect20n 5 The guidel~nes

for th~s cont2ngency are spec2f2ed 2n reference 7

In2t2al preparat~ons for TLI pos2t20n the necessary system sW2tches2n add~t~on to perform~ng an EMS ~V test and a GDC al~gnment Afterthe DET ~s set for mon2tor2ng TB6 the CMP ~ncreases the 12ght levelof the LEB DSKY to max~mum and returns to the h2s couch Th2s 2Sdone so that the LEB DSKY can be observed ~n the event sunl~ght orreflect20ns wash out the ma2n d2splay panel DSKY dur2ng cr2t2calmaneuvers The crew then straps ~n and prepares for mon2tor~ng TB6as 2nd2cated by the SII SEP L~te The t2mes se~uence of procedures2S keyed on th~s d~splay and ~ncludes the DET START funct~on andSIVB IGNITION Dur2ng the burn the crew mon2tors the FDAIs foratt~tude excurs20ns and abnormal rates report~ng status checks toM~ss2on Control at d2screet t~mes dur2ng the maneuver Upon SIVBSHUTDOWN the eMP records the DSKY d~splayed performance parametersand awa2ts ground conf2rmat~on

The rat~onal for TLI aborts ~s descr~bed 2n reference 7 A summar2shyzat20n 2S extracted to prov2de background and gu2de12nes 2n th2sdocument The abort procedures cover aborts 10 m2nutes after conshyt2ngent SIVE shutdown and aborts 90 m2nutes after normal SIVE shutshydown t2me

The 10 m~nute TLI abort ~s des2gned to be used dur~ng TLI ~n theevent a spacecraft problem develops Wh2Ch can result 2n catastrophe2f ~mmed~ate act~on 2S not taken If the s~tuat20n perm~ts the crewshould always allow the SIVB to complete TLI at wh~ch t~me the groundand crew can perform a malfunct~on analys~s to determ~ne ~f an abort~s adv~sable If a fa~lure occurs that necess2tates the shutdown ofthe SIVB and the ~u~ck return of the crew to earth th~s abort ~s

des~gned to be as ~nsens~t~ve to execut~on errors as poss~ble andst21l be targeted to m2dcorr2dor The burn att~tude w~th the f~ed

hor~zon reference ~s a constant value for any shutdown t~me Theburn durat~on 2S a funct20n of shutdown t2me and 2S ava21able fromcrew charts S~nce the pr~mary purpose of th~s abort ~s to returnto earth as qU2ckly as poss2ble there are no restr2ct20ns as toland~ng locat~on However ~f the t~me to EI is greater than abouttwo hours a midcourse correct20n should be ant~c~pated

The 90 m2nute TLI abort 2S to be used 2f a cr2t2cal subsystem malshyfunct~on ~s determ2ned and the dec2s~on to abort ~s made after the

-51-

TLI cutoff and before TLI cutoff plus approxlmately 80 m1nutesTh1S allows suff1c1ent separatlon and procedural t1me to set upfor the SPS deorb1t burn performed at about TLI + 90 Note thatgenerally the deorb1t burns w1ll be performed a fe11 m1nutes beforeTLI + 90 accord1ng to crew charts shown In reference 8 The no-comm except10n requ1res that 90 m1nutes be the 1nput t1me of 19n1shytlon for P-37 (onboard return-to-earth abort program) so that onshyboard calculatlons can correspond w1th ground calculat10ns to computethe CM land1ng p01nt Th1S TLI abort lS des1gned so that returnfl1ght t1me does not exceed 18 hours and abort ~V does not exceed7000 fps ThlS abort can be performed uSlng chart ~Vs and attltudesand the earths hor1zon serves as a suff1c1ent reference The maneushyver lS targeted to ach1eve the mldcorr1dor entry target Ilne andtlmed to result 1n a deslgnated recovery area

It 1S ObV10US for abort deC1S1ons early 1n the TLI + 90 m1nute t1meshyframe that a GampN SPS burn should be performed In order to keep theTLI abort procedures cons1stent and w1th emphasls on slmpl1c1ty theprocedures here reflect a SCS SPS abort burn to cover the full abortdec1s1on t1meframe

A m1dcourse correct1on for corr1dor control after a TLI abort may bedeS1red 1f the SPS burn d1d not meet expectat1ons The TLIabortprocedures 1n th1S sect10n adapt to the normal lunar return tlmel1neand procedures pr10r to the f1nal MCC

-52-

61 TLI PREPARATION PROCEDURES

GET = 150

CRO AOS(___)

CRO LOS( )(22142)

5100

Don Helmets amp Gloves

XLUNAR - INJECT (verify)EDS PWR - on (venfy)EMS FUNC - OFF (verlfy)EMS MODE - STBYEMS FUNC - IW SETVHF RNGEMS MODE - NORMALSet ~V indo to +15868 fpsEMS FUMC - ~V Test

SPS THRUST Lt - onoff (10 sec)~V lnd stops at -01 to -415

EMS MODE - STBYEMS FUMC - ~V SETVHF RNGSet ~VC

EMS FUNC---~~V=----

GDC ALIGNFDAI Select - liZcb SECS LOGIC (Z) - close (verify)cb SECS ARM (Z) - closeSECS LOGIC (Z) - on (up)MSFN Conflrm GO for PYRO ARM (If pass)SECS PYRO ARM (Z) - on (up)TRANS CONTROL PWR - ONROT CONTR PWR NORMAL (Z) - ACDC(verlfy)ROT CONTR PWR DIRECT (Z) - MNAMNBLV INnGPI - SIISIVB (venfy)LV GUID - IU (venfy)cb DIRECT ULLAGE (Z) - closedSet EVENT TIMER to 5100Begin MONITOR For TB6

CMP to Couch

TB 6 - SII SEP Lt on (TIG-9 mln 38 sec)KEY V83E

SET ORDEALFDAI Z ORB RATE at 180 0 0SII SEP Lt out (38 sec later)Start DET COUNTING UPSC CaNT - SCS (verify)MONITOR LV TANK PRESS

~P lt 36 psid (OXID gt FUEL)~P lt Z6 psid (FUEL gt OXID)

EMERGENCY CSMLV SEP UP TLM CM - BLOCK (verify)UP TLM IU - BLOCK (venfy)

-53-

+45degPY))0middot sec PY

lOK nmltHAlt25K nm

Two phas~ng mnvrs two SPS mnvrs to circular~ze at 150 nmearth orb~t

CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ssion 4K nmltHAltlOK nm CSM amp1M - Two phasing mnvrs two SPS mnvrs to circularize at 150 nm earth orb~t CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ss~on

CSM amp 1M - Two phas~ng mnvrs APS burn todepletion th~rd phasing mnvrSPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn tosem~sync orb~t

25K nmltHAlt40K nm CSM amp 1M - Two phasmg mnvrs APS burn to depletion third phas~ng mnvr SPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn to sem~sync orbit HA)40K nm DPS ava~l - DPS LOll circularize with SPS

DPS not ava~l - Lunar flyby or CSM only to lunar orbit (if reqd gtV lt4000 fps)

V37E 47E (check b~as) Record -=--rshy(Limit 98 fpsmm)

( 1fps)tVXYZN62EVIHDOTHPAD (fpsfpslnm)MONITOR VI ( ) at ECO

SCS TVC SERVO PWR 1 - ACIMNA2 - OFF

TAPE RCDR - CMD RESETHBREMS MODE - NORMAL

SIr SEP Lt - ONTLI Inhib~t S~gnals w~11 not be honored after 5942

SIVB ULLAGE BeginsSII SEP Lt - off (TIG - 18 sec)SIVB FUEL LEADSIVB ULLAGE d~scont~nues

LV ENG I Lt - onSIVB IGNITION ( GETI)LV ENG I Lt - off - -shyMONITOR THRUST amp ATTITUDEMONITOR LV TANK PRESSSIVE ECO (Lt on) (BEGIN TB7)

EMER SIVE CUTOFF AT 6 SEC PAST BURN TIME IF VI ATTAINEDTHC CCW ampNEUTRAL IN 1 SEC or SIISIVB sW - LV STAGEPremature Shutdown HAlt4K nm CSM amp 1M -

5700

58205836

F 16 835800

F 16 62

5838594259525955595900000002SUNRISE(___)

HAW AOS(__=_) KEY VERB (freeze d~splay)

SIVB ATT HOLD 20 sec amp BEGIN VENTINGSIVB NNVR TO ORB RT (HDS DN) (3middot sec)

Record VI -c---HDOT _

HPAD _

KEY RLSEF 16 62

F 16 83

HAW LOS(__=-)

KEYmiddotRLSE~VXYZ (lfps)

Record ~VX---_

~vy

WZ--

AVC---_

TAPE RCDR - off (ctr)EMS MODE - STBYEMS FUNC - OFFSECS PYRO ARM (2) - SAFE

PRO

BURN STATUS REPORT

____--~TIG

BT------VGX____-R

-----P----_Y

REMARKS

_____VI

______--HDOT______--H______---AVC______---FUEL_______OXID

_______UNBAL

F 3708=00 OOEGOS AOS CMP TO LEB

(-=-=-)

0000

0003

0005

0014

0100

-55-

62 TLI 10 MIN ABORTSECS LOGIC (2) - on (up)SECS PYRO ARM (2) - ARM

TRANS CONTR - CGH (4 sec) amp +XDET RESET (verlfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS GMD-ON

TRANS GONTR - neutral then +X for10 sec

SIVBGPI s~ - GPIExcesslve rates 6V THRUST A - NORMAL SPS THRUST - DIRECT When rates damped 6V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

TRANS CONTR +X - OFFV37E OOE

PITGH UP to LOGAL VERT (+X axlSto~ard the earth)

RATE - LOWBMAG MODE (3) - ATTIRATE 2EDS PHR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SEGS ARM (2) - opencb EDS (3) - open

TRANS CONTR -X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (180deg)P (199deg)Y (0deg)

RETRO UPDATEGETI _

JV _VG

Jtb ---GET 400K _

05G _GET DROGUE _

ENTRY P _R _

Y_--

0945

-56-

ALIGN HORIZ ON RET +1 MKGMBL CHECK (T11lle Pentattlng)MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conflnn)cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FUMC - JV SETVHF RNGSET JV from chartE~S FUMC - JVEMS fODE - NOIDlAL

lV THRUST A - NORMALV37E 47E (THRUST fONITOR)

F 16 83 lVXYZ (1 fps)

0950

1000

NOTE For aborts durlng 1st mln of TLIKEY V82E F 16 44 (HaHpTff)Burn untll Hp lt 19NM

TRANS CONTR +X

THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN JV reqdJV THRUST (2) - OFFReport cutoff

cb SPS P2 Y2- closeGfBL MTRS (4) - OFF (LMP Confinn)TRANS CONT PWR - OFFTVC SERVO PWR (2) - OFFMN BUS TIE (2) - OFFcb SPS P1amp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREIf est time to EIltOl5500 omlt fCC andenter the SUPERCIRC CKLIST as early as pos-slb1e Pg ~2~3~ __If est time to EI)Ol5500 anticlpate afCC Enter the ENTRY PREP CKLIST at step 9pg 18

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

-2tl C

l I W gt- ~-4

z laquo I I- 0 -6

l- I J u gt- ~-8

z w w -10

~_ONSANT

9O

VER

SHO

OT

BOU

ND

ARY

LIF

TV

EC

TOR

OR

IEN

TATI

ON

LIN

E

SH

ALL

OW

TAR

GE

TLI

NE

STE

EP

TAR

GE

TLI

NE 12

gU

ND

ERSH

OO

TBO

UN

DAR

Y

RE

EN

TRY

CO

RR

IDO

R

I ~ I

-12 24

26

28

30

32

34

RE

EN

TRY

VE

LOC

ITY

VE

1-F

TS

EC

Ch

art

1

36

3B

6-i

~

5CM

CC

ON

ST

NT

DR

VI z gt

~

I4

0 Cl W

I

gtamp

J+

-I

-

J Cl z

2U

l z 0_bull

bull-1

+-

u ubullbull

~r

U

)

2829

JOn

J23

33

43

5IN

ER

TIA

LR

EE

NTR

YV

ELO

CIT

YA

T4

00

00

0fl

VE

I-F

TS

EC

Ch

art

2

J63

73

8X

03

-i- rtREQUIRED PITCH GIMBAL ANG LETO OBTAIN HOR-IZON AT 317

DEGREES IN wiiiiDOW

260

z~I- ~ i5 24000

1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

-I

-1-

NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

I LU HD~-

LUHD

lt0 120UJ0

~

80 HOLD PRESENT TRIMgt LU HD013

~Y~HOIgtlt

TOP OF WINDOWa 40to

31 7 SCRIBEaaI

80 TTOM OF WINDOWi= 0

0--ltoa

-40t-z

~~~Uw w u lt0 -80

HOLO PRESENT TRIlJCl

LOHU0 lt0

J gt -120 HOLD 059 TRIMlt0 z

LDHUlt0 FIELD OF VI S10 NLDHU LIFT-DOWNHEADS -UPLUHD LIFT-UP HEADS-DOWN

~~H~-160 q - P63 LIMITI- NOrE-VALIO ONLY FO~t~--

LUNAR RETURN VELOCITY

plusmnl8020 244middot 8 12 16

TIME TO 400K FT ALTITUDE-MIN

4

P37

LONG

ITUD

ECO

RREC

TION

TOOB

TAIN

1350

NM

ENTR

YRA

NGE

Ugt

UJ

cgt

3z 0 I- u U

J0

0

0

2I

U~

UJ

cgt

I

gtI- U

gt z 0 J ltJ

1 -0

340

344

348

352

356

364

368

x10

3

CMC

INER

TIAL

VELO

CITY

AT40

0KAL

TITU

DE-

FTS

EC

Ch

art

5

I l I

o

20 100 -40

-10

-50

30

-20

--

+

-BB

A+

lrBB

A

=----

-----

t~I

AB

SA_

-04

0A

AV

Z=

-()4

D_

+

j

+

-

tfJ i~

plusmniff

--d~~tj

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it

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-I

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-

~

_-_

l

_-

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--10

-

+

~ni

-

-II

r

r-

60--

--1-

-0

2030

NOTE

40

NO

MIN

AL

RET

RB

=22

MIN

30

-40

-50

---------O

VE

RB

UR

N---------I------U

ND

ER

BU

RN

------I

~30

-20

-tD

010

20

AA

VX

FTS

EC

-60

Ch

art

6

1000

0 90

00 70

00 60

00 i50

00 iMl

OO ilOO

O i20

00 10

00 o

040

120

200

EMS

6V-

FTS

EC

240

320

400

440

520

S-IV

BeO

RN-

NSE

C

105

0

I 1- I

I

LAUN

CHAZ

IMUT

H

72r

rr

ml

lJ8

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+rmr)lfl~

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BAL

ANGL

E

ROLL

=IS

OPI

TCH

=199

YAW

0

TLI

-10

MIN

ABO

RTLA

UNCH

DEC

21

1968

400050

z =gt co23

0on 3

~7 X ampJ V

gt ~ 6

2627

~B

~n

_n

INER

TIAL

VELO

CITY

ATAB

ORT

IS-IV

BC

UTO

FF)middot

FTIS

EC34

3536

Xllf

Ch

art

7

7

1000

0i

0-00

EMS

V-F

TSE

C90

0080

0070

0060

0050

0040

0030

0020

0010

000

II

II

II

II

S-IV

BBU

RNTI

ME

-M

INSE

Cll-

41)

120

200

241)

320

400

441)

520

TlI

-I0

MIN

ABOR

TlA

UNCH

-DE

C21

19

68

lAUN

CHA

ZIM

UTH

lllJ

72I ~ I

Z526

27~

~bull

DX

~IN

ERTI

ALVE

LOCI

TYAT

ABOR

T(5

-IVB

CU

TaF

l-

FTlS

EC

Ch

art

8

34l6

Xla

3

-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 26: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

-23-

52 SUPERCIRCULAR ENTRY

1 SET DET (up to ET)

2

3

4

5

3000(-30-00)

EMS INITIALIZATIONSET RNG TO PAD DATA RNGEMS FUNC - Vo SETSlew Scroll to Pad Data VIOEMS FUNC - ENTRY

RS I ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on (up)GDC ALIGN PB - PUSH amp HOLDYAW Tw - Pos~t~on RSI thru

45deg amp back to LIFT UPGDC ALIGN PB - ReleaseEMS ROLL - OFFA1~gn CDC to lMU

CM RCS RING A CKRCS TRNFR - CMcb CM RCS LOGIC MNB - openAUTO RCS SEL MNB (6) - OFFSC CONT - SCSTest R~ng A ThrustersSC CONT - CMCRCS TRNFR - SMAUTO RCS SEL (12) - MNAMNB

(hftoff conflg)cb CM RCS LOGIC MNB - close

OPTICS PWR - OFFCMP to COUCH

MN BUS TIE (2) - ONTAPE RCDR - REWIND

6 35middot0Om(-25middot 00)

-24-

SEPARATION CK LISTTVC SERVO PWR 1 - AClMNAcb ELS (2) - close (ver1fy)PRIM GLY TO RAn - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY vlv - OFFCAB PRESS REL vlv (2) - NORMGMBL MTRS (4) - STARTABORT SYS PRPLNT - RCS CMD (venfy)SM RCS PRIM PRPLNT (4) - ONVHF 11M (AampB) - OFFHI GAIN ANT PWR - OFFFC PUMPS (3) - OFFVer1fy s1ugle SU1t compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - 10101cb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2) - opencb HTRS OVLD (2) - openPOT H20 RTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANSEC COOL EVAP - RESETSEC COOL PUMP - off (etr)

MtiVR TO CMSM SEP P R ATTSC CONT - SCSCMC MODE - FREEMNVR TO PAD ATTR (0deg)PY----W)

-25-

SUPERCIRCULAR ENTRY (Cont~nued)

1

4100m(-1900)

P61 - ENTRY PREP

V37E 61E

k 05 09 01427 - ROLL REVERSED 05 09 01426 - IMU UNSAT ~

2 F 06 61 IMPACT LAT LONG HDS UPDN (+-)PRO (010

fps +00001)

3 F 06 60 GMAXVPREDGAMMA EIRecord

GMAXV400K----

GAMMA EI _PRO

(01deg fpsOldeg)

4 F 06 63 RTOGO (lnm) PAD _VIO (fps) PAD _TFE(m~n-sec)

Compare w~th ~M~SFN==C~f~o-r~P~GNS GONO GOIf NO COMM Set RTOGO amp VIO In EMS

amp lnltla11ze(ACCEPT) PRO(RECALC) V32E To 4

5 F 50 25

4300m

(-1700)

45 oOm(-1500)

500Om(-1000)

6 F 06 61

-26-

P62 - CMSM SEP amp PRE-ENTRY MNVRCAUTION Call No EXT Verbs In P62

00041 REQUEST CMSM SEPSC CONT - SCSFREE

COMPARE PITCH ATT WITH PAD DATA ---0=-

(W~thLU 5deg)YAW - 45deg OUT-OF-PLANE (LEFT)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTIRATE 2MN BUS TIE (2) - ON (ver~fy)

PRIM GLY TO RAD - BYPASS (verlfy)CM RCS LOGIC - ON (venfy)SECS LOGIC (2) - on (up)SECS PYRO ARM - ARMCMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 ps~a

CM RCS LOGIC - OFFSECS PYRO ARM (2) - SAFEMonltor VMAB

If lt25 vdc go to EMERGPOWERDOWN pg E6-l

AUTO RCS SEL AC ROLL (4) - OFFAUTO RCS SEL CM 2(6)-OFFAUTO RCS SEL CM 1(6)-MNAYAW back to 0degPITCH TO HORIZ TRACK ATT

ROLL - 0deg (LIFT UP)PITCH - 400K Horiz Mark (317deg)YAW - 0deg

ATT DB - MAXMAN ATT PITCH - ACCEL CMDEMS DATA - Ver~fy

EMS FliNC - ENTRY (ver~fy)

EMS MODE - NORMALcb SPS PampY (4) - openMAINT HORIZ TRK

PRO (Act ENTRY DAP)

IMPACT LATLONGHDSDN (01deg01deg-00001)PRO

7 POSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axis beyond 45deg of Vel vector)

8 06 64

58middot00m(-0200)

9

05G tlme(+0 )

(--=---)

06 68

-27-

P63 - ENTRY INIT

GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PIJR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRmDHORIZ CKPltch error needle goes toward

zero approachlng OSG tlmeMAN ATT (PITCH) - RATE CMD

If CMC lS GOBMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS I

FLY BETA If CMC NO GO ilt

1 SC CaNT - SCS I

FLY EMS k

p64 - ENTRY POST 05G

RTOGO AT 05G AGREES HITH EMS-venfyHORIZ CK05G Lt - ON (EMS START)

No EMS START wlthln 3 sec ~ EMS MODE - BACKUP VHF RNG c

05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds Llft DN

NNVR Llft DNEMS GONO GO

G-V Plot wlthln IlmltsRng ctr dwn 60plusmn7 durlng 10 sec

perlodMonltor G-meter for

convergence wlth pad data (Do)(Vlt27K fps) Go to 13

-28-

P65 - ENTRY - UP CONT (Vgt27K fps)

10 F 16 69 BETA (01middot) _DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT lt~ SC CONT - SCS FLY EMS

PRO

11 06 68 BETAVIHDOT (OIdegfpsfps)(VltV1+500 fps amp RnOT Neg) Go To 13

P66 - ENTRY - BALLISTIC (D(DL)

12 06 22 DESIRED GMBL ANGLES RPYMoultor horlz +12middot of 317middot mark

P67 - ENTRY - FINAL PHASE (02G)

13 06 66 BETACRSRNG ERRDNRNG ERR(010 1um 1um)

KEY VERBRecord DNRNG ERR _KEY RLSEMoultor l~ft vector ou RSI amp FDAI

16 67 RTOGOLATLONG (Vrel=1000fps)(lumOldegOldeg)

SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOWNMonitor a1t~meter

Go To EARTHLANDING pg ---4L5 _

-29-

53 GampN HYBRID DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL tV1 V37E 30E

2 F 06 33 GETI(ACCEPT) PRO (hrm~n Olsec)(REJECT) LOAD DESIRED GETI

3 F 06 81 tVXYZ (LV) (lfps)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

4 F 06 42 HAHPtV (lnm lfps)Record tV

(ACCEPT) PRO(REJECT) Reselect P30 or P27 Load new paramo

5 F 16 45 MTFIMGA (marksm~n-secOlO)

MGA -00002 ~f k

k lMU not al~gned

SET DETPRO

6

7

8

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (Pull)PLSS 02 vlv - FILL02 8M SUPPLY vlv - OFFCAB PRESS REL vlv (2) - NORMcb ELS (2) - closecb SECS ARM (2) - closecb SECS LOGIC (2) - close (ver~fy)

AUTO RCS SEL CM (12) - MNA or ~ffiB

(hftoff conhg)ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM (AampB) - OFF

CMP to Couch

9

10

11

-30-

MNVR TO PAD BURN ATTLOAD DAPBMAG MODE (3) - RATE 2SC CONT - CMCAUTOATT DB - MINMAN ATT (3) - RATE CMD

v62E

v49E

12 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLES

PRO

13 F 50 18 REQ MNVR TO FDAI RPY ANGLES (01deg)(AUTO) PRO(MAN) SC CONT - SCS

BMAG MODE (3) - RATE 2MNVR To 15

14 06 18 AUTO MNVR TO FDAI RPY ANGLES (01deg)

15 F 50 18 REQ TRIM TO FDAI RPY ANGLES (01deg)(TRIM) Go to 13(ByPASS) ENTR

16

17

CHECK BORESIGHT amp SKT STARSOPT MODE - CMCOPT ZERO - OFF

v41 N91E

18 F 21 92 SHAFTTRUN (01deg 001deg)Load SXTS angles

19 41 OPTICS DRIVECheck SKT STAR

OPT ZERO - ZEROCheck BORESIGHT STAR (~f ava~l)

20 V25 N17E (01deg)Load Pad Data GMBL Angles

for CM BURN ATTATT SETtw - SET

to PAD DATA GMBL ANGLESfor CM BURN ATT

21

22

-31-

PHR REDUCTIONHGA PHR - OFFFC PUMPS (3) - OFFVerify s~ngle su~t compr oper loads

balancedFC 2 MN AampB - OFFS BD PiR AMP - LOWcb ECS RAD CONTHTR (2) - opencb HASTE H20URINE DUMP HTRS(2)- opencb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANMN BUS TIE (2) - ONTVC SERVO PHR 1 - AC1MNAGMBL MTR (4) - START

p41 - RCS THRUSTINGV37E 41E

23 F 50 18 REQ MNVR TO LCL HORIZ (HDS ON)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CMCAUTOPRO To 24

(gtfANDAP) BMAG MODE (3) - RATE 2SC CONT - CMCHOLD

V62EMNVR To 25

24 06 18 AUTO MNVR TO FDAI RPY

25 F 50 18 REQ TRIM TO LCL HORIZ (01deg)ALIGN SC ROLL

(AUTO TRIM) PRO To 24(BYPASS) ATT DB - MIN

RATE - LOHMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTlRATE 2

ENTR

550Om26 06 85

59middot2527

-32-

VGXYZ (1fps)RECHECK BORESIGHT STARTRANS CONIR PWR - on (up)EMS MODE - STBY (ver~fy)

EMS FliNC - bV SETVHF RNGSET (IV for SM BURN _EMS FliNC - bVS BD ANT - OMNI CSECS LOGIC (2) - ONMSFN conhrm Go for PYRO ARMSECS PYRO ARM (2) - ARMCM RCS LOGIC - ON (ver~fy)

DSKY BLANKS

593028 16 85 VG XYZ (AVE G ON) (lfps)

RHCs amp THC - ARMEDLIMIT CYCLE - OFFTAPE RCDR - CMD RESETHBREMS MODE - NORMAL

000029 F 16 85 REQ NULL VG XYZ (lfps)

BURN EMS bV CTR TO ZERORESET DET amp COUNT UP

If SM ONLY burn go to step 32THC - LOCKEDSC CaNT - SCSFREERATE - HIGHPRIM GLY To RAD - BYPASS (ver~fy)

MN BUS TIE (2) - ON (ver~fy)

CMSM SEP (2) - on (up)CSMLM FNL SEP (2) - on (up) (verify)CampW MODE - CMRCS TRNFR - CMCM RCS LOGIC - OFF

Momtor VM ABIf lt25 vdc go to EMERGPOWER DOWN Pg E6-l

V63E

If CMC NO GO FDAI SOURCE - ATT FDAI SEL - 1 or 2 ATT SET - GDC

SET

-33-

~Uili ATT PITCH - ACCEL CMDFDAI SCALE - 55MNVR TO CM BURN ATT (NULL ERR NEEDLES)

R 0degPY --00--

30

31

CM RCS BURNRHC III-ContJnuous PJtch DownRHC HZ-Module PJtch to null needlesBURN VGZ TO ZERO

If only 1 RHC Pulse + P=5deg from retro att MaJnta~n rates lt3degsec

BURN COMPLETION ATllV CTR= or DET= _

V8ZE

32 F 16 44 HAHPTFF (1nmffiJn-sec)Check HP-

If gt Pad data contJnue burnuntJ1 lt Pad

PRO

33 F 16 85 VGXYZ (Ups)Read VG resJduals to MSFN

(HYBRID) PRO to 34(SM ONLY BURN)

PROF 37 ODE

EI-1500 V37E 47EF 16 83 twx Y Z (Ups)

SC CONT - SCSFREEMAN ATT (PITCH) - RATE CMDRATE - HIGHPRIM GLY To RAD - BYPASS (verJfy)MN BUS TIE (2) - ON (verJfy)CMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verJfy)Campl MODE - CMRCS TRNFR - CMCM ReS LOGIC - OFFSECS PYRO ~I (2) - SAFE

-34-

PROMonitor VMAB

If lt25 vdc go to EMERGPOWER DOWN

34 F 37 OOEPCM BIT RATE - LOWATT DB - MAXEMS MODE - STBYEMS FUNC - OFF

Go To EARTH ORBIT ENTRY pg _--40-__

-36-

8 SPS THRUSTING PREPCYCLE CRYO FANSSPS GAGING - ACI (ver~fy)

PUG MODE - NORM (venfy)BMAG MODE (3) - RATE 2tv CG - CSMCMC MODE - FREEAUTO RCS SEL (16) - MNA or HNB

(hftoff conbg)SC CONT - CMCAUTO

9 MNVR TO PAD BURN ATTV62E

10 V49E

11 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLESPRO

12 F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) PRO(HAN) SC CONT - ses

MNVR to 14

06 18 AUTO MNVR TO FDAI RPY ANGLES13

14 F 50 18 REO TRIH TO FDAI RPY ANGLES(TRIM) Go to 12(BYPASS) ENTR

15 BORESIGHT STAR CHECK

16 V37E 40EOPT PWR - OFF

17 F 50 18 REQUEST MNVR TO FDAI RPY ANGLES (01deg)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CHCAUTOPRO to 18

(MANDAP) BMAG HODE (3) - RATE 2SC CONT - CMCHOLDMNVR to 19

(HANseS) se eONT - sesMNVR to 19

-35-

54 NORMAL DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL ~V

1 V37E 30E

2 F 06 33 GETI (hrm~nOlsec)

(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

3 F 06 81 ~VXYZ (LV)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

( lfps)

4 F 06 42 HAHP~V (1nmlfps)Record W

(ACCEPT) PRO -----(REJECT) Rese1ect P30 or P27 Load new pa~am

5 F 16 45 MTFIMGA (marksmln-secOldeg)MGA -00002 If ~ lMU not a1~gned

SET DETPRO

6

7

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY v1v - OFFCAB PRESS REL v1v (2) - NORMcb ELS (2) - close (verify)cb SECS ARM (2) - close (ver~fy)

cb SECS LOGIC (2) - close (verlfy)AUTO RCS SEL CM (12) - ~mA or MNB

(l~ftoff conf~g)

ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM AampB - off (ctr)

18

-37-

06 18 AUTO MNVR TO FDAI RPY ANGLES (01 0)

19 l 50 18 REOUEST TRIM MNVR TOALIGN SIC ROLLGDC ALIGN

FDAI RPY ANGLES(010

)

+54-00m(-06-00)

TIG-5mJn

5500m(-0500)

TVC CHECK amp PREPcb STAB CONT SYS (all) - closecb SPS (12) - closeATT DB - MINRATE - LOl~

LIMIT CYCLE - ONMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE 2ROT CONTR PWR DIRECT (2) - OFFSCS TVC (2) - RATE CMD

If SCS SCS TVC (2) - AUTO SC CONT - SCS ~

TVC GMBL DRIVE PampY - AUTOMN BUS TIE (2) - ONTVC SERVO PWR 1 - AC1MNA

2 - AC2MNBTRANS CONTR PWR - ONROT CONTR PWR NORMAL 2 - ACRHC 2 - ARMED

HORIZ CHK - HorJz on 12deg wJndmlmark (LJffiJt +3 0 PNGCS GONO GO)

If NO GO set tw 180 0 180deg0 0

Track horJz wJth 24deg wJndow markAt TIG-2 mJn Ahgn GDC

PRIMARY TVC CHECKGMBL MOT P1-Y1 -STARTON(LMP confJrm)

If SCS verJfy Thumbwheel TrJmTHC - CWVenfy NO MTVC

SEC TVC CHECKGHBL MOT P2-Y2 -STARTON(LMP confJrm)SET GPI TRIHVenfy MTVCTHC NEUTRALGPI returns to 00 (CMC) or trJm (SCS)ROT CONT Pl~ NORM 2 - ACDC

(TRIM) Go to step 17(BYPASS) BMAG MODE(3) - ATTIRATE2 (ver1fy)

ENTR

-38-

20 F SO 25 00204 GMBL TEST OPTION(ACCEPT) SC CONT - GMC (ver~fy)

PROMonitor GPI Response

0020-2000020-200Tr~m

TEST FAIL SC CONT - SCS SCS TVC (2) - AUTO

(REJECT) ENTR

21 06 40 TFIVG~VM (m~n-sec1fps)

PROG ALM - TIG s1~pped

V5N9E 01703

KEY RLSE To 21 ROT CONTR PWR DIRECT (2) - MNABSPS He v1vs (2) - AUTO (ver~fy)

LIMIT CYCLE - OFFFDAI SCALE - SOIScb SPS P2Y2 - open (for cr~t burn)

5800(-02 00)

5925(-0035)

59middot 30(-0030)

06 40

59XX(-OOXX)

AV THRUST A(B) - NORMALTHC - ARMEDRlIC (2) - ARMEDTAPE RCDR - GID RESETHBR

DSKY BLANKS

(AVE G ON)EMS MODE - NORMAL

TFIVG~VM (m~n-seclfps)

CHECK PIPA BIAS lt2fps for 5 sec

ULLAGE AS REQ

IF NO ULLAGE DIR ULLAGE PB - PUSH~

CONTROL ATT WRlIC MONITOR AVM (R3) COUNTING UP

5955(-0005)

F 99 40 ENG ON ENABLE REQUEST(AUTO IGN) PRO AT TFI gt0 sec(BYPASS IGN) ENTR to 24

22 0000 IGN

-39-

If SCS - THRUST ON PB - PUSH

06 40 TFCVG~VM (m~n-seclfpslfps)

~F 97 40 SPS Thrust fall ~

~(RESTART) PRO To IGN (RECYCLE) ENTR To TIG-05 sec

SPS THRUST LITE - ONMONITOR THRUSTING

Pc 95-105 pSlaEMS COUNTING DOWNSPS IN3 v1vs (4) - OPENSPS He v1vs tb (2) - graySPS FUELOXID PRESS - 175-195 pSlaPUGS - BALANCED

PROG ALARM V5N9E 01407 VG INCTHC - CW FLY MTVC

ECOEMER SPS CUTOFF J

AV THRUST (2) - OFF

23 F 16 40 TFC(STATIC)VG~VM (mln-seclfps)~V THRUST AB - OFF

SPS IN3 v1vs (4) - CLOSEDSPS He tb (2) - bp

cb SPS P2Y2 - closed (verlfy)TVC SERVO PHR - AC1MNA (venfy)TVC SERVO PWR 2 - OFF

PRO

24 F 16 85 VG XYZ(CM) CUps)NULL RESIDUALSRECORD ~V CTR amp RESIDUALS I1VCEMS FUNC - OFF VGXEMS MODE - STBY VGYBMAG MODE (3) - RATE 2ATT DB - MAX VGZTRANS CONT PHR - OFF

PRO

25 F 37 V82E

26 F 16 44 HAHPTFF (lnmm~n-sec)

R3-59B59 HP gt494 nmPRO

27 F 37 OOE

-40-

55 EARTH ORBIT ENTRY

1 Venfy CMSMR __

P_shyY_-

SEP ATT(180deg)

(0deg )

2

3

4

EMS INITIALIZATIONEMS FUNC - RNG SETSET RNG TO PAD DATA RNGEMS FUNC - VA SETSlew scroll to pad data VIOEMS FUNC - ENTRY

RSI ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on(up)GDC ALIGN PB - PUSH amp HOLDYAW tw - Pos1tion RSI thru 45deg amp

back to LIFl UPGDC ALIGN PB - RELEASEEMS ROLL - OFFAl1gn GDC to lMU

PWR REDUCT (Norm Deorb Only)HGA PWR - OFFFC PUMPS (3) - OFFVer1fy s1ngle suit compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - Lowcb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2)-openlOb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MAN

-41-

P61 - ENTRY PREP

5 V37E 61E05 09 01427 - ROLL REVERSED05 09 01426 - IMU UNSAT

6 F 06 61 IMPACT LAT LONG liDS UPDN (+-)(01 0

010

+00001)

PRO

PAD VALUESLATLON==G------liDS UP DN _

7 F 06 60 GMAXV400KGAMMA EIRecord

GMAXV400K----GAMMA EI _

PRO

8 F 06 63 RTOGO (1nm) PAD _VIa (fps) PADTFE (mln-sec) ----Compare wlth MSFN for PGNS GONO GONO COMM SET RTOGO amp VIO IN EMS amp

INITIALIZE(ACCEPT) PRO(RECALC) V32E to 8

-42-

P62 - CMSM SEP amp PRE-ENTRY MNVR

9 F 50 25 00041 REQUEST CMSM SEPSC CONT - SCSFREEYAW - 45deg out-of-plane (left for RCS

nght for SPS)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE2PRIM GLY to RAD - BYPASS (verlfy)SECS LOGIC (2) - on (up)MSFN conflrm GO for PYRO ARMSECS PYRO ARM - ARMMN BUS TIE (2) - ON (verlfy)CMSM SEF (2) - ONCSMLM FNl SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 pSlaCM RCS LOGIC - OFFSECS PYRO ARM - SAFEMonltor VMAB

If lt25vdc go to EMERG POWERDOWN Pg E6-1AUTO RCS SEL AlC ROLL (4) - OFFAUTO RCS SEL CM 2(6) - OFFAUTO RCS SEL CM 1(6) - MNA or MNBYAW back to 00

PITCH TO ENTRY ATTROLL 0deg (LIFT UP)PITCH - HORIZ on 317deg MARK (400K)YAW 00

ATT DB - MAXMAN ATT (PITCH) - ACCEL CMDEMS DATA - VerifyEMS FUNC - ENTRY (verlfy)EMS MODE - NORMALMAINTAIN HORIZ TRK

PRO (Act ENTRY DAP)

10 F 06 61 IMPACT LAT LONG HDSDN(010 010 -00001)

PRO

11 FOSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axlS beyond 45deg of Vel vector)

-43-

P63 - ENTRY INIT

12 06 64 GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PWR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRHORIZ CKP~tch error needle goes toward

zero approach~ng 05G t~me

MAN ATT (PITCH) - RATE CMDIf CMC ~s GO

BMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS FLY BETA If CMC NO GO ~

SC CONT - SCS~

FLY EMS RCS Deorh Roll HDS UPTRACK HORIZ w~th 29deg w~ndow mk

P64 - ENTRY POST 05G

13

05G t=elt+0___)

06 68

RTOGO AT 05G AGREES WITH EMS - venfyHORIZ CK05E Lt - on (EMS start)

No EMS start w~th~n 3 secsEMS MODE - BACKUP VHF RNG 05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds L~ft DN

NNVR L~ft DNEMS GONO GO

G-V Plot w~th~n llm~ts

Rng ctr dwn 60 + 7 durlng 10 sec per~od

Mon~tor G-meter forconvergence wlth pad data (Do)

(Vlt27K fps) Go To 17

-44-

P65 - ENTRY - UP CONT (Vgt27K fps)

14 F 16 69 BETA (01deg)DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT~

SC CONT - SCS FLY EMS

PRO

15 06 68 BElA VI HOOT (01deg fpsfps)(VltVL +500 fps amp RDOT Neg) Go To 17

p66 - ENTRY - BALLISTIC (DltDL)

16 06 22 DESIRED GMBL ANGLES RPY (01deg)Mon~tor hor~z +12deg of 317deg mark

P67 - ENTRY - FINAL PHASE (02G)

17 0666 BETACRSRNG ERRDNRNG ERR (Oldeglnmlnm)KEY VERBRecord DNRNG ERR _KEY RLSEL~m~t +100nm from PAD DRE

Mon~tor l~ft vector on RSI amp FDAIF 16 67 RTOGOLATLONG (Vre1=1000fps)

(lnm 010 01deg)SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOlfflMon~tor altimeter

Go To EARTHLANDING pg _I4L5__

-45-

56 EARTHLANDING

90K STEAM PRESS - PEGGED50K CABIN PRESS REL vIv (2) - BOOSTENTRY

SECS PYRO ARM (2) - ARM

40K(90K + 63s)

CM UNSTABLE RCS CMD - OFF ~ 40K APEX COVER JETT PG-PUSH DROGUE DEPLOY PG - PUSH (2 secafter apex cover Jett)

30K ELS LOGIC - ON (up)ELS - AUTO

24K RCS hsable (auto)(90K+92s) RCS CMD - OFF

Apex cover Jett (auto)APEX COVER JETT PB - PUSH

(WAIT 2 SECS)Drogue parachutes deployed (auto)

DROGUE DEPLOY PB - PUSH~

If Drogues FallELS - ~ ~Stablllze CM 5K MAIN DPLY PB - PUSHELS - AUTO

235K Cabln Pressure lncreaslng (Drogues + 50s)If not lncreaSlng by 17K CABIN PRESS REL vlv (RR) - DUMP

-46-

10K Maln parachutes deployedMAIN DEPLOY PB - PUSH (wlthln 1 sec)VHF ANT - RECYVHF AMA - SIMPLEXVHF BCN - ONCABIN PRESS REL v1v (2) - CLOSEDIRECT 02 vlv - OPENCM RCS LOGIC - on (up)CM PRPLNT - DUMP (burn audlb1e)Monltor CM ReS 1amp2 for He press decrease

NO BURN or PRESS DECREASE USE BOTH RHCs DO NOT FIRE PITCH JETS

CM PRPLNT-PURGE (to zero He press)CM RCS He DUMP PB - PUSH RHC (2) - 30 sees NO PITCH k

STRUT LOCKS (2) - UNLOCK

cb FLT amp PL BAT BUS ABampBAT C (3) - closecb FLT amp PLT MNA amp B (2) - opencb ECS RAD HTR OVLD (2) - opencb SPS PampY (4) - open

3K CABIN PRESS REL v1v (RH) - DUMP (after purgecompleted)

FLOOD Lts - POST LDGCM RCS PRPLNT (2) - OFFROT CONTR PWR DIRECT (2) - OFF

800 CAB PRESS RELF vlv - CLOSE (latch off)MN BUS TIE (2) - OFF

AFTER LANDINGcb MAIN REL PYRO (2) - closeMAIN RELEASE - on(up)

Go to POSTLANDING pg _47L-__

I

2

3

-47-

57 POSTLANDING

STABILIZATION VENTILATION COMMUNICATIONS

DIRECT 02 vlv - CLOSE

Stablllzation after landlngELS - AUTO (verlfy)cb MAIN REL PYRO (2) - close (venfy)MAIN RELEASE - on (up) (verlfy)S~CS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb BAT RLY BUS (2) - open

No contact w1th recovery forcesVHF AM AampB - off (ctr) ~

VHF AM Rev ONLY - A cb PL VENT - closecb FLOAT BAG (3) - closecb UPRIGHT SYS COMPRESS (2) - closeIf Stable II

FLOAT BAG(3)-FILL t1ll 2 m1n afterupr1ght then - OFF

VHF AM AlB amp BCN - OFF whlle lnvertedIf Stable I

After 10 M1n Coollng Per1odFLOAT BAG (3) - FILL 7 mln then OFF

Post Stab1lizat1on And Ventllat10nPL BCN LT - BCN LT LOWPL VENT vlv - UNLOCK (Pull)Remove PL VENT Exh CoverPL VENT - HIGH or LOWPL DYE MARKER - ON (swlmmer comm)Release foots traps and_restralntscb MNA BAT BUS A amp BAT C (2) - opencb MNB BAT BUS B amp BAT C (2) - opencb FLT amp PL BAT C - opencb PYRO A SEQ A - opencb PYRO B SEQ B - open

EACH HR - CHECK DC VOLTSgt 275 V If Notmiddot cb FLT amp PL-BAT BUS AampB (2) -open cb FLT amp PL BAT C (1) - open GO TO LOW POWER CHECKLIST

Unstow and lnstall PLV DISTRIB DUCTDeploy grappllng hook and 11ne 1f req

4

-48-

Post Landing Communlcatl0nsVHF ANT-RECY (venfy)VHF BCN - ON (verlfy)

If no contact ~lth recovery forcesperform VHF BEACON Check

MONITOR VHF BEACON transmlSSlonnth VHF AM B Rcvr andor Su)vlval

TransceiverkVHF Beacon not operatlng ~connect Surv~val TranscelVer to antcable behlnd VHF ant access pnland place radio ln BCN mode

LOW POHER CHECKLISTVHF BCN - OFFVHF AM (3) - RCVFLOOD Lts - OFFVHF AM AampB - off (ctr)VHF AM RCV ONLY - A (venfy)COUCH LIGHTS - OFFPOSTLANDING VENT SYS mlnlmlze useSURV RADIO - plug mto VHF BCN ANT cableconn behind VHF ant acess pnl amp turn radloon l-n BCN mode

EGRESS PROCEDURES

CMPCDRLMPCDR

CMPCDRCMP

LMPLl1PCDR

STABLE IDlsconnect Umblll-calsNeck darn onCenter couch - 270 0 positionArmrests stowedConnect raft to SIC l-f desl-red wlth

green lanyardConnect raft ~hl-te lanyards to SUltS amp

lnflate water wlngs when eXltl-ngHATCH PISTON PRESS vlv - PRESS (Outbd)Slde Hatch openedPL VENT - OFFcb Pnl 250 (all) - openEgress with 11feraftPut hardware klt outEgress

or CDIPALL

CMF

CDRCMF

CDR

LMF

CMFCMP LMFCMP

UlP

CDR

-49-

STABLE IIcb CREW STA AUDIO (3) - openD~sconnect umb~1~ca1s

Release foots trapsRelease restra~nt harnessCouch seat pans (3) - 170 0 pos1t10nArm rests stowedSurv1va1 k~ts removed from stowageConnect life raft ma~n1~ne to CDR or SicConnect f~rst wh~te lanyard from

11fe raft to suitConnect th~rd wh~te lanyard from

l~fe raft to SU1tConnect rucksacks together to yellow

lanyard on raft bagPRESSURE EQUALIZATION vlv - OPENRemove and stow fwd hatchEX1t feet f1rst w1th rucksacks when clear

of siC 1nflate water w1ngs and raftExit feet f1rst when clear of SiC

1nflate water w1ngsEX1t feet f1rst when clear of sic

1nflate water w1ngs

-50-

60 TLI ABORTS

TLI Aborts are conta~ned ~n the ESD s~nce the bulk of the funct~ons

concern entry preparat20ns and performance Th~s allows a s2nglesource of procedures for procedure rev2ew val~dat~on checkout andtra~n~ng These procedures ~ncorporate TLI preparat20ns as found ~n

reference 6 w~th the TLI Abort Procedures and these t~e 2nto normallunar return Entry Procedures found ~n sect20n 5 The guidel~nes

for th~s cont2ngency are spec2f2ed 2n reference 7

In2t2al preparat~ons for TLI pos2t20n the necessary system sW2tches2n add~t~on to perform~ng an EMS ~V test and a GDC al~gnment Afterthe DET ~s set for mon2tor2ng TB6 the CMP ~ncreases the 12ght levelof the LEB DSKY to max~mum and returns to the h2s couch Th2s 2Sdone so that the LEB DSKY can be observed ~n the event sunl~ght orreflect20ns wash out the ma2n d2splay panel DSKY dur2ng cr2t2calmaneuvers The crew then straps ~n and prepares for mon2tor~ng TB6as 2nd2cated by the SII SEP L~te The t2mes se~uence of procedures2S keyed on th~s d~splay and ~ncludes the DET START funct~on andSIVB IGNITION Dur2ng the burn the crew mon2tors the FDAIs foratt~tude excurs20ns and abnormal rates report~ng status checks toM~ss2on Control at d2screet t~mes dur2ng the maneuver Upon SIVBSHUTDOWN the eMP records the DSKY d~splayed performance parametersand awa2ts ground conf2rmat~on

The rat~onal for TLI aborts ~s descr~bed 2n reference 7 A summar2shyzat20n 2S extracted to prov2de background and gu2de12nes 2n th2sdocument The abort procedures cover aborts 10 m2nutes after conshyt2ngent SIVE shutdown and aborts 90 m2nutes after normal SIVE shutshydown t2me

The 10 m~nute TLI abort ~s des2gned to be used dur~ng TLI ~n theevent a spacecraft problem develops Wh2Ch can result 2n catastrophe2f ~mmed~ate act~on 2S not taken If the s~tuat20n perm~ts the crewshould always allow the SIVB to complete TLI at wh~ch t~me the groundand crew can perform a malfunct~on analys~s to determ~ne ~f an abort~s adv~sable If a fa~lure occurs that necess2tates the shutdown ofthe SIVB and the ~u~ck return of the crew to earth th~s abort ~s

des~gned to be as ~nsens~t~ve to execut~on errors as poss~ble andst21l be targeted to m2dcorr2dor The burn att~tude w~th the f~ed

hor~zon reference ~s a constant value for any shutdown t~me Theburn durat~on 2S a funct20n of shutdown t2me and 2S ava21able fromcrew charts S~nce the pr~mary purpose of th~s abort ~s to returnto earth as qU2ckly as poss2ble there are no restr2ct20ns as toland~ng locat~on However ~f the t~me to EI is greater than abouttwo hours a midcourse correct20n should be ant~c~pated

The 90 m2nute TLI abort 2S to be used 2f a cr2t2cal subsystem malshyfunct~on ~s determ2ned and the dec2s~on to abort ~s made after the

-51-

TLI cutoff and before TLI cutoff plus approxlmately 80 m1nutesTh1S allows suff1c1ent separatlon and procedural t1me to set upfor the SPS deorb1t burn performed at about TLI + 90 Note thatgenerally the deorb1t burns w1ll be performed a fe11 m1nutes beforeTLI + 90 accord1ng to crew charts shown In reference 8 The no-comm except10n requ1res that 90 m1nutes be the 1nput t1me of 19n1shytlon for P-37 (onboard return-to-earth abort program) so that onshyboard calculatlons can correspond w1th ground calculat10ns to computethe CM land1ng p01nt Th1S TLI abort lS des1gned so that returnfl1ght t1me does not exceed 18 hours and abort ~V does not exceed7000 fps ThlS abort can be performed uSlng chart ~Vs and attltudesand the earths hor1zon serves as a suff1c1ent reference The maneushyver lS targeted to ach1eve the mldcorr1dor entry target Ilne andtlmed to result 1n a deslgnated recovery area

It 1S ObV10US for abort deC1S1ons early 1n the TLI + 90 m1nute t1meshyframe that a GampN SPS burn should be performed In order to keep theTLI abort procedures cons1stent and w1th emphasls on slmpl1c1ty theprocedures here reflect a SCS SPS abort burn to cover the full abortdec1s1on t1meframe

A m1dcourse correct1on for corr1dor control after a TLI abort may bedeS1red 1f the SPS burn d1d not meet expectat1ons The TLIabortprocedures 1n th1S sect10n adapt to the normal lunar return tlmel1neand procedures pr10r to the f1nal MCC

-52-

61 TLI PREPARATION PROCEDURES

GET = 150

CRO AOS(___)

CRO LOS( )(22142)

5100

Don Helmets amp Gloves

XLUNAR - INJECT (verify)EDS PWR - on (venfy)EMS FUNC - OFF (verlfy)EMS MODE - STBYEMS FUNC - IW SETVHF RNGEMS MODE - NORMALSet ~V indo to +15868 fpsEMS FUMC - ~V Test

SPS THRUST Lt - onoff (10 sec)~V lnd stops at -01 to -415

EMS MODE - STBYEMS FUMC - ~V SETVHF RNGSet ~VC

EMS FUNC---~~V=----

GDC ALIGNFDAI Select - liZcb SECS LOGIC (Z) - close (verify)cb SECS ARM (Z) - closeSECS LOGIC (Z) - on (up)MSFN Conflrm GO for PYRO ARM (If pass)SECS PYRO ARM (Z) - on (up)TRANS CONTROL PWR - ONROT CONTR PWR NORMAL (Z) - ACDC(verlfy)ROT CONTR PWR DIRECT (Z) - MNAMNBLV INnGPI - SIISIVB (venfy)LV GUID - IU (venfy)cb DIRECT ULLAGE (Z) - closedSet EVENT TIMER to 5100Begin MONITOR For TB6

CMP to Couch

TB 6 - SII SEP Lt on (TIG-9 mln 38 sec)KEY V83E

SET ORDEALFDAI Z ORB RATE at 180 0 0SII SEP Lt out (38 sec later)Start DET COUNTING UPSC CaNT - SCS (verify)MONITOR LV TANK PRESS

~P lt 36 psid (OXID gt FUEL)~P lt Z6 psid (FUEL gt OXID)

EMERGENCY CSMLV SEP UP TLM CM - BLOCK (verify)UP TLM IU - BLOCK (venfy)

-53-

+45degPY))0middot sec PY

lOK nmltHAlt25K nm

Two phas~ng mnvrs two SPS mnvrs to circular~ze at 150 nmearth orb~t

CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ssion 4K nmltHAltlOK nm CSM amp1M - Two phasing mnvrs two SPS mnvrs to circularize at 150 nm earth orb~t CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ss~on

CSM amp 1M - Two phas~ng mnvrs APS burn todepletion th~rd phasing mnvrSPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn tosem~sync orb~t

25K nmltHAlt40K nm CSM amp 1M - Two phasmg mnvrs APS burn to depletion third phas~ng mnvr SPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn to sem~sync orbit HA)40K nm DPS ava~l - DPS LOll circularize with SPS

DPS not ava~l - Lunar flyby or CSM only to lunar orbit (if reqd gtV lt4000 fps)

V37E 47E (check b~as) Record -=--rshy(Limit 98 fpsmm)

( 1fps)tVXYZN62EVIHDOTHPAD (fpsfpslnm)MONITOR VI ( ) at ECO

SCS TVC SERVO PWR 1 - ACIMNA2 - OFF

TAPE RCDR - CMD RESETHBREMS MODE - NORMAL

SIr SEP Lt - ONTLI Inhib~t S~gnals w~11 not be honored after 5942

SIVB ULLAGE BeginsSII SEP Lt - off (TIG - 18 sec)SIVB FUEL LEADSIVB ULLAGE d~scont~nues

LV ENG I Lt - onSIVB IGNITION ( GETI)LV ENG I Lt - off - -shyMONITOR THRUST amp ATTITUDEMONITOR LV TANK PRESSSIVE ECO (Lt on) (BEGIN TB7)

EMER SIVE CUTOFF AT 6 SEC PAST BURN TIME IF VI ATTAINEDTHC CCW ampNEUTRAL IN 1 SEC or SIISIVB sW - LV STAGEPremature Shutdown HAlt4K nm CSM amp 1M -

5700

58205836

F 16 835800

F 16 62

5838594259525955595900000002SUNRISE(___)

HAW AOS(__=_) KEY VERB (freeze d~splay)

SIVB ATT HOLD 20 sec amp BEGIN VENTINGSIVB NNVR TO ORB RT (HDS DN) (3middot sec)

Record VI -c---HDOT _

HPAD _

KEY RLSEF 16 62

F 16 83

HAW LOS(__=-)

KEYmiddotRLSE~VXYZ (lfps)

Record ~VX---_

~vy

WZ--

AVC---_

TAPE RCDR - off (ctr)EMS MODE - STBYEMS FUNC - OFFSECS PYRO ARM (2) - SAFE

PRO

BURN STATUS REPORT

____--~TIG

BT------VGX____-R

-----P----_Y

REMARKS

_____VI

______--HDOT______--H______---AVC______---FUEL_______OXID

_______UNBAL

F 3708=00 OOEGOS AOS CMP TO LEB

(-=-=-)

0000

0003

0005

0014

0100

-55-

62 TLI 10 MIN ABORTSECS LOGIC (2) - on (up)SECS PYRO ARM (2) - ARM

TRANS CONTR - CGH (4 sec) amp +XDET RESET (verlfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS GMD-ON

TRANS GONTR - neutral then +X for10 sec

SIVBGPI s~ - GPIExcesslve rates 6V THRUST A - NORMAL SPS THRUST - DIRECT When rates damped 6V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

TRANS CONTR +X - OFFV37E OOE

PITGH UP to LOGAL VERT (+X axlSto~ard the earth)

RATE - LOWBMAG MODE (3) - ATTIRATE 2EDS PHR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SEGS ARM (2) - opencb EDS (3) - open

TRANS CONTR -X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (180deg)P (199deg)Y (0deg)

RETRO UPDATEGETI _

JV _VG

Jtb ---GET 400K _

05G _GET DROGUE _

ENTRY P _R _

Y_--

0945

-56-

ALIGN HORIZ ON RET +1 MKGMBL CHECK (T11lle Pentattlng)MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conflnn)cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FUMC - JV SETVHF RNGSET JV from chartE~S FUMC - JVEMS fODE - NOIDlAL

lV THRUST A - NORMALV37E 47E (THRUST fONITOR)

F 16 83 lVXYZ (1 fps)

0950

1000

NOTE For aborts durlng 1st mln of TLIKEY V82E F 16 44 (HaHpTff)Burn untll Hp lt 19NM

TRANS CONTR +X

THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN JV reqdJV THRUST (2) - OFFReport cutoff

cb SPS P2 Y2- closeGfBL MTRS (4) - OFF (LMP Confinn)TRANS CONT PWR - OFFTVC SERVO PWR (2) - OFFMN BUS TIE (2) - OFFcb SPS P1amp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREIf est time to EIltOl5500 omlt fCC andenter the SUPERCIRC CKLIST as early as pos-slb1e Pg ~2~3~ __If est time to EI)Ol5500 anticlpate afCC Enter the ENTRY PREP CKLIST at step 9pg 18

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

-2tl C

l I W gt- ~-4

z laquo I I- 0 -6

l- I J u gt- ~-8

z w w -10

~_ONSANT

9O

VER

SHO

OT

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LIF

TV

EC

TOR

OR

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TATI

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LIN

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SH

ALL

OW

TAR

GE

TLI

NE

STE

EP

TAR

GE

TLI

NE 12

gU

ND

ERSH

OO

TBO

UN

DAR

Y

RE

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TRY

CO

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IDO

R

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26

28

30

32

34

RE

EN

TRY

VE

LOC

ITY

VE

1-F

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3B

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73

8X

03

-i- rtREQUIRED PITCH GIMBAL ANG LETO OBTAIN HOR-IZON AT 317

DEGREES IN wiiiiDOW

260

z~I- ~ i5 24000

1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

-I

-1-

NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

I LU HD~-

LUHD

lt0 120UJ0

~

80 HOLD PRESENT TRIMgt LU HD013

~Y~HOIgtlt

TOP OF WINDOWa 40to

31 7 SCRIBEaaI

80 TTOM OF WINDOWi= 0

0--ltoa

-40t-z

~~~Uw w u lt0 -80

HOLO PRESENT TRIlJCl

LOHU0 lt0

J gt -120 HOLD 059 TRIMlt0 z

LDHUlt0 FIELD OF VI S10 NLDHU LIFT-DOWNHEADS -UPLUHD LIFT-UP HEADS-DOWN

~~H~-160 q - P63 LIMITI- NOrE-VALIO ONLY FO~t~--

LUNAR RETURN VELOCITY

plusmnl8020 244middot 8 12 16

TIME TO 400K FT ALTITUDE-MIN

4

P37

LONG

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TOOB

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1350

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344

348

352

356

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120

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Cll-

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120

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320

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-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 27: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

6 35middot0Om(-25middot 00)

-24-

SEPARATION CK LISTTVC SERVO PWR 1 - AClMNAcb ELS (2) - close (ver1fy)PRIM GLY TO RAn - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY vlv - OFFCAB PRESS REL vlv (2) - NORMGMBL MTRS (4) - STARTABORT SYS PRPLNT - RCS CMD (venfy)SM RCS PRIM PRPLNT (4) - ONVHF 11M (AampB) - OFFHI GAIN ANT PWR - OFFFC PUMPS (3) - OFFVer1fy s1ugle SU1t compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - 10101cb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2) - opencb HTRS OVLD (2) - openPOT H20 RTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANSEC COOL EVAP - RESETSEC COOL PUMP - off (etr)

MtiVR TO CMSM SEP P R ATTSC CONT - SCSCMC MODE - FREEMNVR TO PAD ATTR (0deg)PY----W)

-25-

SUPERCIRCULAR ENTRY (Cont~nued)

1

4100m(-1900)

P61 - ENTRY PREP

V37E 61E

k 05 09 01427 - ROLL REVERSED 05 09 01426 - IMU UNSAT ~

2 F 06 61 IMPACT LAT LONG HDS UPDN (+-)PRO (010

fps +00001)

3 F 06 60 GMAXVPREDGAMMA EIRecord

GMAXV400K----

GAMMA EI _PRO

(01deg fpsOldeg)

4 F 06 63 RTOGO (lnm) PAD _VIO (fps) PAD _TFE(m~n-sec)

Compare w~th ~M~SFN==C~f~o-r~P~GNS GONO GOIf NO COMM Set RTOGO amp VIO In EMS

amp lnltla11ze(ACCEPT) PRO(RECALC) V32E To 4

5 F 50 25

4300m

(-1700)

45 oOm(-1500)

500Om(-1000)

6 F 06 61

-26-

P62 - CMSM SEP amp PRE-ENTRY MNVRCAUTION Call No EXT Verbs In P62

00041 REQUEST CMSM SEPSC CONT - SCSFREE

COMPARE PITCH ATT WITH PAD DATA ---0=-

(W~thLU 5deg)YAW - 45deg OUT-OF-PLANE (LEFT)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTIRATE 2MN BUS TIE (2) - ON (ver~fy)

PRIM GLY TO RAD - BYPASS (verlfy)CM RCS LOGIC - ON (venfy)SECS LOGIC (2) - on (up)SECS PYRO ARM - ARMCMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 ps~a

CM RCS LOGIC - OFFSECS PYRO ARM (2) - SAFEMonltor VMAB

If lt25 vdc go to EMERGPOWERDOWN pg E6-l

AUTO RCS SEL AC ROLL (4) - OFFAUTO RCS SEL CM 2(6)-OFFAUTO RCS SEL CM 1(6)-MNAYAW back to 0degPITCH TO HORIZ TRACK ATT

ROLL - 0deg (LIFT UP)PITCH - 400K Horiz Mark (317deg)YAW - 0deg

ATT DB - MAXMAN ATT PITCH - ACCEL CMDEMS DATA - Ver~fy

EMS FliNC - ENTRY (ver~fy)

EMS MODE - NORMALcb SPS PampY (4) - openMAINT HORIZ TRK

PRO (Act ENTRY DAP)

IMPACT LATLONGHDSDN (01deg01deg-00001)PRO

7 POSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axis beyond 45deg of Vel vector)

8 06 64

58middot00m(-0200)

9

05G tlme(+0 )

(--=---)

06 68

-27-

P63 - ENTRY INIT

GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PIJR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRmDHORIZ CKPltch error needle goes toward

zero approachlng OSG tlmeMAN ATT (PITCH) - RATE CMD

If CMC lS GOBMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS I

FLY BETA If CMC NO GO ilt

1 SC CaNT - SCS I

FLY EMS k

p64 - ENTRY POST 05G

RTOGO AT 05G AGREES HITH EMS-venfyHORIZ CK05G Lt - ON (EMS START)

No EMS START wlthln 3 sec ~ EMS MODE - BACKUP VHF RNG c

05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds Llft DN

NNVR Llft DNEMS GONO GO

G-V Plot wlthln IlmltsRng ctr dwn 60plusmn7 durlng 10 sec

perlodMonltor G-meter for

convergence wlth pad data (Do)(Vlt27K fps) Go to 13

-28-

P65 - ENTRY - UP CONT (Vgt27K fps)

10 F 16 69 BETA (01middot) _DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT lt~ SC CONT - SCS FLY EMS

PRO

11 06 68 BETAVIHDOT (OIdegfpsfps)(VltV1+500 fps amp RnOT Neg) Go To 13

P66 - ENTRY - BALLISTIC (D(DL)

12 06 22 DESIRED GMBL ANGLES RPYMoultor horlz +12middot of 317middot mark

P67 - ENTRY - FINAL PHASE (02G)

13 06 66 BETACRSRNG ERRDNRNG ERR(010 1um 1um)

KEY VERBRecord DNRNG ERR _KEY RLSEMoultor l~ft vector ou RSI amp FDAI

16 67 RTOGOLATLONG (Vrel=1000fps)(lumOldegOldeg)

SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOWNMonitor a1t~meter

Go To EARTHLANDING pg ---4L5 _

-29-

53 GampN HYBRID DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL tV1 V37E 30E

2 F 06 33 GETI(ACCEPT) PRO (hrm~n Olsec)(REJECT) LOAD DESIRED GETI

3 F 06 81 tVXYZ (LV) (lfps)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

4 F 06 42 HAHPtV (lnm lfps)Record tV

(ACCEPT) PRO(REJECT) Reselect P30 or P27 Load new paramo

5 F 16 45 MTFIMGA (marksm~n-secOlO)

MGA -00002 ~f k

k lMU not al~gned

SET DETPRO

6

7

8

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (Pull)PLSS 02 vlv - FILL02 8M SUPPLY vlv - OFFCAB PRESS REL vlv (2) - NORMcb ELS (2) - closecb SECS ARM (2) - closecb SECS LOGIC (2) - close (ver~fy)

AUTO RCS SEL CM (12) - MNA or ~ffiB

(hftoff conhg)ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM (AampB) - OFF

CMP to Couch

9

10

11

-30-

MNVR TO PAD BURN ATTLOAD DAPBMAG MODE (3) - RATE 2SC CONT - CMCAUTOATT DB - MINMAN ATT (3) - RATE CMD

v62E

v49E

12 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLES

PRO

13 F 50 18 REQ MNVR TO FDAI RPY ANGLES (01deg)(AUTO) PRO(MAN) SC CONT - SCS

BMAG MODE (3) - RATE 2MNVR To 15

14 06 18 AUTO MNVR TO FDAI RPY ANGLES (01deg)

15 F 50 18 REQ TRIM TO FDAI RPY ANGLES (01deg)(TRIM) Go to 13(ByPASS) ENTR

16

17

CHECK BORESIGHT amp SKT STARSOPT MODE - CMCOPT ZERO - OFF

v41 N91E

18 F 21 92 SHAFTTRUN (01deg 001deg)Load SXTS angles

19 41 OPTICS DRIVECheck SKT STAR

OPT ZERO - ZEROCheck BORESIGHT STAR (~f ava~l)

20 V25 N17E (01deg)Load Pad Data GMBL Angles

for CM BURN ATTATT SETtw - SET

to PAD DATA GMBL ANGLESfor CM BURN ATT

21

22

-31-

PHR REDUCTIONHGA PHR - OFFFC PUMPS (3) - OFFVerify s~ngle su~t compr oper loads

balancedFC 2 MN AampB - OFFS BD PiR AMP - LOWcb ECS RAD CONTHTR (2) - opencb HASTE H20URINE DUMP HTRS(2)- opencb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANMN BUS TIE (2) - ONTVC SERVO PHR 1 - AC1MNAGMBL MTR (4) - START

p41 - RCS THRUSTINGV37E 41E

23 F 50 18 REQ MNVR TO LCL HORIZ (HDS ON)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CMCAUTOPRO To 24

(gtfANDAP) BMAG MODE (3) - RATE 2SC CONT - CMCHOLD

V62EMNVR To 25

24 06 18 AUTO MNVR TO FDAI RPY

25 F 50 18 REQ TRIM TO LCL HORIZ (01deg)ALIGN SC ROLL

(AUTO TRIM) PRO To 24(BYPASS) ATT DB - MIN

RATE - LOHMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTlRATE 2

ENTR

550Om26 06 85

59middot2527

-32-

VGXYZ (1fps)RECHECK BORESIGHT STARTRANS CONIR PWR - on (up)EMS MODE - STBY (ver~fy)

EMS FliNC - bV SETVHF RNGSET (IV for SM BURN _EMS FliNC - bVS BD ANT - OMNI CSECS LOGIC (2) - ONMSFN conhrm Go for PYRO ARMSECS PYRO ARM (2) - ARMCM RCS LOGIC - ON (ver~fy)

DSKY BLANKS

593028 16 85 VG XYZ (AVE G ON) (lfps)

RHCs amp THC - ARMEDLIMIT CYCLE - OFFTAPE RCDR - CMD RESETHBREMS MODE - NORMAL

000029 F 16 85 REQ NULL VG XYZ (lfps)

BURN EMS bV CTR TO ZERORESET DET amp COUNT UP

If SM ONLY burn go to step 32THC - LOCKEDSC CaNT - SCSFREERATE - HIGHPRIM GLY To RAD - BYPASS (ver~fy)

MN BUS TIE (2) - ON (ver~fy)

CMSM SEP (2) - on (up)CSMLM FNL SEP (2) - on (up) (verify)CampW MODE - CMRCS TRNFR - CMCM RCS LOGIC - OFF

Momtor VM ABIf lt25 vdc go to EMERGPOWER DOWN Pg E6-l

V63E

If CMC NO GO FDAI SOURCE - ATT FDAI SEL - 1 or 2 ATT SET - GDC

SET

-33-

~Uili ATT PITCH - ACCEL CMDFDAI SCALE - 55MNVR TO CM BURN ATT (NULL ERR NEEDLES)

R 0degPY --00--

30

31

CM RCS BURNRHC III-ContJnuous PJtch DownRHC HZ-Module PJtch to null needlesBURN VGZ TO ZERO

If only 1 RHC Pulse + P=5deg from retro att MaJnta~n rates lt3degsec

BURN COMPLETION ATllV CTR= or DET= _

V8ZE

32 F 16 44 HAHPTFF (1nmffiJn-sec)Check HP-

If gt Pad data contJnue burnuntJ1 lt Pad

PRO

33 F 16 85 VGXYZ (Ups)Read VG resJduals to MSFN

(HYBRID) PRO to 34(SM ONLY BURN)

PROF 37 ODE

EI-1500 V37E 47EF 16 83 twx Y Z (Ups)

SC CONT - SCSFREEMAN ATT (PITCH) - RATE CMDRATE - HIGHPRIM GLY To RAD - BYPASS (verJfy)MN BUS TIE (2) - ON (verJfy)CMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verJfy)Campl MODE - CMRCS TRNFR - CMCM ReS LOGIC - OFFSECS PYRO ~I (2) - SAFE

-34-

PROMonitor VMAB

If lt25 vdc go to EMERGPOWER DOWN

34 F 37 OOEPCM BIT RATE - LOWATT DB - MAXEMS MODE - STBYEMS FUNC - OFF

Go To EARTH ORBIT ENTRY pg _--40-__

-36-

8 SPS THRUSTING PREPCYCLE CRYO FANSSPS GAGING - ACI (ver~fy)

PUG MODE - NORM (venfy)BMAG MODE (3) - RATE 2tv CG - CSMCMC MODE - FREEAUTO RCS SEL (16) - MNA or HNB

(hftoff conbg)SC CONT - CMCAUTO

9 MNVR TO PAD BURN ATTV62E

10 V49E

11 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLESPRO

12 F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) PRO(HAN) SC CONT - ses

MNVR to 14

06 18 AUTO MNVR TO FDAI RPY ANGLES13

14 F 50 18 REO TRIH TO FDAI RPY ANGLES(TRIM) Go to 12(BYPASS) ENTR

15 BORESIGHT STAR CHECK

16 V37E 40EOPT PWR - OFF

17 F 50 18 REQUEST MNVR TO FDAI RPY ANGLES (01deg)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CHCAUTOPRO to 18

(MANDAP) BMAG HODE (3) - RATE 2SC CONT - CMCHOLDMNVR to 19

(HANseS) se eONT - sesMNVR to 19

-35-

54 NORMAL DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL ~V

1 V37E 30E

2 F 06 33 GETI (hrm~nOlsec)

(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

3 F 06 81 ~VXYZ (LV)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

( lfps)

4 F 06 42 HAHP~V (1nmlfps)Record W

(ACCEPT) PRO -----(REJECT) Rese1ect P30 or P27 Load new pa~am

5 F 16 45 MTFIMGA (marksmln-secOldeg)MGA -00002 If ~ lMU not a1~gned

SET DETPRO

6

7

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY v1v - OFFCAB PRESS REL v1v (2) - NORMcb ELS (2) - close (verify)cb SECS ARM (2) - close (ver~fy)

cb SECS LOGIC (2) - close (verlfy)AUTO RCS SEL CM (12) - ~mA or MNB

(l~ftoff conf~g)

ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM AampB - off (ctr)

18

-37-

06 18 AUTO MNVR TO FDAI RPY ANGLES (01 0)

19 l 50 18 REOUEST TRIM MNVR TOALIGN SIC ROLLGDC ALIGN

FDAI RPY ANGLES(010

)

+54-00m(-06-00)

TIG-5mJn

5500m(-0500)

TVC CHECK amp PREPcb STAB CONT SYS (all) - closecb SPS (12) - closeATT DB - MINRATE - LOl~

LIMIT CYCLE - ONMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE 2ROT CONTR PWR DIRECT (2) - OFFSCS TVC (2) - RATE CMD

If SCS SCS TVC (2) - AUTO SC CONT - SCS ~

TVC GMBL DRIVE PampY - AUTOMN BUS TIE (2) - ONTVC SERVO PWR 1 - AC1MNA

2 - AC2MNBTRANS CONTR PWR - ONROT CONTR PWR NORMAL 2 - ACRHC 2 - ARMED

HORIZ CHK - HorJz on 12deg wJndmlmark (LJffiJt +3 0 PNGCS GONO GO)

If NO GO set tw 180 0 180deg0 0

Track horJz wJth 24deg wJndow markAt TIG-2 mJn Ahgn GDC

PRIMARY TVC CHECKGMBL MOT P1-Y1 -STARTON(LMP confJrm)

If SCS verJfy Thumbwheel TrJmTHC - CWVenfy NO MTVC

SEC TVC CHECKGHBL MOT P2-Y2 -STARTON(LMP confJrm)SET GPI TRIHVenfy MTVCTHC NEUTRALGPI returns to 00 (CMC) or trJm (SCS)ROT CONT Pl~ NORM 2 - ACDC

(TRIM) Go to step 17(BYPASS) BMAG MODE(3) - ATTIRATE2 (ver1fy)

ENTR

-38-

20 F SO 25 00204 GMBL TEST OPTION(ACCEPT) SC CONT - GMC (ver~fy)

PROMonitor GPI Response

0020-2000020-200Tr~m

TEST FAIL SC CONT - SCS SCS TVC (2) - AUTO

(REJECT) ENTR

21 06 40 TFIVG~VM (m~n-sec1fps)

PROG ALM - TIG s1~pped

V5N9E 01703

KEY RLSE To 21 ROT CONTR PWR DIRECT (2) - MNABSPS He v1vs (2) - AUTO (ver~fy)

LIMIT CYCLE - OFFFDAI SCALE - SOIScb SPS P2Y2 - open (for cr~t burn)

5800(-02 00)

5925(-0035)

59middot 30(-0030)

06 40

59XX(-OOXX)

AV THRUST A(B) - NORMALTHC - ARMEDRlIC (2) - ARMEDTAPE RCDR - GID RESETHBR

DSKY BLANKS

(AVE G ON)EMS MODE - NORMAL

TFIVG~VM (m~n-seclfps)

CHECK PIPA BIAS lt2fps for 5 sec

ULLAGE AS REQ

IF NO ULLAGE DIR ULLAGE PB - PUSH~

CONTROL ATT WRlIC MONITOR AVM (R3) COUNTING UP

5955(-0005)

F 99 40 ENG ON ENABLE REQUEST(AUTO IGN) PRO AT TFI gt0 sec(BYPASS IGN) ENTR to 24

22 0000 IGN

-39-

If SCS - THRUST ON PB - PUSH

06 40 TFCVG~VM (m~n-seclfpslfps)

~F 97 40 SPS Thrust fall ~

~(RESTART) PRO To IGN (RECYCLE) ENTR To TIG-05 sec

SPS THRUST LITE - ONMONITOR THRUSTING

Pc 95-105 pSlaEMS COUNTING DOWNSPS IN3 v1vs (4) - OPENSPS He v1vs tb (2) - graySPS FUELOXID PRESS - 175-195 pSlaPUGS - BALANCED

PROG ALARM V5N9E 01407 VG INCTHC - CW FLY MTVC

ECOEMER SPS CUTOFF J

AV THRUST (2) - OFF

23 F 16 40 TFC(STATIC)VG~VM (mln-seclfps)~V THRUST AB - OFF

SPS IN3 v1vs (4) - CLOSEDSPS He tb (2) - bp

cb SPS P2Y2 - closed (verlfy)TVC SERVO PHR - AC1MNA (venfy)TVC SERVO PWR 2 - OFF

PRO

24 F 16 85 VG XYZ(CM) CUps)NULL RESIDUALSRECORD ~V CTR amp RESIDUALS I1VCEMS FUNC - OFF VGXEMS MODE - STBY VGYBMAG MODE (3) - RATE 2ATT DB - MAX VGZTRANS CONT PHR - OFF

PRO

25 F 37 V82E

26 F 16 44 HAHPTFF (lnmm~n-sec)

R3-59B59 HP gt494 nmPRO

27 F 37 OOE

-40-

55 EARTH ORBIT ENTRY

1 Venfy CMSMR __

P_shyY_-

SEP ATT(180deg)

(0deg )

2

3

4

EMS INITIALIZATIONEMS FUNC - RNG SETSET RNG TO PAD DATA RNGEMS FUNC - VA SETSlew scroll to pad data VIOEMS FUNC - ENTRY

RSI ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on(up)GDC ALIGN PB - PUSH amp HOLDYAW tw - Pos1tion RSI thru 45deg amp

back to LIFl UPGDC ALIGN PB - RELEASEEMS ROLL - OFFAl1gn GDC to lMU

PWR REDUCT (Norm Deorb Only)HGA PWR - OFFFC PUMPS (3) - OFFVer1fy s1ngle suit compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - Lowcb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2)-openlOb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MAN

-41-

P61 - ENTRY PREP

5 V37E 61E05 09 01427 - ROLL REVERSED05 09 01426 - IMU UNSAT

6 F 06 61 IMPACT LAT LONG liDS UPDN (+-)(01 0

010

+00001)

PRO

PAD VALUESLATLON==G------liDS UP DN _

7 F 06 60 GMAXV400KGAMMA EIRecord

GMAXV400K----GAMMA EI _

PRO

8 F 06 63 RTOGO (1nm) PAD _VIa (fps) PADTFE (mln-sec) ----Compare wlth MSFN for PGNS GONO GONO COMM SET RTOGO amp VIO IN EMS amp

INITIALIZE(ACCEPT) PRO(RECALC) V32E to 8

-42-

P62 - CMSM SEP amp PRE-ENTRY MNVR

9 F 50 25 00041 REQUEST CMSM SEPSC CONT - SCSFREEYAW - 45deg out-of-plane (left for RCS

nght for SPS)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE2PRIM GLY to RAD - BYPASS (verlfy)SECS LOGIC (2) - on (up)MSFN conflrm GO for PYRO ARMSECS PYRO ARM - ARMMN BUS TIE (2) - ON (verlfy)CMSM SEF (2) - ONCSMLM FNl SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 pSlaCM RCS LOGIC - OFFSECS PYRO ARM - SAFEMonltor VMAB

If lt25vdc go to EMERG POWERDOWN Pg E6-1AUTO RCS SEL AlC ROLL (4) - OFFAUTO RCS SEL CM 2(6) - OFFAUTO RCS SEL CM 1(6) - MNA or MNBYAW back to 00

PITCH TO ENTRY ATTROLL 0deg (LIFT UP)PITCH - HORIZ on 317deg MARK (400K)YAW 00

ATT DB - MAXMAN ATT (PITCH) - ACCEL CMDEMS DATA - VerifyEMS FUNC - ENTRY (verlfy)EMS MODE - NORMALMAINTAIN HORIZ TRK

PRO (Act ENTRY DAP)

10 F 06 61 IMPACT LAT LONG HDSDN(010 010 -00001)

PRO

11 FOSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axlS beyond 45deg of Vel vector)

-43-

P63 - ENTRY INIT

12 06 64 GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PWR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRHORIZ CKP~tch error needle goes toward

zero approach~ng 05G t~me

MAN ATT (PITCH) - RATE CMDIf CMC ~s GO

BMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS FLY BETA If CMC NO GO ~

SC CONT - SCS~

FLY EMS RCS Deorh Roll HDS UPTRACK HORIZ w~th 29deg w~ndow mk

P64 - ENTRY POST 05G

13

05G t=elt+0___)

06 68

RTOGO AT 05G AGREES WITH EMS - venfyHORIZ CK05E Lt - on (EMS start)

No EMS start w~th~n 3 secsEMS MODE - BACKUP VHF RNG 05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds L~ft DN

NNVR L~ft DNEMS GONO GO

G-V Plot w~th~n llm~ts

Rng ctr dwn 60 + 7 durlng 10 sec per~od

Mon~tor G-meter forconvergence wlth pad data (Do)

(Vlt27K fps) Go To 17

-44-

P65 - ENTRY - UP CONT (Vgt27K fps)

14 F 16 69 BETA (01deg)DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT~

SC CONT - SCS FLY EMS

PRO

15 06 68 BElA VI HOOT (01deg fpsfps)(VltVL +500 fps amp RDOT Neg) Go To 17

p66 - ENTRY - BALLISTIC (DltDL)

16 06 22 DESIRED GMBL ANGLES RPY (01deg)Mon~tor hor~z +12deg of 317deg mark

P67 - ENTRY - FINAL PHASE (02G)

17 0666 BETACRSRNG ERRDNRNG ERR (Oldeglnmlnm)KEY VERBRecord DNRNG ERR _KEY RLSEL~m~t +100nm from PAD DRE

Mon~tor l~ft vector on RSI amp FDAIF 16 67 RTOGOLATLONG (Vre1=1000fps)

(lnm 010 01deg)SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOlfflMon~tor altimeter

Go To EARTHLANDING pg _I4L5__

-45-

56 EARTHLANDING

90K STEAM PRESS - PEGGED50K CABIN PRESS REL vIv (2) - BOOSTENTRY

SECS PYRO ARM (2) - ARM

40K(90K + 63s)

CM UNSTABLE RCS CMD - OFF ~ 40K APEX COVER JETT PG-PUSH DROGUE DEPLOY PG - PUSH (2 secafter apex cover Jett)

30K ELS LOGIC - ON (up)ELS - AUTO

24K RCS hsable (auto)(90K+92s) RCS CMD - OFF

Apex cover Jett (auto)APEX COVER JETT PB - PUSH

(WAIT 2 SECS)Drogue parachutes deployed (auto)

DROGUE DEPLOY PB - PUSH~

If Drogues FallELS - ~ ~Stablllze CM 5K MAIN DPLY PB - PUSHELS - AUTO

235K Cabln Pressure lncreaslng (Drogues + 50s)If not lncreaSlng by 17K CABIN PRESS REL vlv (RR) - DUMP

-46-

10K Maln parachutes deployedMAIN DEPLOY PB - PUSH (wlthln 1 sec)VHF ANT - RECYVHF AMA - SIMPLEXVHF BCN - ONCABIN PRESS REL v1v (2) - CLOSEDIRECT 02 vlv - OPENCM RCS LOGIC - on (up)CM PRPLNT - DUMP (burn audlb1e)Monltor CM ReS 1amp2 for He press decrease

NO BURN or PRESS DECREASE USE BOTH RHCs DO NOT FIRE PITCH JETS

CM PRPLNT-PURGE (to zero He press)CM RCS He DUMP PB - PUSH RHC (2) - 30 sees NO PITCH k

STRUT LOCKS (2) - UNLOCK

cb FLT amp PL BAT BUS ABampBAT C (3) - closecb FLT amp PLT MNA amp B (2) - opencb ECS RAD HTR OVLD (2) - opencb SPS PampY (4) - open

3K CABIN PRESS REL v1v (RH) - DUMP (after purgecompleted)

FLOOD Lts - POST LDGCM RCS PRPLNT (2) - OFFROT CONTR PWR DIRECT (2) - OFF

800 CAB PRESS RELF vlv - CLOSE (latch off)MN BUS TIE (2) - OFF

AFTER LANDINGcb MAIN REL PYRO (2) - closeMAIN RELEASE - on(up)

Go to POSTLANDING pg _47L-__

I

2

3

-47-

57 POSTLANDING

STABILIZATION VENTILATION COMMUNICATIONS

DIRECT 02 vlv - CLOSE

Stablllzation after landlngELS - AUTO (verlfy)cb MAIN REL PYRO (2) - close (venfy)MAIN RELEASE - on (up) (verlfy)S~CS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb BAT RLY BUS (2) - open

No contact w1th recovery forcesVHF AM AampB - off (ctr) ~

VHF AM Rev ONLY - A cb PL VENT - closecb FLOAT BAG (3) - closecb UPRIGHT SYS COMPRESS (2) - closeIf Stable II

FLOAT BAG(3)-FILL t1ll 2 m1n afterupr1ght then - OFF

VHF AM AlB amp BCN - OFF whlle lnvertedIf Stable I

After 10 M1n Coollng Per1odFLOAT BAG (3) - FILL 7 mln then OFF

Post Stab1lizat1on And Ventllat10nPL BCN LT - BCN LT LOWPL VENT vlv - UNLOCK (Pull)Remove PL VENT Exh CoverPL VENT - HIGH or LOWPL DYE MARKER - ON (swlmmer comm)Release foots traps and_restralntscb MNA BAT BUS A amp BAT C (2) - opencb MNB BAT BUS B amp BAT C (2) - opencb FLT amp PL BAT C - opencb PYRO A SEQ A - opencb PYRO B SEQ B - open

EACH HR - CHECK DC VOLTSgt 275 V If Notmiddot cb FLT amp PL-BAT BUS AampB (2) -open cb FLT amp PL BAT C (1) - open GO TO LOW POWER CHECKLIST

Unstow and lnstall PLV DISTRIB DUCTDeploy grappllng hook and 11ne 1f req

4

-48-

Post Landing Communlcatl0nsVHF ANT-RECY (venfy)VHF BCN - ON (verlfy)

If no contact ~lth recovery forcesperform VHF BEACON Check

MONITOR VHF BEACON transmlSSlonnth VHF AM B Rcvr andor Su)vlval

TransceiverkVHF Beacon not operatlng ~connect Surv~val TranscelVer to antcable behlnd VHF ant access pnland place radio ln BCN mode

LOW POHER CHECKLISTVHF BCN - OFFVHF AM (3) - RCVFLOOD Lts - OFFVHF AM AampB - off (ctr)VHF AM RCV ONLY - A (venfy)COUCH LIGHTS - OFFPOSTLANDING VENT SYS mlnlmlze useSURV RADIO - plug mto VHF BCN ANT cableconn behind VHF ant acess pnl amp turn radloon l-n BCN mode

EGRESS PROCEDURES

CMPCDRLMPCDR

CMPCDRCMP

LMPLl1PCDR

STABLE IDlsconnect Umblll-calsNeck darn onCenter couch - 270 0 positionArmrests stowedConnect raft to SIC l-f desl-red wlth

green lanyardConnect raft ~hl-te lanyards to SUltS amp

lnflate water wlngs when eXltl-ngHATCH PISTON PRESS vlv - PRESS (Outbd)Slde Hatch openedPL VENT - OFFcb Pnl 250 (all) - openEgress with 11feraftPut hardware klt outEgress

or CDIPALL

CMF

CDRCMF

CDR

LMF

CMFCMP LMFCMP

UlP

CDR

-49-

STABLE IIcb CREW STA AUDIO (3) - openD~sconnect umb~1~ca1s

Release foots trapsRelease restra~nt harnessCouch seat pans (3) - 170 0 pos1t10nArm rests stowedSurv1va1 k~ts removed from stowageConnect life raft ma~n1~ne to CDR or SicConnect f~rst wh~te lanyard from

11fe raft to suitConnect th~rd wh~te lanyard from

l~fe raft to SU1tConnect rucksacks together to yellow

lanyard on raft bagPRESSURE EQUALIZATION vlv - OPENRemove and stow fwd hatchEX1t feet f1rst w1th rucksacks when clear

of siC 1nflate water w1ngs and raftExit feet f1rst when clear of SiC

1nflate water w1ngsEX1t feet f1rst when clear of sic

1nflate water w1ngs

-50-

60 TLI ABORTS

TLI Aborts are conta~ned ~n the ESD s~nce the bulk of the funct~ons

concern entry preparat20ns and performance Th~s allows a s2nglesource of procedures for procedure rev2ew val~dat~on checkout andtra~n~ng These procedures ~ncorporate TLI preparat20ns as found ~n

reference 6 w~th the TLI Abort Procedures and these t~e 2nto normallunar return Entry Procedures found ~n sect20n 5 The guidel~nes

for th~s cont2ngency are spec2f2ed 2n reference 7

In2t2al preparat~ons for TLI pos2t20n the necessary system sW2tches2n add~t~on to perform~ng an EMS ~V test and a GDC al~gnment Afterthe DET ~s set for mon2tor2ng TB6 the CMP ~ncreases the 12ght levelof the LEB DSKY to max~mum and returns to the h2s couch Th2s 2Sdone so that the LEB DSKY can be observed ~n the event sunl~ght orreflect20ns wash out the ma2n d2splay panel DSKY dur2ng cr2t2calmaneuvers The crew then straps ~n and prepares for mon2tor~ng TB6as 2nd2cated by the SII SEP L~te The t2mes se~uence of procedures2S keyed on th~s d~splay and ~ncludes the DET START funct~on andSIVB IGNITION Dur2ng the burn the crew mon2tors the FDAIs foratt~tude excurs20ns and abnormal rates report~ng status checks toM~ss2on Control at d2screet t~mes dur2ng the maneuver Upon SIVBSHUTDOWN the eMP records the DSKY d~splayed performance parametersand awa2ts ground conf2rmat~on

The rat~onal for TLI aborts ~s descr~bed 2n reference 7 A summar2shyzat20n 2S extracted to prov2de background and gu2de12nes 2n th2sdocument The abort procedures cover aborts 10 m2nutes after conshyt2ngent SIVE shutdown and aborts 90 m2nutes after normal SIVE shutshydown t2me

The 10 m~nute TLI abort ~s des2gned to be used dur~ng TLI ~n theevent a spacecraft problem develops Wh2Ch can result 2n catastrophe2f ~mmed~ate act~on 2S not taken If the s~tuat20n perm~ts the crewshould always allow the SIVB to complete TLI at wh~ch t~me the groundand crew can perform a malfunct~on analys~s to determ~ne ~f an abort~s adv~sable If a fa~lure occurs that necess2tates the shutdown ofthe SIVB and the ~u~ck return of the crew to earth th~s abort ~s

des~gned to be as ~nsens~t~ve to execut~on errors as poss~ble andst21l be targeted to m2dcorr2dor The burn att~tude w~th the f~ed

hor~zon reference ~s a constant value for any shutdown t~me Theburn durat~on 2S a funct20n of shutdown t2me and 2S ava21able fromcrew charts S~nce the pr~mary purpose of th~s abort ~s to returnto earth as qU2ckly as poss2ble there are no restr2ct20ns as toland~ng locat~on However ~f the t~me to EI is greater than abouttwo hours a midcourse correct20n should be ant~c~pated

The 90 m2nute TLI abort 2S to be used 2f a cr2t2cal subsystem malshyfunct~on ~s determ2ned and the dec2s~on to abort ~s made after the

-51-

TLI cutoff and before TLI cutoff plus approxlmately 80 m1nutesTh1S allows suff1c1ent separatlon and procedural t1me to set upfor the SPS deorb1t burn performed at about TLI + 90 Note thatgenerally the deorb1t burns w1ll be performed a fe11 m1nutes beforeTLI + 90 accord1ng to crew charts shown In reference 8 The no-comm except10n requ1res that 90 m1nutes be the 1nput t1me of 19n1shytlon for P-37 (onboard return-to-earth abort program) so that onshyboard calculatlons can correspond w1th ground calculat10ns to computethe CM land1ng p01nt Th1S TLI abort lS des1gned so that returnfl1ght t1me does not exceed 18 hours and abort ~V does not exceed7000 fps ThlS abort can be performed uSlng chart ~Vs and attltudesand the earths hor1zon serves as a suff1c1ent reference The maneushyver lS targeted to ach1eve the mldcorr1dor entry target Ilne andtlmed to result 1n a deslgnated recovery area

It 1S ObV10US for abort deC1S1ons early 1n the TLI + 90 m1nute t1meshyframe that a GampN SPS burn should be performed In order to keep theTLI abort procedures cons1stent and w1th emphasls on slmpl1c1ty theprocedures here reflect a SCS SPS abort burn to cover the full abortdec1s1on t1meframe

A m1dcourse correct1on for corr1dor control after a TLI abort may bedeS1red 1f the SPS burn d1d not meet expectat1ons The TLIabortprocedures 1n th1S sect10n adapt to the normal lunar return tlmel1neand procedures pr10r to the f1nal MCC

-52-

61 TLI PREPARATION PROCEDURES

GET = 150

CRO AOS(___)

CRO LOS( )(22142)

5100

Don Helmets amp Gloves

XLUNAR - INJECT (verify)EDS PWR - on (venfy)EMS FUNC - OFF (verlfy)EMS MODE - STBYEMS FUNC - IW SETVHF RNGEMS MODE - NORMALSet ~V indo to +15868 fpsEMS FUMC - ~V Test

SPS THRUST Lt - onoff (10 sec)~V lnd stops at -01 to -415

EMS MODE - STBYEMS FUMC - ~V SETVHF RNGSet ~VC

EMS FUNC---~~V=----

GDC ALIGNFDAI Select - liZcb SECS LOGIC (Z) - close (verify)cb SECS ARM (Z) - closeSECS LOGIC (Z) - on (up)MSFN Conflrm GO for PYRO ARM (If pass)SECS PYRO ARM (Z) - on (up)TRANS CONTROL PWR - ONROT CONTR PWR NORMAL (Z) - ACDC(verlfy)ROT CONTR PWR DIRECT (Z) - MNAMNBLV INnGPI - SIISIVB (venfy)LV GUID - IU (venfy)cb DIRECT ULLAGE (Z) - closedSet EVENT TIMER to 5100Begin MONITOR For TB6

CMP to Couch

TB 6 - SII SEP Lt on (TIG-9 mln 38 sec)KEY V83E

SET ORDEALFDAI Z ORB RATE at 180 0 0SII SEP Lt out (38 sec later)Start DET COUNTING UPSC CaNT - SCS (verify)MONITOR LV TANK PRESS

~P lt 36 psid (OXID gt FUEL)~P lt Z6 psid (FUEL gt OXID)

EMERGENCY CSMLV SEP UP TLM CM - BLOCK (verify)UP TLM IU - BLOCK (venfy)

-53-

+45degPY))0middot sec PY

lOK nmltHAlt25K nm

Two phas~ng mnvrs two SPS mnvrs to circular~ze at 150 nmearth orb~t

CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ssion 4K nmltHAltlOK nm CSM amp1M - Two phasing mnvrs two SPS mnvrs to circularize at 150 nm earth orb~t CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ss~on

CSM amp 1M - Two phas~ng mnvrs APS burn todepletion th~rd phasing mnvrSPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn tosem~sync orb~t

25K nmltHAlt40K nm CSM amp 1M - Two phasmg mnvrs APS burn to depletion third phas~ng mnvr SPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn to sem~sync orbit HA)40K nm DPS ava~l - DPS LOll circularize with SPS

DPS not ava~l - Lunar flyby or CSM only to lunar orbit (if reqd gtV lt4000 fps)

V37E 47E (check b~as) Record -=--rshy(Limit 98 fpsmm)

( 1fps)tVXYZN62EVIHDOTHPAD (fpsfpslnm)MONITOR VI ( ) at ECO

SCS TVC SERVO PWR 1 - ACIMNA2 - OFF

TAPE RCDR - CMD RESETHBREMS MODE - NORMAL

SIr SEP Lt - ONTLI Inhib~t S~gnals w~11 not be honored after 5942

SIVB ULLAGE BeginsSII SEP Lt - off (TIG - 18 sec)SIVB FUEL LEADSIVB ULLAGE d~scont~nues

LV ENG I Lt - onSIVB IGNITION ( GETI)LV ENG I Lt - off - -shyMONITOR THRUST amp ATTITUDEMONITOR LV TANK PRESSSIVE ECO (Lt on) (BEGIN TB7)

EMER SIVE CUTOFF AT 6 SEC PAST BURN TIME IF VI ATTAINEDTHC CCW ampNEUTRAL IN 1 SEC or SIISIVB sW - LV STAGEPremature Shutdown HAlt4K nm CSM amp 1M -

5700

58205836

F 16 835800

F 16 62

5838594259525955595900000002SUNRISE(___)

HAW AOS(__=_) KEY VERB (freeze d~splay)

SIVB ATT HOLD 20 sec amp BEGIN VENTINGSIVB NNVR TO ORB RT (HDS DN) (3middot sec)

Record VI -c---HDOT _

HPAD _

KEY RLSEF 16 62

F 16 83

HAW LOS(__=-)

KEYmiddotRLSE~VXYZ (lfps)

Record ~VX---_

~vy

WZ--

AVC---_

TAPE RCDR - off (ctr)EMS MODE - STBYEMS FUNC - OFFSECS PYRO ARM (2) - SAFE

PRO

BURN STATUS REPORT

____--~TIG

BT------VGX____-R

-----P----_Y

REMARKS

_____VI

______--HDOT______--H______---AVC______---FUEL_______OXID

_______UNBAL

F 3708=00 OOEGOS AOS CMP TO LEB

(-=-=-)

0000

0003

0005

0014

0100

-55-

62 TLI 10 MIN ABORTSECS LOGIC (2) - on (up)SECS PYRO ARM (2) - ARM

TRANS CONTR - CGH (4 sec) amp +XDET RESET (verlfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS GMD-ON

TRANS GONTR - neutral then +X for10 sec

SIVBGPI s~ - GPIExcesslve rates 6V THRUST A - NORMAL SPS THRUST - DIRECT When rates damped 6V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

TRANS CONTR +X - OFFV37E OOE

PITGH UP to LOGAL VERT (+X axlSto~ard the earth)

RATE - LOWBMAG MODE (3) - ATTIRATE 2EDS PHR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SEGS ARM (2) - opencb EDS (3) - open

TRANS CONTR -X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (180deg)P (199deg)Y (0deg)

RETRO UPDATEGETI _

JV _VG

Jtb ---GET 400K _

05G _GET DROGUE _

ENTRY P _R _

Y_--

0945

-56-

ALIGN HORIZ ON RET +1 MKGMBL CHECK (T11lle Pentattlng)MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conflnn)cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FUMC - JV SETVHF RNGSET JV from chartE~S FUMC - JVEMS fODE - NOIDlAL

lV THRUST A - NORMALV37E 47E (THRUST fONITOR)

F 16 83 lVXYZ (1 fps)

0950

1000

NOTE For aborts durlng 1st mln of TLIKEY V82E F 16 44 (HaHpTff)Burn untll Hp lt 19NM

TRANS CONTR +X

THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN JV reqdJV THRUST (2) - OFFReport cutoff

cb SPS P2 Y2- closeGfBL MTRS (4) - OFF (LMP Confinn)TRANS CONT PWR - OFFTVC SERVO PWR (2) - OFFMN BUS TIE (2) - OFFcb SPS P1amp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREIf est time to EIltOl5500 omlt fCC andenter the SUPERCIRC CKLIST as early as pos-slb1e Pg ~2~3~ __If est time to EI)Ol5500 anticlpate afCC Enter the ENTRY PREP CKLIST at step 9pg 18

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

-2tl C

l I W gt- ~-4

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l- I J u gt- ~-8

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26

28

30

32

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-i- rtREQUIRED PITCH GIMBAL ANG LETO OBTAIN HOR-IZON AT 317

DEGREES IN wiiiiDOW

260

z~I- ~ i5 24000

1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

-I

-1-

NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

I LU HD~-

LUHD

lt0 120UJ0

~

80 HOLD PRESENT TRIMgt LU HD013

~Y~HOIgtlt

TOP OF WINDOWa 40to

31 7 SCRIBEaaI

80 TTOM OF WINDOWi= 0

0--ltoa

-40t-z

~~~Uw w u lt0 -80

HOLO PRESENT TRIlJCl

LOHU0 lt0

J gt -120 HOLD 059 TRIMlt0 z

LDHUlt0 FIELD OF VI S10 NLDHU LIFT-DOWNHEADS -UPLUHD LIFT-UP HEADS-DOWN

~~H~-160 q - P63 LIMITI- NOrE-VALIO ONLY FO~t~--

LUNAR RETURN VELOCITY

plusmnl8020 244middot 8 12 16

TIME TO 400K FT ALTITUDE-MIN

4

P37

LONG

ITUD

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TOOB

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1350

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344

348

352

356

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00 60

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120

200

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240

320

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1968

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0080

0070

0060

0050

0040

0030

0020

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000

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II

II

II

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RNTI

ME

-M

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Cll-

41)

120

200

241)

320

400

441)

520

TlI

-I0

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ABOR

TlA

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-DE

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19

68

lAUN

CHA

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UTH

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3

-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 28: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

-25-

SUPERCIRCULAR ENTRY (Cont~nued)

1

4100m(-1900)

P61 - ENTRY PREP

V37E 61E

k 05 09 01427 - ROLL REVERSED 05 09 01426 - IMU UNSAT ~

2 F 06 61 IMPACT LAT LONG HDS UPDN (+-)PRO (010

fps +00001)

3 F 06 60 GMAXVPREDGAMMA EIRecord

GMAXV400K----

GAMMA EI _PRO

(01deg fpsOldeg)

4 F 06 63 RTOGO (lnm) PAD _VIO (fps) PAD _TFE(m~n-sec)

Compare w~th ~M~SFN==C~f~o-r~P~GNS GONO GOIf NO COMM Set RTOGO amp VIO In EMS

amp lnltla11ze(ACCEPT) PRO(RECALC) V32E To 4

5 F 50 25

4300m

(-1700)

45 oOm(-1500)

500Om(-1000)

6 F 06 61

-26-

P62 - CMSM SEP amp PRE-ENTRY MNVRCAUTION Call No EXT Verbs In P62

00041 REQUEST CMSM SEPSC CONT - SCSFREE

COMPARE PITCH ATT WITH PAD DATA ---0=-

(W~thLU 5deg)YAW - 45deg OUT-OF-PLANE (LEFT)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTIRATE 2MN BUS TIE (2) - ON (ver~fy)

PRIM GLY TO RAD - BYPASS (verlfy)CM RCS LOGIC - ON (venfy)SECS LOGIC (2) - on (up)SECS PYRO ARM - ARMCMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 ps~a

CM RCS LOGIC - OFFSECS PYRO ARM (2) - SAFEMonltor VMAB

If lt25 vdc go to EMERGPOWERDOWN pg E6-l

AUTO RCS SEL AC ROLL (4) - OFFAUTO RCS SEL CM 2(6)-OFFAUTO RCS SEL CM 1(6)-MNAYAW back to 0degPITCH TO HORIZ TRACK ATT

ROLL - 0deg (LIFT UP)PITCH - 400K Horiz Mark (317deg)YAW - 0deg

ATT DB - MAXMAN ATT PITCH - ACCEL CMDEMS DATA - Ver~fy

EMS FliNC - ENTRY (ver~fy)

EMS MODE - NORMALcb SPS PampY (4) - openMAINT HORIZ TRK

PRO (Act ENTRY DAP)

IMPACT LATLONGHDSDN (01deg01deg-00001)PRO

7 POSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axis beyond 45deg of Vel vector)

8 06 64

58middot00m(-0200)

9

05G tlme(+0 )

(--=---)

06 68

-27-

P63 - ENTRY INIT

GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PIJR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRmDHORIZ CKPltch error needle goes toward

zero approachlng OSG tlmeMAN ATT (PITCH) - RATE CMD

If CMC lS GOBMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS I

FLY BETA If CMC NO GO ilt

1 SC CaNT - SCS I

FLY EMS k

p64 - ENTRY POST 05G

RTOGO AT 05G AGREES HITH EMS-venfyHORIZ CK05G Lt - ON (EMS START)

No EMS START wlthln 3 sec ~ EMS MODE - BACKUP VHF RNG c

05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds Llft DN

NNVR Llft DNEMS GONO GO

G-V Plot wlthln IlmltsRng ctr dwn 60plusmn7 durlng 10 sec

perlodMonltor G-meter for

convergence wlth pad data (Do)(Vlt27K fps) Go to 13

-28-

P65 - ENTRY - UP CONT (Vgt27K fps)

10 F 16 69 BETA (01middot) _DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT lt~ SC CONT - SCS FLY EMS

PRO

11 06 68 BETAVIHDOT (OIdegfpsfps)(VltV1+500 fps amp RnOT Neg) Go To 13

P66 - ENTRY - BALLISTIC (D(DL)

12 06 22 DESIRED GMBL ANGLES RPYMoultor horlz +12middot of 317middot mark

P67 - ENTRY - FINAL PHASE (02G)

13 06 66 BETACRSRNG ERRDNRNG ERR(010 1um 1um)

KEY VERBRecord DNRNG ERR _KEY RLSEMoultor l~ft vector ou RSI amp FDAI

16 67 RTOGOLATLONG (Vrel=1000fps)(lumOldegOldeg)

SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOWNMonitor a1t~meter

Go To EARTHLANDING pg ---4L5 _

-29-

53 GampN HYBRID DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL tV1 V37E 30E

2 F 06 33 GETI(ACCEPT) PRO (hrm~n Olsec)(REJECT) LOAD DESIRED GETI

3 F 06 81 tVXYZ (LV) (lfps)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

4 F 06 42 HAHPtV (lnm lfps)Record tV

(ACCEPT) PRO(REJECT) Reselect P30 or P27 Load new paramo

5 F 16 45 MTFIMGA (marksm~n-secOlO)

MGA -00002 ~f k

k lMU not al~gned

SET DETPRO

6

7

8

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (Pull)PLSS 02 vlv - FILL02 8M SUPPLY vlv - OFFCAB PRESS REL vlv (2) - NORMcb ELS (2) - closecb SECS ARM (2) - closecb SECS LOGIC (2) - close (ver~fy)

AUTO RCS SEL CM (12) - MNA or ~ffiB

(hftoff conhg)ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM (AampB) - OFF

CMP to Couch

9

10

11

-30-

MNVR TO PAD BURN ATTLOAD DAPBMAG MODE (3) - RATE 2SC CONT - CMCAUTOATT DB - MINMAN ATT (3) - RATE CMD

v62E

v49E

12 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLES

PRO

13 F 50 18 REQ MNVR TO FDAI RPY ANGLES (01deg)(AUTO) PRO(MAN) SC CONT - SCS

BMAG MODE (3) - RATE 2MNVR To 15

14 06 18 AUTO MNVR TO FDAI RPY ANGLES (01deg)

15 F 50 18 REQ TRIM TO FDAI RPY ANGLES (01deg)(TRIM) Go to 13(ByPASS) ENTR

16

17

CHECK BORESIGHT amp SKT STARSOPT MODE - CMCOPT ZERO - OFF

v41 N91E

18 F 21 92 SHAFTTRUN (01deg 001deg)Load SXTS angles

19 41 OPTICS DRIVECheck SKT STAR

OPT ZERO - ZEROCheck BORESIGHT STAR (~f ava~l)

20 V25 N17E (01deg)Load Pad Data GMBL Angles

for CM BURN ATTATT SETtw - SET

to PAD DATA GMBL ANGLESfor CM BURN ATT

21

22

-31-

PHR REDUCTIONHGA PHR - OFFFC PUMPS (3) - OFFVerify s~ngle su~t compr oper loads

balancedFC 2 MN AampB - OFFS BD PiR AMP - LOWcb ECS RAD CONTHTR (2) - opencb HASTE H20URINE DUMP HTRS(2)- opencb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANMN BUS TIE (2) - ONTVC SERVO PHR 1 - AC1MNAGMBL MTR (4) - START

p41 - RCS THRUSTINGV37E 41E

23 F 50 18 REQ MNVR TO LCL HORIZ (HDS ON)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CMCAUTOPRO To 24

(gtfANDAP) BMAG MODE (3) - RATE 2SC CONT - CMCHOLD

V62EMNVR To 25

24 06 18 AUTO MNVR TO FDAI RPY

25 F 50 18 REQ TRIM TO LCL HORIZ (01deg)ALIGN SC ROLL

(AUTO TRIM) PRO To 24(BYPASS) ATT DB - MIN

RATE - LOHMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTlRATE 2

ENTR

550Om26 06 85

59middot2527

-32-

VGXYZ (1fps)RECHECK BORESIGHT STARTRANS CONIR PWR - on (up)EMS MODE - STBY (ver~fy)

EMS FliNC - bV SETVHF RNGSET (IV for SM BURN _EMS FliNC - bVS BD ANT - OMNI CSECS LOGIC (2) - ONMSFN conhrm Go for PYRO ARMSECS PYRO ARM (2) - ARMCM RCS LOGIC - ON (ver~fy)

DSKY BLANKS

593028 16 85 VG XYZ (AVE G ON) (lfps)

RHCs amp THC - ARMEDLIMIT CYCLE - OFFTAPE RCDR - CMD RESETHBREMS MODE - NORMAL

000029 F 16 85 REQ NULL VG XYZ (lfps)

BURN EMS bV CTR TO ZERORESET DET amp COUNT UP

If SM ONLY burn go to step 32THC - LOCKEDSC CaNT - SCSFREERATE - HIGHPRIM GLY To RAD - BYPASS (ver~fy)

MN BUS TIE (2) - ON (ver~fy)

CMSM SEP (2) - on (up)CSMLM FNL SEP (2) - on (up) (verify)CampW MODE - CMRCS TRNFR - CMCM RCS LOGIC - OFF

Momtor VM ABIf lt25 vdc go to EMERGPOWER DOWN Pg E6-l

V63E

If CMC NO GO FDAI SOURCE - ATT FDAI SEL - 1 or 2 ATT SET - GDC

SET

-33-

~Uili ATT PITCH - ACCEL CMDFDAI SCALE - 55MNVR TO CM BURN ATT (NULL ERR NEEDLES)

R 0degPY --00--

30

31

CM RCS BURNRHC III-ContJnuous PJtch DownRHC HZ-Module PJtch to null needlesBURN VGZ TO ZERO

If only 1 RHC Pulse + P=5deg from retro att MaJnta~n rates lt3degsec

BURN COMPLETION ATllV CTR= or DET= _

V8ZE

32 F 16 44 HAHPTFF (1nmffiJn-sec)Check HP-

If gt Pad data contJnue burnuntJ1 lt Pad

PRO

33 F 16 85 VGXYZ (Ups)Read VG resJduals to MSFN

(HYBRID) PRO to 34(SM ONLY BURN)

PROF 37 ODE

EI-1500 V37E 47EF 16 83 twx Y Z (Ups)

SC CONT - SCSFREEMAN ATT (PITCH) - RATE CMDRATE - HIGHPRIM GLY To RAD - BYPASS (verJfy)MN BUS TIE (2) - ON (verJfy)CMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verJfy)Campl MODE - CMRCS TRNFR - CMCM ReS LOGIC - OFFSECS PYRO ~I (2) - SAFE

-34-

PROMonitor VMAB

If lt25 vdc go to EMERGPOWER DOWN

34 F 37 OOEPCM BIT RATE - LOWATT DB - MAXEMS MODE - STBYEMS FUNC - OFF

Go To EARTH ORBIT ENTRY pg _--40-__

-36-

8 SPS THRUSTING PREPCYCLE CRYO FANSSPS GAGING - ACI (ver~fy)

PUG MODE - NORM (venfy)BMAG MODE (3) - RATE 2tv CG - CSMCMC MODE - FREEAUTO RCS SEL (16) - MNA or HNB

(hftoff conbg)SC CONT - CMCAUTO

9 MNVR TO PAD BURN ATTV62E

10 V49E

11 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLESPRO

12 F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) PRO(HAN) SC CONT - ses

MNVR to 14

06 18 AUTO MNVR TO FDAI RPY ANGLES13

14 F 50 18 REO TRIH TO FDAI RPY ANGLES(TRIM) Go to 12(BYPASS) ENTR

15 BORESIGHT STAR CHECK

16 V37E 40EOPT PWR - OFF

17 F 50 18 REQUEST MNVR TO FDAI RPY ANGLES (01deg)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CHCAUTOPRO to 18

(MANDAP) BMAG HODE (3) - RATE 2SC CONT - CMCHOLDMNVR to 19

(HANseS) se eONT - sesMNVR to 19

-35-

54 NORMAL DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL ~V

1 V37E 30E

2 F 06 33 GETI (hrm~nOlsec)

(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

3 F 06 81 ~VXYZ (LV)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

( lfps)

4 F 06 42 HAHP~V (1nmlfps)Record W

(ACCEPT) PRO -----(REJECT) Rese1ect P30 or P27 Load new pa~am

5 F 16 45 MTFIMGA (marksmln-secOldeg)MGA -00002 If ~ lMU not a1~gned

SET DETPRO

6

7

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY v1v - OFFCAB PRESS REL v1v (2) - NORMcb ELS (2) - close (verify)cb SECS ARM (2) - close (ver~fy)

cb SECS LOGIC (2) - close (verlfy)AUTO RCS SEL CM (12) - ~mA or MNB

(l~ftoff conf~g)

ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM AampB - off (ctr)

18

-37-

06 18 AUTO MNVR TO FDAI RPY ANGLES (01 0)

19 l 50 18 REOUEST TRIM MNVR TOALIGN SIC ROLLGDC ALIGN

FDAI RPY ANGLES(010

)

+54-00m(-06-00)

TIG-5mJn

5500m(-0500)

TVC CHECK amp PREPcb STAB CONT SYS (all) - closecb SPS (12) - closeATT DB - MINRATE - LOl~

LIMIT CYCLE - ONMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE 2ROT CONTR PWR DIRECT (2) - OFFSCS TVC (2) - RATE CMD

If SCS SCS TVC (2) - AUTO SC CONT - SCS ~

TVC GMBL DRIVE PampY - AUTOMN BUS TIE (2) - ONTVC SERVO PWR 1 - AC1MNA

2 - AC2MNBTRANS CONTR PWR - ONROT CONTR PWR NORMAL 2 - ACRHC 2 - ARMED

HORIZ CHK - HorJz on 12deg wJndmlmark (LJffiJt +3 0 PNGCS GONO GO)

If NO GO set tw 180 0 180deg0 0

Track horJz wJth 24deg wJndow markAt TIG-2 mJn Ahgn GDC

PRIMARY TVC CHECKGMBL MOT P1-Y1 -STARTON(LMP confJrm)

If SCS verJfy Thumbwheel TrJmTHC - CWVenfy NO MTVC

SEC TVC CHECKGHBL MOT P2-Y2 -STARTON(LMP confJrm)SET GPI TRIHVenfy MTVCTHC NEUTRALGPI returns to 00 (CMC) or trJm (SCS)ROT CONT Pl~ NORM 2 - ACDC

(TRIM) Go to step 17(BYPASS) BMAG MODE(3) - ATTIRATE2 (ver1fy)

ENTR

-38-

20 F SO 25 00204 GMBL TEST OPTION(ACCEPT) SC CONT - GMC (ver~fy)

PROMonitor GPI Response

0020-2000020-200Tr~m

TEST FAIL SC CONT - SCS SCS TVC (2) - AUTO

(REJECT) ENTR

21 06 40 TFIVG~VM (m~n-sec1fps)

PROG ALM - TIG s1~pped

V5N9E 01703

KEY RLSE To 21 ROT CONTR PWR DIRECT (2) - MNABSPS He v1vs (2) - AUTO (ver~fy)

LIMIT CYCLE - OFFFDAI SCALE - SOIScb SPS P2Y2 - open (for cr~t burn)

5800(-02 00)

5925(-0035)

59middot 30(-0030)

06 40

59XX(-OOXX)

AV THRUST A(B) - NORMALTHC - ARMEDRlIC (2) - ARMEDTAPE RCDR - GID RESETHBR

DSKY BLANKS

(AVE G ON)EMS MODE - NORMAL

TFIVG~VM (m~n-seclfps)

CHECK PIPA BIAS lt2fps for 5 sec

ULLAGE AS REQ

IF NO ULLAGE DIR ULLAGE PB - PUSH~

CONTROL ATT WRlIC MONITOR AVM (R3) COUNTING UP

5955(-0005)

F 99 40 ENG ON ENABLE REQUEST(AUTO IGN) PRO AT TFI gt0 sec(BYPASS IGN) ENTR to 24

22 0000 IGN

-39-

If SCS - THRUST ON PB - PUSH

06 40 TFCVG~VM (m~n-seclfpslfps)

~F 97 40 SPS Thrust fall ~

~(RESTART) PRO To IGN (RECYCLE) ENTR To TIG-05 sec

SPS THRUST LITE - ONMONITOR THRUSTING

Pc 95-105 pSlaEMS COUNTING DOWNSPS IN3 v1vs (4) - OPENSPS He v1vs tb (2) - graySPS FUELOXID PRESS - 175-195 pSlaPUGS - BALANCED

PROG ALARM V5N9E 01407 VG INCTHC - CW FLY MTVC

ECOEMER SPS CUTOFF J

AV THRUST (2) - OFF

23 F 16 40 TFC(STATIC)VG~VM (mln-seclfps)~V THRUST AB - OFF

SPS IN3 v1vs (4) - CLOSEDSPS He tb (2) - bp

cb SPS P2Y2 - closed (verlfy)TVC SERVO PHR - AC1MNA (venfy)TVC SERVO PWR 2 - OFF

PRO

24 F 16 85 VG XYZ(CM) CUps)NULL RESIDUALSRECORD ~V CTR amp RESIDUALS I1VCEMS FUNC - OFF VGXEMS MODE - STBY VGYBMAG MODE (3) - RATE 2ATT DB - MAX VGZTRANS CONT PHR - OFF

PRO

25 F 37 V82E

26 F 16 44 HAHPTFF (lnmm~n-sec)

R3-59B59 HP gt494 nmPRO

27 F 37 OOE

-40-

55 EARTH ORBIT ENTRY

1 Venfy CMSMR __

P_shyY_-

SEP ATT(180deg)

(0deg )

2

3

4

EMS INITIALIZATIONEMS FUNC - RNG SETSET RNG TO PAD DATA RNGEMS FUNC - VA SETSlew scroll to pad data VIOEMS FUNC - ENTRY

RSI ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on(up)GDC ALIGN PB - PUSH amp HOLDYAW tw - Pos1tion RSI thru 45deg amp

back to LIFl UPGDC ALIGN PB - RELEASEEMS ROLL - OFFAl1gn GDC to lMU

PWR REDUCT (Norm Deorb Only)HGA PWR - OFFFC PUMPS (3) - OFFVer1fy s1ngle suit compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - Lowcb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2)-openlOb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MAN

-41-

P61 - ENTRY PREP

5 V37E 61E05 09 01427 - ROLL REVERSED05 09 01426 - IMU UNSAT

6 F 06 61 IMPACT LAT LONG liDS UPDN (+-)(01 0

010

+00001)

PRO

PAD VALUESLATLON==G------liDS UP DN _

7 F 06 60 GMAXV400KGAMMA EIRecord

GMAXV400K----GAMMA EI _

PRO

8 F 06 63 RTOGO (1nm) PAD _VIa (fps) PADTFE (mln-sec) ----Compare wlth MSFN for PGNS GONO GONO COMM SET RTOGO amp VIO IN EMS amp

INITIALIZE(ACCEPT) PRO(RECALC) V32E to 8

-42-

P62 - CMSM SEP amp PRE-ENTRY MNVR

9 F 50 25 00041 REQUEST CMSM SEPSC CONT - SCSFREEYAW - 45deg out-of-plane (left for RCS

nght for SPS)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE2PRIM GLY to RAD - BYPASS (verlfy)SECS LOGIC (2) - on (up)MSFN conflrm GO for PYRO ARMSECS PYRO ARM - ARMMN BUS TIE (2) - ON (verlfy)CMSM SEF (2) - ONCSMLM FNl SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 pSlaCM RCS LOGIC - OFFSECS PYRO ARM - SAFEMonltor VMAB

If lt25vdc go to EMERG POWERDOWN Pg E6-1AUTO RCS SEL AlC ROLL (4) - OFFAUTO RCS SEL CM 2(6) - OFFAUTO RCS SEL CM 1(6) - MNA or MNBYAW back to 00

PITCH TO ENTRY ATTROLL 0deg (LIFT UP)PITCH - HORIZ on 317deg MARK (400K)YAW 00

ATT DB - MAXMAN ATT (PITCH) - ACCEL CMDEMS DATA - VerifyEMS FUNC - ENTRY (verlfy)EMS MODE - NORMALMAINTAIN HORIZ TRK

PRO (Act ENTRY DAP)

10 F 06 61 IMPACT LAT LONG HDSDN(010 010 -00001)

PRO

11 FOSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axlS beyond 45deg of Vel vector)

-43-

P63 - ENTRY INIT

12 06 64 GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PWR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRHORIZ CKP~tch error needle goes toward

zero approach~ng 05G t~me

MAN ATT (PITCH) - RATE CMDIf CMC ~s GO

BMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS FLY BETA If CMC NO GO ~

SC CONT - SCS~

FLY EMS RCS Deorh Roll HDS UPTRACK HORIZ w~th 29deg w~ndow mk

P64 - ENTRY POST 05G

13

05G t=elt+0___)

06 68

RTOGO AT 05G AGREES WITH EMS - venfyHORIZ CK05E Lt - on (EMS start)

No EMS start w~th~n 3 secsEMS MODE - BACKUP VHF RNG 05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds L~ft DN

NNVR L~ft DNEMS GONO GO

G-V Plot w~th~n llm~ts

Rng ctr dwn 60 + 7 durlng 10 sec per~od

Mon~tor G-meter forconvergence wlth pad data (Do)

(Vlt27K fps) Go To 17

-44-

P65 - ENTRY - UP CONT (Vgt27K fps)

14 F 16 69 BETA (01deg)DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT~

SC CONT - SCS FLY EMS

PRO

15 06 68 BElA VI HOOT (01deg fpsfps)(VltVL +500 fps amp RDOT Neg) Go To 17

p66 - ENTRY - BALLISTIC (DltDL)

16 06 22 DESIRED GMBL ANGLES RPY (01deg)Mon~tor hor~z +12deg of 317deg mark

P67 - ENTRY - FINAL PHASE (02G)

17 0666 BETACRSRNG ERRDNRNG ERR (Oldeglnmlnm)KEY VERBRecord DNRNG ERR _KEY RLSEL~m~t +100nm from PAD DRE

Mon~tor l~ft vector on RSI amp FDAIF 16 67 RTOGOLATLONG (Vre1=1000fps)

(lnm 010 01deg)SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOlfflMon~tor altimeter

Go To EARTHLANDING pg _I4L5__

-45-

56 EARTHLANDING

90K STEAM PRESS - PEGGED50K CABIN PRESS REL vIv (2) - BOOSTENTRY

SECS PYRO ARM (2) - ARM

40K(90K + 63s)

CM UNSTABLE RCS CMD - OFF ~ 40K APEX COVER JETT PG-PUSH DROGUE DEPLOY PG - PUSH (2 secafter apex cover Jett)

30K ELS LOGIC - ON (up)ELS - AUTO

24K RCS hsable (auto)(90K+92s) RCS CMD - OFF

Apex cover Jett (auto)APEX COVER JETT PB - PUSH

(WAIT 2 SECS)Drogue parachutes deployed (auto)

DROGUE DEPLOY PB - PUSH~

If Drogues FallELS - ~ ~Stablllze CM 5K MAIN DPLY PB - PUSHELS - AUTO

235K Cabln Pressure lncreaslng (Drogues + 50s)If not lncreaSlng by 17K CABIN PRESS REL vlv (RR) - DUMP

-46-

10K Maln parachutes deployedMAIN DEPLOY PB - PUSH (wlthln 1 sec)VHF ANT - RECYVHF AMA - SIMPLEXVHF BCN - ONCABIN PRESS REL v1v (2) - CLOSEDIRECT 02 vlv - OPENCM RCS LOGIC - on (up)CM PRPLNT - DUMP (burn audlb1e)Monltor CM ReS 1amp2 for He press decrease

NO BURN or PRESS DECREASE USE BOTH RHCs DO NOT FIRE PITCH JETS

CM PRPLNT-PURGE (to zero He press)CM RCS He DUMP PB - PUSH RHC (2) - 30 sees NO PITCH k

STRUT LOCKS (2) - UNLOCK

cb FLT amp PL BAT BUS ABampBAT C (3) - closecb FLT amp PLT MNA amp B (2) - opencb ECS RAD HTR OVLD (2) - opencb SPS PampY (4) - open

3K CABIN PRESS REL v1v (RH) - DUMP (after purgecompleted)

FLOOD Lts - POST LDGCM RCS PRPLNT (2) - OFFROT CONTR PWR DIRECT (2) - OFF

800 CAB PRESS RELF vlv - CLOSE (latch off)MN BUS TIE (2) - OFF

AFTER LANDINGcb MAIN REL PYRO (2) - closeMAIN RELEASE - on(up)

Go to POSTLANDING pg _47L-__

I

2

3

-47-

57 POSTLANDING

STABILIZATION VENTILATION COMMUNICATIONS

DIRECT 02 vlv - CLOSE

Stablllzation after landlngELS - AUTO (verlfy)cb MAIN REL PYRO (2) - close (venfy)MAIN RELEASE - on (up) (verlfy)S~CS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb BAT RLY BUS (2) - open

No contact w1th recovery forcesVHF AM AampB - off (ctr) ~

VHF AM Rev ONLY - A cb PL VENT - closecb FLOAT BAG (3) - closecb UPRIGHT SYS COMPRESS (2) - closeIf Stable II

FLOAT BAG(3)-FILL t1ll 2 m1n afterupr1ght then - OFF

VHF AM AlB amp BCN - OFF whlle lnvertedIf Stable I

After 10 M1n Coollng Per1odFLOAT BAG (3) - FILL 7 mln then OFF

Post Stab1lizat1on And Ventllat10nPL BCN LT - BCN LT LOWPL VENT vlv - UNLOCK (Pull)Remove PL VENT Exh CoverPL VENT - HIGH or LOWPL DYE MARKER - ON (swlmmer comm)Release foots traps and_restralntscb MNA BAT BUS A amp BAT C (2) - opencb MNB BAT BUS B amp BAT C (2) - opencb FLT amp PL BAT C - opencb PYRO A SEQ A - opencb PYRO B SEQ B - open

EACH HR - CHECK DC VOLTSgt 275 V If Notmiddot cb FLT amp PL-BAT BUS AampB (2) -open cb FLT amp PL BAT C (1) - open GO TO LOW POWER CHECKLIST

Unstow and lnstall PLV DISTRIB DUCTDeploy grappllng hook and 11ne 1f req

4

-48-

Post Landing Communlcatl0nsVHF ANT-RECY (venfy)VHF BCN - ON (verlfy)

If no contact ~lth recovery forcesperform VHF BEACON Check

MONITOR VHF BEACON transmlSSlonnth VHF AM B Rcvr andor Su)vlval

TransceiverkVHF Beacon not operatlng ~connect Surv~val TranscelVer to antcable behlnd VHF ant access pnland place radio ln BCN mode

LOW POHER CHECKLISTVHF BCN - OFFVHF AM (3) - RCVFLOOD Lts - OFFVHF AM AampB - off (ctr)VHF AM RCV ONLY - A (venfy)COUCH LIGHTS - OFFPOSTLANDING VENT SYS mlnlmlze useSURV RADIO - plug mto VHF BCN ANT cableconn behind VHF ant acess pnl amp turn radloon l-n BCN mode

EGRESS PROCEDURES

CMPCDRLMPCDR

CMPCDRCMP

LMPLl1PCDR

STABLE IDlsconnect Umblll-calsNeck darn onCenter couch - 270 0 positionArmrests stowedConnect raft to SIC l-f desl-red wlth

green lanyardConnect raft ~hl-te lanyards to SUltS amp

lnflate water wlngs when eXltl-ngHATCH PISTON PRESS vlv - PRESS (Outbd)Slde Hatch openedPL VENT - OFFcb Pnl 250 (all) - openEgress with 11feraftPut hardware klt outEgress

or CDIPALL

CMF

CDRCMF

CDR

LMF

CMFCMP LMFCMP

UlP

CDR

-49-

STABLE IIcb CREW STA AUDIO (3) - openD~sconnect umb~1~ca1s

Release foots trapsRelease restra~nt harnessCouch seat pans (3) - 170 0 pos1t10nArm rests stowedSurv1va1 k~ts removed from stowageConnect life raft ma~n1~ne to CDR or SicConnect f~rst wh~te lanyard from

11fe raft to suitConnect th~rd wh~te lanyard from

l~fe raft to SU1tConnect rucksacks together to yellow

lanyard on raft bagPRESSURE EQUALIZATION vlv - OPENRemove and stow fwd hatchEX1t feet f1rst w1th rucksacks when clear

of siC 1nflate water w1ngs and raftExit feet f1rst when clear of SiC

1nflate water w1ngsEX1t feet f1rst when clear of sic

1nflate water w1ngs

-50-

60 TLI ABORTS

TLI Aborts are conta~ned ~n the ESD s~nce the bulk of the funct~ons

concern entry preparat20ns and performance Th~s allows a s2nglesource of procedures for procedure rev2ew val~dat~on checkout andtra~n~ng These procedures ~ncorporate TLI preparat20ns as found ~n

reference 6 w~th the TLI Abort Procedures and these t~e 2nto normallunar return Entry Procedures found ~n sect20n 5 The guidel~nes

for th~s cont2ngency are spec2f2ed 2n reference 7

In2t2al preparat~ons for TLI pos2t20n the necessary system sW2tches2n add~t~on to perform~ng an EMS ~V test and a GDC al~gnment Afterthe DET ~s set for mon2tor2ng TB6 the CMP ~ncreases the 12ght levelof the LEB DSKY to max~mum and returns to the h2s couch Th2s 2Sdone so that the LEB DSKY can be observed ~n the event sunl~ght orreflect20ns wash out the ma2n d2splay panel DSKY dur2ng cr2t2calmaneuvers The crew then straps ~n and prepares for mon2tor~ng TB6as 2nd2cated by the SII SEP L~te The t2mes se~uence of procedures2S keyed on th~s d~splay and ~ncludes the DET START funct~on andSIVB IGNITION Dur2ng the burn the crew mon2tors the FDAIs foratt~tude excurs20ns and abnormal rates report~ng status checks toM~ss2on Control at d2screet t~mes dur2ng the maneuver Upon SIVBSHUTDOWN the eMP records the DSKY d~splayed performance parametersand awa2ts ground conf2rmat~on

The rat~onal for TLI aborts ~s descr~bed 2n reference 7 A summar2shyzat20n 2S extracted to prov2de background and gu2de12nes 2n th2sdocument The abort procedures cover aborts 10 m2nutes after conshyt2ngent SIVE shutdown and aborts 90 m2nutes after normal SIVE shutshydown t2me

The 10 m~nute TLI abort ~s des2gned to be used dur~ng TLI ~n theevent a spacecraft problem develops Wh2Ch can result 2n catastrophe2f ~mmed~ate act~on 2S not taken If the s~tuat20n perm~ts the crewshould always allow the SIVB to complete TLI at wh~ch t~me the groundand crew can perform a malfunct~on analys~s to determ~ne ~f an abort~s adv~sable If a fa~lure occurs that necess2tates the shutdown ofthe SIVB and the ~u~ck return of the crew to earth th~s abort ~s

des~gned to be as ~nsens~t~ve to execut~on errors as poss~ble andst21l be targeted to m2dcorr2dor The burn att~tude w~th the f~ed

hor~zon reference ~s a constant value for any shutdown t~me Theburn durat~on 2S a funct20n of shutdown t2me and 2S ava21able fromcrew charts S~nce the pr~mary purpose of th~s abort ~s to returnto earth as qU2ckly as poss2ble there are no restr2ct20ns as toland~ng locat~on However ~f the t~me to EI is greater than abouttwo hours a midcourse correct20n should be ant~c~pated

The 90 m2nute TLI abort 2S to be used 2f a cr2t2cal subsystem malshyfunct~on ~s determ2ned and the dec2s~on to abort ~s made after the

-51-

TLI cutoff and before TLI cutoff plus approxlmately 80 m1nutesTh1S allows suff1c1ent separatlon and procedural t1me to set upfor the SPS deorb1t burn performed at about TLI + 90 Note thatgenerally the deorb1t burns w1ll be performed a fe11 m1nutes beforeTLI + 90 accord1ng to crew charts shown In reference 8 The no-comm except10n requ1res that 90 m1nutes be the 1nput t1me of 19n1shytlon for P-37 (onboard return-to-earth abort program) so that onshyboard calculatlons can correspond w1th ground calculat10ns to computethe CM land1ng p01nt Th1S TLI abort lS des1gned so that returnfl1ght t1me does not exceed 18 hours and abort ~V does not exceed7000 fps ThlS abort can be performed uSlng chart ~Vs and attltudesand the earths hor1zon serves as a suff1c1ent reference The maneushyver lS targeted to ach1eve the mldcorr1dor entry target Ilne andtlmed to result 1n a deslgnated recovery area

It 1S ObV10US for abort deC1S1ons early 1n the TLI + 90 m1nute t1meshyframe that a GampN SPS burn should be performed In order to keep theTLI abort procedures cons1stent and w1th emphasls on slmpl1c1ty theprocedures here reflect a SCS SPS abort burn to cover the full abortdec1s1on t1meframe

A m1dcourse correct1on for corr1dor control after a TLI abort may bedeS1red 1f the SPS burn d1d not meet expectat1ons The TLIabortprocedures 1n th1S sect10n adapt to the normal lunar return tlmel1neand procedures pr10r to the f1nal MCC

-52-

61 TLI PREPARATION PROCEDURES

GET = 150

CRO AOS(___)

CRO LOS( )(22142)

5100

Don Helmets amp Gloves

XLUNAR - INJECT (verify)EDS PWR - on (venfy)EMS FUNC - OFF (verlfy)EMS MODE - STBYEMS FUNC - IW SETVHF RNGEMS MODE - NORMALSet ~V indo to +15868 fpsEMS FUMC - ~V Test

SPS THRUST Lt - onoff (10 sec)~V lnd stops at -01 to -415

EMS MODE - STBYEMS FUMC - ~V SETVHF RNGSet ~VC

EMS FUNC---~~V=----

GDC ALIGNFDAI Select - liZcb SECS LOGIC (Z) - close (verify)cb SECS ARM (Z) - closeSECS LOGIC (Z) - on (up)MSFN Conflrm GO for PYRO ARM (If pass)SECS PYRO ARM (Z) - on (up)TRANS CONTROL PWR - ONROT CONTR PWR NORMAL (Z) - ACDC(verlfy)ROT CONTR PWR DIRECT (Z) - MNAMNBLV INnGPI - SIISIVB (venfy)LV GUID - IU (venfy)cb DIRECT ULLAGE (Z) - closedSet EVENT TIMER to 5100Begin MONITOR For TB6

CMP to Couch

TB 6 - SII SEP Lt on (TIG-9 mln 38 sec)KEY V83E

SET ORDEALFDAI Z ORB RATE at 180 0 0SII SEP Lt out (38 sec later)Start DET COUNTING UPSC CaNT - SCS (verify)MONITOR LV TANK PRESS

~P lt 36 psid (OXID gt FUEL)~P lt Z6 psid (FUEL gt OXID)

EMERGENCY CSMLV SEP UP TLM CM - BLOCK (verify)UP TLM IU - BLOCK (venfy)

-53-

+45degPY))0middot sec PY

lOK nmltHAlt25K nm

Two phas~ng mnvrs two SPS mnvrs to circular~ze at 150 nmearth orb~t

CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ssion 4K nmltHAltlOK nm CSM amp1M - Two phasing mnvrs two SPS mnvrs to circularize at 150 nm earth orb~t CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ss~on

CSM amp 1M - Two phas~ng mnvrs APS burn todepletion th~rd phasing mnvrSPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn tosem~sync orb~t

25K nmltHAlt40K nm CSM amp 1M - Two phasmg mnvrs APS burn to depletion third phas~ng mnvr SPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn to sem~sync orbit HA)40K nm DPS ava~l - DPS LOll circularize with SPS

DPS not ava~l - Lunar flyby or CSM only to lunar orbit (if reqd gtV lt4000 fps)

V37E 47E (check b~as) Record -=--rshy(Limit 98 fpsmm)

( 1fps)tVXYZN62EVIHDOTHPAD (fpsfpslnm)MONITOR VI ( ) at ECO

SCS TVC SERVO PWR 1 - ACIMNA2 - OFF

TAPE RCDR - CMD RESETHBREMS MODE - NORMAL

SIr SEP Lt - ONTLI Inhib~t S~gnals w~11 not be honored after 5942

SIVB ULLAGE BeginsSII SEP Lt - off (TIG - 18 sec)SIVB FUEL LEADSIVB ULLAGE d~scont~nues

LV ENG I Lt - onSIVB IGNITION ( GETI)LV ENG I Lt - off - -shyMONITOR THRUST amp ATTITUDEMONITOR LV TANK PRESSSIVE ECO (Lt on) (BEGIN TB7)

EMER SIVE CUTOFF AT 6 SEC PAST BURN TIME IF VI ATTAINEDTHC CCW ampNEUTRAL IN 1 SEC or SIISIVB sW - LV STAGEPremature Shutdown HAlt4K nm CSM amp 1M -

5700

58205836

F 16 835800

F 16 62

5838594259525955595900000002SUNRISE(___)

HAW AOS(__=_) KEY VERB (freeze d~splay)

SIVB ATT HOLD 20 sec amp BEGIN VENTINGSIVB NNVR TO ORB RT (HDS DN) (3middot sec)

Record VI -c---HDOT _

HPAD _

KEY RLSEF 16 62

F 16 83

HAW LOS(__=-)

KEYmiddotRLSE~VXYZ (lfps)

Record ~VX---_

~vy

WZ--

AVC---_

TAPE RCDR - off (ctr)EMS MODE - STBYEMS FUNC - OFFSECS PYRO ARM (2) - SAFE

PRO

BURN STATUS REPORT

____--~TIG

BT------VGX____-R

-----P----_Y

REMARKS

_____VI

______--HDOT______--H______---AVC______---FUEL_______OXID

_______UNBAL

F 3708=00 OOEGOS AOS CMP TO LEB

(-=-=-)

0000

0003

0005

0014

0100

-55-

62 TLI 10 MIN ABORTSECS LOGIC (2) - on (up)SECS PYRO ARM (2) - ARM

TRANS CONTR - CGH (4 sec) amp +XDET RESET (verlfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS GMD-ON

TRANS GONTR - neutral then +X for10 sec

SIVBGPI s~ - GPIExcesslve rates 6V THRUST A - NORMAL SPS THRUST - DIRECT When rates damped 6V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

TRANS CONTR +X - OFFV37E OOE

PITGH UP to LOGAL VERT (+X axlSto~ard the earth)

RATE - LOWBMAG MODE (3) - ATTIRATE 2EDS PHR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SEGS ARM (2) - opencb EDS (3) - open

TRANS CONTR -X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (180deg)P (199deg)Y (0deg)

RETRO UPDATEGETI _

JV _VG

Jtb ---GET 400K _

05G _GET DROGUE _

ENTRY P _R _

Y_--

0945

-56-

ALIGN HORIZ ON RET +1 MKGMBL CHECK (T11lle Pentattlng)MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conflnn)cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FUMC - JV SETVHF RNGSET JV from chartE~S FUMC - JVEMS fODE - NOIDlAL

lV THRUST A - NORMALV37E 47E (THRUST fONITOR)

F 16 83 lVXYZ (1 fps)

0950

1000

NOTE For aborts durlng 1st mln of TLIKEY V82E F 16 44 (HaHpTff)Burn untll Hp lt 19NM

TRANS CONTR +X

THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN JV reqdJV THRUST (2) - OFFReport cutoff

cb SPS P2 Y2- closeGfBL MTRS (4) - OFF (LMP Confinn)TRANS CONT PWR - OFFTVC SERVO PWR (2) - OFFMN BUS TIE (2) - OFFcb SPS P1amp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREIf est time to EIltOl5500 omlt fCC andenter the SUPERCIRC CKLIST as early as pos-slb1e Pg ~2~3~ __If est time to EI)Ol5500 anticlpate afCC Enter the ENTRY PREP CKLIST at step 9pg 18

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

-2tl C

l I W gt- ~-4

z laquo I I- 0 -6

l- I J u gt- ~-8

z w w -10

~_ONSANT

9O

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SHO

OT

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LIF

TV

EC

TOR

OR

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TATI

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LIN

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SH

ALL

OW

TAR

GE

TLI

NE

STE

EP

TAR

GE

TLI

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gU

ND

ERSH

OO

TBO

UN

DAR

Y

RE

EN

TRY

CO

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IDO

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26

28

30

32

34

RE

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TRY

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LOC

ITY

VE

1-F

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73

8X

03

-i- rtREQUIRED PITCH GIMBAL ANG LETO OBTAIN HOR-IZON AT 317

DEGREES IN wiiiiDOW

260

z~I- ~ i5 24000

1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

-I

-1-

NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

I LU HD~-

LUHD

lt0 120UJ0

~

80 HOLD PRESENT TRIMgt LU HD013

~Y~HOIgtlt

TOP OF WINDOWa 40to

31 7 SCRIBEaaI

80 TTOM OF WINDOWi= 0

0--ltoa

-40t-z

~~~Uw w u lt0 -80

HOLO PRESENT TRIlJCl

LOHU0 lt0

J gt -120 HOLD 059 TRIMlt0 z

LDHUlt0 FIELD OF VI S10 NLDHU LIFT-DOWNHEADS -UPLUHD LIFT-UP HEADS-DOWN

~~H~-160 q - P63 LIMITI- NOrE-VALIO ONLY FO~t~--

LUNAR RETURN VELOCITY

plusmnl8020 244middot 8 12 16

TIME TO 400K FT ALTITUDE-MIN

4

P37

LONG

ITUD

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RREC

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TOOB

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1350

NM

ENTR

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340

344

348

352

356

364

368

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AA

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-60

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6

1000

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00 60

00 i50

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120

200

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6V-

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240

320

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1968

400050

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2627

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Cll-

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120

200

241)

320

400

441)

520

TlI

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-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 29: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

5 F 50 25

4300m

(-1700)

45 oOm(-1500)

500Om(-1000)

6 F 06 61

-26-

P62 - CMSM SEP amp PRE-ENTRY MNVRCAUTION Call No EXT Verbs In P62

00041 REQUEST CMSM SEPSC CONT - SCSFREE

COMPARE PITCH ATT WITH PAD DATA ---0=-

(W~thLU 5deg)YAW - 45deg OUT-OF-PLANE (LEFT)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTIRATE 2MN BUS TIE (2) - ON (ver~fy)

PRIM GLY TO RAD - BYPASS (verlfy)CM RCS LOGIC - ON (venfy)SECS LOGIC (2) - on (up)SECS PYRO ARM - ARMCMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 ps~a

CM RCS LOGIC - OFFSECS PYRO ARM (2) - SAFEMonltor VMAB

If lt25 vdc go to EMERGPOWERDOWN pg E6-l

AUTO RCS SEL AC ROLL (4) - OFFAUTO RCS SEL CM 2(6)-OFFAUTO RCS SEL CM 1(6)-MNAYAW back to 0degPITCH TO HORIZ TRACK ATT

ROLL - 0deg (LIFT UP)PITCH - 400K Horiz Mark (317deg)YAW - 0deg

ATT DB - MAXMAN ATT PITCH - ACCEL CMDEMS DATA - Ver~fy

EMS FliNC - ENTRY (ver~fy)

EMS MODE - NORMALcb SPS PampY (4) - openMAINT HORIZ TRK

PRO (Act ENTRY DAP)

IMPACT LATLONGHDSDN (01deg01deg-00001)PRO

7 POSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axis beyond 45deg of Vel vector)

8 06 64

58middot00m(-0200)

9

05G tlme(+0 )

(--=---)

06 68

-27-

P63 - ENTRY INIT

GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PIJR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRmDHORIZ CKPltch error needle goes toward

zero approachlng OSG tlmeMAN ATT (PITCH) - RATE CMD

If CMC lS GOBMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS I

FLY BETA If CMC NO GO ilt

1 SC CaNT - SCS I

FLY EMS k

p64 - ENTRY POST 05G

RTOGO AT 05G AGREES HITH EMS-venfyHORIZ CK05G Lt - ON (EMS START)

No EMS START wlthln 3 sec ~ EMS MODE - BACKUP VHF RNG c

05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds Llft DN

NNVR Llft DNEMS GONO GO

G-V Plot wlthln IlmltsRng ctr dwn 60plusmn7 durlng 10 sec

perlodMonltor G-meter for

convergence wlth pad data (Do)(Vlt27K fps) Go to 13

-28-

P65 - ENTRY - UP CONT (Vgt27K fps)

10 F 16 69 BETA (01middot) _DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT lt~ SC CONT - SCS FLY EMS

PRO

11 06 68 BETAVIHDOT (OIdegfpsfps)(VltV1+500 fps amp RnOT Neg) Go To 13

P66 - ENTRY - BALLISTIC (D(DL)

12 06 22 DESIRED GMBL ANGLES RPYMoultor horlz +12middot of 317middot mark

P67 - ENTRY - FINAL PHASE (02G)

13 06 66 BETACRSRNG ERRDNRNG ERR(010 1um 1um)

KEY VERBRecord DNRNG ERR _KEY RLSEMoultor l~ft vector ou RSI amp FDAI

16 67 RTOGOLATLONG (Vrel=1000fps)(lumOldegOldeg)

SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOWNMonitor a1t~meter

Go To EARTHLANDING pg ---4L5 _

-29-

53 GampN HYBRID DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL tV1 V37E 30E

2 F 06 33 GETI(ACCEPT) PRO (hrm~n Olsec)(REJECT) LOAD DESIRED GETI

3 F 06 81 tVXYZ (LV) (lfps)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

4 F 06 42 HAHPtV (lnm lfps)Record tV

(ACCEPT) PRO(REJECT) Reselect P30 or P27 Load new paramo

5 F 16 45 MTFIMGA (marksm~n-secOlO)

MGA -00002 ~f k

k lMU not al~gned

SET DETPRO

6

7

8

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (Pull)PLSS 02 vlv - FILL02 8M SUPPLY vlv - OFFCAB PRESS REL vlv (2) - NORMcb ELS (2) - closecb SECS ARM (2) - closecb SECS LOGIC (2) - close (ver~fy)

AUTO RCS SEL CM (12) - MNA or ~ffiB

(hftoff conhg)ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM (AampB) - OFF

CMP to Couch

9

10

11

-30-

MNVR TO PAD BURN ATTLOAD DAPBMAG MODE (3) - RATE 2SC CONT - CMCAUTOATT DB - MINMAN ATT (3) - RATE CMD

v62E

v49E

12 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLES

PRO

13 F 50 18 REQ MNVR TO FDAI RPY ANGLES (01deg)(AUTO) PRO(MAN) SC CONT - SCS

BMAG MODE (3) - RATE 2MNVR To 15

14 06 18 AUTO MNVR TO FDAI RPY ANGLES (01deg)

15 F 50 18 REQ TRIM TO FDAI RPY ANGLES (01deg)(TRIM) Go to 13(ByPASS) ENTR

16

17

CHECK BORESIGHT amp SKT STARSOPT MODE - CMCOPT ZERO - OFF

v41 N91E

18 F 21 92 SHAFTTRUN (01deg 001deg)Load SXTS angles

19 41 OPTICS DRIVECheck SKT STAR

OPT ZERO - ZEROCheck BORESIGHT STAR (~f ava~l)

20 V25 N17E (01deg)Load Pad Data GMBL Angles

for CM BURN ATTATT SETtw - SET

to PAD DATA GMBL ANGLESfor CM BURN ATT

21

22

-31-

PHR REDUCTIONHGA PHR - OFFFC PUMPS (3) - OFFVerify s~ngle su~t compr oper loads

balancedFC 2 MN AampB - OFFS BD PiR AMP - LOWcb ECS RAD CONTHTR (2) - opencb HASTE H20URINE DUMP HTRS(2)- opencb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANMN BUS TIE (2) - ONTVC SERVO PHR 1 - AC1MNAGMBL MTR (4) - START

p41 - RCS THRUSTINGV37E 41E

23 F 50 18 REQ MNVR TO LCL HORIZ (HDS ON)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CMCAUTOPRO To 24

(gtfANDAP) BMAG MODE (3) - RATE 2SC CONT - CMCHOLD

V62EMNVR To 25

24 06 18 AUTO MNVR TO FDAI RPY

25 F 50 18 REQ TRIM TO LCL HORIZ (01deg)ALIGN SC ROLL

(AUTO TRIM) PRO To 24(BYPASS) ATT DB - MIN

RATE - LOHMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTlRATE 2

ENTR

550Om26 06 85

59middot2527

-32-

VGXYZ (1fps)RECHECK BORESIGHT STARTRANS CONIR PWR - on (up)EMS MODE - STBY (ver~fy)

EMS FliNC - bV SETVHF RNGSET (IV for SM BURN _EMS FliNC - bVS BD ANT - OMNI CSECS LOGIC (2) - ONMSFN conhrm Go for PYRO ARMSECS PYRO ARM (2) - ARMCM RCS LOGIC - ON (ver~fy)

DSKY BLANKS

593028 16 85 VG XYZ (AVE G ON) (lfps)

RHCs amp THC - ARMEDLIMIT CYCLE - OFFTAPE RCDR - CMD RESETHBREMS MODE - NORMAL

000029 F 16 85 REQ NULL VG XYZ (lfps)

BURN EMS bV CTR TO ZERORESET DET amp COUNT UP

If SM ONLY burn go to step 32THC - LOCKEDSC CaNT - SCSFREERATE - HIGHPRIM GLY To RAD - BYPASS (ver~fy)

MN BUS TIE (2) - ON (ver~fy)

CMSM SEP (2) - on (up)CSMLM FNL SEP (2) - on (up) (verify)CampW MODE - CMRCS TRNFR - CMCM RCS LOGIC - OFF

Momtor VM ABIf lt25 vdc go to EMERGPOWER DOWN Pg E6-l

V63E

If CMC NO GO FDAI SOURCE - ATT FDAI SEL - 1 or 2 ATT SET - GDC

SET

-33-

~Uili ATT PITCH - ACCEL CMDFDAI SCALE - 55MNVR TO CM BURN ATT (NULL ERR NEEDLES)

R 0degPY --00--

30

31

CM RCS BURNRHC III-ContJnuous PJtch DownRHC HZ-Module PJtch to null needlesBURN VGZ TO ZERO

If only 1 RHC Pulse + P=5deg from retro att MaJnta~n rates lt3degsec

BURN COMPLETION ATllV CTR= or DET= _

V8ZE

32 F 16 44 HAHPTFF (1nmffiJn-sec)Check HP-

If gt Pad data contJnue burnuntJ1 lt Pad

PRO

33 F 16 85 VGXYZ (Ups)Read VG resJduals to MSFN

(HYBRID) PRO to 34(SM ONLY BURN)

PROF 37 ODE

EI-1500 V37E 47EF 16 83 twx Y Z (Ups)

SC CONT - SCSFREEMAN ATT (PITCH) - RATE CMDRATE - HIGHPRIM GLY To RAD - BYPASS (verJfy)MN BUS TIE (2) - ON (verJfy)CMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verJfy)Campl MODE - CMRCS TRNFR - CMCM ReS LOGIC - OFFSECS PYRO ~I (2) - SAFE

-34-

PROMonitor VMAB

If lt25 vdc go to EMERGPOWER DOWN

34 F 37 OOEPCM BIT RATE - LOWATT DB - MAXEMS MODE - STBYEMS FUNC - OFF

Go To EARTH ORBIT ENTRY pg _--40-__

-36-

8 SPS THRUSTING PREPCYCLE CRYO FANSSPS GAGING - ACI (ver~fy)

PUG MODE - NORM (venfy)BMAG MODE (3) - RATE 2tv CG - CSMCMC MODE - FREEAUTO RCS SEL (16) - MNA or HNB

(hftoff conbg)SC CONT - CMCAUTO

9 MNVR TO PAD BURN ATTV62E

10 V49E

11 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLESPRO

12 F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) PRO(HAN) SC CONT - ses

MNVR to 14

06 18 AUTO MNVR TO FDAI RPY ANGLES13

14 F 50 18 REO TRIH TO FDAI RPY ANGLES(TRIM) Go to 12(BYPASS) ENTR

15 BORESIGHT STAR CHECK

16 V37E 40EOPT PWR - OFF

17 F 50 18 REQUEST MNVR TO FDAI RPY ANGLES (01deg)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CHCAUTOPRO to 18

(MANDAP) BMAG HODE (3) - RATE 2SC CONT - CMCHOLDMNVR to 19

(HANseS) se eONT - sesMNVR to 19

-35-

54 NORMAL DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL ~V

1 V37E 30E

2 F 06 33 GETI (hrm~nOlsec)

(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

3 F 06 81 ~VXYZ (LV)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

( lfps)

4 F 06 42 HAHP~V (1nmlfps)Record W

(ACCEPT) PRO -----(REJECT) Rese1ect P30 or P27 Load new pa~am

5 F 16 45 MTFIMGA (marksmln-secOldeg)MGA -00002 If ~ lMU not a1~gned

SET DETPRO

6

7

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY v1v - OFFCAB PRESS REL v1v (2) - NORMcb ELS (2) - close (verify)cb SECS ARM (2) - close (ver~fy)

cb SECS LOGIC (2) - close (verlfy)AUTO RCS SEL CM (12) - ~mA or MNB

(l~ftoff conf~g)

ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM AampB - off (ctr)

18

-37-

06 18 AUTO MNVR TO FDAI RPY ANGLES (01 0)

19 l 50 18 REOUEST TRIM MNVR TOALIGN SIC ROLLGDC ALIGN

FDAI RPY ANGLES(010

)

+54-00m(-06-00)

TIG-5mJn

5500m(-0500)

TVC CHECK amp PREPcb STAB CONT SYS (all) - closecb SPS (12) - closeATT DB - MINRATE - LOl~

LIMIT CYCLE - ONMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE 2ROT CONTR PWR DIRECT (2) - OFFSCS TVC (2) - RATE CMD

If SCS SCS TVC (2) - AUTO SC CONT - SCS ~

TVC GMBL DRIVE PampY - AUTOMN BUS TIE (2) - ONTVC SERVO PWR 1 - AC1MNA

2 - AC2MNBTRANS CONTR PWR - ONROT CONTR PWR NORMAL 2 - ACRHC 2 - ARMED

HORIZ CHK - HorJz on 12deg wJndmlmark (LJffiJt +3 0 PNGCS GONO GO)

If NO GO set tw 180 0 180deg0 0

Track horJz wJth 24deg wJndow markAt TIG-2 mJn Ahgn GDC

PRIMARY TVC CHECKGMBL MOT P1-Y1 -STARTON(LMP confJrm)

If SCS verJfy Thumbwheel TrJmTHC - CWVenfy NO MTVC

SEC TVC CHECKGHBL MOT P2-Y2 -STARTON(LMP confJrm)SET GPI TRIHVenfy MTVCTHC NEUTRALGPI returns to 00 (CMC) or trJm (SCS)ROT CONT Pl~ NORM 2 - ACDC

(TRIM) Go to step 17(BYPASS) BMAG MODE(3) - ATTIRATE2 (ver1fy)

ENTR

-38-

20 F SO 25 00204 GMBL TEST OPTION(ACCEPT) SC CONT - GMC (ver~fy)

PROMonitor GPI Response

0020-2000020-200Tr~m

TEST FAIL SC CONT - SCS SCS TVC (2) - AUTO

(REJECT) ENTR

21 06 40 TFIVG~VM (m~n-sec1fps)

PROG ALM - TIG s1~pped

V5N9E 01703

KEY RLSE To 21 ROT CONTR PWR DIRECT (2) - MNABSPS He v1vs (2) - AUTO (ver~fy)

LIMIT CYCLE - OFFFDAI SCALE - SOIScb SPS P2Y2 - open (for cr~t burn)

5800(-02 00)

5925(-0035)

59middot 30(-0030)

06 40

59XX(-OOXX)

AV THRUST A(B) - NORMALTHC - ARMEDRlIC (2) - ARMEDTAPE RCDR - GID RESETHBR

DSKY BLANKS

(AVE G ON)EMS MODE - NORMAL

TFIVG~VM (m~n-seclfps)

CHECK PIPA BIAS lt2fps for 5 sec

ULLAGE AS REQ

IF NO ULLAGE DIR ULLAGE PB - PUSH~

CONTROL ATT WRlIC MONITOR AVM (R3) COUNTING UP

5955(-0005)

F 99 40 ENG ON ENABLE REQUEST(AUTO IGN) PRO AT TFI gt0 sec(BYPASS IGN) ENTR to 24

22 0000 IGN

-39-

If SCS - THRUST ON PB - PUSH

06 40 TFCVG~VM (m~n-seclfpslfps)

~F 97 40 SPS Thrust fall ~

~(RESTART) PRO To IGN (RECYCLE) ENTR To TIG-05 sec

SPS THRUST LITE - ONMONITOR THRUSTING

Pc 95-105 pSlaEMS COUNTING DOWNSPS IN3 v1vs (4) - OPENSPS He v1vs tb (2) - graySPS FUELOXID PRESS - 175-195 pSlaPUGS - BALANCED

PROG ALARM V5N9E 01407 VG INCTHC - CW FLY MTVC

ECOEMER SPS CUTOFF J

AV THRUST (2) - OFF

23 F 16 40 TFC(STATIC)VG~VM (mln-seclfps)~V THRUST AB - OFF

SPS IN3 v1vs (4) - CLOSEDSPS He tb (2) - bp

cb SPS P2Y2 - closed (verlfy)TVC SERVO PHR - AC1MNA (venfy)TVC SERVO PWR 2 - OFF

PRO

24 F 16 85 VG XYZ(CM) CUps)NULL RESIDUALSRECORD ~V CTR amp RESIDUALS I1VCEMS FUNC - OFF VGXEMS MODE - STBY VGYBMAG MODE (3) - RATE 2ATT DB - MAX VGZTRANS CONT PHR - OFF

PRO

25 F 37 V82E

26 F 16 44 HAHPTFF (lnmm~n-sec)

R3-59B59 HP gt494 nmPRO

27 F 37 OOE

-40-

55 EARTH ORBIT ENTRY

1 Venfy CMSMR __

P_shyY_-

SEP ATT(180deg)

(0deg )

2

3

4

EMS INITIALIZATIONEMS FUNC - RNG SETSET RNG TO PAD DATA RNGEMS FUNC - VA SETSlew scroll to pad data VIOEMS FUNC - ENTRY

RSI ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on(up)GDC ALIGN PB - PUSH amp HOLDYAW tw - Pos1tion RSI thru 45deg amp

back to LIFl UPGDC ALIGN PB - RELEASEEMS ROLL - OFFAl1gn GDC to lMU

PWR REDUCT (Norm Deorb Only)HGA PWR - OFFFC PUMPS (3) - OFFVer1fy s1ngle suit compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - Lowcb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2)-openlOb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MAN

-41-

P61 - ENTRY PREP

5 V37E 61E05 09 01427 - ROLL REVERSED05 09 01426 - IMU UNSAT

6 F 06 61 IMPACT LAT LONG liDS UPDN (+-)(01 0

010

+00001)

PRO

PAD VALUESLATLON==G------liDS UP DN _

7 F 06 60 GMAXV400KGAMMA EIRecord

GMAXV400K----GAMMA EI _

PRO

8 F 06 63 RTOGO (1nm) PAD _VIa (fps) PADTFE (mln-sec) ----Compare wlth MSFN for PGNS GONO GONO COMM SET RTOGO amp VIO IN EMS amp

INITIALIZE(ACCEPT) PRO(RECALC) V32E to 8

-42-

P62 - CMSM SEP amp PRE-ENTRY MNVR

9 F 50 25 00041 REQUEST CMSM SEPSC CONT - SCSFREEYAW - 45deg out-of-plane (left for RCS

nght for SPS)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE2PRIM GLY to RAD - BYPASS (verlfy)SECS LOGIC (2) - on (up)MSFN conflrm GO for PYRO ARMSECS PYRO ARM - ARMMN BUS TIE (2) - ON (verlfy)CMSM SEF (2) - ONCSMLM FNl SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 pSlaCM RCS LOGIC - OFFSECS PYRO ARM - SAFEMonltor VMAB

If lt25vdc go to EMERG POWERDOWN Pg E6-1AUTO RCS SEL AlC ROLL (4) - OFFAUTO RCS SEL CM 2(6) - OFFAUTO RCS SEL CM 1(6) - MNA or MNBYAW back to 00

PITCH TO ENTRY ATTROLL 0deg (LIFT UP)PITCH - HORIZ on 317deg MARK (400K)YAW 00

ATT DB - MAXMAN ATT (PITCH) - ACCEL CMDEMS DATA - VerifyEMS FUNC - ENTRY (verlfy)EMS MODE - NORMALMAINTAIN HORIZ TRK

PRO (Act ENTRY DAP)

10 F 06 61 IMPACT LAT LONG HDSDN(010 010 -00001)

PRO

11 FOSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axlS beyond 45deg of Vel vector)

-43-

P63 - ENTRY INIT

12 06 64 GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PWR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRHORIZ CKP~tch error needle goes toward

zero approach~ng 05G t~me

MAN ATT (PITCH) - RATE CMDIf CMC ~s GO

BMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS FLY BETA If CMC NO GO ~

SC CONT - SCS~

FLY EMS RCS Deorh Roll HDS UPTRACK HORIZ w~th 29deg w~ndow mk

P64 - ENTRY POST 05G

13

05G t=elt+0___)

06 68

RTOGO AT 05G AGREES WITH EMS - venfyHORIZ CK05E Lt - on (EMS start)

No EMS start w~th~n 3 secsEMS MODE - BACKUP VHF RNG 05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds L~ft DN

NNVR L~ft DNEMS GONO GO

G-V Plot w~th~n llm~ts

Rng ctr dwn 60 + 7 durlng 10 sec per~od

Mon~tor G-meter forconvergence wlth pad data (Do)

(Vlt27K fps) Go To 17

-44-

P65 - ENTRY - UP CONT (Vgt27K fps)

14 F 16 69 BETA (01deg)DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT~

SC CONT - SCS FLY EMS

PRO

15 06 68 BElA VI HOOT (01deg fpsfps)(VltVL +500 fps amp RDOT Neg) Go To 17

p66 - ENTRY - BALLISTIC (DltDL)

16 06 22 DESIRED GMBL ANGLES RPY (01deg)Mon~tor hor~z +12deg of 317deg mark

P67 - ENTRY - FINAL PHASE (02G)

17 0666 BETACRSRNG ERRDNRNG ERR (Oldeglnmlnm)KEY VERBRecord DNRNG ERR _KEY RLSEL~m~t +100nm from PAD DRE

Mon~tor l~ft vector on RSI amp FDAIF 16 67 RTOGOLATLONG (Vre1=1000fps)

(lnm 010 01deg)SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOlfflMon~tor altimeter

Go To EARTHLANDING pg _I4L5__

-45-

56 EARTHLANDING

90K STEAM PRESS - PEGGED50K CABIN PRESS REL vIv (2) - BOOSTENTRY

SECS PYRO ARM (2) - ARM

40K(90K + 63s)

CM UNSTABLE RCS CMD - OFF ~ 40K APEX COVER JETT PG-PUSH DROGUE DEPLOY PG - PUSH (2 secafter apex cover Jett)

30K ELS LOGIC - ON (up)ELS - AUTO

24K RCS hsable (auto)(90K+92s) RCS CMD - OFF

Apex cover Jett (auto)APEX COVER JETT PB - PUSH

(WAIT 2 SECS)Drogue parachutes deployed (auto)

DROGUE DEPLOY PB - PUSH~

If Drogues FallELS - ~ ~Stablllze CM 5K MAIN DPLY PB - PUSHELS - AUTO

235K Cabln Pressure lncreaslng (Drogues + 50s)If not lncreaSlng by 17K CABIN PRESS REL vlv (RR) - DUMP

-46-

10K Maln parachutes deployedMAIN DEPLOY PB - PUSH (wlthln 1 sec)VHF ANT - RECYVHF AMA - SIMPLEXVHF BCN - ONCABIN PRESS REL v1v (2) - CLOSEDIRECT 02 vlv - OPENCM RCS LOGIC - on (up)CM PRPLNT - DUMP (burn audlb1e)Monltor CM ReS 1amp2 for He press decrease

NO BURN or PRESS DECREASE USE BOTH RHCs DO NOT FIRE PITCH JETS

CM PRPLNT-PURGE (to zero He press)CM RCS He DUMP PB - PUSH RHC (2) - 30 sees NO PITCH k

STRUT LOCKS (2) - UNLOCK

cb FLT amp PL BAT BUS ABampBAT C (3) - closecb FLT amp PLT MNA amp B (2) - opencb ECS RAD HTR OVLD (2) - opencb SPS PampY (4) - open

3K CABIN PRESS REL v1v (RH) - DUMP (after purgecompleted)

FLOOD Lts - POST LDGCM RCS PRPLNT (2) - OFFROT CONTR PWR DIRECT (2) - OFF

800 CAB PRESS RELF vlv - CLOSE (latch off)MN BUS TIE (2) - OFF

AFTER LANDINGcb MAIN REL PYRO (2) - closeMAIN RELEASE - on(up)

Go to POSTLANDING pg _47L-__

I

2

3

-47-

57 POSTLANDING

STABILIZATION VENTILATION COMMUNICATIONS

DIRECT 02 vlv - CLOSE

Stablllzation after landlngELS - AUTO (verlfy)cb MAIN REL PYRO (2) - close (venfy)MAIN RELEASE - on (up) (verlfy)S~CS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb BAT RLY BUS (2) - open

No contact w1th recovery forcesVHF AM AampB - off (ctr) ~

VHF AM Rev ONLY - A cb PL VENT - closecb FLOAT BAG (3) - closecb UPRIGHT SYS COMPRESS (2) - closeIf Stable II

FLOAT BAG(3)-FILL t1ll 2 m1n afterupr1ght then - OFF

VHF AM AlB amp BCN - OFF whlle lnvertedIf Stable I

After 10 M1n Coollng Per1odFLOAT BAG (3) - FILL 7 mln then OFF

Post Stab1lizat1on And Ventllat10nPL BCN LT - BCN LT LOWPL VENT vlv - UNLOCK (Pull)Remove PL VENT Exh CoverPL VENT - HIGH or LOWPL DYE MARKER - ON (swlmmer comm)Release foots traps and_restralntscb MNA BAT BUS A amp BAT C (2) - opencb MNB BAT BUS B amp BAT C (2) - opencb FLT amp PL BAT C - opencb PYRO A SEQ A - opencb PYRO B SEQ B - open

EACH HR - CHECK DC VOLTSgt 275 V If Notmiddot cb FLT amp PL-BAT BUS AampB (2) -open cb FLT amp PL BAT C (1) - open GO TO LOW POWER CHECKLIST

Unstow and lnstall PLV DISTRIB DUCTDeploy grappllng hook and 11ne 1f req

4

-48-

Post Landing Communlcatl0nsVHF ANT-RECY (venfy)VHF BCN - ON (verlfy)

If no contact ~lth recovery forcesperform VHF BEACON Check

MONITOR VHF BEACON transmlSSlonnth VHF AM B Rcvr andor Su)vlval

TransceiverkVHF Beacon not operatlng ~connect Surv~val TranscelVer to antcable behlnd VHF ant access pnland place radio ln BCN mode

LOW POHER CHECKLISTVHF BCN - OFFVHF AM (3) - RCVFLOOD Lts - OFFVHF AM AampB - off (ctr)VHF AM RCV ONLY - A (venfy)COUCH LIGHTS - OFFPOSTLANDING VENT SYS mlnlmlze useSURV RADIO - plug mto VHF BCN ANT cableconn behind VHF ant acess pnl amp turn radloon l-n BCN mode

EGRESS PROCEDURES

CMPCDRLMPCDR

CMPCDRCMP

LMPLl1PCDR

STABLE IDlsconnect Umblll-calsNeck darn onCenter couch - 270 0 positionArmrests stowedConnect raft to SIC l-f desl-red wlth

green lanyardConnect raft ~hl-te lanyards to SUltS amp

lnflate water wlngs when eXltl-ngHATCH PISTON PRESS vlv - PRESS (Outbd)Slde Hatch openedPL VENT - OFFcb Pnl 250 (all) - openEgress with 11feraftPut hardware klt outEgress

or CDIPALL

CMF

CDRCMF

CDR

LMF

CMFCMP LMFCMP

UlP

CDR

-49-

STABLE IIcb CREW STA AUDIO (3) - openD~sconnect umb~1~ca1s

Release foots trapsRelease restra~nt harnessCouch seat pans (3) - 170 0 pos1t10nArm rests stowedSurv1va1 k~ts removed from stowageConnect life raft ma~n1~ne to CDR or SicConnect f~rst wh~te lanyard from

11fe raft to suitConnect th~rd wh~te lanyard from

l~fe raft to SU1tConnect rucksacks together to yellow

lanyard on raft bagPRESSURE EQUALIZATION vlv - OPENRemove and stow fwd hatchEX1t feet f1rst w1th rucksacks when clear

of siC 1nflate water w1ngs and raftExit feet f1rst when clear of SiC

1nflate water w1ngsEX1t feet f1rst when clear of sic

1nflate water w1ngs

-50-

60 TLI ABORTS

TLI Aborts are conta~ned ~n the ESD s~nce the bulk of the funct~ons

concern entry preparat20ns and performance Th~s allows a s2nglesource of procedures for procedure rev2ew val~dat~on checkout andtra~n~ng These procedures ~ncorporate TLI preparat20ns as found ~n

reference 6 w~th the TLI Abort Procedures and these t~e 2nto normallunar return Entry Procedures found ~n sect20n 5 The guidel~nes

for th~s cont2ngency are spec2f2ed 2n reference 7

In2t2al preparat~ons for TLI pos2t20n the necessary system sW2tches2n add~t~on to perform~ng an EMS ~V test and a GDC al~gnment Afterthe DET ~s set for mon2tor2ng TB6 the CMP ~ncreases the 12ght levelof the LEB DSKY to max~mum and returns to the h2s couch Th2s 2Sdone so that the LEB DSKY can be observed ~n the event sunl~ght orreflect20ns wash out the ma2n d2splay panel DSKY dur2ng cr2t2calmaneuvers The crew then straps ~n and prepares for mon2tor~ng TB6as 2nd2cated by the SII SEP L~te The t2mes se~uence of procedures2S keyed on th~s d~splay and ~ncludes the DET START funct~on andSIVB IGNITION Dur2ng the burn the crew mon2tors the FDAIs foratt~tude excurs20ns and abnormal rates report~ng status checks toM~ss2on Control at d2screet t~mes dur2ng the maneuver Upon SIVBSHUTDOWN the eMP records the DSKY d~splayed performance parametersand awa2ts ground conf2rmat~on

The rat~onal for TLI aborts ~s descr~bed 2n reference 7 A summar2shyzat20n 2S extracted to prov2de background and gu2de12nes 2n th2sdocument The abort procedures cover aborts 10 m2nutes after conshyt2ngent SIVE shutdown and aborts 90 m2nutes after normal SIVE shutshydown t2me

The 10 m~nute TLI abort ~s des2gned to be used dur~ng TLI ~n theevent a spacecraft problem develops Wh2Ch can result 2n catastrophe2f ~mmed~ate act~on 2S not taken If the s~tuat20n perm~ts the crewshould always allow the SIVB to complete TLI at wh~ch t~me the groundand crew can perform a malfunct~on analys~s to determ~ne ~f an abort~s adv~sable If a fa~lure occurs that necess2tates the shutdown ofthe SIVB and the ~u~ck return of the crew to earth th~s abort ~s

des~gned to be as ~nsens~t~ve to execut~on errors as poss~ble andst21l be targeted to m2dcorr2dor The burn att~tude w~th the f~ed

hor~zon reference ~s a constant value for any shutdown t~me Theburn durat~on 2S a funct20n of shutdown t2me and 2S ava21able fromcrew charts S~nce the pr~mary purpose of th~s abort ~s to returnto earth as qU2ckly as poss2ble there are no restr2ct20ns as toland~ng locat~on However ~f the t~me to EI is greater than abouttwo hours a midcourse correct20n should be ant~c~pated

The 90 m2nute TLI abort 2S to be used 2f a cr2t2cal subsystem malshyfunct~on ~s determ2ned and the dec2s~on to abort ~s made after the

-51-

TLI cutoff and before TLI cutoff plus approxlmately 80 m1nutesTh1S allows suff1c1ent separatlon and procedural t1me to set upfor the SPS deorb1t burn performed at about TLI + 90 Note thatgenerally the deorb1t burns w1ll be performed a fe11 m1nutes beforeTLI + 90 accord1ng to crew charts shown In reference 8 The no-comm except10n requ1res that 90 m1nutes be the 1nput t1me of 19n1shytlon for P-37 (onboard return-to-earth abort program) so that onshyboard calculatlons can correspond w1th ground calculat10ns to computethe CM land1ng p01nt Th1S TLI abort lS des1gned so that returnfl1ght t1me does not exceed 18 hours and abort ~V does not exceed7000 fps ThlS abort can be performed uSlng chart ~Vs and attltudesand the earths hor1zon serves as a suff1c1ent reference The maneushyver lS targeted to ach1eve the mldcorr1dor entry target Ilne andtlmed to result 1n a deslgnated recovery area

It 1S ObV10US for abort deC1S1ons early 1n the TLI + 90 m1nute t1meshyframe that a GampN SPS burn should be performed In order to keep theTLI abort procedures cons1stent and w1th emphasls on slmpl1c1ty theprocedures here reflect a SCS SPS abort burn to cover the full abortdec1s1on t1meframe

A m1dcourse correct1on for corr1dor control after a TLI abort may bedeS1red 1f the SPS burn d1d not meet expectat1ons The TLIabortprocedures 1n th1S sect10n adapt to the normal lunar return tlmel1neand procedures pr10r to the f1nal MCC

-52-

61 TLI PREPARATION PROCEDURES

GET = 150

CRO AOS(___)

CRO LOS( )(22142)

5100

Don Helmets amp Gloves

XLUNAR - INJECT (verify)EDS PWR - on (venfy)EMS FUNC - OFF (verlfy)EMS MODE - STBYEMS FUNC - IW SETVHF RNGEMS MODE - NORMALSet ~V indo to +15868 fpsEMS FUMC - ~V Test

SPS THRUST Lt - onoff (10 sec)~V lnd stops at -01 to -415

EMS MODE - STBYEMS FUMC - ~V SETVHF RNGSet ~VC

EMS FUNC---~~V=----

GDC ALIGNFDAI Select - liZcb SECS LOGIC (Z) - close (verify)cb SECS ARM (Z) - closeSECS LOGIC (Z) - on (up)MSFN Conflrm GO for PYRO ARM (If pass)SECS PYRO ARM (Z) - on (up)TRANS CONTROL PWR - ONROT CONTR PWR NORMAL (Z) - ACDC(verlfy)ROT CONTR PWR DIRECT (Z) - MNAMNBLV INnGPI - SIISIVB (venfy)LV GUID - IU (venfy)cb DIRECT ULLAGE (Z) - closedSet EVENT TIMER to 5100Begin MONITOR For TB6

CMP to Couch

TB 6 - SII SEP Lt on (TIG-9 mln 38 sec)KEY V83E

SET ORDEALFDAI Z ORB RATE at 180 0 0SII SEP Lt out (38 sec later)Start DET COUNTING UPSC CaNT - SCS (verify)MONITOR LV TANK PRESS

~P lt 36 psid (OXID gt FUEL)~P lt Z6 psid (FUEL gt OXID)

EMERGENCY CSMLV SEP UP TLM CM - BLOCK (verify)UP TLM IU - BLOCK (venfy)

-53-

+45degPY))0middot sec PY

lOK nmltHAlt25K nm

Two phas~ng mnvrs two SPS mnvrs to circular~ze at 150 nmearth orb~t

CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ssion 4K nmltHAltlOK nm CSM amp1M - Two phasing mnvrs two SPS mnvrs to circularize at 150 nm earth orb~t CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ss~on

CSM amp 1M - Two phas~ng mnvrs APS burn todepletion th~rd phasing mnvrSPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn tosem~sync orb~t

25K nmltHAlt40K nm CSM amp 1M - Two phasmg mnvrs APS burn to depletion third phas~ng mnvr SPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn to sem~sync orbit HA)40K nm DPS ava~l - DPS LOll circularize with SPS

DPS not ava~l - Lunar flyby or CSM only to lunar orbit (if reqd gtV lt4000 fps)

V37E 47E (check b~as) Record -=--rshy(Limit 98 fpsmm)

( 1fps)tVXYZN62EVIHDOTHPAD (fpsfpslnm)MONITOR VI ( ) at ECO

SCS TVC SERVO PWR 1 - ACIMNA2 - OFF

TAPE RCDR - CMD RESETHBREMS MODE - NORMAL

SIr SEP Lt - ONTLI Inhib~t S~gnals w~11 not be honored after 5942

SIVB ULLAGE BeginsSII SEP Lt - off (TIG - 18 sec)SIVB FUEL LEADSIVB ULLAGE d~scont~nues

LV ENG I Lt - onSIVB IGNITION ( GETI)LV ENG I Lt - off - -shyMONITOR THRUST amp ATTITUDEMONITOR LV TANK PRESSSIVE ECO (Lt on) (BEGIN TB7)

EMER SIVE CUTOFF AT 6 SEC PAST BURN TIME IF VI ATTAINEDTHC CCW ampNEUTRAL IN 1 SEC or SIISIVB sW - LV STAGEPremature Shutdown HAlt4K nm CSM amp 1M -

5700

58205836

F 16 835800

F 16 62

5838594259525955595900000002SUNRISE(___)

HAW AOS(__=_) KEY VERB (freeze d~splay)

SIVB ATT HOLD 20 sec amp BEGIN VENTINGSIVB NNVR TO ORB RT (HDS DN) (3middot sec)

Record VI -c---HDOT _

HPAD _

KEY RLSEF 16 62

F 16 83

HAW LOS(__=-)

KEYmiddotRLSE~VXYZ (lfps)

Record ~VX---_

~vy

WZ--

AVC---_

TAPE RCDR - off (ctr)EMS MODE - STBYEMS FUNC - OFFSECS PYRO ARM (2) - SAFE

PRO

BURN STATUS REPORT

____--~TIG

BT------VGX____-R

-----P----_Y

REMARKS

_____VI

______--HDOT______--H______---AVC______---FUEL_______OXID

_______UNBAL

F 3708=00 OOEGOS AOS CMP TO LEB

(-=-=-)

0000

0003

0005

0014

0100

-55-

62 TLI 10 MIN ABORTSECS LOGIC (2) - on (up)SECS PYRO ARM (2) - ARM

TRANS CONTR - CGH (4 sec) amp +XDET RESET (verlfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS GMD-ON

TRANS GONTR - neutral then +X for10 sec

SIVBGPI s~ - GPIExcesslve rates 6V THRUST A - NORMAL SPS THRUST - DIRECT When rates damped 6V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

TRANS CONTR +X - OFFV37E OOE

PITGH UP to LOGAL VERT (+X axlSto~ard the earth)

RATE - LOWBMAG MODE (3) - ATTIRATE 2EDS PHR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SEGS ARM (2) - opencb EDS (3) - open

TRANS CONTR -X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (180deg)P (199deg)Y (0deg)

RETRO UPDATEGETI _

JV _VG

Jtb ---GET 400K _

05G _GET DROGUE _

ENTRY P _R _

Y_--

0945

-56-

ALIGN HORIZ ON RET +1 MKGMBL CHECK (T11lle Pentattlng)MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conflnn)cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FUMC - JV SETVHF RNGSET JV from chartE~S FUMC - JVEMS fODE - NOIDlAL

lV THRUST A - NORMALV37E 47E (THRUST fONITOR)

F 16 83 lVXYZ (1 fps)

0950

1000

NOTE For aborts durlng 1st mln of TLIKEY V82E F 16 44 (HaHpTff)Burn untll Hp lt 19NM

TRANS CONTR +X

THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN JV reqdJV THRUST (2) - OFFReport cutoff

cb SPS P2 Y2- closeGfBL MTRS (4) - OFF (LMP Confinn)TRANS CONT PWR - OFFTVC SERVO PWR (2) - OFFMN BUS TIE (2) - OFFcb SPS P1amp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREIf est time to EIltOl5500 omlt fCC andenter the SUPERCIRC CKLIST as early as pos-slb1e Pg ~2~3~ __If est time to EI)Ol5500 anticlpate afCC Enter the ENTRY PREP CKLIST at step 9pg 18

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

-2tl C

l I W gt- ~-4

z laquo I I- 0 -6

l- I J u gt- ~-8

z w w -10

~_ONSANT

9O

VER

SHO

OT

BOU

ND

ARY

LIF

TV

EC

TOR

OR

IEN

TATI

ON

LIN

E

SH

ALL

OW

TAR

GE

TLI

NE

STE

EP

TAR

GE

TLI

NE 12

gU

ND

ERSH

OO

TBO

UN

DAR

Y

RE

EN

TRY

CO

RR

IDO

R

I ~ I

-12 24

26

28

30

32

34

RE

EN

TRY

VE

LOC

ITY

VE

1-F

TS

EC

Ch

art

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36

3B

6-i

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CC

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ST

NT

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bull-1

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2829

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J23

33

43

5IN

ER

TIA

LR

EE

NTR

YV

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00

00

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EC

Ch

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J63

73

8X

03

-i- rtREQUIRED PITCH GIMBAL ANG LETO OBTAIN HOR-IZON AT 317

DEGREES IN wiiiiDOW

260

z~I- ~ i5 24000

1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

-I

-1-

NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

I LU HD~-

LUHD

lt0 120UJ0

~

80 HOLD PRESENT TRIMgt LU HD013

~Y~HOIgtlt

TOP OF WINDOWa 40to

31 7 SCRIBEaaI

80 TTOM OF WINDOWi= 0

0--ltoa

-40t-z

~~~Uw w u lt0 -80

HOLO PRESENT TRIlJCl

LOHU0 lt0

J gt -120 HOLD 059 TRIMlt0 z

LDHUlt0 FIELD OF VI S10 NLDHU LIFT-DOWNHEADS -UPLUHD LIFT-UP HEADS-DOWN

~~H~-160 q - P63 LIMITI- NOrE-VALIO ONLY FO~t~--

LUNAR RETURN VELOCITY

plusmnl8020 244middot 8 12 16

TIME TO 400K FT ALTITUDE-MIN

4

P37

LONG

ITUD

ECO

RREC

TION

TOOB

TAIN

1350

NM

ENTR

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340

344

348

352

356

364

368

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-50

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010

20

AA

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-60

Ch

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6

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00 70

00 60

00 i50

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120

200

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240

320

400

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DEC

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1968

400050

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2627

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0080

0070

0060

0050

0040

0030

0020

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000

II

II

II

II

S-IV

BBU

RNTI

ME

-M

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Cll-

41)

120

200

241)

320

400

441)

520

TlI

-I0

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ABOR

TlA

UNCH

-DE

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19

68

lAUN

CHA

ZIM

UTH

lllJ

72I ~ I

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3

-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 30: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

8 06 64

58middot00m(-0200)

9

05G tlme(+0 )

(--=---)

06 68

-27-

P63 - ENTRY INIT

GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PIJR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRmDHORIZ CKPltch error needle goes toward

zero approachlng OSG tlmeMAN ATT (PITCH) - RATE CMD

If CMC lS GOBMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS I

FLY BETA If CMC NO GO ilt

1 SC CaNT - SCS I

FLY EMS k

p64 - ENTRY POST 05G

RTOGO AT 05G AGREES HITH EMS-venfyHORIZ CK05G Lt - ON (EMS START)

No EMS START wlthln 3 sec ~ EMS MODE - BACKUP VHF RNG c

05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds Llft DN

NNVR Llft DNEMS GONO GO

G-V Plot wlthln IlmltsRng ctr dwn 60plusmn7 durlng 10 sec

perlodMonltor G-meter for

convergence wlth pad data (Do)(Vlt27K fps) Go to 13

-28-

P65 - ENTRY - UP CONT (Vgt27K fps)

10 F 16 69 BETA (01middot) _DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT lt~ SC CONT - SCS FLY EMS

PRO

11 06 68 BETAVIHDOT (OIdegfpsfps)(VltV1+500 fps amp RnOT Neg) Go To 13

P66 - ENTRY - BALLISTIC (D(DL)

12 06 22 DESIRED GMBL ANGLES RPYMoultor horlz +12middot of 317middot mark

P67 - ENTRY - FINAL PHASE (02G)

13 06 66 BETACRSRNG ERRDNRNG ERR(010 1um 1um)

KEY VERBRecord DNRNG ERR _KEY RLSEMoultor l~ft vector ou RSI amp FDAI

16 67 RTOGOLATLONG (Vrel=1000fps)(lumOldegOldeg)

SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOWNMonitor a1t~meter

Go To EARTHLANDING pg ---4L5 _

-29-

53 GampN HYBRID DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL tV1 V37E 30E

2 F 06 33 GETI(ACCEPT) PRO (hrm~n Olsec)(REJECT) LOAD DESIRED GETI

3 F 06 81 tVXYZ (LV) (lfps)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

4 F 06 42 HAHPtV (lnm lfps)Record tV

(ACCEPT) PRO(REJECT) Reselect P30 or P27 Load new paramo

5 F 16 45 MTFIMGA (marksm~n-secOlO)

MGA -00002 ~f k

k lMU not al~gned

SET DETPRO

6

7

8

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (Pull)PLSS 02 vlv - FILL02 8M SUPPLY vlv - OFFCAB PRESS REL vlv (2) - NORMcb ELS (2) - closecb SECS ARM (2) - closecb SECS LOGIC (2) - close (ver~fy)

AUTO RCS SEL CM (12) - MNA or ~ffiB

(hftoff conhg)ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM (AampB) - OFF

CMP to Couch

9

10

11

-30-

MNVR TO PAD BURN ATTLOAD DAPBMAG MODE (3) - RATE 2SC CONT - CMCAUTOATT DB - MINMAN ATT (3) - RATE CMD

v62E

v49E

12 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLES

PRO

13 F 50 18 REQ MNVR TO FDAI RPY ANGLES (01deg)(AUTO) PRO(MAN) SC CONT - SCS

BMAG MODE (3) - RATE 2MNVR To 15

14 06 18 AUTO MNVR TO FDAI RPY ANGLES (01deg)

15 F 50 18 REQ TRIM TO FDAI RPY ANGLES (01deg)(TRIM) Go to 13(ByPASS) ENTR

16

17

CHECK BORESIGHT amp SKT STARSOPT MODE - CMCOPT ZERO - OFF

v41 N91E

18 F 21 92 SHAFTTRUN (01deg 001deg)Load SXTS angles

19 41 OPTICS DRIVECheck SKT STAR

OPT ZERO - ZEROCheck BORESIGHT STAR (~f ava~l)

20 V25 N17E (01deg)Load Pad Data GMBL Angles

for CM BURN ATTATT SETtw - SET

to PAD DATA GMBL ANGLESfor CM BURN ATT

21

22

-31-

PHR REDUCTIONHGA PHR - OFFFC PUMPS (3) - OFFVerify s~ngle su~t compr oper loads

balancedFC 2 MN AampB - OFFS BD PiR AMP - LOWcb ECS RAD CONTHTR (2) - opencb HASTE H20URINE DUMP HTRS(2)- opencb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANMN BUS TIE (2) - ONTVC SERVO PHR 1 - AC1MNAGMBL MTR (4) - START

p41 - RCS THRUSTINGV37E 41E

23 F 50 18 REQ MNVR TO LCL HORIZ (HDS ON)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CMCAUTOPRO To 24

(gtfANDAP) BMAG MODE (3) - RATE 2SC CONT - CMCHOLD

V62EMNVR To 25

24 06 18 AUTO MNVR TO FDAI RPY

25 F 50 18 REQ TRIM TO LCL HORIZ (01deg)ALIGN SC ROLL

(AUTO TRIM) PRO To 24(BYPASS) ATT DB - MIN

RATE - LOHMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTlRATE 2

ENTR

550Om26 06 85

59middot2527

-32-

VGXYZ (1fps)RECHECK BORESIGHT STARTRANS CONIR PWR - on (up)EMS MODE - STBY (ver~fy)

EMS FliNC - bV SETVHF RNGSET (IV for SM BURN _EMS FliNC - bVS BD ANT - OMNI CSECS LOGIC (2) - ONMSFN conhrm Go for PYRO ARMSECS PYRO ARM (2) - ARMCM RCS LOGIC - ON (ver~fy)

DSKY BLANKS

593028 16 85 VG XYZ (AVE G ON) (lfps)

RHCs amp THC - ARMEDLIMIT CYCLE - OFFTAPE RCDR - CMD RESETHBREMS MODE - NORMAL

000029 F 16 85 REQ NULL VG XYZ (lfps)

BURN EMS bV CTR TO ZERORESET DET amp COUNT UP

If SM ONLY burn go to step 32THC - LOCKEDSC CaNT - SCSFREERATE - HIGHPRIM GLY To RAD - BYPASS (ver~fy)

MN BUS TIE (2) - ON (ver~fy)

CMSM SEP (2) - on (up)CSMLM FNL SEP (2) - on (up) (verify)CampW MODE - CMRCS TRNFR - CMCM RCS LOGIC - OFF

Momtor VM ABIf lt25 vdc go to EMERGPOWER DOWN Pg E6-l

V63E

If CMC NO GO FDAI SOURCE - ATT FDAI SEL - 1 or 2 ATT SET - GDC

SET

-33-

~Uili ATT PITCH - ACCEL CMDFDAI SCALE - 55MNVR TO CM BURN ATT (NULL ERR NEEDLES)

R 0degPY --00--

30

31

CM RCS BURNRHC III-ContJnuous PJtch DownRHC HZ-Module PJtch to null needlesBURN VGZ TO ZERO

If only 1 RHC Pulse + P=5deg from retro att MaJnta~n rates lt3degsec

BURN COMPLETION ATllV CTR= or DET= _

V8ZE

32 F 16 44 HAHPTFF (1nmffiJn-sec)Check HP-

If gt Pad data contJnue burnuntJ1 lt Pad

PRO

33 F 16 85 VGXYZ (Ups)Read VG resJduals to MSFN

(HYBRID) PRO to 34(SM ONLY BURN)

PROF 37 ODE

EI-1500 V37E 47EF 16 83 twx Y Z (Ups)

SC CONT - SCSFREEMAN ATT (PITCH) - RATE CMDRATE - HIGHPRIM GLY To RAD - BYPASS (verJfy)MN BUS TIE (2) - ON (verJfy)CMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verJfy)Campl MODE - CMRCS TRNFR - CMCM ReS LOGIC - OFFSECS PYRO ~I (2) - SAFE

-34-

PROMonitor VMAB

If lt25 vdc go to EMERGPOWER DOWN

34 F 37 OOEPCM BIT RATE - LOWATT DB - MAXEMS MODE - STBYEMS FUNC - OFF

Go To EARTH ORBIT ENTRY pg _--40-__

-36-

8 SPS THRUSTING PREPCYCLE CRYO FANSSPS GAGING - ACI (ver~fy)

PUG MODE - NORM (venfy)BMAG MODE (3) - RATE 2tv CG - CSMCMC MODE - FREEAUTO RCS SEL (16) - MNA or HNB

(hftoff conbg)SC CONT - CMCAUTO

9 MNVR TO PAD BURN ATTV62E

10 V49E

11 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLESPRO

12 F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) PRO(HAN) SC CONT - ses

MNVR to 14

06 18 AUTO MNVR TO FDAI RPY ANGLES13

14 F 50 18 REO TRIH TO FDAI RPY ANGLES(TRIM) Go to 12(BYPASS) ENTR

15 BORESIGHT STAR CHECK

16 V37E 40EOPT PWR - OFF

17 F 50 18 REQUEST MNVR TO FDAI RPY ANGLES (01deg)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CHCAUTOPRO to 18

(MANDAP) BMAG HODE (3) - RATE 2SC CONT - CMCHOLDMNVR to 19

(HANseS) se eONT - sesMNVR to 19

-35-

54 NORMAL DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL ~V

1 V37E 30E

2 F 06 33 GETI (hrm~nOlsec)

(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

3 F 06 81 ~VXYZ (LV)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

( lfps)

4 F 06 42 HAHP~V (1nmlfps)Record W

(ACCEPT) PRO -----(REJECT) Rese1ect P30 or P27 Load new pa~am

5 F 16 45 MTFIMGA (marksmln-secOldeg)MGA -00002 If ~ lMU not a1~gned

SET DETPRO

6

7

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY v1v - OFFCAB PRESS REL v1v (2) - NORMcb ELS (2) - close (verify)cb SECS ARM (2) - close (ver~fy)

cb SECS LOGIC (2) - close (verlfy)AUTO RCS SEL CM (12) - ~mA or MNB

(l~ftoff conf~g)

ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM AampB - off (ctr)

18

-37-

06 18 AUTO MNVR TO FDAI RPY ANGLES (01 0)

19 l 50 18 REOUEST TRIM MNVR TOALIGN SIC ROLLGDC ALIGN

FDAI RPY ANGLES(010

)

+54-00m(-06-00)

TIG-5mJn

5500m(-0500)

TVC CHECK amp PREPcb STAB CONT SYS (all) - closecb SPS (12) - closeATT DB - MINRATE - LOl~

LIMIT CYCLE - ONMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE 2ROT CONTR PWR DIRECT (2) - OFFSCS TVC (2) - RATE CMD

If SCS SCS TVC (2) - AUTO SC CONT - SCS ~

TVC GMBL DRIVE PampY - AUTOMN BUS TIE (2) - ONTVC SERVO PWR 1 - AC1MNA

2 - AC2MNBTRANS CONTR PWR - ONROT CONTR PWR NORMAL 2 - ACRHC 2 - ARMED

HORIZ CHK - HorJz on 12deg wJndmlmark (LJffiJt +3 0 PNGCS GONO GO)

If NO GO set tw 180 0 180deg0 0

Track horJz wJth 24deg wJndow markAt TIG-2 mJn Ahgn GDC

PRIMARY TVC CHECKGMBL MOT P1-Y1 -STARTON(LMP confJrm)

If SCS verJfy Thumbwheel TrJmTHC - CWVenfy NO MTVC

SEC TVC CHECKGHBL MOT P2-Y2 -STARTON(LMP confJrm)SET GPI TRIHVenfy MTVCTHC NEUTRALGPI returns to 00 (CMC) or trJm (SCS)ROT CONT Pl~ NORM 2 - ACDC

(TRIM) Go to step 17(BYPASS) BMAG MODE(3) - ATTIRATE2 (ver1fy)

ENTR

-38-

20 F SO 25 00204 GMBL TEST OPTION(ACCEPT) SC CONT - GMC (ver~fy)

PROMonitor GPI Response

0020-2000020-200Tr~m

TEST FAIL SC CONT - SCS SCS TVC (2) - AUTO

(REJECT) ENTR

21 06 40 TFIVG~VM (m~n-sec1fps)

PROG ALM - TIG s1~pped

V5N9E 01703

KEY RLSE To 21 ROT CONTR PWR DIRECT (2) - MNABSPS He v1vs (2) - AUTO (ver~fy)

LIMIT CYCLE - OFFFDAI SCALE - SOIScb SPS P2Y2 - open (for cr~t burn)

5800(-02 00)

5925(-0035)

59middot 30(-0030)

06 40

59XX(-OOXX)

AV THRUST A(B) - NORMALTHC - ARMEDRlIC (2) - ARMEDTAPE RCDR - GID RESETHBR

DSKY BLANKS

(AVE G ON)EMS MODE - NORMAL

TFIVG~VM (m~n-seclfps)

CHECK PIPA BIAS lt2fps for 5 sec

ULLAGE AS REQ

IF NO ULLAGE DIR ULLAGE PB - PUSH~

CONTROL ATT WRlIC MONITOR AVM (R3) COUNTING UP

5955(-0005)

F 99 40 ENG ON ENABLE REQUEST(AUTO IGN) PRO AT TFI gt0 sec(BYPASS IGN) ENTR to 24

22 0000 IGN

-39-

If SCS - THRUST ON PB - PUSH

06 40 TFCVG~VM (m~n-seclfpslfps)

~F 97 40 SPS Thrust fall ~

~(RESTART) PRO To IGN (RECYCLE) ENTR To TIG-05 sec

SPS THRUST LITE - ONMONITOR THRUSTING

Pc 95-105 pSlaEMS COUNTING DOWNSPS IN3 v1vs (4) - OPENSPS He v1vs tb (2) - graySPS FUELOXID PRESS - 175-195 pSlaPUGS - BALANCED

PROG ALARM V5N9E 01407 VG INCTHC - CW FLY MTVC

ECOEMER SPS CUTOFF J

AV THRUST (2) - OFF

23 F 16 40 TFC(STATIC)VG~VM (mln-seclfps)~V THRUST AB - OFF

SPS IN3 v1vs (4) - CLOSEDSPS He tb (2) - bp

cb SPS P2Y2 - closed (verlfy)TVC SERVO PHR - AC1MNA (venfy)TVC SERVO PWR 2 - OFF

PRO

24 F 16 85 VG XYZ(CM) CUps)NULL RESIDUALSRECORD ~V CTR amp RESIDUALS I1VCEMS FUNC - OFF VGXEMS MODE - STBY VGYBMAG MODE (3) - RATE 2ATT DB - MAX VGZTRANS CONT PHR - OFF

PRO

25 F 37 V82E

26 F 16 44 HAHPTFF (lnmm~n-sec)

R3-59B59 HP gt494 nmPRO

27 F 37 OOE

-40-

55 EARTH ORBIT ENTRY

1 Venfy CMSMR __

P_shyY_-

SEP ATT(180deg)

(0deg )

2

3

4

EMS INITIALIZATIONEMS FUNC - RNG SETSET RNG TO PAD DATA RNGEMS FUNC - VA SETSlew scroll to pad data VIOEMS FUNC - ENTRY

RSI ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on(up)GDC ALIGN PB - PUSH amp HOLDYAW tw - Pos1tion RSI thru 45deg amp

back to LIFl UPGDC ALIGN PB - RELEASEEMS ROLL - OFFAl1gn GDC to lMU

PWR REDUCT (Norm Deorb Only)HGA PWR - OFFFC PUMPS (3) - OFFVer1fy s1ngle suit compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - Lowcb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2)-openlOb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MAN

-41-

P61 - ENTRY PREP

5 V37E 61E05 09 01427 - ROLL REVERSED05 09 01426 - IMU UNSAT

6 F 06 61 IMPACT LAT LONG liDS UPDN (+-)(01 0

010

+00001)

PRO

PAD VALUESLATLON==G------liDS UP DN _

7 F 06 60 GMAXV400KGAMMA EIRecord

GMAXV400K----GAMMA EI _

PRO

8 F 06 63 RTOGO (1nm) PAD _VIa (fps) PADTFE (mln-sec) ----Compare wlth MSFN for PGNS GONO GONO COMM SET RTOGO amp VIO IN EMS amp

INITIALIZE(ACCEPT) PRO(RECALC) V32E to 8

-42-

P62 - CMSM SEP amp PRE-ENTRY MNVR

9 F 50 25 00041 REQUEST CMSM SEPSC CONT - SCSFREEYAW - 45deg out-of-plane (left for RCS

nght for SPS)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE2PRIM GLY to RAD - BYPASS (verlfy)SECS LOGIC (2) - on (up)MSFN conflrm GO for PYRO ARMSECS PYRO ARM - ARMMN BUS TIE (2) - ON (verlfy)CMSM SEF (2) - ONCSMLM FNl SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 pSlaCM RCS LOGIC - OFFSECS PYRO ARM - SAFEMonltor VMAB

If lt25vdc go to EMERG POWERDOWN Pg E6-1AUTO RCS SEL AlC ROLL (4) - OFFAUTO RCS SEL CM 2(6) - OFFAUTO RCS SEL CM 1(6) - MNA or MNBYAW back to 00

PITCH TO ENTRY ATTROLL 0deg (LIFT UP)PITCH - HORIZ on 317deg MARK (400K)YAW 00

ATT DB - MAXMAN ATT (PITCH) - ACCEL CMDEMS DATA - VerifyEMS FUNC - ENTRY (verlfy)EMS MODE - NORMALMAINTAIN HORIZ TRK

PRO (Act ENTRY DAP)

10 F 06 61 IMPACT LAT LONG HDSDN(010 010 -00001)

PRO

11 FOSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axlS beyond 45deg of Vel vector)

-43-

P63 - ENTRY INIT

12 06 64 GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PWR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRHORIZ CKP~tch error needle goes toward

zero approach~ng 05G t~me

MAN ATT (PITCH) - RATE CMDIf CMC ~s GO

BMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS FLY BETA If CMC NO GO ~

SC CONT - SCS~

FLY EMS RCS Deorh Roll HDS UPTRACK HORIZ w~th 29deg w~ndow mk

P64 - ENTRY POST 05G

13

05G t=elt+0___)

06 68

RTOGO AT 05G AGREES WITH EMS - venfyHORIZ CK05E Lt - on (EMS start)

No EMS start w~th~n 3 secsEMS MODE - BACKUP VHF RNG 05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds L~ft DN

NNVR L~ft DNEMS GONO GO

G-V Plot w~th~n llm~ts

Rng ctr dwn 60 + 7 durlng 10 sec per~od

Mon~tor G-meter forconvergence wlth pad data (Do)

(Vlt27K fps) Go To 17

-44-

P65 - ENTRY - UP CONT (Vgt27K fps)

14 F 16 69 BETA (01deg)DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT~

SC CONT - SCS FLY EMS

PRO

15 06 68 BElA VI HOOT (01deg fpsfps)(VltVL +500 fps amp RDOT Neg) Go To 17

p66 - ENTRY - BALLISTIC (DltDL)

16 06 22 DESIRED GMBL ANGLES RPY (01deg)Mon~tor hor~z +12deg of 317deg mark

P67 - ENTRY - FINAL PHASE (02G)

17 0666 BETACRSRNG ERRDNRNG ERR (Oldeglnmlnm)KEY VERBRecord DNRNG ERR _KEY RLSEL~m~t +100nm from PAD DRE

Mon~tor l~ft vector on RSI amp FDAIF 16 67 RTOGOLATLONG (Vre1=1000fps)

(lnm 010 01deg)SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOlfflMon~tor altimeter

Go To EARTHLANDING pg _I4L5__

-45-

56 EARTHLANDING

90K STEAM PRESS - PEGGED50K CABIN PRESS REL vIv (2) - BOOSTENTRY

SECS PYRO ARM (2) - ARM

40K(90K + 63s)

CM UNSTABLE RCS CMD - OFF ~ 40K APEX COVER JETT PG-PUSH DROGUE DEPLOY PG - PUSH (2 secafter apex cover Jett)

30K ELS LOGIC - ON (up)ELS - AUTO

24K RCS hsable (auto)(90K+92s) RCS CMD - OFF

Apex cover Jett (auto)APEX COVER JETT PB - PUSH

(WAIT 2 SECS)Drogue parachutes deployed (auto)

DROGUE DEPLOY PB - PUSH~

If Drogues FallELS - ~ ~Stablllze CM 5K MAIN DPLY PB - PUSHELS - AUTO

235K Cabln Pressure lncreaslng (Drogues + 50s)If not lncreaSlng by 17K CABIN PRESS REL vlv (RR) - DUMP

-46-

10K Maln parachutes deployedMAIN DEPLOY PB - PUSH (wlthln 1 sec)VHF ANT - RECYVHF AMA - SIMPLEXVHF BCN - ONCABIN PRESS REL v1v (2) - CLOSEDIRECT 02 vlv - OPENCM RCS LOGIC - on (up)CM PRPLNT - DUMP (burn audlb1e)Monltor CM ReS 1amp2 for He press decrease

NO BURN or PRESS DECREASE USE BOTH RHCs DO NOT FIRE PITCH JETS

CM PRPLNT-PURGE (to zero He press)CM RCS He DUMP PB - PUSH RHC (2) - 30 sees NO PITCH k

STRUT LOCKS (2) - UNLOCK

cb FLT amp PL BAT BUS ABampBAT C (3) - closecb FLT amp PLT MNA amp B (2) - opencb ECS RAD HTR OVLD (2) - opencb SPS PampY (4) - open

3K CABIN PRESS REL v1v (RH) - DUMP (after purgecompleted)

FLOOD Lts - POST LDGCM RCS PRPLNT (2) - OFFROT CONTR PWR DIRECT (2) - OFF

800 CAB PRESS RELF vlv - CLOSE (latch off)MN BUS TIE (2) - OFF

AFTER LANDINGcb MAIN REL PYRO (2) - closeMAIN RELEASE - on(up)

Go to POSTLANDING pg _47L-__

I

2

3

-47-

57 POSTLANDING

STABILIZATION VENTILATION COMMUNICATIONS

DIRECT 02 vlv - CLOSE

Stablllzation after landlngELS - AUTO (verlfy)cb MAIN REL PYRO (2) - close (venfy)MAIN RELEASE - on (up) (verlfy)S~CS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb BAT RLY BUS (2) - open

No contact w1th recovery forcesVHF AM AampB - off (ctr) ~

VHF AM Rev ONLY - A cb PL VENT - closecb FLOAT BAG (3) - closecb UPRIGHT SYS COMPRESS (2) - closeIf Stable II

FLOAT BAG(3)-FILL t1ll 2 m1n afterupr1ght then - OFF

VHF AM AlB amp BCN - OFF whlle lnvertedIf Stable I

After 10 M1n Coollng Per1odFLOAT BAG (3) - FILL 7 mln then OFF

Post Stab1lizat1on And Ventllat10nPL BCN LT - BCN LT LOWPL VENT vlv - UNLOCK (Pull)Remove PL VENT Exh CoverPL VENT - HIGH or LOWPL DYE MARKER - ON (swlmmer comm)Release foots traps and_restralntscb MNA BAT BUS A amp BAT C (2) - opencb MNB BAT BUS B amp BAT C (2) - opencb FLT amp PL BAT C - opencb PYRO A SEQ A - opencb PYRO B SEQ B - open

EACH HR - CHECK DC VOLTSgt 275 V If Notmiddot cb FLT amp PL-BAT BUS AampB (2) -open cb FLT amp PL BAT C (1) - open GO TO LOW POWER CHECKLIST

Unstow and lnstall PLV DISTRIB DUCTDeploy grappllng hook and 11ne 1f req

4

-48-

Post Landing Communlcatl0nsVHF ANT-RECY (venfy)VHF BCN - ON (verlfy)

If no contact ~lth recovery forcesperform VHF BEACON Check

MONITOR VHF BEACON transmlSSlonnth VHF AM B Rcvr andor Su)vlval

TransceiverkVHF Beacon not operatlng ~connect Surv~val TranscelVer to antcable behlnd VHF ant access pnland place radio ln BCN mode

LOW POHER CHECKLISTVHF BCN - OFFVHF AM (3) - RCVFLOOD Lts - OFFVHF AM AampB - off (ctr)VHF AM RCV ONLY - A (venfy)COUCH LIGHTS - OFFPOSTLANDING VENT SYS mlnlmlze useSURV RADIO - plug mto VHF BCN ANT cableconn behind VHF ant acess pnl amp turn radloon l-n BCN mode

EGRESS PROCEDURES

CMPCDRLMPCDR

CMPCDRCMP

LMPLl1PCDR

STABLE IDlsconnect Umblll-calsNeck darn onCenter couch - 270 0 positionArmrests stowedConnect raft to SIC l-f desl-red wlth

green lanyardConnect raft ~hl-te lanyards to SUltS amp

lnflate water wlngs when eXltl-ngHATCH PISTON PRESS vlv - PRESS (Outbd)Slde Hatch openedPL VENT - OFFcb Pnl 250 (all) - openEgress with 11feraftPut hardware klt outEgress

or CDIPALL

CMF

CDRCMF

CDR

LMF

CMFCMP LMFCMP

UlP

CDR

-49-

STABLE IIcb CREW STA AUDIO (3) - openD~sconnect umb~1~ca1s

Release foots trapsRelease restra~nt harnessCouch seat pans (3) - 170 0 pos1t10nArm rests stowedSurv1va1 k~ts removed from stowageConnect life raft ma~n1~ne to CDR or SicConnect f~rst wh~te lanyard from

11fe raft to suitConnect th~rd wh~te lanyard from

l~fe raft to SU1tConnect rucksacks together to yellow

lanyard on raft bagPRESSURE EQUALIZATION vlv - OPENRemove and stow fwd hatchEX1t feet f1rst w1th rucksacks when clear

of siC 1nflate water w1ngs and raftExit feet f1rst when clear of SiC

1nflate water w1ngsEX1t feet f1rst when clear of sic

1nflate water w1ngs

-50-

60 TLI ABORTS

TLI Aborts are conta~ned ~n the ESD s~nce the bulk of the funct~ons

concern entry preparat20ns and performance Th~s allows a s2nglesource of procedures for procedure rev2ew val~dat~on checkout andtra~n~ng These procedures ~ncorporate TLI preparat20ns as found ~n

reference 6 w~th the TLI Abort Procedures and these t~e 2nto normallunar return Entry Procedures found ~n sect20n 5 The guidel~nes

for th~s cont2ngency are spec2f2ed 2n reference 7

In2t2al preparat~ons for TLI pos2t20n the necessary system sW2tches2n add~t~on to perform~ng an EMS ~V test and a GDC al~gnment Afterthe DET ~s set for mon2tor2ng TB6 the CMP ~ncreases the 12ght levelof the LEB DSKY to max~mum and returns to the h2s couch Th2s 2Sdone so that the LEB DSKY can be observed ~n the event sunl~ght orreflect20ns wash out the ma2n d2splay panel DSKY dur2ng cr2t2calmaneuvers The crew then straps ~n and prepares for mon2tor~ng TB6as 2nd2cated by the SII SEP L~te The t2mes se~uence of procedures2S keyed on th~s d~splay and ~ncludes the DET START funct~on andSIVB IGNITION Dur2ng the burn the crew mon2tors the FDAIs foratt~tude excurs20ns and abnormal rates report~ng status checks toM~ss2on Control at d2screet t~mes dur2ng the maneuver Upon SIVBSHUTDOWN the eMP records the DSKY d~splayed performance parametersand awa2ts ground conf2rmat~on

The rat~onal for TLI aborts ~s descr~bed 2n reference 7 A summar2shyzat20n 2S extracted to prov2de background and gu2de12nes 2n th2sdocument The abort procedures cover aborts 10 m2nutes after conshyt2ngent SIVE shutdown and aborts 90 m2nutes after normal SIVE shutshydown t2me

The 10 m~nute TLI abort ~s des2gned to be used dur~ng TLI ~n theevent a spacecraft problem develops Wh2Ch can result 2n catastrophe2f ~mmed~ate act~on 2S not taken If the s~tuat20n perm~ts the crewshould always allow the SIVB to complete TLI at wh~ch t~me the groundand crew can perform a malfunct~on analys~s to determ~ne ~f an abort~s adv~sable If a fa~lure occurs that necess2tates the shutdown ofthe SIVB and the ~u~ck return of the crew to earth th~s abort ~s

des~gned to be as ~nsens~t~ve to execut~on errors as poss~ble andst21l be targeted to m2dcorr2dor The burn att~tude w~th the f~ed

hor~zon reference ~s a constant value for any shutdown t~me Theburn durat~on 2S a funct20n of shutdown t2me and 2S ava21able fromcrew charts S~nce the pr~mary purpose of th~s abort ~s to returnto earth as qU2ckly as poss2ble there are no restr2ct20ns as toland~ng locat~on However ~f the t~me to EI is greater than abouttwo hours a midcourse correct20n should be ant~c~pated

The 90 m2nute TLI abort 2S to be used 2f a cr2t2cal subsystem malshyfunct~on ~s determ2ned and the dec2s~on to abort ~s made after the

-51-

TLI cutoff and before TLI cutoff plus approxlmately 80 m1nutesTh1S allows suff1c1ent separatlon and procedural t1me to set upfor the SPS deorb1t burn performed at about TLI + 90 Note thatgenerally the deorb1t burns w1ll be performed a fe11 m1nutes beforeTLI + 90 accord1ng to crew charts shown In reference 8 The no-comm except10n requ1res that 90 m1nutes be the 1nput t1me of 19n1shytlon for P-37 (onboard return-to-earth abort program) so that onshyboard calculatlons can correspond w1th ground calculat10ns to computethe CM land1ng p01nt Th1S TLI abort lS des1gned so that returnfl1ght t1me does not exceed 18 hours and abort ~V does not exceed7000 fps ThlS abort can be performed uSlng chart ~Vs and attltudesand the earths hor1zon serves as a suff1c1ent reference The maneushyver lS targeted to ach1eve the mldcorr1dor entry target Ilne andtlmed to result 1n a deslgnated recovery area

It 1S ObV10US for abort deC1S1ons early 1n the TLI + 90 m1nute t1meshyframe that a GampN SPS burn should be performed In order to keep theTLI abort procedures cons1stent and w1th emphasls on slmpl1c1ty theprocedures here reflect a SCS SPS abort burn to cover the full abortdec1s1on t1meframe

A m1dcourse correct1on for corr1dor control after a TLI abort may bedeS1red 1f the SPS burn d1d not meet expectat1ons The TLIabortprocedures 1n th1S sect10n adapt to the normal lunar return tlmel1neand procedures pr10r to the f1nal MCC

-52-

61 TLI PREPARATION PROCEDURES

GET = 150

CRO AOS(___)

CRO LOS( )(22142)

5100

Don Helmets amp Gloves

XLUNAR - INJECT (verify)EDS PWR - on (venfy)EMS FUNC - OFF (verlfy)EMS MODE - STBYEMS FUNC - IW SETVHF RNGEMS MODE - NORMALSet ~V indo to +15868 fpsEMS FUMC - ~V Test

SPS THRUST Lt - onoff (10 sec)~V lnd stops at -01 to -415

EMS MODE - STBYEMS FUMC - ~V SETVHF RNGSet ~VC

EMS FUNC---~~V=----

GDC ALIGNFDAI Select - liZcb SECS LOGIC (Z) - close (verify)cb SECS ARM (Z) - closeSECS LOGIC (Z) - on (up)MSFN Conflrm GO for PYRO ARM (If pass)SECS PYRO ARM (Z) - on (up)TRANS CONTROL PWR - ONROT CONTR PWR NORMAL (Z) - ACDC(verlfy)ROT CONTR PWR DIRECT (Z) - MNAMNBLV INnGPI - SIISIVB (venfy)LV GUID - IU (venfy)cb DIRECT ULLAGE (Z) - closedSet EVENT TIMER to 5100Begin MONITOR For TB6

CMP to Couch

TB 6 - SII SEP Lt on (TIG-9 mln 38 sec)KEY V83E

SET ORDEALFDAI Z ORB RATE at 180 0 0SII SEP Lt out (38 sec later)Start DET COUNTING UPSC CaNT - SCS (verify)MONITOR LV TANK PRESS

~P lt 36 psid (OXID gt FUEL)~P lt Z6 psid (FUEL gt OXID)

EMERGENCY CSMLV SEP UP TLM CM - BLOCK (verify)UP TLM IU - BLOCK (venfy)

-53-

+45degPY))0middot sec PY

lOK nmltHAlt25K nm

Two phas~ng mnvrs two SPS mnvrs to circular~ze at 150 nmearth orb~t

CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ssion 4K nmltHAltlOK nm CSM amp1M - Two phasing mnvrs two SPS mnvrs to circularize at 150 nm earth orb~t CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ss~on

CSM amp 1M - Two phas~ng mnvrs APS burn todepletion th~rd phasing mnvrSPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn tosem~sync orb~t

25K nmltHAlt40K nm CSM amp 1M - Two phasmg mnvrs APS burn to depletion third phas~ng mnvr SPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn to sem~sync orbit HA)40K nm DPS ava~l - DPS LOll circularize with SPS

DPS not ava~l - Lunar flyby or CSM only to lunar orbit (if reqd gtV lt4000 fps)

V37E 47E (check b~as) Record -=--rshy(Limit 98 fpsmm)

( 1fps)tVXYZN62EVIHDOTHPAD (fpsfpslnm)MONITOR VI ( ) at ECO

SCS TVC SERVO PWR 1 - ACIMNA2 - OFF

TAPE RCDR - CMD RESETHBREMS MODE - NORMAL

SIr SEP Lt - ONTLI Inhib~t S~gnals w~11 not be honored after 5942

SIVB ULLAGE BeginsSII SEP Lt - off (TIG - 18 sec)SIVB FUEL LEADSIVB ULLAGE d~scont~nues

LV ENG I Lt - onSIVB IGNITION ( GETI)LV ENG I Lt - off - -shyMONITOR THRUST amp ATTITUDEMONITOR LV TANK PRESSSIVE ECO (Lt on) (BEGIN TB7)

EMER SIVE CUTOFF AT 6 SEC PAST BURN TIME IF VI ATTAINEDTHC CCW ampNEUTRAL IN 1 SEC or SIISIVB sW - LV STAGEPremature Shutdown HAlt4K nm CSM amp 1M -

5700

58205836

F 16 835800

F 16 62

5838594259525955595900000002SUNRISE(___)

HAW AOS(__=_) KEY VERB (freeze d~splay)

SIVB ATT HOLD 20 sec amp BEGIN VENTINGSIVB NNVR TO ORB RT (HDS DN) (3middot sec)

Record VI -c---HDOT _

HPAD _

KEY RLSEF 16 62

F 16 83

HAW LOS(__=-)

KEYmiddotRLSE~VXYZ (lfps)

Record ~VX---_

~vy

WZ--

AVC---_

TAPE RCDR - off (ctr)EMS MODE - STBYEMS FUNC - OFFSECS PYRO ARM (2) - SAFE

PRO

BURN STATUS REPORT

____--~TIG

BT------VGX____-R

-----P----_Y

REMARKS

_____VI

______--HDOT______--H______---AVC______---FUEL_______OXID

_______UNBAL

F 3708=00 OOEGOS AOS CMP TO LEB

(-=-=-)

0000

0003

0005

0014

0100

-55-

62 TLI 10 MIN ABORTSECS LOGIC (2) - on (up)SECS PYRO ARM (2) - ARM

TRANS CONTR - CGH (4 sec) amp +XDET RESET (verlfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS GMD-ON

TRANS GONTR - neutral then +X for10 sec

SIVBGPI s~ - GPIExcesslve rates 6V THRUST A - NORMAL SPS THRUST - DIRECT When rates damped 6V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

TRANS CONTR +X - OFFV37E OOE

PITGH UP to LOGAL VERT (+X axlSto~ard the earth)

RATE - LOWBMAG MODE (3) - ATTIRATE 2EDS PHR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SEGS ARM (2) - opencb EDS (3) - open

TRANS CONTR -X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (180deg)P (199deg)Y (0deg)

RETRO UPDATEGETI _

JV _VG

Jtb ---GET 400K _

05G _GET DROGUE _

ENTRY P _R _

Y_--

0945

-56-

ALIGN HORIZ ON RET +1 MKGMBL CHECK (T11lle Pentattlng)MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conflnn)cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FUMC - JV SETVHF RNGSET JV from chartE~S FUMC - JVEMS fODE - NOIDlAL

lV THRUST A - NORMALV37E 47E (THRUST fONITOR)

F 16 83 lVXYZ (1 fps)

0950

1000

NOTE For aborts durlng 1st mln of TLIKEY V82E F 16 44 (HaHpTff)Burn untll Hp lt 19NM

TRANS CONTR +X

THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN JV reqdJV THRUST (2) - OFFReport cutoff

cb SPS P2 Y2- closeGfBL MTRS (4) - OFF (LMP Confinn)TRANS CONT PWR - OFFTVC SERVO PWR (2) - OFFMN BUS TIE (2) - OFFcb SPS P1amp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREIf est time to EIltOl5500 omlt fCC andenter the SUPERCIRC CKLIST as early as pos-slb1e Pg ~2~3~ __If est time to EI)Ol5500 anticlpate afCC Enter the ENTRY PREP CKLIST at step 9pg 18

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

-2tl C

l I W gt- ~-4

z laquo I I- 0 -6

l- I J u gt- ~-8

z w w -10

~_ONSANT

9O

VER

SHO

OT

BOU

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ARY

LIF

TV

EC

TOR

OR

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TATI

ON

LIN

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SH

ALL

OW

TAR

GE

TLI

NE

STE

EP

TAR

GE

TLI

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gU

ND

ERSH

OO

TBO

UN

DAR

Y

RE

EN

TRY

CO

RR

IDO

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-12 24

26

28

30

32

34

RE

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TRY

VE

LOC

ITY

VE

1-F

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36

3B

6-i

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CC

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bull-1

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43

5IN

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LR

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73

8X

03

-i- rtREQUIRED PITCH GIMBAL ANG LETO OBTAIN HOR-IZON AT 317

DEGREES IN wiiiiDOW

260

z~I- ~ i5 24000

1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

-I

-1-

NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

I LU HD~-

LUHD

lt0 120UJ0

~

80 HOLD PRESENT TRIMgt LU HD013

~Y~HOIgtlt

TOP OF WINDOWa 40to

31 7 SCRIBEaaI

80 TTOM OF WINDOWi= 0

0--ltoa

-40t-z

~~~Uw w u lt0 -80

HOLO PRESENT TRIlJCl

LOHU0 lt0

J gt -120 HOLD 059 TRIMlt0 z

LDHUlt0 FIELD OF VI S10 NLDHU LIFT-DOWNHEADS -UPLUHD LIFT-UP HEADS-DOWN

~~H~-160 q - P63 LIMITI- NOrE-VALIO ONLY FO~t~--

LUNAR RETURN VELOCITY

plusmnl8020 244middot 8 12 16

TIME TO 400K FT ALTITUDE-MIN

4

P37

LONG

ITUD

ECO

RREC

TION

TOOB

TAIN

1350

NM

ENTR

YRA

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Ugt

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cgt

I

gtI- U

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340

344

348

352

356

364

368

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CMC

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VELO

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TITU

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FTS

EC

Ch

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20 100 -40

-10

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t~I

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-04

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NOTE

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NO

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=22

MIN

30

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---------O

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------I

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-20

-tD

010

20

AA

VX

FTS

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-60

Ch

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6

1000

0 90

00 70

00 60

00 i50

00 iMl

OO ilOO

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00 10

00 o

040

120

200

EMS

6V-

FTS

EC

240

320

400

440

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DEC

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1968

400050

z =gt co23

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2627

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~n

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VELO

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3536

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7

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1000

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EMS

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C90

0080

0070

0060

0050

0040

0030

0020

0010

000

II

II

II

II

S-IV

BBU

RNTI

ME

-M

INSE

Cll-

41)

120

200

241)

320

400

441)

520

TlI

-I0

MIN

ABOR

TlA

UNCH

-DE

C21

19

68

lAUN

CHA

ZIM

UTH

lllJ

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27~

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DX

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8

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3

-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 31: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

-28-

P65 - ENTRY - UP CONT (Vgt27K fps)

10 F 16 69 BETA (01middot) _DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT lt~ SC CONT - SCS FLY EMS

PRO

11 06 68 BETAVIHDOT (OIdegfpsfps)(VltV1+500 fps amp RnOT Neg) Go To 13

P66 - ENTRY - BALLISTIC (D(DL)

12 06 22 DESIRED GMBL ANGLES RPYMoultor horlz +12middot of 317middot mark

P67 - ENTRY - FINAL PHASE (02G)

13 06 66 BETACRSRNG ERRDNRNG ERR(010 1um 1um)

KEY VERBRecord DNRNG ERR _KEY RLSEMoultor l~ft vector ou RSI amp FDAI

16 67 RTOGOLATLONG (Vrel=1000fps)(lumOldegOldeg)

SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOWNMonitor a1t~meter

Go To EARTHLANDING pg ---4L5 _

-29-

53 GampN HYBRID DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL tV1 V37E 30E

2 F 06 33 GETI(ACCEPT) PRO (hrm~n Olsec)(REJECT) LOAD DESIRED GETI

3 F 06 81 tVXYZ (LV) (lfps)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

4 F 06 42 HAHPtV (lnm lfps)Record tV

(ACCEPT) PRO(REJECT) Reselect P30 or P27 Load new paramo

5 F 16 45 MTFIMGA (marksm~n-secOlO)

MGA -00002 ~f k

k lMU not al~gned

SET DETPRO

6

7

8

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (Pull)PLSS 02 vlv - FILL02 8M SUPPLY vlv - OFFCAB PRESS REL vlv (2) - NORMcb ELS (2) - closecb SECS ARM (2) - closecb SECS LOGIC (2) - close (ver~fy)

AUTO RCS SEL CM (12) - MNA or ~ffiB

(hftoff conhg)ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM (AampB) - OFF

CMP to Couch

9

10

11

-30-

MNVR TO PAD BURN ATTLOAD DAPBMAG MODE (3) - RATE 2SC CONT - CMCAUTOATT DB - MINMAN ATT (3) - RATE CMD

v62E

v49E

12 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLES

PRO

13 F 50 18 REQ MNVR TO FDAI RPY ANGLES (01deg)(AUTO) PRO(MAN) SC CONT - SCS

BMAG MODE (3) - RATE 2MNVR To 15

14 06 18 AUTO MNVR TO FDAI RPY ANGLES (01deg)

15 F 50 18 REQ TRIM TO FDAI RPY ANGLES (01deg)(TRIM) Go to 13(ByPASS) ENTR

16

17

CHECK BORESIGHT amp SKT STARSOPT MODE - CMCOPT ZERO - OFF

v41 N91E

18 F 21 92 SHAFTTRUN (01deg 001deg)Load SXTS angles

19 41 OPTICS DRIVECheck SKT STAR

OPT ZERO - ZEROCheck BORESIGHT STAR (~f ava~l)

20 V25 N17E (01deg)Load Pad Data GMBL Angles

for CM BURN ATTATT SETtw - SET

to PAD DATA GMBL ANGLESfor CM BURN ATT

21

22

-31-

PHR REDUCTIONHGA PHR - OFFFC PUMPS (3) - OFFVerify s~ngle su~t compr oper loads

balancedFC 2 MN AampB - OFFS BD PiR AMP - LOWcb ECS RAD CONTHTR (2) - opencb HASTE H20URINE DUMP HTRS(2)- opencb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANMN BUS TIE (2) - ONTVC SERVO PHR 1 - AC1MNAGMBL MTR (4) - START

p41 - RCS THRUSTINGV37E 41E

23 F 50 18 REQ MNVR TO LCL HORIZ (HDS ON)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CMCAUTOPRO To 24

(gtfANDAP) BMAG MODE (3) - RATE 2SC CONT - CMCHOLD

V62EMNVR To 25

24 06 18 AUTO MNVR TO FDAI RPY

25 F 50 18 REQ TRIM TO LCL HORIZ (01deg)ALIGN SC ROLL

(AUTO TRIM) PRO To 24(BYPASS) ATT DB - MIN

RATE - LOHMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTlRATE 2

ENTR

550Om26 06 85

59middot2527

-32-

VGXYZ (1fps)RECHECK BORESIGHT STARTRANS CONIR PWR - on (up)EMS MODE - STBY (ver~fy)

EMS FliNC - bV SETVHF RNGSET (IV for SM BURN _EMS FliNC - bVS BD ANT - OMNI CSECS LOGIC (2) - ONMSFN conhrm Go for PYRO ARMSECS PYRO ARM (2) - ARMCM RCS LOGIC - ON (ver~fy)

DSKY BLANKS

593028 16 85 VG XYZ (AVE G ON) (lfps)

RHCs amp THC - ARMEDLIMIT CYCLE - OFFTAPE RCDR - CMD RESETHBREMS MODE - NORMAL

000029 F 16 85 REQ NULL VG XYZ (lfps)

BURN EMS bV CTR TO ZERORESET DET amp COUNT UP

If SM ONLY burn go to step 32THC - LOCKEDSC CaNT - SCSFREERATE - HIGHPRIM GLY To RAD - BYPASS (ver~fy)

MN BUS TIE (2) - ON (ver~fy)

CMSM SEP (2) - on (up)CSMLM FNL SEP (2) - on (up) (verify)CampW MODE - CMRCS TRNFR - CMCM RCS LOGIC - OFF

Momtor VM ABIf lt25 vdc go to EMERGPOWER DOWN Pg E6-l

V63E

If CMC NO GO FDAI SOURCE - ATT FDAI SEL - 1 or 2 ATT SET - GDC

SET

-33-

~Uili ATT PITCH - ACCEL CMDFDAI SCALE - 55MNVR TO CM BURN ATT (NULL ERR NEEDLES)

R 0degPY --00--

30

31

CM RCS BURNRHC III-ContJnuous PJtch DownRHC HZ-Module PJtch to null needlesBURN VGZ TO ZERO

If only 1 RHC Pulse + P=5deg from retro att MaJnta~n rates lt3degsec

BURN COMPLETION ATllV CTR= or DET= _

V8ZE

32 F 16 44 HAHPTFF (1nmffiJn-sec)Check HP-

If gt Pad data contJnue burnuntJ1 lt Pad

PRO

33 F 16 85 VGXYZ (Ups)Read VG resJduals to MSFN

(HYBRID) PRO to 34(SM ONLY BURN)

PROF 37 ODE

EI-1500 V37E 47EF 16 83 twx Y Z (Ups)

SC CONT - SCSFREEMAN ATT (PITCH) - RATE CMDRATE - HIGHPRIM GLY To RAD - BYPASS (verJfy)MN BUS TIE (2) - ON (verJfy)CMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verJfy)Campl MODE - CMRCS TRNFR - CMCM ReS LOGIC - OFFSECS PYRO ~I (2) - SAFE

-34-

PROMonitor VMAB

If lt25 vdc go to EMERGPOWER DOWN

34 F 37 OOEPCM BIT RATE - LOWATT DB - MAXEMS MODE - STBYEMS FUNC - OFF

Go To EARTH ORBIT ENTRY pg _--40-__

-36-

8 SPS THRUSTING PREPCYCLE CRYO FANSSPS GAGING - ACI (ver~fy)

PUG MODE - NORM (venfy)BMAG MODE (3) - RATE 2tv CG - CSMCMC MODE - FREEAUTO RCS SEL (16) - MNA or HNB

(hftoff conbg)SC CONT - CMCAUTO

9 MNVR TO PAD BURN ATTV62E

10 V49E

11 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLESPRO

12 F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) PRO(HAN) SC CONT - ses

MNVR to 14

06 18 AUTO MNVR TO FDAI RPY ANGLES13

14 F 50 18 REO TRIH TO FDAI RPY ANGLES(TRIM) Go to 12(BYPASS) ENTR

15 BORESIGHT STAR CHECK

16 V37E 40EOPT PWR - OFF

17 F 50 18 REQUEST MNVR TO FDAI RPY ANGLES (01deg)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CHCAUTOPRO to 18

(MANDAP) BMAG HODE (3) - RATE 2SC CONT - CMCHOLDMNVR to 19

(HANseS) se eONT - sesMNVR to 19

-35-

54 NORMAL DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL ~V

1 V37E 30E

2 F 06 33 GETI (hrm~nOlsec)

(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

3 F 06 81 ~VXYZ (LV)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

( lfps)

4 F 06 42 HAHP~V (1nmlfps)Record W

(ACCEPT) PRO -----(REJECT) Rese1ect P30 or P27 Load new pa~am

5 F 16 45 MTFIMGA (marksmln-secOldeg)MGA -00002 If ~ lMU not a1~gned

SET DETPRO

6

7

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY v1v - OFFCAB PRESS REL v1v (2) - NORMcb ELS (2) - close (verify)cb SECS ARM (2) - close (ver~fy)

cb SECS LOGIC (2) - close (verlfy)AUTO RCS SEL CM (12) - ~mA or MNB

(l~ftoff conf~g)

ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM AampB - off (ctr)

18

-37-

06 18 AUTO MNVR TO FDAI RPY ANGLES (01 0)

19 l 50 18 REOUEST TRIM MNVR TOALIGN SIC ROLLGDC ALIGN

FDAI RPY ANGLES(010

)

+54-00m(-06-00)

TIG-5mJn

5500m(-0500)

TVC CHECK amp PREPcb STAB CONT SYS (all) - closecb SPS (12) - closeATT DB - MINRATE - LOl~

LIMIT CYCLE - ONMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE 2ROT CONTR PWR DIRECT (2) - OFFSCS TVC (2) - RATE CMD

If SCS SCS TVC (2) - AUTO SC CONT - SCS ~

TVC GMBL DRIVE PampY - AUTOMN BUS TIE (2) - ONTVC SERVO PWR 1 - AC1MNA

2 - AC2MNBTRANS CONTR PWR - ONROT CONTR PWR NORMAL 2 - ACRHC 2 - ARMED

HORIZ CHK - HorJz on 12deg wJndmlmark (LJffiJt +3 0 PNGCS GONO GO)

If NO GO set tw 180 0 180deg0 0

Track horJz wJth 24deg wJndow markAt TIG-2 mJn Ahgn GDC

PRIMARY TVC CHECKGMBL MOT P1-Y1 -STARTON(LMP confJrm)

If SCS verJfy Thumbwheel TrJmTHC - CWVenfy NO MTVC

SEC TVC CHECKGHBL MOT P2-Y2 -STARTON(LMP confJrm)SET GPI TRIHVenfy MTVCTHC NEUTRALGPI returns to 00 (CMC) or trJm (SCS)ROT CONT Pl~ NORM 2 - ACDC

(TRIM) Go to step 17(BYPASS) BMAG MODE(3) - ATTIRATE2 (ver1fy)

ENTR

-38-

20 F SO 25 00204 GMBL TEST OPTION(ACCEPT) SC CONT - GMC (ver~fy)

PROMonitor GPI Response

0020-2000020-200Tr~m

TEST FAIL SC CONT - SCS SCS TVC (2) - AUTO

(REJECT) ENTR

21 06 40 TFIVG~VM (m~n-sec1fps)

PROG ALM - TIG s1~pped

V5N9E 01703

KEY RLSE To 21 ROT CONTR PWR DIRECT (2) - MNABSPS He v1vs (2) - AUTO (ver~fy)

LIMIT CYCLE - OFFFDAI SCALE - SOIScb SPS P2Y2 - open (for cr~t burn)

5800(-02 00)

5925(-0035)

59middot 30(-0030)

06 40

59XX(-OOXX)

AV THRUST A(B) - NORMALTHC - ARMEDRlIC (2) - ARMEDTAPE RCDR - GID RESETHBR

DSKY BLANKS

(AVE G ON)EMS MODE - NORMAL

TFIVG~VM (m~n-seclfps)

CHECK PIPA BIAS lt2fps for 5 sec

ULLAGE AS REQ

IF NO ULLAGE DIR ULLAGE PB - PUSH~

CONTROL ATT WRlIC MONITOR AVM (R3) COUNTING UP

5955(-0005)

F 99 40 ENG ON ENABLE REQUEST(AUTO IGN) PRO AT TFI gt0 sec(BYPASS IGN) ENTR to 24

22 0000 IGN

-39-

If SCS - THRUST ON PB - PUSH

06 40 TFCVG~VM (m~n-seclfpslfps)

~F 97 40 SPS Thrust fall ~

~(RESTART) PRO To IGN (RECYCLE) ENTR To TIG-05 sec

SPS THRUST LITE - ONMONITOR THRUSTING

Pc 95-105 pSlaEMS COUNTING DOWNSPS IN3 v1vs (4) - OPENSPS He v1vs tb (2) - graySPS FUELOXID PRESS - 175-195 pSlaPUGS - BALANCED

PROG ALARM V5N9E 01407 VG INCTHC - CW FLY MTVC

ECOEMER SPS CUTOFF J

AV THRUST (2) - OFF

23 F 16 40 TFC(STATIC)VG~VM (mln-seclfps)~V THRUST AB - OFF

SPS IN3 v1vs (4) - CLOSEDSPS He tb (2) - bp

cb SPS P2Y2 - closed (verlfy)TVC SERVO PHR - AC1MNA (venfy)TVC SERVO PWR 2 - OFF

PRO

24 F 16 85 VG XYZ(CM) CUps)NULL RESIDUALSRECORD ~V CTR amp RESIDUALS I1VCEMS FUNC - OFF VGXEMS MODE - STBY VGYBMAG MODE (3) - RATE 2ATT DB - MAX VGZTRANS CONT PHR - OFF

PRO

25 F 37 V82E

26 F 16 44 HAHPTFF (lnmm~n-sec)

R3-59B59 HP gt494 nmPRO

27 F 37 OOE

-40-

55 EARTH ORBIT ENTRY

1 Venfy CMSMR __

P_shyY_-

SEP ATT(180deg)

(0deg )

2

3

4

EMS INITIALIZATIONEMS FUNC - RNG SETSET RNG TO PAD DATA RNGEMS FUNC - VA SETSlew scroll to pad data VIOEMS FUNC - ENTRY

RSI ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on(up)GDC ALIGN PB - PUSH amp HOLDYAW tw - Pos1tion RSI thru 45deg amp

back to LIFl UPGDC ALIGN PB - RELEASEEMS ROLL - OFFAl1gn GDC to lMU

PWR REDUCT (Norm Deorb Only)HGA PWR - OFFFC PUMPS (3) - OFFVer1fy s1ngle suit compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - Lowcb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2)-openlOb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MAN

-41-

P61 - ENTRY PREP

5 V37E 61E05 09 01427 - ROLL REVERSED05 09 01426 - IMU UNSAT

6 F 06 61 IMPACT LAT LONG liDS UPDN (+-)(01 0

010

+00001)

PRO

PAD VALUESLATLON==G------liDS UP DN _

7 F 06 60 GMAXV400KGAMMA EIRecord

GMAXV400K----GAMMA EI _

PRO

8 F 06 63 RTOGO (1nm) PAD _VIa (fps) PADTFE (mln-sec) ----Compare wlth MSFN for PGNS GONO GONO COMM SET RTOGO amp VIO IN EMS amp

INITIALIZE(ACCEPT) PRO(RECALC) V32E to 8

-42-

P62 - CMSM SEP amp PRE-ENTRY MNVR

9 F 50 25 00041 REQUEST CMSM SEPSC CONT - SCSFREEYAW - 45deg out-of-plane (left for RCS

nght for SPS)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE2PRIM GLY to RAD - BYPASS (verlfy)SECS LOGIC (2) - on (up)MSFN conflrm GO for PYRO ARMSECS PYRO ARM - ARMMN BUS TIE (2) - ON (verlfy)CMSM SEF (2) - ONCSMLM FNl SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 pSlaCM RCS LOGIC - OFFSECS PYRO ARM - SAFEMonltor VMAB

If lt25vdc go to EMERG POWERDOWN Pg E6-1AUTO RCS SEL AlC ROLL (4) - OFFAUTO RCS SEL CM 2(6) - OFFAUTO RCS SEL CM 1(6) - MNA or MNBYAW back to 00

PITCH TO ENTRY ATTROLL 0deg (LIFT UP)PITCH - HORIZ on 317deg MARK (400K)YAW 00

ATT DB - MAXMAN ATT (PITCH) - ACCEL CMDEMS DATA - VerifyEMS FUNC - ENTRY (verlfy)EMS MODE - NORMALMAINTAIN HORIZ TRK

PRO (Act ENTRY DAP)

10 F 06 61 IMPACT LAT LONG HDSDN(010 010 -00001)

PRO

11 FOSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axlS beyond 45deg of Vel vector)

-43-

P63 - ENTRY INIT

12 06 64 GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PWR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRHORIZ CKP~tch error needle goes toward

zero approach~ng 05G t~me

MAN ATT (PITCH) - RATE CMDIf CMC ~s GO

BMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS FLY BETA If CMC NO GO ~

SC CONT - SCS~

FLY EMS RCS Deorh Roll HDS UPTRACK HORIZ w~th 29deg w~ndow mk

P64 - ENTRY POST 05G

13

05G t=elt+0___)

06 68

RTOGO AT 05G AGREES WITH EMS - venfyHORIZ CK05E Lt - on (EMS start)

No EMS start w~th~n 3 secsEMS MODE - BACKUP VHF RNG 05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds L~ft DN

NNVR L~ft DNEMS GONO GO

G-V Plot w~th~n llm~ts

Rng ctr dwn 60 + 7 durlng 10 sec per~od

Mon~tor G-meter forconvergence wlth pad data (Do)

(Vlt27K fps) Go To 17

-44-

P65 - ENTRY - UP CONT (Vgt27K fps)

14 F 16 69 BETA (01deg)DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT~

SC CONT - SCS FLY EMS

PRO

15 06 68 BElA VI HOOT (01deg fpsfps)(VltVL +500 fps amp RDOT Neg) Go To 17

p66 - ENTRY - BALLISTIC (DltDL)

16 06 22 DESIRED GMBL ANGLES RPY (01deg)Mon~tor hor~z +12deg of 317deg mark

P67 - ENTRY - FINAL PHASE (02G)

17 0666 BETACRSRNG ERRDNRNG ERR (Oldeglnmlnm)KEY VERBRecord DNRNG ERR _KEY RLSEL~m~t +100nm from PAD DRE

Mon~tor l~ft vector on RSI amp FDAIF 16 67 RTOGOLATLONG (Vre1=1000fps)

(lnm 010 01deg)SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOlfflMon~tor altimeter

Go To EARTHLANDING pg _I4L5__

-45-

56 EARTHLANDING

90K STEAM PRESS - PEGGED50K CABIN PRESS REL vIv (2) - BOOSTENTRY

SECS PYRO ARM (2) - ARM

40K(90K + 63s)

CM UNSTABLE RCS CMD - OFF ~ 40K APEX COVER JETT PG-PUSH DROGUE DEPLOY PG - PUSH (2 secafter apex cover Jett)

30K ELS LOGIC - ON (up)ELS - AUTO

24K RCS hsable (auto)(90K+92s) RCS CMD - OFF

Apex cover Jett (auto)APEX COVER JETT PB - PUSH

(WAIT 2 SECS)Drogue parachutes deployed (auto)

DROGUE DEPLOY PB - PUSH~

If Drogues FallELS - ~ ~Stablllze CM 5K MAIN DPLY PB - PUSHELS - AUTO

235K Cabln Pressure lncreaslng (Drogues + 50s)If not lncreaSlng by 17K CABIN PRESS REL vlv (RR) - DUMP

-46-

10K Maln parachutes deployedMAIN DEPLOY PB - PUSH (wlthln 1 sec)VHF ANT - RECYVHF AMA - SIMPLEXVHF BCN - ONCABIN PRESS REL v1v (2) - CLOSEDIRECT 02 vlv - OPENCM RCS LOGIC - on (up)CM PRPLNT - DUMP (burn audlb1e)Monltor CM ReS 1amp2 for He press decrease

NO BURN or PRESS DECREASE USE BOTH RHCs DO NOT FIRE PITCH JETS

CM PRPLNT-PURGE (to zero He press)CM RCS He DUMP PB - PUSH RHC (2) - 30 sees NO PITCH k

STRUT LOCKS (2) - UNLOCK

cb FLT amp PL BAT BUS ABampBAT C (3) - closecb FLT amp PLT MNA amp B (2) - opencb ECS RAD HTR OVLD (2) - opencb SPS PampY (4) - open

3K CABIN PRESS REL v1v (RH) - DUMP (after purgecompleted)

FLOOD Lts - POST LDGCM RCS PRPLNT (2) - OFFROT CONTR PWR DIRECT (2) - OFF

800 CAB PRESS RELF vlv - CLOSE (latch off)MN BUS TIE (2) - OFF

AFTER LANDINGcb MAIN REL PYRO (2) - closeMAIN RELEASE - on(up)

Go to POSTLANDING pg _47L-__

I

2

3

-47-

57 POSTLANDING

STABILIZATION VENTILATION COMMUNICATIONS

DIRECT 02 vlv - CLOSE

Stablllzation after landlngELS - AUTO (verlfy)cb MAIN REL PYRO (2) - close (venfy)MAIN RELEASE - on (up) (verlfy)S~CS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb BAT RLY BUS (2) - open

No contact w1th recovery forcesVHF AM AampB - off (ctr) ~

VHF AM Rev ONLY - A cb PL VENT - closecb FLOAT BAG (3) - closecb UPRIGHT SYS COMPRESS (2) - closeIf Stable II

FLOAT BAG(3)-FILL t1ll 2 m1n afterupr1ght then - OFF

VHF AM AlB amp BCN - OFF whlle lnvertedIf Stable I

After 10 M1n Coollng Per1odFLOAT BAG (3) - FILL 7 mln then OFF

Post Stab1lizat1on And Ventllat10nPL BCN LT - BCN LT LOWPL VENT vlv - UNLOCK (Pull)Remove PL VENT Exh CoverPL VENT - HIGH or LOWPL DYE MARKER - ON (swlmmer comm)Release foots traps and_restralntscb MNA BAT BUS A amp BAT C (2) - opencb MNB BAT BUS B amp BAT C (2) - opencb FLT amp PL BAT C - opencb PYRO A SEQ A - opencb PYRO B SEQ B - open

EACH HR - CHECK DC VOLTSgt 275 V If Notmiddot cb FLT amp PL-BAT BUS AampB (2) -open cb FLT amp PL BAT C (1) - open GO TO LOW POWER CHECKLIST

Unstow and lnstall PLV DISTRIB DUCTDeploy grappllng hook and 11ne 1f req

4

-48-

Post Landing Communlcatl0nsVHF ANT-RECY (venfy)VHF BCN - ON (verlfy)

If no contact ~lth recovery forcesperform VHF BEACON Check

MONITOR VHF BEACON transmlSSlonnth VHF AM B Rcvr andor Su)vlval

TransceiverkVHF Beacon not operatlng ~connect Surv~val TranscelVer to antcable behlnd VHF ant access pnland place radio ln BCN mode

LOW POHER CHECKLISTVHF BCN - OFFVHF AM (3) - RCVFLOOD Lts - OFFVHF AM AampB - off (ctr)VHF AM RCV ONLY - A (venfy)COUCH LIGHTS - OFFPOSTLANDING VENT SYS mlnlmlze useSURV RADIO - plug mto VHF BCN ANT cableconn behind VHF ant acess pnl amp turn radloon l-n BCN mode

EGRESS PROCEDURES

CMPCDRLMPCDR

CMPCDRCMP

LMPLl1PCDR

STABLE IDlsconnect Umblll-calsNeck darn onCenter couch - 270 0 positionArmrests stowedConnect raft to SIC l-f desl-red wlth

green lanyardConnect raft ~hl-te lanyards to SUltS amp

lnflate water wlngs when eXltl-ngHATCH PISTON PRESS vlv - PRESS (Outbd)Slde Hatch openedPL VENT - OFFcb Pnl 250 (all) - openEgress with 11feraftPut hardware klt outEgress

or CDIPALL

CMF

CDRCMF

CDR

LMF

CMFCMP LMFCMP

UlP

CDR

-49-

STABLE IIcb CREW STA AUDIO (3) - openD~sconnect umb~1~ca1s

Release foots trapsRelease restra~nt harnessCouch seat pans (3) - 170 0 pos1t10nArm rests stowedSurv1va1 k~ts removed from stowageConnect life raft ma~n1~ne to CDR or SicConnect f~rst wh~te lanyard from

11fe raft to suitConnect th~rd wh~te lanyard from

l~fe raft to SU1tConnect rucksacks together to yellow

lanyard on raft bagPRESSURE EQUALIZATION vlv - OPENRemove and stow fwd hatchEX1t feet f1rst w1th rucksacks when clear

of siC 1nflate water w1ngs and raftExit feet f1rst when clear of SiC

1nflate water w1ngsEX1t feet f1rst when clear of sic

1nflate water w1ngs

-50-

60 TLI ABORTS

TLI Aborts are conta~ned ~n the ESD s~nce the bulk of the funct~ons

concern entry preparat20ns and performance Th~s allows a s2nglesource of procedures for procedure rev2ew val~dat~on checkout andtra~n~ng These procedures ~ncorporate TLI preparat20ns as found ~n

reference 6 w~th the TLI Abort Procedures and these t~e 2nto normallunar return Entry Procedures found ~n sect20n 5 The guidel~nes

for th~s cont2ngency are spec2f2ed 2n reference 7

In2t2al preparat~ons for TLI pos2t20n the necessary system sW2tches2n add~t~on to perform~ng an EMS ~V test and a GDC al~gnment Afterthe DET ~s set for mon2tor2ng TB6 the CMP ~ncreases the 12ght levelof the LEB DSKY to max~mum and returns to the h2s couch Th2s 2Sdone so that the LEB DSKY can be observed ~n the event sunl~ght orreflect20ns wash out the ma2n d2splay panel DSKY dur2ng cr2t2calmaneuvers The crew then straps ~n and prepares for mon2tor~ng TB6as 2nd2cated by the SII SEP L~te The t2mes se~uence of procedures2S keyed on th~s d~splay and ~ncludes the DET START funct~on andSIVB IGNITION Dur2ng the burn the crew mon2tors the FDAIs foratt~tude excurs20ns and abnormal rates report~ng status checks toM~ss2on Control at d2screet t~mes dur2ng the maneuver Upon SIVBSHUTDOWN the eMP records the DSKY d~splayed performance parametersand awa2ts ground conf2rmat~on

The rat~onal for TLI aborts ~s descr~bed 2n reference 7 A summar2shyzat20n 2S extracted to prov2de background and gu2de12nes 2n th2sdocument The abort procedures cover aborts 10 m2nutes after conshyt2ngent SIVE shutdown and aborts 90 m2nutes after normal SIVE shutshydown t2me

The 10 m~nute TLI abort ~s des2gned to be used dur~ng TLI ~n theevent a spacecraft problem develops Wh2Ch can result 2n catastrophe2f ~mmed~ate act~on 2S not taken If the s~tuat20n perm~ts the crewshould always allow the SIVB to complete TLI at wh~ch t~me the groundand crew can perform a malfunct~on analys~s to determ~ne ~f an abort~s adv~sable If a fa~lure occurs that necess2tates the shutdown ofthe SIVB and the ~u~ck return of the crew to earth th~s abort ~s

des~gned to be as ~nsens~t~ve to execut~on errors as poss~ble andst21l be targeted to m2dcorr2dor The burn att~tude w~th the f~ed

hor~zon reference ~s a constant value for any shutdown t~me Theburn durat~on 2S a funct20n of shutdown t2me and 2S ava21able fromcrew charts S~nce the pr~mary purpose of th~s abort ~s to returnto earth as qU2ckly as poss2ble there are no restr2ct20ns as toland~ng locat~on However ~f the t~me to EI is greater than abouttwo hours a midcourse correct20n should be ant~c~pated

The 90 m2nute TLI abort 2S to be used 2f a cr2t2cal subsystem malshyfunct~on ~s determ2ned and the dec2s~on to abort ~s made after the

-51-

TLI cutoff and before TLI cutoff plus approxlmately 80 m1nutesTh1S allows suff1c1ent separatlon and procedural t1me to set upfor the SPS deorb1t burn performed at about TLI + 90 Note thatgenerally the deorb1t burns w1ll be performed a fe11 m1nutes beforeTLI + 90 accord1ng to crew charts shown In reference 8 The no-comm except10n requ1res that 90 m1nutes be the 1nput t1me of 19n1shytlon for P-37 (onboard return-to-earth abort program) so that onshyboard calculatlons can correspond w1th ground calculat10ns to computethe CM land1ng p01nt Th1S TLI abort lS des1gned so that returnfl1ght t1me does not exceed 18 hours and abort ~V does not exceed7000 fps ThlS abort can be performed uSlng chart ~Vs and attltudesand the earths hor1zon serves as a suff1c1ent reference The maneushyver lS targeted to ach1eve the mldcorr1dor entry target Ilne andtlmed to result 1n a deslgnated recovery area

It 1S ObV10US for abort deC1S1ons early 1n the TLI + 90 m1nute t1meshyframe that a GampN SPS burn should be performed In order to keep theTLI abort procedures cons1stent and w1th emphasls on slmpl1c1ty theprocedures here reflect a SCS SPS abort burn to cover the full abortdec1s1on t1meframe

A m1dcourse correct1on for corr1dor control after a TLI abort may bedeS1red 1f the SPS burn d1d not meet expectat1ons The TLIabortprocedures 1n th1S sect10n adapt to the normal lunar return tlmel1neand procedures pr10r to the f1nal MCC

-52-

61 TLI PREPARATION PROCEDURES

GET = 150

CRO AOS(___)

CRO LOS( )(22142)

5100

Don Helmets amp Gloves

XLUNAR - INJECT (verify)EDS PWR - on (venfy)EMS FUNC - OFF (verlfy)EMS MODE - STBYEMS FUNC - IW SETVHF RNGEMS MODE - NORMALSet ~V indo to +15868 fpsEMS FUMC - ~V Test

SPS THRUST Lt - onoff (10 sec)~V lnd stops at -01 to -415

EMS MODE - STBYEMS FUMC - ~V SETVHF RNGSet ~VC

EMS FUNC---~~V=----

GDC ALIGNFDAI Select - liZcb SECS LOGIC (Z) - close (verify)cb SECS ARM (Z) - closeSECS LOGIC (Z) - on (up)MSFN Conflrm GO for PYRO ARM (If pass)SECS PYRO ARM (Z) - on (up)TRANS CONTROL PWR - ONROT CONTR PWR NORMAL (Z) - ACDC(verlfy)ROT CONTR PWR DIRECT (Z) - MNAMNBLV INnGPI - SIISIVB (venfy)LV GUID - IU (venfy)cb DIRECT ULLAGE (Z) - closedSet EVENT TIMER to 5100Begin MONITOR For TB6

CMP to Couch

TB 6 - SII SEP Lt on (TIG-9 mln 38 sec)KEY V83E

SET ORDEALFDAI Z ORB RATE at 180 0 0SII SEP Lt out (38 sec later)Start DET COUNTING UPSC CaNT - SCS (verify)MONITOR LV TANK PRESS

~P lt 36 psid (OXID gt FUEL)~P lt Z6 psid (FUEL gt OXID)

EMERGENCY CSMLV SEP UP TLM CM - BLOCK (verify)UP TLM IU - BLOCK (venfy)

-53-

+45degPY))0middot sec PY

lOK nmltHAlt25K nm

Two phas~ng mnvrs two SPS mnvrs to circular~ze at 150 nmearth orb~t

CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ssion 4K nmltHAltlOK nm CSM amp1M - Two phasing mnvrs two SPS mnvrs to circularize at 150 nm earth orb~t CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ss~on

CSM amp 1M - Two phas~ng mnvrs APS burn todepletion th~rd phasing mnvrSPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn tosem~sync orb~t

25K nmltHAlt40K nm CSM amp 1M - Two phasmg mnvrs APS burn to depletion third phas~ng mnvr SPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn to sem~sync orbit HA)40K nm DPS ava~l - DPS LOll circularize with SPS

DPS not ava~l - Lunar flyby or CSM only to lunar orbit (if reqd gtV lt4000 fps)

V37E 47E (check b~as) Record -=--rshy(Limit 98 fpsmm)

( 1fps)tVXYZN62EVIHDOTHPAD (fpsfpslnm)MONITOR VI ( ) at ECO

SCS TVC SERVO PWR 1 - ACIMNA2 - OFF

TAPE RCDR - CMD RESETHBREMS MODE - NORMAL

SIr SEP Lt - ONTLI Inhib~t S~gnals w~11 not be honored after 5942

SIVB ULLAGE BeginsSII SEP Lt - off (TIG - 18 sec)SIVB FUEL LEADSIVB ULLAGE d~scont~nues

LV ENG I Lt - onSIVB IGNITION ( GETI)LV ENG I Lt - off - -shyMONITOR THRUST amp ATTITUDEMONITOR LV TANK PRESSSIVE ECO (Lt on) (BEGIN TB7)

EMER SIVE CUTOFF AT 6 SEC PAST BURN TIME IF VI ATTAINEDTHC CCW ampNEUTRAL IN 1 SEC or SIISIVB sW - LV STAGEPremature Shutdown HAlt4K nm CSM amp 1M -

5700

58205836

F 16 835800

F 16 62

5838594259525955595900000002SUNRISE(___)

HAW AOS(__=_) KEY VERB (freeze d~splay)

SIVB ATT HOLD 20 sec amp BEGIN VENTINGSIVB NNVR TO ORB RT (HDS DN) (3middot sec)

Record VI -c---HDOT _

HPAD _

KEY RLSEF 16 62

F 16 83

HAW LOS(__=-)

KEYmiddotRLSE~VXYZ (lfps)

Record ~VX---_

~vy

WZ--

AVC---_

TAPE RCDR - off (ctr)EMS MODE - STBYEMS FUNC - OFFSECS PYRO ARM (2) - SAFE

PRO

BURN STATUS REPORT

____--~TIG

BT------VGX____-R

-----P----_Y

REMARKS

_____VI

______--HDOT______--H______---AVC______---FUEL_______OXID

_______UNBAL

F 3708=00 OOEGOS AOS CMP TO LEB

(-=-=-)

0000

0003

0005

0014

0100

-55-

62 TLI 10 MIN ABORTSECS LOGIC (2) - on (up)SECS PYRO ARM (2) - ARM

TRANS CONTR - CGH (4 sec) amp +XDET RESET (verlfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS GMD-ON

TRANS GONTR - neutral then +X for10 sec

SIVBGPI s~ - GPIExcesslve rates 6V THRUST A - NORMAL SPS THRUST - DIRECT When rates damped 6V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

TRANS CONTR +X - OFFV37E OOE

PITGH UP to LOGAL VERT (+X axlSto~ard the earth)

RATE - LOWBMAG MODE (3) - ATTIRATE 2EDS PHR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SEGS ARM (2) - opencb EDS (3) - open

TRANS CONTR -X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (180deg)P (199deg)Y (0deg)

RETRO UPDATEGETI _

JV _VG

Jtb ---GET 400K _

05G _GET DROGUE _

ENTRY P _R _

Y_--

0945

-56-

ALIGN HORIZ ON RET +1 MKGMBL CHECK (T11lle Pentattlng)MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conflnn)cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FUMC - JV SETVHF RNGSET JV from chartE~S FUMC - JVEMS fODE - NOIDlAL

lV THRUST A - NORMALV37E 47E (THRUST fONITOR)

F 16 83 lVXYZ (1 fps)

0950

1000

NOTE For aborts durlng 1st mln of TLIKEY V82E F 16 44 (HaHpTff)Burn untll Hp lt 19NM

TRANS CONTR +X

THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN JV reqdJV THRUST (2) - OFFReport cutoff

cb SPS P2 Y2- closeGfBL MTRS (4) - OFF (LMP Confinn)TRANS CONT PWR - OFFTVC SERVO PWR (2) - OFFMN BUS TIE (2) - OFFcb SPS P1amp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREIf est time to EIltOl5500 omlt fCC andenter the SUPERCIRC CKLIST as early as pos-slb1e Pg ~2~3~ __If est time to EI)Ol5500 anticlpate afCC Enter the ENTRY PREP CKLIST at step 9pg 18

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

-2tl C

l I W gt- ~-4

z laquo I I- 0 -6

l- I J u gt- ~-8

z w w -10

~_ONSANT

9O

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LIF

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OR

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TATI

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SH

ALL

OW

TAR

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TLI

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STE

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TAR

GE

TLI

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gU

ND

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OO

TBO

UN

DAR

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TRY

CO

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IDO

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-12 24

26

28

30

32

34

RE

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TRY

VE

LOC

ITY

VE

1-F

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6-i

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73

8X

03

-i- rtREQUIRED PITCH GIMBAL ANG LETO OBTAIN HOR-IZON AT 317

DEGREES IN wiiiiDOW

260

z~I- ~ i5 24000

1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

-I

-1-

NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

I LU HD~-

LUHD

lt0 120UJ0

~

80 HOLD PRESENT TRIMgt LU HD013

~Y~HOIgtlt

TOP OF WINDOWa 40to

31 7 SCRIBEaaI

80 TTOM OF WINDOWi= 0

0--ltoa

-40t-z

~~~Uw w u lt0 -80

HOLO PRESENT TRIlJCl

LOHU0 lt0

J gt -120 HOLD 059 TRIMlt0 z

LDHUlt0 FIELD OF VI S10 NLDHU LIFT-DOWNHEADS -UPLUHD LIFT-UP HEADS-DOWN

~~H~-160 q - P63 LIMITI- NOrE-VALIO ONLY FO~t~--

LUNAR RETURN VELOCITY

plusmnl8020 244middot 8 12 16

TIME TO 400K FT ALTITUDE-MIN

4

P37

LONG

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TOOB

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340

344

348

352

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120

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1968

400050

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2627

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Cll-

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120

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320

400

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3

-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 32: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

-29-

53 GampN HYBRID DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL tV1 V37E 30E

2 F 06 33 GETI(ACCEPT) PRO (hrm~n Olsec)(REJECT) LOAD DESIRED GETI

3 F 06 81 tVXYZ (LV) (lfps)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

4 F 06 42 HAHPtV (lnm lfps)Record tV

(ACCEPT) PRO(REJECT) Reselect P30 or P27 Load new paramo

5 F 16 45 MTFIMGA (marksm~n-secOlO)

MGA -00002 ~f k

k lMU not al~gned

SET DETPRO

6

7

8

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (Pull)PLSS 02 vlv - FILL02 8M SUPPLY vlv - OFFCAB PRESS REL vlv (2) - NORMcb ELS (2) - closecb SECS ARM (2) - closecb SECS LOGIC (2) - close (ver~fy)

AUTO RCS SEL CM (12) - MNA or ~ffiB

(hftoff conhg)ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM (AampB) - OFF

CMP to Couch

9

10

11

-30-

MNVR TO PAD BURN ATTLOAD DAPBMAG MODE (3) - RATE 2SC CONT - CMCAUTOATT DB - MINMAN ATT (3) - RATE CMD

v62E

v49E

12 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLES

PRO

13 F 50 18 REQ MNVR TO FDAI RPY ANGLES (01deg)(AUTO) PRO(MAN) SC CONT - SCS

BMAG MODE (3) - RATE 2MNVR To 15

14 06 18 AUTO MNVR TO FDAI RPY ANGLES (01deg)

15 F 50 18 REQ TRIM TO FDAI RPY ANGLES (01deg)(TRIM) Go to 13(ByPASS) ENTR

16

17

CHECK BORESIGHT amp SKT STARSOPT MODE - CMCOPT ZERO - OFF

v41 N91E

18 F 21 92 SHAFTTRUN (01deg 001deg)Load SXTS angles

19 41 OPTICS DRIVECheck SKT STAR

OPT ZERO - ZEROCheck BORESIGHT STAR (~f ava~l)

20 V25 N17E (01deg)Load Pad Data GMBL Angles

for CM BURN ATTATT SETtw - SET

to PAD DATA GMBL ANGLESfor CM BURN ATT

21

22

-31-

PHR REDUCTIONHGA PHR - OFFFC PUMPS (3) - OFFVerify s~ngle su~t compr oper loads

balancedFC 2 MN AampB - OFFS BD PiR AMP - LOWcb ECS RAD CONTHTR (2) - opencb HASTE H20URINE DUMP HTRS(2)- opencb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANMN BUS TIE (2) - ONTVC SERVO PHR 1 - AC1MNAGMBL MTR (4) - START

p41 - RCS THRUSTINGV37E 41E

23 F 50 18 REQ MNVR TO LCL HORIZ (HDS ON)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CMCAUTOPRO To 24

(gtfANDAP) BMAG MODE (3) - RATE 2SC CONT - CMCHOLD

V62EMNVR To 25

24 06 18 AUTO MNVR TO FDAI RPY

25 F 50 18 REQ TRIM TO LCL HORIZ (01deg)ALIGN SC ROLL

(AUTO TRIM) PRO To 24(BYPASS) ATT DB - MIN

RATE - LOHMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTlRATE 2

ENTR

550Om26 06 85

59middot2527

-32-

VGXYZ (1fps)RECHECK BORESIGHT STARTRANS CONIR PWR - on (up)EMS MODE - STBY (ver~fy)

EMS FliNC - bV SETVHF RNGSET (IV for SM BURN _EMS FliNC - bVS BD ANT - OMNI CSECS LOGIC (2) - ONMSFN conhrm Go for PYRO ARMSECS PYRO ARM (2) - ARMCM RCS LOGIC - ON (ver~fy)

DSKY BLANKS

593028 16 85 VG XYZ (AVE G ON) (lfps)

RHCs amp THC - ARMEDLIMIT CYCLE - OFFTAPE RCDR - CMD RESETHBREMS MODE - NORMAL

000029 F 16 85 REQ NULL VG XYZ (lfps)

BURN EMS bV CTR TO ZERORESET DET amp COUNT UP

If SM ONLY burn go to step 32THC - LOCKEDSC CaNT - SCSFREERATE - HIGHPRIM GLY To RAD - BYPASS (ver~fy)

MN BUS TIE (2) - ON (ver~fy)

CMSM SEP (2) - on (up)CSMLM FNL SEP (2) - on (up) (verify)CampW MODE - CMRCS TRNFR - CMCM RCS LOGIC - OFF

Momtor VM ABIf lt25 vdc go to EMERGPOWER DOWN Pg E6-l

V63E

If CMC NO GO FDAI SOURCE - ATT FDAI SEL - 1 or 2 ATT SET - GDC

SET

-33-

~Uili ATT PITCH - ACCEL CMDFDAI SCALE - 55MNVR TO CM BURN ATT (NULL ERR NEEDLES)

R 0degPY --00--

30

31

CM RCS BURNRHC III-ContJnuous PJtch DownRHC HZ-Module PJtch to null needlesBURN VGZ TO ZERO

If only 1 RHC Pulse + P=5deg from retro att MaJnta~n rates lt3degsec

BURN COMPLETION ATllV CTR= or DET= _

V8ZE

32 F 16 44 HAHPTFF (1nmffiJn-sec)Check HP-

If gt Pad data contJnue burnuntJ1 lt Pad

PRO

33 F 16 85 VGXYZ (Ups)Read VG resJduals to MSFN

(HYBRID) PRO to 34(SM ONLY BURN)

PROF 37 ODE

EI-1500 V37E 47EF 16 83 twx Y Z (Ups)

SC CONT - SCSFREEMAN ATT (PITCH) - RATE CMDRATE - HIGHPRIM GLY To RAD - BYPASS (verJfy)MN BUS TIE (2) - ON (verJfy)CMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verJfy)Campl MODE - CMRCS TRNFR - CMCM ReS LOGIC - OFFSECS PYRO ~I (2) - SAFE

-34-

PROMonitor VMAB

If lt25 vdc go to EMERGPOWER DOWN

34 F 37 OOEPCM BIT RATE - LOWATT DB - MAXEMS MODE - STBYEMS FUNC - OFF

Go To EARTH ORBIT ENTRY pg _--40-__

-36-

8 SPS THRUSTING PREPCYCLE CRYO FANSSPS GAGING - ACI (ver~fy)

PUG MODE - NORM (venfy)BMAG MODE (3) - RATE 2tv CG - CSMCMC MODE - FREEAUTO RCS SEL (16) - MNA or HNB

(hftoff conbg)SC CONT - CMCAUTO

9 MNVR TO PAD BURN ATTV62E

10 V49E

11 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLESPRO

12 F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) PRO(HAN) SC CONT - ses

MNVR to 14

06 18 AUTO MNVR TO FDAI RPY ANGLES13

14 F 50 18 REO TRIH TO FDAI RPY ANGLES(TRIM) Go to 12(BYPASS) ENTR

15 BORESIGHT STAR CHECK

16 V37E 40EOPT PWR - OFF

17 F 50 18 REQUEST MNVR TO FDAI RPY ANGLES (01deg)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CHCAUTOPRO to 18

(MANDAP) BMAG HODE (3) - RATE 2SC CONT - CMCHOLDMNVR to 19

(HANseS) se eONT - sesMNVR to 19

-35-

54 NORMAL DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL ~V

1 V37E 30E

2 F 06 33 GETI (hrm~nOlsec)

(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

3 F 06 81 ~VXYZ (LV)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

( lfps)

4 F 06 42 HAHP~V (1nmlfps)Record W

(ACCEPT) PRO -----(REJECT) Rese1ect P30 or P27 Load new pa~am

5 F 16 45 MTFIMGA (marksmln-secOldeg)MGA -00002 If ~ lMU not a1~gned

SET DETPRO

6

7

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY v1v - OFFCAB PRESS REL v1v (2) - NORMcb ELS (2) - close (verify)cb SECS ARM (2) - close (ver~fy)

cb SECS LOGIC (2) - close (verlfy)AUTO RCS SEL CM (12) - ~mA or MNB

(l~ftoff conf~g)

ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM AampB - off (ctr)

18

-37-

06 18 AUTO MNVR TO FDAI RPY ANGLES (01 0)

19 l 50 18 REOUEST TRIM MNVR TOALIGN SIC ROLLGDC ALIGN

FDAI RPY ANGLES(010

)

+54-00m(-06-00)

TIG-5mJn

5500m(-0500)

TVC CHECK amp PREPcb STAB CONT SYS (all) - closecb SPS (12) - closeATT DB - MINRATE - LOl~

LIMIT CYCLE - ONMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE 2ROT CONTR PWR DIRECT (2) - OFFSCS TVC (2) - RATE CMD

If SCS SCS TVC (2) - AUTO SC CONT - SCS ~

TVC GMBL DRIVE PampY - AUTOMN BUS TIE (2) - ONTVC SERVO PWR 1 - AC1MNA

2 - AC2MNBTRANS CONTR PWR - ONROT CONTR PWR NORMAL 2 - ACRHC 2 - ARMED

HORIZ CHK - HorJz on 12deg wJndmlmark (LJffiJt +3 0 PNGCS GONO GO)

If NO GO set tw 180 0 180deg0 0

Track horJz wJth 24deg wJndow markAt TIG-2 mJn Ahgn GDC

PRIMARY TVC CHECKGMBL MOT P1-Y1 -STARTON(LMP confJrm)

If SCS verJfy Thumbwheel TrJmTHC - CWVenfy NO MTVC

SEC TVC CHECKGHBL MOT P2-Y2 -STARTON(LMP confJrm)SET GPI TRIHVenfy MTVCTHC NEUTRALGPI returns to 00 (CMC) or trJm (SCS)ROT CONT Pl~ NORM 2 - ACDC

(TRIM) Go to step 17(BYPASS) BMAG MODE(3) - ATTIRATE2 (ver1fy)

ENTR

-38-

20 F SO 25 00204 GMBL TEST OPTION(ACCEPT) SC CONT - GMC (ver~fy)

PROMonitor GPI Response

0020-2000020-200Tr~m

TEST FAIL SC CONT - SCS SCS TVC (2) - AUTO

(REJECT) ENTR

21 06 40 TFIVG~VM (m~n-sec1fps)

PROG ALM - TIG s1~pped

V5N9E 01703

KEY RLSE To 21 ROT CONTR PWR DIRECT (2) - MNABSPS He v1vs (2) - AUTO (ver~fy)

LIMIT CYCLE - OFFFDAI SCALE - SOIScb SPS P2Y2 - open (for cr~t burn)

5800(-02 00)

5925(-0035)

59middot 30(-0030)

06 40

59XX(-OOXX)

AV THRUST A(B) - NORMALTHC - ARMEDRlIC (2) - ARMEDTAPE RCDR - GID RESETHBR

DSKY BLANKS

(AVE G ON)EMS MODE - NORMAL

TFIVG~VM (m~n-seclfps)

CHECK PIPA BIAS lt2fps for 5 sec

ULLAGE AS REQ

IF NO ULLAGE DIR ULLAGE PB - PUSH~

CONTROL ATT WRlIC MONITOR AVM (R3) COUNTING UP

5955(-0005)

F 99 40 ENG ON ENABLE REQUEST(AUTO IGN) PRO AT TFI gt0 sec(BYPASS IGN) ENTR to 24

22 0000 IGN

-39-

If SCS - THRUST ON PB - PUSH

06 40 TFCVG~VM (m~n-seclfpslfps)

~F 97 40 SPS Thrust fall ~

~(RESTART) PRO To IGN (RECYCLE) ENTR To TIG-05 sec

SPS THRUST LITE - ONMONITOR THRUSTING

Pc 95-105 pSlaEMS COUNTING DOWNSPS IN3 v1vs (4) - OPENSPS He v1vs tb (2) - graySPS FUELOXID PRESS - 175-195 pSlaPUGS - BALANCED

PROG ALARM V5N9E 01407 VG INCTHC - CW FLY MTVC

ECOEMER SPS CUTOFF J

AV THRUST (2) - OFF

23 F 16 40 TFC(STATIC)VG~VM (mln-seclfps)~V THRUST AB - OFF

SPS IN3 v1vs (4) - CLOSEDSPS He tb (2) - bp

cb SPS P2Y2 - closed (verlfy)TVC SERVO PHR - AC1MNA (venfy)TVC SERVO PWR 2 - OFF

PRO

24 F 16 85 VG XYZ(CM) CUps)NULL RESIDUALSRECORD ~V CTR amp RESIDUALS I1VCEMS FUNC - OFF VGXEMS MODE - STBY VGYBMAG MODE (3) - RATE 2ATT DB - MAX VGZTRANS CONT PHR - OFF

PRO

25 F 37 V82E

26 F 16 44 HAHPTFF (lnmm~n-sec)

R3-59B59 HP gt494 nmPRO

27 F 37 OOE

-40-

55 EARTH ORBIT ENTRY

1 Venfy CMSMR __

P_shyY_-

SEP ATT(180deg)

(0deg )

2

3

4

EMS INITIALIZATIONEMS FUNC - RNG SETSET RNG TO PAD DATA RNGEMS FUNC - VA SETSlew scroll to pad data VIOEMS FUNC - ENTRY

RSI ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on(up)GDC ALIGN PB - PUSH amp HOLDYAW tw - Pos1tion RSI thru 45deg amp

back to LIFl UPGDC ALIGN PB - RELEASEEMS ROLL - OFFAl1gn GDC to lMU

PWR REDUCT (Norm Deorb Only)HGA PWR - OFFFC PUMPS (3) - OFFVer1fy s1ngle suit compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - Lowcb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2)-openlOb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MAN

-41-

P61 - ENTRY PREP

5 V37E 61E05 09 01427 - ROLL REVERSED05 09 01426 - IMU UNSAT

6 F 06 61 IMPACT LAT LONG liDS UPDN (+-)(01 0

010

+00001)

PRO

PAD VALUESLATLON==G------liDS UP DN _

7 F 06 60 GMAXV400KGAMMA EIRecord

GMAXV400K----GAMMA EI _

PRO

8 F 06 63 RTOGO (1nm) PAD _VIa (fps) PADTFE (mln-sec) ----Compare wlth MSFN for PGNS GONO GONO COMM SET RTOGO amp VIO IN EMS amp

INITIALIZE(ACCEPT) PRO(RECALC) V32E to 8

-42-

P62 - CMSM SEP amp PRE-ENTRY MNVR

9 F 50 25 00041 REQUEST CMSM SEPSC CONT - SCSFREEYAW - 45deg out-of-plane (left for RCS

nght for SPS)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE2PRIM GLY to RAD - BYPASS (verlfy)SECS LOGIC (2) - on (up)MSFN conflrm GO for PYRO ARMSECS PYRO ARM - ARMMN BUS TIE (2) - ON (verlfy)CMSM SEF (2) - ONCSMLM FNl SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 pSlaCM RCS LOGIC - OFFSECS PYRO ARM - SAFEMonltor VMAB

If lt25vdc go to EMERG POWERDOWN Pg E6-1AUTO RCS SEL AlC ROLL (4) - OFFAUTO RCS SEL CM 2(6) - OFFAUTO RCS SEL CM 1(6) - MNA or MNBYAW back to 00

PITCH TO ENTRY ATTROLL 0deg (LIFT UP)PITCH - HORIZ on 317deg MARK (400K)YAW 00

ATT DB - MAXMAN ATT (PITCH) - ACCEL CMDEMS DATA - VerifyEMS FUNC - ENTRY (verlfy)EMS MODE - NORMALMAINTAIN HORIZ TRK

PRO (Act ENTRY DAP)

10 F 06 61 IMPACT LAT LONG HDSDN(010 010 -00001)

PRO

11 FOSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axlS beyond 45deg of Vel vector)

-43-

P63 - ENTRY INIT

12 06 64 GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PWR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRHORIZ CKP~tch error needle goes toward

zero approach~ng 05G t~me

MAN ATT (PITCH) - RATE CMDIf CMC ~s GO

BMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS FLY BETA If CMC NO GO ~

SC CONT - SCS~

FLY EMS RCS Deorh Roll HDS UPTRACK HORIZ w~th 29deg w~ndow mk

P64 - ENTRY POST 05G

13

05G t=elt+0___)

06 68

RTOGO AT 05G AGREES WITH EMS - venfyHORIZ CK05E Lt - on (EMS start)

No EMS start w~th~n 3 secsEMS MODE - BACKUP VHF RNG 05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds L~ft DN

NNVR L~ft DNEMS GONO GO

G-V Plot w~th~n llm~ts

Rng ctr dwn 60 + 7 durlng 10 sec per~od

Mon~tor G-meter forconvergence wlth pad data (Do)

(Vlt27K fps) Go To 17

-44-

P65 - ENTRY - UP CONT (Vgt27K fps)

14 F 16 69 BETA (01deg)DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT~

SC CONT - SCS FLY EMS

PRO

15 06 68 BElA VI HOOT (01deg fpsfps)(VltVL +500 fps amp RDOT Neg) Go To 17

p66 - ENTRY - BALLISTIC (DltDL)

16 06 22 DESIRED GMBL ANGLES RPY (01deg)Mon~tor hor~z +12deg of 317deg mark

P67 - ENTRY - FINAL PHASE (02G)

17 0666 BETACRSRNG ERRDNRNG ERR (Oldeglnmlnm)KEY VERBRecord DNRNG ERR _KEY RLSEL~m~t +100nm from PAD DRE

Mon~tor l~ft vector on RSI amp FDAIF 16 67 RTOGOLATLONG (Vre1=1000fps)

(lnm 010 01deg)SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOlfflMon~tor altimeter

Go To EARTHLANDING pg _I4L5__

-45-

56 EARTHLANDING

90K STEAM PRESS - PEGGED50K CABIN PRESS REL vIv (2) - BOOSTENTRY

SECS PYRO ARM (2) - ARM

40K(90K + 63s)

CM UNSTABLE RCS CMD - OFF ~ 40K APEX COVER JETT PG-PUSH DROGUE DEPLOY PG - PUSH (2 secafter apex cover Jett)

30K ELS LOGIC - ON (up)ELS - AUTO

24K RCS hsable (auto)(90K+92s) RCS CMD - OFF

Apex cover Jett (auto)APEX COVER JETT PB - PUSH

(WAIT 2 SECS)Drogue parachutes deployed (auto)

DROGUE DEPLOY PB - PUSH~

If Drogues FallELS - ~ ~Stablllze CM 5K MAIN DPLY PB - PUSHELS - AUTO

235K Cabln Pressure lncreaslng (Drogues + 50s)If not lncreaSlng by 17K CABIN PRESS REL vlv (RR) - DUMP

-46-

10K Maln parachutes deployedMAIN DEPLOY PB - PUSH (wlthln 1 sec)VHF ANT - RECYVHF AMA - SIMPLEXVHF BCN - ONCABIN PRESS REL v1v (2) - CLOSEDIRECT 02 vlv - OPENCM RCS LOGIC - on (up)CM PRPLNT - DUMP (burn audlb1e)Monltor CM ReS 1amp2 for He press decrease

NO BURN or PRESS DECREASE USE BOTH RHCs DO NOT FIRE PITCH JETS

CM PRPLNT-PURGE (to zero He press)CM RCS He DUMP PB - PUSH RHC (2) - 30 sees NO PITCH k

STRUT LOCKS (2) - UNLOCK

cb FLT amp PL BAT BUS ABampBAT C (3) - closecb FLT amp PLT MNA amp B (2) - opencb ECS RAD HTR OVLD (2) - opencb SPS PampY (4) - open

3K CABIN PRESS REL v1v (RH) - DUMP (after purgecompleted)

FLOOD Lts - POST LDGCM RCS PRPLNT (2) - OFFROT CONTR PWR DIRECT (2) - OFF

800 CAB PRESS RELF vlv - CLOSE (latch off)MN BUS TIE (2) - OFF

AFTER LANDINGcb MAIN REL PYRO (2) - closeMAIN RELEASE - on(up)

Go to POSTLANDING pg _47L-__

I

2

3

-47-

57 POSTLANDING

STABILIZATION VENTILATION COMMUNICATIONS

DIRECT 02 vlv - CLOSE

Stablllzation after landlngELS - AUTO (verlfy)cb MAIN REL PYRO (2) - close (venfy)MAIN RELEASE - on (up) (verlfy)S~CS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb BAT RLY BUS (2) - open

No contact w1th recovery forcesVHF AM AampB - off (ctr) ~

VHF AM Rev ONLY - A cb PL VENT - closecb FLOAT BAG (3) - closecb UPRIGHT SYS COMPRESS (2) - closeIf Stable II

FLOAT BAG(3)-FILL t1ll 2 m1n afterupr1ght then - OFF

VHF AM AlB amp BCN - OFF whlle lnvertedIf Stable I

After 10 M1n Coollng Per1odFLOAT BAG (3) - FILL 7 mln then OFF

Post Stab1lizat1on And Ventllat10nPL BCN LT - BCN LT LOWPL VENT vlv - UNLOCK (Pull)Remove PL VENT Exh CoverPL VENT - HIGH or LOWPL DYE MARKER - ON (swlmmer comm)Release foots traps and_restralntscb MNA BAT BUS A amp BAT C (2) - opencb MNB BAT BUS B amp BAT C (2) - opencb FLT amp PL BAT C - opencb PYRO A SEQ A - opencb PYRO B SEQ B - open

EACH HR - CHECK DC VOLTSgt 275 V If Notmiddot cb FLT amp PL-BAT BUS AampB (2) -open cb FLT amp PL BAT C (1) - open GO TO LOW POWER CHECKLIST

Unstow and lnstall PLV DISTRIB DUCTDeploy grappllng hook and 11ne 1f req

4

-48-

Post Landing Communlcatl0nsVHF ANT-RECY (venfy)VHF BCN - ON (verlfy)

If no contact ~lth recovery forcesperform VHF BEACON Check

MONITOR VHF BEACON transmlSSlonnth VHF AM B Rcvr andor Su)vlval

TransceiverkVHF Beacon not operatlng ~connect Surv~val TranscelVer to antcable behlnd VHF ant access pnland place radio ln BCN mode

LOW POHER CHECKLISTVHF BCN - OFFVHF AM (3) - RCVFLOOD Lts - OFFVHF AM AampB - off (ctr)VHF AM RCV ONLY - A (venfy)COUCH LIGHTS - OFFPOSTLANDING VENT SYS mlnlmlze useSURV RADIO - plug mto VHF BCN ANT cableconn behind VHF ant acess pnl amp turn radloon l-n BCN mode

EGRESS PROCEDURES

CMPCDRLMPCDR

CMPCDRCMP

LMPLl1PCDR

STABLE IDlsconnect Umblll-calsNeck darn onCenter couch - 270 0 positionArmrests stowedConnect raft to SIC l-f desl-red wlth

green lanyardConnect raft ~hl-te lanyards to SUltS amp

lnflate water wlngs when eXltl-ngHATCH PISTON PRESS vlv - PRESS (Outbd)Slde Hatch openedPL VENT - OFFcb Pnl 250 (all) - openEgress with 11feraftPut hardware klt outEgress

or CDIPALL

CMF

CDRCMF

CDR

LMF

CMFCMP LMFCMP

UlP

CDR

-49-

STABLE IIcb CREW STA AUDIO (3) - openD~sconnect umb~1~ca1s

Release foots trapsRelease restra~nt harnessCouch seat pans (3) - 170 0 pos1t10nArm rests stowedSurv1va1 k~ts removed from stowageConnect life raft ma~n1~ne to CDR or SicConnect f~rst wh~te lanyard from

11fe raft to suitConnect th~rd wh~te lanyard from

l~fe raft to SU1tConnect rucksacks together to yellow

lanyard on raft bagPRESSURE EQUALIZATION vlv - OPENRemove and stow fwd hatchEX1t feet f1rst w1th rucksacks when clear

of siC 1nflate water w1ngs and raftExit feet f1rst when clear of SiC

1nflate water w1ngsEX1t feet f1rst when clear of sic

1nflate water w1ngs

-50-

60 TLI ABORTS

TLI Aborts are conta~ned ~n the ESD s~nce the bulk of the funct~ons

concern entry preparat20ns and performance Th~s allows a s2nglesource of procedures for procedure rev2ew val~dat~on checkout andtra~n~ng These procedures ~ncorporate TLI preparat20ns as found ~n

reference 6 w~th the TLI Abort Procedures and these t~e 2nto normallunar return Entry Procedures found ~n sect20n 5 The guidel~nes

for th~s cont2ngency are spec2f2ed 2n reference 7

In2t2al preparat~ons for TLI pos2t20n the necessary system sW2tches2n add~t~on to perform~ng an EMS ~V test and a GDC al~gnment Afterthe DET ~s set for mon2tor2ng TB6 the CMP ~ncreases the 12ght levelof the LEB DSKY to max~mum and returns to the h2s couch Th2s 2Sdone so that the LEB DSKY can be observed ~n the event sunl~ght orreflect20ns wash out the ma2n d2splay panel DSKY dur2ng cr2t2calmaneuvers The crew then straps ~n and prepares for mon2tor~ng TB6as 2nd2cated by the SII SEP L~te The t2mes se~uence of procedures2S keyed on th~s d~splay and ~ncludes the DET START funct~on andSIVB IGNITION Dur2ng the burn the crew mon2tors the FDAIs foratt~tude excurs20ns and abnormal rates report~ng status checks toM~ss2on Control at d2screet t~mes dur2ng the maneuver Upon SIVBSHUTDOWN the eMP records the DSKY d~splayed performance parametersand awa2ts ground conf2rmat~on

The rat~onal for TLI aborts ~s descr~bed 2n reference 7 A summar2shyzat20n 2S extracted to prov2de background and gu2de12nes 2n th2sdocument The abort procedures cover aborts 10 m2nutes after conshyt2ngent SIVE shutdown and aborts 90 m2nutes after normal SIVE shutshydown t2me

The 10 m~nute TLI abort ~s des2gned to be used dur~ng TLI ~n theevent a spacecraft problem develops Wh2Ch can result 2n catastrophe2f ~mmed~ate act~on 2S not taken If the s~tuat20n perm~ts the crewshould always allow the SIVB to complete TLI at wh~ch t~me the groundand crew can perform a malfunct~on analys~s to determ~ne ~f an abort~s adv~sable If a fa~lure occurs that necess2tates the shutdown ofthe SIVB and the ~u~ck return of the crew to earth th~s abort ~s

des~gned to be as ~nsens~t~ve to execut~on errors as poss~ble andst21l be targeted to m2dcorr2dor The burn att~tude w~th the f~ed

hor~zon reference ~s a constant value for any shutdown t~me Theburn durat~on 2S a funct20n of shutdown t2me and 2S ava21able fromcrew charts S~nce the pr~mary purpose of th~s abort ~s to returnto earth as qU2ckly as poss2ble there are no restr2ct20ns as toland~ng locat~on However ~f the t~me to EI is greater than abouttwo hours a midcourse correct20n should be ant~c~pated

The 90 m2nute TLI abort 2S to be used 2f a cr2t2cal subsystem malshyfunct~on ~s determ2ned and the dec2s~on to abort ~s made after the

-51-

TLI cutoff and before TLI cutoff plus approxlmately 80 m1nutesTh1S allows suff1c1ent separatlon and procedural t1me to set upfor the SPS deorb1t burn performed at about TLI + 90 Note thatgenerally the deorb1t burns w1ll be performed a fe11 m1nutes beforeTLI + 90 accord1ng to crew charts shown In reference 8 The no-comm except10n requ1res that 90 m1nutes be the 1nput t1me of 19n1shytlon for P-37 (onboard return-to-earth abort program) so that onshyboard calculatlons can correspond w1th ground calculat10ns to computethe CM land1ng p01nt Th1S TLI abort lS des1gned so that returnfl1ght t1me does not exceed 18 hours and abort ~V does not exceed7000 fps ThlS abort can be performed uSlng chart ~Vs and attltudesand the earths hor1zon serves as a suff1c1ent reference The maneushyver lS targeted to ach1eve the mldcorr1dor entry target Ilne andtlmed to result 1n a deslgnated recovery area

It 1S ObV10US for abort deC1S1ons early 1n the TLI + 90 m1nute t1meshyframe that a GampN SPS burn should be performed In order to keep theTLI abort procedures cons1stent and w1th emphasls on slmpl1c1ty theprocedures here reflect a SCS SPS abort burn to cover the full abortdec1s1on t1meframe

A m1dcourse correct1on for corr1dor control after a TLI abort may bedeS1red 1f the SPS burn d1d not meet expectat1ons The TLIabortprocedures 1n th1S sect10n adapt to the normal lunar return tlmel1neand procedures pr10r to the f1nal MCC

-52-

61 TLI PREPARATION PROCEDURES

GET = 150

CRO AOS(___)

CRO LOS( )(22142)

5100

Don Helmets amp Gloves

XLUNAR - INJECT (verify)EDS PWR - on (venfy)EMS FUNC - OFF (verlfy)EMS MODE - STBYEMS FUNC - IW SETVHF RNGEMS MODE - NORMALSet ~V indo to +15868 fpsEMS FUMC - ~V Test

SPS THRUST Lt - onoff (10 sec)~V lnd stops at -01 to -415

EMS MODE - STBYEMS FUMC - ~V SETVHF RNGSet ~VC

EMS FUNC---~~V=----

GDC ALIGNFDAI Select - liZcb SECS LOGIC (Z) - close (verify)cb SECS ARM (Z) - closeSECS LOGIC (Z) - on (up)MSFN Conflrm GO for PYRO ARM (If pass)SECS PYRO ARM (Z) - on (up)TRANS CONTROL PWR - ONROT CONTR PWR NORMAL (Z) - ACDC(verlfy)ROT CONTR PWR DIRECT (Z) - MNAMNBLV INnGPI - SIISIVB (venfy)LV GUID - IU (venfy)cb DIRECT ULLAGE (Z) - closedSet EVENT TIMER to 5100Begin MONITOR For TB6

CMP to Couch

TB 6 - SII SEP Lt on (TIG-9 mln 38 sec)KEY V83E

SET ORDEALFDAI Z ORB RATE at 180 0 0SII SEP Lt out (38 sec later)Start DET COUNTING UPSC CaNT - SCS (verify)MONITOR LV TANK PRESS

~P lt 36 psid (OXID gt FUEL)~P lt Z6 psid (FUEL gt OXID)

EMERGENCY CSMLV SEP UP TLM CM - BLOCK (verify)UP TLM IU - BLOCK (venfy)

-53-

+45degPY))0middot sec PY

lOK nmltHAlt25K nm

Two phas~ng mnvrs two SPS mnvrs to circular~ze at 150 nmearth orb~t

CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ssion 4K nmltHAltlOK nm CSM amp1M - Two phasing mnvrs two SPS mnvrs to circularize at 150 nm earth orb~t CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ss~on

CSM amp 1M - Two phas~ng mnvrs APS burn todepletion th~rd phasing mnvrSPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn tosem~sync orb~t

25K nmltHAlt40K nm CSM amp 1M - Two phasmg mnvrs APS burn to depletion third phas~ng mnvr SPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn to sem~sync orbit HA)40K nm DPS ava~l - DPS LOll circularize with SPS

DPS not ava~l - Lunar flyby or CSM only to lunar orbit (if reqd gtV lt4000 fps)

V37E 47E (check b~as) Record -=--rshy(Limit 98 fpsmm)

( 1fps)tVXYZN62EVIHDOTHPAD (fpsfpslnm)MONITOR VI ( ) at ECO

SCS TVC SERVO PWR 1 - ACIMNA2 - OFF

TAPE RCDR - CMD RESETHBREMS MODE - NORMAL

SIr SEP Lt - ONTLI Inhib~t S~gnals w~11 not be honored after 5942

SIVB ULLAGE BeginsSII SEP Lt - off (TIG - 18 sec)SIVB FUEL LEADSIVB ULLAGE d~scont~nues

LV ENG I Lt - onSIVB IGNITION ( GETI)LV ENG I Lt - off - -shyMONITOR THRUST amp ATTITUDEMONITOR LV TANK PRESSSIVE ECO (Lt on) (BEGIN TB7)

EMER SIVE CUTOFF AT 6 SEC PAST BURN TIME IF VI ATTAINEDTHC CCW ampNEUTRAL IN 1 SEC or SIISIVB sW - LV STAGEPremature Shutdown HAlt4K nm CSM amp 1M -

5700

58205836

F 16 835800

F 16 62

5838594259525955595900000002SUNRISE(___)

HAW AOS(__=_) KEY VERB (freeze d~splay)

SIVB ATT HOLD 20 sec amp BEGIN VENTINGSIVB NNVR TO ORB RT (HDS DN) (3middot sec)

Record VI -c---HDOT _

HPAD _

KEY RLSEF 16 62

F 16 83

HAW LOS(__=-)

KEYmiddotRLSE~VXYZ (lfps)

Record ~VX---_

~vy

WZ--

AVC---_

TAPE RCDR - off (ctr)EMS MODE - STBYEMS FUNC - OFFSECS PYRO ARM (2) - SAFE

PRO

BURN STATUS REPORT

____--~TIG

BT------VGX____-R

-----P----_Y

REMARKS

_____VI

______--HDOT______--H______---AVC______---FUEL_______OXID

_______UNBAL

F 3708=00 OOEGOS AOS CMP TO LEB

(-=-=-)

0000

0003

0005

0014

0100

-55-

62 TLI 10 MIN ABORTSECS LOGIC (2) - on (up)SECS PYRO ARM (2) - ARM

TRANS CONTR - CGH (4 sec) amp +XDET RESET (verlfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS GMD-ON

TRANS GONTR - neutral then +X for10 sec

SIVBGPI s~ - GPIExcesslve rates 6V THRUST A - NORMAL SPS THRUST - DIRECT When rates damped 6V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

TRANS CONTR +X - OFFV37E OOE

PITGH UP to LOGAL VERT (+X axlSto~ard the earth)

RATE - LOWBMAG MODE (3) - ATTIRATE 2EDS PHR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SEGS ARM (2) - opencb EDS (3) - open

TRANS CONTR -X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (180deg)P (199deg)Y (0deg)

RETRO UPDATEGETI _

JV _VG

Jtb ---GET 400K _

05G _GET DROGUE _

ENTRY P _R _

Y_--

0945

-56-

ALIGN HORIZ ON RET +1 MKGMBL CHECK (T11lle Pentattlng)MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conflnn)cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FUMC - JV SETVHF RNGSET JV from chartE~S FUMC - JVEMS fODE - NOIDlAL

lV THRUST A - NORMALV37E 47E (THRUST fONITOR)

F 16 83 lVXYZ (1 fps)

0950

1000

NOTE For aborts durlng 1st mln of TLIKEY V82E F 16 44 (HaHpTff)Burn untll Hp lt 19NM

TRANS CONTR +X

THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN JV reqdJV THRUST (2) - OFFReport cutoff

cb SPS P2 Y2- closeGfBL MTRS (4) - OFF (LMP Confinn)TRANS CONT PWR - OFFTVC SERVO PWR (2) - OFFMN BUS TIE (2) - OFFcb SPS P1amp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREIf est time to EIltOl5500 omlt fCC andenter the SUPERCIRC CKLIST as early as pos-slb1e Pg ~2~3~ __If est time to EI)Ol5500 anticlpate afCC Enter the ENTRY PREP CKLIST at step 9pg 18

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

-2tl C

l I W gt- ~-4

z laquo I I- 0 -6

l- I J u gt- ~-8

z w w -10

~_ONSANT

9O

VER

SHO

OT

BOU

ND

ARY

LIF

TV

EC

TOR

OR

IEN

TATI

ON

LIN

E

SH

ALL

OW

TAR

GE

TLI

NE

STE

EP

TAR

GE

TLI

NE 12

gU

ND

ERSH

OO

TBO

UN

DAR

Y

RE

EN

TRY

CO

RR

IDO

R

I ~ I

-12 24

26

28

30

32

34

RE

EN

TRY

VE

LOC

ITY

VE

1-F

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EC

Ch

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36

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6-i

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CC

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ST

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bull-1

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2829

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J23

33

43

5IN

ER

TIA

LR

EE

NTR

YV

ELO

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YA

T4

00

00

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VE

I-F

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EC

Ch

art

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J63

73

8X

03

-i- rtREQUIRED PITCH GIMBAL ANG LETO OBTAIN HOR-IZON AT 317

DEGREES IN wiiiiDOW

260

z~I- ~ i5 24000

1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

-I

-1-

NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

I LU HD~-

LUHD

lt0 120UJ0

~

80 HOLD PRESENT TRIMgt LU HD013

~Y~HOIgtlt

TOP OF WINDOWa 40to

31 7 SCRIBEaaI

80 TTOM OF WINDOWi= 0

0--ltoa

-40t-z

~~~Uw w u lt0 -80

HOLO PRESENT TRIlJCl

LOHU0 lt0

J gt -120 HOLD 059 TRIMlt0 z

LDHUlt0 FIELD OF VI S10 NLDHU LIFT-DOWNHEADS -UPLUHD LIFT-UP HEADS-DOWN

~~H~-160 q - P63 LIMITI- NOrE-VALIO ONLY FO~t~--

LUNAR RETURN VELOCITY

plusmnl8020 244middot 8 12 16

TIME TO 400K FT ALTITUDE-MIN

4

P37

LONG

ITUD

ECO

RREC

TION

TOOB

TAIN

1350

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ENTR

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344

348

352

356

364

368

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-----

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---------O

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1000

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00 70

00 60

00 i50

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120

200

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6V-

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EC

240

320

400

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DEC

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1968

400050

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2627

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7

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C90

0080

0070

0060

0050

0040

0030

0020

0010

000

II

II

II

II

S-IV

BBU

RNTI

ME

-M

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Cll-

41)

120

200

241)

320

400

441)

520

TlI

-I0

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ABOR

TlA

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-DE

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19

68

lAUN

CHA

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UTH

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3

-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 33: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

9

10

11

-30-

MNVR TO PAD BURN ATTLOAD DAPBMAG MODE (3) - RATE 2SC CONT - CMCAUTOATT DB - MINMAN ATT (3) - RATE CMD

v62E

v49E

12 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLES

PRO

13 F 50 18 REQ MNVR TO FDAI RPY ANGLES (01deg)(AUTO) PRO(MAN) SC CONT - SCS

BMAG MODE (3) - RATE 2MNVR To 15

14 06 18 AUTO MNVR TO FDAI RPY ANGLES (01deg)

15 F 50 18 REQ TRIM TO FDAI RPY ANGLES (01deg)(TRIM) Go to 13(ByPASS) ENTR

16

17

CHECK BORESIGHT amp SKT STARSOPT MODE - CMCOPT ZERO - OFF

v41 N91E

18 F 21 92 SHAFTTRUN (01deg 001deg)Load SXTS angles

19 41 OPTICS DRIVECheck SKT STAR

OPT ZERO - ZEROCheck BORESIGHT STAR (~f ava~l)

20 V25 N17E (01deg)Load Pad Data GMBL Angles

for CM BURN ATTATT SETtw - SET

to PAD DATA GMBL ANGLESfor CM BURN ATT

21

22

-31-

PHR REDUCTIONHGA PHR - OFFFC PUMPS (3) - OFFVerify s~ngle su~t compr oper loads

balancedFC 2 MN AampB - OFFS BD PiR AMP - LOWcb ECS RAD CONTHTR (2) - opencb HASTE H20URINE DUMP HTRS(2)- opencb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANMN BUS TIE (2) - ONTVC SERVO PHR 1 - AC1MNAGMBL MTR (4) - START

p41 - RCS THRUSTINGV37E 41E

23 F 50 18 REQ MNVR TO LCL HORIZ (HDS ON)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CMCAUTOPRO To 24

(gtfANDAP) BMAG MODE (3) - RATE 2SC CONT - CMCHOLD

V62EMNVR To 25

24 06 18 AUTO MNVR TO FDAI RPY

25 F 50 18 REQ TRIM TO LCL HORIZ (01deg)ALIGN SC ROLL

(AUTO TRIM) PRO To 24(BYPASS) ATT DB - MIN

RATE - LOHMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTlRATE 2

ENTR

550Om26 06 85

59middot2527

-32-

VGXYZ (1fps)RECHECK BORESIGHT STARTRANS CONIR PWR - on (up)EMS MODE - STBY (ver~fy)

EMS FliNC - bV SETVHF RNGSET (IV for SM BURN _EMS FliNC - bVS BD ANT - OMNI CSECS LOGIC (2) - ONMSFN conhrm Go for PYRO ARMSECS PYRO ARM (2) - ARMCM RCS LOGIC - ON (ver~fy)

DSKY BLANKS

593028 16 85 VG XYZ (AVE G ON) (lfps)

RHCs amp THC - ARMEDLIMIT CYCLE - OFFTAPE RCDR - CMD RESETHBREMS MODE - NORMAL

000029 F 16 85 REQ NULL VG XYZ (lfps)

BURN EMS bV CTR TO ZERORESET DET amp COUNT UP

If SM ONLY burn go to step 32THC - LOCKEDSC CaNT - SCSFREERATE - HIGHPRIM GLY To RAD - BYPASS (ver~fy)

MN BUS TIE (2) - ON (ver~fy)

CMSM SEP (2) - on (up)CSMLM FNL SEP (2) - on (up) (verify)CampW MODE - CMRCS TRNFR - CMCM RCS LOGIC - OFF

Momtor VM ABIf lt25 vdc go to EMERGPOWER DOWN Pg E6-l

V63E

If CMC NO GO FDAI SOURCE - ATT FDAI SEL - 1 or 2 ATT SET - GDC

SET

-33-

~Uili ATT PITCH - ACCEL CMDFDAI SCALE - 55MNVR TO CM BURN ATT (NULL ERR NEEDLES)

R 0degPY --00--

30

31

CM RCS BURNRHC III-ContJnuous PJtch DownRHC HZ-Module PJtch to null needlesBURN VGZ TO ZERO

If only 1 RHC Pulse + P=5deg from retro att MaJnta~n rates lt3degsec

BURN COMPLETION ATllV CTR= or DET= _

V8ZE

32 F 16 44 HAHPTFF (1nmffiJn-sec)Check HP-

If gt Pad data contJnue burnuntJ1 lt Pad

PRO

33 F 16 85 VGXYZ (Ups)Read VG resJduals to MSFN

(HYBRID) PRO to 34(SM ONLY BURN)

PROF 37 ODE

EI-1500 V37E 47EF 16 83 twx Y Z (Ups)

SC CONT - SCSFREEMAN ATT (PITCH) - RATE CMDRATE - HIGHPRIM GLY To RAD - BYPASS (verJfy)MN BUS TIE (2) - ON (verJfy)CMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verJfy)Campl MODE - CMRCS TRNFR - CMCM ReS LOGIC - OFFSECS PYRO ~I (2) - SAFE

-34-

PROMonitor VMAB

If lt25 vdc go to EMERGPOWER DOWN

34 F 37 OOEPCM BIT RATE - LOWATT DB - MAXEMS MODE - STBYEMS FUNC - OFF

Go To EARTH ORBIT ENTRY pg _--40-__

-36-

8 SPS THRUSTING PREPCYCLE CRYO FANSSPS GAGING - ACI (ver~fy)

PUG MODE - NORM (venfy)BMAG MODE (3) - RATE 2tv CG - CSMCMC MODE - FREEAUTO RCS SEL (16) - MNA or HNB

(hftoff conbg)SC CONT - CMCAUTO

9 MNVR TO PAD BURN ATTV62E

10 V49E

11 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLESPRO

12 F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) PRO(HAN) SC CONT - ses

MNVR to 14

06 18 AUTO MNVR TO FDAI RPY ANGLES13

14 F 50 18 REO TRIH TO FDAI RPY ANGLES(TRIM) Go to 12(BYPASS) ENTR

15 BORESIGHT STAR CHECK

16 V37E 40EOPT PWR - OFF

17 F 50 18 REQUEST MNVR TO FDAI RPY ANGLES (01deg)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CHCAUTOPRO to 18

(MANDAP) BMAG HODE (3) - RATE 2SC CONT - CMCHOLDMNVR to 19

(HANseS) se eONT - sesMNVR to 19

-35-

54 NORMAL DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL ~V

1 V37E 30E

2 F 06 33 GETI (hrm~nOlsec)

(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

3 F 06 81 ~VXYZ (LV)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

( lfps)

4 F 06 42 HAHP~V (1nmlfps)Record W

(ACCEPT) PRO -----(REJECT) Rese1ect P30 or P27 Load new pa~am

5 F 16 45 MTFIMGA (marksmln-secOldeg)MGA -00002 If ~ lMU not a1~gned

SET DETPRO

6

7

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY v1v - OFFCAB PRESS REL v1v (2) - NORMcb ELS (2) - close (verify)cb SECS ARM (2) - close (ver~fy)

cb SECS LOGIC (2) - close (verlfy)AUTO RCS SEL CM (12) - ~mA or MNB

(l~ftoff conf~g)

ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM AampB - off (ctr)

18

-37-

06 18 AUTO MNVR TO FDAI RPY ANGLES (01 0)

19 l 50 18 REOUEST TRIM MNVR TOALIGN SIC ROLLGDC ALIGN

FDAI RPY ANGLES(010

)

+54-00m(-06-00)

TIG-5mJn

5500m(-0500)

TVC CHECK amp PREPcb STAB CONT SYS (all) - closecb SPS (12) - closeATT DB - MINRATE - LOl~

LIMIT CYCLE - ONMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE 2ROT CONTR PWR DIRECT (2) - OFFSCS TVC (2) - RATE CMD

If SCS SCS TVC (2) - AUTO SC CONT - SCS ~

TVC GMBL DRIVE PampY - AUTOMN BUS TIE (2) - ONTVC SERVO PWR 1 - AC1MNA

2 - AC2MNBTRANS CONTR PWR - ONROT CONTR PWR NORMAL 2 - ACRHC 2 - ARMED

HORIZ CHK - HorJz on 12deg wJndmlmark (LJffiJt +3 0 PNGCS GONO GO)

If NO GO set tw 180 0 180deg0 0

Track horJz wJth 24deg wJndow markAt TIG-2 mJn Ahgn GDC

PRIMARY TVC CHECKGMBL MOT P1-Y1 -STARTON(LMP confJrm)

If SCS verJfy Thumbwheel TrJmTHC - CWVenfy NO MTVC

SEC TVC CHECKGHBL MOT P2-Y2 -STARTON(LMP confJrm)SET GPI TRIHVenfy MTVCTHC NEUTRALGPI returns to 00 (CMC) or trJm (SCS)ROT CONT Pl~ NORM 2 - ACDC

(TRIM) Go to step 17(BYPASS) BMAG MODE(3) - ATTIRATE2 (ver1fy)

ENTR

-38-

20 F SO 25 00204 GMBL TEST OPTION(ACCEPT) SC CONT - GMC (ver~fy)

PROMonitor GPI Response

0020-2000020-200Tr~m

TEST FAIL SC CONT - SCS SCS TVC (2) - AUTO

(REJECT) ENTR

21 06 40 TFIVG~VM (m~n-sec1fps)

PROG ALM - TIG s1~pped

V5N9E 01703

KEY RLSE To 21 ROT CONTR PWR DIRECT (2) - MNABSPS He v1vs (2) - AUTO (ver~fy)

LIMIT CYCLE - OFFFDAI SCALE - SOIScb SPS P2Y2 - open (for cr~t burn)

5800(-02 00)

5925(-0035)

59middot 30(-0030)

06 40

59XX(-OOXX)

AV THRUST A(B) - NORMALTHC - ARMEDRlIC (2) - ARMEDTAPE RCDR - GID RESETHBR

DSKY BLANKS

(AVE G ON)EMS MODE - NORMAL

TFIVG~VM (m~n-seclfps)

CHECK PIPA BIAS lt2fps for 5 sec

ULLAGE AS REQ

IF NO ULLAGE DIR ULLAGE PB - PUSH~

CONTROL ATT WRlIC MONITOR AVM (R3) COUNTING UP

5955(-0005)

F 99 40 ENG ON ENABLE REQUEST(AUTO IGN) PRO AT TFI gt0 sec(BYPASS IGN) ENTR to 24

22 0000 IGN

-39-

If SCS - THRUST ON PB - PUSH

06 40 TFCVG~VM (m~n-seclfpslfps)

~F 97 40 SPS Thrust fall ~

~(RESTART) PRO To IGN (RECYCLE) ENTR To TIG-05 sec

SPS THRUST LITE - ONMONITOR THRUSTING

Pc 95-105 pSlaEMS COUNTING DOWNSPS IN3 v1vs (4) - OPENSPS He v1vs tb (2) - graySPS FUELOXID PRESS - 175-195 pSlaPUGS - BALANCED

PROG ALARM V5N9E 01407 VG INCTHC - CW FLY MTVC

ECOEMER SPS CUTOFF J

AV THRUST (2) - OFF

23 F 16 40 TFC(STATIC)VG~VM (mln-seclfps)~V THRUST AB - OFF

SPS IN3 v1vs (4) - CLOSEDSPS He tb (2) - bp

cb SPS P2Y2 - closed (verlfy)TVC SERVO PHR - AC1MNA (venfy)TVC SERVO PWR 2 - OFF

PRO

24 F 16 85 VG XYZ(CM) CUps)NULL RESIDUALSRECORD ~V CTR amp RESIDUALS I1VCEMS FUNC - OFF VGXEMS MODE - STBY VGYBMAG MODE (3) - RATE 2ATT DB - MAX VGZTRANS CONT PHR - OFF

PRO

25 F 37 V82E

26 F 16 44 HAHPTFF (lnmm~n-sec)

R3-59B59 HP gt494 nmPRO

27 F 37 OOE

-40-

55 EARTH ORBIT ENTRY

1 Venfy CMSMR __

P_shyY_-

SEP ATT(180deg)

(0deg )

2

3

4

EMS INITIALIZATIONEMS FUNC - RNG SETSET RNG TO PAD DATA RNGEMS FUNC - VA SETSlew scroll to pad data VIOEMS FUNC - ENTRY

RSI ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on(up)GDC ALIGN PB - PUSH amp HOLDYAW tw - Pos1tion RSI thru 45deg amp

back to LIFl UPGDC ALIGN PB - RELEASEEMS ROLL - OFFAl1gn GDC to lMU

PWR REDUCT (Norm Deorb Only)HGA PWR - OFFFC PUMPS (3) - OFFVer1fy s1ngle suit compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - Lowcb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2)-openlOb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MAN

-41-

P61 - ENTRY PREP

5 V37E 61E05 09 01427 - ROLL REVERSED05 09 01426 - IMU UNSAT

6 F 06 61 IMPACT LAT LONG liDS UPDN (+-)(01 0

010

+00001)

PRO

PAD VALUESLATLON==G------liDS UP DN _

7 F 06 60 GMAXV400KGAMMA EIRecord

GMAXV400K----GAMMA EI _

PRO

8 F 06 63 RTOGO (1nm) PAD _VIa (fps) PADTFE (mln-sec) ----Compare wlth MSFN for PGNS GONO GONO COMM SET RTOGO amp VIO IN EMS amp

INITIALIZE(ACCEPT) PRO(RECALC) V32E to 8

-42-

P62 - CMSM SEP amp PRE-ENTRY MNVR

9 F 50 25 00041 REQUEST CMSM SEPSC CONT - SCSFREEYAW - 45deg out-of-plane (left for RCS

nght for SPS)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE2PRIM GLY to RAD - BYPASS (verlfy)SECS LOGIC (2) - on (up)MSFN conflrm GO for PYRO ARMSECS PYRO ARM - ARMMN BUS TIE (2) - ON (verlfy)CMSM SEF (2) - ONCSMLM FNl SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 pSlaCM RCS LOGIC - OFFSECS PYRO ARM - SAFEMonltor VMAB

If lt25vdc go to EMERG POWERDOWN Pg E6-1AUTO RCS SEL AlC ROLL (4) - OFFAUTO RCS SEL CM 2(6) - OFFAUTO RCS SEL CM 1(6) - MNA or MNBYAW back to 00

PITCH TO ENTRY ATTROLL 0deg (LIFT UP)PITCH - HORIZ on 317deg MARK (400K)YAW 00

ATT DB - MAXMAN ATT (PITCH) - ACCEL CMDEMS DATA - VerifyEMS FUNC - ENTRY (verlfy)EMS MODE - NORMALMAINTAIN HORIZ TRK

PRO (Act ENTRY DAP)

10 F 06 61 IMPACT LAT LONG HDSDN(010 010 -00001)

PRO

11 FOSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axlS beyond 45deg of Vel vector)

-43-

P63 - ENTRY INIT

12 06 64 GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PWR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRHORIZ CKP~tch error needle goes toward

zero approach~ng 05G t~me

MAN ATT (PITCH) - RATE CMDIf CMC ~s GO

BMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS FLY BETA If CMC NO GO ~

SC CONT - SCS~

FLY EMS RCS Deorh Roll HDS UPTRACK HORIZ w~th 29deg w~ndow mk

P64 - ENTRY POST 05G

13

05G t=elt+0___)

06 68

RTOGO AT 05G AGREES WITH EMS - venfyHORIZ CK05E Lt - on (EMS start)

No EMS start w~th~n 3 secsEMS MODE - BACKUP VHF RNG 05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds L~ft DN

NNVR L~ft DNEMS GONO GO

G-V Plot w~th~n llm~ts

Rng ctr dwn 60 + 7 durlng 10 sec per~od

Mon~tor G-meter forconvergence wlth pad data (Do)

(Vlt27K fps) Go To 17

-44-

P65 - ENTRY - UP CONT (Vgt27K fps)

14 F 16 69 BETA (01deg)DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT~

SC CONT - SCS FLY EMS

PRO

15 06 68 BElA VI HOOT (01deg fpsfps)(VltVL +500 fps amp RDOT Neg) Go To 17

p66 - ENTRY - BALLISTIC (DltDL)

16 06 22 DESIRED GMBL ANGLES RPY (01deg)Mon~tor hor~z +12deg of 317deg mark

P67 - ENTRY - FINAL PHASE (02G)

17 0666 BETACRSRNG ERRDNRNG ERR (Oldeglnmlnm)KEY VERBRecord DNRNG ERR _KEY RLSEL~m~t +100nm from PAD DRE

Mon~tor l~ft vector on RSI amp FDAIF 16 67 RTOGOLATLONG (Vre1=1000fps)

(lnm 010 01deg)SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOlfflMon~tor altimeter

Go To EARTHLANDING pg _I4L5__

-45-

56 EARTHLANDING

90K STEAM PRESS - PEGGED50K CABIN PRESS REL vIv (2) - BOOSTENTRY

SECS PYRO ARM (2) - ARM

40K(90K + 63s)

CM UNSTABLE RCS CMD - OFF ~ 40K APEX COVER JETT PG-PUSH DROGUE DEPLOY PG - PUSH (2 secafter apex cover Jett)

30K ELS LOGIC - ON (up)ELS - AUTO

24K RCS hsable (auto)(90K+92s) RCS CMD - OFF

Apex cover Jett (auto)APEX COVER JETT PB - PUSH

(WAIT 2 SECS)Drogue parachutes deployed (auto)

DROGUE DEPLOY PB - PUSH~

If Drogues FallELS - ~ ~Stablllze CM 5K MAIN DPLY PB - PUSHELS - AUTO

235K Cabln Pressure lncreaslng (Drogues + 50s)If not lncreaSlng by 17K CABIN PRESS REL vlv (RR) - DUMP

-46-

10K Maln parachutes deployedMAIN DEPLOY PB - PUSH (wlthln 1 sec)VHF ANT - RECYVHF AMA - SIMPLEXVHF BCN - ONCABIN PRESS REL v1v (2) - CLOSEDIRECT 02 vlv - OPENCM RCS LOGIC - on (up)CM PRPLNT - DUMP (burn audlb1e)Monltor CM ReS 1amp2 for He press decrease

NO BURN or PRESS DECREASE USE BOTH RHCs DO NOT FIRE PITCH JETS

CM PRPLNT-PURGE (to zero He press)CM RCS He DUMP PB - PUSH RHC (2) - 30 sees NO PITCH k

STRUT LOCKS (2) - UNLOCK

cb FLT amp PL BAT BUS ABampBAT C (3) - closecb FLT amp PLT MNA amp B (2) - opencb ECS RAD HTR OVLD (2) - opencb SPS PampY (4) - open

3K CABIN PRESS REL v1v (RH) - DUMP (after purgecompleted)

FLOOD Lts - POST LDGCM RCS PRPLNT (2) - OFFROT CONTR PWR DIRECT (2) - OFF

800 CAB PRESS RELF vlv - CLOSE (latch off)MN BUS TIE (2) - OFF

AFTER LANDINGcb MAIN REL PYRO (2) - closeMAIN RELEASE - on(up)

Go to POSTLANDING pg _47L-__

I

2

3

-47-

57 POSTLANDING

STABILIZATION VENTILATION COMMUNICATIONS

DIRECT 02 vlv - CLOSE

Stablllzation after landlngELS - AUTO (verlfy)cb MAIN REL PYRO (2) - close (venfy)MAIN RELEASE - on (up) (verlfy)S~CS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb BAT RLY BUS (2) - open

No contact w1th recovery forcesVHF AM AampB - off (ctr) ~

VHF AM Rev ONLY - A cb PL VENT - closecb FLOAT BAG (3) - closecb UPRIGHT SYS COMPRESS (2) - closeIf Stable II

FLOAT BAG(3)-FILL t1ll 2 m1n afterupr1ght then - OFF

VHF AM AlB amp BCN - OFF whlle lnvertedIf Stable I

After 10 M1n Coollng Per1odFLOAT BAG (3) - FILL 7 mln then OFF

Post Stab1lizat1on And Ventllat10nPL BCN LT - BCN LT LOWPL VENT vlv - UNLOCK (Pull)Remove PL VENT Exh CoverPL VENT - HIGH or LOWPL DYE MARKER - ON (swlmmer comm)Release foots traps and_restralntscb MNA BAT BUS A amp BAT C (2) - opencb MNB BAT BUS B amp BAT C (2) - opencb FLT amp PL BAT C - opencb PYRO A SEQ A - opencb PYRO B SEQ B - open

EACH HR - CHECK DC VOLTSgt 275 V If Notmiddot cb FLT amp PL-BAT BUS AampB (2) -open cb FLT amp PL BAT C (1) - open GO TO LOW POWER CHECKLIST

Unstow and lnstall PLV DISTRIB DUCTDeploy grappllng hook and 11ne 1f req

4

-48-

Post Landing Communlcatl0nsVHF ANT-RECY (venfy)VHF BCN - ON (verlfy)

If no contact ~lth recovery forcesperform VHF BEACON Check

MONITOR VHF BEACON transmlSSlonnth VHF AM B Rcvr andor Su)vlval

TransceiverkVHF Beacon not operatlng ~connect Surv~val TranscelVer to antcable behlnd VHF ant access pnland place radio ln BCN mode

LOW POHER CHECKLISTVHF BCN - OFFVHF AM (3) - RCVFLOOD Lts - OFFVHF AM AampB - off (ctr)VHF AM RCV ONLY - A (venfy)COUCH LIGHTS - OFFPOSTLANDING VENT SYS mlnlmlze useSURV RADIO - plug mto VHF BCN ANT cableconn behind VHF ant acess pnl amp turn radloon l-n BCN mode

EGRESS PROCEDURES

CMPCDRLMPCDR

CMPCDRCMP

LMPLl1PCDR

STABLE IDlsconnect Umblll-calsNeck darn onCenter couch - 270 0 positionArmrests stowedConnect raft to SIC l-f desl-red wlth

green lanyardConnect raft ~hl-te lanyards to SUltS amp

lnflate water wlngs when eXltl-ngHATCH PISTON PRESS vlv - PRESS (Outbd)Slde Hatch openedPL VENT - OFFcb Pnl 250 (all) - openEgress with 11feraftPut hardware klt outEgress

or CDIPALL

CMF

CDRCMF

CDR

LMF

CMFCMP LMFCMP

UlP

CDR

-49-

STABLE IIcb CREW STA AUDIO (3) - openD~sconnect umb~1~ca1s

Release foots trapsRelease restra~nt harnessCouch seat pans (3) - 170 0 pos1t10nArm rests stowedSurv1va1 k~ts removed from stowageConnect life raft ma~n1~ne to CDR or SicConnect f~rst wh~te lanyard from

11fe raft to suitConnect th~rd wh~te lanyard from

l~fe raft to SU1tConnect rucksacks together to yellow

lanyard on raft bagPRESSURE EQUALIZATION vlv - OPENRemove and stow fwd hatchEX1t feet f1rst w1th rucksacks when clear

of siC 1nflate water w1ngs and raftExit feet f1rst when clear of SiC

1nflate water w1ngsEX1t feet f1rst when clear of sic

1nflate water w1ngs

-50-

60 TLI ABORTS

TLI Aborts are conta~ned ~n the ESD s~nce the bulk of the funct~ons

concern entry preparat20ns and performance Th~s allows a s2nglesource of procedures for procedure rev2ew val~dat~on checkout andtra~n~ng These procedures ~ncorporate TLI preparat20ns as found ~n

reference 6 w~th the TLI Abort Procedures and these t~e 2nto normallunar return Entry Procedures found ~n sect20n 5 The guidel~nes

for th~s cont2ngency are spec2f2ed 2n reference 7

In2t2al preparat~ons for TLI pos2t20n the necessary system sW2tches2n add~t~on to perform~ng an EMS ~V test and a GDC al~gnment Afterthe DET ~s set for mon2tor2ng TB6 the CMP ~ncreases the 12ght levelof the LEB DSKY to max~mum and returns to the h2s couch Th2s 2Sdone so that the LEB DSKY can be observed ~n the event sunl~ght orreflect20ns wash out the ma2n d2splay panel DSKY dur2ng cr2t2calmaneuvers The crew then straps ~n and prepares for mon2tor~ng TB6as 2nd2cated by the SII SEP L~te The t2mes se~uence of procedures2S keyed on th~s d~splay and ~ncludes the DET START funct~on andSIVB IGNITION Dur2ng the burn the crew mon2tors the FDAIs foratt~tude excurs20ns and abnormal rates report~ng status checks toM~ss2on Control at d2screet t~mes dur2ng the maneuver Upon SIVBSHUTDOWN the eMP records the DSKY d~splayed performance parametersand awa2ts ground conf2rmat~on

The rat~onal for TLI aborts ~s descr~bed 2n reference 7 A summar2shyzat20n 2S extracted to prov2de background and gu2de12nes 2n th2sdocument The abort procedures cover aborts 10 m2nutes after conshyt2ngent SIVE shutdown and aborts 90 m2nutes after normal SIVE shutshydown t2me

The 10 m~nute TLI abort ~s des2gned to be used dur~ng TLI ~n theevent a spacecraft problem develops Wh2Ch can result 2n catastrophe2f ~mmed~ate act~on 2S not taken If the s~tuat20n perm~ts the crewshould always allow the SIVB to complete TLI at wh~ch t~me the groundand crew can perform a malfunct~on analys~s to determ~ne ~f an abort~s adv~sable If a fa~lure occurs that necess2tates the shutdown ofthe SIVB and the ~u~ck return of the crew to earth th~s abort ~s

des~gned to be as ~nsens~t~ve to execut~on errors as poss~ble andst21l be targeted to m2dcorr2dor The burn att~tude w~th the f~ed

hor~zon reference ~s a constant value for any shutdown t~me Theburn durat~on 2S a funct20n of shutdown t2me and 2S ava21able fromcrew charts S~nce the pr~mary purpose of th~s abort ~s to returnto earth as qU2ckly as poss2ble there are no restr2ct20ns as toland~ng locat~on However ~f the t~me to EI is greater than abouttwo hours a midcourse correct20n should be ant~c~pated

The 90 m2nute TLI abort 2S to be used 2f a cr2t2cal subsystem malshyfunct~on ~s determ2ned and the dec2s~on to abort ~s made after the

-51-

TLI cutoff and before TLI cutoff plus approxlmately 80 m1nutesTh1S allows suff1c1ent separatlon and procedural t1me to set upfor the SPS deorb1t burn performed at about TLI + 90 Note thatgenerally the deorb1t burns w1ll be performed a fe11 m1nutes beforeTLI + 90 accord1ng to crew charts shown In reference 8 The no-comm except10n requ1res that 90 m1nutes be the 1nput t1me of 19n1shytlon for P-37 (onboard return-to-earth abort program) so that onshyboard calculatlons can correspond w1th ground calculat10ns to computethe CM land1ng p01nt Th1S TLI abort lS des1gned so that returnfl1ght t1me does not exceed 18 hours and abort ~V does not exceed7000 fps ThlS abort can be performed uSlng chart ~Vs and attltudesand the earths hor1zon serves as a suff1c1ent reference The maneushyver lS targeted to ach1eve the mldcorr1dor entry target Ilne andtlmed to result 1n a deslgnated recovery area

It 1S ObV10US for abort deC1S1ons early 1n the TLI + 90 m1nute t1meshyframe that a GampN SPS burn should be performed In order to keep theTLI abort procedures cons1stent and w1th emphasls on slmpl1c1ty theprocedures here reflect a SCS SPS abort burn to cover the full abortdec1s1on t1meframe

A m1dcourse correct1on for corr1dor control after a TLI abort may bedeS1red 1f the SPS burn d1d not meet expectat1ons The TLIabortprocedures 1n th1S sect10n adapt to the normal lunar return tlmel1neand procedures pr10r to the f1nal MCC

-52-

61 TLI PREPARATION PROCEDURES

GET = 150

CRO AOS(___)

CRO LOS( )(22142)

5100

Don Helmets amp Gloves

XLUNAR - INJECT (verify)EDS PWR - on (venfy)EMS FUNC - OFF (verlfy)EMS MODE - STBYEMS FUNC - IW SETVHF RNGEMS MODE - NORMALSet ~V indo to +15868 fpsEMS FUMC - ~V Test

SPS THRUST Lt - onoff (10 sec)~V lnd stops at -01 to -415

EMS MODE - STBYEMS FUMC - ~V SETVHF RNGSet ~VC

EMS FUNC---~~V=----

GDC ALIGNFDAI Select - liZcb SECS LOGIC (Z) - close (verify)cb SECS ARM (Z) - closeSECS LOGIC (Z) - on (up)MSFN Conflrm GO for PYRO ARM (If pass)SECS PYRO ARM (Z) - on (up)TRANS CONTROL PWR - ONROT CONTR PWR NORMAL (Z) - ACDC(verlfy)ROT CONTR PWR DIRECT (Z) - MNAMNBLV INnGPI - SIISIVB (venfy)LV GUID - IU (venfy)cb DIRECT ULLAGE (Z) - closedSet EVENT TIMER to 5100Begin MONITOR For TB6

CMP to Couch

TB 6 - SII SEP Lt on (TIG-9 mln 38 sec)KEY V83E

SET ORDEALFDAI Z ORB RATE at 180 0 0SII SEP Lt out (38 sec later)Start DET COUNTING UPSC CaNT - SCS (verify)MONITOR LV TANK PRESS

~P lt 36 psid (OXID gt FUEL)~P lt Z6 psid (FUEL gt OXID)

EMERGENCY CSMLV SEP UP TLM CM - BLOCK (verify)UP TLM IU - BLOCK (venfy)

-53-

+45degPY))0middot sec PY

lOK nmltHAlt25K nm

Two phas~ng mnvrs two SPS mnvrs to circular~ze at 150 nmearth orb~t

CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ssion 4K nmltHAltlOK nm CSM amp1M - Two phasing mnvrs two SPS mnvrs to circularize at 150 nm earth orb~t CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ss~on

CSM amp 1M - Two phas~ng mnvrs APS burn todepletion th~rd phasing mnvrSPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn tosem~sync orb~t

25K nmltHAlt40K nm CSM amp 1M - Two phasmg mnvrs APS burn to depletion third phas~ng mnvr SPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn to sem~sync orbit HA)40K nm DPS ava~l - DPS LOll circularize with SPS

DPS not ava~l - Lunar flyby or CSM only to lunar orbit (if reqd gtV lt4000 fps)

V37E 47E (check b~as) Record -=--rshy(Limit 98 fpsmm)

( 1fps)tVXYZN62EVIHDOTHPAD (fpsfpslnm)MONITOR VI ( ) at ECO

SCS TVC SERVO PWR 1 - ACIMNA2 - OFF

TAPE RCDR - CMD RESETHBREMS MODE - NORMAL

SIr SEP Lt - ONTLI Inhib~t S~gnals w~11 not be honored after 5942

SIVB ULLAGE BeginsSII SEP Lt - off (TIG - 18 sec)SIVB FUEL LEADSIVB ULLAGE d~scont~nues

LV ENG I Lt - onSIVB IGNITION ( GETI)LV ENG I Lt - off - -shyMONITOR THRUST amp ATTITUDEMONITOR LV TANK PRESSSIVE ECO (Lt on) (BEGIN TB7)

EMER SIVE CUTOFF AT 6 SEC PAST BURN TIME IF VI ATTAINEDTHC CCW ampNEUTRAL IN 1 SEC or SIISIVB sW - LV STAGEPremature Shutdown HAlt4K nm CSM amp 1M -

5700

58205836

F 16 835800

F 16 62

5838594259525955595900000002SUNRISE(___)

HAW AOS(__=_) KEY VERB (freeze d~splay)

SIVB ATT HOLD 20 sec amp BEGIN VENTINGSIVB NNVR TO ORB RT (HDS DN) (3middot sec)

Record VI -c---HDOT _

HPAD _

KEY RLSEF 16 62

F 16 83

HAW LOS(__=-)

KEYmiddotRLSE~VXYZ (lfps)

Record ~VX---_

~vy

WZ--

AVC---_

TAPE RCDR - off (ctr)EMS MODE - STBYEMS FUNC - OFFSECS PYRO ARM (2) - SAFE

PRO

BURN STATUS REPORT

____--~TIG

BT------VGX____-R

-----P----_Y

REMARKS

_____VI

______--HDOT______--H______---AVC______---FUEL_______OXID

_______UNBAL

F 3708=00 OOEGOS AOS CMP TO LEB

(-=-=-)

0000

0003

0005

0014

0100

-55-

62 TLI 10 MIN ABORTSECS LOGIC (2) - on (up)SECS PYRO ARM (2) - ARM

TRANS CONTR - CGH (4 sec) amp +XDET RESET (verlfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS GMD-ON

TRANS GONTR - neutral then +X for10 sec

SIVBGPI s~ - GPIExcesslve rates 6V THRUST A - NORMAL SPS THRUST - DIRECT When rates damped 6V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

TRANS CONTR +X - OFFV37E OOE

PITGH UP to LOGAL VERT (+X axlSto~ard the earth)

RATE - LOWBMAG MODE (3) - ATTIRATE 2EDS PHR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SEGS ARM (2) - opencb EDS (3) - open

TRANS CONTR -X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (180deg)P (199deg)Y (0deg)

RETRO UPDATEGETI _

JV _VG

Jtb ---GET 400K _

05G _GET DROGUE _

ENTRY P _R _

Y_--

0945

-56-

ALIGN HORIZ ON RET +1 MKGMBL CHECK (T11lle Pentattlng)MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conflnn)cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FUMC - JV SETVHF RNGSET JV from chartE~S FUMC - JVEMS fODE - NOIDlAL

lV THRUST A - NORMALV37E 47E (THRUST fONITOR)

F 16 83 lVXYZ (1 fps)

0950

1000

NOTE For aborts durlng 1st mln of TLIKEY V82E F 16 44 (HaHpTff)Burn untll Hp lt 19NM

TRANS CONTR +X

THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN JV reqdJV THRUST (2) - OFFReport cutoff

cb SPS P2 Y2- closeGfBL MTRS (4) - OFF (LMP Confinn)TRANS CONT PWR - OFFTVC SERVO PWR (2) - OFFMN BUS TIE (2) - OFFcb SPS P1amp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREIf est time to EIltOl5500 omlt fCC andenter the SUPERCIRC CKLIST as early as pos-slb1e Pg ~2~3~ __If est time to EI)Ol5500 anticlpate afCC Enter the ENTRY PREP CKLIST at step 9pg 18

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

-2tl C

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-i- rtREQUIRED PITCH GIMBAL ANG LETO OBTAIN HOR-IZON AT 317

DEGREES IN wiiiiDOW

260

z~I- ~ i5 24000

1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

-I

-1-

NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

I LU HD~-

LUHD

lt0 120UJ0

~

80 HOLD PRESENT TRIMgt LU HD013

~Y~HOIgtlt

TOP OF WINDOWa 40to

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80 TTOM OF WINDOWi= 0

0--ltoa

-40t-z

~~~Uw w u lt0 -80

HOLO PRESENT TRIlJCl

LOHU0 lt0

J gt -120 HOLD 059 TRIMlt0 z

LDHUlt0 FIELD OF VI S10 NLDHU LIFT-DOWNHEADS -UPLUHD LIFT-UP HEADS-DOWN

~~H~-160 q - P63 LIMITI- NOrE-VALIO ONLY FO~t~--

LUNAR RETURN VELOCITY

plusmnl8020 244middot 8 12 16

TIME TO 400K FT ALTITUDE-MIN

4

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320

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-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 34: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

21

22

-31-

PHR REDUCTIONHGA PHR - OFFFC PUMPS (3) - OFFVerify s~ngle su~t compr oper loads

balancedFC 2 MN AampB - OFFS BD PiR AMP - LOWcb ECS RAD CONTHTR (2) - opencb HASTE H20URINE DUMP HTRS(2)- opencb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MANMN BUS TIE (2) - ONTVC SERVO PHR 1 - AC1MNAGMBL MTR (4) - START

p41 - RCS THRUSTINGV37E 41E

23 F 50 18 REQ MNVR TO LCL HORIZ (HDS ON)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CMCAUTOPRO To 24

(gtfANDAP) BMAG MODE (3) - RATE 2SC CONT - CMCHOLD

V62EMNVR To 25

24 06 18 AUTO MNVR TO FDAI RPY

25 F 50 18 REQ TRIM TO LCL HORIZ (01deg)ALIGN SC ROLL

(AUTO TRIM) PRO To 24(BYPASS) ATT DB - MIN

RATE - LOHMAN ATT (3) - RATE CMDBMAG MODE (3) - ATTlRATE 2

ENTR

550Om26 06 85

59middot2527

-32-

VGXYZ (1fps)RECHECK BORESIGHT STARTRANS CONIR PWR - on (up)EMS MODE - STBY (ver~fy)

EMS FliNC - bV SETVHF RNGSET (IV for SM BURN _EMS FliNC - bVS BD ANT - OMNI CSECS LOGIC (2) - ONMSFN conhrm Go for PYRO ARMSECS PYRO ARM (2) - ARMCM RCS LOGIC - ON (ver~fy)

DSKY BLANKS

593028 16 85 VG XYZ (AVE G ON) (lfps)

RHCs amp THC - ARMEDLIMIT CYCLE - OFFTAPE RCDR - CMD RESETHBREMS MODE - NORMAL

000029 F 16 85 REQ NULL VG XYZ (lfps)

BURN EMS bV CTR TO ZERORESET DET amp COUNT UP

If SM ONLY burn go to step 32THC - LOCKEDSC CaNT - SCSFREERATE - HIGHPRIM GLY To RAD - BYPASS (ver~fy)

MN BUS TIE (2) - ON (ver~fy)

CMSM SEP (2) - on (up)CSMLM FNL SEP (2) - on (up) (verify)CampW MODE - CMRCS TRNFR - CMCM RCS LOGIC - OFF

Momtor VM ABIf lt25 vdc go to EMERGPOWER DOWN Pg E6-l

V63E

If CMC NO GO FDAI SOURCE - ATT FDAI SEL - 1 or 2 ATT SET - GDC

SET

-33-

~Uili ATT PITCH - ACCEL CMDFDAI SCALE - 55MNVR TO CM BURN ATT (NULL ERR NEEDLES)

R 0degPY --00--

30

31

CM RCS BURNRHC III-ContJnuous PJtch DownRHC HZ-Module PJtch to null needlesBURN VGZ TO ZERO

If only 1 RHC Pulse + P=5deg from retro att MaJnta~n rates lt3degsec

BURN COMPLETION ATllV CTR= or DET= _

V8ZE

32 F 16 44 HAHPTFF (1nmffiJn-sec)Check HP-

If gt Pad data contJnue burnuntJ1 lt Pad

PRO

33 F 16 85 VGXYZ (Ups)Read VG resJduals to MSFN

(HYBRID) PRO to 34(SM ONLY BURN)

PROF 37 ODE

EI-1500 V37E 47EF 16 83 twx Y Z (Ups)

SC CONT - SCSFREEMAN ATT (PITCH) - RATE CMDRATE - HIGHPRIM GLY To RAD - BYPASS (verJfy)MN BUS TIE (2) - ON (verJfy)CMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verJfy)Campl MODE - CMRCS TRNFR - CMCM ReS LOGIC - OFFSECS PYRO ~I (2) - SAFE

-34-

PROMonitor VMAB

If lt25 vdc go to EMERGPOWER DOWN

34 F 37 OOEPCM BIT RATE - LOWATT DB - MAXEMS MODE - STBYEMS FUNC - OFF

Go To EARTH ORBIT ENTRY pg _--40-__

-36-

8 SPS THRUSTING PREPCYCLE CRYO FANSSPS GAGING - ACI (ver~fy)

PUG MODE - NORM (venfy)BMAG MODE (3) - RATE 2tv CG - CSMCMC MODE - FREEAUTO RCS SEL (16) - MNA or HNB

(hftoff conbg)SC CONT - CMCAUTO

9 MNVR TO PAD BURN ATTV62E

10 V49E

11 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLESPRO

12 F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) PRO(HAN) SC CONT - ses

MNVR to 14

06 18 AUTO MNVR TO FDAI RPY ANGLES13

14 F 50 18 REO TRIH TO FDAI RPY ANGLES(TRIM) Go to 12(BYPASS) ENTR

15 BORESIGHT STAR CHECK

16 V37E 40EOPT PWR - OFF

17 F 50 18 REQUEST MNVR TO FDAI RPY ANGLES (01deg)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CHCAUTOPRO to 18

(MANDAP) BMAG HODE (3) - RATE 2SC CONT - CMCHOLDMNVR to 19

(HANseS) se eONT - sesMNVR to 19

-35-

54 NORMAL DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL ~V

1 V37E 30E

2 F 06 33 GETI (hrm~nOlsec)

(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

3 F 06 81 ~VXYZ (LV)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

( lfps)

4 F 06 42 HAHP~V (1nmlfps)Record W

(ACCEPT) PRO -----(REJECT) Rese1ect P30 or P27 Load new pa~am

5 F 16 45 MTFIMGA (marksmln-secOldeg)MGA -00002 If ~ lMU not a1~gned

SET DETPRO

6

7

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY v1v - OFFCAB PRESS REL v1v (2) - NORMcb ELS (2) - close (verify)cb SECS ARM (2) - close (ver~fy)

cb SECS LOGIC (2) - close (verlfy)AUTO RCS SEL CM (12) - ~mA or MNB

(l~ftoff conf~g)

ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM AampB - off (ctr)

18

-37-

06 18 AUTO MNVR TO FDAI RPY ANGLES (01 0)

19 l 50 18 REOUEST TRIM MNVR TOALIGN SIC ROLLGDC ALIGN

FDAI RPY ANGLES(010

)

+54-00m(-06-00)

TIG-5mJn

5500m(-0500)

TVC CHECK amp PREPcb STAB CONT SYS (all) - closecb SPS (12) - closeATT DB - MINRATE - LOl~

LIMIT CYCLE - ONMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE 2ROT CONTR PWR DIRECT (2) - OFFSCS TVC (2) - RATE CMD

If SCS SCS TVC (2) - AUTO SC CONT - SCS ~

TVC GMBL DRIVE PampY - AUTOMN BUS TIE (2) - ONTVC SERVO PWR 1 - AC1MNA

2 - AC2MNBTRANS CONTR PWR - ONROT CONTR PWR NORMAL 2 - ACRHC 2 - ARMED

HORIZ CHK - HorJz on 12deg wJndmlmark (LJffiJt +3 0 PNGCS GONO GO)

If NO GO set tw 180 0 180deg0 0

Track horJz wJth 24deg wJndow markAt TIG-2 mJn Ahgn GDC

PRIMARY TVC CHECKGMBL MOT P1-Y1 -STARTON(LMP confJrm)

If SCS verJfy Thumbwheel TrJmTHC - CWVenfy NO MTVC

SEC TVC CHECKGHBL MOT P2-Y2 -STARTON(LMP confJrm)SET GPI TRIHVenfy MTVCTHC NEUTRALGPI returns to 00 (CMC) or trJm (SCS)ROT CONT Pl~ NORM 2 - ACDC

(TRIM) Go to step 17(BYPASS) BMAG MODE(3) - ATTIRATE2 (ver1fy)

ENTR

-38-

20 F SO 25 00204 GMBL TEST OPTION(ACCEPT) SC CONT - GMC (ver~fy)

PROMonitor GPI Response

0020-2000020-200Tr~m

TEST FAIL SC CONT - SCS SCS TVC (2) - AUTO

(REJECT) ENTR

21 06 40 TFIVG~VM (m~n-sec1fps)

PROG ALM - TIG s1~pped

V5N9E 01703

KEY RLSE To 21 ROT CONTR PWR DIRECT (2) - MNABSPS He v1vs (2) - AUTO (ver~fy)

LIMIT CYCLE - OFFFDAI SCALE - SOIScb SPS P2Y2 - open (for cr~t burn)

5800(-02 00)

5925(-0035)

59middot 30(-0030)

06 40

59XX(-OOXX)

AV THRUST A(B) - NORMALTHC - ARMEDRlIC (2) - ARMEDTAPE RCDR - GID RESETHBR

DSKY BLANKS

(AVE G ON)EMS MODE - NORMAL

TFIVG~VM (m~n-seclfps)

CHECK PIPA BIAS lt2fps for 5 sec

ULLAGE AS REQ

IF NO ULLAGE DIR ULLAGE PB - PUSH~

CONTROL ATT WRlIC MONITOR AVM (R3) COUNTING UP

5955(-0005)

F 99 40 ENG ON ENABLE REQUEST(AUTO IGN) PRO AT TFI gt0 sec(BYPASS IGN) ENTR to 24

22 0000 IGN

-39-

If SCS - THRUST ON PB - PUSH

06 40 TFCVG~VM (m~n-seclfpslfps)

~F 97 40 SPS Thrust fall ~

~(RESTART) PRO To IGN (RECYCLE) ENTR To TIG-05 sec

SPS THRUST LITE - ONMONITOR THRUSTING

Pc 95-105 pSlaEMS COUNTING DOWNSPS IN3 v1vs (4) - OPENSPS He v1vs tb (2) - graySPS FUELOXID PRESS - 175-195 pSlaPUGS - BALANCED

PROG ALARM V5N9E 01407 VG INCTHC - CW FLY MTVC

ECOEMER SPS CUTOFF J

AV THRUST (2) - OFF

23 F 16 40 TFC(STATIC)VG~VM (mln-seclfps)~V THRUST AB - OFF

SPS IN3 v1vs (4) - CLOSEDSPS He tb (2) - bp

cb SPS P2Y2 - closed (verlfy)TVC SERVO PHR - AC1MNA (venfy)TVC SERVO PWR 2 - OFF

PRO

24 F 16 85 VG XYZ(CM) CUps)NULL RESIDUALSRECORD ~V CTR amp RESIDUALS I1VCEMS FUNC - OFF VGXEMS MODE - STBY VGYBMAG MODE (3) - RATE 2ATT DB - MAX VGZTRANS CONT PHR - OFF

PRO

25 F 37 V82E

26 F 16 44 HAHPTFF (lnmm~n-sec)

R3-59B59 HP gt494 nmPRO

27 F 37 OOE

-40-

55 EARTH ORBIT ENTRY

1 Venfy CMSMR __

P_shyY_-

SEP ATT(180deg)

(0deg )

2

3

4

EMS INITIALIZATIONEMS FUNC - RNG SETSET RNG TO PAD DATA RNGEMS FUNC - VA SETSlew scroll to pad data VIOEMS FUNC - ENTRY

RSI ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on(up)GDC ALIGN PB - PUSH amp HOLDYAW tw - Pos1tion RSI thru 45deg amp

back to LIFl UPGDC ALIGN PB - RELEASEEMS ROLL - OFFAl1gn GDC to lMU

PWR REDUCT (Norm Deorb Only)HGA PWR - OFFFC PUMPS (3) - OFFVer1fy s1ngle suit compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - Lowcb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2)-openlOb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MAN

-41-

P61 - ENTRY PREP

5 V37E 61E05 09 01427 - ROLL REVERSED05 09 01426 - IMU UNSAT

6 F 06 61 IMPACT LAT LONG liDS UPDN (+-)(01 0

010

+00001)

PRO

PAD VALUESLATLON==G------liDS UP DN _

7 F 06 60 GMAXV400KGAMMA EIRecord

GMAXV400K----GAMMA EI _

PRO

8 F 06 63 RTOGO (1nm) PAD _VIa (fps) PADTFE (mln-sec) ----Compare wlth MSFN for PGNS GONO GONO COMM SET RTOGO amp VIO IN EMS amp

INITIALIZE(ACCEPT) PRO(RECALC) V32E to 8

-42-

P62 - CMSM SEP amp PRE-ENTRY MNVR

9 F 50 25 00041 REQUEST CMSM SEPSC CONT - SCSFREEYAW - 45deg out-of-plane (left for RCS

nght for SPS)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE2PRIM GLY to RAD - BYPASS (verlfy)SECS LOGIC (2) - on (up)MSFN conflrm GO for PYRO ARMSECS PYRO ARM - ARMMN BUS TIE (2) - ON (verlfy)CMSM SEF (2) - ONCSMLM FNl SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 pSlaCM RCS LOGIC - OFFSECS PYRO ARM - SAFEMonltor VMAB

If lt25vdc go to EMERG POWERDOWN Pg E6-1AUTO RCS SEL AlC ROLL (4) - OFFAUTO RCS SEL CM 2(6) - OFFAUTO RCS SEL CM 1(6) - MNA or MNBYAW back to 00

PITCH TO ENTRY ATTROLL 0deg (LIFT UP)PITCH - HORIZ on 317deg MARK (400K)YAW 00

ATT DB - MAXMAN ATT (PITCH) - ACCEL CMDEMS DATA - VerifyEMS FUNC - ENTRY (verlfy)EMS MODE - NORMALMAINTAIN HORIZ TRK

PRO (Act ENTRY DAP)

10 F 06 61 IMPACT LAT LONG HDSDN(010 010 -00001)

PRO

11 FOSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axlS beyond 45deg of Vel vector)

-43-

P63 - ENTRY INIT

12 06 64 GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PWR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRHORIZ CKP~tch error needle goes toward

zero approach~ng 05G t~me

MAN ATT (PITCH) - RATE CMDIf CMC ~s GO

BMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS FLY BETA If CMC NO GO ~

SC CONT - SCS~

FLY EMS RCS Deorh Roll HDS UPTRACK HORIZ w~th 29deg w~ndow mk

P64 - ENTRY POST 05G

13

05G t=elt+0___)

06 68

RTOGO AT 05G AGREES WITH EMS - venfyHORIZ CK05E Lt - on (EMS start)

No EMS start w~th~n 3 secsEMS MODE - BACKUP VHF RNG 05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds L~ft DN

NNVR L~ft DNEMS GONO GO

G-V Plot w~th~n llm~ts

Rng ctr dwn 60 + 7 durlng 10 sec per~od

Mon~tor G-meter forconvergence wlth pad data (Do)

(Vlt27K fps) Go To 17

-44-

P65 - ENTRY - UP CONT (Vgt27K fps)

14 F 16 69 BETA (01deg)DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT~

SC CONT - SCS FLY EMS

PRO

15 06 68 BElA VI HOOT (01deg fpsfps)(VltVL +500 fps amp RDOT Neg) Go To 17

p66 - ENTRY - BALLISTIC (DltDL)

16 06 22 DESIRED GMBL ANGLES RPY (01deg)Mon~tor hor~z +12deg of 317deg mark

P67 - ENTRY - FINAL PHASE (02G)

17 0666 BETACRSRNG ERRDNRNG ERR (Oldeglnmlnm)KEY VERBRecord DNRNG ERR _KEY RLSEL~m~t +100nm from PAD DRE

Mon~tor l~ft vector on RSI amp FDAIF 16 67 RTOGOLATLONG (Vre1=1000fps)

(lnm 010 01deg)SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOlfflMon~tor altimeter

Go To EARTHLANDING pg _I4L5__

-45-

56 EARTHLANDING

90K STEAM PRESS - PEGGED50K CABIN PRESS REL vIv (2) - BOOSTENTRY

SECS PYRO ARM (2) - ARM

40K(90K + 63s)

CM UNSTABLE RCS CMD - OFF ~ 40K APEX COVER JETT PG-PUSH DROGUE DEPLOY PG - PUSH (2 secafter apex cover Jett)

30K ELS LOGIC - ON (up)ELS - AUTO

24K RCS hsable (auto)(90K+92s) RCS CMD - OFF

Apex cover Jett (auto)APEX COVER JETT PB - PUSH

(WAIT 2 SECS)Drogue parachutes deployed (auto)

DROGUE DEPLOY PB - PUSH~

If Drogues FallELS - ~ ~Stablllze CM 5K MAIN DPLY PB - PUSHELS - AUTO

235K Cabln Pressure lncreaslng (Drogues + 50s)If not lncreaSlng by 17K CABIN PRESS REL vlv (RR) - DUMP

-46-

10K Maln parachutes deployedMAIN DEPLOY PB - PUSH (wlthln 1 sec)VHF ANT - RECYVHF AMA - SIMPLEXVHF BCN - ONCABIN PRESS REL v1v (2) - CLOSEDIRECT 02 vlv - OPENCM RCS LOGIC - on (up)CM PRPLNT - DUMP (burn audlb1e)Monltor CM ReS 1amp2 for He press decrease

NO BURN or PRESS DECREASE USE BOTH RHCs DO NOT FIRE PITCH JETS

CM PRPLNT-PURGE (to zero He press)CM RCS He DUMP PB - PUSH RHC (2) - 30 sees NO PITCH k

STRUT LOCKS (2) - UNLOCK

cb FLT amp PL BAT BUS ABampBAT C (3) - closecb FLT amp PLT MNA amp B (2) - opencb ECS RAD HTR OVLD (2) - opencb SPS PampY (4) - open

3K CABIN PRESS REL v1v (RH) - DUMP (after purgecompleted)

FLOOD Lts - POST LDGCM RCS PRPLNT (2) - OFFROT CONTR PWR DIRECT (2) - OFF

800 CAB PRESS RELF vlv - CLOSE (latch off)MN BUS TIE (2) - OFF

AFTER LANDINGcb MAIN REL PYRO (2) - closeMAIN RELEASE - on(up)

Go to POSTLANDING pg _47L-__

I

2

3

-47-

57 POSTLANDING

STABILIZATION VENTILATION COMMUNICATIONS

DIRECT 02 vlv - CLOSE

Stablllzation after landlngELS - AUTO (verlfy)cb MAIN REL PYRO (2) - close (venfy)MAIN RELEASE - on (up) (verlfy)S~CS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb BAT RLY BUS (2) - open

No contact w1th recovery forcesVHF AM AampB - off (ctr) ~

VHF AM Rev ONLY - A cb PL VENT - closecb FLOAT BAG (3) - closecb UPRIGHT SYS COMPRESS (2) - closeIf Stable II

FLOAT BAG(3)-FILL t1ll 2 m1n afterupr1ght then - OFF

VHF AM AlB amp BCN - OFF whlle lnvertedIf Stable I

After 10 M1n Coollng Per1odFLOAT BAG (3) - FILL 7 mln then OFF

Post Stab1lizat1on And Ventllat10nPL BCN LT - BCN LT LOWPL VENT vlv - UNLOCK (Pull)Remove PL VENT Exh CoverPL VENT - HIGH or LOWPL DYE MARKER - ON (swlmmer comm)Release foots traps and_restralntscb MNA BAT BUS A amp BAT C (2) - opencb MNB BAT BUS B amp BAT C (2) - opencb FLT amp PL BAT C - opencb PYRO A SEQ A - opencb PYRO B SEQ B - open

EACH HR - CHECK DC VOLTSgt 275 V If Notmiddot cb FLT amp PL-BAT BUS AampB (2) -open cb FLT amp PL BAT C (1) - open GO TO LOW POWER CHECKLIST

Unstow and lnstall PLV DISTRIB DUCTDeploy grappllng hook and 11ne 1f req

4

-48-

Post Landing Communlcatl0nsVHF ANT-RECY (venfy)VHF BCN - ON (verlfy)

If no contact ~lth recovery forcesperform VHF BEACON Check

MONITOR VHF BEACON transmlSSlonnth VHF AM B Rcvr andor Su)vlval

TransceiverkVHF Beacon not operatlng ~connect Surv~val TranscelVer to antcable behlnd VHF ant access pnland place radio ln BCN mode

LOW POHER CHECKLISTVHF BCN - OFFVHF AM (3) - RCVFLOOD Lts - OFFVHF AM AampB - off (ctr)VHF AM RCV ONLY - A (venfy)COUCH LIGHTS - OFFPOSTLANDING VENT SYS mlnlmlze useSURV RADIO - plug mto VHF BCN ANT cableconn behind VHF ant acess pnl amp turn radloon l-n BCN mode

EGRESS PROCEDURES

CMPCDRLMPCDR

CMPCDRCMP

LMPLl1PCDR

STABLE IDlsconnect Umblll-calsNeck darn onCenter couch - 270 0 positionArmrests stowedConnect raft to SIC l-f desl-red wlth

green lanyardConnect raft ~hl-te lanyards to SUltS amp

lnflate water wlngs when eXltl-ngHATCH PISTON PRESS vlv - PRESS (Outbd)Slde Hatch openedPL VENT - OFFcb Pnl 250 (all) - openEgress with 11feraftPut hardware klt outEgress

or CDIPALL

CMF

CDRCMF

CDR

LMF

CMFCMP LMFCMP

UlP

CDR

-49-

STABLE IIcb CREW STA AUDIO (3) - openD~sconnect umb~1~ca1s

Release foots trapsRelease restra~nt harnessCouch seat pans (3) - 170 0 pos1t10nArm rests stowedSurv1va1 k~ts removed from stowageConnect life raft ma~n1~ne to CDR or SicConnect f~rst wh~te lanyard from

11fe raft to suitConnect th~rd wh~te lanyard from

l~fe raft to SU1tConnect rucksacks together to yellow

lanyard on raft bagPRESSURE EQUALIZATION vlv - OPENRemove and stow fwd hatchEX1t feet f1rst w1th rucksacks when clear

of siC 1nflate water w1ngs and raftExit feet f1rst when clear of SiC

1nflate water w1ngsEX1t feet f1rst when clear of sic

1nflate water w1ngs

-50-

60 TLI ABORTS

TLI Aborts are conta~ned ~n the ESD s~nce the bulk of the funct~ons

concern entry preparat20ns and performance Th~s allows a s2nglesource of procedures for procedure rev2ew val~dat~on checkout andtra~n~ng These procedures ~ncorporate TLI preparat20ns as found ~n

reference 6 w~th the TLI Abort Procedures and these t~e 2nto normallunar return Entry Procedures found ~n sect20n 5 The guidel~nes

for th~s cont2ngency are spec2f2ed 2n reference 7

In2t2al preparat~ons for TLI pos2t20n the necessary system sW2tches2n add~t~on to perform~ng an EMS ~V test and a GDC al~gnment Afterthe DET ~s set for mon2tor2ng TB6 the CMP ~ncreases the 12ght levelof the LEB DSKY to max~mum and returns to the h2s couch Th2s 2Sdone so that the LEB DSKY can be observed ~n the event sunl~ght orreflect20ns wash out the ma2n d2splay panel DSKY dur2ng cr2t2calmaneuvers The crew then straps ~n and prepares for mon2tor~ng TB6as 2nd2cated by the SII SEP L~te The t2mes se~uence of procedures2S keyed on th~s d~splay and ~ncludes the DET START funct~on andSIVB IGNITION Dur2ng the burn the crew mon2tors the FDAIs foratt~tude excurs20ns and abnormal rates report~ng status checks toM~ss2on Control at d2screet t~mes dur2ng the maneuver Upon SIVBSHUTDOWN the eMP records the DSKY d~splayed performance parametersand awa2ts ground conf2rmat~on

The rat~onal for TLI aborts ~s descr~bed 2n reference 7 A summar2shyzat20n 2S extracted to prov2de background and gu2de12nes 2n th2sdocument The abort procedures cover aborts 10 m2nutes after conshyt2ngent SIVE shutdown and aborts 90 m2nutes after normal SIVE shutshydown t2me

The 10 m~nute TLI abort ~s des2gned to be used dur~ng TLI ~n theevent a spacecraft problem develops Wh2Ch can result 2n catastrophe2f ~mmed~ate act~on 2S not taken If the s~tuat20n perm~ts the crewshould always allow the SIVB to complete TLI at wh~ch t~me the groundand crew can perform a malfunct~on analys~s to determ~ne ~f an abort~s adv~sable If a fa~lure occurs that necess2tates the shutdown ofthe SIVB and the ~u~ck return of the crew to earth th~s abort ~s

des~gned to be as ~nsens~t~ve to execut~on errors as poss~ble andst21l be targeted to m2dcorr2dor The burn att~tude w~th the f~ed

hor~zon reference ~s a constant value for any shutdown t~me Theburn durat~on 2S a funct20n of shutdown t2me and 2S ava21able fromcrew charts S~nce the pr~mary purpose of th~s abort ~s to returnto earth as qU2ckly as poss2ble there are no restr2ct20ns as toland~ng locat~on However ~f the t~me to EI is greater than abouttwo hours a midcourse correct20n should be ant~c~pated

The 90 m2nute TLI abort 2S to be used 2f a cr2t2cal subsystem malshyfunct~on ~s determ2ned and the dec2s~on to abort ~s made after the

-51-

TLI cutoff and before TLI cutoff plus approxlmately 80 m1nutesTh1S allows suff1c1ent separatlon and procedural t1me to set upfor the SPS deorb1t burn performed at about TLI + 90 Note thatgenerally the deorb1t burns w1ll be performed a fe11 m1nutes beforeTLI + 90 accord1ng to crew charts shown In reference 8 The no-comm except10n requ1res that 90 m1nutes be the 1nput t1me of 19n1shytlon for P-37 (onboard return-to-earth abort program) so that onshyboard calculatlons can correspond w1th ground calculat10ns to computethe CM land1ng p01nt Th1S TLI abort lS des1gned so that returnfl1ght t1me does not exceed 18 hours and abort ~V does not exceed7000 fps ThlS abort can be performed uSlng chart ~Vs and attltudesand the earths hor1zon serves as a suff1c1ent reference The maneushyver lS targeted to ach1eve the mldcorr1dor entry target Ilne andtlmed to result 1n a deslgnated recovery area

It 1S ObV10US for abort deC1S1ons early 1n the TLI + 90 m1nute t1meshyframe that a GampN SPS burn should be performed In order to keep theTLI abort procedures cons1stent and w1th emphasls on slmpl1c1ty theprocedures here reflect a SCS SPS abort burn to cover the full abortdec1s1on t1meframe

A m1dcourse correct1on for corr1dor control after a TLI abort may bedeS1red 1f the SPS burn d1d not meet expectat1ons The TLIabortprocedures 1n th1S sect10n adapt to the normal lunar return tlmel1neand procedures pr10r to the f1nal MCC

-52-

61 TLI PREPARATION PROCEDURES

GET = 150

CRO AOS(___)

CRO LOS( )(22142)

5100

Don Helmets amp Gloves

XLUNAR - INJECT (verify)EDS PWR - on (venfy)EMS FUNC - OFF (verlfy)EMS MODE - STBYEMS FUNC - IW SETVHF RNGEMS MODE - NORMALSet ~V indo to +15868 fpsEMS FUMC - ~V Test

SPS THRUST Lt - onoff (10 sec)~V lnd stops at -01 to -415

EMS MODE - STBYEMS FUMC - ~V SETVHF RNGSet ~VC

EMS FUNC---~~V=----

GDC ALIGNFDAI Select - liZcb SECS LOGIC (Z) - close (verify)cb SECS ARM (Z) - closeSECS LOGIC (Z) - on (up)MSFN Conflrm GO for PYRO ARM (If pass)SECS PYRO ARM (Z) - on (up)TRANS CONTROL PWR - ONROT CONTR PWR NORMAL (Z) - ACDC(verlfy)ROT CONTR PWR DIRECT (Z) - MNAMNBLV INnGPI - SIISIVB (venfy)LV GUID - IU (venfy)cb DIRECT ULLAGE (Z) - closedSet EVENT TIMER to 5100Begin MONITOR For TB6

CMP to Couch

TB 6 - SII SEP Lt on (TIG-9 mln 38 sec)KEY V83E

SET ORDEALFDAI Z ORB RATE at 180 0 0SII SEP Lt out (38 sec later)Start DET COUNTING UPSC CaNT - SCS (verify)MONITOR LV TANK PRESS

~P lt 36 psid (OXID gt FUEL)~P lt Z6 psid (FUEL gt OXID)

EMERGENCY CSMLV SEP UP TLM CM - BLOCK (verify)UP TLM IU - BLOCK (venfy)

-53-

+45degPY))0middot sec PY

lOK nmltHAlt25K nm

Two phas~ng mnvrs two SPS mnvrs to circular~ze at 150 nmearth orb~t

CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ssion 4K nmltHAltlOK nm CSM amp1M - Two phasing mnvrs two SPS mnvrs to circularize at 150 nm earth orb~t CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ss~on

CSM amp 1M - Two phas~ng mnvrs APS burn todepletion th~rd phasing mnvrSPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn tosem~sync orb~t

25K nmltHAlt40K nm CSM amp 1M - Two phasmg mnvrs APS burn to depletion third phas~ng mnvr SPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn to sem~sync orbit HA)40K nm DPS ava~l - DPS LOll circularize with SPS

DPS not ava~l - Lunar flyby or CSM only to lunar orbit (if reqd gtV lt4000 fps)

V37E 47E (check b~as) Record -=--rshy(Limit 98 fpsmm)

( 1fps)tVXYZN62EVIHDOTHPAD (fpsfpslnm)MONITOR VI ( ) at ECO

SCS TVC SERVO PWR 1 - ACIMNA2 - OFF

TAPE RCDR - CMD RESETHBREMS MODE - NORMAL

SIr SEP Lt - ONTLI Inhib~t S~gnals w~11 not be honored after 5942

SIVB ULLAGE BeginsSII SEP Lt - off (TIG - 18 sec)SIVB FUEL LEADSIVB ULLAGE d~scont~nues

LV ENG I Lt - onSIVB IGNITION ( GETI)LV ENG I Lt - off - -shyMONITOR THRUST amp ATTITUDEMONITOR LV TANK PRESSSIVE ECO (Lt on) (BEGIN TB7)

EMER SIVE CUTOFF AT 6 SEC PAST BURN TIME IF VI ATTAINEDTHC CCW ampNEUTRAL IN 1 SEC or SIISIVB sW - LV STAGEPremature Shutdown HAlt4K nm CSM amp 1M -

5700

58205836

F 16 835800

F 16 62

5838594259525955595900000002SUNRISE(___)

HAW AOS(__=_) KEY VERB (freeze d~splay)

SIVB ATT HOLD 20 sec amp BEGIN VENTINGSIVB NNVR TO ORB RT (HDS DN) (3middot sec)

Record VI -c---HDOT _

HPAD _

KEY RLSEF 16 62

F 16 83

HAW LOS(__=-)

KEYmiddotRLSE~VXYZ (lfps)

Record ~VX---_

~vy

WZ--

AVC---_

TAPE RCDR - off (ctr)EMS MODE - STBYEMS FUNC - OFFSECS PYRO ARM (2) - SAFE

PRO

BURN STATUS REPORT

____--~TIG

BT------VGX____-R

-----P----_Y

REMARKS

_____VI

______--HDOT______--H______---AVC______---FUEL_______OXID

_______UNBAL

F 3708=00 OOEGOS AOS CMP TO LEB

(-=-=-)

0000

0003

0005

0014

0100

-55-

62 TLI 10 MIN ABORTSECS LOGIC (2) - on (up)SECS PYRO ARM (2) - ARM

TRANS CONTR - CGH (4 sec) amp +XDET RESET (verlfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS GMD-ON

TRANS GONTR - neutral then +X for10 sec

SIVBGPI s~ - GPIExcesslve rates 6V THRUST A - NORMAL SPS THRUST - DIRECT When rates damped 6V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

TRANS CONTR +X - OFFV37E OOE

PITGH UP to LOGAL VERT (+X axlSto~ard the earth)

RATE - LOWBMAG MODE (3) - ATTIRATE 2EDS PHR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SEGS ARM (2) - opencb EDS (3) - open

TRANS CONTR -X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (180deg)P (199deg)Y (0deg)

RETRO UPDATEGETI _

JV _VG

Jtb ---GET 400K _

05G _GET DROGUE _

ENTRY P _R _

Y_--

0945

-56-

ALIGN HORIZ ON RET +1 MKGMBL CHECK (T11lle Pentattlng)MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conflnn)cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FUMC - JV SETVHF RNGSET JV from chartE~S FUMC - JVEMS fODE - NOIDlAL

lV THRUST A - NORMALV37E 47E (THRUST fONITOR)

F 16 83 lVXYZ (1 fps)

0950

1000

NOTE For aborts durlng 1st mln of TLIKEY V82E F 16 44 (HaHpTff)Burn untll Hp lt 19NM

TRANS CONTR +X

THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN JV reqdJV THRUST (2) - OFFReport cutoff

cb SPS P2 Y2- closeGfBL MTRS (4) - OFF (LMP Confinn)TRANS CONT PWR - OFFTVC SERVO PWR (2) - OFFMN BUS TIE (2) - OFFcb SPS P1amp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREIf est time to EIltOl5500 omlt fCC andenter the SUPERCIRC CKLIST as early as pos-slb1e Pg ~2~3~ __If est time to EI)Ol5500 anticlpate afCC Enter the ENTRY PREP CKLIST at step 9pg 18

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

-2tl C

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UN

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26

28

30

32

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RE

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03

-i- rtREQUIRED PITCH GIMBAL ANG LETO OBTAIN HOR-IZON AT 317

DEGREES IN wiiiiDOW

260

z~I- ~ i5 24000

1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

-I

-1-

NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

I LU HD~-

LUHD

lt0 120UJ0

~

80 HOLD PRESENT TRIMgt LU HD013

~Y~HOIgtlt

TOP OF WINDOWa 40to

31 7 SCRIBEaaI

80 TTOM OF WINDOWi= 0

0--ltoa

-40t-z

~~~Uw w u lt0 -80

HOLO PRESENT TRIlJCl

LOHU0 lt0

J gt -120 HOLD 059 TRIMlt0 z

LDHUlt0 FIELD OF VI S10 NLDHU LIFT-DOWNHEADS -UPLUHD LIFT-UP HEADS-DOWN

~~H~-160 q - P63 LIMITI- NOrE-VALIO ONLY FO~t~--

LUNAR RETURN VELOCITY

plusmnl8020 244middot 8 12 16

TIME TO 400K FT ALTITUDE-MIN

4

P37

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352

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120

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320

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-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 35: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

550Om26 06 85

59middot2527

-32-

VGXYZ (1fps)RECHECK BORESIGHT STARTRANS CONIR PWR - on (up)EMS MODE - STBY (ver~fy)

EMS FliNC - bV SETVHF RNGSET (IV for SM BURN _EMS FliNC - bVS BD ANT - OMNI CSECS LOGIC (2) - ONMSFN conhrm Go for PYRO ARMSECS PYRO ARM (2) - ARMCM RCS LOGIC - ON (ver~fy)

DSKY BLANKS

593028 16 85 VG XYZ (AVE G ON) (lfps)

RHCs amp THC - ARMEDLIMIT CYCLE - OFFTAPE RCDR - CMD RESETHBREMS MODE - NORMAL

000029 F 16 85 REQ NULL VG XYZ (lfps)

BURN EMS bV CTR TO ZERORESET DET amp COUNT UP

If SM ONLY burn go to step 32THC - LOCKEDSC CaNT - SCSFREERATE - HIGHPRIM GLY To RAD - BYPASS (ver~fy)

MN BUS TIE (2) - ON (ver~fy)

CMSM SEP (2) - on (up)CSMLM FNL SEP (2) - on (up) (verify)CampW MODE - CMRCS TRNFR - CMCM RCS LOGIC - OFF

Momtor VM ABIf lt25 vdc go to EMERGPOWER DOWN Pg E6-l

V63E

If CMC NO GO FDAI SOURCE - ATT FDAI SEL - 1 or 2 ATT SET - GDC

SET

-33-

~Uili ATT PITCH - ACCEL CMDFDAI SCALE - 55MNVR TO CM BURN ATT (NULL ERR NEEDLES)

R 0degPY --00--

30

31

CM RCS BURNRHC III-ContJnuous PJtch DownRHC HZ-Module PJtch to null needlesBURN VGZ TO ZERO

If only 1 RHC Pulse + P=5deg from retro att MaJnta~n rates lt3degsec

BURN COMPLETION ATllV CTR= or DET= _

V8ZE

32 F 16 44 HAHPTFF (1nmffiJn-sec)Check HP-

If gt Pad data contJnue burnuntJ1 lt Pad

PRO

33 F 16 85 VGXYZ (Ups)Read VG resJduals to MSFN

(HYBRID) PRO to 34(SM ONLY BURN)

PROF 37 ODE

EI-1500 V37E 47EF 16 83 twx Y Z (Ups)

SC CONT - SCSFREEMAN ATT (PITCH) - RATE CMDRATE - HIGHPRIM GLY To RAD - BYPASS (verJfy)MN BUS TIE (2) - ON (verJfy)CMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verJfy)Campl MODE - CMRCS TRNFR - CMCM ReS LOGIC - OFFSECS PYRO ~I (2) - SAFE

-34-

PROMonitor VMAB

If lt25 vdc go to EMERGPOWER DOWN

34 F 37 OOEPCM BIT RATE - LOWATT DB - MAXEMS MODE - STBYEMS FUNC - OFF

Go To EARTH ORBIT ENTRY pg _--40-__

-36-

8 SPS THRUSTING PREPCYCLE CRYO FANSSPS GAGING - ACI (ver~fy)

PUG MODE - NORM (venfy)BMAG MODE (3) - RATE 2tv CG - CSMCMC MODE - FREEAUTO RCS SEL (16) - MNA or HNB

(hftoff conbg)SC CONT - CMCAUTO

9 MNVR TO PAD BURN ATTV62E

10 V49E

11 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLESPRO

12 F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) PRO(HAN) SC CONT - ses

MNVR to 14

06 18 AUTO MNVR TO FDAI RPY ANGLES13

14 F 50 18 REO TRIH TO FDAI RPY ANGLES(TRIM) Go to 12(BYPASS) ENTR

15 BORESIGHT STAR CHECK

16 V37E 40EOPT PWR - OFF

17 F 50 18 REQUEST MNVR TO FDAI RPY ANGLES (01deg)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CHCAUTOPRO to 18

(MANDAP) BMAG HODE (3) - RATE 2SC CONT - CMCHOLDMNVR to 19

(HANseS) se eONT - sesMNVR to 19

-35-

54 NORMAL DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL ~V

1 V37E 30E

2 F 06 33 GETI (hrm~nOlsec)

(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

3 F 06 81 ~VXYZ (LV)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

( lfps)

4 F 06 42 HAHP~V (1nmlfps)Record W

(ACCEPT) PRO -----(REJECT) Rese1ect P30 or P27 Load new pa~am

5 F 16 45 MTFIMGA (marksmln-secOldeg)MGA -00002 If ~ lMU not a1~gned

SET DETPRO

6

7

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY v1v - OFFCAB PRESS REL v1v (2) - NORMcb ELS (2) - close (verify)cb SECS ARM (2) - close (ver~fy)

cb SECS LOGIC (2) - close (verlfy)AUTO RCS SEL CM (12) - ~mA or MNB

(l~ftoff conf~g)

ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM AampB - off (ctr)

18

-37-

06 18 AUTO MNVR TO FDAI RPY ANGLES (01 0)

19 l 50 18 REOUEST TRIM MNVR TOALIGN SIC ROLLGDC ALIGN

FDAI RPY ANGLES(010

)

+54-00m(-06-00)

TIG-5mJn

5500m(-0500)

TVC CHECK amp PREPcb STAB CONT SYS (all) - closecb SPS (12) - closeATT DB - MINRATE - LOl~

LIMIT CYCLE - ONMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE 2ROT CONTR PWR DIRECT (2) - OFFSCS TVC (2) - RATE CMD

If SCS SCS TVC (2) - AUTO SC CONT - SCS ~

TVC GMBL DRIVE PampY - AUTOMN BUS TIE (2) - ONTVC SERVO PWR 1 - AC1MNA

2 - AC2MNBTRANS CONTR PWR - ONROT CONTR PWR NORMAL 2 - ACRHC 2 - ARMED

HORIZ CHK - HorJz on 12deg wJndmlmark (LJffiJt +3 0 PNGCS GONO GO)

If NO GO set tw 180 0 180deg0 0

Track horJz wJth 24deg wJndow markAt TIG-2 mJn Ahgn GDC

PRIMARY TVC CHECKGMBL MOT P1-Y1 -STARTON(LMP confJrm)

If SCS verJfy Thumbwheel TrJmTHC - CWVenfy NO MTVC

SEC TVC CHECKGHBL MOT P2-Y2 -STARTON(LMP confJrm)SET GPI TRIHVenfy MTVCTHC NEUTRALGPI returns to 00 (CMC) or trJm (SCS)ROT CONT Pl~ NORM 2 - ACDC

(TRIM) Go to step 17(BYPASS) BMAG MODE(3) - ATTIRATE2 (ver1fy)

ENTR

-38-

20 F SO 25 00204 GMBL TEST OPTION(ACCEPT) SC CONT - GMC (ver~fy)

PROMonitor GPI Response

0020-2000020-200Tr~m

TEST FAIL SC CONT - SCS SCS TVC (2) - AUTO

(REJECT) ENTR

21 06 40 TFIVG~VM (m~n-sec1fps)

PROG ALM - TIG s1~pped

V5N9E 01703

KEY RLSE To 21 ROT CONTR PWR DIRECT (2) - MNABSPS He v1vs (2) - AUTO (ver~fy)

LIMIT CYCLE - OFFFDAI SCALE - SOIScb SPS P2Y2 - open (for cr~t burn)

5800(-02 00)

5925(-0035)

59middot 30(-0030)

06 40

59XX(-OOXX)

AV THRUST A(B) - NORMALTHC - ARMEDRlIC (2) - ARMEDTAPE RCDR - GID RESETHBR

DSKY BLANKS

(AVE G ON)EMS MODE - NORMAL

TFIVG~VM (m~n-seclfps)

CHECK PIPA BIAS lt2fps for 5 sec

ULLAGE AS REQ

IF NO ULLAGE DIR ULLAGE PB - PUSH~

CONTROL ATT WRlIC MONITOR AVM (R3) COUNTING UP

5955(-0005)

F 99 40 ENG ON ENABLE REQUEST(AUTO IGN) PRO AT TFI gt0 sec(BYPASS IGN) ENTR to 24

22 0000 IGN

-39-

If SCS - THRUST ON PB - PUSH

06 40 TFCVG~VM (m~n-seclfpslfps)

~F 97 40 SPS Thrust fall ~

~(RESTART) PRO To IGN (RECYCLE) ENTR To TIG-05 sec

SPS THRUST LITE - ONMONITOR THRUSTING

Pc 95-105 pSlaEMS COUNTING DOWNSPS IN3 v1vs (4) - OPENSPS He v1vs tb (2) - graySPS FUELOXID PRESS - 175-195 pSlaPUGS - BALANCED

PROG ALARM V5N9E 01407 VG INCTHC - CW FLY MTVC

ECOEMER SPS CUTOFF J

AV THRUST (2) - OFF

23 F 16 40 TFC(STATIC)VG~VM (mln-seclfps)~V THRUST AB - OFF

SPS IN3 v1vs (4) - CLOSEDSPS He tb (2) - bp

cb SPS P2Y2 - closed (verlfy)TVC SERVO PHR - AC1MNA (venfy)TVC SERVO PWR 2 - OFF

PRO

24 F 16 85 VG XYZ(CM) CUps)NULL RESIDUALSRECORD ~V CTR amp RESIDUALS I1VCEMS FUNC - OFF VGXEMS MODE - STBY VGYBMAG MODE (3) - RATE 2ATT DB - MAX VGZTRANS CONT PHR - OFF

PRO

25 F 37 V82E

26 F 16 44 HAHPTFF (lnmm~n-sec)

R3-59B59 HP gt494 nmPRO

27 F 37 OOE

-40-

55 EARTH ORBIT ENTRY

1 Venfy CMSMR __

P_shyY_-

SEP ATT(180deg)

(0deg )

2

3

4

EMS INITIALIZATIONEMS FUNC - RNG SETSET RNG TO PAD DATA RNGEMS FUNC - VA SETSlew scroll to pad data VIOEMS FUNC - ENTRY

RSI ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on(up)GDC ALIGN PB - PUSH amp HOLDYAW tw - Pos1tion RSI thru 45deg amp

back to LIFl UPGDC ALIGN PB - RELEASEEMS ROLL - OFFAl1gn GDC to lMU

PWR REDUCT (Norm Deorb Only)HGA PWR - OFFFC PUMPS (3) - OFFVer1fy s1ngle suit compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - Lowcb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2)-openlOb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MAN

-41-

P61 - ENTRY PREP

5 V37E 61E05 09 01427 - ROLL REVERSED05 09 01426 - IMU UNSAT

6 F 06 61 IMPACT LAT LONG liDS UPDN (+-)(01 0

010

+00001)

PRO

PAD VALUESLATLON==G------liDS UP DN _

7 F 06 60 GMAXV400KGAMMA EIRecord

GMAXV400K----GAMMA EI _

PRO

8 F 06 63 RTOGO (1nm) PAD _VIa (fps) PADTFE (mln-sec) ----Compare wlth MSFN for PGNS GONO GONO COMM SET RTOGO amp VIO IN EMS amp

INITIALIZE(ACCEPT) PRO(RECALC) V32E to 8

-42-

P62 - CMSM SEP amp PRE-ENTRY MNVR

9 F 50 25 00041 REQUEST CMSM SEPSC CONT - SCSFREEYAW - 45deg out-of-plane (left for RCS

nght for SPS)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE2PRIM GLY to RAD - BYPASS (verlfy)SECS LOGIC (2) - on (up)MSFN conflrm GO for PYRO ARMSECS PYRO ARM - ARMMN BUS TIE (2) - ON (verlfy)CMSM SEF (2) - ONCSMLM FNl SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 pSlaCM RCS LOGIC - OFFSECS PYRO ARM - SAFEMonltor VMAB

If lt25vdc go to EMERG POWERDOWN Pg E6-1AUTO RCS SEL AlC ROLL (4) - OFFAUTO RCS SEL CM 2(6) - OFFAUTO RCS SEL CM 1(6) - MNA or MNBYAW back to 00

PITCH TO ENTRY ATTROLL 0deg (LIFT UP)PITCH - HORIZ on 317deg MARK (400K)YAW 00

ATT DB - MAXMAN ATT (PITCH) - ACCEL CMDEMS DATA - VerifyEMS FUNC - ENTRY (verlfy)EMS MODE - NORMALMAINTAIN HORIZ TRK

PRO (Act ENTRY DAP)

10 F 06 61 IMPACT LAT LONG HDSDN(010 010 -00001)

PRO

11 FOSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axlS beyond 45deg of Vel vector)

-43-

P63 - ENTRY INIT

12 06 64 GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PWR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRHORIZ CKP~tch error needle goes toward

zero approach~ng 05G t~me

MAN ATT (PITCH) - RATE CMDIf CMC ~s GO

BMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS FLY BETA If CMC NO GO ~

SC CONT - SCS~

FLY EMS RCS Deorh Roll HDS UPTRACK HORIZ w~th 29deg w~ndow mk

P64 - ENTRY POST 05G

13

05G t=elt+0___)

06 68

RTOGO AT 05G AGREES WITH EMS - venfyHORIZ CK05E Lt - on (EMS start)

No EMS start w~th~n 3 secsEMS MODE - BACKUP VHF RNG 05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds L~ft DN

NNVR L~ft DNEMS GONO GO

G-V Plot w~th~n llm~ts

Rng ctr dwn 60 + 7 durlng 10 sec per~od

Mon~tor G-meter forconvergence wlth pad data (Do)

(Vlt27K fps) Go To 17

-44-

P65 - ENTRY - UP CONT (Vgt27K fps)

14 F 16 69 BETA (01deg)DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT~

SC CONT - SCS FLY EMS

PRO

15 06 68 BElA VI HOOT (01deg fpsfps)(VltVL +500 fps amp RDOT Neg) Go To 17

p66 - ENTRY - BALLISTIC (DltDL)

16 06 22 DESIRED GMBL ANGLES RPY (01deg)Mon~tor hor~z +12deg of 317deg mark

P67 - ENTRY - FINAL PHASE (02G)

17 0666 BETACRSRNG ERRDNRNG ERR (Oldeglnmlnm)KEY VERBRecord DNRNG ERR _KEY RLSEL~m~t +100nm from PAD DRE

Mon~tor l~ft vector on RSI amp FDAIF 16 67 RTOGOLATLONG (Vre1=1000fps)

(lnm 010 01deg)SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOlfflMon~tor altimeter

Go To EARTHLANDING pg _I4L5__

-45-

56 EARTHLANDING

90K STEAM PRESS - PEGGED50K CABIN PRESS REL vIv (2) - BOOSTENTRY

SECS PYRO ARM (2) - ARM

40K(90K + 63s)

CM UNSTABLE RCS CMD - OFF ~ 40K APEX COVER JETT PG-PUSH DROGUE DEPLOY PG - PUSH (2 secafter apex cover Jett)

30K ELS LOGIC - ON (up)ELS - AUTO

24K RCS hsable (auto)(90K+92s) RCS CMD - OFF

Apex cover Jett (auto)APEX COVER JETT PB - PUSH

(WAIT 2 SECS)Drogue parachutes deployed (auto)

DROGUE DEPLOY PB - PUSH~

If Drogues FallELS - ~ ~Stablllze CM 5K MAIN DPLY PB - PUSHELS - AUTO

235K Cabln Pressure lncreaslng (Drogues + 50s)If not lncreaSlng by 17K CABIN PRESS REL vlv (RR) - DUMP

-46-

10K Maln parachutes deployedMAIN DEPLOY PB - PUSH (wlthln 1 sec)VHF ANT - RECYVHF AMA - SIMPLEXVHF BCN - ONCABIN PRESS REL v1v (2) - CLOSEDIRECT 02 vlv - OPENCM RCS LOGIC - on (up)CM PRPLNT - DUMP (burn audlb1e)Monltor CM ReS 1amp2 for He press decrease

NO BURN or PRESS DECREASE USE BOTH RHCs DO NOT FIRE PITCH JETS

CM PRPLNT-PURGE (to zero He press)CM RCS He DUMP PB - PUSH RHC (2) - 30 sees NO PITCH k

STRUT LOCKS (2) - UNLOCK

cb FLT amp PL BAT BUS ABampBAT C (3) - closecb FLT amp PLT MNA amp B (2) - opencb ECS RAD HTR OVLD (2) - opencb SPS PampY (4) - open

3K CABIN PRESS REL v1v (RH) - DUMP (after purgecompleted)

FLOOD Lts - POST LDGCM RCS PRPLNT (2) - OFFROT CONTR PWR DIRECT (2) - OFF

800 CAB PRESS RELF vlv - CLOSE (latch off)MN BUS TIE (2) - OFF

AFTER LANDINGcb MAIN REL PYRO (2) - closeMAIN RELEASE - on(up)

Go to POSTLANDING pg _47L-__

I

2

3

-47-

57 POSTLANDING

STABILIZATION VENTILATION COMMUNICATIONS

DIRECT 02 vlv - CLOSE

Stablllzation after landlngELS - AUTO (verlfy)cb MAIN REL PYRO (2) - close (venfy)MAIN RELEASE - on (up) (verlfy)S~CS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb BAT RLY BUS (2) - open

No contact w1th recovery forcesVHF AM AampB - off (ctr) ~

VHF AM Rev ONLY - A cb PL VENT - closecb FLOAT BAG (3) - closecb UPRIGHT SYS COMPRESS (2) - closeIf Stable II

FLOAT BAG(3)-FILL t1ll 2 m1n afterupr1ght then - OFF

VHF AM AlB amp BCN - OFF whlle lnvertedIf Stable I

After 10 M1n Coollng Per1odFLOAT BAG (3) - FILL 7 mln then OFF

Post Stab1lizat1on And Ventllat10nPL BCN LT - BCN LT LOWPL VENT vlv - UNLOCK (Pull)Remove PL VENT Exh CoverPL VENT - HIGH or LOWPL DYE MARKER - ON (swlmmer comm)Release foots traps and_restralntscb MNA BAT BUS A amp BAT C (2) - opencb MNB BAT BUS B amp BAT C (2) - opencb FLT amp PL BAT C - opencb PYRO A SEQ A - opencb PYRO B SEQ B - open

EACH HR - CHECK DC VOLTSgt 275 V If Notmiddot cb FLT amp PL-BAT BUS AampB (2) -open cb FLT amp PL BAT C (1) - open GO TO LOW POWER CHECKLIST

Unstow and lnstall PLV DISTRIB DUCTDeploy grappllng hook and 11ne 1f req

4

-48-

Post Landing Communlcatl0nsVHF ANT-RECY (venfy)VHF BCN - ON (verlfy)

If no contact ~lth recovery forcesperform VHF BEACON Check

MONITOR VHF BEACON transmlSSlonnth VHF AM B Rcvr andor Su)vlval

TransceiverkVHF Beacon not operatlng ~connect Surv~val TranscelVer to antcable behlnd VHF ant access pnland place radio ln BCN mode

LOW POHER CHECKLISTVHF BCN - OFFVHF AM (3) - RCVFLOOD Lts - OFFVHF AM AampB - off (ctr)VHF AM RCV ONLY - A (venfy)COUCH LIGHTS - OFFPOSTLANDING VENT SYS mlnlmlze useSURV RADIO - plug mto VHF BCN ANT cableconn behind VHF ant acess pnl amp turn radloon l-n BCN mode

EGRESS PROCEDURES

CMPCDRLMPCDR

CMPCDRCMP

LMPLl1PCDR

STABLE IDlsconnect Umblll-calsNeck darn onCenter couch - 270 0 positionArmrests stowedConnect raft to SIC l-f desl-red wlth

green lanyardConnect raft ~hl-te lanyards to SUltS amp

lnflate water wlngs when eXltl-ngHATCH PISTON PRESS vlv - PRESS (Outbd)Slde Hatch openedPL VENT - OFFcb Pnl 250 (all) - openEgress with 11feraftPut hardware klt outEgress

or CDIPALL

CMF

CDRCMF

CDR

LMF

CMFCMP LMFCMP

UlP

CDR

-49-

STABLE IIcb CREW STA AUDIO (3) - openD~sconnect umb~1~ca1s

Release foots trapsRelease restra~nt harnessCouch seat pans (3) - 170 0 pos1t10nArm rests stowedSurv1va1 k~ts removed from stowageConnect life raft ma~n1~ne to CDR or SicConnect f~rst wh~te lanyard from

11fe raft to suitConnect th~rd wh~te lanyard from

l~fe raft to SU1tConnect rucksacks together to yellow

lanyard on raft bagPRESSURE EQUALIZATION vlv - OPENRemove and stow fwd hatchEX1t feet f1rst w1th rucksacks when clear

of siC 1nflate water w1ngs and raftExit feet f1rst when clear of SiC

1nflate water w1ngsEX1t feet f1rst when clear of sic

1nflate water w1ngs

-50-

60 TLI ABORTS

TLI Aborts are conta~ned ~n the ESD s~nce the bulk of the funct~ons

concern entry preparat20ns and performance Th~s allows a s2nglesource of procedures for procedure rev2ew val~dat~on checkout andtra~n~ng These procedures ~ncorporate TLI preparat20ns as found ~n

reference 6 w~th the TLI Abort Procedures and these t~e 2nto normallunar return Entry Procedures found ~n sect20n 5 The guidel~nes

for th~s cont2ngency are spec2f2ed 2n reference 7

In2t2al preparat~ons for TLI pos2t20n the necessary system sW2tches2n add~t~on to perform~ng an EMS ~V test and a GDC al~gnment Afterthe DET ~s set for mon2tor2ng TB6 the CMP ~ncreases the 12ght levelof the LEB DSKY to max~mum and returns to the h2s couch Th2s 2Sdone so that the LEB DSKY can be observed ~n the event sunl~ght orreflect20ns wash out the ma2n d2splay panel DSKY dur2ng cr2t2calmaneuvers The crew then straps ~n and prepares for mon2tor~ng TB6as 2nd2cated by the SII SEP L~te The t2mes se~uence of procedures2S keyed on th~s d~splay and ~ncludes the DET START funct~on andSIVB IGNITION Dur2ng the burn the crew mon2tors the FDAIs foratt~tude excurs20ns and abnormal rates report~ng status checks toM~ss2on Control at d2screet t~mes dur2ng the maneuver Upon SIVBSHUTDOWN the eMP records the DSKY d~splayed performance parametersand awa2ts ground conf2rmat~on

The rat~onal for TLI aborts ~s descr~bed 2n reference 7 A summar2shyzat20n 2S extracted to prov2de background and gu2de12nes 2n th2sdocument The abort procedures cover aborts 10 m2nutes after conshyt2ngent SIVE shutdown and aborts 90 m2nutes after normal SIVE shutshydown t2me

The 10 m~nute TLI abort ~s des2gned to be used dur~ng TLI ~n theevent a spacecraft problem develops Wh2Ch can result 2n catastrophe2f ~mmed~ate act~on 2S not taken If the s~tuat20n perm~ts the crewshould always allow the SIVB to complete TLI at wh~ch t~me the groundand crew can perform a malfunct~on analys~s to determ~ne ~f an abort~s adv~sable If a fa~lure occurs that necess2tates the shutdown ofthe SIVB and the ~u~ck return of the crew to earth th~s abort ~s

des~gned to be as ~nsens~t~ve to execut~on errors as poss~ble andst21l be targeted to m2dcorr2dor The burn att~tude w~th the f~ed

hor~zon reference ~s a constant value for any shutdown t~me Theburn durat~on 2S a funct20n of shutdown t2me and 2S ava21able fromcrew charts S~nce the pr~mary purpose of th~s abort ~s to returnto earth as qU2ckly as poss2ble there are no restr2ct20ns as toland~ng locat~on However ~f the t~me to EI is greater than abouttwo hours a midcourse correct20n should be ant~c~pated

The 90 m2nute TLI abort 2S to be used 2f a cr2t2cal subsystem malshyfunct~on ~s determ2ned and the dec2s~on to abort ~s made after the

-51-

TLI cutoff and before TLI cutoff plus approxlmately 80 m1nutesTh1S allows suff1c1ent separatlon and procedural t1me to set upfor the SPS deorb1t burn performed at about TLI + 90 Note thatgenerally the deorb1t burns w1ll be performed a fe11 m1nutes beforeTLI + 90 accord1ng to crew charts shown In reference 8 The no-comm except10n requ1res that 90 m1nutes be the 1nput t1me of 19n1shytlon for P-37 (onboard return-to-earth abort program) so that onshyboard calculatlons can correspond w1th ground calculat10ns to computethe CM land1ng p01nt Th1S TLI abort lS des1gned so that returnfl1ght t1me does not exceed 18 hours and abort ~V does not exceed7000 fps ThlS abort can be performed uSlng chart ~Vs and attltudesand the earths hor1zon serves as a suff1c1ent reference The maneushyver lS targeted to ach1eve the mldcorr1dor entry target Ilne andtlmed to result 1n a deslgnated recovery area

It 1S ObV10US for abort deC1S1ons early 1n the TLI + 90 m1nute t1meshyframe that a GampN SPS burn should be performed In order to keep theTLI abort procedures cons1stent and w1th emphasls on slmpl1c1ty theprocedures here reflect a SCS SPS abort burn to cover the full abortdec1s1on t1meframe

A m1dcourse correct1on for corr1dor control after a TLI abort may bedeS1red 1f the SPS burn d1d not meet expectat1ons The TLIabortprocedures 1n th1S sect10n adapt to the normal lunar return tlmel1neand procedures pr10r to the f1nal MCC

-52-

61 TLI PREPARATION PROCEDURES

GET = 150

CRO AOS(___)

CRO LOS( )(22142)

5100

Don Helmets amp Gloves

XLUNAR - INJECT (verify)EDS PWR - on (venfy)EMS FUNC - OFF (verlfy)EMS MODE - STBYEMS FUNC - IW SETVHF RNGEMS MODE - NORMALSet ~V indo to +15868 fpsEMS FUMC - ~V Test

SPS THRUST Lt - onoff (10 sec)~V lnd stops at -01 to -415

EMS MODE - STBYEMS FUMC - ~V SETVHF RNGSet ~VC

EMS FUNC---~~V=----

GDC ALIGNFDAI Select - liZcb SECS LOGIC (Z) - close (verify)cb SECS ARM (Z) - closeSECS LOGIC (Z) - on (up)MSFN Conflrm GO for PYRO ARM (If pass)SECS PYRO ARM (Z) - on (up)TRANS CONTROL PWR - ONROT CONTR PWR NORMAL (Z) - ACDC(verlfy)ROT CONTR PWR DIRECT (Z) - MNAMNBLV INnGPI - SIISIVB (venfy)LV GUID - IU (venfy)cb DIRECT ULLAGE (Z) - closedSet EVENT TIMER to 5100Begin MONITOR For TB6

CMP to Couch

TB 6 - SII SEP Lt on (TIG-9 mln 38 sec)KEY V83E

SET ORDEALFDAI Z ORB RATE at 180 0 0SII SEP Lt out (38 sec later)Start DET COUNTING UPSC CaNT - SCS (verify)MONITOR LV TANK PRESS

~P lt 36 psid (OXID gt FUEL)~P lt Z6 psid (FUEL gt OXID)

EMERGENCY CSMLV SEP UP TLM CM - BLOCK (verify)UP TLM IU - BLOCK (venfy)

-53-

+45degPY))0middot sec PY

lOK nmltHAlt25K nm

Two phas~ng mnvrs two SPS mnvrs to circular~ze at 150 nmearth orb~t

CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ssion 4K nmltHAltlOK nm CSM amp1M - Two phasing mnvrs two SPS mnvrs to circularize at 150 nm earth orb~t CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ss~on

CSM amp 1M - Two phas~ng mnvrs APS burn todepletion th~rd phasing mnvrSPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn tosem~sync orb~t

25K nmltHAlt40K nm CSM amp 1M - Two phasmg mnvrs APS burn to depletion third phas~ng mnvr SPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn to sem~sync orbit HA)40K nm DPS ava~l - DPS LOll circularize with SPS

DPS not ava~l - Lunar flyby or CSM only to lunar orbit (if reqd gtV lt4000 fps)

V37E 47E (check b~as) Record -=--rshy(Limit 98 fpsmm)

( 1fps)tVXYZN62EVIHDOTHPAD (fpsfpslnm)MONITOR VI ( ) at ECO

SCS TVC SERVO PWR 1 - ACIMNA2 - OFF

TAPE RCDR - CMD RESETHBREMS MODE - NORMAL

SIr SEP Lt - ONTLI Inhib~t S~gnals w~11 not be honored after 5942

SIVB ULLAGE BeginsSII SEP Lt - off (TIG - 18 sec)SIVB FUEL LEADSIVB ULLAGE d~scont~nues

LV ENG I Lt - onSIVB IGNITION ( GETI)LV ENG I Lt - off - -shyMONITOR THRUST amp ATTITUDEMONITOR LV TANK PRESSSIVE ECO (Lt on) (BEGIN TB7)

EMER SIVE CUTOFF AT 6 SEC PAST BURN TIME IF VI ATTAINEDTHC CCW ampNEUTRAL IN 1 SEC or SIISIVB sW - LV STAGEPremature Shutdown HAlt4K nm CSM amp 1M -

5700

58205836

F 16 835800

F 16 62

5838594259525955595900000002SUNRISE(___)

HAW AOS(__=_) KEY VERB (freeze d~splay)

SIVB ATT HOLD 20 sec amp BEGIN VENTINGSIVB NNVR TO ORB RT (HDS DN) (3middot sec)

Record VI -c---HDOT _

HPAD _

KEY RLSEF 16 62

F 16 83

HAW LOS(__=-)

KEYmiddotRLSE~VXYZ (lfps)

Record ~VX---_

~vy

WZ--

AVC---_

TAPE RCDR - off (ctr)EMS MODE - STBYEMS FUNC - OFFSECS PYRO ARM (2) - SAFE

PRO

BURN STATUS REPORT

____--~TIG

BT------VGX____-R

-----P----_Y

REMARKS

_____VI

______--HDOT______--H______---AVC______---FUEL_______OXID

_______UNBAL

F 3708=00 OOEGOS AOS CMP TO LEB

(-=-=-)

0000

0003

0005

0014

0100

-55-

62 TLI 10 MIN ABORTSECS LOGIC (2) - on (up)SECS PYRO ARM (2) - ARM

TRANS CONTR - CGH (4 sec) amp +XDET RESET (verlfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS GMD-ON

TRANS GONTR - neutral then +X for10 sec

SIVBGPI s~ - GPIExcesslve rates 6V THRUST A - NORMAL SPS THRUST - DIRECT When rates damped 6V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

TRANS CONTR +X - OFFV37E OOE

PITGH UP to LOGAL VERT (+X axlSto~ard the earth)

RATE - LOWBMAG MODE (3) - ATTIRATE 2EDS PHR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SEGS ARM (2) - opencb EDS (3) - open

TRANS CONTR -X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (180deg)P (199deg)Y (0deg)

RETRO UPDATEGETI _

JV _VG

Jtb ---GET 400K _

05G _GET DROGUE _

ENTRY P _R _

Y_--

0945

-56-

ALIGN HORIZ ON RET +1 MKGMBL CHECK (T11lle Pentattlng)MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conflnn)cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FUMC - JV SETVHF RNGSET JV from chartE~S FUMC - JVEMS fODE - NOIDlAL

lV THRUST A - NORMALV37E 47E (THRUST fONITOR)

F 16 83 lVXYZ (1 fps)

0950

1000

NOTE For aborts durlng 1st mln of TLIKEY V82E F 16 44 (HaHpTff)Burn untll Hp lt 19NM

TRANS CONTR +X

THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN JV reqdJV THRUST (2) - OFFReport cutoff

cb SPS P2 Y2- closeGfBL MTRS (4) - OFF (LMP Confinn)TRANS CONT PWR - OFFTVC SERVO PWR (2) - OFFMN BUS TIE (2) - OFFcb SPS P1amp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREIf est time to EIltOl5500 omlt fCC andenter the SUPERCIRC CKLIST as early as pos-slb1e Pg ~2~3~ __If est time to EI)Ol5500 anticlpate afCC Enter the ENTRY PREP CKLIST at step 9pg 18

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

-2tl C

l I W gt- ~-4

z laquo I I- 0 -6

l- I J u gt- ~-8

z w w -10

~_ONSANT

9O

VER

SHO

OT

BOU

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LIF

TV

EC

TOR

OR

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TATI

ON

LIN

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SH

ALL

OW

TAR

GE

TLI

NE

STE

EP

TAR

GE

TLI

NE 12

gU

ND

ERSH

OO

TBO

UN

DAR

Y

RE

EN

TRY

CO

RR

IDO

R

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26

28

30

32

34

RE

EN

TRY

VE

LOC

ITY

VE

1-F

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3B

6-i

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CC

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bull-1

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43

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73

8X

03

-i- rtREQUIRED PITCH GIMBAL ANG LETO OBTAIN HOR-IZON AT 317

DEGREES IN wiiiiDOW

260

z~I- ~ i5 24000

1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

-I

-1-

NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

I LU HD~-

LUHD

lt0 120UJ0

~

80 HOLD PRESENT TRIMgt LU HD013

~Y~HOIgtlt

TOP OF WINDOWa 40to

31 7 SCRIBEaaI

80 TTOM OF WINDOWi= 0

0--ltoa

-40t-z

~~~Uw w u lt0 -80

HOLO PRESENT TRIlJCl

LOHU0 lt0

J gt -120 HOLD 059 TRIMlt0 z

LDHUlt0 FIELD OF VI S10 NLDHU LIFT-DOWNHEADS -UPLUHD LIFT-UP HEADS-DOWN

~~H~-160 q - P63 LIMITI- NOrE-VALIO ONLY FO~t~--

LUNAR RETURN VELOCITY

plusmnl8020 244middot 8 12 16

TIME TO 400K FT ALTITUDE-MIN

4

P37

LONG

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344

348

352

356

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120

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320

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-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 36: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

-33-

~Uili ATT PITCH - ACCEL CMDFDAI SCALE - 55MNVR TO CM BURN ATT (NULL ERR NEEDLES)

R 0degPY --00--

30

31

CM RCS BURNRHC III-ContJnuous PJtch DownRHC HZ-Module PJtch to null needlesBURN VGZ TO ZERO

If only 1 RHC Pulse + P=5deg from retro att MaJnta~n rates lt3degsec

BURN COMPLETION ATllV CTR= or DET= _

V8ZE

32 F 16 44 HAHPTFF (1nmffiJn-sec)Check HP-

If gt Pad data contJnue burnuntJ1 lt Pad

PRO

33 F 16 85 VGXYZ (Ups)Read VG resJduals to MSFN

(HYBRID) PRO to 34(SM ONLY BURN)

PROF 37 ODE

EI-1500 V37E 47EF 16 83 twx Y Z (Ups)

SC CONT - SCSFREEMAN ATT (PITCH) - RATE CMDRATE - HIGHPRIM GLY To RAD - BYPASS (verJfy)MN BUS TIE (2) - ON (verJfy)CMSM SEP (2) - ONCSMLM FNL SEP (2) - on (up) (verJfy)Campl MODE - CMRCS TRNFR - CMCM ReS LOGIC - OFFSECS PYRO ~I (2) - SAFE

-34-

PROMonitor VMAB

If lt25 vdc go to EMERGPOWER DOWN

34 F 37 OOEPCM BIT RATE - LOWATT DB - MAXEMS MODE - STBYEMS FUNC - OFF

Go To EARTH ORBIT ENTRY pg _--40-__

-36-

8 SPS THRUSTING PREPCYCLE CRYO FANSSPS GAGING - ACI (ver~fy)

PUG MODE - NORM (venfy)BMAG MODE (3) - RATE 2tv CG - CSMCMC MODE - FREEAUTO RCS SEL (16) - MNA or HNB

(hftoff conbg)SC CONT - CMCAUTO

9 MNVR TO PAD BURN ATTV62E

10 V49E

11 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLESPRO

12 F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) PRO(HAN) SC CONT - ses

MNVR to 14

06 18 AUTO MNVR TO FDAI RPY ANGLES13

14 F 50 18 REO TRIH TO FDAI RPY ANGLES(TRIM) Go to 12(BYPASS) ENTR

15 BORESIGHT STAR CHECK

16 V37E 40EOPT PWR - OFF

17 F 50 18 REQUEST MNVR TO FDAI RPY ANGLES (01deg)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CHCAUTOPRO to 18

(MANDAP) BMAG HODE (3) - RATE 2SC CONT - CMCHOLDMNVR to 19

(HANseS) se eONT - sesMNVR to 19

-35-

54 NORMAL DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL ~V

1 V37E 30E

2 F 06 33 GETI (hrm~nOlsec)

(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

3 F 06 81 ~VXYZ (LV)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

( lfps)

4 F 06 42 HAHP~V (1nmlfps)Record W

(ACCEPT) PRO -----(REJECT) Rese1ect P30 or P27 Load new pa~am

5 F 16 45 MTFIMGA (marksmln-secOldeg)MGA -00002 If ~ lMU not a1~gned

SET DETPRO

6

7

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY v1v - OFFCAB PRESS REL v1v (2) - NORMcb ELS (2) - close (verify)cb SECS ARM (2) - close (ver~fy)

cb SECS LOGIC (2) - close (verlfy)AUTO RCS SEL CM (12) - ~mA or MNB

(l~ftoff conf~g)

ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM AampB - off (ctr)

18

-37-

06 18 AUTO MNVR TO FDAI RPY ANGLES (01 0)

19 l 50 18 REOUEST TRIM MNVR TOALIGN SIC ROLLGDC ALIGN

FDAI RPY ANGLES(010

)

+54-00m(-06-00)

TIG-5mJn

5500m(-0500)

TVC CHECK amp PREPcb STAB CONT SYS (all) - closecb SPS (12) - closeATT DB - MINRATE - LOl~

LIMIT CYCLE - ONMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE 2ROT CONTR PWR DIRECT (2) - OFFSCS TVC (2) - RATE CMD

If SCS SCS TVC (2) - AUTO SC CONT - SCS ~

TVC GMBL DRIVE PampY - AUTOMN BUS TIE (2) - ONTVC SERVO PWR 1 - AC1MNA

2 - AC2MNBTRANS CONTR PWR - ONROT CONTR PWR NORMAL 2 - ACRHC 2 - ARMED

HORIZ CHK - HorJz on 12deg wJndmlmark (LJffiJt +3 0 PNGCS GONO GO)

If NO GO set tw 180 0 180deg0 0

Track horJz wJth 24deg wJndow markAt TIG-2 mJn Ahgn GDC

PRIMARY TVC CHECKGMBL MOT P1-Y1 -STARTON(LMP confJrm)

If SCS verJfy Thumbwheel TrJmTHC - CWVenfy NO MTVC

SEC TVC CHECKGHBL MOT P2-Y2 -STARTON(LMP confJrm)SET GPI TRIHVenfy MTVCTHC NEUTRALGPI returns to 00 (CMC) or trJm (SCS)ROT CONT Pl~ NORM 2 - ACDC

(TRIM) Go to step 17(BYPASS) BMAG MODE(3) - ATTIRATE2 (ver1fy)

ENTR

-38-

20 F SO 25 00204 GMBL TEST OPTION(ACCEPT) SC CONT - GMC (ver~fy)

PROMonitor GPI Response

0020-2000020-200Tr~m

TEST FAIL SC CONT - SCS SCS TVC (2) - AUTO

(REJECT) ENTR

21 06 40 TFIVG~VM (m~n-sec1fps)

PROG ALM - TIG s1~pped

V5N9E 01703

KEY RLSE To 21 ROT CONTR PWR DIRECT (2) - MNABSPS He v1vs (2) - AUTO (ver~fy)

LIMIT CYCLE - OFFFDAI SCALE - SOIScb SPS P2Y2 - open (for cr~t burn)

5800(-02 00)

5925(-0035)

59middot 30(-0030)

06 40

59XX(-OOXX)

AV THRUST A(B) - NORMALTHC - ARMEDRlIC (2) - ARMEDTAPE RCDR - GID RESETHBR

DSKY BLANKS

(AVE G ON)EMS MODE - NORMAL

TFIVG~VM (m~n-seclfps)

CHECK PIPA BIAS lt2fps for 5 sec

ULLAGE AS REQ

IF NO ULLAGE DIR ULLAGE PB - PUSH~

CONTROL ATT WRlIC MONITOR AVM (R3) COUNTING UP

5955(-0005)

F 99 40 ENG ON ENABLE REQUEST(AUTO IGN) PRO AT TFI gt0 sec(BYPASS IGN) ENTR to 24

22 0000 IGN

-39-

If SCS - THRUST ON PB - PUSH

06 40 TFCVG~VM (m~n-seclfpslfps)

~F 97 40 SPS Thrust fall ~

~(RESTART) PRO To IGN (RECYCLE) ENTR To TIG-05 sec

SPS THRUST LITE - ONMONITOR THRUSTING

Pc 95-105 pSlaEMS COUNTING DOWNSPS IN3 v1vs (4) - OPENSPS He v1vs tb (2) - graySPS FUELOXID PRESS - 175-195 pSlaPUGS - BALANCED

PROG ALARM V5N9E 01407 VG INCTHC - CW FLY MTVC

ECOEMER SPS CUTOFF J

AV THRUST (2) - OFF

23 F 16 40 TFC(STATIC)VG~VM (mln-seclfps)~V THRUST AB - OFF

SPS IN3 v1vs (4) - CLOSEDSPS He tb (2) - bp

cb SPS P2Y2 - closed (verlfy)TVC SERVO PHR - AC1MNA (venfy)TVC SERVO PWR 2 - OFF

PRO

24 F 16 85 VG XYZ(CM) CUps)NULL RESIDUALSRECORD ~V CTR amp RESIDUALS I1VCEMS FUNC - OFF VGXEMS MODE - STBY VGYBMAG MODE (3) - RATE 2ATT DB - MAX VGZTRANS CONT PHR - OFF

PRO

25 F 37 V82E

26 F 16 44 HAHPTFF (lnmm~n-sec)

R3-59B59 HP gt494 nmPRO

27 F 37 OOE

-40-

55 EARTH ORBIT ENTRY

1 Venfy CMSMR __

P_shyY_-

SEP ATT(180deg)

(0deg )

2

3

4

EMS INITIALIZATIONEMS FUNC - RNG SETSET RNG TO PAD DATA RNGEMS FUNC - VA SETSlew scroll to pad data VIOEMS FUNC - ENTRY

RSI ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on(up)GDC ALIGN PB - PUSH amp HOLDYAW tw - Pos1tion RSI thru 45deg amp

back to LIFl UPGDC ALIGN PB - RELEASEEMS ROLL - OFFAl1gn GDC to lMU

PWR REDUCT (Norm Deorb Only)HGA PWR - OFFFC PUMPS (3) - OFFVer1fy s1ngle suit compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - Lowcb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2)-openlOb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MAN

-41-

P61 - ENTRY PREP

5 V37E 61E05 09 01427 - ROLL REVERSED05 09 01426 - IMU UNSAT

6 F 06 61 IMPACT LAT LONG liDS UPDN (+-)(01 0

010

+00001)

PRO

PAD VALUESLATLON==G------liDS UP DN _

7 F 06 60 GMAXV400KGAMMA EIRecord

GMAXV400K----GAMMA EI _

PRO

8 F 06 63 RTOGO (1nm) PAD _VIa (fps) PADTFE (mln-sec) ----Compare wlth MSFN for PGNS GONO GONO COMM SET RTOGO amp VIO IN EMS amp

INITIALIZE(ACCEPT) PRO(RECALC) V32E to 8

-42-

P62 - CMSM SEP amp PRE-ENTRY MNVR

9 F 50 25 00041 REQUEST CMSM SEPSC CONT - SCSFREEYAW - 45deg out-of-plane (left for RCS

nght for SPS)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE2PRIM GLY to RAD - BYPASS (verlfy)SECS LOGIC (2) - on (up)MSFN conflrm GO for PYRO ARMSECS PYRO ARM - ARMMN BUS TIE (2) - ON (verlfy)CMSM SEF (2) - ONCSMLM FNl SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 pSlaCM RCS LOGIC - OFFSECS PYRO ARM - SAFEMonltor VMAB

If lt25vdc go to EMERG POWERDOWN Pg E6-1AUTO RCS SEL AlC ROLL (4) - OFFAUTO RCS SEL CM 2(6) - OFFAUTO RCS SEL CM 1(6) - MNA or MNBYAW back to 00

PITCH TO ENTRY ATTROLL 0deg (LIFT UP)PITCH - HORIZ on 317deg MARK (400K)YAW 00

ATT DB - MAXMAN ATT (PITCH) - ACCEL CMDEMS DATA - VerifyEMS FUNC - ENTRY (verlfy)EMS MODE - NORMALMAINTAIN HORIZ TRK

PRO (Act ENTRY DAP)

10 F 06 61 IMPACT LAT LONG HDSDN(010 010 -00001)

PRO

11 FOSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axlS beyond 45deg of Vel vector)

-43-

P63 - ENTRY INIT

12 06 64 GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PWR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRHORIZ CKP~tch error needle goes toward

zero approach~ng 05G t~me

MAN ATT (PITCH) - RATE CMDIf CMC ~s GO

BMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS FLY BETA If CMC NO GO ~

SC CONT - SCS~

FLY EMS RCS Deorh Roll HDS UPTRACK HORIZ w~th 29deg w~ndow mk

P64 - ENTRY POST 05G

13

05G t=elt+0___)

06 68

RTOGO AT 05G AGREES WITH EMS - venfyHORIZ CK05E Lt - on (EMS start)

No EMS start w~th~n 3 secsEMS MODE - BACKUP VHF RNG 05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds L~ft DN

NNVR L~ft DNEMS GONO GO

G-V Plot w~th~n llm~ts

Rng ctr dwn 60 + 7 durlng 10 sec per~od

Mon~tor G-meter forconvergence wlth pad data (Do)

(Vlt27K fps) Go To 17

-44-

P65 - ENTRY - UP CONT (Vgt27K fps)

14 F 16 69 BETA (01deg)DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT~

SC CONT - SCS FLY EMS

PRO

15 06 68 BElA VI HOOT (01deg fpsfps)(VltVL +500 fps amp RDOT Neg) Go To 17

p66 - ENTRY - BALLISTIC (DltDL)

16 06 22 DESIRED GMBL ANGLES RPY (01deg)Mon~tor hor~z +12deg of 317deg mark

P67 - ENTRY - FINAL PHASE (02G)

17 0666 BETACRSRNG ERRDNRNG ERR (Oldeglnmlnm)KEY VERBRecord DNRNG ERR _KEY RLSEL~m~t +100nm from PAD DRE

Mon~tor l~ft vector on RSI amp FDAIF 16 67 RTOGOLATLONG (Vre1=1000fps)

(lnm 010 01deg)SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOlfflMon~tor altimeter

Go To EARTHLANDING pg _I4L5__

-45-

56 EARTHLANDING

90K STEAM PRESS - PEGGED50K CABIN PRESS REL vIv (2) - BOOSTENTRY

SECS PYRO ARM (2) - ARM

40K(90K + 63s)

CM UNSTABLE RCS CMD - OFF ~ 40K APEX COVER JETT PG-PUSH DROGUE DEPLOY PG - PUSH (2 secafter apex cover Jett)

30K ELS LOGIC - ON (up)ELS - AUTO

24K RCS hsable (auto)(90K+92s) RCS CMD - OFF

Apex cover Jett (auto)APEX COVER JETT PB - PUSH

(WAIT 2 SECS)Drogue parachutes deployed (auto)

DROGUE DEPLOY PB - PUSH~

If Drogues FallELS - ~ ~Stablllze CM 5K MAIN DPLY PB - PUSHELS - AUTO

235K Cabln Pressure lncreaslng (Drogues + 50s)If not lncreaSlng by 17K CABIN PRESS REL vlv (RR) - DUMP

-46-

10K Maln parachutes deployedMAIN DEPLOY PB - PUSH (wlthln 1 sec)VHF ANT - RECYVHF AMA - SIMPLEXVHF BCN - ONCABIN PRESS REL v1v (2) - CLOSEDIRECT 02 vlv - OPENCM RCS LOGIC - on (up)CM PRPLNT - DUMP (burn audlb1e)Monltor CM ReS 1amp2 for He press decrease

NO BURN or PRESS DECREASE USE BOTH RHCs DO NOT FIRE PITCH JETS

CM PRPLNT-PURGE (to zero He press)CM RCS He DUMP PB - PUSH RHC (2) - 30 sees NO PITCH k

STRUT LOCKS (2) - UNLOCK

cb FLT amp PL BAT BUS ABampBAT C (3) - closecb FLT amp PLT MNA amp B (2) - opencb ECS RAD HTR OVLD (2) - opencb SPS PampY (4) - open

3K CABIN PRESS REL v1v (RH) - DUMP (after purgecompleted)

FLOOD Lts - POST LDGCM RCS PRPLNT (2) - OFFROT CONTR PWR DIRECT (2) - OFF

800 CAB PRESS RELF vlv - CLOSE (latch off)MN BUS TIE (2) - OFF

AFTER LANDINGcb MAIN REL PYRO (2) - closeMAIN RELEASE - on(up)

Go to POSTLANDING pg _47L-__

I

2

3

-47-

57 POSTLANDING

STABILIZATION VENTILATION COMMUNICATIONS

DIRECT 02 vlv - CLOSE

Stablllzation after landlngELS - AUTO (verlfy)cb MAIN REL PYRO (2) - close (venfy)MAIN RELEASE - on (up) (verlfy)S~CS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb BAT RLY BUS (2) - open

No contact w1th recovery forcesVHF AM AampB - off (ctr) ~

VHF AM Rev ONLY - A cb PL VENT - closecb FLOAT BAG (3) - closecb UPRIGHT SYS COMPRESS (2) - closeIf Stable II

FLOAT BAG(3)-FILL t1ll 2 m1n afterupr1ght then - OFF

VHF AM AlB amp BCN - OFF whlle lnvertedIf Stable I

After 10 M1n Coollng Per1odFLOAT BAG (3) - FILL 7 mln then OFF

Post Stab1lizat1on And Ventllat10nPL BCN LT - BCN LT LOWPL VENT vlv - UNLOCK (Pull)Remove PL VENT Exh CoverPL VENT - HIGH or LOWPL DYE MARKER - ON (swlmmer comm)Release foots traps and_restralntscb MNA BAT BUS A amp BAT C (2) - opencb MNB BAT BUS B amp BAT C (2) - opencb FLT amp PL BAT C - opencb PYRO A SEQ A - opencb PYRO B SEQ B - open

EACH HR - CHECK DC VOLTSgt 275 V If Notmiddot cb FLT amp PL-BAT BUS AampB (2) -open cb FLT amp PL BAT C (1) - open GO TO LOW POWER CHECKLIST

Unstow and lnstall PLV DISTRIB DUCTDeploy grappllng hook and 11ne 1f req

4

-48-

Post Landing Communlcatl0nsVHF ANT-RECY (venfy)VHF BCN - ON (verlfy)

If no contact ~lth recovery forcesperform VHF BEACON Check

MONITOR VHF BEACON transmlSSlonnth VHF AM B Rcvr andor Su)vlval

TransceiverkVHF Beacon not operatlng ~connect Surv~val TranscelVer to antcable behlnd VHF ant access pnland place radio ln BCN mode

LOW POHER CHECKLISTVHF BCN - OFFVHF AM (3) - RCVFLOOD Lts - OFFVHF AM AampB - off (ctr)VHF AM RCV ONLY - A (venfy)COUCH LIGHTS - OFFPOSTLANDING VENT SYS mlnlmlze useSURV RADIO - plug mto VHF BCN ANT cableconn behind VHF ant acess pnl amp turn radloon l-n BCN mode

EGRESS PROCEDURES

CMPCDRLMPCDR

CMPCDRCMP

LMPLl1PCDR

STABLE IDlsconnect Umblll-calsNeck darn onCenter couch - 270 0 positionArmrests stowedConnect raft to SIC l-f desl-red wlth

green lanyardConnect raft ~hl-te lanyards to SUltS amp

lnflate water wlngs when eXltl-ngHATCH PISTON PRESS vlv - PRESS (Outbd)Slde Hatch openedPL VENT - OFFcb Pnl 250 (all) - openEgress with 11feraftPut hardware klt outEgress

or CDIPALL

CMF

CDRCMF

CDR

LMF

CMFCMP LMFCMP

UlP

CDR

-49-

STABLE IIcb CREW STA AUDIO (3) - openD~sconnect umb~1~ca1s

Release foots trapsRelease restra~nt harnessCouch seat pans (3) - 170 0 pos1t10nArm rests stowedSurv1va1 k~ts removed from stowageConnect life raft ma~n1~ne to CDR or SicConnect f~rst wh~te lanyard from

11fe raft to suitConnect th~rd wh~te lanyard from

l~fe raft to SU1tConnect rucksacks together to yellow

lanyard on raft bagPRESSURE EQUALIZATION vlv - OPENRemove and stow fwd hatchEX1t feet f1rst w1th rucksacks when clear

of siC 1nflate water w1ngs and raftExit feet f1rst when clear of SiC

1nflate water w1ngsEX1t feet f1rst when clear of sic

1nflate water w1ngs

-50-

60 TLI ABORTS

TLI Aborts are conta~ned ~n the ESD s~nce the bulk of the funct~ons

concern entry preparat20ns and performance Th~s allows a s2nglesource of procedures for procedure rev2ew val~dat~on checkout andtra~n~ng These procedures ~ncorporate TLI preparat20ns as found ~n

reference 6 w~th the TLI Abort Procedures and these t~e 2nto normallunar return Entry Procedures found ~n sect20n 5 The guidel~nes

for th~s cont2ngency are spec2f2ed 2n reference 7

In2t2al preparat~ons for TLI pos2t20n the necessary system sW2tches2n add~t~on to perform~ng an EMS ~V test and a GDC al~gnment Afterthe DET ~s set for mon2tor2ng TB6 the CMP ~ncreases the 12ght levelof the LEB DSKY to max~mum and returns to the h2s couch Th2s 2Sdone so that the LEB DSKY can be observed ~n the event sunl~ght orreflect20ns wash out the ma2n d2splay panel DSKY dur2ng cr2t2calmaneuvers The crew then straps ~n and prepares for mon2tor~ng TB6as 2nd2cated by the SII SEP L~te The t2mes se~uence of procedures2S keyed on th~s d~splay and ~ncludes the DET START funct~on andSIVB IGNITION Dur2ng the burn the crew mon2tors the FDAIs foratt~tude excurs20ns and abnormal rates report~ng status checks toM~ss2on Control at d2screet t~mes dur2ng the maneuver Upon SIVBSHUTDOWN the eMP records the DSKY d~splayed performance parametersand awa2ts ground conf2rmat~on

The rat~onal for TLI aborts ~s descr~bed 2n reference 7 A summar2shyzat20n 2S extracted to prov2de background and gu2de12nes 2n th2sdocument The abort procedures cover aborts 10 m2nutes after conshyt2ngent SIVE shutdown and aborts 90 m2nutes after normal SIVE shutshydown t2me

The 10 m~nute TLI abort ~s des2gned to be used dur~ng TLI ~n theevent a spacecraft problem develops Wh2Ch can result 2n catastrophe2f ~mmed~ate act~on 2S not taken If the s~tuat20n perm~ts the crewshould always allow the SIVB to complete TLI at wh~ch t~me the groundand crew can perform a malfunct~on analys~s to determ~ne ~f an abort~s adv~sable If a fa~lure occurs that necess2tates the shutdown ofthe SIVB and the ~u~ck return of the crew to earth th~s abort ~s

des~gned to be as ~nsens~t~ve to execut~on errors as poss~ble andst21l be targeted to m2dcorr2dor The burn att~tude w~th the f~ed

hor~zon reference ~s a constant value for any shutdown t~me Theburn durat~on 2S a funct20n of shutdown t2me and 2S ava21able fromcrew charts S~nce the pr~mary purpose of th~s abort ~s to returnto earth as qU2ckly as poss2ble there are no restr2ct20ns as toland~ng locat~on However ~f the t~me to EI is greater than abouttwo hours a midcourse correct20n should be ant~c~pated

The 90 m2nute TLI abort 2S to be used 2f a cr2t2cal subsystem malshyfunct~on ~s determ2ned and the dec2s~on to abort ~s made after the

-51-

TLI cutoff and before TLI cutoff plus approxlmately 80 m1nutesTh1S allows suff1c1ent separatlon and procedural t1me to set upfor the SPS deorb1t burn performed at about TLI + 90 Note thatgenerally the deorb1t burns w1ll be performed a fe11 m1nutes beforeTLI + 90 accord1ng to crew charts shown In reference 8 The no-comm except10n requ1res that 90 m1nutes be the 1nput t1me of 19n1shytlon for P-37 (onboard return-to-earth abort program) so that onshyboard calculatlons can correspond w1th ground calculat10ns to computethe CM land1ng p01nt Th1S TLI abort lS des1gned so that returnfl1ght t1me does not exceed 18 hours and abort ~V does not exceed7000 fps ThlS abort can be performed uSlng chart ~Vs and attltudesand the earths hor1zon serves as a suff1c1ent reference The maneushyver lS targeted to ach1eve the mldcorr1dor entry target Ilne andtlmed to result 1n a deslgnated recovery area

It 1S ObV10US for abort deC1S1ons early 1n the TLI + 90 m1nute t1meshyframe that a GampN SPS burn should be performed In order to keep theTLI abort procedures cons1stent and w1th emphasls on slmpl1c1ty theprocedures here reflect a SCS SPS abort burn to cover the full abortdec1s1on t1meframe

A m1dcourse correct1on for corr1dor control after a TLI abort may bedeS1red 1f the SPS burn d1d not meet expectat1ons The TLIabortprocedures 1n th1S sect10n adapt to the normal lunar return tlmel1neand procedures pr10r to the f1nal MCC

-52-

61 TLI PREPARATION PROCEDURES

GET = 150

CRO AOS(___)

CRO LOS( )(22142)

5100

Don Helmets amp Gloves

XLUNAR - INJECT (verify)EDS PWR - on (venfy)EMS FUNC - OFF (verlfy)EMS MODE - STBYEMS FUNC - IW SETVHF RNGEMS MODE - NORMALSet ~V indo to +15868 fpsEMS FUMC - ~V Test

SPS THRUST Lt - onoff (10 sec)~V lnd stops at -01 to -415

EMS MODE - STBYEMS FUMC - ~V SETVHF RNGSet ~VC

EMS FUNC---~~V=----

GDC ALIGNFDAI Select - liZcb SECS LOGIC (Z) - close (verify)cb SECS ARM (Z) - closeSECS LOGIC (Z) - on (up)MSFN Conflrm GO for PYRO ARM (If pass)SECS PYRO ARM (Z) - on (up)TRANS CONTROL PWR - ONROT CONTR PWR NORMAL (Z) - ACDC(verlfy)ROT CONTR PWR DIRECT (Z) - MNAMNBLV INnGPI - SIISIVB (venfy)LV GUID - IU (venfy)cb DIRECT ULLAGE (Z) - closedSet EVENT TIMER to 5100Begin MONITOR For TB6

CMP to Couch

TB 6 - SII SEP Lt on (TIG-9 mln 38 sec)KEY V83E

SET ORDEALFDAI Z ORB RATE at 180 0 0SII SEP Lt out (38 sec later)Start DET COUNTING UPSC CaNT - SCS (verify)MONITOR LV TANK PRESS

~P lt 36 psid (OXID gt FUEL)~P lt Z6 psid (FUEL gt OXID)

EMERGENCY CSMLV SEP UP TLM CM - BLOCK (verify)UP TLM IU - BLOCK (venfy)

-53-

+45degPY))0middot sec PY

lOK nmltHAlt25K nm

Two phas~ng mnvrs two SPS mnvrs to circular~ze at 150 nmearth orb~t

CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ssion 4K nmltHAltlOK nm CSM amp1M - Two phasing mnvrs two SPS mnvrs to circularize at 150 nm earth orb~t CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ss~on

CSM amp 1M - Two phas~ng mnvrs APS burn todepletion th~rd phasing mnvrSPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn tosem~sync orb~t

25K nmltHAlt40K nm CSM amp 1M - Two phasmg mnvrs APS burn to depletion third phas~ng mnvr SPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn to sem~sync orbit HA)40K nm DPS ava~l - DPS LOll circularize with SPS

DPS not ava~l - Lunar flyby or CSM only to lunar orbit (if reqd gtV lt4000 fps)

V37E 47E (check b~as) Record -=--rshy(Limit 98 fpsmm)

( 1fps)tVXYZN62EVIHDOTHPAD (fpsfpslnm)MONITOR VI ( ) at ECO

SCS TVC SERVO PWR 1 - ACIMNA2 - OFF

TAPE RCDR - CMD RESETHBREMS MODE - NORMAL

SIr SEP Lt - ONTLI Inhib~t S~gnals w~11 not be honored after 5942

SIVB ULLAGE BeginsSII SEP Lt - off (TIG - 18 sec)SIVB FUEL LEADSIVB ULLAGE d~scont~nues

LV ENG I Lt - onSIVB IGNITION ( GETI)LV ENG I Lt - off - -shyMONITOR THRUST amp ATTITUDEMONITOR LV TANK PRESSSIVE ECO (Lt on) (BEGIN TB7)

EMER SIVE CUTOFF AT 6 SEC PAST BURN TIME IF VI ATTAINEDTHC CCW ampNEUTRAL IN 1 SEC or SIISIVB sW - LV STAGEPremature Shutdown HAlt4K nm CSM amp 1M -

5700

58205836

F 16 835800

F 16 62

5838594259525955595900000002SUNRISE(___)

HAW AOS(__=_) KEY VERB (freeze d~splay)

SIVB ATT HOLD 20 sec amp BEGIN VENTINGSIVB NNVR TO ORB RT (HDS DN) (3middot sec)

Record VI -c---HDOT _

HPAD _

KEY RLSEF 16 62

F 16 83

HAW LOS(__=-)

KEYmiddotRLSE~VXYZ (lfps)

Record ~VX---_

~vy

WZ--

AVC---_

TAPE RCDR - off (ctr)EMS MODE - STBYEMS FUNC - OFFSECS PYRO ARM (2) - SAFE

PRO

BURN STATUS REPORT

____--~TIG

BT------VGX____-R

-----P----_Y

REMARKS

_____VI

______--HDOT______--H______---AVC______---FUEL_______OXID

_______UNBAL

F 3708=00 OOEGOS AOS CMP TO LEB

(-=-=-)

0000

0003

0005

0014

0100

-55-

62 TLI 10 MIN ABORTSECS LOGIC (2) - on (up)SECS PYRO ARM (2) - ARM

TRANS CONTR - CGH (4 sec) amp +XDET RESET (verlfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS GMD-ON

TRANS GONTR - neutral then +X for10 sec

SIVBGPI s~ - GPIExcesslve rates 6V THRUST A - NORMAL SPS THRUST - DIRECT When rates damped 6V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

TRANS CONTR +X - OFFV37E OOE

PITGH UP to LOGAL VERT (+X axlSto~ard the earth)

RATE - LOWBMAG MODE (3) - ATTIRATE 2EDS PHR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SEGS ARM (2) - opencb EDS (3) - open

TRANS CONTR -X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (180deg)P (199deg)Y (0deg)

RETRO UPDATEGETI _

JV _VG

Jtb ---GET 400K _

05G _GET DROGUE _

ENTRY P _R _

Y_--

0945

-56-

ALIGN HORIZ ON RET +1 MKGMBL CHECK (T11lle Pentattlng)MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conflnn)cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FUMC - JV SETVHF RNGSET JV from chartE~S FUMC - JVEMS fODE - NOIDlAL

lV THRUST A - NORMALV37E 47E (THRUST fONITOR)

F 16 83 lVXYZ (1 fps)

0950

1000

NOTE For aborts durlng 1st mln of TLIKEY V82E F 16 44 (HaHpTff)Burn untll Hp lt 19NM

TRANS CONTR +X

THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN JV reqdJV THRUST (2) - OFFReport cutoff

cb SPS P2 Y2- closeGfBL MTRS (4) - OFF (LMP Confinn)TRANS CONT PWR - OFFTVC SERVO PWR (2) - OFFMN BUS TIE (2) - OFFcb SPS P1amp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREIf est time to EIltOl5500 omlt fCC andenter the SUPERCIRC CKLIST as early as pos-slb1e Pg ~2~3~ __If est time to EI)Ol5500 anticlpate afCC Enter the ENTRY PREP CKLIST at step 9pg 18

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

-2tl C

l I W gt- ~-4

z laquo I I- 0 -6

l- I J u gt- ~-8

z w w -10

~_ONSANT

9O

VER

SHO

OT

BOU

ND

ARY

LIF

TV

EC

TOR

OR

IEN

TATI

ON

LIN

E

SH

ALL

OW

TAR

GE

TLI

NE

STE

EP

TAR

GE

TLI

NE 12

gU

ND

ERSH

OO

TBO

UN

DAR

Y

RE

EN

TRY

CO

RR

IDO

R

I ~ I

-12 24

26

28

30

32

34

RE

EN

TRY

VE

LOC

ITY

VE

1-F

TS

EC

Ch

art

1

36

3B

6-i

~

5CM

CC

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bull-1

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43

5IN

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LR

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73

8X

03

-i- rtREQUIRED PITCH GIMBAL ANG LETO OBTAIN HOR-IZON AT 317

DEGREES IN wiiiiDOW

260

z~I- ~ i5 24000

1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

-I

-1-

NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

I LU HD~-

LUHD

lt0 120UJ0

~

80 HOLD PRESENT TRIMgt LU HD013

~Y~HOIgtlt

TOP OF WINDOWa 40to

31 7 SCRIBEaaI

80 TTOM OF WINDOWi= 0

0--ltoa

-40t-z

~~~Uw w u lt0 -80

HOLO PRESENT TRIlJCl

LOHU0 lt0

J gt -120 HOLD 059 TRIMlt0 z

LDHUlt0 FIELD OF VI S10 NLDHU LIFT-DOWNHEADS -UPLUHD LIFT-UP HEADS-DOWN

~~H~-160 q - P63 LIMITI- NOrE-VALIO ONLY FO~t~--

LUNAR RETURN VELOCITY

plusmnl8020 244middot 8 12 16

TIME TO 400K FT ALTITUDE-MIN

4

P37

LONG

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1350

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340

344

348

352

356

364

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120

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320

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7

1000

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EMS

V-F

TSE

C90

0080

0070

0060

0050

0040

0030

0020

0010

000

II

II

II

II

S-IV

BBU

RNTI

ME

-M

INSE

Cll-

41)

120

200

241)

320

400

441)

520

TlI

-I0

MIN

ABOR

TlA

UNCH

-DE

C21

19

68

lAUN

CHA

ZIM

UTH

lllJ

72I ~ I

Z526

27~

~bull

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ERTI

ALVE

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ABOR

T(5

-IVB

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TaF

l-

FTlS

EC

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art

8

34l6

Xla

3

-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 37: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

-34-

PROMonitor VMAB

If lt25 vdc go to EMERGPOWER DOWN

34 F 37 OOEPCM BIT RATE - LOWATT DB - MAXEMS MODE - STBYEMS FUNC - OFF

Go To EARTH ORBIT ENTRY pg _--40-__

-36-

8 SPS THRUSTING PREPCYCLE CRYO FANSSPS GAGING - ACI (ver~fy)

PUG MODE - NORM (venfy)BMAG MODE (3) - RATE 2tv CG - CSMCMC MODE - FREEAUTO RCS SEL (16) - MNA or HNB

(hftoff conbg)SC CONT - CMCAUTO

9 MNVR TO PAD BURN ATTV62E

10 V49E

11 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLESPRO

12 F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) PRO(HAN) SC CONT - ses

MNVR to 14

06 18 AUTO MNVR TO FDAI RPY ANGLES13

14 F 50 18 REO TRIH TO FDAI RPY ANGLES(TRIM) Go to 12(BYPASS) ENTR

15 BORESIGHT STAR CHECK

16 V37E 40EOPT PWR - OFF

17 F 50 18 REQUEST MNVR TO FDAI RPY ANGLES (01deg)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CHCAUTOPRO to 18

(MANDAP) BMAG HODE (3) - RATE 2SC CONT - CMCHOLDMNVR to 19

(HANseS) se eONT - sesMNVR to 19

-35-

54 NORMAL DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL ~V

1 V37E 30E

2 F 06 33 GETI (hrm~nOlsec)

(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

3 F 06 81 ~VXYZ (LV)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

( lfps)

4 F 06 42 HAHP~V (1nmlfps)Record W

(ACCEPT) PRO -----(REJECT) Rese1ect P30 or P27 Load new pa~am

5 F 16 45 MTFIMGA (marksmln-secOldeg)MGA -00002 If ~ lMU not a1~gned

SET DETPRO

6

7

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY v1v - OFFCAB PRESS REL v1v (2) - NORMcb ELS (2) - close (verify)cb SECS ARM (2) - close (ver~fy)

cb SECS LOGIC (2) - close (verlfy)AUTO RCS SEL CM (12) - ~mA or MNB

(l~ftoff conf~g)

ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM AampB - off (ctr)

18

-37-

06 18 AUTO MNVR TO FDAI RPY ANGLES (01 0)

19 l 50 18 REOUEST TRIM MNVR TOALIGN SIC ROLLGDC ALIGN

FDAI RPY ANGLES(010

)

+54-00m(-06-00)

TIG-5mJn

5500m(-0500)

TVC CHECK amp PREPcb STAB CONT SYS (all) - closecb SPS (12) - closeATT DB - MINRATE - LOl~

LIMIT CYCLE - ONMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE 2ROT CONTR PWR DIRECT (2) - OFFSCS TVC (2) - RATE CMD

If SCS SCS TVC (2) - AUTO SC CONT - SCS ~

TVC GMBL DRIVE PampY - AUTOMN BUS TIE (2) - ONTVC SERVO PWR 1 - AC1MNA

2 - AC2MNBTRANS CONTR PWR - ONROT CONTR PWR NORMAL 2 - ACRHC 2 - ARMED

HORIZ CHK - HorJz on 12deg wJndmlmark (LJffiJt +3 0 PNGCS GONO GO)

If NO GO set tw 180 0 180deg0 0

Track horJz wJth 24deg wJndow markAt TIG-2 mJn Ahgn GDC

PRIMARY TVC CHECKGMBL MOT P1-Y1 -STARTON(LMP confJrm)

If SCS verJfy Thumbwheel TrJmTHC - CWVenfy NO MTVC

SEC TVC CHECKGHBL MOT P2-Y2 -STARTON(LMP confJrm)SET GPI TRIHVenfy MTVCTHC NEUTRALGPI returns to 00 (CMC) or trJm (SCS)ROT CONT Pl~ NORM 2 - ACDC

(TRIM) Go to step 17(BYPASS) BMAG MODE(3) - ATTIRATE2 (ver1fy)

ENTR

-38-

20 F SO 25 00204 GMBL TEST OPTION(ACCEPT) SC CONT - GMC (ver~fy)

PROMonitor GPI Response

0020-2000020-200Tr~m

TEST FAIL SC CONT - SCS SCS TVC (2) - AUTO

(REJECT) ENTR

21 06 40 TFIVG~VM (m~n-sec1fps)

PROG ALM - TIG s1~pped

V5N9E 01703

KEY RLSE To 21 ROT CONTR PWR DIRECT (2) - MNABSPS He v1vs (2) - AUTO (ver~fy)

LIMIT CYCLE - OFFFDAI SCALE - SOIScb SPS P2Y2 - open (for cr~t burn)

5800(-02 00)

5925(-0035)

59middot 30(-0030)

06 40

59XX(-OOXX)

AV THRUST A(B) - NORMALTHC - ARMEDRlIC (2) - ARMEDTAPE RCDR - GID RESETHBR

DSKY BLANKS

(AVE G ON)EMS MODE - NORMAL

TFIVG~VM (m~n-seclfps)

CHECK PIPA BIAS lt2fps for 5 sec

ULLAGE AS REQ

IF NO ULLAGE DIR ULLAGE PB - PUSH~

CONTROL ATT WRlIC MONITOR AVM (R3) COUNTING UP

5955(-0005)

F 99 40 ENG ON ENABLE REQUEST(AUTO IGN) PRO AT TFI gt0 sec(BYPASS IGN) ENTR to 24

22 0000 IGN

-39-

If SCS - THRUST ON PB - PUSH

06 40 TFCVG~VM (m~n-seclfpslfps)

~F 97 40 SPS Thrust fall ~

~(RESTART) PRO To IGN (RECYCLE) ENTR To TIG-05 sec

SPS THRUST LITE - ONMONITOR THRUSTING

Pc 95-105 pSlaEMS COUNTING DOWNSPS IN3 v1vs (4) - OPENSPS He v1vs tb (2) - graySPS FUELOXID PRESS - 175-195 pSlaPUGS - BALANCED

PROG ALARM V5N9E 01407 VG INCTHC - CW FLY MTVC

ECOEMER SPS CUTOFF J

AV THRUST (2) - OFF

23 F 16 40 TFC(STATIC)VG~VM (mln-seclfps)~V THRUST AB - OFF

SPS IN3 v1vs (4) - CLOSEDSPS He tb (2) - bp

cb SPS P2Y2 - closed (verlfy)TVC SERVO PHR - AC1MNA (venfy)TVC SERVO PWR 2 - OFF

PRO

24 F 16 85 VG XYZ(CM) CUps)NULL RESIDUALSRECORD ~V CTR amp RESIDUALS I1VCEMS FUNC - OFF VGXEMS MODE - STBY VGYBMAG MODE (3) - RATE 2ATT DB - MAX VGZTRANS CONT PHR - OFF

PRO

25 F 37 V82E

26 F 16 44 HAHPTFF (lnmm~n-sec)

R3-59B59 HP gt494 nmPRO

27 F 37 OOE

-40-

55 EARTH ORBIT ENTRY

1 Venfy CMSMR __

P_shyY_-

SEP ATT(180deg)

(0deg )

2

3

4

EMS INITIALIZATIONEMS FUNC - RNG SETSET RNG TO PAD DATA RNGEMS FUNC - VA SETSlew scroll to pad data VIOEMS FUNC - ENTRY

RSI ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on(up)GDC ALIGN PB - PUSH amp HOLDYAW tw - Pos1tion RSI thru 45deg amp

back to LIFl UPGDC ALIGN PB - RELEASEEMS ROLL - OFFAl1gn GDC to lMU

PWR REDUCT (Norm Deorb Only)HGA PWR - OFFFC PUMPS (3) - OFFVer1fy s1ngle suit compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - Lowcb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2)-openlOb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MAN

-41-

P61 - ENTRY PREP

5 V37E 61E05 09 01427 - ROLL REVERSED05 09 01426 - IMU UNSAT

6 F 06 61 IMPACT LAT LONG liDS UPDN (+-)(01 0

010

+00001)

PRO

PAD VALUESLATLON==G------liDS UP DN _

7 F 06 60 GMAXV400KGAMMA EIRecord

GMAXV400K----GAMMA EI _

PRO

8 F 06 63 RTOGO (1nm) PAD _VIa (fps) PADTFE (mln-sec) ----Compare wlth MSFN for PGNS GONO GONO COMM SET RTOGO amp VIO IN EMS amp

INITIALIZE(ACCEPT) PRO(RECALC) V32E to 8

-42-

P62 - CMSM SEP amp PRE-ENTRY MNVR

9 F 50 25 00041 REQUEST CMSM SEPSC CONT - SCSFREEYAW - 45deg out-of-plane (left for RCS

nght for SPS)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE2PRIM GLY to RAD - BYPASS (verlfy)SECS LOGIC (2) - on (up)MSFN conflrm GO for PYRO ARMSECS PYRO ARM - ARMMN BUS TIE (2) - ON (verlfy)CMSM SEF (2) - ONCSMLM FNl SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 pSlaCM RCS LOGIC - OFFSECS PYRO ARM - SAFEMonltor VMAB

If lt25vdc go to EMERG POWERDOWN Pg E6-1AUTO RCS SEL AlC ROLL (4) - OFFAUTO RCS SEL CM 2(6) - OFFAUTO RCS SEL CM 1(6) - MNA or MNBYAW back to 00

PITCH TO ENTRY ATTROLL 0deg (LIFT UP)PITCH - HORIZ on 317deg MARK (400K)YAW 00

ATT DB - MAXMAN ATT (PITCH) - ACCEL CMDEMS DATA - VerifyEMS FUNC - ENTRY (verlfy)EMS MODE - NORMALMAINTAIN HORIZ TRK

PRO (Act ENTRY DAP)

10 F 06 61 IMPACT LAT LONG HDSDN(010 010 -00001)

PRO

11 FOSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axlS beyond 45deg of Vel vector)

-43-

P63 - ENTRY INIT

12 06 64 GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PWR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRHORIZ CKP~tch error needle goes toward

zero approach~ng 05G t~me

MAN ATT (PITCH) - RATE CMDIf CMC ~s GO

BMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS FLY BETA If CMC NO GO ~

SC CONT - SCS~

FLY EMS RCS Deorh Roll HDS UPTRACK HORIZ w~th 29deg w~ndow mk

P64 - ENTRY POST 05G

13

05G t=elt+0___)

06 68

RTOGO AT 05G AGREES WITH EMS - venfyHORIZ CK05E Lt - on (EMS start)

No EMS start w~th~n 3 secsEMS MODE - BACKUP VHF RNG 05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds L~ft DN

NNVR L~ft DNEMS GONO GO

G-V Plot w~th~n llm~ts

Rng ctr dwn 60 + 7 durlng 10 sec per~od

Mon~tor G-meter forconvergence wlth pad data (Do)

(Vlt27K fps) Go To 17

-44-

P65 - ENTRY - UP CONT (Vgt27K fps)

14 F 16 69 BETA (01deg)DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT~

SC CONT - SCS FLY EMS

PRO

15 06 68 BElA VI HOOT (01deg fpsfps)(VltVL +500 fps amp RDOT Neg) Go To 17

p66 - ENTRY - BALLISTIC (DltDL)

16 06 22 DESIRED GMBL ANGLES RPY (01deg)Mon~tor hor~z +12deg of 317deg mark

P67 - ENTRY - FINAL PHASE (02G)

17 0666 BETACRSRNG ERRDNRNG ERR (Oldeglnmlnm)KEY VERBRecord DNRNG ERR _KEY RLSEL~m~t +100nm from PAD DRE

Mon~tor l~ft vector on RSI amp FDAIF 16 67 RTOGOLATLONG (Vre1=1000fps)

(lnm 010 01deg)SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOlfflMon~tor altimeter

Go To EARTHLANDING pg _I4L5__

-45-

56 EARTHLANDING

90K STEAM PRESS - PEGGED50K CABIN PRESS REL vIv (2) - BOOSTENTRY

SECS PYRO ARM (2) - ARM

40K(90K + 63s)

CM UNSTABLE RCS CMD - OFF ~ 40K APEX COVER JETT PG-PUSH DROGUE DEPLOY PG - PUSH (2 secafter apex cover Jett)

30K ELS LOGIC - ON (up)ELS - AUTO

24K RCS hsable (auto)(90K+92s) RCS CMD - OFF

Apex cover Jett (auto)APEX COVER JETT PB - PUSH

(WAIT 2 SECS)Drogue parachutes deployed (auto)

DROGUE DEPLOY PB - PUSH~

If Drogues FallELS - ~ ~Stablllze CM 5K MAIN DPLY PB - PUSHELS - AUTO

235K Cabln Pressure lncreaslng (Drogues + 50s)If not lncreaSlng by 17K CABIN PRESS REL vlv (RR) - DUMP

-46-

10K Maln parachutes deployedMAIN DEPLOY PB - PUSH (wlthln 1 sec)VHF ANT - RECYVHF AMA - SIMPLEXVHF BCN - ONCABIN PRESS REL v1v (2) - CLOSEDIRECT 02 vlv - OPENCM RCS LOGIC - on (up)CM PRPLNT - DUMP (burn audlb1e)Monltor CM ReS 1amp2 for He press decrease

NO BURN or PRESS DECREASE USE BOTH RHCs DO NOT FIRE PITCH JETS

CM PRPLNT-PURGE (to zero He press)CM RCS He DUMP PB - PUSH RHC (2) - 30 sees NO PITCH k

STRUT LOCKS (2) - UNLOCK

cb FLT amp PL BAT BUS ABampBAT C (3) - closecb FLT amp PLT MNA amp B (2) - opencb ECS RAD HTR OVLD (2) - opencb SPS PampY (4) - open

3K CABIN PRESS REL v1v (RH) - DUMP (after purgecompleted)

FLOOD Lts - POST LDGCM RCS PRPLNT (2) - OFFROT CONTR PWR DIRECT (2) - OFF

800 CAB PRESS RELF vlv - CLOSE (latch off)MN BUS TIE (2) - OFF

AFTER LANDINGcb MAIN REL PYRO (2) - closeMAIN RELEASE - on(up)

Go to POSTLANDING pg _47L-__

I

2

3

-47-

57 POSTLANDING

STABILIZATION VENTILATION COMMUNICATIONS

DIRECT 02 vlv - CLOSE

Stablllzation after landlngELS - AUTO (verlfy)cb MAIN REL PYRO (2) - close (venfy)MAIN RELEASE - on (up) (verlfy)S~CS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb BAT RLY BUS (2) - open

No contact w1th recovery forcesVHF AM AampB - off (ctr) ~

VHF AM Rev ONLY - A cb PL VENT - closecb FLOAT BAG (3) - closecb UPRIGHT SYS COMPRESS (2) - closeIf Stable II

FLOAT BAG(3)-FILL t1ll 2 m1n afterupr1ght then - OFF

VHF AM AlB amp BCN - OFF whlle lnvertedIf Stable I

After 10 M1n Coollng Per1odFLOAT BAG (3) - FILL 7 mln then OFF

Post Stab1lizat1on And Ventllat10nPL BCN LT - BCN LT LOWPL VENT vlv - UNLOCK (Pull)Remove PL VENT Exh CoverPL VENT - HIGH or LOWPL DYE MARKER - ON (swlmmer comm)Release foots traps and_restralntscb MNA BAT BUS A amp BAT C (2) - opencb MNB BAT BUS B amp BAT C (2) - opencb FLT amp PL BAT C - opencb PYRO A SEQ A - opencb PYRO B SEQ B - open

EACH HR - CHECK DC VOLTSgt 275 V If Notmiddot cb FLT amp PL-BAT BUS AampB (2) -open cb FLT amp PL BAT C (1) - open GO TO LOW POWER CHECKLIST

Unstow and lnstall PLV DISTRIB DUCTDeploy grappllng hook and 11ne 1f req

4

-48-

Post Landing Communlcatl0nsVHF ANT-RECY (venfy)VHF BCN - ON (verlfy)

If no contact ~lth recovery forcesperform VHF BEACON Check

MONITOR VHF BEACON transmlSSlonnth VHF AM B Rcvr andor Su)vlval

TransceiverkVHF Beacon not operatlng ~connect Surv~val TranscelVer to antcable behlnd VHF ant access pnland place radio ln BCN mode

LOW POHER CHECKLISTVHF BCN - OFFVHF AM (3) - RCVFLOOD Lts - OFFVHF AM AampB - off (ctr)VHF AM RCV ONLY - A (venfy)COUCH LIGHTS - OFFPOSTLANDING VENT SYS mlnlmlze useSURV RADIO - plug mto VHF BCN ANT cableconn behind VHF ant acess pnl amp turn radloon l-n BCN mode

EGRESS PROCEDURES

CMPCDRLMPCDR

CMPCDRCMP

LMPLl1PCDR

STABLE IDlsconnect Umblll-calsNeck darn onCenter couch - 270 0 positionArmrests stowedConnect raft to SIC l-f desl-red wlth

green lanyardConnect raft ~hl-te lanyards to SUltS amp

lnflate water wlngs when eXltl-ngHATCH PISTON PRESS vlv - PRESS (Outbd)Slde Hatch openedPL VENT - OFFcb Pnl 250 (all) - openEgress with 11feraftPut hardware klt outEgress

or CDIPALL

CMF

CDRCMF

CDR

LMF

CMFCMP LMFCMP

UlP

CDR

-49-

STABLE IIcb CREW STA AUDIO (3) - openD~sconnect umb~1~ca1s

Release foots trapsRelease restra~nt harnessCouch seat pans (3) - 170 0 pos1t10nArm rests stowedSurv1va1 k~ts removed from stowageConnect life raft ma~n1~ne to CDR or SicConnect f~rst wh~te lanyard from

11fe raft to suitConnect th~rd wh~te lanyard from

l~fe raft to SU1tConnect rucksacks together to yellow

lanyard on raft bagPRESSURE EQUALIZATION vlv - OPENRemove and stow fwd hatchEX1t feet f1rst w1th rucksacks when clear

of siC 1nflate water w1ngs and raftExit feet f1rst when clear of SiC

1nflate water w1ngsEX1t feet f1rst when clear of sic

1nflate water w1ngs

-50-

60 TLI ABORTS

TLI Aborts are conta~ned ~n the ESD s~nce the bulk of the funct~ons

concern entry preparat20ns and performance Th~s allows a s2nglesource of procedures for procedure rev2ew val~dat~on checkout andtra~n~ng These procedures ~ncorporate TLI preparat20ns as found ~n

reference 6 w~th the TLI Abort Procedures and these t~e 2nto normallunar return Entry Procedures found ~n sect20n 5 The guidel~nes

for th~s cont2ngency are spec2f2ed 2n reference 7

In2t2al preparat~ons for TLI pos2t20n the necessary system sW2tches2n add~t~on to perform~ng an EMS ~V test and a GDC al~gnment Afterthe DET ~s set for mon2tor2ng TB6 the CMP ~ncreases the 12ght levelof the LEB DSKY to max~mum and returns to the h2s couch Th2s 2Sdone so that the LEB DSKY can be observed ~n the event sunl~ght orreflect20ns wash out the ma2n d2splay panel DSKY dur2ng cr2t2calmaneuvers The crew then straps ~n and prepares for mon2tor~ng TB6as 2nd2cated by the SII SEP L~te The t2mes se~uence of procedures2S keyed on th~s d~splay and ~ncludes the DET START funct~on andSIVB IGNITION Dur2ng the burn the crew mon2tors the FDAIs foratt~tude excurs20ns and abnormal rates report~ng status checks toM~ss2on Control at d2screet t~mes dur2ng the maneuver Upon SIVBSHUTDOWN the eMP records the DSKY d~splayed performance parametersand awa2ts ground conf2rmat~on

The rat~onal for TLI aborts ~s descr~bed 2n reference 7 A summar2shyzat20n 2S extracted to prov2de background and gu2de12nes 2n th2sdocument The abort procedures cover aborts 10 m2nutes after conshyt2ngent SIVE shutdown and aborts 90 m2nutes after normal SIVE shutshydown t2me

The 10 m~nute TLI abort ~s des2gned to be used dur~ng TLI ~n theevent a spacecraft problem develops Wh2Ch can result 2n catastrophe2f ~mmed~ate act~on 2S not taken If the s~tuat20n perm~ts the crewshould always allow the SIVB to complete TLI at wh~ch t~me the groundand crew can perform a malfunct~on analys~s to determ~ne ~f an abort~s adv~sable If a fa~lure occurs that necess2tates the shutdown ofthe SIVB and the ~u~ck return of the crew to earth th~s abort ~s

des~gned to be as ~nsens~t~ve to execut~on errors as poss~ble andst21l be targeted to m2dcorr2dor The burn att~tude w~th the f~ed

hor~zon reference ~s a constant value for any shutdown t~me Theburn durat~on 2S a funct20n of shutdown t2me and 2S ava21able fromcrew charts S~nce the pr~mary purpose of th~s abort ~s to returnto earth as qU2ckly as poss2ble there are no restr2ct20ns as toland~ng locat~on However ~f the t~me to EI is greater than abouttwo hours a midcourse correct20n should be ant~c~pated

The 90 m2nute TLI abort 2S to be used 2f a cr2t2cal subsystem malshyfunct~on ~s determ2ned and the dec2s~on to abort ~s made after the

-51-

TLI cutoff and before TLI cutoff plus approxlmately 80 m1nutesTh1S allows suff1c1ent separatlon and procedural t1me to set upfor the SPS deorb1t burn performed at about TLI + 90 Note thatgenerally the deorb1t burns w1ll be performed a fe11 m1nutes beforeTLI + 90 accord1ng to crew charts shown In reference 8 The no-comm except10n requ1res that 90 m1nutes be the 1nput t1me of 19n1shytlon for P-37 (onboard return-to-earth abort program) so that onshyboard calculatlons can correspond w1th ground calculat10ns to computethe CM land1ng p01nt Th1S TLI abort lS des1gned so that returnfl1ght t1me does not exceed 18 hours and abort ~V does not exceed7000 fps ThlS abort can be performed uSlng chart ~Vs and attltudesand the earths hor1zon serves as a suff1c1ent reference The maneushyver lS targeted to ach1eve the mldcorr1dor entry target Ilne andtlmed to result 1n a deslgnated recovery area

It 1S ObV10US for abort deC1S1ons early 1n the TLI + 90 m1nute t1meshyframe that a GampN SPS burn should be performed In order to keep theTLI abort procedures cons1stent and w1th emphasls on slmpl1c1ty theprocedures here reflect a SCS SPS abort burn to cover the full abortdec1s1on t1meframe

A m1dcourse correct1on for corr1dor control after a TLI abort may bedeS1red 1f the SPS burn d1d not meet expectat1ons The TLIabortprocedures 1n th1S sect10n adapt to the normal lunar return tlmel1neand procedures pr10r to the f1nal MCC

-52-

61 TLI PREPARATION PROCEDURES

GET = 150

CRO AOS(___)

CRO LOS( )(22142)

5100

Don Helmets amp Gloves

XLUNAR - INJECT (verify)EDS PWR - on (venfy)EMS FUNC - OFF (verlfy)EMS MODE - STBYEMS FUNC - IW SETVHF RNGEMS MODE - NORMALSet ~V indo to +15868 fpsEMS FUMC - ~V Test

SPS THRUST Lt - onoff (10 sec)~V lnd stops at -01 to -415

EMS MODE - STBYEMS FUMC - ~V SETVHF RNGSet ~VC

EMS FUNC---~~V=----

GDC ALIGNFDAI Select - liZcb SECS LOGIC (Z) - close (verify)cb SECS ARM (Z) - closeSECS LOGIC (Z) - on (up)MSFN Conflrm GO for PYRO ARM (If pass)SECS PYRO ARM (Z) - on (up)TRANS CONTROL PWR - ONROT CONTR PWR NORMAL (Z) - ACDC(verlfy)ROT CONTR PWR DIRECT (Z) - MNAMNBLV INnGPI - SIISIVB (venfy)LV GUID - IU (venfy)cb DIRECT ULLAGE (Z) - closedSet EVENT TIMER to 5100Begin MONITOR For TB6

CMP to Couch

TB 6 - SII SEP Lt on (TIG-9 mln 38 sec)KEY V83E

SET ORDEALFDAI Z ORB RATE at 180 0 0SII SEP Lt out (38 sec later)Start DET COUNTING UPSC CaNT - SCS (verify)MONITOR LV TANK PRESS

~P lt 36 psid (OXID gt FUEL)~P lt Z6 psid (FUEL gt OXID)

EMERGENCY CSMLV SEP UP TLM CM - BLOCK (verify)UP TLM IU - BLOCK (venfy)

-53-

+45degPY))0middot sec PY

lOK nmltHAlt25K nm

Two phas~ng mnvrs two SPS mnvrs to circular~ze at 150 nmearth orb~t

CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ssion 4K nmltHAltlOK nm CSM amp1M - Two phasing mnvrs two SPS mnvrs to circularize at 150 nm earth orb~t CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ss~on

CSM amp 1M - Two phas~ng mnvrs APS burn todepletion th~rd phasing mnvrSPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn tosem~sync orb~t

25K nmltHAlt40K nm CSM amp 1M - Two phasmg mnvrs APS burn to depletion third phas~ng mnvr SPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn to sem~sync orbit HA)40K nm DPS ava~l - DPS LOll circularize with SPS

DPS not ava~l - Lunar flyby or CSM only to lunar orbit (if reqd gtV lt4000 fps)

V37E 47E (check b~as) Record -=--rshy(Limit 98 fpsmm)

( 1fps)tVXYZN62EVIHDOTHPAD (fpsfpslnm)MONITOR VI ( ) at ECO

SCS TVC SERVO PWR 1 - ACIMNA2 - OFF

TAPE RCDR - CMD RESETHBREMS MODE - NORMAL

SIr SEP Lt - ONTLI Inhib~t S~gnals w~11 not be honored after 5942

SIVB ULLAGE BeginsSII SEP Lt - off (TIG - 18 sec)SIVB FUEL LEADSIVB ULLAGE d~scont~nues

LV ENG I Lt - onSIVB IGNITION ( GETI)LV ENG I Lt - off - -shyMONITOR THRUST amp ATTITUDEMONITOR LV TANK PRESSSIVE ECO (Lt on) (BEGIN TB7)

EMER SIVE CUTOFF AT 6 SEC PAST BURN TIME IF VI ATTAINEDTHC CCW ampNEUTRAL IN 1 SEC or SIISIVB sW - LV STAGEPremature Shutdown HAlt4K nm CSM amp 1M -

5700

58205836

F 16 835800

F 16 62

5838594259525955595900000002SUNRISE(___)

HAW AOS(__=_) KEY VERB (freeze d~splay)

SIVB ATT HOLD 20 sec amp BEGIN VENTINGSIVB NNVR TO ORB RT (HDS DN) (3middot sec)

Record VI -c---HDOT _

HPAD _

KEY RLSEF 16 62

F 16 83

HAW LOS(__=-)

KEYmiddotRLSE~VXYZ (lfps)

Record ~VX---_

~vy

WZ--

AVC---_

TAPE RCDR - off (ctr)EMS MODE - STBYEMS FUNC - OFFSECS PYRO ARM (2) - SAFE

PRO

BURN STATUS REPORT

____--~TIG

BT------VGX____-R

-----P----_Y

REMARKS

_____VI

______--HDOT______--H______---AVC______---FUEL_______OXID

_______UNBAL

F 3708=00 OOEGOS AOS CMP TO LEB

(-=-=-)

0000

0003

0005

0014

0100

-55-

62 TLI 10 MIN ABORTSECS LOGIC (2) - on (up)SECS PYRO ARM (2) - ARM

TRANS CONTR - CGH (4 sec) amp +XDET RESET (verlfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS GMD-ON

TRANS GONTR - neutral then +X for10 sec

SIVBGPI s~ - GPIExcesslve rates 6V THRUST A - NORMAL SPS THRUST - DIRECT When rates damped 6V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

TRANS CONTR +X - OFFV37E OOE

PITGH UP to LOGAL VERT (+X axlSto~ard the earth)

RATE - LOWBMAG MODE (3) - ATTIRATE 2EDS PHR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SEGS ARM (2) - opencb EDS (3) - open

TRANS CONTR -X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (180deg)P (199deg)Y (0deg)

RETRO UPDATEGETI _

JV _VG

Jtb ---GET 400K _

05G _GET DROGUE _

ENTRY P _R _

Y_--

0945

-56-

ALIGN HORIZ ON RET +1 MKGMBL CHECK (T11lle Pentattlng)MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conflnn)cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FUMC - JV SETVHF RNGSET JV from chartE~S FUMC - JVEMS fODE - NOIDlAL

lV THRUST A - NORMALV37E 47E (THRUST fONITOR)

F 16 83 lVXYZ (1 fps)

0950

1000

NOTE For aborts durlng 1st mln of TLIKEY V82E F 16 44 (HaHpTff)Burn untll Hp lt 19NM

TRANS CONTR +X

THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN JV reqdJV THRUST (2) - OFFReport cutoff

cb SPS P2 Y2- closeGfBL MTRS (4) - OFF (LMP Confinn)TRANS CONT PWR - OFFTVC SERVO PWR (2) - OFFMN BUS TIE (2) - OFFcb SPS P1amp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREIf est time to EIltOl5500 omlt fCC andenter the SUPERCIRC CKLIST as early as pos-slb1e Pg ~2~3~ __If est time to EI)Ol5500 anticlpate afCC Enter the ENTRY PREP CKLIST at step 9pg 18

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

-2tl C

l I W gt- ~-4

z laquo I I- 0 -6

l- I J u gt- ~-8

z w w -10

~_ONSANT

9O

VER

SHO

OT

BOU

ND

ARY

LIF

TV

EC

TOR

OR

IEN

TATI

ON

LIN

E

SH

ALL

OW

TAR

GE

TLI

NE

STE

EP

TAR

GE

TLI

NE 12

gU

ND

ERSH

OO

TBO

UN

DAR

Y

RE

EN

TRY

CO

RR

IDO

R

I ~ I

-12 24

26

28

30

32

34

RE

EN

TRY

VE

LOC

ITY

VE

1-F

TS

EC

Ch

art

1

36

3B

6-i

~

5CM

CC

ON

ST

NT

DR

VI z gt

~

I4

0 Cl W

I

gtamp

J+

-I

-

J Cl z

2U

l z 0_bull

bull-1

+-

u ubullbull

~r

U

)

2829

JOn

J23

33

43

5IN

ER

TIA

LR

EE

NTR

YV

ELO

CIT

YA

T4

00

00

0fl

VE

I-F

TS

EC

Ch

art

2

J63

73

8X

03

-i- rtREQUIRED PITCH GIMBAL ANG LETO OBTAIN HOR-IZON AT 317

DEGREES IN wiiiiDOW

260

z~I- ~ i5 24000

1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

-I

-1-

NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

I LU HD~-

LUHD

lt0 120UJ0

~

80 HOLD PRESENT TRIMgt LU HD013

~Y~HOIgtlt

TOP OF WINDOWa 40to

31 7 SCRIBEaaI

80 TTOM OF WINDOWi= 0

0--ltoa

-40t-z

~~~Uw w u lt0 -80

HOLO PRESENT TRIlJCl

LOHU0 lt0

J gt -120 HOLD 059 TRIMlt0 z

LDHUlt0 FIELD OF VI S10 NLDHU LIFT-DOWNHEADS -UPLUHD LIFT-UP HEADS-DOWN

~~H~-160 q - P63 LIMITI- NOrE-VALIO ONLY FO~t~--

LUNAR RETURN VELOCITY

plusmnl8020 244middot 8 12 16

TIME TO 400K FT ALTITUDE-MIN

4

P37

LONG

ITUD

ECO

RREC

TION

TOOB

TAIN

1350

NM

ENTR

YRA

NGE

Ugt

UJ

cgt

3z 0 I- u U

J0

0

0

2I

U~

UJ

cgt

I

gtI- U

gt z 0 J ltJ

1 -0

340

344

348

352

356

364

368

x10

3

CMC

INER

TIAL

VELO

CITY

AT40

0KAL

TITU

DE-

FTS

EC

Ch

art

5

I l I

o

20 100 -40

-10

-50

30

-20

--

+

-BB

A+

lrBB

A

=----

-----

t~I

AB

SA_

-04

0A

AV

Z=

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D_

+

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plusmniff

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60--

--1-

-0

2030

NOTE

40

NO

MIN

AL

RET

RB

=22

MIN

30

-40

-50

---------O

VE

RB

UR

N---------I------U

ND

ER

BU

RN

------I

~30

-20

-tD

010

20

AA

VX

FTS

EC

-60

Ch

art

6

1000

0 90

00 70

00 60

00 i50

00 iMl

OO ilOO

O i20

00 10

00 o

040

120

200

EMS

6V-

FTS

EC

240

320

400

440

520

S-IV

BeO

RN-

NSE

C

105

0

I 1- I

I

LAUN

CHAZ

IMUT

H

72r

rr

ml

lJ8

ilLIG

gtEA

ilt1t

1I0R

IZON

+rmr)lfl~

GIM

BAL

ANGL

E

ROLL

=IS

OPI

TCH

=199

YAW

0

TLI

-10

MIN

ABO

RTLA

UNCH

DEC

21

1968

400050

z =gt co23

0on 3

~7 X ampJ V

gt ~ 6

2627

~B

~n

_n

INER

TIAL

VELO

CITY

ATAB

ORT

IS-IV

BC

UTO

FF)middot

FTIS

EC34

3536

Xllf

Ch

art

7

7

1000

0i

0-00

EMS

V-F

TSE

C90

0080

0070

0060

0050

0040

0030

0020

0010

000

II

II

II

II

S-IV

BBU

RNTI

ME

-M

INSE

Cll-

41)

120

200

241)

320

400

441)

520

TlI

-I0

MIN

ABOR

TlA

UNCH

-DE

C21

19

68

lAUN

CHA

ZIM

UTH

lllJ

72I ~ I

Z526

27~

~bull

DX

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ERTI

ALVE

LOCI

TYAT

ABOR

T(5

-IVB

CU

TaF

l-

FTlS

EC

Ch

art

8

34l6

Xla

3

-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 38: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

-36-

8 SPS THRUSTING PREPCYCLE CRYO FANSSPS GAGING - ACI (ver~fy)

PUG MODE - NORM (venfy)BMAG MODE (3) - RATE 2tv CG - CSMCMC MODE - FREEAUTO RCS SEL (16) - MNA or HNB

(hftoff conbg)SC CONT - CMCAUTO

9 MNVR TO PAD BURN ATTV62E

10 V49E

11 F 06 22 DESIRED FINAL GMBL ANGLESLOAD MNVR PAD GMBL ANGLESPRO

12 F 50 18 REQ MNVR TO FDAI RPY ANGLES(AUTO) PRO(HAN) SC CONT - ses

MNVR to 14

06 18 AUTO MNVR TO FDAI RPY ANGLES13

14 F 50 18 REO TRIH TO FDAI RPY ANGLES(TRIM) Go to 12(BYPASS) ENTR

15 BORESIGHT STAR CHECK

16 V37E 40EOPT PWR - OFF

17 F 50 18 REQUEST MNVR TO FDAI RPY ANGLES (01deg)(AUTO) BMAG MODE (3) - RATE 2

SC CONT - CHCAUTOPRO to 18

(MANDAP) BMAG HODE (3) - RATE 2SC CONT - CMCHOLDMNVR to 19

(HANseS) se eONT - sesMNVR to 19

-35-

54 NORMAL DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL ~V

1 V37E 30E

2 F 06 33 GETI (hrm~nOlsec)

(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

3 F 06 81 ~VXYZ (LV)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

( lfps)

4 F 06 42 HAHP~V (1nmlfps)Record W

(ACCEPT) PRO -----(REJECT) Rese1ect P30 or P27 Load new pa~am

5 F 16 45 MTFIMGA (marksmln-secOldeg)MGA -00002 If ~ lMU not a1~gned

SET DETPRO

6

7

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY v1v - OFFCAB PRESS REL v1v (2) - NORMcb ELS (2) - close (verify)cb SECS ARM (2) - close (ver~fy)

cb SECS LOGIC (2) - close (verlfy)AUTO RCS SEL CM (12) - ~mA or MNB

(l~ftoff conf~g)

ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM AampB - off (ctr)

18

-37-

06 18 AUTO MNVR TO FDAI RPY ANGLES (01 0)

19 l 50 18 REOUEST TRIM MNVR TOALIGN SIC ROLLGDC ALIGN

FDAI RPY ANGLES(010

)

+54-00m(-06-00)

TIG-5mJn

5500m(-0500)

TVC CHECK amp PREPcb STAB CONT SYS (all) - closecb SPS (12) - closeATT DB - MINRATE - LOl~

LIMIT CYCLE - ONMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE 2ROT CONTR PWR DIRECT (2) - OFFSCS TVC (2) - RATE CMD

If SCS SCS TVC (2) - AUTO SC CONT - SCS ~

TVC GMBL DRIVE PampY - AUTOMN BUS TIE (2) - ONTVC SERVO PWR 1 - AC1MNA

2 - AC2MNBTRANS CONTR PWR - ONROT CONTR PWR NORMAL 2 - ACRHC 2 - ARMED

HORIZ CHK - HorJz on 12deg wJndmlmark (LJffiJt +3 0 PNGCS GONO GO)

If NO GO set tw 180 0 180deg0 0

Track horJz wJth 24deg wJndow markAt TIG-2 mJn Ahgn GDC

PRIMARY TVC CHECKGMBL MOT P1-Y1 -STARTON(LMP confJrm)

If SCS verJfy Thumbwheel TrJmTHC - CWVenfy NO MTVC

SEC TVC CHECKGHBL MOT P2-Y2 -STARTON(LMP confJrm)SET GPI TRIHVenfy MTVCTHC NEUTRALGPI returns to 00 (CMC) or trJm (SCS)ROT CONT Pl~ NORM 2 - ACDC

(TRIM) Go to step 17(BYPASS) BMAG MODE(3) - ATTIRATE2 (ver1fy)

ENTR

-38-

20 F SO 25 00204 GMBL TEST OPTION(ACCEPT) SC CONT - GMC (ver~fy)

PROMonitor GPI Response

0020-2000020-200Tr~m

TEST FAIL SC CONT - SCS SCS TVC (2) - AUTO

(REJECT) ENTR

21 06 40 TFIVG~VM (m~n-sec1fps)

PROG ALM - TIG s1~pped

V5N9E 01703

KEY RLSE To 21 ROT CONTR PWR DIRECT (2) - MNABSPS He v1vs (2) - AUTO (ver~fy)

LIMIT CYCLE - OFFFDAI SCALE - SOIScb SPS P2Y2 - open (for cr~t burn)

5800(-02 00)

5925(-0035)

59middot 30(-0030)

06 40

59XX(-OOXX)

AV THRUST A(B) - NORMALTHC - ARMEDRlIC (2) - ARMEDTAPE RCDR - GID RESETHBR

DSKY BLANKS

(AVE G ON)EMS MODE - NORMAL

TFIVG~VM (m~n-seclfps)

CHECK PIPA BIAS lt2fps for 5 sec

ULLAGE AS REQ

IF NO ULLAGE DIR ULLAGE PB - PUSH~

CONTROL ATT WRlIC MONITOR AVM (R3) COUNTING UP

5955(-0005)

F 99 40 ENG ON ENABLE REQUEST(AUTO IGN) PRO AT TFI gt0 sec(BYPASS IGN) ENTR to 24

22 0000 IGN

-39-

If SCS - THRUST ON PB - PUSH

06 40 TFCVG~VM (m~n-seclfpslfps)

~F 97 40 SPS Thrust fall ~

~(RESTART) PRO To IGN (RECYCLE) ENTR To TIG-05 sec

SPS THRUST LITE - ONMONITOR THRUSTING

Pc 95-105 pSlaEMS COUNTING DOWNSPS IN3 v1vs (4) - OPENSPS He v1vs tb (2) - graySPS FUELOXID PRESS - 175-195 pSlaPUGS - BALANCED

PROG ALARM V5N9E 01407 VG INCTHC - CW FLY MTVC

ECOEMER SPS CUTOFF J

AV THRUST (2) - OFF

23 F 16 40 TFC(STATIC)VG~VM (mln-seclfps)~V THRUST AB - OFF

SPS IN3 v1vs (4) - CLOSEDSPS He tb (2) - bp

cb SPS P2Y2 - closed (verlfy)TVC SERVO PHR - AC1MNA (venfy)TVC SERVO PWR 2 - OFF

PRO

24 F 16 85 VG XYZ(CM) CUps)NULL RESIDUALSRECORD ~V CTR amp RESIDUALS I1VCEMS FUNC - OFF VGXEMS MODE - STBY VGYBMAG MODE (3) - RATE 2ATT DB - MAX VGZTRANS CONT PHR - OFF

PRO

25 F 37 V82E

26 F 16 44 HAHPTFF (lnmm~n-sec)

R3-59B59 HP gt494 nmPRO

27 F 37 OOE

-40-

55 EARTH ORBIT ENTRY

1 Venfy CMSMR __

P_shyY_-

SEP ATT(180deg)

(0deg )

2

3

4

EMS INITIALIZATIONEMS FUNC - RNG SETSET RNG TO PAD DATA RNGEMS FUNC - VA SETSlew scroll to pad data VIOEMS FUNC - ENTRY

RSI ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on(up)GDC ALIGN PB - PUSH amp HOLDYAW tw - Pos1tion RSI thru 45deg amp

back to LIFl UPGDC ALIGN PB - RELEASEEMS ROLL - OFFAl1gn GDC to lMU

PWR REDUCT (Norm Deorb Only)HGA PWR - OFFFC PUMPS (3) - OFFVer1fy s1ngle suit compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - Lowcb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2)-openlOb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MAN

-41-

P61 - ENTRY PREP

5 V37E 61E05 09 01427 - ROLL REVERSED05 09 01426 - IMU UNSAT

6 F 06 61 IMPACT LAT LONG liDS UPDN (+-)(01 0

010

+00001)

PRO

PAD VALUESLATLON==G------liDS UP DN _

7 F 06 60 GMAXV400KGAMMA EIRecord

GMAXV400K----GAMMA EI _

PRO

8 F 06 63 RTOGO (1nm) PAD _VIa (fps) PADTFE (mln-sec) ----Compare wlth MSFN for PGNS GONO GONO COMM SET RTOGO amp VIO IN EMS amp

INITIALIZE(ACCEPT) PRO(RECALC) V32E to 8

-42-

P62 - CMSM SEP amp PRE-ENTRY MNVR

9 F 50 25 00041 REQUEST CMSM SEPSC CONT - SCSFREEYAW - 45deg out-of-plane (left for RCS

nght for SPS)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE2PRIM GLY to RAD - BYPASS (verlfy)SECS LOGIC (2) - on (up)MSFN conflrm GO for PYRO ARMSECS PYRO ARM - ARMMN BUS TIE (2) - ON (verlfy)CMSM SEF (2) - ONCSMLM FNl SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 pSlaCM RCS LOGIC - OFFSECS PYRO ARM - SAFEMonltor VMAB

If lt25vdc go to EMERG POWERDOWN Pg E6-1AUTO RCS SEL AlC ROLL (4) - OFFAUTO RCS SEL CM 2(6) - OFFAUTO RCS SEL CM 1(6) - MNA or MNBYAW back to 00

PITCH TO ENTRY ATTROLL 0deg (LIFT UP)PITCH - HORIZ on 317deg MARK (400K)YAW 00

ATT DB - MAXMAN ATT (PITCH) - ACCEL CMDEMS DATA - VerifyEMS FUNC - ENTRY (verlfy)EMS MODE - NORMALMAINTAIN HORIZ TRK

PRO (Act ENTRY DAP)

10 F 06 61 IMPACT LAT LONG HDSDN(010 010 -00001)

PRO

11 FOSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axlS beyond 45deg of Vel vector)

-43-

P63 - ENTRY INIT

12 06 64 GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PWR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRHORIZ CKP~tch error needle goes toward

zero approach~ng 05G t~me

MAN ATT (PITCH) - RATE CMDIf CMC ~s GO

BMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS FLY BETA If CMC NO GO ~

SC CONT - SCS~

FLY EMS RCS Deorh Roll HDS UPTRACK HORIZ w~th 29deg w~ndow mk

P64 - ENTRY POST 05G

13

05G t=elt+0___)

06 68

RTOGO AT 05G AGREES WITH EMS - venfyHORIZ CK05E Lt - on (EMS start)

No EMS start w~th~n 3 secsEMS MODE - BACKUP VHF RNG 05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds L~ft DN

NNVR L~ft DNEMS GONO GO

G-V Plot w~th~n llm~ts

Rng ctr dwn 60 + 7 durlng 10 sec per~od

Mon~tor G-meter forconvergence wlth pad data (Do)

(Vlt27K fps) Go To 17

-44-

P65 - ENTRY - UP CONT (Vgt27K fps)

14 F 16 69 BETA (01deg)DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT~

SC CONT - SCS FLY EMS

PRO

15 06 68 BElA VI HOOT (01deg fpsfps)(VltVL +500 fps amp RDOT Neg) Go To 17

p66 - ENTRY - BALLISTIC (DltDL)

16 06 22 DESIRED GMBL ANGLES RPY (01deg)Mon~tor hor~z +12deg of 317deg mark

P67 - ENTRY - FINAL PHASE (02G)

17 0666 BETACRSRNG ERRDNRNG ERR (Oldeglnmlnm)KEY VERBRecord DNRNG ERR _KEY RLSEL~m~t +100nm from PAD DRE

Mon~tor l~ft vector on RSI amp FDAIF 16 67 RTOGOLATLONG (Vre1=1000fps)

(lnm 010 01deg)SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOlfflMon~tor altimeter

Go To EARTHLANDING pg _I4L5__

-45-

56 EARTHLANDING

90K STEAM PRESS - PEGGED50K CABIN PRESS REL vIv (2) - BOOSTENTRY

SECS PYRO ARM (2) - ARM

40K(90K + 63s)

CM UNSTABLE RCS CMD - OFF ~ 40K APEX COVER JETT PG-PUSH DROGUE DEPLOY PG - PUSH (2 secafter apex cover Jett)

30K ELS LOGIC - ON (up)ELS - AUTO

24K RCS hsable (auto)(90K+92s) RCS CMD - OFF

Apex cover Jett (auto)APEX COVER JETT PB - PUSH

(WAIT 2 SECS)Drogue parachutes deployed (auto)

DROGUE DEPLOY PB - PUSH~

If Drogues FallELS - ~ ~Stablllze CM 5K MAIN DPLY PB - PUSHELS - AUTO

235K Cabln Pressure lncreaslng (Drogues + 50s)If not lncreaSlng by 17K CABIN PRESS REL vlv (RR) - DUMP

-46-

10K Maln parachutes deployedMAIN DEPLOY PB - PUSH (wlthln 1 sec)VHF ANT - RECYVHF AMA - SIMPLEXVHF BCN - ONCABIN PRESS REL v1v (2) - CLOSEDIRECT 02 vlv - OPENCM RCS LOGIC - on (up)CM PRPLNT - DUMP (burn audlb1e)Monltor CM ReS 1amp2 for He press decrease

NO BURN or PRESS DECREASE USE BOTH RHCs DO NOT FIRE PITCH JETS

CM PRPLNT-PURGE (to zero He press)CM RCS He DUMP PB - PUSH RHC (2) - 30 sees NO PITCH k

STRUT LOCKS (2) - UNLOCK

cb FLT amp PL BAT BUS ABampBAT C (3) - closecb FLT amp PLT MNA amp B (2) - opencb ECS RAD HTR OVLD (2) - opencb SPS PampY (4) - open

3K CABIN PRESS REL v1v (RH) - DUMP (after purgecompleted)

FLOOD Lts - POST LDGCM RCS PRPLNT (2) - OFFROT CONTR PWR DIRECT (2) - OFF

800 CAB PRESS RELF vlv - CLOSE (latch off)MN BUS TIE (2) - OFF

AFTER LANDINGcb MAIN REL PYRO (2) - closeMAIN RELEASE - on(up)

Go to POSTLANDING pg _47L-__

I

2

3

-47-

57 POSTLANDING

STABILIZATION VENTILATION COMMUNICATIONS

DIRECT 02 vlv - CLOSE

Stablllzation after landlngELS - AUTO (verlfy)cb MAIN REL PYRO (2) - close (venfy)MAIN RELEASE - on (up) (verlfy)S~CS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb BAT RLY BUS (2) - open

No contact w1th recovery forcesVHF AM AampB - off (ctr) ~

VHF AM Rev ONLY - A cb PL VENT - closecb FLOAT BAG (3) - closecb UPRIGHT SYS COMPRESS (2) - closeIf Stable II

FLOAT BAG(3)-FILL t1ll 2 m1n afterupr1ght then - OFF

VHF AM AlB amp BCN - OFF whlle lnvertedIf Stable I

After 10 M1n Coollng Per1odFLOAT BAG (3) - FILL 7 mln then OFF

Post Stab1lizat1on And Ventllat10nPL BCN LT - BCN LT LOWPL VENT vlv - UNLOCK (Pull)Remove PL VENT Exh CoverPL VENT - HIGH or LOWPL DYE MARKER - ON (swlmmer comm)Release foots traps and_restralntscb MNA BAT BUS A amp BAT C (2) - opencb MNB BAT BUS B amp BAT C (2) - opencb FLT amp PL BAT C - opencb PYRO A SEQ A - opencb PYRO B SEQ B - open

EACH HR - CHECK DC VOLTSgt 275 V If Notmiddot cb FLT amp PL-BAT BUS AampB (2) -open cb FLT amp PL BAT C (1) - open GO TO LOW POWER CHECKLIST

Unstow and lnstall PLV DISTRIB DUCTDeploy grappllng hook and 11ne 1f req

4

-48-

Post Landing Communlcatl0nsVHF ANT-RECY (venfy)VHF BCN - ON (verlfy)

If no contact ~lth recovery forcesperform VHF BEACON Check

MONITOR VHF BEACON transmlSSlonnth VHF AM B Rcvr andor Su)vlval

TransceiverkVHF Beacon not operatlng ~connect Surv~val TranscelVer to antcable behlnd VHF ant access pnland place radio ln BCN mode

LOW POHER CHECKLISTVHF BCN - OFFVHF AM (3) - RCVFLOOD Lts - OFFVHF AM AampB - off (ctr)VHF AM RCV ONLY - A (venfy)COUCH LIGHTS - OFFPOSTLANDING VENT SYS mlnlmlze useSURV RADIO - plug mto VHF BCN ANT cableconn behind VHF ant acess pnl amp turn radloon l-n BCN mode

EGRESS PROCEDURES

CMPCDRLMPCDR

CMPCDRCMP

LMPLl1PCDR

STABLE IDlsconnect Umblll-calsNeck darn onCenter couch - 270 0 positionArmrests stowedConnect raft to SIC l-f desl-red wlth

green lanyardConnect raft ~hl-te lanyards to SUltS amp

lnflate water wlngs when eXltl-ngHATCH PISTON PRESS vlv - PRESS (Outbd)Slde Hatch openedPL VENT - OFFcb Pnl 250 (all) - openEgress with 11feraftPut hardware klt outEgress

or CDIPALL

CMF

CDRCMF

CDR

LMF

CMFCMP LMFCMP

UlP

CDR

-49-

STABLE IIcb CREW STA AUDIO (3) - openD~sconnect umb~1~ca1s

Release foots trapsRelease restra~nt harnessCouch seat pans (3) - 170 0 pos1t10nArm rests stowedSurv1va1 k~ts removed from stowageConnect life raft ma~n1~ne to CDR or SicConnect f~rst wh~te lanyard from

11fe raft to suitConnect th~rd wh~te lanyard from

l~fe raft to SU1tConnect rucksacks together to yellow

lanyard on raft bagPRESSURE EQUALIZATION vlv - OPENRemove and stow fwd hatchEX1t feet f1rst w1th rucksacks when clear

of siC 1nflate water w1ngs and raftExit feet f1rst when clear of SiC

1nflate water w1ngsEX1t feet f1rst when clear of sic

1nflate water w1ngs

-50-

60 TLI ABORTS

TLI Aborts are conta~ned ~n the ESD s~nce the bulk of the funct~ons

concern entry preparat20ns and performance Th~s allows a s2nglesource of procedures for procedure rev2ew val~dat~on checkout andtra~n~ng These procedures ~ncorporate TLI preparat20ns as found ~n

reference 6 w~th the TLI Abort Procedures and these t~e 2nto normallunar return Entry Procedures found ~n sect20n 5 The guidel~nes

for th~s cont2ngency are spec2f2ed 2n reference 7

In2t2al preparat~ons for TLI pos2t20n the necessary system sW2tches2n add~t~on to perform~ng an EMS ~V test and a GDC al~gnment Afterthe DET ~s set for mon2tor2ng TB6 the CMP ~ncreases the 12ght levelof the LEB DSKY to max~mum and returns to the h2s couch Th2s 2Sdone so that the LEB DSKY can be observed ~n the event sunl~ght orreflect20ns wash out the ma2n d2splay panel DSKY dur2ng cr2t2calmaneuvers The crew then straps ~n and prepares for mon2tor~ng TB6as 2nd2cated by the SII SEP L~te The t2mes se~uence of procedures2S keyed on th~s d~splay and ~ncludes the DET START funct~on andSIVB IGNITION Dur2ng the burn the crew mon2tors the FDAIs foratt~tude excurs20ns and abnormal rates report~ng status checks toM~ss2on Control at d2screet t~mes dur2ng the maneuver Upon SIVBSHUTDOWN the eMP records the DSKY d~splayed performance parametersand awa2ts ground conf2rmat~on

The rat~onal for TLI aborts ~s descr~bed 2n reference 7 A summar2shyzat20n 2S extracted to prov2de background and gu2de12nes 2n th2sdocument The abort procedures cover aborts 10 m2nutes after conshyt2ngent SIVE shutdown and aborts 90 m2nutes after normal SIVE shutshydown t2me

The 10 m~nute TLI abort ~s des2gned to be used dur~ng TLI ~n theevent a spacecraft problem develops Wh2Ch can result 2n catastrophe2f ~mmed~ate act~on 2S not taken If the s~tuat20n perm~ts the crewshould always allow the SIVB to complete TLI at wh~ch t~me the groundand crew can perform a malfunct~on analys~s to determ~ne ~f an abort~s adv~sable If a fa~lure occurs that necess2tates the shutdown ofthe SIVB and the ~u~ck return of the crew to earth th~s abort ~s

des~gned to be as ~nsens~t~ve to execut~on errors as poss~ble andst21l be targeted to m2dcorr2dor The burn att~tude w~th the f~ed

hor~zon reference ~s a constant value for any shutdown t~me Theburn durat~on 2S a funct20n of shutdown t2me and 2S ava21able fromcrew charts S~nce the pr~mary purpose of th~s abort ~s to returnto earth as qU2ckly as poss2ble there are no restr2ct20ns as toland~ng locat~on However ~f the t~me to EI is greater than abouttwo hours a midcourse correct20n should be ant~c~pated

The 90 m2nute TLI abort 2S to be used 2f a cr2t2cal subsystem malshyfunct~on ~s determ2ned and the dec2s~on to abort ~s made after the

-51-

TLI cutoff and before TLI cutoff plus approxlmately 80 m1nutesTh1S allows suff1c1ent separatlon and procedural t1me to set upfor the SPS deorb1t burn performed at about TLI + 90 Note thatgenerally the deorb1t burns w1ll be performed a fe11 m1nutes beforeTLI + 90 accord1ng to crew charts shown In reference 8 The no-comm except10n requ1res that 90 m1nutes be the 1nput t1me of 19n1shytlon for P-37 (onboard return-to-earth abort program) so that onshyboard calculatlons can correspond w1th ground calculat10ns to computethe CM land1ng p01nt Th1S TLI abort lS des1gned so that returnfl1ght t1me does not exceed 18 hours and abort ~V does not exceed7000 fps ThlS abort can be performed uSlng chart ~Vs and attltudesand the earths hor1zon serves as a suff1c1ent reference The maneushyver lS targeted to ach1eve the mldcorr1dor entry target Ilne andtlmed to result 1n a deslgnated recovery area

It 1S ObV10US for abort deC1S1ons early 1n the TLI + 90 m1nute t1meshyframe that a GampN SPS burn should be performed In order to keep theTLI abort procedures cons1stent and w1th emphasls on slmpl1c1ty theprocedures here reflect a SCS SPS abort burn to cover the full abortdec1s1on t1meframe

A m1dcourse correct1on for corr1dor control after a TLI abort may bedeS1red 1f the SPS burn d1d not meet expectat1ons The TLIabortprocedures 1n th1S sect10n adapt to the normal lunar return tlmel1neand procedures pr10r to the f1nal MCC

-52-

61 TLI PREPARATION PROCEDURES

GET = 150

CRO AOS(___)

CRO LOS( )(22142)

5100

Don Helmets amp Gloves

XLUNAR - INJECT (verify)EDS PWR - on (venfy)EMS FUNC - OFF (verlfy)EMS MODE - STBYEMS FUNC - IW SETVHF RNGEMS MODE - NORMALSet ~V indo to +15868 fpsEMS FUMC - ~V Test

SPS THRUST Lt - onoff (10 sec)~V lnd stops at -01 to -415

EMS MODE - STBYEMS FUMC - ~V SETVHF RNGSet ~VC

EMS FUNC---~~V=----

GDC ALIGNFDAI Select - liZcb SECS LOGIC (Z) - close (verify)cb SECS ARM (Z) - closeSECS LOGIC (Z) - on (up)MSFN Conflrm GO for PYRO ARM (If pass)SECS PYRO ARM (Z) - on (up)TRANS CONTROL PWR - ONROT CONTR PWR NORMAL (Z) - ACDC(verlfy)ROT CONTR PWR DIRECT (Z) - MNAMNBLV INnGPI - SIISIVB (venfy)LV GUID - IU (venfy)cb DIRECT ULLAGE (Z) - closedSet EVENT TIMER to 5100Begin MONITOR For TB6

CMP to Couch

TB 6 - SII SEP Lt on (TIG-9 mln 38 sec)KEY V83E

SET ORDEALFDAI Z ORB RATE at 180 0 0SII SEP Lt out (38 sec later)Start DET COUNTING UPSC CaNT - SCS (verify)MONITOR LV TANK PRESS

~P lt 36 psid (OXID gt FUEL)~P lt Z6 psid (FUEL gt OXID)

EMERGENCY CSMLV SEP UP TLM CM - BLOCK (verify)UP TLM IU - BLOCK (venfy)

-53-

+45degPY))0middot sec PY

lOK nmltHAlt25K nm

Two phas~ng mnvrs two SPS mnvrs to circular~ze at 150 nmearth orb~t

CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ssion 4K nmltHAltlOK nm CSM amp1M - Two phasing mnvrs two SPS mnvrs to circularize at 150 nm earth orb~t CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ss~on

CSM amp 1M - Two phas~ng mnvrs APS burn todepletion th~rd phasing mnvrSPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn tosem~sync orb~t

25K nmltHAlt40K nm CSM amp 1M - Two phasmg mnvrs APS burn to depletion third phas~ng mnvr SPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn to sem~sync orbit HA)40K nm DPS ava~l - DPS LOll circularize with SPS

DPS not ava~l - Lunar flyby or CSM only to lunar orbit (if reqd gtV lt4000 fps)

V37E 47E (check b~as) Record -=--rshy(Limit 98 fpsmm)

( 1fps)tVXYZN62EVIHDOTHPAD (fpsfpslnm)MONITOR VI ( ) at ECO

SCS TVC SERVO PWR 1 - ACIMNA2 - OFF

TAPE RCDR - CMD RESETHBREMS MODE - NORMAL

SIr SEP Lt - ONTLI Inhib~t S~gnals w~11 not be honored after 5942

SIVB ULLAGE BeginsSII SEP Lt - off (TIG - 18 sec)SIVB FUEL LEADSIVB ULLAGE d~scont~nues

LV ENG I Lt - onSIVB IGNITION ( GETI)LV ENG I Lt - off - -shyMONITOR THRUST amp ATTITUDEMONITOR LV TANK PRESSSIVE ECO (Lt on) (BEGIN TB7)

EMER SIVE CUTOFF AT 6 SEC PAST BURN TIME IF VI ATTAINEDTHC CCW ampNEUTRAL IN 1 SEC or SIISIVB sW - LV STAGEPremature Shutdown HAlt4K nm CSM amp 1M -

5700

58205836

F 16 835800

F 16 62

5838594259525955595900000002SUNRISE(___)

HAW AOS(__=_) KEY VERB (freeze d~splay)

SIVB ATT HOLD 20 sec amp BEGIN VENTINGSIVB NNVR TO ORB RT (HDS DN) (3middot sec)

Record VI -c---HDOT _

HPAD _

KEY RLSEF 16 62

F 16 83

HAW LOS(__=-)

KEYmiddotRLSE~VXYZ (lfps)

Record ~VX---_

~vy

WZ--

AVC---_

TAPE RCDR - off (ctr)EMS MODE - STBYEMS FUNC - OFFSECS PYRO ARM (2) - SAFE

PRO

BURN STATUS REPORT

____--~TIG

BT------VGX____-R

-----P----_Y

REMARKS

_____VI

______--HDOT______--H______---AVC______---FUEL_______OXID

_______UNBAL

F 3708=00 OOEGOS AOS CMP TO LEB

(-=-=-)

0000

0003

0005

0014

0100

-55-

62 TLI 10 MIN ABORTSECS LOGIC (2) - on (up)SECS PYRO ARM (2) - ARM

TRANS CONTR - CGH (4 sec) amp +XDET RESET (verlfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS GMD-ON

TRANS GONTR - neutral then +X for10 sec

SIVBGPI s~ - GPIExcesslve rates 6V THRUST A - NORMAL SPS THRUST - DIRECT When rates damped 6V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

TRANS CONTR +X - OFFV37E OOE

PITGH UP to LOGAL VERT (+X axlSto~ard the earth)

RATE - LOWBMAG MODE (3) - ATTIRATE 2EDS PHR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SEGS ARM (2) - opencb EDS (3) - open

TRANS CONTR -X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (180deg)P (199deg)Y (0deg)

RETRO UPDATEGETI _

JV _VG

Jtb ---GET 400K _

05G _GET DROGUE _

ENTRY P _R _

Y_--

0945

-56-

ALIGN HORIZ ON RET +1 MKGMBL CHECK (T11lle Pentattlng)MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conflnn)cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FUMC - JV SETVHF RNGSET JV from chartE~S FUMC - JVEMS fODE - NOIDlAL

lV THRUST A - NORMALV37E 47E (THRUST fONITOR)

F 16 83 lVXYZ (1 fps)

0950

1000

NOTE For aborts durlng 1st mln of TLIKEY V82E F 16 44 (HaHpTff)Burn untll Hp lt 19NM

TRANS CONTR +X

THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN JV reqdJV THRUST (2) - OFFReport cutoff

cb SPS P2 Y2- closeGfBL MTRS (4) - OFF (LMP Confinn)TRANS CONT PWR - OFFTVC SERVO PWR (2) - OFFMN BUS TIE (2) - OFFcb SPS P1amp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREIf est time to EIltOl5500 omlt fCC andenter the SUPERCIRC CKLIST as early as pos-slb1e Pg ~2~3~ __If est time to EI)Ol5500 anticlpate afCC Enter the ENTRY PREP CKLIST at step 9pg 18

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

-2tl C

l I W gt- ~-4

z laquo I I- 0 -6

l- I J u gt- ~-8

z w w -10

~_ONSANT

9O

VER

SHO

OT

BOU

ND

ARY

LIF

TV

EC

TOR

OR

IEN

TATI

ON

LIN

E

SH

ALL

OW

TAR

GE

TLI

NE

STE

EP

TAR

GE

TLI

NE 12

gU

ND

ERSH

OO

TBO

UN

DAR

Y

RE

EN

TRY

CO

RR

IDO

R

I ~ I

-12 24

26

28

30

32

34

RE

EN

TRY

VE

LOC

ITY

VE

1-F

TS

EC

Ch

art

1

36

3B

6-i

~

5CM

CC

ON

ST

NT

DR

VI z gt

~

I4

0 Cl W

I

gtamp

J+

-I

-

J Cl z

2U

l z 0_bull

bull-1

+-

u ubullbull

~r

U

)

2829

JOn

J23

33

43

5IN

ER

TIA

LR

EE

NTR

YV

ELO

CIT

YA

T4

00

00

0fl

VE

I-F

TS

EC

Ch

art

2

J63

73

8X

03

-i- rtREQUIRED PITCH GIMBAL ANG LETO OBTAIN HOR-IZON AT 317

DEGREES IN wiiiiDOW

260

z~I- ~ i5 24000

1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

-I

-1-

NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

I LU HD~-

LUHD

lt0 120UJ0

~

80 HOLD PRESENT TRIMgt LU HD013

~Y~HOIgtlt

TOP OF WINDOWa 40to

31 7 SCRIBEaaI

80 TTOM OF WINDOWi= 0

0--ltoa

-40t-z

~~~Uw w u lt0 -80

HOLO PRESENT TRIlJCl

LOHU0 lt0

J gt -120 HOLD 059 TRIMlt0 z

LDHUlt0 FIELD OF VI S10 NLDHU LIFT-DOWNHEADS -UPLUHD LIFT-UP HEADS-DOWN

~~H~-160 q - P63 LIMITI- NOrE-VALIO ONLY FO~t~--

LUNAR RETURN VELOCITY

plusmnl8020 244middot 8 12 16

TIME TO 400K FT ALTITUDE-MIN

4

P37

LONG

ITUD

ECO

RREC

TION

TOOB

TAIN

1350

NM

ENTR

YRA

NGE

Ugt

UJ

cgt

3z 0 I- u U

J0

0

0

2I

U~

UJ

cgt

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-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 39: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

-35-

54 NORMAL DEORBIT

VEHICLE PREP COMPLETE

P30 - EXTERNAL ~V

1 V37E 30E

2 F 06 33 GETI (hrm~nOlsec)

(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

3 F 06 81 ~VXYZ (LV)(ACCEPT) PRO(REJECT) LOAD DESIRED GETI

( lfps)

4 F 06 42 HAHP~V (1nmlfps)Record W

(ACCEPT) PRO -----(REJECT) Rese1ect P30 or P27 Load new pa~am

5 F 16 45 MTFIMGA (marksmln-secOldeg)MGA -00002 If ~ lMU not a1~gned

SET DETPRO

6

7

F 37 OOE

SEPARATION CK LISTPRIM GLY TO RAD - BYPASS (pull)PLSS 02 vlv - FILL02 SM SUPPLY v1v - OFFCAB PRESS REL v1v (2) - NORMcb ELS (2) - close (verify)cb SECS ARM (2) - close (ver~fy)

cb SECS LOGIC (2) - close (verlfy)AUTO RCS SEL CM (12) - ~mA or MNB

(l~ftoff conf~g)

ROT CONTR PWR NORM 1amp2 - ACDCABORT SYS PRPLNT - RCS CMDSM RCS PRIM PRPLNT (4) - OPENVHF AM AampB - off (ctr)

18

-37-

06 18 AUTO MNVR TO FDAI RPY ANGLES (01 0)

19 l 50 18 REOUEST TRIM MNVR TOALIGN SIC ROLLGDC ALIGN

FDAI RPY ANGLES(010

)

+54-00m(-06-00)

TIG-5mJn

5500m(-0500)

TVC CHECK amp PREPcb STAB CONT SYS (all) - closecb SPS (12) - closeATT DB - MINRATE - LOl~

LIMIT CYCLE - ONMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE 2ROT CONTR PWR DIRECT (2) - OFFSCS TVC (2) - RATE CMD

If SCS SCS TVC (2) - AUTO SC CONT - SCS ~

TVC GMBL DRIVE PampY - AUTOMN BUS TIE (2) - ONTVC SERVO PWR 1 - AC1MNA

2 - AC2MNBTRANS CONTR PWR - ONROT CONTR PWR NORMAL 2 - ACRHC 2 - ARMED

HORIZ CHK - HorJz on 12deg wJndmlmark (LJffiJt +3 0 PNGCS GONO GO)

If NO GO set tw 180 0 180deg0 0

Track horJz wJth 24deg wJndow markAt TIG-2 mJn Ahgn GDC

PRIMARY TVC CHECKGMBL MOT P1-Y1 -STARTON(LMP confJrm)

If SCS verJfy Thumbwheel TrJmTHC - CWVenfy NO MTVC

SEC TVC CHECKGHBL MOT P2-Y2 -STARTON(LMP confJrm)SET GPI TRIHVenfy MTVCTHC NEUTRALGPI returns to 00 (CMC) or trJm (SCS)ROT CONT Pl~ NORM 2 - ACDC

(TRIM) Go to step 17(BYPASS) BMAG MODE(3) - ATTIRATE2 (ver1fy)

ENTR

-38-

20 F SO 25 00204 GMBL TEST OPTION(ACCEPT) SC CONT - GMC (ver~fy)

PROMonitor GPI Response

0020-2000020-200Tr~m

TEST FAIL SC CONT - SCS SCS TVC (2) - AUTO

(REJECT) ENTR

21 06 40 TFIVG~VM (m~n-sec1fps)

PROG ALM - TIG s1~pped

V5N9E 01703

KEY RLSE To 21 ROT CONTR PWR DIRECT (2) - MNABSPS He v1vs (2) - AUTO (ver~fy)

LIMIT CYCLE - OFFFDAI SCALE - SOIScb SPS P2Y2 - open (for cr~t burn)

5800(-02 00)

5925(-0035)

59middot 30(-0030)

06 40

59XX(-OOXX)

AV THRUST A(B) - NORMALTHC - ARMEDRlIC (2) - ARMEDTAPE RCDR - GID RESETHBR

DSKY BLANKS

(AVE G ON)EMS MODE - NORMAL

TFIVG~VM (m~n-seclfps)

CHECK PIPA BIAS lt2fps for 5 sec

ULLAGE AS REQ

IF NO ULLAGE DIR ULLAGE PB - PUSH~

CONTROL ATT WRlIC MONITOR AVM (R3) COUNTING UP

5955(-0005)

F 99 40 ENG ON ENABLE REQUEST(AUTO IGN) PRO AT TFI gt0 sec(BYPASS IGN) ENTR to 24

22 0000 IGN

-39-

If SCS - THRUST ON PB - PUSH

06 40 TFCVG~VM (m~n-seclfpslfps)

~F 97 40 SPS Thrust fall ~

~(RESTART) PRO To IGN (RECYCLE) ENTR To TIG-05 sec

SPS THRUST LITE - ONMONITOR THRUSTING

Pc 95-105 pSlaEMS COUNTING DOWNSPS IN3 v1vs (4) - OPENSPS He v1vs tb (2) - graySPS FUELOXID PRESS - 175-195 pSlaPUGS - BALANCED

PROG ALARM V5N9E 01407 VG INCTHC - CW FLY MTVC

ECOEMER SPS CUTOFF J

AV THRUST (2) - OFF

23 F 16 40 TFC(STATIC)VG~VM (mln-seclfps)~V THRUST AB - OFF

SPS IN3 v1vs (4) - CLOSEDSPS He tb (2) - bp

cb SPS P2Y2 - closed (verlfy)TVC SERVO PHR - AC1MNA (venfy)TVC SERVO PWR 2 - OFF

PRO

24 F 16 85 VG XYZ(CM) CUps)NULL RESIDUALSRECORD ~V CTR amp RESIDUALS I1VCEMS FUNC - OFF VGXEMS MODE - STBY VGYBMAG MODE (3) - RATE 2ATT DB - MAX VGZTRANS CONT PHR - OFF

PRO

25 F 37 V82E

26 F 16 44 HAHPTFF (lnmm~n-sec)

R3-59B59 HP gt494 nmPRO

27 F 37 OOE

-40-

55 EARTH ORBIT ENTRY

1 Venfy CMSMR __

P_shyY_-

SEP ATT(180deg)

(0deg )

2

3

4

EMS INITIALIZATIONEMS FUNC - RNG SETSET RNG TO PAD DATA RNGEMS FUNC - VA SETSlew scroll to pad data VIOEMS FUNC - ENTRY

RSI ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on(up)GDC ALIGN PB - PUSH amp HOLDYAW tw - Pos1tion RSI thru 45deg amp

back to LIFl UPGDC ALIGN PB - RELEASEEMS ROLL - OFFAl1gn GDC to lMU

PWR REDUCT (Norm Deorb Only)HGA PWR - OFFFC PUMPS (3) - OFFVer1fy s1ngle suit compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - Lowcb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2)-openlOb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MAN

-41-

P61 - ENTRY PREP

5 V37E 61E05 09 01427 - ROLL REVERSED05 09 01426 - IMU UNSAT

6 F 06 61 IMPACT LAT LONG liDS UPDN (+-)(01 0

010

+00001)

PRO

PAD VALUESLATLON==G------liDS UP DN _

7 F 06 60 GMAXV400KGAMMA EIRecord

GMAXV400K----GAMMA EI _

PRO

8 F 06 63 RTOGO (1nm) PAD _VIa (fps) PADTFE (mln-sec) ----Compare wlth MSFN for PGNS GONO GONO COMM SET RTOGO amp VIO IN EMS amp

INITIALIZE(ACCEPT) PRO(RECALC) V32E to 8

-42-

P62 - CMSM SEP amp PRE-ENTRY MNVR

9 F 50 25 00041 REQUEST CMSM SEPSC CONT - SCSFREEYAW - 45deg out-of-plane (left for RCS

nght for SPS)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE2PRIM GLY to RAD - BYPASS (verlfy)SECS LOGIC (2) - on (up)MSFN conflrm GO for PYRO ARMSECS PYRO ARM - ARMMN BUS TIE (2) - ON (verlfy)CMSM SEF (2) - ONCSMLM FNl SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 pSlaCM RCS LOGIC - OFFSECS PYRO ARM - SAFEMonltor VMAB

If lt25vdc go to EMERG POWERDOWN Pg E6-1AUTO RCS SEL AlC ROLL (4) - OFFAUTO RCS SEL CM 2(6) - OFFAUTO RCS SEL CM 1(6) - MNA or MNBYAW back to 00

PITCH TO ENTRY ATTROLL 0deg (LIFT UP)PITCH - HORIZ on 317deg MARK (400K)YAW 00

ATT DB - MAXMAN ATT (PITCH) - ACCEL CMDEMS DATA - VerifyEMS FUNC - ENTRY (verlfy)EMS MODE - NORMALMAINTAIN HORIZ TRK

PRO (Act ENTRY DAP)

10 F 06 61 IMPACT LAT LONG HDSDN(010 010 -00001)

PRO

11 FOSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axlS beyond 45deg of Vel vector)

-43-

P63 - ENTRY INIT

12 06 64 GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PWR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRHORIZ CKP~tch error needle goes toward

zero approach~ng 05G t~me

MAN ATT (PITCH) - RATE CMDIf CMC ~s GO

BMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS FLY BETA If CMC NO GO ~

SC CONT - SCS~

FLY EMS RCS Deorh Roll HDS UPTRACK HORIZ w~th 29deg w~ndow mk

P64 - ENTRY POST 05G

13

05G t=elt+0___)

06 68

RTOGO AT 05G AGREES WITH EMS - venfyHORIZ CK05E Lt - on (EMS start)

No EMS start w~th~n 3 secsEMS MODE - BACKUP VHF RNG 05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds L~ft DN

NNVR L~ft DNEMS GONO GO

G-V Plot w~th~n llm~ts

Rng ctr dwn 60 + 7 durlng 10 sec per~od

Mon~tor G-meter forconvergence wlth pad data (Do)

(Vlt27K fps) Go To 17

-44-

P65 - ENTRY - UP CONT (Vgt27K fps)

14 F 16 69 BETA (01deg)DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT~

SC CONT - SCS FLY EMS

PRO

15 06 68 BElA VI HOOT (01deg fpsfps)(VltVL +500 fps amp RDOT Neg) Go To 17

p66 - ENTRY - BALLISTIC (DltDL)

16 06 22 DESIRED GMBL ANGLES RPY (01deg)Mon~tor hor~z +12deg of 317deg mark

P67 - ENTRY - FINAL PHASE (02G)

17 0666 BETACRSRNG ERRDNRNG ERR (Oldeglnmlnm)KEY VERBRecord DNRNG ERR _KEY RLSEL~m~t +100nm from PAD DRE

Mon~tor l~ft vector on RSI amp FDAIF 16 67 RTOGOLATLONG (Vre1=1000fps)

(lnm 010 01deg)SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOlfflMon~tor altimeter

Go To EARTHLANDING pg _I4L5__

-45-

56 EARTHLANDING

90K STEAM PRESS - PEGGED50K CABIN PRESS REL vIv (2) - BOOSTENTRY

SECS PYRO ARM (2) - ARM

40K(90K + 63s)

CM UNSTABLE RCS CMD - OFF ~ 40K APEX COVER JETT PG-PUSH DROGUE DEPLOY PG - PUSH (2 secafter apex cover Jett)

30K ELS LOGIC - ON (up)ELS - AUTO

24K RCS hsable (auto)(90K+92s) RCS CMD - OFF

Apex cover Jett (auto)APEX COVER JETT PB - PUSH

(WAIT 2 SECS)Drogue parachutes deployed (auto)

DROGUE DEPLOY PB - PUSH~

If Drogues FallELS - ~ ~Stablllze CM 5K MAIN DPLY PB - PUSHELS - AUTO

235K Cabln Pressure lncreaslng (Drogues + 50s)If not lncreaSlng by 17K CABIN PRESS REL vlv (RR) - DUMP

-46-

10K Maln parachutes deployedMAIN DEPLOY PB - PUSH (wlthln 1 sec)VHF ANT - RECYVHF AMA - SIMPLEXVHF BCN - ONCABIN PRESS REL v1v (2) - CLOSEDIRECT 02 vlv - OPENCM RCS LOGIC - on (up)CM PRPLNT - DUMP (burn audlb1e)Monltor CM ReS 1amp2 for He press decrease

NO BURN or PRESS DECREASE USE BOTH RHCs DO NOT FIRE PITCH JETS

CM PRPLNT-PURGE (to zero He press)CM RCS He DUMP PB - PUSH RHC (2) - 30 sees NO PITCH k

STRUT LOCKS (2) - UNLOCK

cb FLT amp PL BAT BUS ABampBAT C (3) - closecb FLT amp PLT MNA amp B (2) - opencb ECS RAD HTR OVLD (2) - opencb SPS PampY (4) - open

3K CABIN PRESS REL v1v (RH) - DUMP (after purgecompleted)

FLOOD Lts - POST LDGCM RCS PRPLNT (2) - OFFROT CONTR PWR DIRECT (2) - OFF

800 CAB PRESS RELF vlv - CLOSE (latch off)MN BUS TIE (2) - OFF

AFTER LANDINGcb MAIN REL PYRO (2) - closeMAIN RELEASE - on(up)

Go to POSTLANDING pg _47L-__

I

2

3

-47-

57 POSTLANDING

STABILIZATION VENTILATION COMMUNICATIONS

DIRECT 02 vlv - CLOSE

Stablllzation after landlngELS - AUTO (verlfy)cb MAIN REL PYRO (2) - close (venfy)MAIN RELEASE - on (up) (verlfy)S~CS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb BAT RLY BUS (2) - open

No contact w1th recovery forcesVHF AM AampB - off (ctr) ~

VHF AM Rev ONLY - A cb PL VENT - closecb FLOAT BAG (3) - closecb UPRIGHT SYS COMPRESS (2) - closeIf Stable II

FLOAT BAG(3)-FILL t1ll 2 m1n afterupr1ght then - OFF

VHF AM AlB amp BCN - OFF whlle lnvertedIf Stable I

After 10 M1n Coollng Per1odFLOAT BAG (3) - FILL 7 mln then OFF

Post Stab1lizat1on And Ventllat10nPL BCN LT - BCN LT LOWPL VENT vlv - UNLOCK (Pull)Remove PL VENT Exh CoverPL VENT - HIGH or LOWPL DYE MARKER - ON (swlmmer comm)Release foots traps and_restralntscb MNA BAT BUS A amp BAT C (2) - opencb MNB BAT BUS B amp BAT C (2) - opencb FLT amp PL BAT C - opencb PYRO A SEQ A - opencb PYRO B SEQ B - open

EACH HR - CHECK DC VOLTSgt 275 V If Notmiddot cb FLT amp PL-BAT BUS AampB (2) -open cb FLT amp PL BAT C (1) - open GO TO LOW POWER CHECKLIST

Unstow and lnstall PLV DISTRIB DUCTDeploy grappllng hook and 11ne 1f req

4

-48-

Post Landing Communlcatl0nsVHF ANT-RECY (venfy)VHF BCN - ON (verlfy)

If no contact ~lth recovery forcesperform VHF BEACON Check

MONITOR VHF BEACON transmlSSlonnth VHF AM B Rcvr andor Su)vlval

TransceiverkVHF Beacon not operatlng ~connect Surv~val TranscelVer to antcable behlnd VHF ant access pnland place radio ln BCN mode

LOW POHER CHECKLISTVHF BCN - OFFVHF AM (3) - RCVFLOOD Lts - OFFVHF AM AampB - off (ctr)VHF AM RCV ONLY - A (venfy)COUCH LIGHTS - OFFPOSTLANDING VENT SYS mlnlmlze useSURV RADIO - plug mto VHF BCN ANT cableconn behind VHF ant acess pnl amp turn radloon l-n BCN mode

EGRESS PROCEDURES

CMPCDRLMPCDR

CMPCDRCMP

LMPLl1PCDR

STABLE IDlsconnect Umblll-calsNeck darn onCenter couch - 270 0 positionArmrests stowedConnect raft to SIC l-f desl-red wlth

green lanyardConnect raft ~hl-te lanyards to SUltS amp

lnflate water wlngs when eXltl-ngHATCH PISTON PRESS vlv - PRESS (Outbd)Slde Hatch openedPL VENT - OFFcb Pnl 250 (all) - openEgress with 11feraftPut hardware klt outEgress

or CDIPALL

CMF

CDRCMF

CDR

LMF

CMFCMP LMFCMP

UlP

CDR

-49-

STABLE IIcb CREW STA AUDIO (3) - openD~sconnect umb~1~ca1s

Release foots trapsRelease restra~nt harnessCouch seat pans (3) - 170 0 pos1t10nArm rests stowedSurv1va1 k~ts removed from stowageConnect life raft ma~n1~ne to CDR or SicConnect f~rst wh~te lanyard from

11fe raft to suitConnect th~rd wh~te lanyard from

l~fe raft to SU1tConnect rucksacks together to yellow

lanyard on raft bagPRESSURE EQUALIZATION vlv - OPENRemove and stow fwd hatchEX1t feet f1rst w1th rucksacks when clear

of siC 1nflate water w1ngs and raftExit feet f1rst when clear of SiC

1nflate water w1ngsEX1t feet f1rst when clear of sic

1nflate water w1ngs

-50-

60 TLI ABORTS

TLI Aborts are conta~ned ~n the ESD s~nce the bulk of the funct~ons

concern entry preparat20ns and performance Th~s allows a s2nglesource of procedures for procedure rev2ew val~dat~on checkout andtra~n~ng These procedures ~ncorporate TLI preparat20ns as found ~n

reference 6 w~th the TLI Abort Procedures and these t~e 2nto normallunar return Entry Procedures found ~n sect20n 5 The guidel~nes

for th~s cont2ngency are spec2f2ed 2n reference 7

In2t2al preparat~ons for TLI pos2t20n the necessary system sW2tches2n add~t~on to perform~ng an EMS ~V test and a GDC al~gnment Afterthe DET ~s set for mon2tor2ng TB6 the CMP ~ncreases the 12ght levelof the LEB DSKY to max~mum and returns to the h2s couch Th2s 2Sdone so that the LEB DSKY can be observed ~n the event sunl~ght orreflect20ns wash out the ma2n d2splay panel DSKY dur2ng cr2t2calmaneuvers The crew then straps ~n and prepares for mon2tor~ng TB6as 2nd2cated by the SII SEP L~te The t2mes se~uence of procedures2S keyed on th~s d~splay and ~ncludes the DET START funct~on andSIVB IGNITION Dur2ng the burn the crew mon2tors the FDAIs foratt~tude excurs20ns and abnormal rates report~ng status checks toM~ss2on Control at d2screet t~mes dur2ng the maneuver Upon SIVBSHUTDOWN the eMP records the DSKY d~splayed performance parametersand awa2ts ground conf2rmat~on

The rat~onal for TLI aborts ~s descr~bed 2n reference 7 A summar2shyzat20n 2S extracted to prov2de background and gu2de12nes 2n th2sdocument The abort procedures cover aborts 10 m2nutes after conshyt2ngent SIVE shutdown and aborts 90 m2nutes after normal SIVE shutshydown t2me

The 10 m~nute TLI abort ~s des2gned to be used dur~ng TLI ~n theevent a spacecraft problem develops Wh2Ch can result 2n catastrophe2f ~mmed~ate act~on 2S not taken If the s~tuat20n perm~ts the crewshould always allow the SIVB to complete TLI at wh~ch t~me the groundand crew can perform a malfunct~on analys~s to determ~ne ~f an abort~s adv~sable If a fa~lure occurs that necess2tates the shutdown ofthe SIVB and the ~u~ck return of the crew to earth th~s abort ~s

des~gned to be as ~nsens~t~ve to execut~on errors as poss~ble andst21l be targeted to m2dcorr2dor The burn att~tude w~th the f~ed

hor~zon reference ~s a constant value for any shutdown t~me Theburn durat~on 2S a funct20n of shutdown t2me and 2S ava21able fromcrew charts S~nce the pr~mary purpose of th~s abort ~s to returnto earth as qU2ckly as poss2ble there are no restr2ct20ns as toland~ng locat~on However ~f the t~me to EI is greater than abouttwo hours a midcourse correct20n should be ant~c~pated

The 90 m2nute TLI abort 2S to be used 2f a cr2t2cal subsystem malshyfunct~on ~s determ2ned and the dec2s~on to abort ~s made after the

-51-

TLI cutoff and before TLI cutoff plus approxlmately 80 m1nutesTh1S allows suff1c1ent separatlon and procedural t1me to set upfor the SPS deorb1t burn performed at about TLI + 90 Note thatgenerally the deorb1t burns w1ll be performed a fe11 m1nutes beforeTLI + 90 accord1ng to crew charts shown In reference 8 The no-comm except10n requ1res that 90 m1nutes be the 1nput t1me of 19n1shytlon for P-37 (onboard return-to-earth abort program) so that onshyboard calculatlons can correspond w1th ground calculat10ns to computethe CM land1ng p01nt Th1S TLI abort lS des1gned so that returnfl1ght t1me does not exceed 18 hours and abort ~V does not exceed7000 fps ThlS abort can be performed uSlng chart ~Vs and attltudesand the earths hor1zon serves as a suff1c1ent reference The maneushyver lS targeted to ach1eve the mldcorr1dor entry target Ilne andtlmed to result 1n a deslgnated recovery area

It 1S ObV10US for abort deC1S1ons early 1n the TLI + 90 m1nute t1meshyframe that a GampN SPS burn should be performed In order to keep theTLI abort procedures cons1stent and w1th emphasls on slmpl1c1ty theprocedures here reflect a SCS SPS abort burn to cover the full abortdec1s1on t1meframe

A m1dcourse correct1on for corr1dor control after a TLI abort may bedeS1red 1f the SPS burn d1d not meet expectat1ons The TLIabortprocedures 1n th1S sect10n adapt to the normal lunar return tlmel1neand procedures pr10r to the f1nal MCC

-52-

61 TLI PREPARATION PROCEDURES

GET = 150

CRO AOS(___)

CRO LOS( )(22142)

5100

Don Helmets amp Gloves

XLUNAR - INJECT (verify)EDS PWR - on (venfy)EMS FUNC - OFF (verlfy)EMS MODE - STBYEMS FUNC - IW SETVHF RNGEMS MODE - NORMALSet ~V indo to +15868 fpsEMS FUMC - ~V Test

SPS THRUST Lt - onoff (10 sec)~V lnd stops at -01 to -415

EMS MODE - STBYEMS FUMC - ~V SETVHF RNGSet ~VC

EMS FUNC---~~V=----

GDC ALIGNFDAI Select - liZcb SECS LOGIC (Z) - close (verify)cb SECS ARM (Z) - closeSECS LOGIC (Z) - on (up)MSFN Conflrm GO for PYRO ARM (If pass)SECS PYRO ARM (Z) - on (up)TRANS CONTROL PWR - ONROT CONTR PWR NORMAL (Z) - ACDC(verlfy)ROT CONTR PWR DIRECT (Z) - MNAMNBLV INnGPI - SIISIVB (venfy)LV GUID - IU (venfy)cb DIRECT ULLAGE (Z) - closedSet EVENT TIMER to 5100Begin MONITOR For TB6

CMP to Couch

TB 6 - SII SEP Lt on (TIG-9 mln 38 sec)KEY V83E

SET ORDEALFDAI Z ORB RATE at 180 0 0SII SEP Lt out (38 sec later)Start DET COUNTING UPSC CaNT - SCS (verify)MONITOR LV TANK PRESS

~P lt 36 psid (OXID gt FUEL)~P lt Z6 psid (FUEL gt OXID)

EMERGENCY CSMLV SEP UP TLM CM - BLOCK (verify)UP TLM IU - BLOCK (venfy)

-53-

+45degPY))0middot sec PY

lOK nmltHAlt25K nm

Two phas~ng mnvrs two SPS mnvrs to circular~ze at 150 nmearth orb~t

CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ssion 4K nmltHAltlOK nm CSM amp1M - Two phasing mnvrs two SPS mnvrs to circularize at 150 nm earth orb~t CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ss~on

CSM amp 1M - Two phas~ng mnvrs APS burn todepletion th~rd phasing mnvrSPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn tosem~sync orb~t

25K nmltHAlt40K nm CSM amp 1M - Two phasmg mnvrs APS burn to depletion third phas~ng mnvr SPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn to sem~sync orbit HA)40K nm DPS ava~l - DPS LOll circularize with SPS

DPS not ava~l - Lunar flyby or CSM only to lunar orbit (if reqd gtV lt4000 fps)

V37E 47E (check b~as) Record -=--rshy(Limit 98 fpsmm)

( 1fps)tVXYZN62EVIHDOTHPAD (fpsfpslnm)MONITOR VI ( ) at ECO

SCS TVC SERVO PWR 1 - ACIMNA2 - OFF

TAPE RCDR - CMD RESETHBREMS MODE - NORMAL

SIr SEP Lt - ONTLI Inhib~t S~gnals w~11 not be honored after 5942

SIVB ULLAGE BeginsSII SEP Lt - off (TIG - 18 sec)SIVB FUEL LEADSIVB ULLAGE d~scont~nues

LV ENG I Lt - onSIVB IGNITION ( GETI)LV ENG I Lt - off - -shyMONITOR THRUST amp ATTITUDEMONITOR LV TANK PRESSSIVE ECO (Lt on) (BEGIN TB7)

EMER SIVE CUTOFF AT 6 SEC PAST BURN TIME IF VI ATTAINEDTHC CCW ampNEUTRAL IN 1 SEC or SIISIVB sW - LV STAGEPremature Shutdown HAlt4K nm CSM amp 1M -

5700

58205836

F 16 835800

F 16 62

5838594259525955595900000002SUNRISE(___)

HAW AOS(__=_) KEY VERB (freeze d~splay)

SIVB ATT HOLD 20 sec amp BEGIN VENTINGSIVB NNVR TO ORB RT (HDS DN) (3middot sec)

Record VI -c---HDOT _

HPAD _

KEY RLSEF 16 62

F 16 83

HAW LOS(__=-)

KEYmiddotRLSE~VXYZ (lfps)

Record ~VX---_

~vy

WZ--

AVC---_

TAPE RCDR - off (ctr)EMS MODE - STBYEMS FUNC - OFFSECS PYRO ARM (2) - SAFE

PRO

BURN STATUS REPORT

____--~TIG

BT------VGX____-R

-----P----_Y

REMARKS

_____VI

______--HDOT______--H______---AVC______---FUEL_______OXID

_______UNBAL

F 3708=00 OOEGOS AOS CMP TO LEB

(-=-=-)

0000

0003

0005

0014

0100

-55-

62 TLI 10 MIN ABORTSECS LOGIC (2) - on (up)SECS PYRO ARM (2) - ARM

TRANS CONTR - CGH (4 sec) amp +XDET RESET (verlfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS GMD-ON

TRANS GONTR - neutral then +X for10 sec

SIVBGPI s~ - GPIExcesslve rates 6V THRUST A - NORMAL SPS THRUST - DIRECT When rates damped 6V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

TRANS CONTR +X - OFFV37E OOE

PITGH UP to LOGAL VERT (+X axlSto~ard the earth)

RATE - LOWBMAG MODE (3) - ATTIRATE 2EDS PHR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SEGS ARM (2) - opencb EDS (3) - open

TRANS CONTR -X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (180deg)P (199deg)Y (0deg)

RETRO UPDATEGETI _

JV _VG

Jtb ---GET 400K _

05G _GET DROGUE _

ENTRY P _R _

Y_--

0945

-56-

ALIGN HORIZ ON RET +1 MKGMBL CHECK (T11lle Pentattlng)MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conflnn)cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FUMC - JV SETVHF RNGSET JV from chartE~S FUMC - JVEMS fODE - NOIDlAL

lV THRUST A - NORMALV37E 47E (THRUST fONITOR)

F 16 83 lVXYZ (1 fps)

0950

1000

NOTE For aborts durlng 1st mln of TLIKEY V82E F 16 44 (HaHpTff)Burn untll Hp lt 19NM

TRANS CONTR +X

THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN JV reqdJV THRUST (2) - OFFReport cutoff

cb SPS P2 Y2- closeGfBL MTRS (4) - OFF (LMP Confinn)TRANS CONT PWR - OFFTVC SERVO PWR (2) - OFFMN BUS TIE (2) - OFFcb SPS P1amp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREIf est time to EIltOl5500 omlt fCC andenter the SUPERCIRC CKLIST as early as pos-slb1e Pg ~2~3~ __If est time to EI)Ol5500 anticlpate afCC Enter the ENTRY PREP CKLIST at step 9pg 18

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

-2tl C

l I W gt- ~-4

z laquo I I- 0 -6

l- I J u gt- ~-8

z w w -10

~_ONSANT

9O

VER

SHO

OT

BOU

ND

ARY

LIF

TV

EC

TOR

OR

IEN

TATI

ON

LIN

E

SH

ALL

OW

TAR

GE

TLI

NE

STE

EP

TAR

GE

TLI

NE 12

gU

ND

ERSH

OO

TBO

UN

DAR

Y

RE

EN

TRY

CO

RR

IDO

R

I ~ I

-12 24

26

28

30

32

34

RE

EN

TRY

VE

LOC

ITY

VE

1-F

TS

EC

Ch

art

1

36

3B

6-i

~

5CM

CC

ON

ST

NT

DR

VI z gt

~

I4

0 Cl W

I

gtamp

J+

-I

-

J Cl z

2U

l z 0_bull

bull-1

+-

u ubullbull

~r

U

)

2829

JOn

J23

33

43

5IN

ER

TIA

LR

EE

NTR

YV

ELO

CIT

YA

T4

00

00

0fl

VE

I-F

TS

EC

Ch

art

2

J63

73

8X

03

-i- rtREQUIRED PITCH GIMBAL ANG LETO OBTAIN HOR-IZON AT 317

DEGREES IN wiiiiDOW

260

z~I- ~ i5 24000

1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

-I

-1-

NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

I LU HD~-

LUHD

lt0 120UJ0

~

80 HOLD PRESENT TRIMgt LU HD013

~Y~HOIgtlt

TOP OF WINDOWa 40to

31 7 SCRIBEaaI

80 TTOM OF WINDOWi= 0

0--ltoa

-40t-z

~~~Uw w u lt0 -80

HOLO PRESENT TRIlJCl

LOHU0 lt0

J gt -120 HOLD 059 TRIMlt0 z

LDHUlt0 FIELD OF VI S10 NLDHU LIFT-DOWNHEADS -UPLUHD LIFT-UP HEADS-DOWN

~~H~-160 q - P63 LIMITI- NOrE-VALIO ONLY FO~t~--

LUNAR RETURN VELOCITY

plusmnl8020 244middot 8 12 16

TIME TO 400K FT ALTITUDE-MIN

4

P37

LONG

ITUD

ECO

RREC

TION

TOOB

TAIN

1350

NM

ENTR

YRA

NGE

Ugt

UJ

cgt

3z 0 I- u U

J0

0

0

2I

U~

UJ

cgt

I

gtI- U

gt z 0 J ltJ

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-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 40: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

18

-37-

06 18 AUTO MNVR TO FDAI RPY ANGLES (01 0)

19 l 50 18 REOUEST TRIM MNVR TOALIGN SIC ROLLGDC ALIGN

FDAI RPY ANGLES(010

)

+54-00m(-06-00)

TIG-5mJn

5500m(-0500)

TVC CHECK amp PREPcb STAB CONT SYS (all) - closecb SPS (12) - closeATT DB - MINRATE - LOl~

LIMIT CYCLE - ONMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE 2ROT CONTR PWR DIRECT (2) - OFFSCS TVC (2) - RATE CMD

If SCS SCS TVC (2) - AUTO SC CONT - SCS ~

TVC GMBL DRIVE PampY - AUTOMN BUS TIE (2) - ONTVC SERVO PWR 1 - AC1MNA

2 - AC2MNBTRANS CONTR PWR - ONROT CONTR PWR NORMAL 2 - ACRHC 2 - ARMED

HORIZ CHK - HorJz on 12deg wJndmlmark (LJffiJt +3 0 PNGCS GONO GO)

If NO GO set tw 180 0 180deg0 0

Track horJz wJth 24deg wJndow markAt TIG-2 mJn Ahgn GDC

PRIMARY TVC CHECKGMBL MOT P1-Y1 -STARTON(LMP confJrm)

If SCS verJfy Thumbwheel TrJmTHC - CWVenfy NO MTVC

SEC TVC CHECKGHBL MOT P2-Y2 -STARTON(LMP confJrm)SET GPI TRIHVenfy MTVCTHC NEUTRALGPI returns to 00 (CMC) or trJm (SCS)ROT CONT Pl~ NORM 2 - ACDC

(TRIM) Go to step 17(BYPASS) BMAG MODE(3) - ATTIRATE2 (ver1fy)

ENTR

-38-

20 F SO 25 00204 GMBL TEST OPTION(ACCEPT) SC CONT - GMC (ver~fy)

PROMonitor GPI Response

0020-2000020-200Tr~m

TEST FAIL SC CONT - SCS SCS TVC (2) - AUTO

(REJECT) ENTR

21 06 40 TFIVG~VM (m~n-sec1fps)

PROG ALM - TIG s1~pped

V5N9E 01703

KEY RLSE To 21 ROT CONTR PWR DIRECT (2) - MNABSPS He v1vs (2) - AUTO (ver~fy)

LIMIT CYCLE - OFFFDAI SCALE - SOIScb SPS P2Y2 - open (for cr~t burn)

5800(-02 00)

5925(-0035)

59middot 30(-0030)

06 40

59XX(-OOXX)

AV THRUST A(B) - NORMALTHC - ARMEDRlIC (2) - ARMEDTAPE RCDR - GID RESETHBR

DSKY BLANKS

(AVE G ON)EMS MODE - NORMAL

TFIVG~VM (m~n-seclfps)

CHECK PIPA BIAS lt2fps for 5 sec

ULLAGE AS REQ

IF NO ULLAGE DIR ULLAGE PB - PUSH~

CONTROL ATT WRlIC MONITOR AVM (R3) COUNTING UP

5955(-0005)

F 99 40 ENG ON ENABLE REQUEST(AUTO IGN) PRO AT TFI gt0 sec(BYPASS IGN) ENTR to 24

22 0000 IGN

-39-

If SCS - THRUST ON PB - PUSH

06 40 TFCVG~VM (m~n-seclfpslfps)

~F 97 40 SPS Thrust fall ~

~(RESTART) PRO To IGN (RECYCLE) ENTR To TIG-05 sec

SPS THRUST LITE - ONMONITOR THRUSTING

Pc 95-105 pSlaEMS COUNTING DOWNSPS IN3 v1vs (4) - OPENSPS He v1vs tb (2) - graySPS FUELOXID PRESS - 175-195 pSlaPUGS - BALANCED

PROG ALARM V5N9E 01407 VG INCTHC - CW FLY MTVC

ECOEMER SPS CUTOFF J

AV THRUST (2) - OFF

23 F 16 40 TFC(STATIC)VG~VM (mln-seclfps)~V THRUST AB - OFF

SPS IN3 v1vs (4) - CLOSEDSPS He tb (2) - bp

cb SPS P2Y2 - closed (verlfy)TVC SERVO PHR - AC1MNA (venfy)TVC SERVO PWR 2 - OFF

PRO

24 F 16 85 VG XYZ(CM) CUps)NULL RESIDUALSRECORD ~V CTR amp RESIDUALS I1VCEMS FUNC - OFF VGXEMS MODE - STBY VGYBMAG MODE (3) - RATE 2ATT DB - MAX VGZTRANS CONT PHR - OFF

PRO

25 F 37 V82E

26 F 16 44 HAHPTFF (lnmm~n-sec)

R3-59B59 HP gt494 nmPRO

27 F 37 OOE

-40-

55 EARTH ORBIT ENTRY

1 Venfy CMSMR __

P_shyY_-

SEP ATT(180deg)

(0deg )

2

3

4

EMS INITIALIZATIONEMS FUNC - RNG SETSET RNG TO PAD DATA RNGEMS FUNC - VA SETSlew scroll to pad data VIOEMS FUNC - ENTRY

RSI ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on(up)GDC ALIGN PB - PUSH amp HOLDYAW tw - Pos1tion RSI thru 45deg amp

back to LIFl UPGDC ALIGN PB - RELEASEEMS ROLL - OFFAl1gn GDC to lMU

PWR REDUCT (Norm Deorb Only)HGA PWR - OFFFC PUMPS (3) - OFFVer1fy s1ngle suit compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - Lowcb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2)-openlOb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MAN

-41-

P61 - ENTRY PREP

5 V37E 61E05 09 01427 - ROLL REVERSED05 09 01426 - IMU UNSAT

6 F 06 61 IMPACT LAT LONG liDS UPDN (+-)(01 0

010

+00001)

PRO

PAD VALUESLATLON==G------liDS UP DN _

7 F 06 60 GMAXV400KGAMMA EIRecord

GMAXV400K----GAMMA EI _

PRO

8 F 06 63 RTOGO (1nm) PAD _VIa (fps) PADTFE (mln-sec) ----Compare wlth MSFN for PGNS GONO GONO COMM SET RTOGO amp VIO IN EMS amp

INITIALIZE(ACCEPT) PRO(RECALC) V32E to 8

-42-

P62 - CMSM SEP amp PRE-ENTRY MNVR

9 F 50 25 00041 REQUEST CMSM SEPSC CONT - SCSFREEYAW - 45deg out-of-plane (left for RCS

nght for SPS)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE2PRIM GLY to RAD - BYPASS (verlfy)SECS LOGIC (2) - on (up)MSFN conflrm GO for PYRO ARMSECS PYRO ARM - ARMMN BUS TIE (2) - ON (verlfy)CMSM SEF (2) - ONCSMLM FNl SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 pSlaCM RCS LOGIC - OFFSECS PYRO ARM - SAFEMonltor VMAB

If lt25vdc go to EMERG POWERDOWN Pg E6-1AUTO RCS SEL AlC ROLL (4) - OFFAUTO RCS SEL CM 2(6) - OFFAUTO RCS SEL CM 1(6) - MNA or MNBYAW back to 00

PITCH TO ENTRY ATTROLL 0deg (LIFT UP)PITCH - HORIZ on 317deg MARK (400K)YAW 00

ATT DB - MAXMAN ATT (PITCH) - ACCEL CMDEMS DATA - VerifyEMS FUNC - ENTRY (verlfy)EMS MODE - NORMALMAINTAIN HORIZ TRK

PRO (Act ENTRY DAP)

10 F 06 61 IMPACT LAT LONG HDSDN(010 010 -00001)

PRO

11 FOSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axlS beyond 45deg of Vel vector)

-43-

P63 - ENTRY INIT

12 06 64 GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PWR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRHORIZ CKP~tch error needle goes toward

zero approach~ng 05G t~me

MAN ATT (PITCH) - RATE CMDIf CMC ~s GO

BMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS FLY BETA If CMC NO GO ~

SC CONT - SCS~

FLY EMS RCS Deorh Roll HDS UPTRACK HORIZ w~th 29deg w~ndow mk

P64 - ENTRY POST 05G

13

05G t=elt+0___)

06 68

RTOGO AT 05G AGREES WITH EMS - venfyHORIZ CK05E Lt - on (EMS start)

No EMS start w~th~n 3 secsEMS MODE - BACKUP VHF RNG 05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds L~ft DN

NNVR L~ft DNEMS GONO GO

G-V Plot w~th~n llm~ts

Rng ctr dwn 60 + 7 durlng 10 sec per~od

Mon~tor G-meter forconvergence wlth pad data (Do)

(Vlt27K fps) Go To 17

-44-

P65 - ENTRY - UP CONT (Vgt27K fps)

14 F 16 69 BETA (01deg)DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT~

SC CONT - SCS FLY EMS

PRO

15 06 68 BElA VI HOOT (01deg fpsfps)(VltVL +500 fps amp RDOT Neg) Go To 17

p66 - ENTRY - BALLISTIC (DltDL)

16 06 22 DESIRED GMBL ANGLES RPY (01deg)Mon~tor hor~z +12deg of 317deg mark

P67 - ENTRY - FINAL PHASE (02G)

17 0666 BETACRSRNG ERRDNRNG ERR (Oldeglnmlnm)KEY VERBRecord DNRNG ERR _KEY RLSEL~m~t +100nm from PAD DRE

Mon~tor l~ft vector on RSI amp FDAIF 16 67 RTOGOLATLONG (Vre1=1000fps)

(lnm 010 01deg)SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOlfflMon~tor altimeter

Go To EARTHLANDING pg _I4L5__

-45-

56 EARTHLANDING

90K STEAM PRESS - PEGGED50K CABIN PRESS REL vIv (2) - BOOSTENTRY

SECS PYRO ARM (2) - ARM

40K(90K + 63s)

CM UNSTABLE RCS CMD - OFF ~ 40K APEX COVER JETT PG-PUSH DROGUE DEPLOY PG - PUSH (2 secafter apex cover Jett)

30K ELS LOGIC - ON (up)ELS - AUTO

24K RCS hsable (auto)(90K+92s) RCS CMD - OFF

Apex cover Jett (auto)APEX COVER JETT PB - PUSH

(WAIT 2 SECS)Drogue parachutes deployed (auto)

DROGUE DEPLOY PB - PUSH~

If Drogues FallELS - ~ ~Stablllze CM 5K MAIN DPLY PB - PUSHELS - AUTO

235K Cabln Pressure lncreaslng (Drogues + 50s)If not lncreaSlng by 17K CABIN PRESS REL vlv (RR) - DUMP

-46-

10K Maln parachutes deployedMAIN DEPLOY PB - PUSH (wlthln 1 sec)VHF ANT - RECYVHF AMA - SIMPLEXVHF BCN - ONCABIN PRESS REL v1v (2) - CLOSEDIRECT 02 vlv - OPENCM RCS LOGIC - on (up)CM PRPLNT - DUMP (burn audlb1e)Monltor CM ReS 1amp2 for He press decrease

NO BURN or PRESS DECREASE USE BOTH RHCs DO NOT FIRE PITCH JETS

CM PRPLNT-PURGE (to zero He press)CM RCS He DUMP PB - PUSH RHC (2) - 30 sees NO PITCH k

STRUT LOCKS (2) - UNLOCK

cb FLT amp PL BAT BUS ABampBAT C (3) - closecb FLT amp PLT MNA amp B (2) - opencb ECS RAD HTR OVLD (2) - opencb SPS PampY (4) - open

3K CABIN PRESS REL v1v (RH) - DUMP (after purgecompleted)

FLOOD Lts - POST LDGCM RCS PRPLNT (2) - OFFROT CONTR PWR DIRECT (2) - OFF

800 CAB PRESS RELF vlv - CLOSE (latch off)MN BUS TIE (2) - OFF

AFTER LANDINGcb MAIN REL PYRO (2) - closeMAIN RELEASE - on(up)

Go to POSTLANDING pg _47L-__

I

2

3

-47-

57 POSTLANDING

STABILIZATION VENTILATION COMMUNICATIONS

DIRECT 02 vlv - CLOSE

Stablllzation after landlngELS - AUTO (verlfy)cb MAIN REL PYRO (2) - close (venfy)MAIN RELEASE - on (up) (verlfy)S~CS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb BAT RLY BUS (2) - open

No contact w1th recovery forcesVHF AM AampB - off (ctr) ~

VHF AM Rev ONLY - A cb PL VENT - closecb FLOAT BAG (3) - closecb UPRIGHT SYS COMPRESS (2) - closeIf Stable II

FLOAT BAG(3)-FILL t1ll 2 m1n afterupr1ght then - OFF

VHF AM AlB amp BCN - OFF whlle lnvertedIf Stable I

After 10 M1n Coollng Per1odFLOAT BAG (3) - FILL 7 mln then OFF

Post Stab1lizat1on And Ventllat10nPL BCN LT - BCN LT LOWPL VENT vlv - UNLOCK (Pull)Remove PL VENT Exh CoverPL VENT - HIGH or LOWPL DYE MARKER - ON (swlmmer comm)Release foots traps and_restralntscb MNA BAT BUS A amp BAT C (2) - opencb MNB BAT BUS B amp BAT C (2) - opencb FLT amp PL BAT C - opencb PYRO A SEQ A - opencb PYRO B SEQ B - open

EACH HR - CHECK DC VOLTSgt 275 V If Notmiddot cb FLT amp PL-BAT BUS AampB (2) -open cb FLT amp PL BAT C (1) - open GO TO LOW POWER CHECKLIST

Unstow and lnstall PLV DISTRIB DUCTDeploy grappllng hook and 11ne 1f req

4

-48-

Post Landing Communlcatl0nsVHF ANT-RECY (venfy)VHF BCN - ON (verlfy)

If no contact ~lth recovery forcesperform VHF BEACON Check

MONITOR VHF BEACON transmlSSlonnth VHF AM B Rcvr andor Su)vlval

TransceiverkVHF Beacon not operatlng ~connect Surv~val TranscelVer to antcable behlnd VHF ant access pnland place radio ln BCN mode

LOW POHER CHECKLISTVHF BCN - OFFVHF AM (3) - RCVFLOOD Lts - OFFVHF AM AampB - off (ctr)VHF AM RCV ONLY - A (venfy)COUCH LIGHTS - OFFPOSTLANDING VENT SYS mlnlmlze useSURV RADIO - plug mto VHF BCN ANT cableconn behind VHF ant acess pnl amp turn radloon l-n BCN mode

EGRESS PROCEDURES

CMPCDRLMPCDR

CMPCDRCMP

LMPLl1PCDR

STABLE IDlsconnect Umblll-calsNeck darn onCenter couch - 270 0 positionArmrests stowedConnect raft to SIC l-f desl-red wlth

green lanyardConnect raft ~hl-te lanyards to SUltS amp

lnflate water wlngs when eXltl-ngHATCH PISTON PRESS vlv - PRESS (Outbd)Slde Hatch openedPL VENT - OFFcb Pnl 250 (all) - openEgress with 11feraftPut hardware klt outEgress

or CDIPALL

CMF

CDRCMF

CDR

LMF

CMFCMP LMFCMP

UlP

CDR

-49-

STABLE IIcb CREW STA AUDIO (3) - openD~sconnect umb~1~ca1s

Release foots trapsRelease restra~nt harnessCouch seat pans (3) - 170 0 pos1t10nArm rests stowedSurv1va1 k~ts removed from stowageConnect life raft ma~n1~ne to CDR or SicConnect f~rst wh~te lanyard from

11fe raft to suitConnect th~rd wh~te lanyard from

l~fe raft to SU1tConnect rucksacks together to yellow

lanyard on raft bagPRESSURE EQUALIZATION vlv - OPENRemove and stow fwd hatchEX1t feet f1rst w1th rucksacks when clear

of siC 1nflate water w1ngs and raftExit feet f1rst when clear of SiC

1nflate water w1ngsEX1t feet f1rst when clear of sic

1nflate water w1ngs

-50-

60 TLI ABORTS

TLI Aborts are conta~ned ~n the ESD s~nce the bulk of the funct~ons

concern entry preparat20ns and performance Th~s allows a s2nglesource of procedures for procedure rev2ew val~dat~on checkout andtra~n~ng These procedures ~ncorporate TLI preparat20ns as found ~n

reference 6 w~th the TLI Abort Procedures and these t~e 2nto normallunar return Entry Procedures found ~n sect20n 5 The guidel~nes

for th~s cont2ngency are spec2f2ed 2n reference 7

In2t2al preparat~ons for TLI pos2t20n the necessary system sW2tches2n add~t~on to perform~ng an EMS ~V test and a GDC al~gnment Afterthe DET ~s set for mon2tor2ng TB6 the CMP ~ncreases the 12ght levelof the LEB DSKY to max~mum and returns to the h2s couch Th2s 2Sdone so that the LEB DSKY can be observed ~n the event sunl~ght orreflect20ns wash out the ma2n d2splay panel DSKY dur2ng cr2t2calmaneuvers The crew then straps ~n and prepares for mon2tor~ng TB6as 2nd2cated by the SII SEP L~te The t2mes se~uence of procedures2S keyed on th~s d~splay and ~ncludes the DET START funct~on andSIVB IGNITION Dur2ng the burn the crew mon2tors the FDAIs foratt~tude excurs20ns and abnormal rates report~ng status checks toM~ss2on Control at d2screet t~mes dur2ng the maneuver Upon SIVBSHUTDOWN the eMP records the DSKY d~splayed performance parametersand awa2ts ground conf2rmat~on

The rat~onal for TLI aborts ~s descr~bed 2n reference 7 A summar2shyzat20n 2S extracted to prov2de background and gu2de12nes 2n th2sdocument The abort procedures cover aborts 10 m2nutes after conshyt2ngent SIVE shutdown and aborts 90 m2nutes after normal SIVE shutshydown t2me

The 10 m~nute TLI abort ~s des2gned to be used dur~ng TLI ~n theevent a spacecraft problem develops Wh2Ch can result 2n catastrophe2f ~mmed~ate act~on 2S not taken If the s~tuat20n perm~ts the crewshould always allow the SIVB to complete TLI at wh~ch t~me the groundand crew can perform a malfunct~on analys~s to determ~ne ~f an abort~s adv~sable If a fa~lure occurs that necess2tates the shutdown ofthe SIVB and the ~u~ck return of the crew to earth th~s abort ~s

des~gned to be as ~nsens~t~ve to execut~on errors as poss~ble andst21l be targeted to m2dcorr2dor The burn att~tude w~th the f~ed

hor~zon reference ~s a constant value for any shutdown t~me Theburn durat~on 2S a funct20n of shutdown t2me and 2S ava21able fromcrew charts S~nce the pr~mary purpose of th~s abort ~s to returnto earth as qU2ckly as poss2ble there are no restr2ct20ns as toland~ng locat~on However ~f the t~me to EI is greater than abouttwo hours a midcourse correct20n should be ant~c~pated

The 90 m2nute TLI abort 2S to be used 2f a cr2t2cal subsystem malshyfunct~on ~s determ2ned and the dec2s~on to abort ~s made after the

-51-

TLI cutoff and before TLI cutoff plus approxlmately 80 m1nutesTh1S allows suff1c1ent separatlon and procedural t1me to set upfor the SPS deorb1t burn performed at about TLI + 90 Note thatgenerally the deorb1t burns w1ll be performed a fe11 m1nutes beforeTLI + 90 accord1ng to crew charts shown In reference 8 The no-comm except10n requ1res that 90 m1nutes be the 1nput t1me of 19n1shytlon for P-37 (onboard return-to-earth abort program) so that onshyboard calculatlons can correspond w1th ground calculat10ns to computethe CM land1ng p01nt Th1S TLI abort lS des1gned so that returnfl1ght t1me does not exceed 18 hours and abort ~V does not exceed7000 fps ThlS abort can be performed uSlng chart ~Vs and attltudesand the earths hor1zon serves as a suff1c1ent reference The maneushyver lS targeted to ach1eve the mldcorr1dor entry target Ilne andtlmed to result 1n a deslgnated recovery area

It 1S ObV10US for abort deC1S1ons early 1n the TLI + 90 m1nute t1meshyframe that a GampN SPS burn should be performed In order to keep theTLI abort procedures cons1stent and w1th emphasls on slmpl1c1ty theprocedures here reflect a SCS SPS abort burn to cover the full abortdec1s1on t1meframe

A m1dcourse correct1on for corr1dor control after a TLI abort may bedeS1red 1f the SPS burn d1d not meet expectat1ons The TLIabortprocedures 1n th1S sect10n adapt to the normal lunar return tlmel1neand procedures pr10r to the f1nal MCC

-52-

61 TLI PREPARATION PROCEDURES

GET = 150

CRO AOS(___)

CRO LOS( )(22142)

5100

Don Helmets amp Gloves

XLUNAR - INJECT (verify)EDS PWR - on (venfy)EMS FUNC - OFF (verlfy)EMS MODE - STBYEMS FUNC - IW SETVHF RNGEMS MODE - NORMALSet ~V indo to +15868 fpsEMS FUMC - ~V Test

SPS THRUST Lt - onoff (10 sec)~V lnd stops at -01 to -415

EMS MODE - STBYEMS FUMC - ~V SETVHF RNGSet ~VC

EMS FUNC---~~V=----

GDC ALIGNFDAI Select - liZcb SECS LOGIC (Z) - close (verify)cb SECS ARM (Z) - closeSECS LOGIC (Z) - on (up)MSFN Conflrm GO for PYRO ARM (If pass)SECS PYRO ARM (Z) - on (up)TRANS CONTROL PWR - ONROT CONTR PWR NORMAL (Z) - ACDC(verlfy)ROT CONTR PWR DIRECT (Z) - MNAMNBLV INnGPI - SIISIVB (venfy)LV GUID - IU (venfy)cb DIRECT ULLAGE (Z) - closedSet EVENT TIMER to 5100Begin MONITOR For TB6

CMP to Couch

TB 6 - SII SEP Lt on (TIG-9 mln 38 sec)KEY V83E

SET ORDEALFDAI Z ORB RATE at 180 0 0SII SEP Lt out (38 sec later)Start DET COUNTING UPSC CaNT - SCS (verify)MONITOR LV TANK PRESS

~P lt 36 psid (OXID gt FUEL)~P lt Z6 psid (FUEL gt OXID)

EMERGENCY CSMLV SEP UP TLM CM - BLOCK (verify)UP TLM IU - BLOCK (venfy)

-53-

+45degPY))0middot sec PY

lOK nmltHAlt25K nm

Two phas~ng mnvrs two SPS mnvrs to circular~ze at 150 nmearth orb~t

CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ssion 4K nmltHAltlOK nm CSM amp1M - Two phasing mnvrs two SPS mnvrs to circularize at 150 nm earth orb~t CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ss~on

CSM amp 1M - Two phas~ng mnvrs APS burn todepletion th~rd phasing mnvrSPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn tosem~sync orb~t

25K nmltHAlt40K nm CSM amp 1M - Two phasmg mnvrs APS burn to depletion third phas~ng mnvr SPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn to sem~sync orbit HA)40K nm DPS ava~l - DPS LOll circularize with SPS

DPS not ava~l - Lunar flyby or CSM only to lunar orbit (if reqd gtV lt4000 fps)

V37E 47E (check b~as) Record -=--rshy(Limit 98 fpsmm)

( 1fps)tVXYZN62EVIHDOTHPAD (fpsfpslnm)MONITOR VI ( ) at ECO

SCS TVC SERVO PWR 1 - ACIMNA2 - OFF

TAPE RCDR - CMD RESETHBREMS MODE - NORMAL

SIr SEP Lt - ONTLI Inhib~t S~gnals w~11 not be honored after 5942

SIVB ULLAGE BeginsSII SEP Lt - off (TIG - 18 sec)SIVB FUEL LEADSIVB ULLAGE d~scont~nues

LV ENG I Lt - onSIVB IGNITION ( GETI)LV ENG I Lt - off - -shyMONITOR THRUST amp ATTITUDEMONITOR LV TANK PRESSSIVE ECO (Lt on) (BEGIN TB7)

EMER SIVE CUTOFF AT 6 SEC PAST BURN TIME IF VI ATTAINEDTHC CCW ampNEUTRAL IN 1 SEC or SIISIVB sW - LV STAGEPremature Shutdown HAlt4K nm CSM amp 1M -

5700

58205836

F 16 835800

F 16 62

5838594259525955595900000002SUNRISE(___)

HAW AOS(__=_) KEY VERB (freeze d~splay)

SIVB ATT HOLD 20 sec amp BEGIN VENTINGSIVB NNVR TO ORB RT (HDS DN) (3middot sec)

Record VI -c---HDOT _

HPAD _

KEY RLSEF 16 62

F 16 83

HAW LOS(__=-)

KEYmiddotRLSE~VXYZ (lfps)

Record ~VX---_

~vy

WZ--

AVC---_

TAPE RCDR - off (ctr)EMS MODE - STBYEMS FUNC - OFFSECS PYRO ARM (2) - SAFE

PRO

BURN STATUS REPORT

____--~TIG

BT------VGX____-R

-----P----_Y

REMARKS

_____VI

______--HDOT______--H______---AVC______---FUEL_______OXID

_______UNBAL

F 3708=00 OOEGOS AOS CMP TO LEB

(-=-=-)

0000

0003

0005

0014

0100

-55-

62 TLI 10 MIN ABORTSECS LOGIC (2) - on (up)SECS PYRO ARM (2) - ARM

TRANS CONTR - CGH (4 sec) amp +XDET RESET (verlfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS GMD-ON

TRANS GONTR - neutral then +X for10 sec

SIVBGPI s~ - GPIExcesslve rates 6V THRUST A - NORMAL SPS THRUST - DIRECT When rates damped 6V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

TRANS CONTR +X - OFFV37E OOE

PITGH UP to LOGAL VERT (+X axlSto~ard the earth)

RATE - LOWBMAG MODE (3) - ATTIRATE 2EDS PHR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SEGS ARM (2) - opencb EDS (3) - open

TRANS CONTR -X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (180deg)P (199deg)Y (0deg)

RETRO UPDATEGETI _

JV _VG

Jtb ---GET 400K _

05G _GET DROGUE _

ENTRY P _R _

Y_--

0945

-56-

ALIGN HORIZ ON RET +1 MKGMBL CHECK (T11lle Pentattlng)MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conflnn)cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FUMC - JV SETVHF RNGSET JV from chartE~S FUMC - JVEMS fODE - NOIDlAL

lV THRUST A - NORMALV37E 47E (THRUST fONITOR)

F 16 83 lVXYZ (1 fps)

0950

1000

NOTE For aborts durlng 1st mln of TLIKEY V82E F 16 44 (HaHpTff)Burn untll Hp lt 19NM

TRANS CONTR +X

THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN JV reqdJV THRUST (2) - OFFReport cutoff

cb SPS P2 Y2- closeGfBL MTRS (4) - OFF (LMP Confinn)TRANS CONT PWR - OFFTVC SERVO PWR (2) - OFFMN BUS TIE (2) - OFFcb SPS P1amp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREIf est time to EIltOl5500 omlt fCC andenter the SUPERCIRC CKLIST as early as pos-slb1e Pg ~2~3~ __If est time to EI)Ol5500 anticlpate afCC Enter the ENTRY PREP CKLIST at step 9pg 18

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

-2tl C

l I W gt- ~-4

z laquo I I- 0 -6

l- I J u gt- ~-8

z w w -10

~_ONSANT

9O

VER

SHO

OT

BOU

ND

ARY

LIF

TV

EC

TOR

OR

IEN

TATI

ON

LIN

E

SH

ALL

OW

TAR

GE

TLI

NE

STE

EP

TAR

GE

TLI

NE 12

gU

ND

ERSH

OO

TBO

UN

DAR

Y

RE

EN

TRY

CO

RR

IDO

R

I ~ I

-12 24

26

28

30

32

34

RE

EN

TRY

VE

LOC

ITY

VE

1-F

TS

EC

Ch

art

1

36

3B

6-i

~

5CM

CC

ON

ST

NT

DR

VI z gt

~

I4

0 Cl W

I

gtamp

J+

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J Cl z

2U

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bull-1

+-

u ubullbull

~r

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)

2829

JOn

J23

33

43

5IN

ER

TIA

LR

EE

NTR

YV

ELO

CIT

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T4

00

00

0fl

VE

I-F

TS

EC

Ch

art

2

J63

73

8X

03

-i- rtREQUIRED PITCH GIMBAL ANG LETO OBTAIN HOR-IZON AT 317

DEGREES IN wiiiiDOW

260

z~I- ~ i5 24000

1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

-I

-1-

NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

I LU HD~-

LUHD

lt0 120UJ0

~

80 HOLD PRESENT TRIMgt LU HD013

~Y~HOIgtlt

TOP OF WINDOWa 40to

31 7 SCRIBEaaI

80 TTOM OF WINDOWi= 0

0--ltoa

-40t-z

~~~Uw w u lt0 -80

HOLO PRESENT TRIlJCl

LOHU0 lt0

J gt -120 HOLD 059 TRIMlt0 z

LDHUlt0 FIELD OF VI S10 NLDHU LIFT-DOWNHEADS -UPLUHD LIFT-UP HEADS-DOWN

~~H~-160 q - P63 LIMITI- NOrE-VALIO ONLY FO~t~--

LUNAR RETURN VELOCITY

plusmnl8020 244middot 8 12 16

TIME TO 400K FT ALTITUDE-MIN

4

P37

LONG

ITUD

ECO

RREC

TION

TOOB

TAIN

1350

NM

ENTR

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0

2I

U~

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cgt

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gt z 0 J ltJ

1 -0

340

344

348

352

356

364

368

x10

3

CMC

INER

TIAL

VELO

CITY

AT40

0KAL

TITU

DE-

FTS

EC

Ch

art

5

I l I

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20 100 -40

-10

-50

30

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A+

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=----

-----

t~I

AB

SA_

-04

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AV

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-0

2030

NOTE

40

NO

MIN

AL

RET

RB

=22

MIN

30

-40

-50

---------O

VE

RB

UR

N---------I------U

ND

ER

BU

RN

------I

~30

-20

-tD

010

20

AA

VX

FTS

EC

-60

Ch

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6

1000

0 90

00 70

00 60

00 i50

00 iMl

OO ilOO

O i20

00 10

00 o

040

120

200

EMS

6V-

FTS

EC

240

320

400

440

520

S-IV

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RN-

NSE

C

105

0

I 1- I

I

LAUN

CHAZ

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H

72r

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ml

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=199

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0

TLI

-10

MIN

ABO

RTLA

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DEC

21

1968

400050

z =gt co23

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~7 X ampJ V

gt ~ 6

2627

~B

~n

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FF)middot

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EC34

3536

Xllf

Ch

art

7

7

1000

0i

0-00

EMS

V-F

TSE

C90

0080

0070

0060

0050

0040

0030

0020

0010

000

II

II

II

II

S-IV

BBU

RNTI

ME

-M

INSE

Cll-

41)

120

200

241)

320

400

441)

520

TlI

-I0

MIN

ABOR

TlA

UNCH

-DE

C21

19

68

lAUN

CHA

ZIM

UTH

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3

-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 41: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

-38-

20 F SO 25 00204 GMBL TEST OPTION(ACCEPT) SC CONT - GMC (ver~fy)

PROMonitor GPI Response

0020-2000020-200Tr~m

TEST FAIL SC CONT - SCS SCS TVC (2) - AUTO

(REJECT) ENTR

21 06 40 TFIVG~VM (m~n-sec1fps)

PROG ALM - TIG s1~pped

V5N9E 01703

KEY RLSE To 21 ROT CONTR PWR DIRECT (2) - MNABSPS He v1vs (2) - AUTO (ver~fy)

LIMIT CYCLE - OFFFDAI SCALE - SOIScb SPS P2Y2 - open (for cr~t burn)

5800(-02 00)

5925(-0035)

59middot 30(-0030)

06 40

59XX(-OOXX)

AV THRUST A(B) - NORMALTHC - ARMEDRlIC (2) - ARMEDTAPE RCDR - GID RESETHBR

DSKY BLANKS

(AVE G ON)EMS MODE - NORMAL

TFIVG~VM (m~n-seclfps)

CHECK PIPA BIAS lt2fps for 5 sec

ULLAGE AS REQ

IF NO ULLAGE DIR ULLAGE PB - PUSH~

CONTROL ATT WRlIC MONITOR AVM (R3) COUNTING UP

5955(-0005)

F 99 40 ENG ON ENABLE REQUEST(AUTO IGN) PRO AT TFI gt0 sec(BYPASS IGN) ENTR to 24

22 0000 IGN

-39-

If SCS - THRUST ON PB - PUSH

06 40 TFCVG~VM (m~n-seclfpslfps)

~F 97 40 SPS Thrust fall ~

~(RESTART) PRO To IGN (RECYCLE) ENTR To TIG-05 sec

SPS THRUST LITE - ONMONITOR THRUSTING

Pc 95-105 pSlaEMS COUNTING DOWNSPS IN3 v1vs (4) - OPENSPS He v1vs tb (2) - graySPS FUELOXID PRESS - 175-195 pSlaPUGS - BALANCED

PROG ALARM V5N9E 01407 VG INCTHC - CW FLY MTVC

ECOEMER SPS CUTOFF J

AV THRUST (2) - OFF

23 F 16 40 TFC(STATIC)VG~VM (mln-seclfps)~V THRUST AB - OFF

SPS IN3 v1vs (4) - CLOSEDSPS He tb (2) - bp

cb SPS P2Y2 - closed (verlfy)TVC SERVO PHR - AC1MNA (venfy)TVC SERVO PWR 2 - OFF

PRO

24 F 16 85 VG XYZ(CM) CUps)NULL RESIDUALSRECORD ~V CTR amp RESIDUALS I1VCEMS FUNC - OFF VGXEMS MODE - STBY VGYBMAG MODE (3) - RATE 2ATT DB - MAX VGZTRANS CONT PHR - OFF

PRO

25 F 37 V82E

26 F 16 44 HAHPTFF (lnmm~n-sec)

R3-59B59 HP gt494 nmPRO

27 F 37 OOE

-40-

55 EARTH ORBIT ENTRY

1 Venfy CMSMR __

P_shyY_-

SEP ATT(180deg)

(0deg )

2

3

4

EMS INITIALIZATIONEMS FUNC - RNG SETSET RNG TO PAD DATA RNGEMS FUNC - VA SETSlew scroll to pad data VIOEMS FUNC - ENTRY

RSI ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on(up)GDC ALIGN PB - PUSH amp HOLDYAW tw - Pos1tion RSI thru 45deg amp

back to LIFl UPGDC ALIGN PB - RELEASEEMS ROLL - OFFAl1gn GDC to lMU

PWR REDUCT (Norm Deorb Only)HGA PWR - OFFFC PUMPS (3) - OFFVer1fy s1ngle suit compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - Lowcb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2)-openlOb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MAN

-41-

P61 - ENTRY PREP

5 V37E 61E05 09 01427 - ROLL REVERSED05 09 01426 - IMU UNSAT

6 F 06 61 IMPACT LAT LONG liDS UPDN (+-)(01 0

010

+00001)

PRO

PAD VALUESLATLON==G------liDS UP DN _

7 F 06 60 GMAXV400KGAMMA EIRecord

GMAXV400K----GAMMA EI _

PRO

8 F 06 63 RTOGO (1nm) PAD _VIa (fps) PADTFE (mln-sec) ----Compare wlth MSFN for PGNS GONO GONO COMM SET RTOGO amp VIO IN EMS amp

INITIALIZE(ACCEPT) PRO(RECALC) V32E to 8

-42-

P62 - CMSM SEP amp PRE-ENTRY MNVR

9 F 50 25 00041 REQUEST CMSM SEPSC CONT - SCSFREEYAW - 45deg out-of-plane (left for RCS

nght for SPS)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE2PRIM GLY to RAD - BYPASS (verlfy)SECS LOGIC (2) - on (up)MSFN conflrm GO for PYRO ARMSECS PYRO ARM - ARMMN BUS TIE (2) - ON (verlfy)CMSM SEF (2) - ONCSMLM FNl SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 pSlaCM RCS LOGIC - OFFSECS PYRO ARM - SAFEMonltor VMAB

If lt25vdc go to EMERG POWERDOWN Pg E6-1AUTO RCS SEL AlC ROLL (4) - OFFAUTO RCS SEL CM 2(6) - OFFAUTO RCS SEL CM 1(6) - MNA or MNBYAW back to 00

PITCH TO ENTRY ATTROLL 0deg (LIFT UP)PITCH - HORIZ on 317deg MARK (400K)YAW 00

ATT DB - MAXMAN ATT (PITCH) - ACCEL CMDEMS DATA - VerifyEMS FUNC - ENTRY (verlfy)EMS MODE - NORMALMAINTAIN HORIZ TRK

PRO (Act ENTRY DAP)

10 F 06 61 IMPACT LAT LONG HDSDN(010 010 -00001)

PRO

11 FOSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axlS beyond 45deg of Vel vector)

-43-

P63 - ENTRY INIT

12 06 64 GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PWR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRHORIZ CKP~tch error needle goes toward

zero approach~ng 05G t~me

MAN ATT (PITCH) - RATE CMDIf CMC ~s GO

BMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS FLY BETA If CMC NO GO ~

SC CONT - SCS~

FLY EMS RCS Deorh Roll HDS UPTRACK HORIZ w~th 29deg w~ndow mk

P64 - ENTRY POST 05G

13

05G t=elt+0___)

06 68

RTOGO AT 05G AGREES WITH EMS - venfyHORIZ CK05E Lt - on (EMS start)

No EMS start w~th~n 3 secsEMS MODE - BACKUP VHF RNG 05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds L~ft DN

NNVR L~ft DNEMS GONO GO

G-V Plot w~th~n llm~ts

Rng ctr dwn 60 + 7 durlng 10 sec per~od

Mon~tor G-meter forconvergence wlth pad data (Do)

(Vlt27K fps) Go To 17

-44-

P65 - ENTRY - UP CONT (Vgt27K fps)

14 F 16 69 BETA (01deg)DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT~

SC CONT - SCS FLY EMS

PRO

15 06 68 BElA VI HOOT (01deg fpsfps)(VltVL +500 fps amp RDOT Neg) Go To 17

p66 - ENTRY - BALLISTIC (DltDL)

16 06 22 DESIRED GMBL ANGLES RPY (01deg)Mon~tor hor~z +12deg of 317deg mark

P67 - ENTRY - FINAL PHASE (02G)

17 0666 BETACRSRNG ERRDNRNG ERR (Oldeglnmlnm)KEY VERBRecord DNRNG ERR _KEY RLSEL~m~t +100nm from PAD DRE

Mon~tor l~ft vector on RSI amp FDAIF 16 67 RTOGOLATLONG (Vre1=1000fps)

(lnm 010 01deg)SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOlfflMon~tor altimeter

Go To EARTHLANDING pg _I4L5__

-45-

56 EARTHLANDING

90K STEAM PRESS - PEGGED50K CABIN PRESS REL vIv (2) - BOOSTENTRY

SECS PYRO ARM (2) - ARM

40K(90K + 63s)

CM UNSTABLE RCS CMD - OFF ~ 40K APEX COVER JETT PG-PUSH DROGUE DEPLOY PG - PUSH (2 secafter apex cover Jett)

30K ELS LOGIC - ON (up)ELS - AUTO

24K RCS hsable (auto)(90K+92s) RCS CMD - OFF

Apex cover Jett (auto)APEX COVER JETT PB - PUSH

(WAIT 2 SECS)Drogue parachutes deployed (auto)

DROGUE DEPLOY PB - PUSH~

If Drogues FallELS - ~ ~Stablllze CM 5K MAIN DPLY PB - PUSHELS - AUTO

235K Cabln Pressure lncreaslng (Drogues + 50s)If not lncreaSlng by 17K CABIN PRESS REL vlv (RR) - DUMP

-46-

10K Maln parachutes deployedMAIN DEPLOY PB - PUSH (wlthln 1 sec)VHF ANT - RECYVHF AMA - SIMPLEXVHF BCN - ONCABIN PRESS REL v1v (2) - CLOSEDIRECT 02 vlv - OPENCM RCS LOGIC - on (up)CM PRPLNT - DUMP (burn audlb1e)Monltor CM ReS 1amp2 for He press decrease

NO BURN or PRESS DECREASE USE BOTH RHCs DO NOT FIRE PITCH JETS

CM PRPLNT-PURGE (to zero He press)CM RCS He DUMP PB - PUSH RHC (2) - 30 sees NO PITCH k

STRUT LOCKS (2) - UNLOCK

cb FLT amp PL BAT BUS ABampBAT C (3) - closecb FLT amp PLT MNA amp B (2) - opencb ECS RAD HTR OVLD (2) - opencb SPS PampY (4) - open

3K CABIN PRESS REL v1v (RH) - DUMP (after purgecompleted)

FLOOD Lts - POST LDGCM RCS PRPLNT (2) - OFFROT CONTR PWR DIRECT (2) - OFF

800 CAB PRESS RELF vlv - CLOSE (latch off)MN BUS TIE (2) - OFF

AFTER LANDINGcb MAIN REL PYRO (2) - closeMAIN RELEASE - on(up)

Go to POSTLANDING pg _47L-__

I

2

3

-47-

57 POSTLANDING

STABILIZATION VENTILATION COMMUNICATIONS

DIRECT 02 vlv - CLOSE

Stablllzation after landlngELS - AUTO (verlfy)cb MAIN REL PYRO (2) - close (venfy)MAIN RELEASE - on (up) (verlfy)S~CS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb BAT RLY BUS (2) - open

No contact w1th recovery forcesVHF AM AampB - off (ctr) ~

VHF AM Rev ONLY - A cb PL VENT - closecb FLOAT BAG (3) - closecb UPRIGHT SYS COMPRESS (2) - closeIf Stable II

FLOAT BAG(3)-FILL t1ll 2 m1n afterupr1ght then - OFF

VHF AM AlB amp BCN - OFF whlle lnvertedIf Stable I

After 10 M1n Coollng Per1odFLOAT BAG (3) - FILL 7 mln then OFF

Post Stab1lizat1on And Ventllat10nPL BCN LT - BCN LT LOWPL VENT vlv - UNLOCK (Pull)Remove PL VENT Exh CoverPL VENT - HIGH or LOWPL DYE MARKER - ON (swlmmer comm)Release foots traps and_restralntscb MNA BAT BUS A amp BAT C (2) - opencb MNB BAT BUS B amp BAT C (2) - opencb FLT amp PL BAT C - opencb PYRO A SEQ A - opencb PYRO B SEQ B - open

EACH HR - CHECK DC VOLTSgt 275 V If Notmiddot cb FLT amp PL-BAT BUS AampB (2) -open cb FLT amp PL BAT C (1) - open GO TO LOW POWER CHECKLIST

Unstow and lnstall PLV DISTRIB DUCTDeploy grappllng hook and 11ne 1f req

4

-48-

Post Landing Communlcatl0nsVHF ANT-RECY (venfy)VHF BCN - ON (verlfy)

If no contact ~lth recovery forcesperform VHF BEACON Check

MONITOR VHF BEACON transmlSSlonnth VHF AM B Rcvr andor Su)vlval

TransceiverkVHF Beacon not operatlng ~connect Surv~val TranscelVer to antcable behlnd VHF ant access pnland place radio ln BCN mode

LOW POHER CHECKLISTVHF BCN - OFFVHF AM (3) - RCVFLOOD Lts - OFFVHF AM AampB - off (ctr)VHF AM RCV ONLY - A (venfy)COUCH LIGHTS - OFFPOSTLANDING VENT SYS mlnlmlze useSURV RADIO - plug mto VHF BCN ANT cableconn behind VHF ant acess pnl amp turn radloon l-n BCN mode

EGRESS PROCEDURES

CMPCDRLMPCDR

CMPCDRCMP

LMPLl1PCDR

STABLE IDlsconnect Umblll-calsNeck darn onCenter couch - 270 0 positionArmrests stowedConnect raft to SIC l-f desl-red wlth

green lanyardConnect raft ~hl-te lanyards to SUltS amp

lnflate water wlngs when eXltl-ngHATCH PISTON PRESS vlv - PRESS (Outbd)Slde Hatch openedPL VENT - OFFcb Pnl 250 (all) - openEgress with 11feraftPut hardware klt outEgress

or CDIPALL

CMF

CDRCMF

CDR

LMF

CMFCMP LMFCMP

UlP

CDR

-49-

STABLE IIcb CREW STA AUDIO (3) - openD~sconnect umb~1~ca1s

Release foots trapsRelease restra~nt harnessCouch seat pans (3) - 170 0 pos1t10nArm rests stowedSurv1va1 k~ts removed from stowageConnect life raft ma~n1~ne to CDR or SicConnect f~rst wh~te lanyard from

11fe raft to suitConnect th~rd wh~te lanyard from

l~fe raft to SU1tConnect rucksacks together to yellow

lanyard on raft bagPRESSURE EQUALIZATION vlv - OPENRemove and stow fwd hatchEX1t feet f1rst w1th rucksacks when clear

of siC 1nflate water w1ngs and raftExit feet f1rst when clear of SiC

1nflate water w1ngsEX1t feet f1rst when clear of sic

1nflate water w1ngs

-50-

60 TLI ABORTS

TLI Aborts are conta~ned ~n the ESD s~nce the bulk of the funct~ons

concern entry preparat20ns and performance Th~s allows a s2nglesource of procedures for procedure rev2ew val~dat~on checkout andtra~n~ng These procedures ~ncorporate TLI preparat20ns as found ~n

reference 6 w~th the TLI Abort Procedures and these t~e 2nto normallunar return Entry Procedures found ~n sect20n 5 The guidel~nes

for th~s cont2ngency are spec2f2ed 2n reference 7

In2t2al preparat~ons for TLI pos2t20n the necessary system sW2tches2n add~t~on to perform~ng an EMS ~V test and a GDC al~gnment Afterthe DET ~s set for mon2tor2ng TB6 the CMP ~ncreases the 12ght levelof the LEB DSKY to max~mum and returns to the h2s couch Th2s 2Sdone so that the LEB DSKY can be observed ~n the event sunl~ght orreflect20ns wash out the ma2n d2splay panel DSKY dur2ng cr2t2calmaneuvers The crew then straps ~n and prepares for mon2tor~ng TB6as 2nd2cated by the SII SEP L~te The t2mes se~uence of procedures2S keyed on th~s d~splay and ~ncludes the DET START funct~on andSIVB IGNITION Dur2ng the burn the crew mon2tors the FDAIs foratt~tude excurs20ns and abnormal rates report~ng status checks toM~ss2on Control at d2screet t~mes dur2ng the maneuver Upon SIVBSHUTDOWN the eMP records the DSKY d~splayed performance parametersand awa2ts ground conf2rmat~on

The rat~onal for TLI aborts ~s descr~bed 2n reference 7 A summar2shyzat20n 2S extracted to prov2de background and gu2de12nes 2n th2sdocument The abort procedures cover aborts 10 m2nutes after conshyt2ngent SIVE shutdown and aborts 90 m2nutes after normal SIVE shutshydown t2me

The 10 m~nute TLI abort ~s des2gned to be used dur~ng TLI ~n theevent a spacecraft problem develops Wh2Ch can result 2n catastrophe2f ~mmed~ate act~on 2S not taken If the s~tuat20n perm~ts the crewshould always allow the SIVB to complete TLI at wh~ch t~me the groundand crew can perform a malfunct~on analys~s to determ~ne ~f an abort~s adv~sable If a fa~lure occurs that necess2tates the shutdown ofthe SIVB and the ~u~ck return of the crew to earth th~s abort ~s

des~gned to be as ~nsens~t~ve to execut~on errors as poss~ble andst21l be targeted to m2dcorr2dor The burn att~tude w~th the f~ed

hor~zon reference ~s a constant value for any shutdown t~me Theburn durat~on 2S a funct20n of shutdown t2me and 2S ava21able fromcrew charts S~nce the pr~mary purpose of th~s abort ~s to returnto earth as qU2ckly as poss2ble there are no restr2ct20ns as toland~ng locat~on However ~f the t~me to EI is greater than abouttwo hours a midcourse correct20n should be ant~c~pated

The 90 m2nute TLI abort 2S to be used 2f a cr2t2cal subsystem malshyfunct~on ~s determ2ned and the dec2s~on to abort ~s made after the

-51-

TLI cutoff and before TLI cutoff plus approxlmately 80 m1nutesTh1S allows suff1c1ent separatlon and procedural t1me to set upfor the SPS deorb1t burn performed at about TLI + 90 Note thatgenerally the deorb1t burns w1ll be performed a fe11 m1nutes beforeTLI + 90 accord1ng to crew charts shown In reference 8 The no-comm except10n requ1res that 90 m1nutes be the 1nput t1me of 19n1shytlon for P-37 (onboard return-to-earth abort program) so that onshyboard calculatlons can correspond w1th ground calculat10ns to computethe CM land1ng p01nt Th1S TLI abort lS des1gned so that returnfl1ght t1me does not exceed 18 hours and abort ~V does not exceed7000 fps ThlS abort can be performed uSlng chart ~Vs and attltudesand the earths hor1zon serves as a suff1c1ent reference The maneushyver lS targeted to ach1eve the mldcorr1dor entry target Ilne andtlmed to result 1n a deslgnated recovery area

It 1S ObV10US for abort deC1S1ons early 1n the TLI + 90 m1nute t1meshyframe that a GampN SPS burn should be performed In order to keep theTLI abort procedures cons1stent and w1th emphasls on slmpl1c1ty theprocedures here reflect a SCS SPS abort burn to cover the full abortdec1s1on t1meframe

A m1dcourse correct1on for corr1dor control after a TLI abort may bedeS1red 1f the SPS burn d1d not meet expectat1ons The TLIabortprocedures 1n th1S sect10n adapt to the normal lunar return tlmel1neand procedures pr10r to the f1nal MCC

-52-

61 TLI PREPARATION PROCEDURES

GET = 150

CRO AOS(___)

CRO LOS( )(22142)

5100

Don Helmets amp Gloves

XLUNAR - INJECT (verify)EDS PWR - on (venfy)EMS FUNC - OFF (verlfy)EMS MODE - STBYEMS FUNC - IW SETVHF RNGEMS MODE - NORMALSet ~V indo to +15868 fpsEMS FUMC - ~V Test

SPS THRUST Lt - onoff (10 sec)~V lnd stops at -01 to -415

EMS MODE - STBYEMS FUMC - ~V SETVHF RNGSet ~VC

EMS FUNC---~~V=----

GDC ALIGNFDAI Select - liZcb SECS LOGIC (Z) - close (verify)cb SECS ARM (Z) - closeSECS LOGIC (Z) - on (up)MSFN Conflrm GO for PYRO ARM (If pass)SECS PYRO ARM (Z) - on (up)TRANS CONTROL PWR - ONROT CONTR PWR NORMAL (Z) - ACDC(verlfy)ROT CONTR PWR DIRECT (Z) - MNAMNBLV INnGPI - SIISIVB (venfy)LV GUID - IU (venfy)cb DIRECT ULLAGE (Z) - closedSet EVENT TIMER to 5100Begin MONITOR For TB6

CMP to Couch

TB 6 - SII SEP Lt on (TIG-9 mln 38 sec)KEY V83E

SET ORDEALFDAI Z ORB RATE at 180 0 0SII SEP Lt out (38 sec later)Start DET COUNTING UPSC CaNT - SCS (verify)MONITOR LV TANK PRESS

~P lt 36 psid (OXID gt FUEL)~P lt Z6 psid (FUEL gt OXID)

EMERGENCY CSMLV SEP UP TLM CM - BLOCK (verify)UP TLM IU - BLOCK (venfy)

-53-

+45degPY))0middot sec PY

lOK nmltHAlt25K nm

Two phas~ng mnvrs two SPS mnvrs to circular~ze at 150 nmearth orb~t

CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ssion 4K nmltHAltlOK nm CSM amp1M - Two phasing mnvrs two SPS mnvrs to circularize at 150 nm earth orb~t CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ss~on

CSM amp 1M - Two phas~ng mnvrs APS burn todepletion th~rd phasing mnvrSPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn tosem~sync orb~t

25K nmltHAlt40K nm CSM amp 1M - Two phasmg mnvrs APS burn to depletion third phas~ng mnvr SPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn to sem~sync orbit HA)40K nm DPS ava~l - DPS LOll circularize with SPS

DPS not ava~l - Lunar flyby or CSM only to lunar orbit (if reqd gtV lt4000 fps)

V37E 47E (check b~as) Record -=--rshy(Limit 98 fpsmm)

( 1fps)tVXYZN62EVIHDOTHPAD (fpsfpslnm)MONITOR VI ( ) at ECO

SCS TVC SERVO PWR 1 - ACIMNA2 - OFF

TAPE RCDR - CMD RESETHBREMS MODE - NORMAL

SIr SEP Lt - ONTLI Inhib~t S~gnals w~11 not be honored after 5942

SIVB ULLAGE BeginsSII SEP Lt - off (TIG - 18 sec)SIVB FUEL LEADSIVB ULLAGE d~scont~nues

LV ENG I Lt - onSIVB IGNITION ( GETI)LV ENG I Lt - off - -shyMONITOR THRUST amp ATTITUDEMONITOR LV TANK PRESSSIVE ECO (Lt on) (BEGIN TB7)

EMER SIVE CUTOFF AT 6 SEC PAST BURN TIME IF VI ATTAINEDTHC CCW ampNEUTRAL IN 1 SEC or SIISIVB sW - LV STAGEPremature Shutdown HAlt4K nm CSM amp 1M -

5700

58205836

F 16 835800

F 16 62

5838594259525955595900000002SUNRISE(___)

HAW AOS(__=_) KEY VERB (freeze d~splay)

SIVB ATT HOLD 20 sec amp BEGIN VENTINGSIVB NNVR TO ORB RT (HDS DN) (3middot sec)

Record VI -c---HDOT _

HPAD _

KEY RLSEF 16 62

F 16 83

HAW LOS(__=-)

KEYmiddotRLSE~VXYZ (lfps)

Record ~VX---_

~vy

WZ--

AVC---_

TAPE RCDR - off (ctr)EMS MODE - STBYEMS FUNC - OFFSECS PYRO ARM (2) - SAFE

PRO

BURN STATUS REPORT

____--~TIG

BT------VGX____-R

-----P----_Y

REMARKS

_____VI

______--HDOT______--H______---AVC______---FUEL_______OXID

_______UNBAL

F 3708=00 OOEGOS AOS CMP TO LEB

(-=-=-)

0000

0003

0005

0014

0100

-55-

62 TLI 10 MIN ABORTSECS LOGIC (2) - on (up)SECS PYRO ARM (2) - ARM

TRANS CONTR - CGH (4 sec) amp +XDET RESET (verlfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS GMD-ON

TRANS GONTR - neutral then +X for10 sec

SIVBGPI s~ - GPIExcesslve rates 6V THRUST A - NORMAL SPS THRUST - DIRECT When rates damped 6V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

TRANS CONTR +X - OFFV37E OOE

PITGH UP to LOGAL VERT (+X axlSto~ard the earth)

RATE - LOWBMAG MODE (3) - ATTIRATE 2EDS PHR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SEGS ARM (2) - opencb EDS (3) - open

TRANS CONTR -X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (180deg)P (199deg)Y (0deg)

RETRO UPDATEGETI _

JV _VG

Jtb ---GET 400K _

05G _GET DROGUE _

ENTRY P _R _

Y_--

0945

-56-

ALIGN HORIZ ON RET +1 MKGMBL CHECK (T11lle Pentattlng)MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conflnn)cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FUMC - JV SETVHF RNGSET JV from chartE~S FUMC - JVEMS fODE - NOIDlAL

lV THRUST A - NORMALV37E 47E (THRUST fONITOR)

F 16 83 lVXYZ (1 fps)

0950

1000

NOTE For aborts durlng 1st mln of TLIKEY V82E F 16 44 (HaHpTff)Burn untll Hp lt 19NM

TRANS CONTR +X

THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN JV reqdJV THRUST (2) - OFFReport cutoff

cb SPS P2 Y2- closeGfBL MTRS (4) - OFF (LMP Confinn)TRANS CONT PWR - OFFTVC SERVO PWR (2) - OFFMN BUS TIE (2) - OFFcb SPS P1amp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREIf est time to EIltOl5500 omlt fCC andenter the SUPERCIRC CKLIST as early as pos-slb1e Pg ~2~3~ __If est time to EI)Ol5500 anticlpate afCC Enter the ENTRY PREP CKLIST at step 9pg 18

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

-2tl C

l I W gt- ~-4

z laquo I I- 0 -6

l- I J u gt- ~-8

z w w -10

~_ONSANT

9O

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LIF

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TOR

OR

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TATI

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LIN

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SH

ALL

OW

TAR

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TLI

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STE

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TAR

GE

TLI

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gU

ND

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OO

TBO

UN

DAR

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RE

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TRY

CO

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IDO

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-12 24

26

28

30

32

34

RE

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TRY

VE

LOC

ITY

VE

1-F

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6-i

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73

8X

03

-i- rtREQUIRED PITCH GIMBAL ANG LETO OBTAIN HOR-IZON AT 317

DEGREES IN wiiiiDOW

260

z~I- ~ i5 24000

1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

-I

-1-

NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

I LU HD~-

LUHD

lt0 120UJ0

~

80 HOLD PRESENT TRIMgt LU HD013

~Y~HOIgtlt

TOP OF WINDOWa 40to

31 7 SCRIBEaaI

80 TTOM OF WINDOWi= 0

0--ltoa

-40t-z

~~~Uw w u lt0 -80

HOLO PRESENT TRIlJCl

LOHU0 lt0

J gt -120 HOLD 059 TRIMlt0 z

LDHUlt0 FIELD OF VI S10 NLDHU LIFT-DOWNHEADS -UPLUHD LIFT-UP HEADS-DOWN

~~H~-160 q - P63 LIMITI- NOrE-VALIO ONLY FO~t~--

LUNAR RETURN VELOCITY

plusmnl8020 244middot 8 12 16

TIME TO 400K FT ALTITUDE-MIN

4

P37

LONG

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TOOB

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344

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352

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120

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1968

400050

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2627

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Cll-

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120

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320

400

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3

-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 42: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

22 0000 IGN

-39-

If SCS - THRUST ON PB - PUSH

06 40 TFCVG~VM (m~n-seclfpslfps)

~F 97 40 SPS Thrust fall ~

~(RESTART) PRO To IGN (RECYCLE) ENTR To TIG-05 sec

SPS THRUST LITE - ONMONITOR THRUSTING

Pc 95-105 pSlaEMS COUNTING DOWNSPS IN3 v1vs (4) - OPENSPS He v1vs tb (2) - graySPS FUELOXID PRESS - 175-195 pSlaPUGS - BALANCED

PROG ALARM V5N9E 01407 VG INCTHC - CW FLY MTVC

ECOEMER SPS CUTOFF J

AV THRUST (2) - OFF

23 F 16 40 TFC(STATIC)VG~VM (mln-seclfps)~V THRUST AB - OFF

SPS IN3 v1vs (4) - CLOSEDSPS He tb (2) - bp

cb SPS P2Y2 - closed (verlfy)TVC SERVO PHR - AC1MNA (venfy)TVC SERVO PWR 2 - OFF

PRO

24 F 16 85 VG XYZ(CM) CUps)NULL RESIDUALSRECORD ~V CTR amp RESIDUALS I1VCEMS FUNC - OFF VGXEMS MODE - STBY VGYBMAG MODE (3) - RATE 2ATT DB - MAX VGZTRANS CONT PHR - OFF

PRO

25 F 37 V82E

26 F 16 44 HAHPTFF (lnmm~n-sec)

R3-59B59 HP gt494 nmPRO

27 F 37 OOE

-40-

55 EARTH ORBIT ENTRY

1 Venfy CMSMR __

P_shyY_-

SEP ATT(180deg)

(0deg )

2

3

4

EMS INITIALIZATIONEMS FUNC - RNG SETSET RNG TO PAD DATA RNGEMS FUNC - VA SETSlew scroll to pad data VIOEMS FUNC - ENTRY

RSI ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on(up)GDC ALIGN PB - PUSH amp HOLDYAW tw - Pos1tion RSI thru 45deg amp

back to LIFl UPGDC ALIGN PB - RELEASEEMS ROLL - OFFAl1gn GDC to lMU

PWR REDUCT (Norm Deorb Only)HGA PWR - OFFFC PUMPS (3) - OFFVer1fy s1ngle suit compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - Lowcb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2)-openlOb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MAN

-41-

P61 - ENTRY PREP

5 V37E 61E05 09 01427 - ROLL REVERSED05 09 01426 - IMU UNSAT

6 F 06 61 IMPACT LAT LONG liDS UPDN (+-)(01 0

010

+00001)

PRO

PAD VALUESLATLON==G------liDS UP DN _

7 F 06 60 GMAXV400KGAMMA EIRecord

GMAXV400K----GAMMA EI _

PRO

8 F 06 63 RTOGO (1nm) PAD _VIa (fps) PADTFE (mln-sec) ----Compare wlth MSFN for PGNS GONO GONO COMM SET RTOGO amp VIO IN EMS amp

INITIALIZE(ACCEPT) PRO(RECALC) V32E to 8

-42-

P62 - CMSM SEP amp PRE-ENTRY MNVR

9 F 50 25 00041 REQUEST CMSM SEPSC CONT - SCSFREEYAW - 45deg out-of-plane (left for RCS

nght for SPS)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE2PRIM GLY to RAD - BYPASS (verlfy)SECS LOGIC (2) - on (up)MSFN conflrm GO for PYRO ARMSECS PYRO ARM - ARMMN BUS TIE (2) - ON (verlfy)CMSM SEF (2) - ONCSMLM FNl SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 pSlaCM RCS LOGIC - OFFSECS PYRO ARM - SAFEMonltor VMAB

If lt25vdc go to EMERG POWERDOWN Pg E6-1AUTO RCS SEL AlC ROLL (4) - OFFAUTO RCS SEL CM 2(6) - OFFAUTO RCS SEL CM 1(6) - MNA or MNBYAW back to 00

PITCH TO ENTRY ATTROLL 0deg (LIFT UP)PITCH - HORIZ on 317deg MARK (400K)YAW 00

ATT DB - MAXMAN ATT (PITCH) - ACCEL CMDEMS DATA - VerifyEMS FUNC - ENTRY (verlfy)EMS MODE - NORMALMAINTAIN HORIZ TRK

PRO (Act ENTRY DAP)

10 F 06 61 IMPACT LAT LONG HDSDN(010 010 -00001)

PRO

11 FOSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axlS beyond 45deg of Vel vector)

-43-

P63 - ENTRY INIT

12 06 64 GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PWR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRHORIZ CKP~tch error needle goes toward

zero approach~ng 05G t~me

MAN ATT (PITCH) - RATE CMDIf CMC ~s GO

BMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS FLY BETA If CMC NO GO ~

SC CONT - SCS~

FLY EMS RCS Deorh Roll HDS UPTRACK HORIZ w~th 29deg w~ndow mk

P64 - ENTRY POST 05G

13

05G t=elt+0___)

06 68

RTOGO AT 05G AGREES WITH EMS - venfyHORIZ CK05E Lt - on (EMS start)

No EMS start w~th~n 3 secsEMS MODE - BACKUP VHF RNG 05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds L~ft DN

NNVR L~ft DNEMS GONO GO

G-V Plot w~th~n llm~ts

Rng ctr dwn 60 + 7 durlng 10 sec per~od

Mon~tor G-meter forconvergence wlth pad data (Do)

(Vlt27K fps) Go To 17

-44-

P65 - ENTRY - UP CONT (Vgt27K fps)

14 F 16 69 BETA (01deg)DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT~

SC CONT - SCS FLY EMS

PRO

15 06 68 BElA VI HOOT (01deg fpsfps)(VltVL +500 fps amp RDOT Neg) Go To 17

p66 - ENTRY - BALLISTIC (DltDL)

16 06 22 DESIRED GMBL ANGLES RPY (01deg)Mon~tor hor~z +12deg of 317deg mark

P67 - ENTRY - FINAL PHASE (02G)

17 0666 BETACRSRNG ERRDNRNG ERR (Oldeglnmlnm)KEY VERBRecord DNRNG ERR _KEY RLSEL~m~t +100nm from PAD DRE

Mon~tor l~ft vector on RSI amp FDAIF 16 67 RTOGOLATLONG (Vre1=1000fps)

(lnm 010 01deg)SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOlfflMon~tor altimeter

Go To EARTHLANDING pg _I4L5__

-45-

56 EARTHLANDING

90K STEAM PRESS - PEGGED50K CABIN PRESS REL vIv (2) - BOOSTENTRY

SECS PYRO ARM (2) - ARM

40K(90K + 63s)

CM UNSTABLE RCS CMD - OFF ~ 40K APEX COVER JETT PG-PUSH DROGUE DEPLOY PG - PUSH (2 secafter apex cover Jett)

30K ELS LOGIC - ON (up)ELS - AUTO

24K RCS hsable (auto)(90K+92s) RCS CMD - OFF

Apex cover Jett (auto)APEX COVER JETT PB - PUSH

(WAIT 2 SECS)Drogue parachutes deployed (auto)

DROGUE DEPLOY PB - PUSH~

If Drogues FallELS - ~ ~Stablllze CM 5K MAIN DPLY PB - PUSHELS - AUTO

235K Cabln Pressure lncreaslng (Drogues + 50s)If not lncreaSlng by 17K CABIN PRESS REL vlv (RR) - DUMP

-46-

10K Maln parachutes deployedMAIN DEPLOY PB - PUSH (wlthln 1 sec)VHF ANT - RECYVHF AMA - SIMPLEXVHF BCN - ONCABIN PRESS REL v1v (2) - CLOSEDIRECT 02 vlv - OPENCM RCS LOGIC - on (up)CM PRPLNT - DUMP (burn audlb1e)Monltor CM ReS 1amp2 for He press decrease

NO BURN or PRESS DECREASE USE BOTH RHCs DO NOT FIRE PITCH JETS

CM PRPLNT-PURGE (to zero He press)CM RCS He DUMP PB - PUSH RHC (2) - 30 sees NO PITCH k

STRUT LOCKS (2) - UNLOCK

cb FLT amp PL BAT BUS ABampBAT C (3) - closecb FLT amp PLT MNA amp B (2) - opencb ECS RAD HTR OVLD (2) - opencb SPS PampY (4) - open

3K CABIN PRESS REL v1v (RH) - DUMP (after purgecompleted)

FLOOD Lts - POST LDGCM RCS PRPLNT (2) - OFFROT CONTR PWR DIRECT (2) - OFF

800 CAB PRESS RELF vlv - CLOSE (latch off)MN BUS TIE (2) - OFF

AFTER LANDINGcb MAIN REL PYRO (2) - closeMAIN RELEASE - on(up)

Go to POSTLANDING pg _47L-__

I

2

3

-47-

57 POSTLANDING

STABILIZATION VENTILATION COMMUNICATIONS

DIRECT 02 vlv - CLOSE

Stablllzation after landlngELS - AUTO (verlfy)cb MAIN REL PYRO (2) - close (venfy)MAIN RELEASE - on (up) (verlfy)S~CS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb BAT RLY BUS (2) - open

No contact w1th recovery forcesVHF AM AampB - off (ctr) ~

VHF AM Rev ONLY - A cb PL VENT - closecb FLOAT BAG (3) - closecb UPRIGHT SYS COMPRESS (2) - closeIf Stable II

FLOAT BAG(3)-FILL t1ll 2 m1n afterupr1ght then - OFF

VHF AM AlB amp BCN - OFF whlle lnvertedIf Stable I

After 10 M1n Coollng Per1odFLOAT BAG (3) - FILL 7 mln then OFF

Post Stab1lizat1on And Ventllat10nPL BCN LT - BCN LT LOWPL VENT vlv - UNLOCK (Pull)Remove PL VENT Exh CoverPL VENT - HIGH or LOWPL DYE MARKER - ON (swlmmer comm)Release foots traps and_restralntscb MNA BAT BUS A amp BAT C (2) - opencb MNB BAT BUS B amp BAT C (2) - opencb FLT amp PL BAT C - opencb PYRO A SEQ A - opencb PYRO B SEQ B - open

EACH HR - CHECK DC VOLTSgt 275 V If Notmiddot cb FLT amp PL-BAT BUS AampB (2) -open cb FLT amp PL BAT C (1) - open GO TO LOW POWER CHECKLIST

Unstow and lnstall PLV DISTRIB DUCTDeploy grappllng hook and 11ne 1f req

4

-48-

Post Landing Communlcatl0nsVHF ANT-RECY (venfy)VHF BCN - ON (verlfy)

If no contact ~lth recovery forcesperform VHF BEACON Check

MONITOR VHF BEACON transmlSSlonnth VHF AM B Rcvr andor Su)vlval

TransceiverkVHF Beacon not operatlng ~connect Surv~val TranscelVer to antcable behlnd VHF ant access pnland place radio ln BCN mode

LOW POHER CHECKLISTVHF BCN - OFFVHF AM (3) - RCVFLOOD Lts - OFFVHF AM AampB - off (ctr)VHF AM RCV ONLY - A (venfy)COUCH LIGHTS - OFFPOSTLANDING VENT SYS mlnlmlze useSURV RADIO - plug mto VHF BCN ANT cableconn behind VHF ant acess pnl amp turn radloon l-n BCN mode

EGRESS PROCEDURES

CMPCDRLMPCDR

CMPCDRCMP

LMPLl1PCDR

STABLE IDlsconnect Umblll-calsNeck darn onCenter couch - 270 0 positionArmrests stowedConnect raft to SIC l-f desl-red wlth

green lanyardConnect raft ~hl-te lanyards to SUltS amp

lnflate water wlngs when eXltl-ngHATCH PISTON PRESS vlv - PRESS (Outbd)Slde Hatch openedPL VENT - OFFcb Pnl 250 (all) - openEgress with 11feraftPut hardware klt outEgress

or CDIPALL

CMF

CDRCMF

CDR

LMF

CMFCMP LMFCMP

UlP

CDR

-49-

STABLE IIcb CREW STA AUDIO (3) - openD~sconnect umb~1~ca1s

Release foots trapsRelease restra~nt harnessCouch seat pans (3) - 170 0 pos1t10nArm rests stowedSurv1va1 k~ts removed from stowageConnect life raft ma~n1~ne to CDR or SicConnect f~rst wh~te lanyard from

11fe raft to suitConnect th~rd wh~te lanyard from

l~fe raft to SU1tConnect rucksacks together to yellow

lanyard on raft bagPRESSURE EQUALIZATION vlv - OPENRemove and stow fwd hatchEX1t feet f1rst w1th rucksacks when clear

of siC 1nflate water w1ngs and raftExit feet f1rst when clear of SiC

1nflate water w1ngsEX1t feet f1rst when clear of sic

1nflate water w1ngs

-50-

60 TLI ABORTS

TLI Aborts are conta~ned ~n the ESD s~nce the bulk of the funct~ons

concern entry preparat20ns and performance Th~s allows a s2nglesource of procedures for procedure rev2ew val~dat~on checkout andtra~n~ng These procedures ~ncorporate TLI preparat20ns as found ~n

reference 6 w~th the TLI Abort Procedures and these t~e 2nto normallunar return Entry Procedures found ~n sect20n 5 The guidel~nes

for th~s cont2ngency are spec2f2ed 2n reference 7

In2t2al preparat~ons for TLI pos2t20n the necessary system sW2tches2n add~t~on to perform~ng an EMS ~V test and a GDC al~gnment Afterthe DET ~s set for mon2tor2ng TB6 the CMP ~ncreases the 12ght levelof the LEB DSKY to max~mum and returns to the h2s couch Th2s 2Sdone so that the LEB DSKY can be observed ~n the event sunl~ght orreflect20ns wash out the ma2n d2splay panel DSKY dur2ng cr2t2calmaneuvers The crew then straps ~n and prepares for mon2tor~ng TB6as 2nd2cated by the SII SEP L~te The t2mes se~uence of procedures2S keyed on th~s d~splay and ~ncludes the DET START funct~on andSIVB IGNITION Dur2ng the burn the crew mon2tors the FDAIs foratt~tude excurs20ns and abnormal rates report~ng status checks toM~ss2on Control at d2screet t~mes dur2ng the maneuver Upon SIVBSHUTDOWN the eMP records the DSKY d~splayed performance parametersand awa2ts ground conf2rmat~on

The rat~onal for TLI aborts ~s descr~bed 2n reference 7 A summar2shyzat20n 2S extracted to prov2de background and gu2de12nes 2n th2sdocument The abort procedures cover aborts 10 m2nutes after conshyt2ngent SIVE shutdown and aborts 90 m2nutes after normal SIVE shutshydown t2me

The 10 m~nute TLI abort ~s des2gned to be used dur~ng TLI ~n theevent a spacecraft problem develops Wh2Ch can result 2n catastrophe2f ~mmed~ate act~on 2S not taken If the s~tuat20n perm~ts the crewshould always allow the SIVB to complete TLI at wh~ch t~me the groundand crew can perform a malfunct~on analys~s to determ~ne ~f an abort~s adv~sable If a fa~lure occurs that necess2tates the shutdown ofthe SIVB and the ~u~ck return of the crew to earth th~s abort ~s

des~gned to be as ~nsens~t~ve to execut~on errors as poss~ble andst21l be targeted to m2dcorr2dor The burn att~tude w~th the f~ed

hor~zon reference ~s a constant value for any shutdown t~me Theburn durat~on 2S a funct20n of shutdown t2me and 2S ava21able fromcrew charts S~nce the pr~mary purpose of th~s abort ~s to returnto earth as qU2ckly as poss2ble there are no restr2ct20ns as toland~ng locat~on However ~f the t~me to EI is greater than abouttwo hours a midcourse correct20n should be ant~c~pated

The 90 m2nute TLI abort 2S to be used 2f a cr2t2cal subsystem malshyfunct~on ~s determ2ned and the dec2s~on to abort ~s made after the

-51-

TLI cutoff and before TLI cutoff plus approxlmately 80 m1nutesTh1S allows suff1c1ent separatlon and procedural t1me to set upfor the SPS deorb1t burn performed at about TLI + 90 Note thatgenerally the deorb1t burns w1ll be performed a fe11 m1nutes beforeTLI + 90 accord1ng to crew charts shown In reference 8 The no-comm except10n requ1res that 90 m1nutes be the 1nput t1me of 19n1shytlon for P-37 (onboard return-to-earth abort program) so that onshyboard calculatlons can correspond w1th ground calculat10ns to computethe CM land1ng p01nt Th1S TLI abort lS des1gned so that returnfl1ght t1me does not exceed 18 hours and abort ~V does not exceed7000 fps ThlS abort can be performed uSlng chart ~Vs and attltudesand the earths hor1zon serves as a suff1c1ent reference The maneushyver lS targeted to ach1eve the mldcorr1dor entry target Ilne andtlmed to result 1n a deslgnated recovery area

It 1S ObV10US for abort deC1S1ons early 1n the TLI + 90 m1nute t1meshyframe that a GampN SPS burn should be performed In order to keep theTLI abort procedures cons1stent and w1th emphasls on slmpl1c1ty theprocedures here reflect a SCS SPS abort burn to cover the full abortdec1s1on t1meframe

A m1dcourse correct1on for corr1dor control after a TLI abort may bedeS1red 1f the SPS burn d1d not meet expectat1ons The TLIabortprocedures 1n th1S sect10n adapt to the normal lunar return tlmel1neand procedures pr10r to the f1nal MCC

-52-

61 TLI PREPARATION PROCEDURES

GET = 150

CRO AOS(___)

CRO LOS( )(22142)

5100

Don Helmets amp Gloves

XLUNAR - INJECT (verify)EDS PWR - on (venfy)EMS FUNC - OFF (verlfy)EMS MODE - STBYEMS FUNC - IW SETVHF RNGEMS MODE - NORMALSet ~V indo to +15868 fpsEMS FUMC - ~V Test

SPS THRUST Lt - onoff (10 sec)~V lnd stops at -01 to -415

EMS MODE - STBYEMS FUMC - ~V SETVHF RNGSet ~VC

EMS FUNC---~~V=----

GDC ALIGNFDAI Select - liZcb SECS LOGIC (Z) - close (verify)cb SECS ARM (Z) - closeSECS LOGIC (Z) - on (up)MSFN Conflrm GO for PYRO ARM (If pass)SECS PYRO ARM (Z) - on (up)TRANS CONTROL PWR - ONROT CONTR PWR NORMAL (Z) - ACDC(verlfy)ROT CONTR PWR DIRECT (Z) - MNAMNBLV INnGPI - SIISIVB (venfy)LV GUID - IU (venfy)cb DIRECT ULLAGE (Z) - closedSet EVENT TIMER to 5100Begin MONITOR For TB6

CMP to Couch

TB 6 - SII SEP Lt on (TIG-9 mln 38 sec)KEY V83E

SET ORDEALFDAI Z ORB RATE at 180 0 0SII SEP Lt out (38 sec later)Start DET COUNTING UPSC CaNT - SCS (verify)MONITOR LV TANK PRESS

~P lt 36 psid (OXID gt FUEL)~P lt Z6 psid (FUEL gt OXID)

EMERGENCY CSMLV SEP UP TLM CM - BLOCK (verify)UP TLM IU - BLOCK (venfy)

-53-

+45degPY))0middot sec PY

lOK nmltHAlt25K nm

Two phas~ng mnvrs two SPS mnvrs to circular~ze at 150 nmearth orb~t

CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ssion 4K nmltHAltlOK nm CSM amp1M - Two phasing mnvrs two SPS mnvrs to circularize at 150 nm earth orb~t CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ss~on

CSM amp 1M - Two phas~ng mnvrs APS burn todepletion th~rd phasing mnvrSPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn tosem~sync orb~t

25K nmltHAlt40K nm CSM amp 1M - Two phasmg mnvrs APS burn to depletion third phas~ng mnvr SPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn to sem~sync orbit HA)40K nm DPS ava~l - DPS LOll circularize with SPS

DPS not ava~l - Lunar flyby or CSM only to lunar orbit (if reqd gtV lt4000 fps)

V37E 47E (check b~as) Record -=--rshy(Limit 98 fpsmm)

( 1fps)tVXYZN62EVIHDOTHPAD (fpsfpslnm)MONITOR VI ( ) at ECO

SCS TVC SERVO PWR 1 - ACIMNA2 - OFF

TAPE RCDR - CMD RESETHBREMS MODE - NORMAL

SIr SEP Lt - ONTLI Inhib~t S~gnals w~11 not be honored after 5942

SIVB ULLAGE BeginsSII SEP Lt - off (TIG - 18 sec)SIVB FUEL LEADSIVB ULLAGE d~scont~nues

LV ENG I Lt - onSIVB IGNITION ( GETI)LV ENG I Lt - off - -shyMONITOR THRUST amp ATTITUDEMONITOR LV TANK PRESSSIVE ECO (Lt on) (BEGIN TB7)

EMER SIVE CUTOFF AT 6 SEC PAST BURN TIME IF VI ATTAINEDTHC CCW ampNEUTRAL IN 1 SEC or SIISIVB sW - LV STAGEPremature Shutdown HAlt4K nm CSM amp 1M -

5700

58205836

F 16 835800

F 16 62

5838594259525955595900000002SUNRISE(___)

HAW AOS(__=_) KEY VERB (freeze d~splay)

SIVB ATT HOLD 20 sec amp BEGIN VENTINGSIVB NNVR TO ORB RT (HDS DN) (3middot sec)

Record VI -c---HDOT _

HPAD _

KEY RLSEF 16 62

F 16 83

HAW LOS(__=-)

KEYmiddotRLSE~VXYZ (lfps)

Record ~VX---_

~vy

WZ--

AVC---_

TAPE RCDR - off (ctr)EMS MODE - STBYEMS FUNC - OFFSECS PYRO ARM (2) - SAFE

PRO

BURN STATUS REPORT

____--~TIG

BT------VGX____-R

-----P----_Y

REMARKS

_____VI

______--HDOT______--H______---AVC______---FUEL_______OXID

_______UNBAL

F 3708=00 OOEGOS AOS CMP TO LEB

(-=-=-)

0000

0003

0005

0014

0100

-55-

62 TLI 10 MIN ABORTSECS LOGIC (2) - on (up)SECS PYRO ARM (2) - ARM

TRANS CONTR - CGH (4 sec) amp +XDET RESET (verlfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS GMD-ON

TRANS GONTR - neutral then +X for10 sec

SIVBGPI s~ - GPIExcesslve rates 6V THRUST A - NORMAL SPS THRUST - DIRECT When rates damped 6V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

TRANS CONTR +X - OFFV37E OOE

PITGH UP to LOGAL VERT (+X axlSto~ard the earth)

RATE - LOWBMAG MODE (3) - ATTIRATE 2EDS PHR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SEGS ARM (2) - opencb EDS (3) - open

TRANS CONTR -X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (180deg)P (199deg)Y (0deg)

RETRO UPDATEGETI _

JV _VG

Jtb ---GET 400K _

05G _GET DROGUE _

ENTRY P _R _

Y_--

0945

-56-

ALIGN HORIZ ON RET +1 MKGMBL CHECK (T11lle Pentattlng)MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conflnn)cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FUMC - JV SETVHF RNGSET JV from chartE~S FUMC - JVEMS fODE - NOIDlAL

lV THRUST A - NORMALV37E 47E (THRUST fONITOR)

F 16 83 lVXYZ (1 fps)

0950

1000

NOTE For aborts durlng 1st mln of TLIKEY V82E F 16 44 (HaHpTff)Burn untll Hp lt 19NM

TRANS CONTR +X

THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN JV reqdJV THRUST (2) - OFFReport cutoff

cb SPS P2 Y2- closeGfBL MTRS (4) - OFF (LMP Confinn)TRANS CONT PWR - OFFTVC SERVO PWR (2) - OFFMN BUS TIE (2) - OFFcb SPS P1amp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREIf est time to EIltOl5500 omlt fCC andenter the SUPERCIRC CKLIST as early as pos-slb1e Pg ~2~3~ __If est time to EI)Ol5500 anticlpate afCC Enter the ENTRY PREP CKLIST at step 9pg 18

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

-2tl C

l I W gt- ~-4

z laquo I I- 0 -6

l- I J u gt- ~-8

z w w -10

~_ONSANT

9O

VER

SHO

OT

BOU

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ARY

LIF

TV

EC

TOR

OR

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TATI

ON

LIN

E

SH

ALL

OW

TAR

GE

TLI

NE

STE

EP

TAR

GE

TLI

NE 12

gU

ND

ERSH

OO

TBO

UN

DAR

Y

RE

EN

TRY

CO

RR

IDO

R

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-12 24

26

28

30

32

34

RE

EN

TRY

VE

LOC

ITY

VE

1-F

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3B

6-i

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CC

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LR

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73

8X

03

-i- rtREQUIRED PITCH GIMBAL ANG LETO OBTAIN HOR-IZON AT 317

DEGREES IN wiiiiDOW

260

z~I- ~ i5 24000

1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

-I

-1-

NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

I LU HD~-

LUHD

lt0 120UJ0

~

80 HOLD PRESENT TRIMgt LU HD013

~Y~HOIgtlt

TOP OF WINDOWa 40to

31 7 SCRIBEaaI

80 TTOM OF WINDOWi= 0

0--ltoa

-40t-z

~~~Uw w u lt0 -80

HOLO PRESENT TRIlJCl

LOHU0 lt0

J gt -120 HOLD 059 TRIMlt0 z

LDHUlt0 FIELD OF VI S10 NLDHU LIFT-DOWNHEADS -UPLUHD LIFT-UP HEADS-DOWN

~~H~-160 q - P63 LIMITI- NOrE-VALIO ONLY FO~t~--

LUNAR RETURN VELOCITY

plusmnl8020 244middot 8 12 16

TIME TO 400K FT ALTITUDE-MIN

4

P37

LONG

ITUD

ECO

RREC

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TOOB

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1350

NM

ENTR

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340

344

348

352

356

364

368

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AA

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-60

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6

1000

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00 60

00 i50

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120

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6V-

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240

320

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1968

400050

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Cll-

41)

120

200

241)

320

400

441)

520

TlI

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ABOR

TlA

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-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 43: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

-40-

55 EARTH ORBIT ENTRY

1 Venfy CMSMR __

P_shyY_-

SEP ATT(180deg)

(0deg )

2

3

4

EMS INITIALIZATIONEMS FUNC - RNG SETSET RNG TO PAD DATA RNGEMS FUNC - VA SETSlew scroll to pad data VIOEMS FUNC - ENTRY

RSI ALIGNMENTFDAI SOURCE - ATT SETATT SET - GDCEMS ROLL - on(up)GDC ALIGN PB - PUSH amp HOLDYAW tw - Pos1tion RSI thru 45deg amp

back to LIFl UPGDC ALIGN PB - RELEASEEMS ROLL - OFFAl1gn GDC to lMU

PWR REDUCT (Norm Deorb Only)HGA PWR - OFFFC PUMPS (3) - OFFVer1fy s1ngle suit compr oper

loads balancedFC 2 MN AampB - OFFS BD PWR AMP - Lowcb ECS RAn CONTHTR (2) - opencb WASTE H20URINE DUMP HTRS (2)-openlOb HTRS OVLD (2) - openPOT H20 HTR - OFFCAB FAN (2) - OFFGLY EVAP TEMP IN - MAN

-41-

P61 - ENTRY PREP

5 V37E 61E05 09 01427 - ROLL REVERSED05 09 01426 - IMU UNSAT

6 F 06 61 IMPACT LAT LONG liDS UPDN (+-)(01 0

010

+00001)

PRO

PAD VALUESLATLON==G------liDS UP DN _

7 F 06 60 GMAXV400KGAMMA EIRecord

GMAXV400K----GAMMA EI _

PRO

8 F 06 63 RTOGO (1nm) PAD _VIa (fps) PADTFE (mln-sec) ----Compare wlth MSFN for PGNS GONO GONO COMM SET RTOGO amp VIO IN EMS amp

INITIALIZE(ACCEPT) PRO(RECALC) V32E to 8

-42-

P62 - CMSM SEP amp PRE-ENTRY MNVR

9 F 50 25 00041 REQUEST CMSM SEPSC CONT - SCSFREEYAW - 45deg out-of-plane (left for RCS

nght for SPS)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE2PRIM GLY to RAD - BYPASS (verlfy)SECS LOGIC (2) - on (up)MSFN conflrm GO for PYRO ARMSECS PYRO ARM - ARMMN BUS TIE (2) - ON (verlfy)CMSM SEF (2) - ONCSMLM FNl SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 pSlaCM RCS LOGIC - OFFSECS PYRO ARM - SAFEMonltor VMAB

If lt25vdc go to EMERG POWERDOWN Pg E6-1AUTO RCS SEL AlC ROLL (4) - OFFAUTO RCS SEL CM 2(6) - OFFAUTO RCS SEL CM 1(6) - MNA or MNBYAW back to 00

PITCH TO ENTRY ATTROLL 0deg (LIFT UP)PITCH - HORIZ on 317deg MARK (400K)YAW 00

ATT DB - MAXMAN ATT (PITCH) - ACCEL CMDEMS DATA - VerifyEMS FUNC - ENTRY (verlfy)EMS MODE - NORMALMAINTAIN HORIZ TRK

PRO (Act ENTRY DAP)

10 F 06 61 IMPACT LAT LONG HDSDN(010 010 -00001)

PRO

11 FOSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axlS beyond 45deg of Vel vector)

-43-

P63 - ENTRY INIT

12 06 64 GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PWR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRHORIZ CKP~tch error needle goes toward

zero approach~ng 05G t~me

MAN ATT (PITCH) - RATE CMDIf CMC ~s GO

BMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS FLY BETA If CMC NO GO ~

SC CONT - SCS~

FLY EMS RCS Deorh Roll HDS UPTRACK HORIZ w~th 29deg w~ndow mk

P64 - ENTRY POST 05G

13

05G t=elt+0___)

06 68

RTOGO AT 05G AGREES WITH EMS - venfyHORIZ CK05E Lt - on (EMS start)

No EMS start w~th~n 3 secsEMS MODE - BACKUP VHF RNG 05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds L~ft DN

NNVR L~ft DNEMS GONO GO

G-V Plot w~th~n llm~ts

Rng ctr dwn 60 + 7 durlng 10 sec per~od

Mon~tor G-meter forconvergence wlth pad data (Do)

(Vlt27K fps) Go To 17

-44-

P65 - ENTRY - UP CONT (Vgt27K fps)

14 F 16 69 BETA (01deg)DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT~

SC CONT - SCS FLY EMS

PRO

15 06 68 BElA VI HOOT (01deg fpsfps)(VltVL +500 fps amp RDOT Neg) Go To 17

p66 - ENTRY - BALLISTIC (DltDL)

16 06 22 DESIRED GMBL ANGLES RPY (01deg)Mon~tor hor~z +12deg of 317deg mark

P67 - ENTRY - FINAL PHASE (02G)

17 0666 BETACRSRNG ERRDNRNG ERR (Oldeglnmlnm)KEY VERBRecord DNRNG ERR _KEY RLSEL~m~t +100nm from PAD DRE

Mon~tor l~ft vector on RSI amp FDAIF 16 67 RTOGOLATLONG (Vre1=1000fps)

(lnm 010 01deg)SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOlfflMon~tor altimeter

Go To EARTHLANDING pg _I4L5__

-45-

56 EARTHLANDING

90K STEAM PRESS - PEGGED50K CABIN PRESS REL vIv (2) - BOOSTENTRY

SECS PYRO ARM (2) - ARM

40K(90K + 63s)

CM UNSTABLE RCS CMD - OFF ~ 40K APEX COVER JETT PG-PUSH DROGUE DEPLOY PG - PUSH (2 secafter apex cover Jett)

30K ELS LOGIC - ON (up)ELS - AUTO

24K RCS hsable (auto)(90K+92s) RCS CMD - OFF

Apex cover Jett (auto)APEX COVER JETT PB - PUSH

(WAIT 2 SECS)Drogue parachutes deployed (auto)

DROGUE DEPLOY PB - PUSH~

If Drogues FallELS - ~ ~Stablllze CM 5K MAIN DPLY PB - PUSHELS - AUTO

235K Cabln Pressure lncreaslng (Drogues + 50s)If not lncreaSlng by 17K CABIN PRESS REL vlv (RR) - DUMP

-46-

10K Maln parachutes deployedMAIN DEPLOY PB - PUSH (wlthln 1 sec)VHF ANT - RECYVHF AMA - SIMPLEXVHF BCN - ONCABIN PRESS REL v1v (2) - CLOSEDIRECT 02 vlv - OPENCM RCS LOGIC - on (up)CM PRPLNT - DUMP (burn audlb1e)Monltor CM ReS 1amp2 for He press decrease

NO BURN or PRESS DECREASE USE BOTH RHCs DO NOT FIRE PITCH JETS

CM PRPLNT-PURGE (to zero He press)CM RCS He DUMP PB - PUSH RHC (2) - 30 sees NO PITCH k

STRUT LOCKS (2) - UNLOCK

cb FLT amp PL BAT BUS ABampBAT C (3) - closecb FLT amp PLT MNA amp B (2) - opencb ECS RAD HTR OVLD (2) - opencb SPS PampY (4) - open

3K CABIN PRESS REL v1v (RH) - DUMP (after purgecompleted)

FLOOD Lts - POST LDGCM RCS PRPLNT (2) - OFFROT CONTR PWR DIRECT (2) - OFF

800 CAB PRESS RELF vlv - CLOSE (latch off)MN BUS TIE (2) - OFF

AFTER LANDINGcb MAIN REL PYRO (2) - closeMAIN RELEASE - on(up)

Go to POSTLANDING pg _47L-__

I

2

3

-47-

57 POSTLANDING

STABILIZATION VENTILATION COMMUNICATIONS

DIRECT 02 vlv - CLOSE

Stablllzation after landlngELS - AUTO (verlfy)cb MAIN REL PYRO (2) - close (venfy)MAIN RELEASE - on (up) (verlfy)S~CS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb BAT RLY BUS (2) - open

No contact w1th recovery forcesVHF AM AampB - off (ctr) ~

VHF AM Rev ONLY - A cb PL VENT - closecb FLOAT BAG (3) - closecb UPRIGHT SYS COMPRESS (2) - closeIf Stable II

FLOAT BAG(3)-FILL t1ll 2 m1n afterupr1ght then - OFF

VHF AM AlB amp BCN - OFF whlle lnvertedIf Stable I

After 10 M1n Coollng Per1odFLOAT BAG (3) - FILL 7 mln then OFF

Post Stab1lizat1on And Ventllat10nPL BCN LT - BCN LT LOWPL VENT vlv - UNLOCK (Pull)Remove PL VENT Exh CoverPL VENT - HIGH or LOWPL DYE MARKER - ON (swlmmer comm)Release foots traps and_restralntscb MNA BAT BUS A amp BAT C (2) - opencb MNB BAT BUS B amp BAT C (2) - opencb FLT amp PL BAT C - opencb PYRO A SEQ A - opencb PYRO B SEQ B - open

EACH HR - CHECK DC VOLTSgt 275 V If Notmiddot cb FLT amp PL-BAT BUS AampB (2) -open cb FLT amp PL BAT C (1) - open GO TO LOW POWER CHECKLIST

Unstow and lnstall PLV DISTRIB DUCTDeploy grappllng hook and 11ne 1f req

4

-48-

Post Landing Communlcatl0nsVHF ANT-RECY (venfy)VHF BCN - ON (verlfy)

If no contact ~lth recovery forcesperform VHF BEACON Check

MONITOR VHF BEACON transmlSSlonnth VHF AM B Rcvr andor Su)vlval

TransceiverkVHF Beacon not operatlng ~connect Surv~val TranscelVer to antcable behlnd VHF ant access pnland place radio ln BCN mode

LOW POHER CHECKLISTVHF BCN - OFFVHF AM (3) - RCVFLOOD Lts - OFFVHF AM AampB - off (ctr)VHF AM RCV ONLY - A (venfy)COUCH LIGHTS - OFFPOSTLANDING VENT SYS mlnlmlze useSURV RADIO - plug mto VHF BCN ANT cableconn behind VHF ant acess pnl amp turn radloon l-n BCN mode

EGRESS PROCEDURES

CMPCDRLMPCDR

CMPCDRCMP

LMPLl1PCDR

STABLE IDlsconnect Umblll-calsNeck darn onCenter couch - 270 0 positionArmrests stowedConnect raft to SIC l-f desl-red wlth

green lanyardConnect raft ~hl-te lanyards to SUltS amp

lnflate water wlngs when eXltl-ngHATCH PISTON PRESS vlv - PRESS (Outbd)Slde Hatch openedPL VENT - OFFcb Pnl 250 (all) - openEgress with 11feraftPut hardware klt outEgress

or CDIPALL

CMF

CDRCMF

CDR

LMF

CMFCMP LMFCMP

UlP

CDR

-49-

STABLE IIcb CREW STA AUDIO (3) - openD~sconnect umb~1~ca1s

Release foots trapsRelease restra~nt harnessCouch seat pans (3) - 170 0 pos1t10nArm rests stowedSurv1va1 k~ts removed from stowageConnect life raft ma~n1~ne to CDR or SicConnect f~rst wh~te lanyard from

11fe raft to suitConnect th~rd wh~te lanyard from

l~fe raft to SU1tConnect rucksacks together to yellow

lanyard on raft bagPRESSURE EQUALIZATION vlv - OPENRemove and stow fwd hatchEX1t feet f1rst w1th rucksacks when clear

of siC 1nflate water w1ngs and raftExit feet f1rst when clear of SiC

1nflate water w1ngsEX1t feet f1rst when clear of sic

1nflate water w1ngs

-50-

60 TLI ABORTS

TLI Aborts are conta~ned ~n the ESD s~nce the bulk of the funct~ons

concern entry preparat20ns and performance Th~s allows a s2nglesource of procedures for procedure rev2ew val~dat~on checkout andtra~n~ng These procedures ~ncorporate TLI preparat20ns as found ~n

reference 6 w~th the TLI Abort Procedures and these t~e 2nto normallunar return Entry Procedures found ~n sect20n 5 The guidel~nes

for th~s cont2ngency are spec2f2ed 2n reference 7

In2t2al preparat~ons for TLI pos2t20n the necessary system sW2tches2n add~t~on to perform~ng an EMS ~V test and a GDC al~gnment Afterthe DET ~s set for mon2tor2ng TB6 the CMP ~ncreases the 12ght levelof the LEB DSKY to max~mum and returns to the h2s couch Th2s 2Sdone so that the LEB DSKY can be observed ~n the event sunl~ght orreflect20ns wash out the ma2n d2splay panel DSKY dur2ng cr2t2calmaneuvers The crew then straps ~n and prepares for mon2tor~ng TB6as 2nd2cated by the SII SEP L~te The t2mes se~uence of procedures2S keyed on th~s d~splay and ~ncludes the DET START funct~on andSIVB IGNITION Dur2ng the burn the crew mon2tors the FDAIs foratt~tude excurs20ns and abnormal rates report~ng status checks toM~ss2on Control at d2screet t~mes dur2ng the maneuver Upon SIVBSHUTDOWN the eMP records the DSKY d~splayed performance parametersand awa2ts ground conf2rmat~on

The rat~onal for TLI aborts ~s descr~bed 2n reference 7 A summar2shyzat20n 2S extracted to prov2de background and gu2de12nes 2n th2sdocument The abort procedures cover aborts 10 m2nutes after conshyt2ngent SIVE shutdown and aborts 90 m2nutes after normal SIVE shutshydown t2me

The 10 m~nute TLI abort ~s des2gned to be used dur~ng TLI ~n theevent a spacecraft problem develops Wh2Ch can result 2n catastrophe2f ~mmed~ate act~on 2S not taken If the s~tuat20n perm~ts the crewshould always allow the SIVB to complete TLI at wh~ch t~me the groundand crew can perform a malfunct~on analys~s to determ~ne ~f an abort~s adv~sable If a fa~lure occurs that necess2tates the shutdown ofthe SIVB and the ~u~ck return of the crew to earth th~s abort ~s

des~gned to be as ~nsens~t~ve to execut~on errors as poss~ble andst21l be targeted to m2dcorr2dor The burn att~tude w~th the f~ed

hor~zon reference ~s a constant value for any shutdown t~me Theburn durat~on 2S a funct20n of shutdown t2me and 2S ava21able fromcrew charts S~nce the pr~mary purpose of th~s abort ~s to returnto earth as qU2ckly as poss2ble there are no restr2ct20ns as toland~ng locat~on However ~f the t~me to EI is greater than abouttwo hours a midcourse correct20n should be ant~c~pated

The 90 m2nute TLI abort 2S to be used 2f a cr2t2cal subsystem malshyfunct~on ~s determ2ned and the dec2s~on to abort ~s made after the

-51-

TLI cutoff and before TLI cutoff plus approxlmately 80 m1nutesTh1S allows suff1c1ent separatlon and procedural t1me to set upfor the SPS deorb1t burn performed at about TLI + 90 Note thatgenerally the deorb1t burns w1ll be performed a fe11 m1nutes beforeTLI + 90 accord1ng to crew charts shown In reference 8 The no-comm except10n requ1res that 90 m1nutes be the 1nput t1me of 19n1shytlon for P-37 (onboard return-to-earth abort program) so that onshyboard calculatlons can correspond w1th ground calculat10ns to computethe CM land1ng p01nt Th1S TLI abort lS des1gned so that returnfl1ght t1me does not exceed 18 hours and abort ~V does not exceed7000 fps ThlS abort can be performed uSlng chart ~Vs and attltudesand the earths hor1zon serves as a suff1c1ent reference The maneushyver lS targeted to ach1eve the mldcorr1dor entry target Ilne andtlmed to result 1n a deslgnated recovery area

It 1S ObV10US for abort deC1S1ons early 1n the TLI + 90 m1nute t1meshyframe that a GampN SPS burn should be performed In order to keep theTLI abort procedures cons1stent and w1th emphasls on slmpl1c1ty theprocedures here reflect a SCS SPS abort burn to cover the full abortdec1s1on t1meframe

A m1dcourse correct1on for corr1dor control after a TLI abort may bedeS1red 1f the SPS burn d1d not meet expectat1ons The TLIabortprocedures 1n th1S sect10n adapt to the normal lunar return tlmel1neand procedures pr10r to the f1nal MCC

-52-

61 TLI PREPARATION PROCEDURES

GET = 150

CRO AOS(___)

CRO LOS( )(22142)

5100

Don Helmets amp Gloves

XLUNAR - INJECT (verify)EDS PWR - on (venfy)EMS FUNC - OFF (verlfy)EMS MODE - STBYEMS FUNC - IW SETVHF RNGEMS MODE - NORMALSet ~V indo to +15868 fpsEMS FUMC - ~V Test

SPS THRUST Lt - onoff (10 sec)~V lnd stops at -01 to -415

EMS MODE - STBYEMS FUMC - ~V SETVHF RNGSet ~VC

EMS FUNC---~~V=----

GDC ALIGNFDAI Select - liZcb SECS LOGIC (Z) - close (verify)cb SECS ARM (Z) - closeSECS LOGIC (Z) - on (up)MSFN Conflrm GO for PYRO ARM (If pass)SECS PYRO ARM (Z) - on (up)TRANS CONTROL PWR - ONROT CONTR PWR NORMAL (Z) - ACDC(verlfy)ROT CONTR PWR DIRECT (Z) - MNAMNBLV INnGPI - SIISIVB (venfy)LV GUID - IU (venfy)cb DIRECT ULLAGE (Z) - closedSet EVENT TIMER to 5100Begin MONITOR For TB6

CMP to Couch

TB 6 - SII SEP Lt on (TIG-9 mln 38 sec)KEY V83E

SET ORDEALFDAI Z ORB RATE at 180 0 0SII SEP Lt out (38 sec later)Start DET COUNTING UPSC CaNT - SCS (verify)MONITOR LV TANK PRESS

~P lt 36 psid (OXID gt FUEL)~P lt Z6 psid (FUEL gt OXID)

EMERGENCY CSMLV SEP UP TLM CM - BLOCK (verify)UP TLM IU - BLOCK (venfy)

-53-

+45degPY))0middot sec PY

lOK nmltHAlt25K nm

Two phas~ng mnvrs two SPS mnvrs to circular~ze at 150 nmearth orb~t

CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ssion 4K nmltHAltlOK nm CSM amp1M - Two phasing mnvrs two SPS mnvrs to circularize at 150 nm earth orb~t CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ss~on

CSM amp 1M - Two phas~ng mnvrs APS burn todepletion th~rd phasing mnvrSPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn tosem~sync orb~t

25K nmltHAlt40K nm CSM amp 1M - Two phasmg mnvrs APS burn to depletion third phas~ng mnvr SPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn to sem~sync orbit HA)40K nm DPS ava~l - DPS LOll circularize with SPS

DPS not ava~l - Lunar flyby or CSM only to lunar orbit (if reqd gtV lt4000 fps)

V37E 47E (check b~as) Record -=--rshy(Limit 98 fpsmm)

( 1fps)tVXYZN62EVIHDOTHPAD (fpsfpslnm)MONITOR VI ( ) at ECO

SCS TVC SERVO PWR 1 - ACIMNA2 - OFF

TAPE RCDR - CMD RESETHBREMS MODE - NORMAL

SIr SEP Lt - ONTLI Inhib~t S~gnals w~11 not be honored after 5942

SIVB ULLAGE BeginsSII SEP Lt - off (TIG - 18 sec)SIVB FUEL LEADSIVB ULLAGE d~scont~nues

LV ENG I Lt - onSIVB IGNITION ( GETI)LV ENG I Lt - off - -shyMONITOR THRUST amp ATTITUDEMONITOR LV TANK PRESSSIVE ECO (Lt on) (BEGIN TB7)

EMER SIVE CUTOFF AT 6 SEC PAST BURN TIME IF VI ATTAINEDTHC CCW ampNEUTRAL IN 1 SEC or SIISIVB sW - LV STAGEPremature Shutdown HAlt4K nm CSM amp 1M -

5700

58205836

F 16 835800

F 16 62

5838594259525955595900000002SUNRISE(___)

HAW AOS(__=_) KEY VERB (freeze d~splay)

SIVB ATT HOLD 20 sec amp BEGIN VENTINGSIVB NNVR TO ORB RT (HDS DN) (3middot sec)

Record VI -c---HDOT _

HPAD _

KEY RLSEF 16 62

F 16 83

HAW LOS(__=-)

KEYmiddotRLSE~VXYZ (lfps)

Record ~VX---_

~vy

WZ--

AVC---_

TAPE RCDR - off (ctr)EMS MODE - STBYEMS FUNC - OFFSECS PYRO ARM (2) - SAFE

PRO

BURN STATUS REPORT

____--~TIG

BT------VGX____-R

-----P----_Y

REMARKS

_____VI

______--HDOT______--H______---AVC______---FUEL_______OXID

_______UNBAL

F 3708=00 OOEGOS AOS CMP TO LEB

(-=-=-)

0000

0003

0005

0014

0100

-55-

62 TLI 10 MIN ABORTSECS LOGIC (2) - on (up)SECS PYRO ARM (2) - ARM

TRANS CONTR - CGH (4 sec) amp +XDET RESET (verlfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS GMD-ON

TRANS GONTR - neutral then +X for10 sec

SIVBGPI s~ - GPIExcesslve rates 6V THRUST A - NORMAL SPS THRUST - DIRECT When rates damped 6V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

TRANS CONTR +X - OFFV37E OOE

PITGH UP to LOGAL VERT (+X axlSto~ard the earth)

RATE - LOWBMAG MODE (3) - ATTIRATE 2EDS PHR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SEGS ARM (2) - opencb EDS (3) - open

TRANS CONTR -X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (180deg)P (199deg)Y (0deg)

RETRO UPDATEGETI _

JV _VG

Jtb ---GET 400K _

05G _GET DROGUE _

ENTRY P _R _

Y_--

0945

-56-

ALIGN HORIZ ON RET +1 MKGMBL CHECK (T11lle Pentattlng)MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conflnn)cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FUMC - JV SETVHF RNGSET JV from chartE~S FUMC - JVEMS fODE - NOIDlAL

lV THRUST A - NORMALV37E 47E (THRUST fONITOR)

F 16 83 lVXYZ (1 fps)

0950

1000

NOTE For aborts durlng 1st mln of TLIKEY V82E F 16 44 (HaHpTff)Burn untll Hp lt 19NM

TRANS CONTR +X

THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN JV reqdJV THRUST (2) - OFFReport cutoff

cb SPS P2 Y2- closeGfBL MTRS (4) - OFF (LMP Confinn)TRANS CONT PWR - OFFTVC SERVO PWR (2) - OFFMN BUS TIE (2) - OFFcb SPS P1amp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREIf est time to EIltOl5500 omlt fCC andenter the SUPERCIRC CKLIST as early as pos-slb1e Pg ~2~3~ __If est time to EI)Ol5500 anticlpate afCC Enter the ENTRY PREP CKLIST at step 9pg 18

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

-2tl C

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l- I J u gt- ~-8

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GE

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28

30

32

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-i- rtREQUIRED PITCH GIMBAL ANG LETO OBTAIN HOR-IZON AT 317

DEGREES IN wiiiiDOW

260

z~I- ~ i5 24000

1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

-I

-1-

NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

I LU HD~-

LUHD

lt0 120UJ0

~

80 HOLD PRESENT TRIMgt LU HD013

~Y~HOIgtlt

TOP OF WINDOWa 40to

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80 TTOM OF WINDOWi= 0

0--ltoa

-40t-z

~~~Uw w u lt0 -80

HOLO PRESENT TRIlJCl

LOHU0 lt0

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LDHUlt0 FIELD OF VI S10 NLDHU LIFT-DOWNHEADS -UPLUHD LIFT-UP HEADS-DOWN

~~H~-160 q - P63 LIMITI- NOrE-VALIO ONLY FO~t~--

LUNAR RETURN VELOCITY

plusmnl8020 244middot 8 12 16

TIME TO 400K FT ALTITUDE-MIN

4

P37

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320

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Cll-

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120

200

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320

400

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-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 44: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

-41-

P61 - ENTRY PREP

5 V37E 61E05 09 01427 - ROLL REVERSED05 09 01426 - IMU UNSAT

6 F 06 61 IMPACT LAT LONG liDS UPDN (+-)(01 0

010

+00001)

PRO

PAD VALUESLATLON==G------liDS UP DN _

7 F 06 60 GMAXV400KGAMMA EIRecord

GMAXV400K----GAMMA EI _

PRO

8 F 06 63 RTOGO (1nm) PAD _VIa (fps) PADTFE (mln-sec) ----Compare wlth MSFN for PGNS GONO GONO COMM SET RTOGO amp VIO IN EMS amp

INITIALIZE(ACCEPT) PRO(RECALC) V32E to 8

-42-

P62 - CMSM SEP amp PRE-ENTRY MNVR

9 F 50 25 00041 REQUEST CMSM SEPSC CONT - SCSFREEYAW - 45deg out-of-plane (left for RCS

nght for SPS)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE2PRIM GLY to RAD - BYPASS (verlfy)SECS LOGIC (2) - on (up)MSFN conflrm GO for PYRO ARMSECS PYRO ARM - ARMMN BUS TIE (2) - ON (verlfy)CMSM SEF (2) - ONCSMLM FNl SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 pSlaCM RCS LOGIC - OFFSECS PYRO ARM - SAFEMonltor VMAB

If lt25vdc go to EMERG POWERDOWN Pg E6-1AUTO RCS SEL AlC ROLL (4) - OFFAUTO RCS SEL CM 2(6) - OFFAUTO RCS SEL CM 1(6) - MNA or MNBYAW back to 00

PITCH TO ENTRY ATTROLL 0deg (LIFT UP)PITCH - HORIZ on 317deg MARK (400K)YAW 00

ATT DB - MAXMAN ATT (PITCH) - ACCEL CMDEMS DATA - VerifyEMS FUNC - ENTRY (verlfy)EMS MODE - NORMALMAINTAIN HORIZ TRK

PRO (Act ENTRY DAP)

10 F 06 61 IMPACT LAT LONG HDSDN(010 010 -00001)

PRO

11 FOSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axlS beyond 45deg of Vel vector)

-43-

P63 - ENTRY INIT

12 06 64 GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PWR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRHORIZ CKP~tch error needle goes toward

zero approach~ng 05G t~me

MAN ATT (PITCH) - RATE CMDIf CMC ~s GO

BMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS FLY BETA If CMC NO GO ~

SC CONT - SCS~

FLY EMS RCS Deorh Roll HDS UPTRACK HORIZ w~th 29deg w~ndow mk

P64 - ENTRY POST 05G

13

05G t=elt+0___)

06 68

RTOGO AT 05G AGREES WITH EMS - venfyHORIZ CK05E Lt - on (EMS start)

No EMS start w~th~n 3 secsEMS MODE - BACKUP VHF RNG 05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds L~ft DN

NNVR L~ft DNEMS GONO GO

G-V Plot w~th~n llm~ts

Rng ctr dwn 60 + 7 durlng 10 sec per~od

Mon~tor G-meter forconvergence wlth pad data (Do)

(Vlt27K fps) Go To 17

-44-

P65 - ENTRY - UP CONT (Vgt27K fps)

14 F 16 69 BETA (01deg)DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT~

SC CONT - SCS FLY EMS

PRO

15 06 68 BElA VI HOOT (01deg fpsfps)(VltVL +500 fps amp RDOT Neg) Go To 17

p66 - ENTRY - BALLISTIC (DltDL)

16 06 22 DESIRED GMBL ANGLES RPY (01deg)Mon~tor hor~z +12deg of 317deg mark

P67 - ENTRY - FINAL PHASE (02G)

17 0666 BETACRSRNG ERRDNRNG ERR (Oldeglnmlnm)KEY VERBRecord DNRNG ERR _KEY RLSEL~m~t +100nm from PAD DRE

Mon~tor l~ft vector on RSI amp FDAIF 16 67 RTOGOLATLONG (Vre1=1000fps)

(lnm 010 01deg)SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOlfflMon~tor altimeter

Go To EARTHLANDING pg _I4L5__

-45-

56 EARTHLANDING

90K STEAM PRESS - PEGGED50K CABIN PRESS REL vIv (2) - BOOSTENTRY

SECS PYRO ARM (2) - ARM

40K(90K + 63s)

CM UNSTABLE RCS CMD - OFF ~ 40K APEX COVER JETT PG-PUSH DROGUE DEPLOY PG - PUSH (2 secafter apex cover Jett)

30K ELS LOGIC - ON (up)ELS - AUTO

24K RCS hsable (auto)(90K+92s) RCS CMD - OFF

Apex cover Jett (auto)APEX COVER JETT PB - PUSH

(WAIT 2 SECS)Drogue parachutes deployed (auto)

DROGUE DEPLOY PB - PUSH~

If Drogues FallELS - ~ ~Stablllze CM 5K MAIN DPLY PB - PUSHELS - AUTO

235K Cabln Pressure lncreaslng (Drogues + 50s)If not lncreaSlng by 17K CABIN PRESS REL vlv (RR) - DUMP

-46-

10K Maln parachutes deployedMAIN DEPLOY PB - PUSH (wlthln 1 sec)VHF ANT - RECYVHF AMA - SIMPLEXVHF BCN - ONCABIN PRESS REL v1v (2) - CLOSEDIRECT 02 vlv - OPENCM RCS LOGIC - on (up)CM PRPLNT - DUMP (burn audlb1e)Monltor CM ReS 1amp2 for He press decrease

NO BURN or PRESS DECREASE USE BOTH RHCs DO NOT FIRE PITCH JETS

CM PRPLNT-PURGE (to zero He press)CM RCS He DUMP PB - PUSH RHC (2) - 30 sees NO PITCH k

STRUT LOCKS (2) - UNLOCK

cb FLT amp PL BAT BUS ABampBAT C (3) - closecb FLT amp PLT MNA amp B (2) - opencb ECS RAD HTR OVLD (2) - opencb SPS PampY (4) - open

3K CABIN PRESS REL v1v (RH) - DUMP (after purgecompleted)

FLOOD Lts - POST LDGCM RCS PRPLNT (2) - OFFROT CONTR PWR DIRECT (2) - OFF

800 CAB PRESS RELF vlv - CLOSE (latch off)MN BUS TIE (2) - OFF

AFTER LANDINGcb MAIN REL PYRO (2) - closeMAIN RELEASE - on(up)

Go to POSTLANDING pg _47L-__

I

2

3

-47-

57 POSTLANDING

STABILIZATION VENTILATION COMMUNICATIONS

DIRECT 02 vlv - CLOSE

Stablllzation after landlngELS - AUTO (verlfy)cb MAIN REL PYRO (2) - close (venfy)MAIN RELEASE - on (up) (verlfy)S~CS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb BAT RLY BUS (2) - open

No contact w1th recovery forcesVHF AM AampB - off (ctr) ~

VHF AM Rev ONLY - A cb PL VENT - closecb FLOAT BAG (3) - closecb UPRIGHT SYS COMPRESS (2) - closeIf Stable II

FLOAT BAG(3)-FILL t1ll 2 m1n afterupr1ght then - OFF

VHF AM AlB amp BCN - OFF whlle lnvertedIf Stable I

After 10 M1n Coollng Per1odFLOAT BAG (3) - FILL 7 mln then OFF

Post Stab1lizat1on And Ventllat10nPL BCN LT - BCN LT LOWPL VENT vlv - UNLOCK (Pull)Remove PL VENT Exh CoverPL VENT - HIGH or LOWPL DYE MARKER - ON (swlmmer comm)Release foots traps and_restralntscb MNA BAT BUS A amp BAT C (2) - opencb MNB BAT BUS B amp BAT C (2) - opencb FLT amp PL BAT C - opencb PYRO A SEQ A - opencb PYRO B SEQ B - open

EACH HR - CHECK DC VOLTSgt 275 V If Notmiddot cb FLT amp PL-BAT BUS AampB (2) -open cb FLT amp PL BAT C (1) - open GO TO LOW POWER CHECKLIST

Unstow and lnstall PLV DISTRIB DUCTDeploy grappllng hook and 11ne 1f req

4

-48-

Post Landing Communlcatl0nsVHF ANT-RECY (venfy)VHF BCN - ON (verlfy)

If no contact ~lth recovery forcesperform VHF BEACON Check

MONITOR VHF BEACON transmlSSlonnth VHF AM B Rcvr andor Su)vlval

TransceiverkVHF Beacon not operatlng ~connect Surv~val TranscelVer to antcable behlnd VHF ant access pnland place radio ln BCN mode

LOW POHER CHECKLISTVHF BCN - OFFVHF AM (3) - RCVFLOOD Lts - OFFVHF AM AampB - off (ctr)VHF AM RCV ONLY - A (venfy)COUCH LIGHTS - OFFPOSTLANDING VENT SYS mlnlmlze useSURV RADIO - plug mto VHF BCN ANT cableconn behind VHF ant acess pnl amp turn radloon l-n BCN mode

EGRESS PROCEDURES

CMPCDRLMPCDR

CMPCDRCMP

LMPLl1PCDR

STABLE IDlsconnect Umblll-calsNeck darn onCenter couch - 270 0 positionArmrests stowedConnect raft to SIC l-f desl-red wlth

green lanyardConnect raft ~hl-te lanyards to SUltS amp

lnflate water wlngs when eXltl-ngHATCH PISTON PRESS vlv - PRESS (Outbd)Slde Hatch openedPL VENT - OFFcb Pnl 250 (all) - openEgress with 11feraftPut hardware klt outEgress

or CDIPALL

CMF

CDRCMF

CDR

LMF

CMFCMP LMFCMP

UlP

CDR

-49-

STABLE IIcb CREW STA AUDIO (3) - openD~sconnect umb~1~ca1s

Release foots trapsRelease restra~nt harnessCouch seat pans (3) - 170 0 pos1t10nArm rests stowedSurv1va1 k~ts removed from stowageConnect life raft ma~n1~ne to CDR or SicConnect f~rst wh~te lanyard from

11fe raft to suitConnect th~rd wh~te lanyard from

l~fe raft to SU1tConnect rucksacks together to yellow

lanyard on raft bagPRESSURE EQUALIZATION vlv - OPENRemove and stow fwd hatchEX1t feet f1rst w1th rucksacks when clear

of siC 1nflate water w1ngs and raftExit feet f1rst when clear of SiC

1nflate water w1ngsEX1t feet f1rst when clear of sic

1nflate water w1ngs

-50-

60 TLI ABORTS

TLI Aborts are conta~ned ~n the ESD s~nce the bulk of the funct~ons

concern entry preparat20ns and performance Th~s allows a s2nglesource of procedures for procedure rev2ew val~dat~on checkout andtra~n~ng These procedures ~ncorporate TLI preparat20ns as found ~n

reference 6 w~th the TLI Abort Procedures and these t~e 2nto normallunar return Entry Procedures found ~n sect20n 5 The guidel~nes

for th~s cont2ngency are spec2f2ed 2n reference 7

In2t2al preparat~ons for TLI pos2t20n the necessary system sW2tches2n add~t~on to perform~ng an EMS ~V test and a GDC al~gnment Afterthe DET ~s set for mon2tor2ng TB6 the CMP ~ncreases the 12ght levelof the LEB DSKY to max~mum and returns to the h2s couch Th2s 2Sdone so that the LEB DSKY can be observed ~n the event sunl~ght orreflect20ns wash out the ma2n d2splay panel DSKY dur2ng cr2t2calmaneuvers The crew then straps ~n and prepares for mon2tor~ng TB6as 2nd2cated by the SII SEP L~te The t2mes se~uence of procedures2S keyed on th~s d~splay and ~ncludes the DET START funct~on andSIVB IGNITION Dur2ng the burn the crew mon2tors the FDAIs foratt~tude excurs20ns and abnormal rates report~ng status checks toM~ss2on Control at d2screet t~mes dur2ng the maneuver Upon SIVBSHUTDOWN the eMP records the DSKY d~splayed performance parametersand awa2ts ground conf2rmat~on

The rat~onal for TLI aborts ~s descr~bed 2n reference 7 A summar2shyzat20n 2S extracted to prov2de background and gu2de12nes 2n th2sdocument The abort procedures cover aborts 10 m2nutes after conshyt2ngent SIVE shutdown and aborts 90 m2nutes after normal SIVE shutshydown t2me

The 10 m~nute TLI abort ~s des2gned to be used dur~ng TLI ~n theevent a spacecraft problem develops Wh2Ch can result 2n catastrophe2f ~mmed~ate act~on 2S not taken If the s~tuat20n perm~ts the crewshould always allow the SIVB to complete TLI at wh~ch t~me the groundand crew can perform a malfunct~on analys~s to determ~ne ~f an abort~s adv~sable If a fa~lure occurs that necess2tates the shutdown ofthe SIVB and the ~u~ck return of the crew to earth th~s abort ~s

des~gned to be as ~nsens~t~ve to execut~on errors as poss~ble andst21l be targeted to m2dcorr2dor The burn att~tude w~th the f~ed

hor~zon reference ~s a constant value for any shutdown t~me Theburn durat~on 2S a funct20n of shutdown t2me and 2S ava21able fromcrew charts S~nce the pr~mary purpose of th~s abort ~s to returnto earth as qU2ckly as poss2ble there are no restr2ct20ns as toland~ng locat~on However ~f the t~me to EI is greater than abouttwo hours a midcourse correct20n should be ant~c~pated

The 90 m2nute TLI abort 2S to be used 2f a cr2t2cal subsystem malshyfunct~on ~s determ2ned and the dec2s~on to abort ~s made after the

-51-

TLI cutoff and before TLI cutoff plus approxlmately 80 m1nutesTh1S allows suff1c1ent separatlon and procedural t1me to set upfor the SPS deorb1t burn performed at about TLI + 90 Note thatgenerally the deorb1t burns w1ll be performed a fe11 m1nutes beforeTLI + 90 accord1ng to crew charts shown In reference 8 The no-comm except10n requ1res that 90 m1nutes be the 1nput t1me of 19n1shytlon for P-37 (onboard return-to-earth abort program) so that onshyboard calculatlons can correspond w1th ground calculat10ns to computethe CM land1ng p01nt Th1S TLI abort lS des1gned so that returnfl1ght t1me does not exceed 18 hours and abort ~V does not exceed7000 fps ThlS abort can be performed uSlng chart ~Vs and attltudesand the earths hor1zon serves as a suff1c1ent reference The maneushyver lS targeted to ach1eve the mldcorr1dor entry target Ilne andtlmed to result 1n a deslgnated recovery area

It 1S ObV10US for abort deC1S1ons early 1n the TLI + 90 m1nute t1meshyframe that a GampN SPS burn should be performed In order to keep theTLI abort procedures cons1stent and w1th emphasls on slmpl1c1ty theprocedures here reflect a SCS SPS abort burn to cover the full abortdec1s1on t1meframe

A m1dcourse correct1on for corr1dor control after a TLI abort may bedeS1red 1f the SPS burn d1d not meet expectat1ons The TLIabortprocedures 1n th1S sect10n adapt to the normal lunar return tlmel1neand procedures pr10r to the f1nal MCC

-52-

61 TLI PREPARATION PROCEDURES

GET = 150

CRO AOS(___)

CRO LOS( )(22142)

5100

Don Helmets amp Gloves

XLUNAR - INJECT (verify)EDS PWR - on (venfy)EMS FUNC - OFF (verlfy)EMS MODE - STBYEMS FUNC - IW SETVHF RNGEMS MODE - NORMALSet ~V indo to +15868 fpsEMS FUMC - ~V Test

SPS THRUST Lt - onoff (10 sec)~V lnd stops at -01 to -415

EMS MODE - STBYEMS FUMC - ~V SETVHF RNGSet ~VC

EMS FUNC---~~V=----

GDC ALIGNFDAI Select - liZcb SECS LOGIC (Z) - close (verify)cb SECS ARM (Z) - closeSECS LOGIC (Z) - on (up)MSFN Conflrm GO for PYRO ARM (If pass)SECS PYRO ARM (Z) - on (up)TRANS CONTROL PWR - ONROT CONTR PWR NORMAL (Z) - ACDC(verlfy)ROT CONTR PWR DIRECT (Z) - MNAMNBLV INnGPI - SIISIVB (venfy)LV GUID - IU (venfy)cb DIRECT ULLAGE (Z) - closedSet EVENT TIMER to 5100Begin MONITOR For TB6

CMP to Couch

TB 6 - SII SEP Lt on (TIG-9 mln 38 sec)KEY V83E

SET ORDEALFDAI Z ORB RATE at 180 0 0SII SEP Lt out (38 sec later)Start DET COUNTING UPSC CaNT - SCS (verify)MONITOR LV TANK PRESS

~P lt 36 psid (OXID gt FUEL)~P lt Z6 psid (FUEL gt OXID)

EMERGENCY CSMLV SEP UP TLM CM - BLOCK (verify)UP TLM IU - BLOCK (venfy)

-53-

+45degPY))0middot sec PY

lOK nmltHAlt25K nm

Two phas~ng mnvrs two SPS mnvrs to circular~ze at 150 nmearth orb~t

CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ssion 4K nmltHAltlOK nm CSM amp1M - Two phasing mnvrs two SPS mnvrs to circularize at 150 nm earth orb~t CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ss~on

CSM amp 1M - Two phas~ng mnvrs APS burn todepletion th~rd phasing mnvrSPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn tosem~sync orb~t

25K nmltHAlt40K nm CSM amp 1M - Two phasmg mnvrs APS burn to depletion third phas~ng mnvr SPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn to sem~sync orbit HA)40K nm DPS ava~l - DPS LOll circularize with SPS

DPS not ava~l - Lunar flyby or CSM only to lunar orbit (if reqd gtV lt4000 fps)

V37E 47E (check b~as) Record -=--rshy(Limit 98 fpsmm)

( 1fps)tVXYZN62EVIHDOTHPAD (fpsfpslnm)MONITOR VI ( ) at ECO

SCS TVC SERVO PWR 1 - ACIMNA2 - OFF

TAPE RCDR - CMD RESETHBREMS MODE - NORMAL

SIr SEP Lt - ONTLI Inhib~t S~gnals w~11 not be honored after 5942

SIVB ULLAGE BeginsSII SEP Lt - off (TIG - 18 sec)SIVB FUEL LEADSIVB ULLAGE d~scont~nues

LV ENG I Lt - onSIVB IGNITION ( GETI)LV ENG I Lt - off - -shyMONITOR THRUST amp ATTITUDEMONITOR LV TANK PRESSSIVE ECO (Lt on) (BEGIN TB7)

EMER SIVE CUTOFF AT 6 SEC PAST BURN TIME IF VI ATTAINEDTHC CCW ampNEUTRAL IN 1 SEC or SIISIVB sW - LV STAGEPremature Shutdown HAlt4K nm CSM amp 1M -

5700

58205836

F 16 835800

F 16 62

5838594259525955595900000002SUNRISE(___)

HAW AOS(__=_) KEY VERB (freeze d~splay)

SIVB ATT HOLD 20 sec amp BEGIN VENTINGSIVB NNVR TO ORB RT (HDS DN) (3middot sec)

Record VI -c---HDOT _

HPAD _

KEY RLSEF 16 62

F 16 83

HAW LOS(__=-)

KEYmiddotRLSE~VXYZ (lfps)

Record ~VX---_

~vy

WZ--

AVC---_

TAPE RCDR - off (ctr)EMS MODE - STBYEMS FUNC - OFFSECS PYRO ARM (2) - SAFE

PRO

BURN STATUS REPORT

____--~TIG

BT------VGX____-R

-----P----_Y

REMARKS

_____VI

______--HDOT______--H______---AVC______---FUEL_______OXID

_______UNBAL

F 3708=00 OOEGOS AOS CMP TO LEB

(-=-=-)

0000

0003

0005

0014

0100

-55-

62 TLI 10 MIN ABORTSECS LOGIC (2) - on (up)SECS PYRO ARM (2) - ARM

TRANS CONTR - CGH (4 sec) amp +XDET RESET (verlfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS GMD-ON

TRANS GONTR - neutral then +X for10 sec

SIVBGPI s~ - GPIExcesslve rates 6V THRUST A - NORMAL SPS THRUST - DIRECT When rates damped 6V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

TRANS CONTR +X - OFFV37E OOE

PITGH UP to LOGAL VERT (+X axlSto~ard the earth)

RATE - LOWBMAG MODE (3) - ATTIRATE 2EDS PHR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SEGS ARM (2) - opencb EDS (3) - open

TRANS CONTR -X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (180deg)P (199deg)Y (0deg)

RETRO UPDATEGETI _

JV _VG

Jtb ---GET 400K _

05G _GET DROGUE _

ENTRY P _R _

Y_--

0945

-56-

ALIGN HORIZ ON RET +1 MKGMBL CHECK (T11lle Pentattlng)MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conflnn)cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FUMC - JV SETVHF RNGSET JV from chartE~S FUMC - JVEMS fODE - NOIDlAL

lV THRUST A - NORMALV37E 47E (THRUST fONITOR)

F 16 83 lVXYZ (1 fps)

0950

1000

NOTE For aborts durlng 1st mln of TLIKEY V82E F 16 44 (HaHpTff)Burn untll Hp lt 19NM

TRANS CONTR +X

THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN JV reqdJV THRUST (2) - OFFReport cutoff

cb SPS P2 Y2- closeGfBL MTRS (4) - OFF (LMP Confinn)TRANS CONT PWR - OFFTVC SERVO PWR (2) - OFFMN BUS TIE (2) - OFFcb SPS P1amp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREIf est time to EIltOl5500 omlt fCC andenter the SUPERCIRC CKLIST as early as pos-slb1e Pg ~2~3~ __If est time to EI)Ol5500 anticlpate afCC Enter the ENTRY PREP CKLIST at step 9pg 18

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

-2tl C

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-i- rtREQUIRED PITCH GIMBAL ANG LETO OBTAIN HOR-IZON AT 317

DEGREES IN wiiiiDOW

260

z~I- ~ i5 24000

1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

-I

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NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

I LU HD~-

LUHD

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TOP OF WINDOWa 40to

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HOLO PRESENT TRIlJCl

LOHU0 lt0

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LDHUlt0 FIELD OF VI S10 NLDHU LIFT-DOWNHEADS -UPLUHD LIFT-UP HEADS-DOWN

~~H~-160 q - P63 LIMITI- NOrE-VALIO ONLY FO~t~--

LUNAR RETURN VELOCITY

plusmnl8020 244middot 8 12 16

TIME TO 400K FT ALTITUDE-MIN

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320

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-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 45: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

-42-

P62 - CMSM SEP amp PRE-ENTRY MNVR

9 F 50 25 00041 REQUEST CMSM SEPSC CONT - SCSFREEYAW - 45deg out-of-plane (left for RCS

nght for SPS)RATE - HIGHATT DB - MINMAN ATT (3) - RATE CMDBMAG MODE (3) - ATT1RATE2PRIM GLY to RAD - BYPASS (verlfy)SECS LOGIC (2) - on (up)MSFN conflrm GO for PYRO ARMSECS PYRO ARM - ARMMN BUS TIE (2) - ON (verlfy)CMSM SEF (2) - ONCSMLM FNl SEP (2) - on (up) (verlfy)CampW MODE - CMRCS TRNFR - CMCM RCS MANF PRESS - 287-302 pSlaCM RCS LOGIC - OFFSECS PYRO ARM - SAFEMonltor VMAB

If lt25vdc go to EMERG POWERDOWN Pg E6-1AUTO RCS SEL AlC ROLL (4) - OFFAUTO RCS SEL CM 2(6) - OFFAUTO RCS SEL CM 1(6) - MNA or MNBYAW back to 00

PITCH TO ENTRY ATTROLL 0deg (LIFT UP)PITCH - HORIZ on 317deg MARK (400K)YAW 00

ATT DB - MAXMAN ATT (PITCH) - ACCEL CMDEMS DATA - VerifyEMS FUNC - ENTRY (verlfy)EMS MODE - NORMALMAINTAIN HORIZ TRK

PRO (Act ENTRY DAP)

10 F 06 61 IMPACT LAT LONG HDSDN(010 010 -00001)

PRO

11 FOSS 06 22 FINAL ATT DISP RPY (01deg)(Only If X-axlS beyond 45deg of Vel vector)

-43-

P63 - ENTRY INIT

12 06 64 GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PWR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRHORIZ CKP~tch error needle goes toward

zero approach~ng 05G t~me

MAN ATT (PITCH) - RATE CMDIf CMC ~s GO

BMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS FLY BETA If CMC NO GO ~

SC CONT - SCS~

FLY EMS RCS Deorh Roll HDS UPTRACK HORIZ w~th 29deg w~ndow mk

P64 - ENTRY POST 05G

13

05G t=elt+0___)

06 68

RTOGO AT 05G AGREES WITH EMS - venfyHORIZ CK05E Lt - on (EMS start)

No EMS start w~th~n 3 secsEMS MODE - BACKUP VHF RNG 05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds L~ft DN

NNVR L~ft DNEMS GONO GO

G-V Plot w~th~n llm~ts

Rng ctr dwn 60 + 7 durlng 10 sec per~od

Mon~tor G-meter forconvergence wlth pad data (Do)

(Vlt27K fps) Go To 17

-44-

P65 - ENTRY - UP CONT (Vgt27K fps)

14 F 16 69 BETA (01deg)DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT~

SC CONT - SCS FLY EMS

PRO

15 06 68 BElA VI HOOT (01deg fpsfps)(VltVL +500 fps amp RDOT Neg) Go To 17

p66 - ENTRY - BALLISTIC (DltDL)

16 06 22 DESIRED GMBL ANGLES RPY (01deg)Mon~tor hor~z +12deg of 317deg mark

P67 - ENTRY - FINAL PHASE (02G)

17 0666 BETACRSRNG ERRDNRNG ERR (Oldeglnmlnm)KEY VERBRecord DNRNG ERR _KEY RLSEL~m~t +100nm from PAD DRE

Mon~tor l~ft vector on RSI amp FDAIF 16 67 RTOGOLATLONG (Vre1=1000fps)

(lnm 010 01deg)SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOlfflMon~tor altimeter

Go To EARTHLANDING pg _I4L5__

-45-

56 EARTHLANDING

90K STEAM PRESS - PEGGED50K CABIN PRESS REL vIv (2) - BOOSTENTRY

SECS PYRO ARM (2) - ARM

40K(90K + 63s)

CM UNSTABLE RCS CMD - OFF ~ 40K APEX COVER JETT PG-PUSH DROGUE DEPLOY PG - PUSH (2 secafter apex cover Jett)

30K ELS LOGIC - ON (up)ELS - AUTO

24K RCS hsable (auto)(90K+92s) RCS CMD - OFF

Apex cover Jett (auto)APEX COVER JETT PB - PUSH

(WAIT 2 SECS)Drogue parachutes deployed (auto)

DROGUE DEPLOY PB - PUSH~

If Drogues FallELS - ~ ~Stablllze CM 5K MAIN DPLY PB - PUSHELS - AUTO

235K Cabln Pressure lncreaslng (Drogues + 50s)If not lncreaSlng by 17K CABIN PRESS REL vlv (RR) - DUMP

-46-

10K Maln parachutes deployedMAIN DEPLOY PB - PUSH (wlthln 1 sec)VHF ANT - RECYVHF AMA - SIMPLEXVHF BCN - ONCABIN PRESS REL v1v (2) - CLOSEDIRECT 02 vlv - OPENCM RCS LOGIC - on (up)CM PRPLNT - DUMP (burn audlb1e)Monltor CM ReS 1amp2 for He press decrease

NO BURN or PRESS DECREASE USE BOTH RHCs DO NOT FIRE PITCH JETS

CM PRPLNT-PURGE (to zero He press)CM RCS He DUMP PB - PUSH RHC (2) - 30 sees NO PITCH k

STRUT LOCKS (2) - UNLOCK

cb FLT amp PL BAT BUS ABampBAT C (3) - closecb FLT amp PLT MNA amp B (2) - opencb ECS RAD HTR OVLD (2) - opencb SPS PampY (4) - open

3K CABIN PRESS REL v1v (RH) - DUMP (after purgecompleted)

FLOOD Lts - POST LDGCM RCS PRPLNT (2) - OFFROT CONTR PWR DIRECT (2) - OFF

800 CAB PRESS RELF vlv - CLOSE (latch off)MN BUS TIE (2) - OFF

AFTER LANDINGcb MAIN REL PYRO (2) - closeMAIN RELEASE - on(up)

Go to POSTLANDING pg _47L-__

I

2

3

-47-

57 POSTLANDING

STABILIZATION VENTILATION COMMUNICATIONS

DIRECT 02 vlv - CLOSE

Stablllzation after landlngELS - AUTO (verlfy)cb MAIN REL PYRO (2) - close (venfy)MAIN RELEASE - on (up) (verlfy)S~CS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb BAT RLY BUS (2) - open

No contact w1th recovery forcesVHF AM AampB - off (ctr) ~

VHF AM Rev ONLY - A cb PL VENT - closecb FLOAT BAG (3) - closecb UPRIGHT SYS COMPRESS (2) - closeIf Stable II

FLOAT BAG(3)-FILL t1ll 2 m1n afterupr1ght then - OFF

VHF AM AlB amp BCN - OFF whlle lnvertedIf Stable I

After 10 M1n Coollng Per1odFLOAT BAG (3) - FILL 7 mln then OFF

Post Stab1lizat1on And Ventllat10nPL BCN LT - BCN LT LOWPL VENT vlv - UNLOCK (Pull)Remove PL VENT Exh CoverPL VENT - HIGH or LOWPL DYE MARKER - ON (swlmmer comm)Release foots traps and_restralntscb MNA BAT BUS A amp BAT C (2) - opencb MNB BAT BUS B amp BAT C (2) - opencb FLT amp PL BAT C - opencb PYRO A SEQ A - opencb PYRO B SEQ B - open

EACH HR - CHECK DC VOLTSgt 275 V If Notmiddot cb FLT amp PL-BAT BUS AampB (2) -open cb FLT amp PL BAT C (1) - open GO TO LOW POWER CHECKLIST

Unstow and lnstall PLV DISTRIB DUCTDeploy grappllng hook and 11ne 1f req

4

-48-

Post Landing Communlcatl0nsVHF ANT-RECY (venfy)VHF BCN - ON (verlfy)

If no contact ~lth recovery forcesperform VHF BEACON Check

MONITOR VHF BEACON transmlSSlonnth VHF AM B Rcvr andor Su)vlval

TransceiverkVHF Beacon not operatlng ~connect Surv~val TranscelVer to antcable behlnd VHF ant access pnland place radio ln BCN mode

LOW POHER CHECKLISTVHF BCN - OFFVHF AM (3) - RCVFLOOD Lts - OFFVHF AM AampB - off (ctr)VHF AM RCV ONLY - A (venfy)COUCH LIGHTS - OFFPOSTLANDING VENT SYS mlnlmlze useSURV RADIO - plug mto VHF BCN ANT cableconn behind VHF ant acess pnl amp turn radloon l-n BCN mode

EGRESS PROCEDURES

CMPCDRLMPCDR

CMPCDRCMP

LMPLl1PCDR

STABLE IDlsconnect Umblll-calsNeck darn onCenter couch - 270 0 positionArmrests stowedConnect raft to SIC l-f desl-red wlth

green lanyardConnect raft ~hl-te lanyards to SUltS amp

lnflate water wlngs when eXltl-ngHATCH PISTON PRESS vlv - PRESS (Outbd)Slde Hatch openedPL VENT - OFFcb Pnl 250 (all) - openEgress with 11feraftPut hardware klt outEgress

or CDIPALL

CMF

CDRCMF

CDR

LMF

CMFCMP LMFCMP

UlP

CDR

-49-

STABLE IIcb CREW STA AUDIO (3) - openD~sconnect umb~1~ca1s

Release foots trapsRelease restra~nt harnessCouch seat pans (3) - 170 0 pos1t10nArm rests stowedSurv1va1 k~ts removed from stowageConnect life raft ma~n1~ne to CDR or SicConnect f~rst wh~te lanyard from

11fe raft to suitConnect th~rd wh~te lanyard from

l~fe raft to SU1tConnect rucksacks together to yellow

lanyard on raft bagPRESSURE EQUALIZATION vlv - OPENRemove and stow fwd hatchEX1t feet f1rst w1th rucksacks when clear

of siC 1nflate water w1ngs and raftExit feet f1rst when clear of SiC

1nflate water w1ngsEX1t feet f1rst when clear of sic

1nflate water w1ngs

-50-

60 TLI ABORTS

TLI Aborts are conta~ned ~n the ESD s~nce the bulk of the funct~ons

concern entry preparat20ns and performance Th~s allows a s2nglesource of procedures for procedure rev2ew val~dat~on checkout andtra~n~ng These procedures ~ncorporate TLI preparat20ns as found ~n

reference 6 w~th the TLI Abort Procedures and these t~e 2nto normallunar return Entry Procedures found ~n sect20n 5 The guidel~nes

for th~s cont2ngency are spec2f2ed 2n reference 7

In2t2al preparat~ons for TLI pos2t20n the necessary system sW2tches2n add~t~on to perform~ng an EMS ~V test and a GDC al~gnment Afterthe DET ~s set for mon2tor2ng TB6 the CMP ~ncreases the 12ght levelof the LEB DSKY to max~mum and returns to the h2s couch Th2s 2Sdone so that the LEB DSKY can be observed ~n the event sunl~ght orreflect20ns wash out the ma2n d2splay panel DSKY dur2ng cr2t2calmaneuvers The crew then straps ~n and prepares for mon2tor~ng TB6as 2nd2cated by the SII SEP L~te The t2mes se~uence of procedures2S keyed on th~s d~splay and ~ncludes the DET START funct~on andSIVB IGNITION Dur2ng the burn the crew mon2tors the FDAIs foratt~tude excurs20ns and abnormal rates report~ng status checks toM~ss2on Control at d2screet t~mes dur2ng the maneuver Upon SIVBSHUTDOWN the eMP records the DSKY d~splayed performance parametersand awa2ts ground conf2rmat~on

The rat~onal for TLI aborts ~s descr~bed 2n reference 7 A summar2shyzat20n 2S extracted to prov2de background and gu2de12nes 2n th2sdocument The abort procedures cover aborts 10 m2nutes after conshyt2ngent SIVE shutdown and aborts 90 m2nutes after normal SIVE shutshydown t2me

The 10 m~nute TLI abort ~s des2gned to be used dur~ng TLI ~n theevent a spacecraft problem develops Wh2Ch can result 2n catastrophe2f ~mmed~ate act~on 2S not taken If the s~tuat20n perm~ts the crewshould always allow the SIVB to complete TLI at wh~ch t~me the groundand crew can perform a malfunct~on analys~s to determ~ne ~f an abort~s adv~sable If a fa~lure occurs that necess2tates the shutdown ofthe SIVB and the ~u~ck return of the crew to earth th~s abort ~s

des~gned to be as ~nsens~t~ve to execut~on errors as poss~ble andst21l be targeted to m2dcorr2dor The burn att~tude w~th the f~ed

hor~zon reference ~s a constant value for any shutdown t~me Theburn durat~on 2S a funct20n of shutdown t2me and 2S ava21able fromcrew charts S~nce the pr~mary purpose of th~s abort ~s to returnto earth as qU2ckly as poss2ble there are no restr2ct20ns as toland~ng locat~on However ~f the t~me to EI is greater than abouttwo hours a midcourse correct20n should be ant~c~pated

The 90 m2nute TLI abort 2S to be used 2f a cr2t2cal subsystem malshyfunct~on ~s determ2ned and the dec2s~on to abort ~s made after the

-51-

TLI cutoff and before TLI cutoff plus approxlmately 80 m1nutesTh1S allows suff1c1ent separatlon and procedural t1me to set upfor the SPS deorb1t burn performed at about TLI + 90 Note thatgenerally the deorb1t burns w1ll be performed a fe11 m1nutes beforeTLI + 90 accord1ng to crew charts shown In reference 8 The no-comm except10n requ1res that 90 m1nutes be the 1nput t1me of 19n1shytlon for P-37 (onboard return-to-earth abort program) so that onshyboard calculatlons can correspond w1th ground calculat10ns to computethe CM land1ng p01nt Th1S TLI abort lS des1gned so that returnfl1ght t1me does not exceed 18 hours and abort ~V does not exceed7000 fps ThlS abort can be performed uSlng chart ~Vs and attltudesand the earths hor1zon serves as a suff1c1ent reference The maneushyver lS targeted to ach1eve the mldcorr1dor entry target Ilne andtlmed to result 1n a deslgnated recovery area

It 1S ObV10US for abort deC1S1ons early 1n the TLI + 90 m1nute t1meshyframe that a GampN SPS burn should be performed In order to keep theTLI abort procedures cons1stent and w1th emphasls on slmpl1c1ty theprocedures here reflect a SCS SPS abort burn to cover the full abortdec1s1on t1meframe

A m1dcourse correct1on for corr1dor control after a TLI abort may bedeS1red 1f the SPS burn d1d not meet expectat1ons The TLIabortprocedures 1n th1S sect10n adapt to the normal lunar return tlmel1neand procedures pr10r to the f1nal MCC

-52-

61 TLI PREPARATION PROCEDURES

GET = 150

CRO AOS(___)

CRO LOS( )(22142)

5100

Don Helmets amp Gloves

XLUNAR - INJECT (verify)EDS PWR - on (venfy)EMS FUNC - OFF (verlfy)EMS MODE - STBYEMS FUNC - IW SETVHF RNGEMS MODE - NORMALSet ~V indo to +15868 fpsEMS FUMC - ~V Test

SPS THRUST Lt - onoff (10 sec)~V lnd stops at -01 to -415

EMS MODE - STBYEMS FUMC - ~V SETVHF RNGSet ~VC

EMS FUNC---~~V=----

GDC ALIGNFDAI Select - liZcb SECS LOGIC (Z) - close (verify)cb SECS ARM (Z) - closeSECS LOGIC (Z) - on (up)MSFN Conflrm GO for PYRO ARM (If pass)SECS PYRO ARM (Z) - on (up)TRANS CONTROL PWR - ONROT CONTR PWR NORMAL (Z) - ACDC(verlfy)ROT CONTR PWR DIRECT (Z) - MNAMNBLV INnGPI - SIISIVB (venfy)LV GUID - IU (venfy)cb DIRECT ULLAGE (Z) - closedSet EVENT TIMER to 5100Begin MONITOR For TB6

CMP to Couch

TB 6 - SII SEP Lt on (TIG-9 mln 38 sec)KEY V83E

SET ORDEALFDAI Z ORB RATE at 180 0 0SII SEP Lt out (38 sec later)Start DET COUNTING UPSC CaNT - SCS (verify)MONITOR LV TANK PRESS

~P lt 36 psid (OXID gt FUEL)~P lt Z6 psid (FUEL gt OXID)

EMERGENCY CSMLV SEP UP TLM CM - BLOCK (verify)UP TLM IU - BLOCK (venfy)

-53-

+45degPY))0middot sec PY

lOK nmltHAlt25K nm

Two phas~ng mnvrs two SPS mnvrs to circular~ze at 150 nmearth orb~t

CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ssion 4K nmltHAltlOK nm CSM amp1M - Two phasing mnvrs two SPS mnvrs to circularize at 150 nm earth orb~t CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ss~on

CSM amp 1M - Two phas~ng mnvrs APS burn todepletion th~rd phasing mnvrSPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn tosem~sync orb~t

25K nmltHAlt40K nm CSM amp 1M - Two phasmg mnvrs APS burn to depletion third phas~ng mnvr SPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn to sem~sync orbit HA)40K nm DPS ava~l - DPS LOll circularize with SPS

DPS not ava~l - Lunar flyby or CSM only to lunar orbit (if reqd gtV lt4000 fps)

V37E 47E (check b~as) Record -=--rshy(Limit 98 fpsmm)

( 1fps)tVXYZN62EVIHDOTHPAD (fpsfpslnm)MONITOR VI ( ) at ECO

SCS TVC SERVO PWR 1 - ACIMNA2 - OFF

TAPE RCDR - CMD RESETHBREMS MODE - NORMAL

SIr SEP Lt - ONTLI Inhib~t S~gnals w~11 not be honored after 5942

SIVB ULLAGE BeginsSII SEP Lt - off (TIG - 18 sec)SIVB FUEL LEADSIVB ULLAGE d~scont~nues

LV ENG I Lt - onSIVB IGNITION ( GETI)LV ENG I Lt - off - -shyMONITOR THRUST amp ATTITUDEMONITOR LV TANK PRESSSIVE ECO (Lt on) (BEGIN TB7)

EMER SIVE CUTOFF AT 6 SEC PAST BURN TIME IF VI ATTAINEDTHC CCW ampNEUTRAL IN 1 SEC or SIISIVB sW - LV STAGEPremature Shutdown HAlt4K nm CSM amp 1M -

5700

58205836

F 16 835800

F 16 62

5838594259525955595900000002SUNRISE(___)

HAW AOS(__=_) KEY VERB (freeze d~splay)

SIVB ATT HOLD 20 sec amp BEGIN VENTINGSIVB NNVR TO ORB RT (HDS DN) (3middot sec)

Record VI -c---HDOT _

HPAD _

KEY RLSEF 16 62

F 16 83

HAW LOS(__=-)

KEYmiddotRLSE~VXYZ (lfps)

Record ~VX---_

~vy

WZ--

AVC---_

TAPE RCDR - off (ctr)EMS MODE - STBYEMS FUNC - OFFSECS PYRO ARM (2) - SAFE

PRO

BURN STATUS REPORT

____--~TIG

BT------VGX____-R

-----P----_Y

REMARKS

_____VI

______--HDOT______--H______---AVC______---FUEL_______OXID

_______UNBAL

F 3708=00 OOEGOS AOS CMP TO LEB

(-=-=-)

0000

0003

0005

0014

0100

-55-

62 TLI 10 MIN ABORTSECS LOGIC (2) - on (up)SECS PYRO ARM (2) - ARM

TRANS CONTR - CGH (4 sec) amp +XDET RESET (verlfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS GMD-ON

TRANS GONTR - neutral then +X for10 sec

SIVBGPI s~ - GPIExcesslve rates 6V THRUST A - NORMAL SPS THRUST - DIRECT When rates damped 6V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

TRANS CONTR +X - OFFV37E OOE

PITGH UP to LOGAL VERT (+X axlSto~ard the earth)

RATE - LOWBMAG MODE (3) - ATTIRATE 2EDS PHR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SEGS ARM (2) - opencb EDS (3) - open

TRANS CONTR -X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (180deg)P (199deg)Y (0deg)

RETRO UPDATEGETI _

JV _VG

Jtb ---GET 400K _

05G _GET DROGUE _

ENTRY P _R _

Y_--

0945

-56-

ALIGN HORIZ ON RET +1 MKGMBL CHECK (T11lle Pentattlng)MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conflnn)cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FUMC - JV SETVHF RNGSET JV from chartE~S FUMC - JVEMS fODE - NOIDlAL

lV THRUST A - NORMALV37E 47E (THRUST fONITOR)

F 16 83 lVXYZ (1 fps)

0950

1000

NOTE For aborts durlng 1st mln of TLIKEY V82E F 16 44 (HaHpTff)Burn untll Hp lt 19NM

TRANS CONTR +X

THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN JV reqdJV THRUST (2) - OFFReport cutoff

cb SPS P2 Y2- closeGfBL MTRS (4) - OFF (LMP Confinn)TRANS CONT PWR - OFFTVC SERVO PWR (2) - OFFMN BUS TIE (2) - OFFcb SPS P1amp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREIf est time to EIltOl5500 omlt fCC andenter the SUPERCIRC CKLIST as early as pos-slb1e Pg ~2~3~ __If est time to EI)Ol5500 anticlpate afCC Enter the ENTRY PREP CKLIST at step 9pg 18

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

-2tl C

l I W gt- ~-4

z laquo I I- 0 -6

l- I J u gt- ~-8

z w w -10

~_ONSANT

9O

VER

SHO

OT

BOU

ND

ARY

LIF

TV

EC

TOR

OR

IEN

TATI

ON

LIN

E

SH

ALL

OW

TAR

GE

TLI

NE

STE

EP

TAR

GE

TLI

NE 12

gU

ND

ERSH

OO

TBO

UN

DAR

Y

RE

EN

TRY

CO

RR

IDO

R

I ~ I

-12 24

26

28

30

32

34

RE

EN

TRY

VE

LOC

ITY

VE

1-F

TS

EC

Ch

art

1

36

3B

6-i

~

5CM

CC

ON

ST

NT

DR

VI z gt

~

I4

0 Cl W

I

gtamp

J+

-I

-

J Cl z

2U

l z 0_bull

bull-1

+-

u ubullbull

~r

U

)

2829

JOn

J23

33

43

5IN

ER

TIA

LR

EE

NTR

YV

ELO

CIT

YA

T4

00

00

0fl

VE

I-F

TS

EC

Ch

art

2

J63

73

8X

03

-i- rtREQUIRED PITCH GIMBAL ANG LETO OBTAIN HOR-IZON AT 317

DEGREES IN wiiiiDOW

260

z~I- ~ i5 24000

1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

-I

-1-

NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

I LU HD~-

LUHD

lt0 120UJ0

~

80 HOLD PRESENT TRIMgt LU HD013

~Y~HOIgtlt

TOP OF WINDOWa 40to

31 7 SCRIBEaaI

80 TTOM OF WINDOWi= 0

0--ltoa

-40t-z

~~~Uw w u lt0 -80

HOLO PRESENT TRIlJCl

LOHU0 lt0

J gt -120 HOLD 059 TRIMlt0 z

LDHUlt0 FIELD OF VI S10 NLDHU LIFT-DOWNHEADS -UPLUHD LIFT-UP HEADS-DOWN

~~H~-160 q - P63 LIMITI- NOrE-VALIO ONLY FO~t~--

LUNAR RETURN VELOCITY

plusmnl8020 244middot 8 12 16

TIME TO 400K FT ALTITUDE-MIN

4

P37

LONG

ITUD

ECO

RREC

TION

TOOB

TAIN

1350

NM

ENTR

YRA

NGE

Ugt

UJ

cgt

3z 0 I- u U

J0

0

0

2I

U~

UJ

cgt

I

gtI- U

gt z 0 J ltJ

1 -0

340

344

348

352

356

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120

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320

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-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 46: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

-43-

P63 - ENTRY INIT

12 06 64 GVIRTOGO (OlGfpslnm)FDAI SCALE - 5015ROT CONTR PWR DIR (both) - MNAMNBTAPE RCDR - CMD RESETHBRHORIZ CKP~tch error needle goes toward

zero approach~ng 05G t~me

MAN ATT (PITCH) - RATE CMDIf CMC ~s GO

BMAG MODE (3) - RATE 2SC CONT - CMCAUTO

If DAP NO GO SC CONT - SCS FLY BETA If CMC NO GO ~

SC CONT - SCS~

FLY EMS RCS Deorh Roll HDS UPTRACK HORIZ w~th 29deg w~ndow mk

P64 - ENTRY POST 05G

13

05G t=elt+0___)

06 68

RTOGO AT 05G AGREES WITH EMS - venfyHORIZ CK05E Lt - on (EMS start)

No EMS start w~th~n 3 secsEMS MODE - BACKUP VHF RNG 05G sw - on (up)EMS ROLL - on (up)

BETA VI HDOT (Olofpsfps)Compare RSI amp FDAIIf CMC or PAD cmds L~ft DN

NNVR L~ft DNEMS GONO GO

G-V Plot w~th~n llm~ts

Rng ctr dwn 60 + 7 durlng 10 sec per~od

Mon~tor G-meter forconvergence wlth pad data (Do)

(Vlt27K fps) Go To 17

-44-

P65 - ENTRY - UP CONT (Vgt27K fps)

14 F 16 69 BETA (01deg)DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT~

SC CONT - SCS FLY EMS

PRO

15 06 68 BElA VI HOOT (01deg fpsfps)(VltVL +500 fps amp RDOT Neg) Go To 17

p66 - ENTRY - BALLISTIC (DltDL)

16 06 22 DESIRED GMBL ANGLES RPY (01deg)Mon~tor hor~z +12deg of 317deg mark

P67 - ENTRY - FINAL PHASE (02G)

17 0666 BETACRSRNG ERRDNRNG ERR (Oldeglnmlnm)KEY VERBRecord DNRNG ERR _KEY RLSEL~m~t +100nm from PAD DRE

Mon~tor l~ft vector on RSI amp FDAIF 16 67 RTOGOLATLONG (Vre1=1000fps)

(lnm 010 01deg)SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOlfflMon~tor altimeter

Go To EARTHLANDING pg _I4L5__

-45-

56 EARTHLANDING

90K STEAM PRESS - PEGGED50K CABIN PRESS REL vIv (2) - BOOSTENTRY

SECS PYRO ARM (2) - ARM

40K(90K + 63s)

CM UNSTABLE RCS CMD - OFF ~ 40K APEX COVER JETT PG-PUSH DROGUE DEPLOY PG - PUSH (2 secafter apex cover Jett)

30K ELS LOGIC - ON (up)ELS - AUTO

24K RCS hsable (auto)(90K+92s) RCS CMD - OFF

Apex cover Jett (auto)APEX COVER JETT PB - PUSH

(WAIT 2 SECS)Drogue parachutes deployed (auto)

DROGUE DEPLOY PB - PUSH~

If Drogues FallELS - ~ ~Stablllze CM 5K MAIN DPLY PB - PUSHELS - AUTO

235K Cabln Pressure lncreaslng (Drogues + 50s)If not lncreaSlng by 17K CABIN PRESS REL vlv (RR) - DUMP

-46-

10K Maln parachutes deployedMAIN DEPLOY PB - PUSH (wlthln 1 sec)VHF ANT - RECYVHF AMA - SIMPLEXVHF BCN - ONCABIN PRESS REL v1v (2) - CLOSEDIRECT 02 vlv - OPENCM RCS LOGIC - on (up)CM PRPLNT - DUMP (burn audlb1e)Monltor CM ReS 1amp2 for He press decrease

NO BURN or PRESS DECREASE USE BOTH RHCs DO NOT FIRE PITCH JETS

CM PRPLNT-PURGE (to zero He press)CM RCS He DUMP PB - PUSH RHC (2) - 30 sees NO PITCH k

STRUT LOCKS (2) - UNLOCK

cb FLT amp PL BAT BUS ABampBAT C (3) - closecb FLT amp PLT MNA amp B (2) - opencb ECS RAD HTR OVLD (2) - opencb SPS PampY (4) - open

3K CABIN PRESS REL v1v (RH) - DUMP (after purgecompleted)

FLOOD Lts - POST LDGCM RCS PRPLNT (2) - OFFROT CONTR PWR DIRECT (2) - OFF

800 CAB PRESS RELF vlv - CLOSE (latch off)MN BUS TIE (2) - OFF

AFTER LANDINGcb MAIN REL PYRO (2) - closeMAIN RELEASE - on(up)

Go to POSTLANDING pg _47L-__

I

2

3

-47-

57 POSTLANDING

STABILIZATION VENTILATION COMMUNICATIONS

DIRECT 02 vlv - CLOSE

Stablllzation after landlngELS - AUTO (verlfy)cb MAIN REL PYRO (2) - close (venfy)MAIN RELEASE - on (up) (verlfy)S~CS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb BAT RLY BUS (2) - open

No contact w1th recovery forcesVHF AM AampB - off (ctr) ~

VHF AM Rev ONLY - A cb PL VENT - closecb FLOAT BAG (3) - closecb UPRIGHT SYS COMPRESS (2) - closeIf Stable II

FLOAT BAG(3)-FILL t1ll 2 m1n afterupr1ght then - OFF

VHF AM AlB amp BCN - OFF whlle lnvertedIf Stable I

After 10 M1n Coollng Per1odFLOAT BAG (3) - FILL 7 mln then OFF

Post Stab1lizat1on And Ventllat10nPL BCN LT - BCN LT LOWPL VENT vlv - UNLOCK (Pull)Remove PL VENT Exh CoverPL VENT - HIGH or LOWPL DYE MARKER - ON (swlmmer comm)Release foots traps and_restralntscb MNA BAT BUS A amp BAT C (2) - opencb MNB BAT BUS B amp BAT C (2) - opencb FLT amp PL BAT C - opencb PYRO A SEQ A - opencb PYRO B SEQ B - open

EACH HR - CHECK DC VOLTSgt 275 V If Notmiddot cb FLT amp PL-BAT BUS AampB (2) -open cb FLT amp PL BAT C (1) - open GO TO LOW POWER CHECKLIST

Unstow and lnstall PLV DISTRIB DUCTDeploy grappllng hook and 11ne 1f req

4

-48-

Post Landing Communlcatl0nsVHF ANT-RECY (venfy)VHF BCN - ON (verlfy)

If no contact ~lth recovery forcesperform VHF BEACON Check

MONITOR VHF BEACON transmlSSlonnth VHF AM B Rcvr andor Su)vlval

TransceiverkVHF Beacon not operatlng ~connect Surv~val TranscelVer to antcable behlnd VHF ant access pnland place radio ln BCN mode

LOW POHER CHECKLISTVHF BCN - OFFVHF AM (3) - RCVFLOOD Lts - OFFVHF AM AampB - off (ctr)VHF AM RCV ONLY - A (venfy)COUCH LIGHTS - OFFPOSTLANDING VENT SYS mlnlmlze useSURV RADIO - plug mto VHF BCN ANT cableconn behind VHF ant acess pnl amp turn radloon l-n BCN mode

EGRESS PROCEDURES

CMPCDRLMPCDR

CMPCDRCMP

LMPLl1PCDR

STABLE IDlsconnect Umblll-calsNeck darn onCenter couch - 270 0 positionArmrests stowedConnect raft to SIC l-f desl-red wlth

green lanyardConnect raft ~hl-te lanyards to SUltS amp

lnflate water wlngs when eXltl-ngHATCH PISTON PRESS vlv - PRESS (Outbd)Slde Hatch openedPL VENT - OFFcb Pnl 250 (all) - openEgress with 11feraftPut hardware klt outEgress

or CDIPALL

CMF

CDRCMF

CDR

LMF

CMFCMP LMFCMP

UlP

CDR

-49-

STABLE IIcb CREW STA AUDIO (3) - openD~sconnect umb~1~ca1s

Release foots trapsRelease restra~nt harnessCouch seat pans (3) - 170 0 pos1t10nArm rests stowedSurv1va1 k~ts removed from stowageConnect life raft ma~n1~ne to CDR or SicConnect f~rst wh~te lanyard from

11fe raft to suitConnect th~rd wh~te lanyard from

l~fe raft to SU1tConnect rucksacks together to yellow

lanyard on raft bagPRESSURE EQUALIZATION vlv - OPENRemove and stow fwd hatchEX1t feet f1rst w1th rucksacks when clear

of siC 1nflate water w1ngs and raftExit feet f1rst when clear of SiC

1nflate water w1ngsEX1t feet f1rst when clear of sic

1nflate water w1ngs

-50-

60 TLI ABORTS

TLI Aborts are conta~ned ~n the ESD s~nce the bulk of the funct~ons

concern entry preparat20ns and performance Th~s allows a s2nglesource of procedures for procedure rev2ew val~dat~on checkout andtra~n~ng These procedures ~ncorporate TLI preparat20ns as found ~n

reference 6 w~th the TLI Abort Procedures and these t~e 2nto normallunar return Entry Procedures found ~n sect20n 5 The guidel~nes

for th~s cont2ngency are spec2f2ed 2n reference 7

In2t2al preparat~ons for TLI pos2t20n the necessary system sW2tches2n add~t~on to perform~ng an EMS ~V test and a GDC al~gnment Afterthe DET ~s set for mon2tor2ng TB6 the CMP ~ncreases the 12ght levelof the LEB DSKY to max~mum and returns to the h2s couch Th2s 2Sdone so that the LEB DSKY can be observed ~n the event sunl~ght orreflect20ns wash out the ma2n d2splay panel DSKY dur2ng cr2t2calmaneuvers The crew then straps ~n and prepares for mon2tor~ng TB6as 2nd2cated by the SII SEP L~te The t2mes se~uence of procedures2S keyed on th~s d~splay and ~ncludes the DET START funct~on andSIVB IGNITION Dur2ng the burn the crew mon2tors the FDAIs foratt~tude excurs20ns and abnormal rates report~ng status checks toM~ss2on Control at d2screet t~mes dur2ng the maneuver Upon SIVBSHUTDOWN the eMP records the DSKY d~splayed performance parametersand awa2ts ground conf2rmat~on

The rat~onal for TLI aborts ~s descr~bed 2n reference 7 A summar2shyzat20n 2S extracted to prov2de background and gu2de12nes 2n th2sdocument The abort procedures cover aborts 10 m2nutes after conshyt2ngent SIVE shutdown and aborts 90 m2nutes after normal SIVE shutshydown t2me

The 10 m~nute TLI abort ~s des2gned to be used dur~ng TLI ~n theevent a spacecraft problem develops Wh2Ch can result 2n catastrophe2f ~mmed~ate act~on 2S not taken If the s~tuat20n perm~ts the crewshould always allow the SIVB to complete TLI at wh~ch t~me the groundand crew can perform a malfunct~on analys~s to determ~ne ~f an abort~s adv~sable If a fa~lure occurs that necess2tates the shutdown ofthe SIVB and the ~u~ck return of the crew to earth th~s abort ~s

des~gned to be as ~nsens~t~ve to execut~on errors as poss~ble andst21l be targeted to m2dcorr2dor The burn att~tude w~th the f~ed

hor~zon reference ~s a constant value for any shutdown t~me Theburn durat~on 2S a funct20n of shutdown t2me and 2S ava21able fromcrew charts S~nce the pr~mary purpose of th~s abort ~s to returnto earth as qU2ckly as poss2ble there are no restr2ct20ns as toland~ng locat~on However ~f the t~me to EI is greater than abouttwo hours a midcourse correct20n should be ant~c~pated

The 90 m2nute TLI abort 2S to be used 2f a cr2t2cal subsystem malshyfunct~on ~s determ2ned and the dec2s~on to abort ~s made after the

-51-

TLI cutoff and before TLI cutoff plus approxlmately 80 m1nutesTh1S allows suff1c1ent separatlon and procedural t1me to set upfor the SPS deorb1t burn performed at about TLI + 90 Note thatgenerally the deorb1t burns w1ll be performed a fe11 m1nutes beforeTLI + 90 accord1ng to crew charts shown In reference 8 The no-comm except10n requ1res that 90 m1nutes be the 1nput t1me of 19n1shytlon for P-37 (onboard return-to-earth abort program) so that onshyboard calculatlons can correspond w1th ground calculat10ns to computethe CM land1ng p01nt Th1S TLI abort lS des1gned so that returnfl1ght t1me does not exceed 18 hours and abort ~V does not exceed7000 fps ThlS abort can be performed uSlng chart ~Vs and attltudesand the earths hor1zon serves as a suff1c1ent reference The maneushyver lS targeted to ach1eve the mldcorr1dor entry target Ilne andtlmed to result 1n a deslgnated recovery area

It 1S ObV10US for abort deC1S1ons early 1n the TLI + 90 m1nute t1meshyframe that a GampN SPS burn should be performed In order to keep theTLI abort procedures cons1stent and w1th emphasls on slmpl1c1ty theprocedures here reflect a SCS SPS abort burn to cover the full abortdec1s1on t1meframe

A m1dcourse correct1on for corr1dor control after a TLI abort may bedeS1red 1f the SPS burn d1d not meet expectat1ons The TLIabortprocedures 1n th1S sect10n adapt to the normal lunar return tlmel1neand procedures pr10r to the f1nal MCC

-52-

61 TLI PREPARATION PROCEDURES

GET = 150

CRO AOS(___)

CRO LOS( )(22142)

5100

Don Helmets amp Gloves

XLUNAR - INJECT (verify)EDS PWR - on (venfy)EMS FUNC - OFF (verlfy)EMS MODE - STBYEMS FUNC - IW SETVHF RNGEMS MODE - NORMALSet ~V indo to +15868 fpsEMS FUMC - ~V Test

SPS THRUST Lt - onoff (10 sec)~V lnd stops at -01 to -415

EMS MODE - STBYEMS FUMC - ~V SETVHF RNGSet ~VC

EMS FUNC---~~V=----

GDC ALIGNFDAI Select - liZcb SECS LOGIC (Z) - close (verify)cb SECS ARM (Z) - closeSECS LOGIC (Z) - on (up)MSFN Conflrm GO for PYRO ARM (If pass)SECS PYRO ARM (Z) - on (up)TRANS CONTROL PWR - ONROT CONTR PWR NORMAL (Z) - ACDC(verlfy)ROT CONTR PWR DIRECT (Z) - MNAMNBLV INnGPI - SIISIVB (venfy)LV GUID - IU (venfy)cb DIRECT ULLAGE (Z) - closedSet EVENT TIMER to 5100Begin MONITOR For TB6

CMP to Couch

TB 6 - SII SEP Lt on (TIG-9 mln 38 sec)KEY V83E

SET ORDEALFDAI Z ORB RATE at 180 0 0SII SEP Lt out (38 sec later)Start DET COUNTING UPSC CaNT - SCS (verify)MONITOR LV TANK PRESS

~P lt 36 psid (OXID gt FUEL)~P lt Z6 psid (FUEL gt OXID)

EMERGENCY CSMLV SEP UP TLM CM - BLOCK (verify)UP TLM IU - BLOCK (venfy)

-53-

+45degPY))0middot sec PY

lOK nmltHAlt25K nm

Two phas~ng mnvrs two SPS mnvrs to circular~ze at 150 nmearth orb~t

CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ssion 4K nmltHAltlOK nm CSM amp1M - Two phasing mnvrs two SPS mnvrs to circularize at 150 nm earth orb~t CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ss~on

CSM amp 1M - Two phas~ng mnvrs APS burn todepletion th~rd phasing mnvrSPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn tosem~sync orb~t

25K nmltHAlt40K nm CSM amp 1M - Two phasmg mnvrs APS burn to depletion third phas~ng mnvr SPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn to sem~sync orbit HA)40K nm DPS ava~l - DPS LOll circularize with SPS

DPS not ava~l - Lunar flyby or CSM only to lunar orbit (if reqd gtV lt4000 fps)

V37E 47E (check b~as) Record -=--rshy(Limit 98 fpsmm)

( 1fps)tVXYZN62EVIHDOTHPAD (fpsfpslnm)MONITOR VI ( ) at ECO

SCS TVC SERVO PWR 1 - ACIMNA2 - OFF

TAPE RCDR - CMD RESETHBREMS MODE - NORMAL

SIr SEP Lt - ONTLI Inhib~t S~gnals w~11 not be honored after 5942

SIVB ULLAGE BeginsSII SEP Lt - off (TIG - 18 sec)SIVB FUEL LEADSIVB ULLAGE d~scont~nues

LV ENG I Lt - onSIVB IGNITION ( GETI)LV ENG I Lt - off - -shyMONITOR THRUST amp ATTITUDEMONITOR LV TANK PRESSSIVE ECO (Lt on) (BEGIN TB7)

EMER SIVE CUTOFF AT 6 SEC PAST BURN TIME IF VI ATTAINEDTHC CCW ampNEUTRAL IN 1 SEC or SIISIVB sW - LV STAGEPremature Shutdown HAlt4K nm CSM amp 1M -

5700

58205836

F 16 835800

F 16 62

5838594259525955595900000002SUNRISE(___)

HAW AOS(__=_) KEY VERB (freeze d~splay)

SIVB ATT HOLD 20 sec amp BEGIN VENTINGSIVB NNVR TO ORB RT (HDS DN) (3middot sec)

Record VI -c---HDOT _

HPAD _

KEY RLSEF 16 62

F 16 83

HAW LOS(__=-)

KEYmiddotRLSE~VXYZ (lfps)

Record ~VX---_

~vy

WZ--

AVC---_

TAPE RCDR - off (ctr)EMS MODE - STBYEMS FUNC - OFFSECS PYRO ARM (2) - SAFE

PRO

BURN STATUS REPORT

____--~TIG

BT------VGX____-R

-----P----_Y

REMARKS

_____VI

______--HDOT______--H______---AVC______---FUEL_______OXID

_______UNBAL

F 3708=00 OOEGOS AOS CMP TO LEB

(-=-=-)

0000

0003

0005

0014

0100

-55-

62 TLI 10 MIN ABORTSECS LOGIC (2) - on (up)SECS PYRO ARM (2) - ARM

TRANS CONTR - CGH (4 sec) amp +XDET RESET (verlfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS GMD-ON

TRANS GONTR - neutral then +X for10 sec

SIVBGPI s~ - GPIExcesslve rates 6V THRUST A - NORMAL SPS THRUST - DIRECT When rates damped 6V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

TRANS CONTR +X - OFFV37E OOE

PITGH UP to LOGAL VERT (+X axlSto~ard the earth)

RATE - LOWBMAG MODE (3) - ATTIRATE 2EDS PHR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SEGS ARM (2) - opencb EDS (3) - open

TRANS CONTR -X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (180deg)P (199deg)Y (0deg)

RETRO UPDATEGETI _

JV _VG

Jtb ---GET 400K _

05G _GET DROGUE _

ENTRY P _R _

Y_--

0945

-56-

ALIGN HORIZ ON RET +1 MKGMBL CHECK (T11lle Pentattlng)MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conflnn)cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FUMC - JV SETVHF RNGSET JV from chartE~S FUMC - JVEMS fODE - NOIDlAL

lV THRUST A - NORMALV37E 47E (THRUST fONITOR)

F 16 83 lVXYZ (1 fps)

0950

1000

NOTE For aborts durlng 1st mln of TLIKEY V82E F 16 44 (HaHpTff)Burn untll Hp lt 19NM

TRANS CONTR +X

THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN JV reqdJV THRUST (2) - OFFReport cutoff

cb SPS P2 Y2- closeGfBL MTRS (4) - OFF (LMP Confinn)TRANS CONT PWR - OFFTVC SERVO PWR (2) - OFFMN BUS TIE (2) - OFFcb SPS P1amp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREIf est time to EIltOl5500 omlt fCC andenter the SUPERCIRC CKLIST as early as pos-slb1e Pg ~2~3~ __If est time to EI)Ol5500 anticlpate afCC Enter the ENTRY PREP CKLIST at step 9pg 18

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

-2tl C

l I W gt- ~-4

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TAR

GE

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28

30

32

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RE

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03

-i- rtREQUIRED PITCH GIMBAL ANG LETO OBTAIN HOR-IZON AT 317

DEGREES IN wiiiiDOW

260

z~I- ~ i5 24000

1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

-I

-1-

NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

I LU HD~-

LUHD

lt0 120UJ0

~

80 HOLD PRESENT TRIMgt LU HD013

~Y~HOIgtlt

TOP OF WINDOWa 40to

31 7 SCRIBEaaI

80 TTOM OF WINDOWi= 0

0--ltoa

-40t-z

~~~Uw w u lt0 -80

HOLO PRESENT TRIlJCl

LOHU0 lt0

J gt -120 HOLD 059 TRIMlt0 z

LDHUlt0 FIELD OF VI S10 NLDHU LIFT-DOWNHEADS -UPLUHD LIFT-UP HEADS-DOWN

~~H~-160 q - P63 LIMITI- NOrE-VALIO ONLY FO~t~--

LUNAR RETURN VELOCITY

plusmnl8020 244middot 8 12 16

TIME TO 400K FT ALTITUDE-MIN

4

P37

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352

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320

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-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 47: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

-44-

P65 - ENTRY - UP CONT (Vgt27K fps)

14 F 16 69 BETA (01deg)DL (OlG) PAD _VL (fps) PAD _

IF NO AGREEMENT~

SC CONT - SCS FLY EMS

PRO

15 06 68 BElA VI HOOT (01deg fpsfps)(VltVL +500 fps amp RDOT Neg) Go To 17

p66 - ENTRY - BALLISTIC (DltDL)

16 06 22 DESIRED GMBL ANGLES RPY (01deg)Mon~tor hor~z +12deg of 317deg mark

P67 - ENTRY - FINAL PHASE (02G)

17 0666 BETACRSRNG ERRDNRNG ERR (Oldeglnmlnm)KEY VERBRecord DNRNG ERR _KEY RLSEL~m~t +100nm from PAD DRE

Mon~tor l~ft vector on RSI amp FDAIF 16 67 RTOGOLATLONG (Vre1=1000fps)

(lnm 010 01deg)SC CONT - SCSRTOGO NEG - LIFT UPRTOGO POS - LIFT DOlfflMon~tor altimeter

Go To EARTHLANDING pg _I4L5__

-45-

56 EARTHLANDING

90K STEAM PRESS - PEGGED50K CABIN PRESS REL vIv (2) - BOOSTENTRY

SECS PYRO ARM (2) - ARM

40K(90K + 63s)

CM UNSTABLE RCS CMD - OFF ~ 40K APEX COVER JETT PG-PUSH DROGUE DEPLOY PG - PUSH (2 secafter apex cover Jett)

30K ELS LOGIC - ON (up)ELS - AUTO

24K RCS hsable (auto)(90K+92s) RCS CMD - OFF

Apex cover Jett (auto)APEX COVER JETT PB - PUSH

(WAIT 2 SECS)Drogue parachutes deployed (auto)

DROGUE DEPLOY PB - PUSH~

If Drogues FallELS - ~ ~Stablllze CM 5K MAIN DPLY PB - PUSHELS - AUTO

235K Cabln Pressure lncreaslng (Drogues + 50s)If not lncreaSlng by 17K CABIN PRESS REL vlv (RR) - DUMP

-46-

10K Maln parachutes deployedMAIN DEPLOY PB - PUSH (wlthln 1 sec)VHF ANT - RECYVHF AMA - SIMPLEXVHF BCN - ONCABIN PRESS REL v1v (2) - CLOSEDIRECT 02 vlv - OPENCM RCS LOGIC - on (up)CM PRPLNT - DUMP (burn audlb1e)Monltor CM ReS 1amp2 for He press decrease

NO BURN or PRESS DECREASE USE BOTH RHCs DO NOT FIRE PITCH JETS

CM PRPLNT-PURGE (to zero He press)CM RCS He DUMP PB - PUSH RHC (2) - 30 sees NO PITCH k

STRUT LOCKS (2) - UNLOCK

cb FLT amp PL BAT BUS ABampBAT C (3) - closecb FLT amp PLT MNA amp B (2) - opencb ECS RAD HTR OVLD (2) - opencb SPS PampY (4) - open

3K CABIN PRESS REL v1v (RH) - DUMP (after purgecompleted)

FLOOD Lts - POST LDGCM RCS PRPLNT (2) - OFFROT CONTR PWR DIRECT (2) - OFF

800 CAB PRESS RELF vlv - CLOSE (latch off)MN BUS TIE (2) - OFF

AFTER LANDINGcb MAIN REL PYRO (2) - closeMAIN RELEASE - on(up)

Go to POSTLANDING pg _47L-__

I

2

3

-47-

57 POSTLANDING

STABILIZATION VENTILATION COMMUNICATIONS

DIRECT 02 vlv - CLOSE

Stablllzation after landlngELS - AUTO (verlfy)cb MAIN REL PYRO (2) - close (venfy)MAIN RELEASE - on (up) (verlfy)S~CS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb BAT RLY BUS (2) - open

No contact w1th recovery forcesVHF AM AampB - off (ctr) ~

VHF AM Rev ONLY - A cb PL VENT - closecb FLOAT BAG (3) - closecb UPRIGHT SYS COMPRESS (2) - closeIf Stable II

FLOAT BAG(3)-FILL t1ll 2 m1n afterupr1ght then - OFF

VHF AM AlB amp BCN - OFF whlle lnvertedIf Stable I

After 10 M1n Coollng Per1odFLOAT BAG (3) - FILL 7 mln then OFF

Post Stab1lizat1on And Ventllat10nPL BCN LT - BCN LT LOWPL VENT vlv - UNLOCK (Pull)Remove PL VENT Exh CoverPL VENT - HIGH or LOWPL DYE MARKER - ON (swlmmer comm)Release foots traps and_restralntscb MNA BAT BUS A amp BAT C (2) - opencb MNB BAT BUS B amp BAT C (2) - opencb FLT amp PL BAT C - opencb PYRO A SEQ A - opencb PYRO B SEQ B - open

EACH HR - CHECK DC VOLTSgt 275 V If Notmiddot cb FLT amp PL-BAT BUS AampB (2) -open cb FLT amp PL BAT C (1) - open GO TO LOW POWER CHECKLIST

Unstow and lnstall PLV DISTRIB DUCTDeploy grappllng hook and 11ne 1f req

4

-48-

Post Landing Communlcatl0nsVHF ANT-RECY (venfy)VHF BCN - ON (verlfy)

If no contact ~lth recovery forcesperform VHF BEACON Check

MONITOR VHF BEACON transmlSSlonnth VHF AM B Rcvr andor Su)vlval

TransceiverkVHF Beacon not operatlng ~connect Surv~val TranscelVer to antcable behlnd VHF ant access pnland place radio ln BCN mode

LOW POHER CHECKLISTVHF BCN - OFFVHF AM (3) - RCVFLOOD Lts - OFFVHF AM AampB - off (ctr)VHF AM RCV ONLY - A (venfy)COUCH LIGHTS - OFFPOSTLANDING VENT SYS mlnlmlze useSURV RADIO - plug mto VHF BCN ANT cableconn behind VHF ant acess pnl amp turn radloon l-n BCN mode

EGRESS PROCEDURES

CMPCDRLMPCDR

CMPCDRCMP

LMPLl1PCDR

STABLE IDlsconnect Umblll-calsNeck darn onCenter couch - 270 0 positionArmrests stowedConnect raft to SIC l-f desl-red wlth

green lanyardConnect raft ~hl-te lanyards to SUltS amp

lnflate water wlngs when eXltl-ngHATCH PISTON PRESS vlv - PRESS (Outbd)Slde Hatch openedPL VENT - OFFcb Pnl 250 (all) - openEgress with 11feraftPut hardware klt outEgress

or CDIPALL

CMF

CDRCMF

CDR

LMF

CMFCMP LMFCMP

UlP

CDR

-49-

STABLE IIcb CREW STA AUDIO (3) - openD~sconnect umb~1~ca1s

Release foots trapsRelease restra~nt harnessCouch seat pans (3) - 170 0 pos1t10nArm rests stowedSurv1va1 k~ts removed from stowageConnect life raft ma~n1~ne to CDR or SicConnect f~rst wh~te lanyard from

11fe raft to suitConnect th~rd wh~te lanyard from

l~fe raft to SU1tConnect rucksacks together to yellow

lanyard on raft bagPRESSURE EQUALIZATION vlv - OPENRemove and stow fwd hatchEX1t feet f1rst w1th rucksacks when clear

of siC 1nflate water w1ngs and raftExit feet f1rst when clear of SiC

1nflate water w1ngsEX1t feet f1rst when clear of sic

1nflate water w1ngs

-50-

60 TLI ABORTS

TLI Aborts are conta~ned ~n the ESD s~nce the bulk of the funct~ons

concern entry preparat20ns and performance Th~s allows a s2nglesource of procedures for procedure rev2ew val~dat~on checkout andtra~n~ng These procedures ~ncorporate TLI preparat20ns as found ~n

reference 6 w~th the TLI Abort Procedures and these t~e 2nto normallunar return Entry Procedures found ~n sect20n 5 The guidel~nes

for th~s cont2ngency are spec2f2ed 2n reference 7

In2t2al preparat~ons for TLI pos2t20n the necessary system sW2tches2n add~t~on to perform~ng an EMS ~V test and a GDC al~gnment Afterthe DET ~s set for mon2tor2ng TB6 the CMP ~ncreases the 12ght levelof the LEB DSKY to max~mum and returns to the h2s couch Th2s 2Sdone so that the LEB DSKY can be observed ~n the event sunl~ght orreflect20ns wash out the ma2n d2splay panel DSKY dur2ng cr2t2calmaneuvers The crew then straps ~n and prepares for mon2tor~ng TB6as 2nd2cated by the SII SEP L~te The t2mes se~uence of procedures2S keyed on th~s d~splay and ~ncludes the DET START funct~on andSIVB IGNITION Dur2ng the burn the crew mon2tors the FDAIs foratt~tude excurs20ns and abnormal rates report~ng status checks toM~ss2on Control at d2screet t~mes dur2ng the maneuver Upon SIVBSHUTDOWN the eMP records the DSKY d~splayed performance parametersand awa2ts ground conf2rmat~on

The rat~onal for TLI aborts ~s descr~bed 2n reference 7 A summar2shyzat20n 2S extracted to prov2de background and gu2de12nes 2n th2sdocument The abort procedures cover aborts 10 m2nutes after conshyt2ngent SIVE shutdown and aborts 90 m2nutes after normal SIVE shutshydown t2me

The 10 m~nute TLI abort ~s des2gned to be used dur~ng TLI ~n theevent a spacecraft problem develops Wh2Ch can result 2n catastrophe2f ~mmed~ate act~on 2S not taken If the s~tuat20n perm~ts the crewshould always allow the SIVB to complete TLI at wh~ch t~me the groundand crew can perform a malfunct~on analys~s to determ~ne ~f an abort~s adv~sable If a fa~lure occurs that necess2tates the shutdown ofthe SIVB and the ~u~ck return of the crew to earth th~s abort ~s

des~gned to be as ~nsens~t~ve to execut~on errors as poss~ble andst21l be targeted to m2dcorr2dor The burn att~tude w~th the f~ed

hor~zon reference ~s a constant value for any shutdown t~me Theburn durat~on 2S a funct20n of shutdown t2me and 2S ava21able fromcrew charts S~nce the pr~mary purpose of th~s abort ~s to returnto earth as qU2ckly as poss2ble there are no restr2ct20ns as toland~ng locat~on However ~f the t~me to EI is greater than abouttwo hours a midcourse correct20n should be ant~c~pated

The 90 m2nute TLI abort 2S to be used 2f a cr2t2cal subsystem malshyfunct~on ~s determ2ned and the dec2s~on to abort ~s made after the

-51-

TLI cutoff and before TLI cutoff plus approxlmately 80 m1nutesTh1S allows suff1c1ent separatlon and procedural t1me to set upfor the SPS deorb1t burn performed at about TLI + 90 Note thatgenerally the deorb1t burns w1ll be performed a fe11 m1nutes beforeTLI + 90 accord1ng to crew charts shown In reference 8 The no-comm except10n requ1res that 90 m1nutes be the 1nput t1me of 19n1shytlon for P-37 (onboard return-to-earth abort program) so that onshyboard calculatlons can correspond w1th ground calculat10ns to computethe CM land1ng p01nt Th1S TLI abort lS des1gned so that returnfl1ght t1me does not exceed 18 hours and abort ~V does not exceed7000 fps ThlS abort can be performed uSlng chart ~Vs and attltudesand the earths hor1zon serves as a suff1c1ent reference The maneushyver lS targeted to ach1eve the mldcorr1dor entry target Ilne andtlmed to result 1n a deslgnated recovery area

It 1S ObV10US for abort deC1S1ons early 1n the TLI + 90 m1nute t1meshyframe that a GampN SPS burn should be performed In order to keep theTLI abort procedures cons1stent and w1th emphasls on slmpl1c1ty theprocedures here reflect a SCS SPS abort burn to cover the full abortdec1s1on t1meframe

A m1dcourse correct1on for corr1dor control after a TLI abort may bedeS1red 1f the SPS burn d1d not meet expectat1ons The TLIabortprocedures 1n th1S sect10n adapt to the normal lunar return tlmel1neand procedures pr10r to the f1nal MCC

-52-

61 TLI PREPARATION PROCEDURES

GET = 150

CRO AOS(___)

CRO LOS( )(22142)

5100

Don Helmets amp Gloves

XLUNAR - INJECT (verify)EDS PWR - on (venfy)EMS FUNC - OFF (verlfy)EMS MODE - STBYEMS FUNC - IW SETVHF RNGEMS MODE - NORMALSet ~V indo to +15868 fpsEMS FUMC - ~V Test

SPS THRUST Lt - onoff (10 sec)~V lnd stops at -01 to -415

EMS MODE - STBYEMS FUMC - ~V SETVHF RNGSet ~VC

EMS FUNC---~~V=----

GDC ALIGNFDAI Select - liZcb SECS LOGIC (Z) - close (verify)cb SECS ARM (Z) - closeSECS LOGIC (Z) - on (up)MSFN Conflrm GO for PYRO ARM (If pass)SECS PYRO ARM (Z) - on (up)TRANS CONTROL PWR - ONROT CONTR PWR NORMAL (Z) - ACDC(verlfy)ROT CONTR PWR DIRECT (Z) - MNAMNBLV INnGPI - SIISIVB (venfy)LV GUID - IU (venfy)cb DIRECT ULLAGE (Z) - closedSet EVENT TIMER to 5100Begin MONITOR For TB6

CMP to Couch

TB 6 - SII SEP Lt on (TIG-9 mln 38 sec)KEY V83E

SET ORDEALFDAI Z ORB RATE at 180 0 0SII SEP Lt out (38 sec later)Start DET COUNTING UPSC CaNT - SCS (verify)MONITOR LV TANK PRESS

~P lt 36 psid (OXID gt FUEL)~P lt Z6 psid (FUEL gt OXID)

EMERGENCY CSMLV SEP UP TLM CM - BLOCK (verify)UP TLM IU - BLOCK (venfy)

-53-

+45degPY))0middot sec PY

lOK nmltHAlt25K nm

Two phas~ng mnvrs two SPS mnvrs to circular~ze at 150 nmearth orb~t

CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ssion 4K nmltHAltlOK nm CSM amp1M - Two phasing mnvrs two SPS mnvrs to circularize at 150 nm earth orb~t CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ss~on

CSM amp 1M - Two phas~ng mnvrs APS burn todepletion th~rd phasing mnvrSPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn tosem~sync orb~t

25K nmltHAlt40K nm CSM amp 1M - Two phasmg mnvrs APS burn to depletion third phas~ng mnvr SPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn to sem~sync orbit HA)40K nm DPS ava~l - DPS LOll circularize with SPS

DPS not ava~l - Lunar flyby or CSM only to lunar orbit (if reqd gtV lt4000 fps)

V37E 47E (check b~as) Record -=--rshy(Limit 98 fpsmm)

( 1fps)tVXYZN62EVIHDOTHPAD (fpsfpslnm)MONITOR VI ( ) at ECO

SCS TVC SERVO PWR 1 - ACIMNA2 - OFF

TAPE RCDR - CMD RESETHBREMS MODE - NORMAL

SIr SEP Lt - ONTLI Inhib~t S~gnals w~11 not be honored after 5942

SIVB ULLAGE BeginsSII SEP Lt - off (TIG - 18 sec)SIVB FUEL LEADSIVB ULLAGE d~scont~nues

LV ENG I Lt - onSIVB IGNITION ( GETI)LV ENG I Lt - off - -shyMONITOR THRUST amp ATTITUDEMONITOR LV TANK PRESSSIVE ECO (Lt on) (BEGIN TB7)

EMER SIVE CUTOFF AT 6 SEC PAST BURN TIME IF VI ATTAINEDTHC CCW ampNEUTRAL IN 1 SEC or SIISIVB sW - LV STAGEPremature Shutdown HAlt4K nm CSM amp 1M -

5700

58205836

F 16 835800

F 16 62

5838594259525955595900000002SUNRISE(___)

HAW AOS(__=_) KEY VERB (freeze d~splay)

SIVB ATT HOLD 20 sec amp BEGIN VENTINGSIVB NNVR TO ORB RT (HDS DN) (3middot sec)

Record VI -c---HDOT _

HPAD _

KEY RLSEF 16 62

F 16 83

HAW LOS(__=-)

KEYmiddotRLSE~VXYZ (lfps)

Record ~VX---_

~vy

WZ--

AVC---_

TAPE RCDR - off (ctr)EMS MODE - STBYEMS FUNC - OFFSECS PYRO ARM (2) - SAFE

PRO

BURN STATUS REPORT

____--~TIG

BT------VGX____-R

-----P----_Y

REMARKS

_____VI

______--HDOT______--H______---AVC______---FUEL_______OXID

_______UNBAL

F 3708=00 OOEGOS AOS CMP TO LEB

(-=-=-)

0000

0003

0005

0014

0100

-55-

62 TLI 10 MIN ABORTSECS LOGIC (2) - on (up)SECS PYRO ARM (2) - ARM

TRANS CONTR - CGH (4 sec) amp +XDET RESET (verlfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS GMD-ON

TRANS GONTR - neutral then +X for10 sec

SIVBGPI s~ - GPIExcesslve rates 6V THRUST A - NORMAL SPS THRUST - DIRECT When rates damped 6V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

TRANS CONTR +X - OFFV37E OOE

PITGH UP to LOGAL VERT (+X axlSto~ard the earth)

RATE - LOWBMAG MODE (3) - ATTIRATE 2EDS PHR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SEGS ARM (2) - opencb EDS (3) - open

TRANS CONTR -X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (180deg)P (199deg)Y (0deg)

RETRO UPDATEGETI _

JV _VG

Jtb ---GET 400K _

05G _GET DROGUE _

ENTRY P _R _

Y_--

0945

-56-

ALIGN HORIZ ON RET +1 MKGMBL CHECK (T11lle Pentattlng)MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conflnn)cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FUMC - JV SETVHF RNGSET JV from chartE~S FUMC - JVEMS fODE - NOIDlAL

lV THRUST A - NORMALV37E 47E (THRUST fONITOR)

F 16 83 lVXYZ (1 fps)

0950

1000

NOTE For aborts durlng 1st mln of TLIKEY V82E F 16 44 (HaHpTff)Burn untll Hp lt 19NM

TRANS CONTR +X

THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN JV reqdJV THRUST (2) - OFFReport cutoff

cb SPS P2 Y2- closeGfBL MTRS (4) - OFF (LMP Confinn)TRANS CONT PWR - OFFTVC SERVO PWR (2) - OFFMN BUS TIE (2) - OFFcb SPS P1amp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREIf est time to EIltOl5500 omlt fCC andenter the SUPERCIRC CKLIST as early as pos-slb1e Pg ~2~3~ __If est time to EI)Ol5500 anticlpate afCC Enter the ENTRY PREP CKLIST at step 9pg 18

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

-2tl C

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-i- rtREQUIRED PITCH GIMBAL ANG LETO OBTAIN HOR-IZON AT 317

DEGREES IN wiiiiDOW

260

z~I- ~ i5 24000

1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

-I

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NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

I LU HD~-

LUHD

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80 HOLD PRESENT TRIMgt LU HD013

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TOP OF WINDOWa 40to

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80 TTOM OF WINDOWi= 0

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HOLO PRESENT TRIlJCl

LOHU0 lt0

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LDHUlt0 FIELD OF VI S10 NLDHU LIFT-DOWNHEADS -UPLUHD LIFT-UP HEADS-DOWN

~~H~-160 q - P63 LIMITI- NOrE-VALIO ONLY FO~t~--

LUNAR RETURN VELOCITY

plusmnl8020 244middot 8 12 16

TIME TO 400K FT ALTITUDE-MIN

4

P37

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320

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-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 48: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

-45-

56 EARTHLANDING

90K STEAM PRESS - PEGGED50K CABIN PRESS REL vIv (2) - BOOSTENTRY

SECS PYRO ARM (2) - ARM

40K(90K + 63s)

CM UNSTABLE RCS CMD - OFF ~ 40K APEX COVER JETT PG-PUSH DROGUE DEPLOY PG - PUSH (2 secafter apex cover Jett)

30K ELS LOGIC - ON (up)ELS - AUTO

24K RCS hsable (auto)(90K+92s) RCS CMD - OFF

Apex cover Jett (auto)APEX COVER JETT PB - PUSH

(WAIT 2 SECS)Drogue parachutes deployed (auto)

DROGUE DEPLOY PB - PUSH~

If Drogues FallELS - ~ ~Stablllze CM 5K MAIN DPLY PB - PUSHELS - AUTO

235K Cabln Pressure lncreaslng (Drogues + 50s)If not lncreaSlng by 17K CABIN PRESS REL vlv (RR) - DUMP

-46-

10K Maln parachutes deployedMAIN DEPLOY PB - PUSH (wlthln 1 sec)VHF ANT - RECYVHF AMA - SIMPLEXVHF BCN - ONCABIN PRESS REL v1v (2) - CLOSEDIRECT 02 vlv - OPENCM RCS LOGIC - on (up)CM PRPLNT - DUMP (burn audlb1e)Monltor CM ReS 1amp2 for He press decrease

NO BURN or PRESS DECREASE USE BOTH RHCs DO NOT FIRE PITCH JETS

CM PRPLNT-PURGE (to zero He press)CM RCS He DUMP PB - PUSH RHC (2) - 30 sees NO PITCH k

STRUT LOCKS (2) - UNLOCK

cb FLT amp PL BAT BUS ABampBAT C (3) - closecb FLT amp PLT MNA amp B (2) - opencb ECS RAD HTR OVLD (2) - opencb SPS PampY (4) - open

3K CABIN PRESS REL v1v (RH) - DUMP (after purgecompleted)

FLOOD Lts - POST LDGCM RCS PRPLNT (2) - OFFROT CONTR PWR DIRECT (2) - OFF

800 CAB PRESS RELF vlv - CLOSE (latch off)MN BUS TIE (2) - OFF

AFTER LANDINGcb MAIN REL PYRO (2) - closeMAIN RELEASE - on(up)

Go to POSTLANDING pg _47L-__

I

2

3

-47-

57 POSTLANDING

STABILIZATION VENTILATION COMMUNICATIONS

DIRECT 02 vlv - CLOSE

Stablllzation after landlngELS - AUTO (verlfy)cb MAIN REL PYRO (2) - close (venfy)MAIN RELEASE - on (up) (verlfy)S~CS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb BAT RLY BUS (2) - open

No contact w1th recovery forcesVHF AM AampB - off (ctr) ~

VHF AM Rev ONLY - A cb PL VENT - closecb FLOAT BAG (3) - closecb UPRIGHT SYS COMPRESS (2) - closeIf Stable II

FLOAT BAG(3)-FILL t1ll 2 m1n afterupr1ght then - OFF

VHF AM AlB amp BCN - OFF whlle lnvertedIf Stable I

After 10 M1n Coollng Per1odFLOAT BAG (3) - FILL 7 mln then OFF

Post Stab1lizat1on And Ventllat10nPL BCN LT - BCN LT LOWPL VENT vlv - UNLOCK (Pull)Remove PL VENT Exh CoverPL VENT - HIGH or LOWPL DYE MARKER - ON (swlmmer comm)Release foots traps and_restralntscb MNA BAT BUS A amp BAT C (2) - opencb MNB BAT BUS B amp BAT C (2) - opencb FLT amp PL BAT C - opencb PYRO A SEQ A - opencb PYRO B SEQ B - open

EACH HR - CHECK DC VOLTSgt 275 V If Notmiddot cb FLT amp PL-BAT BUS AampB (2) -open cb FLT amp PL BAT C (1) - open GO TO LOW POWER CHECKLIST

Unstow and lnstall PLV DISTRIB DUCTDeploy grappllng hook and 11ne 1f req

4

-48-

Post Landing Communlcatl0nsVHF ANT-RECY (venfy)VHF BCN - ON (verlfy)

If no contact ~lth recovery forcesperform VHF BEACON Check

MONITOR VHF BEACON transmlSSlonnth VHF AM B Rcvr andor Su)vlval

TransceiverkVHF Beacon not operatlng ~connect Surv~val TranscelVer to antcable behlnd VHF ant access pnland place radio ln BCN mode

LOW POHER CHECKLISTVHF BCN - OFFVHF AM (3) - RCVFLOOD Lts - OFFVHF AM AampB - off (ctr)VHF AM RCV ONLY - A (venfy)COUCH LIGHTS - OFFPOSTLANDING VENT SYS mlnlmlze useSURV RADIO - plug mto VHF BCN ANT cableconn behind VHF ant acess pnl amp turn radloon l-n BCN mode

EGRESS PROCEDURES

CMPCDRLMPCDR

CMPCDRCMP

LMPLl1PCDR

STABLE IDlsconnect Umblll-calsNeck darn onCenter couch - 270 0 positionArmrests stowedConnect raft to SIC l-f desl-red wlth

green lanyardConnect raft ~hl-te lanyards to SUltS amp

lnflate water wlngs when eXltl-ngHATCH PISTON PRESS vlv - PRESS (Outbd)Slde Hatch openedPL VENT - OFFcb Pnl 250 (all) - openEgress with 11feraftPut hardware klt outEgress

or CDIPALL

CMF

CDRCMF

CDR

LMF

CMFCMP LMFCMP

UlP

CDR

-49-

STABLE IIcb CREW STA AUDIO (3) - openD~sconnect umb~1~ca1s

Release foots trapsRelease restra~nt harnessCouch seat pans (3) - 170 0 pos1t10nArm rests stowedSurv1va1 k~ts removed from stowageConnect life raft ma~n1~ne to CDR or SicConnect f~rst wh~te lanyard from

11fe raft to suitConnect th~rd wh~te lanyard from

l~fe raft to SU1tConnect rucksacks together to yellow

lanyard on raft bagPRESSURE EQUALIZATION vlv - OPENRemove and stow fwd hatchEX1t feet f1rst w1th rucksacks when clear

of siC 1nflate water w1ngs and raftExit feet f1rst when clear of SiC

1nflate water w1ngsEX1t feet f1rst when clear of sic

1nflate water w1ngs

-50-

60 TLI ABORTS

TLI Aborts are conta~ned ~n the ESD s~nce the bulk of the funct~ons

concern entry preparat20ns and performance Th~s allows a s2nglesource of procedures for procedure rev2ew val~dat~on checkout andtra~n~ng These procedures ~ncorporate TLI preparat20ns as found ~n

reference 6 w~th the TLI Abort Procedures and these t~e 2nto normallunar return Entry Procedures found ~n sect20n 5 The guidel~nes

for th~s cont2ngency are spec2f2ed 2n reference 7

In2t2al preparat~ons for TLI pos2t20n the necessary system sW2tches2n add~t~on to perform~ng an EMS ~V test and a GDC al~gnment Afterthe DET ~s set for mon2tor2ng TB6 the CMP ~ncreases the 12ght levelof the LEB DSKY to max~mum and returns to the h2s couch Th2s 2Sdone so that the LEB DSKY can be observed ~n the event sunl~ght orreflect20ns wash out the ma2n d2splay panel DSKY dur2ng cr2t2calmaneuvers The crew then straps ~n and prepares for mon2tor~ng TB6as 2nd2cated by the SII SEP L~te The t2mes se~uence of procedures2S keyed on th~s d~splay and ~ncludes the DET START funct~on andSIVB IGNITION Dur2ng the burn the crew mon2tors the FDAIs foratt~tude excurs20ns and abnormal rates report~ng status checks toM~ss2on Control at d2screet t~mes dur2ng the maneuver Upon SIVBSHUTDOWN the eMP records the DSKY d~splayed performance parametersand awa2ts ground conf2rmat~on

The rat~onal for TLI aborts ~s descr~bed 2n reference 7 A summar2shyzat20n 2S extracted to prov2de background and gu2de12nes 2n th2sdocument The abort procedures cover aborts 10 m2nutes after conshyt2ngent SIVE shutdown and aborts 90 m2nutes after normal SIVE shutshydown t2me

The 10 m~nute TLI abort ~s des2gned to be used dur~ng TLI ~n theevent a spacecraft problem develops Wh2Ch can result 2n catastrophe2f ~mmed~ate act~on 2S not taken If the s~tuat20n perm~ts the crewshould always allow the SIVB to complete TLI at wh~ch t~me the groundand crew can perform a malfunct~on analys~s to determ~ne ~f an abort~s adv~sable If a fa~lure occurs that necess2tates the shutdown ofthe SIVB and the ~u~ck return of the crew to earth th~s abort ~s

des~gned to be as ~nsens~t~ve to execut~on errors as poss~ble andst21l be targeted to m2dcorr2dor The burn att~tude w~th the f~ed

hor~zon reference ~s a constant value for any shutdown t~me Theburn durat~on 2S a funct20n of shutdown t2me and 2S ava21able fromcrew charts S~nce the pr~mary purpose of th~s abort ~s to returnto earth as qU2ckly as poss2ble there are no restr2ct20ns as toland~ng locat~on However ~f the t~me to EI is greater than abouttwo hours a midcourse correct20n should be ant~c~pated

The 90 m2nute TLI abort 2S to be used 2f a cr2t2cal subsystem malshyfunct~on ~s determ2ned and the dec2s~on to abort ~s made after the

-51-

TLI cutoff and before TLI cutoff plus approxlmately 80 m1nutesTh1S allows suff1c1ent separatlon and procedural t1me to set upfor the SPS deorb1t burn performed at about TLI + 90 Note thatgenerally the deorb1t burns w1ll be performed a fe11 m1nutes beforeTLI + 90 accord1ng to crew charts shown In reference 8 The no-comm except10n requ1res that 90 m1nutes be the 1nput t1me of 19n1shytlon for P-37 (onboard return-to-earth abort program) so that onshyboard calculatlons can correspond w1th ground calculat10ns to computethe CM land1ng p01nt Th1S TLI abort lS des1gned so that returnfl1ght t1me does not exceed 18 hours and abort ~V does not exceed7000 fps ThlS abort can be performed uSlng chart ~Vs and attltudesand the earths hor1zon serves as a suff1c1ent reference The maneushyver lS targeted to ach1eve the mldcorr1dor entry target Ilne andtlmed to result 1n a deslgnated recovery area

It 1S ObV10US for abort deC1S1ons early 1n the TLI + 90 m1nute t1meshyframe that a GampN SPS burn should be performed In order to keep theTLI abort procedures cons1stent and w1th emphasls on slmpl1c1ty theprocedures here reflect a SCS SPS abort burn to cover the full abortdec1s1on t1meframe

A m1dcourse correct1on for corr1dor control after a TLI abort may bedeS1red 1f the SPS burn d1d not meet expectat1ons The TLIabortprocedures 1n th1S sect10n adapt to the normal lunar return tlmel1neand procedures pr10r to the f1nal MCC

-52-

61 TLI PREPARATION PROCEDURES

GET = 150

CRO AOS(___)

CRO LOS( )(22142)

5100

Don Helmets amp Gloves

XLUNAR - INJECT (verify)EDS PWR - on (venfy)EMS FUNC - OFF (verlfy)EMS MODE - STBYEMS FUNC - IW SETVHF RNGEMS MODE - NORMALSet ~V indo to +15868 fpsEMS FUMC - ~V Test

SPS THRUST Lt - onoff (10 sec)~V lnd stops at -01 to -415

EMS MODE - STBYEMS FUMC - ~V SETVHF RNGSet ~VC

EMS FUNC---~~V=----

GDC ALIGNFDAI Select - liZcb SECS LOGIC (Z) - close (verify)cb SECS ARM (Z) - closeSECS LOGIC (Z) - on (up)MSFN Conflrm GO for PYRO ARM (If pass)SECS PYRO ARM (Z) - on (up)TRANS CONTROL PWR - ONROT CONTR PWR NORMAL (Z) - ACDC(verlfy)ROT CONTR PWR DIRECT (Z) - MNAMNBLV INnGPI - SIISIVB (venfy)LV GUID - IU (venfy)cb DIRECT ULLAGE (Z) - closedSet EVENT TIMER to 5100Begin MONITOR For TB6

CMP to Couch

TB 6 - SII SEP Lt on (TIG-9 mln 38 sec)KEY V83E

SET ORDEALFDAI Z ORB RATE at 180 0 0SII SEP Lt out (38 sec later)Start DET COUNTING UPSC CaNT - SCS (verify)MONITOR LV TANK PRESS

~P lt 36 psid (OXID gt FUEL)~P lt Z6 psid (FUEL gt OXID)

EMERGENCY CSMLV SEP UP TLM CM - BLOCK (verify)UP TLM IU - BLOCK (venfy)

-53-

+45degPY))0middot sec PY

lOK nmltHAlt25K nm

Two phas~ng mnvrs two SPS mnvrs to circular~ze at 150 nmearth orb~t

CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ssion 4K nmltHAltlOK nm CSM amp1M - Two phasing mnvrs two SPS mnvrs to circularize at 150 nm earth orb~t CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ss~on

CSM amp 1M - Two phas~ng mnvrs APS burn todepletion th~rd phasing mnvrSPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn tosem~sync orb~t

25K nmltHAlt40K nm CSM amp 1M - Two phasmg mnvrs APS burn to depletion third phas~ng mnvr SPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn to sem~sync orbit HA)40K nm DPS ava~l - DPS LOll circularize with SPS

DPS not ava~l - Lunar flyby or CSM only to lunar orbit (if reqd gtV lt4000 fps)

V37E 47E (check b~as) Record -=--rshy(Limit 98 fpsmm)

( 1fps)tVXYZN62EVIHDOTHPAD (fpsfpslnm)MONITOR VI ( ) at ECO

SCS TVC SERVO PWR 1 - ACIMNA2 - OFF

TAPE RCDR - CMD RESETHBREMS MODE - NORMAL

SIr SEP Lt - ONTLI Inhib~t S~gnals w~11 not be honored after 5942

SIVB ULLAGE BeginsSII SEP Lt - off (TIG - 18 sec)SIVB FUEL LEADSIVB ULLAGE d~scont~nues

LV ENG I Lt - onSIVB IGNITION ( GETI)LV ENG I Lt - off - -shyMONITOR THRUST amp ATTITUDEMONITOR LV TANK PRESSSIVE ECO (Lt on) (BEGIN TB7)

EMER SIVE CUTOFF AT 6 SEC PAST BURN TIME IF VI ATTAINEDTHC CCW ampNEUTRAL IN 1 SEC or SIISIVB sW - LV STAGEPremature Shutdown HAlt4K nm CSM amp 1M -

5700

58205836

F 16 835800

F 16 62

5838594259525955595900000002SUNRISE(___)

HAW AOS(__=_) KEY VERB (freeze d~splay)

SIVB ATT HOLD 20 sec amp BEGIN VENTINGSIVB NNVR TO ORB RT (HDS DN) (3middot sec)

Record VI -c---HDOT _

HPAD _

KEY RLSEF 16 62

F 16 83

HAW LOS(__=-)

KEYmiddotRLSE~VXYZ (lfps)

Record ~VX---_

~vy

WZ--

AVC---_

TAPE RCDR - off (ctr)EMS MODE - STBYEMS FUNC - OFFSECS PYRO ARM (2) - SAFE

PRO

BURN STATUS REPORT

____--~TIG

BT------VGX____-R

-----P----_Y

REMARKS

_____VI

______--HDOT______--H______---AVC______---FUEL_______OXID

_______UNBAL

F 3708=00 OOEGOS AOS CMP TO LEB

(-=-=-)

0000

0003

0005

0014

0100

-55-

62 TLI 10 MIN ABORTSECS LOGIC (2) - on (up)SECS PYRO ARM (2) - ARM

TRANS CONTR - CGH (4 sec) amp +XDET RESET (verlfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS GMD-ON

TRANS GONTR - neutral then +X for10 sec

SIVBGPI s~ - GPIExcesslve rates 6V THRUST A - NORMAL SPS THRUST - DIRECT When rates damped 6V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

TRANS CONTR +X - OFFV37E OOE

PITGH UP to LOGAL VERT (+X axlSto~ard the earth)

RATE - LOWBMAG MODE (3) - ATTIRATE 2EDS PHR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SEGS ARM (2) - opencb EDS (3) - open

TRANS CONTR -X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (180deg)P (199deg)Y (0deg)

RETRO UPDATEGETI _

JV _VG

Jtb ---GET 400K _

05G _GET DROGUE _

ENTRY P _R _

Y_--

0945

-56-

ALIGN HORIZ ON RET +1 MKGMBL CHECK (T11lle Pentattlng)MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conflnn)cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FUMC - JV SETVHF RNGSET JV from chartE~S FUMC - JVEMS fODE - NOIDlAL

lV THRUST A - NORMALV37E 47E (THRUST fONITOR)

F 16 83 lVXYZ (1 fps)

0950

1000

NOTE For aborts durlng 1st mln of TLIKEY V82E F 16 44 (HaHpTff)Burn untll Hp lt 19NM

TRANS CONTR +X

THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN JV reqdJV THRUST (2) - OFFReport cutoff

cb SPS P2 Y2- closeGfBL MTRS (4) - OFF (LMP Confinn)TRANS CONT PWR - OFFTVC SERVO PWR (2) - OFFMN BUS TIE (2) - OFFcb SPS P1amp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREIf est time to EIltOl5500 omlt fCC andenter the SUPERCIRC CKLIST as early as pos-slb1e Pg ~2~3~ __If est time to EI)Ol5500 anticlpate afCC Enter the ENTRY PREP CKLIST at step 9pg 18

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

-2tl C

l I W gt- ~-4

z laquo I I- 0 -6

l- I J u gt- ~-8

z w w -10

~_ONSANT

9O

VER

SHO

OT

BOU

ND

ARY

LIF

TV

EC

TOR

OR

IEN

TATI

ON

LIN

E

SH

ALL

OW

TAR

GE

TLI

NE

STE

EP

TAR

GE

TLI

NE 12

gU

ND

ERSH

OO

TBO

UN

DAR

Y

RE

EN

TRY

CO

RR

IDO

R

I ~ I

-12 24

26

28

30

32

34

RE

EN

TRY

VE

LOC

ITY

VE

1-F

TS

EC

Ch

art

1

36

3B

6-i

~

5CM

CC

ON

ST

NT

DR

VI z gt

~

I4

0 Cl W

I

gtamp

J+

-I

-

J Cl z

2U

l z 0_bull

bull-1

+-

u ubullbull

~r

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)

2829

JOn

J23

33

43

5IN

ER

TIA

LR

EE

NTR

YV

ELO

CIT

YA

T4

00

00

0fl

VE

I-F

TS

EC

Ch

art

2

J63

73

8X

03

-i- rtREQUIRED PITCH GIMBAL ANG LETO OBTAIN HOR-IZON AT 317

DEGREES IN wiiiiDOW

260

z~I- ~ i5 24000

1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

-I

-1-

NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

I LU HD~-

LUHD

lt0 120UJ0

~

80 HOLD PRESENT TRIMgt LU HD013

~Y~HOIgtlt

TOP OF WINDOWa 40to

31 7 SCRIBEaaI

80 TTOM OF WINDOWi= 0

0--ltoa

-40t-z

~~~Uw w u lt0 -80

HOLO PRESENT TRIlJCl

LOHU0 lt0

J gt -120 HOLD 059 TRIMlt0 z

LDHUlt0 FIELD OF VI S10 NLDHU LIFT-DOWNHEADS -UPLUHD LIFT-UP HEADS-DOWN

~~H~-160 q - P63 LIMITI- NOrE-VALIO ONLY FO~t~--

LUNAR RETURN VELOCITY

plusmnl8020 244middot 8 12 16

TIME TO 400K FT ALTITUDE-MIN

4

P37

LONG

ITUD

ECO

RREC

TION

TOOB

TAIN

1350

NM

ENTR

YRA

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Ugt

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0

0

2I

U~

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cgt

I

gtI- U

gt z 0 J ltJ

1 -0

340

344

348

352

356

364

368

x10

3

CMC

INER

TIAL

VELO

CITY

AT40

0KAL

TITU

DE-

FTS

EC

Ch

art

5

I l I

o

20 100 -40

-10

-50

30

-20

--

+

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A+

lrBB

A

=----

-----

t~I

AB

SA_

-04

0A

AV

Z=

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D_

+

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2030

NOTE

40

NO

MIN

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=22

MIN

30

-40

-50

---------O

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UR

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BU

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------I

~30

-20

-tD

010

20

AA

VX

FTS

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-60

Ch

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6

1000

0 90

00 70

00 60

00 i50

00 iMl

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00 10

00 o

040

120

200

EMS

6V-

FTS

EC

240

320

400

440

520

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-10

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DEC

21

1968

400050

z =gt co23

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2627

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7

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0i

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EMS

V-F

TSE

C90

0080

0070

0060

0050

0040

0030

0020

0010

000

II

II

II

II

S-IV

BBU

RNTI

ME

-M

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Cll-

41)

120

200

241)

320

400

441)

520

TlI

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UTH

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T(5

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8

34l6

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3

-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 49: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

-46-

10K Maln parachutes deployedMAIN DEPLOY PB - PUSH (wlthln 1 sec)VHF ANT - RECYVHF AMA - SIMPLEXVHF BCN - ONCABIN PRESS REL v1v (2) - CLOSEDIRECT 02 vlv - OPENCM RCS LOGIC - on (up)CM PRPLNT - DUMP (burn audlb1e)Monltor CM ReS 1amp2 for He press decrease

NO BURN or PRESS DECREASE USE BOTH RHCs DO NOT FIRE PITCH JETS

CM PRPLNT-PURGE (to zero He press)CM RCS He DUMP PB - PUSH RHC (2) - 30 sees NO PITCH k

STRUT LOCKS (2) - UNLOCK

cb FLT amp PL BAT BUS ABampBAT C (3) - closecb FLT amp PLT MNA amp B (2) - opencb ECS RAD HTR OVLD (2) - opencb SPS PampY (4) - open

3K CABIN PRESS REL v1v (RH) - DUMP (after purgecompleted)

FLOOD Lts - POST LDGCM RCS PRPLNT (2) - OFFROT CONTR PWR DIRECT (2) - OFF

800 CAB PRESS RELF vlv - CLOSE (latch off)MN BUS TIE (2) - OFF

AFTER LANDINGcb MAIN REL PYRO (2) - closeMAIN RELEASE - on(up)

Go to POSTLANDING pg _47L-__

I

2

3

-47-

57 POSTLANDING

STABILIZATION VENTILATION COMMUNICATIONS

DIRECT 02 vlv - CLOSE

Stablllzation after landlngELS - AUTO (verlfy)cb MAIN REL PYRO (2) - close (venfy)MAIN RELEASE - on (up) (verlfy)S~CS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb BAT RLY BUS (2) - open

No contact w1th recovery forcesVHF AM AampB - off (ctr) ~

VHF AM Rev ONLY - A cb PL VENT - closecb FLOAT BAG (3) - closecb UPRIGHT SYS COMPRESS (2) - closeIf Stable II

FLOAT BAG(3)-FILL t1ll 2 m1n afterupr1ght then - OFF

VHF AM AlB amp BCN - OFF whlle lnvertedIf Stable I

After 10 M1n Coollng Per1odFLOAT BAG (3) - FILL 7 mln then OFF

Post Stab1lizat1on And Ventllat10nPL BCN LT - BCN LT LOWPL VENT vlv - UNLOCK (Pull)Remove PL VENT Exh CoverPL VENT - HIGH or LOWPL DYE MARKER - ON (swlmmer comm)Release foots traps and_restralntscb MNA BAT BUS A amp BAT C (2) - opencb MNB BAT BUS B amp BAT C (2) - opencb FLT amp PL BAT C - opencb PYRO A SEQ A - opencb PYRO B SEQ B - open

EACH HR - CHECK DC VOLTSgt 275 V If Notmiddot cb FLT amp PL-BAT BUS AampB (2) -open cb FLT amp PL BAT C (1) - open GO TO LOW POWER CHECKLIST

Unstow and lnstall PLV DISTRIB DUCTDeploy grappllng hook and 11ne 1f req

4

-48-

Post Landing Communlcatl0nsVHF ANT-RECY (venfy)VHF BCN - ON (verlfy)

If no contact ~lth recovery forcesperform VHF BEACON Check

MONITOR VHF BEACON transmlSSlonnth VHF AM B Rcvr andor Su)vlval

TransceiverkVHF Beacon not operatlng ~connect Surv~val TranscelVer to antcable behlnd VHF ant access pnland place radio ln BCN mode

LOW POHER CHECKLISTVHF BCN - OFFVHF AM (3) - RCVFLOOD Lts - OFFVHF AM AampB - off (ctr)VHF AM RCV ONLY - A (venfy)COUCH LIGHTS - OFFPOSTLANDING VENT SYS mlnlmlze useSURV RADIO - plug mto VHF BCN ANT cableconn behind VHF ant acess pnl amp turn radloon l-n BCN mode

EGRESS PROCEDURES

CMPCDRLMPCDR

CMPCDRCMP

LMPLl1PCDR

STABLE IDlsconnect Umblll-calsNeck darn onCenter couch - 270 0 positionArmrests stowedConnect raft to SIC l-f desl-red wlth

green lanyardConnect raft ~hl-te lanyards to SUltS amp

lnflate water wlngs when eXltl-ngHATCH PISTON PRESS vlv - PRESS (Outbd)Slde Hatch openedPL VENT - OFFcb Pnl 250 (all) - openEgress with 11feraftPut hardware klt outEgress

or CDIPALL

CMF

CDRCMF

CDR

LMF

CMFCMP LMFCMP

UlP

CDR

-49-

STABLE IIcb CREW STA AUDIO (3) - openD~sconnect umb~1~ca1s

Release foots trapsRelease restra~nt harnessCouch seat pans (3) - 170 0 pos1t10nArm rests stowedSurv1va1 k~ts removed from stowageConnect life raft ma~n1~ne to CDR or SicConnect f~rst wh~te lanyard from

11fe raft to suitConnect th~rd wh~te lanyard from

l~fe raft to SU1tConnect rucksacks together to yellow

lanyard on raft bagPRESSURE EQUALIZATION vlv - OPENRemove and stow fwd hatchEX1t feet f1rst w1th rucksacks when clear

of siC 1nflate water w1ngs and raftExit feet f1rst when clear of SiC

1nflate water w1ngsEX1t feet f1rst when clear of sic

1nflate water w1ngs

-50-

60 TLI ABORTS

TLI Aborts are conta~ned ~n the ESD s~nce the bulk of the funct~ons

concern entry preparat20ns and performance Th~s allows a s2nglesource of procedures for procedure rev2ew val~dat~on checkout andtra~n~ng These procedures ~ncorporate TLI preparat20ns as found ~n

reference 6 w~th the TLI Abort Procedures and these t~e 2nto normallunar return Entry Procedures found ~n sect20n 5 The guidel~nes

for th~s cont2ngency are spec2f2ed 2n reference 7

In2t2al preparat~ons for TLI pos2t20n the necessary system sW2tches2n add~t~on to perform~ng an EMS ~V test and a GDC al~gnment Afterthe DET ~s set for mon2tor2ng TB6 the CMP ~ncreases the 12ght levelof the LEB DSKY to max~mum and returns to the h2s couch Th2s 2Sdone so that the LEB DSKY can be observed ~n the event sunl~ght orreflect20ns wash out the ma2n d2splay panel DSKY dur2ng cr2t2calmaneuvers The crew then straps ~n and prepares for mon2tor~ng TB6as 2nd2cated by the SII SEP L~te The t2mes se~uence of procedures2S keyed on th~s d~splay and ~ncludes the DET START funct~on andSIVB IGNITION Dur2ng the burn the crew mon2tors the FDAIs foratt~tude excurs20ns and abnormal rates report~ng status checks toM~ss2on Control at d2screet t~mes dur2ng the maneuver Upon SIVBSHUTDOWN the eMP records the DSKY d~splayed performance parametersand awa2ts ground conf2rmat~on

The rat~onal for TLI aborts ~s descr~bed 2n reference 7 A summar2shyzat20n 2S extracted to prov2de background and gu2de12nes 2n th2sdocument The abort procedures cover aborts 10 m2nutes after conshyt2ngent SIVE shutdown and aborts 90 m2nutes after normal SIVE shutshydown t2me

The 10 m~nute TLI abort ~s des2gned to be used dur~ng TLI ~n theevent a spacecraft problem develops Wh2Ch can result 2n catastrophe2f ~mmed~ate act~on 2S not taken If the s~tuat20n perm~ts the crewshould always allow the SIVB to complete TLI at wh~ch t~me the groundand crew can perform a malfunct~on analys~s to determ~ne ~f an abort~s adv~sable If a fa~lure occurs that necess2tates the shutdown ofthe SIVB and the ~u~ck return of the crew to earth th~s abort ~s

des~gned to be as ~nsens~t~ve to execut~on errors as poss~ble andst21l be targeted to m2dcorr2dor The burn att~tude w~th the f~ed

hor~zon reference ~s a constant value for any shutdown t~me Theburn durat~on 2S a funct20n of shutdown t2me and 2S ava21able fromcrew charts S~nce the pr~mary purpose of th~s abort ~s to returnto earth as qU2ckly as poss2ble there are no restr2ct20ns as toland~ng locat~on However ~f the t~me to EI is greater than abouttwo hours a midcourse correct20n should be ant~c~pated

The 90 m2nute TLI abort 2S to be used 2f a cr2t2cal subsystem malshyfunct~on ~s determ2ned and the dec2s~on to abort ~s made after the

-51-

TLI cutoff and before TLI cutoff plus approxlmately 80 m1nutesTh1S allows suff1c1ent separatlon and procedural t1me to set upfor the SPS deorb1t burn performed at about TLI + 90 Note thatgenerally the deorb1t burns w1ll be performed a fe11 m1nutes beforeTLI + 90 accord1ng to crew charts shown In reference 8 The no-comm except10n requ1res that 90 m1nutes be the 1nput t1me of 19n1shytlon for P-37 (onboard return-to-earth abort program) so that onshyboard calculatlons can correspond w1th ground calculat10ns to computethe CM land1ng p01nt Th1S TLI abort lS des1gned so that returnfl1ght t1me does not exceed 18 hours and abort ~V does not exceed7000 fps ThlS abort can be performed uSlng chart ~Vs and attltudesand the earths hor1zon serves as a suff1c1ent reference The maneushyver lS targeted to ach1eve the mldcorr1dor entry target Ilne andtlmed to result 1n a deslgnated recovery area

It 1S ObV10US for abort deC1S1ons early 1n the TLI + 90 m1nute t1meshyframe that a GampN SPS burn should be performed In order to keep theTLI abort procedures cons1stent and w1th emphasls on slmpl1c1ty theprocedures here reflect a SCS SPS abort burn to cover the full abortdec1s1on t1meframe

A m1dcourse correct1on for corr1dor control after a TLI abort may bedeS1red 1f the SPS burn d1d not meet expectat1ons The TLIabortprocedures 1n th1S sect10n adapt to the normal lunar return tlmel1neand procedures pr10r to the f1nal MCC

-52-

61 TLI PREPARATION PROCEDURES

GET = 150

CRO AOS(___)

CRO LOS( )(22142)

5100

Don Helmets amp Gloves

XLUNAR - INJECT (verify)EDS PWR - on (venfy)EMS FUNC - OFF (verlfy)EMS MODE - STBYEMS FUNC - IW SETVHF RNGEMS MODE - NORMALSet ~V indo to +15868 fpsEMS FUMC - ~V Test

SPS THRUST Lt - onoff (10 sec)~V lnd stops at -01 to -415

EMS MODE - STBYEMS FUMC - ~V SETVHF RNGSet ~VC

EMS FUNC---~~V=----

GDC ALIGNFDAI Select - liZcb SECS LOGIC (Z) - close (verify)cb SECS ARM (Z) - closeSECS LOGIC (Z) - on (up)MSFN Conflrm GO for PYRO ARM (If pass)SECS PYRO ARM (Z) - on (up)TRANS CONTROL PWR - ONROT CONTR PWR NORMAL (Z) - ACDC(verlfy)ROT CONTR PWR DIRECT (Z) - MNAMNBLV INnGPI - SIISIVB (venfy)LV GUID - IU (venfy)cb DIRECT ULLAGE (Z) - closedSet EVENT TIMER to 5100Begin MONITOR For TB6

CMP to Couch

TB 6 - SII SEP Lt on (TIG-9 mln 38 sec)KEY V83E

SET ORDEALFDAI Z ORB RATE at 180 0 0SII SEP Lt out (38 sec later)Start DET COUNTING UPSC CaNT - SCS (verify)MONITOR LV TANK PRESS

~P lt 36 psid (OXID gt FUEL)~P lt Z6 psid (FUEL gt OXID)

EMERGENCY CSMLV SEP UP TLM CM - BLOCK (verify)UP TLM IU - BLOCK (venfy)

-53-

+45degPY))0middot sec PY

lOK nmltHAlt25K nm

Two phas~ng mnvrs two SPS mnvrs to circular~ze at 150 nmearth orb~t

CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ssion 4K nmltHAltlOK nm CSM amp1M - Two phasing mnvrs two SPS mnvrs to circularize at 150 nm earth orb~t CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ss~on

CSM amp 1M - Two phas~ng mnvrs APS burn todepletion th~rd phasing mnvrSPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn tosem~sync orb~t

25K nmltHAlt40K nm CSM amp 1M - Two phasmg mnvrs APS burn to depletion third phas~ng mnvr SPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn to sem~sync orbit HA)40K nm DPS ava~l - DPS LOll circularize with SPS

DPS not ava~l - Lunar flyby or CSM only to lunar orbit (if reqd gtV lt4000 fps)

V37E 47E (check b~as) Record -=--rshy(Limit 98 fpsmm)

( 1fps)tVXYZN62EVIHDOTHPAD (fpsfpslnm)MONITOR VI ( ) at ECO

SCS TVC SERVO PWR 1 - ACIMNA2 - OFF

TAPE RCDR - CMD RESETHBREMS MODE - NORMAL

SIr SEP Lt - ONTLI Inhib~t S~gnals w~11 not be honored after 5942

SIVB ULLAGE BeginsSII SEP Lt - off (TIG - 18 sec)SIVB FUEL LEADSIVB ULLAGE d~scont~nues

LV ENG I Lt - onSIVB IGNITION ( GETI)LV ENG I Lt - off - -shyMONITOR THRUST amp ATTITUDEMONITOR LV TANK PRESSSIVE ECO (Lt on) (BEGIN TB7)

EMER SIVE CUTOFF AT 6 SEC PAST BURN TIME IF VI ATTAINEDTHC CCW ampNEUTRAL IN 1 SEC or SIISIVB sW - LV STAGEPremature Shutdown HAlt4K nm CSM amp 1M -

5700

58205836

F 16 835800

F 16 62

5838594259525955595900000002SUNRISE(___)

HAW AOS(__=_) KEY VERB (freeze d~splay)

SIVB ATT HOLD 20 sec amp BEGIN VENTINGSIVB NNVR TO ORB RT (HDS DN) (3middot sec)

Record VI -c---HDOT _

HPAD _

KEY RLSEF 16 62

F 16 83

HAW LOS(__=-)

KEYmiddotRLSE~VXYZ (lfps)

Record ~VX---_

~vy

WZ--

AVC---_

TAPE RCDR - off (ctr)EMS MODE - STBYEMS FUNC - OFFSECS PYRO ARM (2) - SAFE

PRO

BURN STATUS REPORT

____--~TIG

BT------VGX____-R

-----P----_Y

REMARKS

_____VI

______--HDOT______--H______---AVC______---FUEL_______OXID

_______UNBAL

F 3708=00 OOEGOS AOS CMP TO LEB

(-=-=-)

0000

0003

0005

0014

0100

-55-

62 TLI 10 MIN ABORTSECS LOGIC (2) - on (up)SECS PYRO ARM (2) - ARM

TRANS CONTR - CGH (4 sec) amp +XDET RESET (verlfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS GMD-ON

TRANS GONTR - neutral then +X for10 sec

SIVBGPI s~ - GPIExcesslve rates 6V THRUST A - NORMAL SPS THRUST - DIRECT When rates damped 6V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

TRANS CONTR +X - OFFV37E OOE

PITGH UP to LOGAL VERT (+X axlSto~ard the earth)

RATE - LOWBMAG MODE (3) - ATTIRATE 2EDS PHR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SEGS ARM (2) - opencb EDS (3) - open

TRANS CONTR -X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (180deg)P (199deg)Y (0deg)

RETRO UPDATEGETI _

JV _VG

Jtb ---GET 400K _

05G _GET DROGUE _

ENTRY P _R _

Y_--

0945

-56-

ALIGN HORIZ ON RET +1 MKGMBL CHECK (T11lle Pentattlng)MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conflnn)cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FUMC - JV SETVHF RNGSET JV from chartE~S FUMC - JVEMS fODE - NOIDlAL

lV THRUST A - NORMALV37E 47E (THRUST fONITOR)

F 16 83 lVXYZ (1 fps)

0950

1000

NOTE For aborts durlng 1st mln of TLIKEY V82E F 16 44 (HaHpTff)Burn untll Hp lt 19NM

TRANS CONTR +X

THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN JV reqdJV THRUST (2) - OFFReport cutoff

cb SPS P2 Y2- closeGfBL MTRS (4) - OFF (LMP Confinn)TRANS CONT PWR - OFFTVC SERVO PWR (2) - OFFMN BUS TIE (2) - OFFcb SPS P1amp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREIf est time to EIltOl5500 omlt fCC andenter the SUPERCIRC CKLIST as early as pos-slb1e Pg ~2~3~ __If est time to EI)Ol5500 anticlpate afCC Enter the ENTRY PREP CKLIST at step 9pg 18

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

-2tl C

l I W gt- ~-4

z laquo I I- 0 -6

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OW

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TLI

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STE

EP

TAR

GE

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OO

TBO

UN

DAR

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RE

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26

28

30

32

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-i- rtREQUIRED PITCH GIMBAL ANG LETO OBTAIN HOR-IZON AT 317

DEGREES IN wiiiiDOW

260

z~I- ~ i5 24000

1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

-I

-1-

NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

I LU HD~-

LUHD

lt0 120UJ0

~

80 HOLD PRESENT TRIMgt LU HD013

~Y~HOIgtlt

TOP OF WINDOWa 40to

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80 TTOM OF WINDOWi= 0

0--ltoa

-40t-z

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HOLO PRESENT TRIlJCl

LOHU0 lt0

J gt -120 HOLD 059 TRIMlt0 z

LDHUlt0 FIELD OF VI S10 NLDHU LIFT-DOWNHEADS -UPLUHD LIFT-UP HEADS-DOWN

~~H~-160 q - P63 LIMITI- NOrE-VALIO ONLY FO~t~--

LUNAR RETURN VELOCITY

plusmnl8020 244middot 8 12 16

TIME TO 400K FT ALTITUDE-MIN

4

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320

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400050

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120

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320

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520

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-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 50: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

I

2

3

-47-

57 POSTLANDING

STABILIZATION VENTILATION COMMUNICATIONS

DIRECT 02 vlv - CLOSE

Stablllzation after landlngELS - AUTO (verlfy)cb MAIN REL PYRO (2) - close (venfy)MAIN RELEASE - on (up) (verlfy)S~CS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb BAT RLY BUS (2) - open

No contact w1th recovery forcesVHF AM AampB - off (ctr) ~

VHF AM Rev ONLY - A cb PL VENT - closecb FLOAT BAG (3) - closecb UPRIGHT SYS COMPRESS (2) - closeIf Stable II

FLOAT BAG(3)-FILL t1ll 2 m1n afterupr1ght then - OFF

VHF AM AlB amp BCN - OFF whlle lnvertedIf Stable I

After 10 M1n Coollng Per1odFLOAT BAG (3) - FILL 7 mln then OFF

Post Stab1lizat1on And Ventllat10nPL BCN LT - BCN LT LOWPL VENT vlv - UNLOCK (Pull)Remove PL VENT Exh CoverPL VENT - HIGH or LOWPL DYE MARKER - ON (swlmmer comm)Release foots traps and_restralntscb MNA BAT BUS A amp BAT C (2) - opencb MNB BAT BUS B amp BAT C (2) - opencb FLT amp PL BAT C - opencb PYRO A SEQ A - opencb PYRO B SEQ B - open

EACH HR - CHECK DC VOLTSgt 275 V If Notmiddot cb FLT amp PL-BAT BUS AampB (2) -open cb FLT amp PL BAT C (1) - open GO TO LOW POWER CHECKLIST

Unstow and lnstall PLV DISTRIB DUCTDeploy grappllng hook and 11ne 1f req

4

-48-

Post Landing Communlcatl0nsVHF ANT-RECY (venfy)VHF BCN - ON (verlfy)

If no contact ~lth recovery forcesperform VHF BEACON Check

MONITOR VHF BEACON transmlSSlonnth VHF AM B Rcvr andor Su)vlval

TransceiverkVHF Beacon not operatlng ~connect Surv~val TranscelVer to antcable behlnd VHF ant access pnland place radio ln BCN mode

LOW POHER CHECKLISTVHF BCN - OFFVHF AM (3) - RCVFLOOD Lts - OFFVHF AM AampB - off (ctr)VHF AM RCV ONLY - A (venfy)COUCH LIGHTS - OFFPOSTLANDING VENT SYS mlnlmlze useSURV RADIO - plug mto VHF BCN ANT cableconn behind VHF ant acess pnl amp turn radloon l-n BCN mode

EGRESS PROCEDURES

CMPCDRLMPCDR

CMPCDRCMP

LMPLl1PCDR

STABLE IDlsconnect Umblll-calsNeck darn onCenter couch - 270 0 positionArmrests stowedConnect raft to SIC l-f desl-red wlth

green lanyardConnect raft ~hl-te lanyards to SUltS amp

lnflate water wlngs when eXltl-ngHATCH PISTON PRESS vlv - PRESS (Outbd)Slde Hatch openedPL VENT - OFFcb Pnl 250 (all) - openEgress with 11feraftPut hardware klt outEgress

or CDIPALL

CMF

CDRCMF

CDR

LMF

CMFCMP LMFCMP

UlP

CDR

-49-

STABLE IIcb CREW STA AUDIO (3) - openD~sconnect umb~1~ca1s

Release foots trapsRelease restra~nt harnessCouch seat pans (3) - 170 0 pos1t10nArm rests stowedSurv1va1 k~ts removed from stowageConnect life raft ma~n1~ne to CDR or SicConnect f~rst wh~te lanyard from

11fe raft to suitConnect th~rd wh~te lanyard from

l~fe raft to SU1tConnect rucksacks together to yellow

lanyard on raft bagPRESSURE EQUALIZATION vlv - OPENRemove and stow fwd hatchEX1t feet f1rst w1th rucksacks when clear

of siC 1nflate water w1ngs and raftExit feet f1rst when clear of SiC

1nflate water w1ngsEX1t feet f1rst when clear of sic

1nflate water w1ngs

-50-

60 TLI ABORTS

TLI Aborts are conta~ned ~n the ESD s~nce the bulk of the funct~ons

concern entry preparat20ns and performance Th~s allows a s2nglesource of procedures for procedure rev2ew val~dat~on checkout andtra~n~ng These procedures ~ncorporate TLI preparat20ns as found ~n

reference 6 w~th the TLI Abort Procedures and these t~e 2nto normallunar return Entry Procedures found ~n sect20n 5 The guidel~nes

for th~s cont2ngency are spec2f2ed 2n reference 7

In2t2al preparat~ons for TLI pos2t20n the necessary system sW2tches2n add~t~on to perform~ng an EMS ~V test and a GDC al~gnment Afterthe DET ~s set for mon2tor2ng TB6 the CMP ~ncreases the 12ght levelof the LEB DSKY to max~mum and returns to the h2s couch Th2s 2Sdone so that the LEB DSKY can be observed ~n the event sunl~ght orreflect20ns wash out the ma2n d2splay panel DSKY dur2ng cr2t2calmaneuvers The crew then straps ~n and prepares for mon2tor~ng TB6as 2nd2cated by the SII SEP L~te The t2mes se~uence of procedures2S keyed on th~s d~splay and ~ncludes the DET START funct~on andSIVB IGNITION Dur2ng the burn the crew mon2tors the FDAIs foratt~tude excurs20ns and abnormal rates report~ng status checks toM~ss2on Control at d2screet t~mes dur2ng the maneuver Upon SIVBSHUTDOWN the eMP records the DSKY d~splayed performance parametersand awa2ts ground conf2rmat~on

The rat~onal for TLI aborts ~s descr~bed 2n reference 7 A summar2shyzat20n 2S extracted to prov2de background and gu2de12nes 2n th2sdocument The abort procedures cover aborts 10 m2nutes after conshyt2ngent SIVE shutdown and aborts 90 m2nutes after normal SIVE shutshydown t2me

The 10 m~nute TLI abort ~s des2gned to be used dur~ng TLI ~n theevent a spacecraft problem develops Wh2Ch can result 2n catastrophe2f ~mmed~ate act~on 2S not taken If the s~tuat20n perm~ts the crewshould always allow the SIVB to complete TLI at wh~ch t~me the groundand crew can perform a malfunct~on analys~s to determ~ne ~f an abort~s adv~sable If a fa~lure occurs that necess2tates the shutdown ofthe SIVB and the ~u~ck return of the crew to earth th~s abort ~s

des~gned to be as ~nsens~t~ve to execut~on errors as poss~ble andst21l be targeted to m2dcorr2dor The burn att~tude w~th the f~ed

hor~zon reference ~s a constant value for any shutdown t~me Theburn durat~on 2S a funct20n of shutdown t2me and 2S ava21able fromcrew charts S~nce the pr~mary purpose of th~s abort ~s to returnto earth as qU2ckly as poss2ble there are no restr2ct20ns as toland~ng locat~on However ~f the t~me to EI is greater than abouttwo hours a midcourse correct20n should be ant~c~pated

The 90 m2nute TLI abort 2S to be used 2f a cr2t2cal subsystem malshyfunct~on ~s determ2ned and the dec2s~on to abort ~s made after the

-51-

TLI cutoff and before TLI cutoff plus approxlmately 80 m1nutesTh1S allows suff1c1ent separatlon and procedural t1me to set upfor the SPS deorb1t burn performed at about TLI + 90 Note thatgenerally the deorb1t burns w1ll be performed a fe11 m1nutes beforeTLI + 90 accord1ng to crew charts shown In reference 8 The no-comm except10n requ1res that 90 m1nutes be the 1nput t1me of 19n1shytlon for P-37 (onboard return-to-earth abort program) so that onshyboard calculatlons can correspond w1th ground calculat10ns to computethe CM land1ng p01nt Th1S TLI abort lS des1gned so that returnfl1ght t1me does not exceed 18 hours and abort ~V does not exceed7000 fps ThlS abort can be performed uSlng chart ~Vs and attltudesand the earths hor1zon serves as a suff1c1ent reference The maneushyver lS targeted to ach1eve the mldcorr1dor entry target Ilne andtlmed to result 1n a deslgnated recovery area

It 1S ObV10US for abort deC1S1ons early 1n the TLI + 90 m1nute t1meshyframe that a GampN SPS burn should be performed In order to keep theTLI abort procedures cons1stent and w1th emphasls on slmpl1c1ty theprocedures here reflect a SCS SPS abort burn to cover the full abortdec1s1on t1meframe

A m1dcourse correct1on for corr1dor control after a TLI abort may bedeS1red 1f the SPS burn d1d not meet expectat1ons The TLIabortprocedures 1n th1S sect10n adapt to the normal lunar return tlmel1neand procedures pr10r to the f1nal MCC

-52-

61 TLI PREPARATION PROCEDURES

GET = 150

CRO AOS(___)

CRO LOS( )(22142)

5100

Don Helmets amp Gloves

XLUNAR - INJECT (verify)EDS PWR - on (venfy)EMS FUNC - OFF (verlfy)EMS MODE - STBYEMS FUNC - IW SETVHF RNGEMS MODE - NORMALSet ~V indo to +15868 fpsEMS FUMC - ~V Test

SPS THRUST Lt - onoff (10 sec)~V lnd stops at -01 to -415

EMS MODE - STBYEMS FUMC - ~V SETVHF RNGSet ~VC

EMS FUNC---~~V=----

GDC ALIGNFDAI Select - liZcb SECS LOGIC (Z) - close (verify)cb SECS ARM (Z) - closeSECS LOGIC (Z) - on (up)MSFN Conflrm GO for PYRO ARM (If pass)SECS PYRO ARM (Z) - on (up)TRANS CONTROL PWR - ONROT CONTR PWR NORMAL (Z) - ACDC(verlfy)ROT CONTR PWR DIRECT (Z) - MNAMNBLV INnGPI - SIISIVB (venfy)LV GUID - IU (venfy)cb DIRECT ULLAGE (Z) - closedSet EVENT TIMER to 5100Begin MONITOR For TB6

CMP to Couch

TB 6 - SII SEP Lt on (TIG-9 mln 38 sec)KEY V83E

SET ORDEALFDAI Z ORB RATE at 180 0 0SII SEP Lt out (38 sec later)Start DET COUNTING UPSC CaNT - SCS (verify)MONITOR LV TANK PRESS

~P lt 36 psid (OXID gt FUEL)~P lt Z6 psid (FUEL gt OXID)

EMERGENCY CSMLV SEP UP TLM CM - BLOCK (verify)UP TLM IU - BLOCK (venfy)

-53-

+45degPY))0middot sec PY

lOK nmltHAlt25K nm

Two phas~ng mnvrs two SPS mnvrs to circular~ze at 150 nmearth orb~t

CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ssion 4K nmltHAltlOK nm CSM amp1M - Two phasing mnvrs two SPS mnvrs to circularize at 150 nm earth orb~t CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ss~on

CSM amp 1M - Two phas~ng mnvrs APS burn todepletion th~rd phasing mnvrSPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn tosem~sync orb~t

25K nmltHAlt40K nm CSM amp 1M - Two phasmg mnvrs APS burn to depletion third phas~ng mnvr SPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn to sem~sync orbit HA)40K nm DPS ava~l - DPS LOll circularize with SPS

DPS not ava~l - Lunar flyby or CSM only to lunar orbit (if reqd gtV lt4000 fps)

V37E 47E (check b~as) Record -=--rshy(Limit 98 fpsmm)

( 1fps)tVXYZN62EVIHDOTHPAD (fpsfpslnm)MONITOR VI ( ) at ECO

SCS TVC SERVO PWR 1 - ACIMNA2 - OFF

TAPE RCDR - CMD RESETHBREMS MODE - NORMAL

SIr SEP Lt - ONTLI Inhib~t S~gnals w~11 not be honored after 5942

SIVB ULLAGE BeginsSII SEP Lt - off (TIG - 18 sec)SIVB FUEL LEADSIVB ULLAGE d~scont~nues

LV ENG I Lt - onSIVB IGNITION ( GETI)LV ENG I Lt - off - -shyMONITOR THRUST amp ATTITUDEMONITOR LV TANK PRESSSIVE ECO (Lt on) (BEGIN TB7)

EMER SIVE CUTOFF AT 6 SEC PAST BURN TIME IF VI ATTAINEDTHC CCW ampNEUTRAL IN 1 SEC or SIISIVB sW - LV STAGEPremature Shutdown HAlt4K nm CSM amp 1M -

5700

58205836

F 16 835800

F 16 62

5838594259525955595900000002SUNRISE(___)

HAW AOS(__=_) KEY VERB (freeze d~splay)

SIVB ATT HOLD 20 sec amp BEGIN VENTINGSIVB NNVR TO ORB RT (HDS DN) (3middot sec)

Record VI -c---HDOT _

HPAD _

KEY RLSEF 16 62

F 16 83

HAW LOS(__=-)

KEYmiddotRLSE~VXYZ (lfps)

Record ~VX---_

~vy

WZ--

AVC---_

TAPE RCDR - off (ctr)EMS MODE - STBYEMS FUNC - OFFSECS PYRO ARM (2) - SAFE

PRO

BURN STATUS REPORT

____--~TIG

BT------VGX____-R

-----P----_Y

REMARKS

_____VI

______--HDOT______--H______---AVC______---FUEL_______OXID

_______UNBAL

F 3708=00 OOEGOS AOS CMP TO LEB

(-=-=-)

0000

0003

0005

0014

0100

-55-

62 TLI 10 MIN ABORTSECS LOGIC (2) - on (up)SECS PYRO ARM (2) - ARM

TRANS CONTR - CGH (4 sec) amp +XDET RESET (verlfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS GMD-ON

TRANS GONTR - neutral then +X for10 sec

SIVBGPI s~ - GPIExcesslve rates 6V THRUST A - NORMAL SPS THRUST - DIRECT When rates damped 6V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

TRANS CONTR +X - OFFV37E OOE

PITGH UP to LOGAL VERT (+X axlSto~ard the earth)

RATE - LOWBMAG MODE (3) - ATTIRATE 2EDS PHR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SEGS ARM (2) - opencb EDS (3) - open

TRANS CONTR -X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (180deg)P (199deg)Y (0deg)

RETRO UPDATEGETI _

JV _VG

Jtb ---GET 400K _

05G _GET DROGUE _

ENTRY P _R _

Y_--

0945

-56-

ALIGN HORIZ ON RET +1 MKGMBL CHECK (T11lle Pentattlng)MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conflnn)cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FUMC - JV SETVHF RNGSET JV from chartE~S FUMC - JVEMS fODE - NOIDlAL

lV THRUST A - NORMALV37E 47E (THRUST fONITOR)

F 16 83 lVXYZ (1 fps)

0950

1000

NOTE For aborts durlng 1st mln of TLIKEY V82E F 16 44 (HaHpTff)Burn untll Hp lt 19NM

TRANS CONTR +X

THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN JV reqdJV THRUST (2) - OFFReport cutoff

cb SPS P2 Y2- closeGfBL MTRS (4) - OFF (LMP Confinn)TRANS CONT PWR - OFFTVC SERVO PWR (2) - OFFMN BUS TIE (2) - OFFcb SPS P1amp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREIf est time to EIltOl5500 omlt fCC andenter the SUPERCIRC CKLIST as early as pos-slb1e Pg ~2~3~ __If est time to EI)Ol5500 anticlpate afCC Enter the ENTRY PREP CKLIST at step 9pg 18

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

-2tl C

l I W gt- ~-4

z laquo I I- 0 -6

l- I J u gt- ~-8

z w w -10

~_ONSANT

9O

VER

SHO

OT

BOU

ND

ARY

LIF

TV

EC

TOR

OR

IEN

TATI

ON

LIN

E

SH

ALL

OW

TAR

GE

TLI

NE

STE

EP

TAR

GE

TLI

NE 12

gU

ND

ERSH

OO

TBO

UN

DAR

Y

RE

EN

TRY

CO

RR

IDO

R

I ~ I

-12 24

26

28

30

32

34

RE

EN

TRY

VE

LOC

ITY

VE

1-F

TS

EC

Ch

art

1

36

3B

6-i

~

5CM

CC

ON

ST

NT

DR

VI z gt

~

I4

0 Cl W

I

gtamp

J+

-I

-

J Cl z

2U

l z 0_bull

bull-1

+-

u ubullbull

~r

U

)

2829

JOn

J23

33

43

5IN

ER

TIA

LR

EE

NTR

YV

ELO

CIT

YA

T4

00

00

0fl

VE

I-F

TS

EC

Ch

art

2

J63

73

8X

03

-i- rtREQUIRED PITCH GIMBAL ANG LETO OBTAIN HOR-IZON AT 317

DEGREES IN wiiiiDOW

260

z~I- ~ i5 24000

1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

-I

-1-

NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

I LU HD~-

LUHD

lt0 120UJ0

~

80 HOLD PRESENT TRIMgt LU HD013

~Y~HOIgtlt

TOP OF WINDOWa 40to

31 7 SCRIBEaaI

80 TTOM OF WINDOWi= 0

0--ltoa

-40t-z

~~~Uw w u lt0 -80

HOLO PRESENT TRIlJCl

LOHU0 lt0

J gt -120 HOLD 059 TRIMlt0 z

LDHUlt0 FIELD OF VI S10 NLDHU LIFT-DOWNHEADS -UPLUHD LIFT-UP HEADS-DOWN

~~H~-160 q - P63 LIMITI- NOrE-VALIO ONLY FO~t~--

LUNAR RETURN VELOCITY

plusmnl8020 244middot 8 12 16

TIME TO 400K FT ALTITUDE-MIN

4

P37

LONG

ITUD

ECO

RREC

TION

TOOB

TAIN

1350

NM

ENTR

YRA

NGE

Ugt

UJ

cgt

3z 0 I- u U

J0

0

0

2I

U~

UJ

cgt

I

gtI- U

gt z 0 J ltJ

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340

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120

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320

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-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 51: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

4

-48-

Post Landing Communlcatl0nsVHF ANT-RECY (venfy)VHF BCN - ON (verlfy)

If no contact ~lth recovery forcesperform VHF BEACON Check

MONITOR VHF BEACON transmlSSlonnth VHF AM B Rcvr andor Su)vlval

TransceiverkVHF Beacon not operatlng ~connect Surv~val TranscelVer to antcable behlnd VHF ant access pnland place radio ln BCN mode

LOW POHER CHECKLISTVHF BCN - OFFVHF AM (3) - RCVFLOOD Lts - OFFVHF AM AampB - off (ctr)VHF AM RCV ONLY - A (venfy)COUCH LIGHTS - OFFPOSTLANDING VENT SYS mlnlmlze useSURV RADIO - plug mto VHF BCN ANT cableconn behind VHF ant acess pnl amp turn radloon l-n BCN mode

EGRESS PROCEDURES

CMPCDRLMPCDR

CMPCDRCMP

LMPLl1PCDR

STABLE IDlsconnect Umblll-calsNeck darn onCenter couch - 270 0 positionArmrests stowedConnect raft to SIC l-f desl-red wlth

green lanyardConnect raft ~hl-te lanyards to SUltS amp

lnflate water wlngs when eXltl-ngHATCH PISTON PRESS vlv - PRESS (Outbd)Slde Hatch openedPL VENT - OFFcb Pnl 250 (all) - openEgress with 11feraftPut hardware klt outEgress

or CDIPALL

CMF

CDRCMF

CDR

LMF

CMFCMP LMFCMP

UlP

CDR

-49-

STABLE IIcb CREW STA AUDIO (3) - openD~sconnect umb~1~ca1s

Release foots trapsRelease restra~nt harnessCouch seat pans (3) - 170 0 pos1t10nArm rests stowedSurv1va1 k~ts removed from stowageConnect life raft ma~n1~ne to CDR or SicConnect f~rst wh~te lanyard from

11fe raft to suitConnect th~rd wh~te lanyard from

l~fe raft to SU1tConnect rucksacks together to yellow

lanyard on raft bagPRESSURE EQUALIZATION vlv - OPENRemove and stow fwd hatchEX1t feet f1rst w1th rucksacks when clear

of siC 1nflate water w1ngs and raftExit feet f1rst when clear of SiC

1nflate water w1ngsEX1t feet f1rst when clear of sic

1nflate water w1ngs

-50-

60 TLI ABORTS

TLI Aborts are conta~ned ~n the ESD s~nce the bulk of the funct~ons

concern entry preparat20ns and performance Th~s allows a s2nglesource of procedures for procedure rev2ew val~dat~on checkout andtra~n~ng These procedures ~ncorporate TLI preparat20ns as found ~n

reference 6 w~th the TLI Abort Procedures and these t~e 2nto normallunar return Entry Procedures found ~n sect20n 5 The guidel~nes

for th~s cont2ngency are spec2f2ed 2n reference 7

In2t2al preparat~ons for TLI pos2t20n the necessary system sW2tches2n add~t~on to perform~ng an EMS ~V test and a GDC al~gnment Afterthe DET ~s set for mon2tor2ng TB6 the CMP ~ncreases the 12ght levelof the LEB DSKY to max~mum and returns to the h2s couch Th2s 2Sdone so that the LEB DSKY can be observed ~n the event sunl~ght orreflect20ns wash out the ma2n d2splay panel DSKY dur2ng cr2t2calmaneuvers The crew then straps ~n and prepares for mon2tor~ng TB6as 2nd2cated by the SII SEP L~te The t2mes se~uence of procedures2S keyed on th~s d~splay and ~ncludes the DET START funct~on andSIVB IGNITION Dur2ng the burn the crew mon2tors the FDAIs foratt~tude excurs20ns and abnormal rates report~ng status checks toM~ss2on Control at d2screet t~mes dur2ng the maneuver Upon SIVBSHUTDOWN the eMP records the DSKY d~splayed performance parametersand awa2ts ground conf2rmat~on

The rat~onal for TLI aborts ~s descr~bed 2n reference 7 A summar2shyzat20n 2S extracted to prov2de background and gu2de12nes 2n th2sdocument The abort procedures cover aborts 10 m2nutes after conshyt2ngent SIVE shutdown and aborts 90 m2nutes after normal SIVE shutshydown t2me

The 10 m~nute TLI abort ~s des2gned to be used dur~ng TLI ~n theevent a spacecraft problem develops Wh2Ch can result 2n catastrophe2f ~mmed~ate act~on 2S not taken If the s~tuat20n perm~ts the crewshould always allow the SIVB to complete TLI at wh~ch t~me the groundand crew can perform a malfunct~on analys~s to determ~ne ~f an abort~s adv~sable If a fa~lure occurs that necess2tates the shutdown ofthe SIVB and the ~u~ck return of the crew to earth th~s abort ~s

des~gned to be as ~nsens~t~ve to execut~on errors as poss~ble andst21l be targeted to m2dcorr2dor The burn att~tude w~th the f~ed

hor~zon reference ~s a constant value for any shutdown t~me Theburn durat~on 2S a funct20n of shutdown t2me and 2S ava21able fromcrew charts S~nce the pr~mary purpose of th~s abort ~s to returnto earth as qU2ckly as poss2ble there are no restr2ct20ns as toland~ng locat~on However ~f the t~me to EI is greater than abouttwo hours a midcourse correct20n should be ant~c~pated

The 90 m2nute TLI abort 2S to be used 2f a cr2t2cal subsystem malshyfunct~on ~s determ2ned and the dec2s~on to abort ~s made after the

-51-

TLI cutoff and before TLI cutoff plus approxlmately 80 m1nutesTh1S allows suff1c1ent separatlon and procedural t1me to set upfor the SPS deorb1t burn performed at about TLI + 90 Note thatgenerally the deorb1t burns w1ll be performed a fe11 m1nutes beforeTLI + 90 accord1ng to crew charts shown In reference 8 The no-comm except10n requ1res that 90 m1nutes be the 1nput t1me of 19n1shytlon for P-37 (onboard return-to-earth abort program) so that onshyboard calculatlons can correspond w1th ground calculat10ns to computethe CM land1ng p01nt Th1S TLI abort lS des1gned so that returnfl1ght t1me does not exceed 18 hours and abort ~V does not exceed7000 fps ThlS abort can be performed uSlng chart ~Vs and attltudesand the earths hor1zon serves as a suff1c1ent reference The maneushyver lS targeted to ach1eve the mldcorr1dor entry target Ilne andtlmed to result 1n a deslgnated recovery area

It 1S ObV10US for abort deC1S1ons early 1n the TLI + 90 m1nute t1meshyframe that a GampN SPS burn should be performed In order to keep theTLI abort procedures cons1stent and w1th emphasls on slmpl1c1ty theprocedures here reflect a SCS SPS abort burn to cover the full abortdec1s1on t1meframe

A m1dcourse correct1on for corr1dor control after a TLI abort may bedeS1red 1f the SPS burn d1d not meet expectat1ons The TLIabortprocedures 1n th1S sect10n adapt to the normal lunar return tlmel1neand procedures pr10r to the f1nal MCC

-52-

61 TLI PREPARATION PROCEDURES

GET = 150

CRO AOS(___)

CRO LOS( )(22142)

5100

Don Helmets amp Gloves

XLUNAR - INJECT (verify)EDS PWR - on (venfy)EMS FUNC - OFF (verlfy)EMS MODE - STBYEMS FUNC - IW SETVHF RNGEMS MODE - NORMALSet ~V indo to +15868 fpsEMS FUMC - ~V Test

SPS THRUST Lt - onoff (10 sec)~V lnd stops at -01 to -415

EMS MODE - STBYEMS FUMC - ~V SETVHF RNGSet ~VC

EMS FUNC---~~V=----

GDC ALIGNFDAI Select - liZcb SECS LOGIC (Z) - close (verify)cb SECS ARM (Z) - closeSECS LOGIC (Z) - on (up)MSFN Conflrm GO for PYRO ARM (If pass)SECS PYRO ARM (Z) - on (up)TRANS CONTROL PWR - ONROT CONTR PWR NORMAL (Z) - ACDC(verlfy)ROT CONTR PWR DIRECT (Z) - MNAMNBLV INnGPI - SIISIVB (venfy)LV GUID - IU (venfy)cb DIRECT ULLAGE (Z) - closedSet EVENT TIMER to 5100Begin MONITOR For TB6

CMP to Couch

TB 6 - SII SEP Lt on (TIG-9 mln 38 sec)KEY V83E

SET ORDEALFDAI Z ORB RATE at 180 0 0SII SEP Lt out (38 sec later)Start DET COUNTING UPSC CaNT - SCS (verify)MONITOR LV TANK PRESS

~P lt 36 psid (OXID gt FUEL)~P lt Z6 psid (FUEL gt OXID)

EMERGENCY CSMLV SEP UP TLM CM - BLOCK (verify)UP TLM IU - BLOCK (venfy)

-53-

+45degPY))0middot sec PY

lOK nmltHAlt25K nm

Two phas~ng mnvrs two SPS mnvrs to circular~ze at 150 nmearth orb~t

CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ssion 4K nmltHAltlOK nm CSM amp1M - Two phasing mnvrs two SPS mnvrs to circularize at 150 nm earth orb~t CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ss~on

CSM amp 1M - Two phas~ng mnvrs APS burn todepletion th~rd phasing mnvrSPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn tosem~sync orb~t

25K nmltHAlt40K nm CSM amp 1M - Two phasmg mnvrs APS burn to depletion third phas~ng mnvr SPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn to sem~sync orbit HA)40K nm DPS ava~l - DPS LOll circularize with SPS

DPS not ava~l - Lunar flyby or CSM only to lunar orbit (if reqd gtV lt4000 fps)

V37E 47E (check b~as) Record -=--rshy(Limit 98 fpsmm)

( 1fps)tVXYZN62EVIHDOTHPAD (fpsfpslnm)MONITOR VI ( ) at ECO

SCS TVC SERVO PWR 1 - ACIMNA2 - OFF

TAPE RCDR - CMD RESETHBREMS MODE - NORMAL

SIr SEP Lt - ONTLI Inhib~t S~gnals w~11 not be honored after 5942

SIVB ULLAGE BeginsSII SEP Lt - off (TIG - 18 sec)SIVB FUEL LEADSIVB ULLAGE d~scont~nues

LV ENG I Lt - onSIVB IGNITION ( GETI)LV ENG I Lt - off - -shyMONITOR THRUST amp ATTITUDEMONITOR LV TANK PRESSSIVE ECO (Lt on) (BEGIN TB7)

EMER SIVE CUTOFF AT 6 SEC PAST BURN TIME IF VI ATTAINEDTHC CCW ampNEUTRAL IN 1 SEC or SIISIVB sW - LV STAGEPremature Shutdown HAlt4K nm CSM amp 1M -

5700

58205836

F 16 835800

F 16 62

5838594259525955595900000002SUNRISE(___)

HAW AOS(__=_) KEY VERB (freeze d~splay)

SIVB ATT HOLD 20 sec amp BEGIN VENTINGSIVB NNVR TO ORB RT (HDS DN) (3middot sec)

Record VI -c---HDOT _

HPAD _

KEY RLSEF 16 62

F 16 83

HAW LOS(__=-)

KEYmiddotRLSE~VXYZ (lfps)

Record ~VX---_

~vy

WZ--

AVC---_

TAPE RCDR - off (ctr)EMS MODE - STBYEMS FUNC - OFFSECS PYRO ARM (2) - SAFE

PRO

BURN STATUS REPORT

____--~TIG

BT------VGX____-R

-----P----_Y

REMARKS

_____VI

______--HDOT______--H______---AVC______---FUEL_______OXID

_______UNBAL

F 3708=00 OOEGOS AOS CMP TO LEB

(-=-=-)

0000

0003

0005

0014

0100

-55-

62 TLI 10 MIN ABORTSECS LOGIC (2) - on (up)SECS PYRO ARM (2) - ARM

TRANS CONTR - CGH (4 sec) amp +XDET RESET (verlfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS GMD-ON

TRANS GONTR - neutral then +X for10 sec

SIVBGPI s~ - GPIExcesslve rates 6V THRUST A - NORMAL SPS THRUST - DIRECT When rates damped 6V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

TRANS CONTR +X - OFFV37E OOE

PITGH UP to LOGAL VERT (+X axlSto~ard the earth)

RATE - LOWBMAG MODE (3) - ATTIRATE 2EDS PHR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SEGS ARM (2) - opencb EDS (3) - open

TRANS CONTR -X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (180deg)P (199deg)Y (0deg)

RETRO UPDATEGETI _

JV _VG

Jtb ---GET 400K _

05G _GET DROGUE _

ENTRY P _R _

Y_--

0945

-56-

ALIGN HORIZ ON RET +1 MKGMBL CHECK (T11lle Pentattlng)MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conflnn)cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FUMC - JV SETVHF RNGSET JV from chartE~S FUMC - JVEMS fODE - NOIDlAL

lV THRUST A - NORMALV37E 47E (THRUST fONITOR)

F 16 83 lVXYZ (1 fps)

0950

1000

NOTE For aborts durlng 1st mln of TLIKEY V82E F 16 44 (HaHpTff)Burn untll Hp lt 19NM

TRANS CONTR +X

THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN JV reqdJV THRUST (2) - OFFReport cutoff

cb SPS P2 Y2- closeGfBL MTRS (4) - OFF (LMP Confinn)TRANS CONT PWR - OFFTVC SERVO PWR (2) - OFFMN BUS TIE (2) - OFFcb SPS P1amp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREIf est time to EIltOl5500 omlt fCC andenter the SUPERCIRC CKLIST as early as pos-slb1e Pg ~2~3~ __If est time to EI)Ol5500 anticlpate afCC Enter the ENTRY PREP CKLIST at step 9pg 18

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

-2tl C

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DEGREES IN wiiiiDOW

260

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1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

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NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

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TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

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LUNAR RETURN VELOCITY

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-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 52: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

or CDIPALL

CMF

CDRCMF

CDR

LMF

CMFCMP LMFCMP

UlP

CDR

-49-

STABLE IIcb CREW STA AUDIO (3) - openD~sconnect umb~1~ca1s

Release foots trapsRelease restra~nt harnessCouch seat pans (3) - 170 0 pos1t10nArm rests stowedSurv1va1 k~ts removed from stowageConnect life raft ma~n1~ne to CDR or SicConnect f~rst wh~te lanyard from

11fe raft to suitConnect th~rd wh~te lanyard from

l~fe raft to SU1tConnect rucksacks together to yellow

lanyard on raft bagPRESSURE EQUALIZATION vlv - OPENRemove and stow fwd hatchEX1t feet f1rst w1th rucksacks when clear

of siC 1nflate water w1ngs and raftExit feet f1rst when clear of SiC

1nflate water w1ngsEX1t feet f1rst when clear of sic

1nflate water w1ngs

-50-

60 TLI ABORTS

TLI Aborts are conta~ned ~n the ESD s~nce the bulk of the funct~ons

concern entry preparat20ns and performance Th~s allows a s2nglesource of procedures for procedure rev2ew val~dat~on checkout andtra~n~ng These procedures ~ncorporate TLI preparat20ns as found ~n

reference 6 w~th the TLI Abort Procedures and these t~e 2nto normallunar return Entry Procedures found ~n sect20n 5 The guidel~nes

for th~s cont2ngency are spec2f2ed 2n reference 7

In2t2al preparat~ons for TLI pos2t20n the necessary system sW2tches2n add~t~on to perform~ng an EMS ~V test and a GDC al~gnment Afterthe DET ~s set for mon2tor2ng TB6 the CMP ~ncreases the 12ght levelof the LEB DSKY to max~mum and returns to the h2s couch Th2s 2Sdone so that the LEB DSKY can be observed ~n the event sunl~ght orreflect20ns wash out the ma2n d2splay panel DSKY dur2ng cr2t2calmaneuvers The crew then straps ~n and prepares for mon2tor~ng TB6as 2nd2cated by the SII SEP L~te The t2mes se~uence of procedures2S keyed on th~s d~splay and ~ncludes the DET START funct~on andSIVB IGNITION Dur2ng the burn the crew mon2tors the FDAIs foratt~tude excurs20ns and abnormal rates report~ng status checks toM~ss2on Control at d2screet t~mes dur2ng the maneuver Upon SIVBSHUTDOWN the eMP records the DSKY d~splayed performance parametersand awa2ts ground conf2rmat~on

The rat~onal for TLI aborts ~s descr~bed 2n reference 7 A summar2shyzat20n 2S extracted to prov2de background and gu2de12nes 2n th2sdocument The abort procedures cover aborts 10 m2nutes after conshyt2ngent SIVE shutdown and aborts 90 m2nutes after normal SIVE shutshydown t2me

The 10 m~nute TLI abort ~s des2gned to be used dur~ng TLI ~n theevent a spacecraft problem develops Wh2Ch can result 2n catastrophe2f ~mmed~ate act~on 2S not taken If the s~tuat20n perm~ts the crewshould always allow the SIVB to complete TLI at wh~ch t~me the groundand crew can perform a malfunct~on analys~s to determ~ne ~f an abort~s adv~sable If a fa~lure occurs that necess2tates the shutdown ofthe SIVB and the ~u~ck return of the crew to earth th~s abort ~s

des~gned to be as ~nsens~t~ve to execut~on errors as poss~ble andst21l be targeted to m2dcorr2dor The burn att~tude w~th the f~ed

hor~zon reference ~s a constant value for any shutdown t~me Theburn durat~on 2S a funct20n of shutdown t2me and 2S ava21able fromcrew charts S~nce the pr~mary purpose of th~s abort ~s to returnto earth as qU2ckly as poss2ble there are no restr2ct20ns as toland~ng locat~on However ~f the t~me to EI is greater than abouttwo hours a midcourse correct20n should be ant~c~pated

The 90 m2nute TLI abort 2S to be used 2f a cr2t2cal subsystem malshyfunct~on ~s determ2ned and the dec2s~on to abort ~s made after the

-51-

TLI cutoff and before TLI cutoff plus approxlmately 80 m1nutesTh1S allows suff1c1ent separatlon and procedural t1me to set upfor the SPS deorb1t burn performed at about TLI + 90 Note thatgenerally the deorb1t burns w1ll be performed a fe11 m1nutes beforeTLI + 90 accord1ng to crew charts shown In reference 8 The no-comm except10n requ1res that 90 m1nutes be the 1nput t1me of 19n1shytlon for P-37 (onboard return-to-earth abort program) so that onshyboard calculatlons can correspond w1th ground calculat10ns to computethe CM land1ng p01nt Th1S TLI abort lS des1gned so that returnfl1ght t1me does not exceed 18 hours and abort ~V does not exceed7000 fps ThlS abort can be performed uSlng chart ~Vs and attltudesand the earths hor1zon serves as a suff1c1ent reference The maneushyver lS targeted to ach1eve the mldcorr1dor entry target Ilne andtlmed to result 1n a deslgnated recovery area

It 1S ObV10US for abort deC1S1ons early 1n the TLI + 90 m1nute t1meshyframe that a GampN SPS burn should be performed In order to keep theTLI abort procedures cons1stent and w1th emphasls on slmpl1c1ty theprocedures here reflect a SCS SPS abort burn to cover the full abortdec1s1on t1meframe

A m1dcourse correct1on for corr1dor control after a TLI abort may bedeS1red 1f the SPS burn d1d not meet expectat1ons The TLIabortprocedures 1n th1S sect10n adapt to the normal lunar return tlmel1neand procedures pr10r to the f1nal MCC

-52-

61 TLI PREPARATION PROCEDURES

GET = 150

CRO AOS(___)

CRO LOS( )(22142)

5100

Don Helmets amp Gloves

XLUNAR - INJECT (verify)EDS PWR - on (venfy)EMS FUNC - OFF (verlfy)EMS MODE - STBYEMS FUNC - IW SETVHF RNGEMS MODE - NORMALSet ~V indo to +15868 fpsEMS FUMC - ~V Test

SPS THRUST Lt - onoff (10 sec)~V lnd stops at -01 to -415

EMS MODE - STBYEMS FUMC - ~V SETVHF RNGSet ~VC

EMS FUNC---~~V=----

GDC ALIGNFDAI Select - liZcb SECS LOGIC (Z) - close (verify)cb SECS ARM (Z) - closeSECS LOGIC (Z) - on (up)MSFN Conflrm GO for PYRO ARM (If pass)SECS PYRO ARM (Z) - on (up)TRANS CONTROL PWR - ONROT CONTR PWR NORMAL (Z) - ACDC(verlfy)ROT CONTR PWR DIRECT (Z) - MNAMNBLV INnGPI - SIISIVB (venfy)LV GUID - IU (venfy)cb DIRECT ULLAGE (Z) - closedSet EVENT TIMER to 5100Begin MONITOR For TB6

CMP to Couch

TB 6 - SII SEP Lt on (TIG-9 mln 38 sec)KEY V83E

SET ORDEALFDAI Z ORB RATE at 180 0 0SII SEP Lt out (38 sec later)Start DET COUNTING UPSC CaNT - SCS (verify)MONITOR LV TANK PRESS

~P lt 36 psid (OXID gt FUEL)~P lt Z6 psid (FUEL gt OXID)

EMERGENCY CSMLV SEP UP TLM CM - BLOCK (verify)UP TLM IU - BLOCK (venfy)

-53-

+45degPY))0middot sec PY

lOK nmltHAlt25K nm

Two phas~ng mnvrs two SPS mnvrs to circular~ze at 150 nmearth orb~t

CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ssion 4K nmltHAltlOK nm CSM amp1M - Two phasing mnvrs two SPS mnvrs to circularize at 150 nm earth orb~t CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ss~on

CSM amp 1M - Two phas~ng mnvrs APS burn todepletion th~rd phasing mnvrSPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn tosem~sync orb~t

25K nmltHAlt40K nm CSM amp 1M - Two phasmg mnvrs APS burn to depletion third phas~ng mnvr SPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn to sem~sync orbit HA)40K nm DPS ava~l - DPS LOll circularize with SPS

DPS not ava~l - Lunar flyby or CSM only to lunar orbit (if reqd gtV lt4000 fps)

V37E 47E (check b~as) Record -=--rshy(Limit 98 fpsmm)

( 1fps)tVXYZN62EVIHDOTHPAD (fpsfpslnm)MONITOR VI ( ) at ECO

SCS TVC SERVO PWR 1 - ACIMNA2 - OFF

TAPE RCDR - CMD RESETHBREMS MODE - NORMAL

SIr SEP Lt - ONTLI Inhib~t S~gnals w~11 not be honored after 5942

SIVB ULLAGE BeginsSII SEP Lt - off (TIG - 18 sec)SIVB FUEL LEADSIVB ULLAGE d~scont~nues

LV ENG I Lt - onSIVB IGNITION ( GETI)LV ENG I Lt - off - -shyMONITOR THRUST amp ATTITUDEMONITOR LV TANK PRESSSIVE ECO (Lt on) (BEGIN TB7)

EMER SIVE CUTOFF AT 6 SEC PAST BURN TIME IF VI ATTAINEDTHC CCW ampNEUTRAL IN 1 SEC or SIISIVB sW - LV STAGEPremature Shutdown HAlt4K nm CSM amp 1M -

5700

58205836

F 16 835800

F 16 62

5838594259525955595900000002SUNRISE(___)

HAW AOS(__=_) KEY VERB (freeze d~splay)

SIVB ATT HOLD 20 sec amp BEGIN VENTINGSIVB NNVR TO ORB RT (HDS DN) (3middot sec)

Record VI -c---HDOT _

HPAD _

KEY RLSEF 16 62

F 16 83

HAW LOS(__=-)

KEYmiddotRLSE~VXYZ (lfps)

Record ~VX---_

~vy

WZ--

AVC---_

TAPE RCDR - off (ctr)EMS MODE - STBYEMS FUNC - OFFSECS PYRO ARM (2) - SAFE

PRO

BURN STATUS REPORT

____--~TIG

BT------VGX____-R

-----P----_Y

REMARKS

_____VI

______--HDOT______--H______---AVC______---FUEL_______OXID

_______UNBAL

F 3708=00 OOEGOS AOS CMP TO LEB

(-=-=-)

0000

0003

0005

0014

0100

-55-

62 TLI 10 MIN ABORTSECS LOGIC (2) - on (up)SECS PYRO ARM (2) - ARM

TRANS CONTR - CGH (4 sec) amp +XDET RESET (verlfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS GMD-ON

TRANS GONTR - neutral then +X for10 sec

SIVBGPI s~ - GPIExcesslve rates 6V THRUST A - NORMAL SPS THRUST - DIRECT When rates damped 6V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

TRANS CONTR +X - OFFV37E OOE

PITGH UP to LOGAL VERT (+X axlSto~ard the earth)

RATE - LOWBMAG MODE (3) - ATTIRATE 2EDS PHR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SEGS ARM (2) - opencb EDS (3) - open

TRANS CONTR -X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (180deg)P (199deg)Y (0deg)

RETRO UPDATEGETI _

JV _VG

Jtb ---GET 400K _

05G _GET DROGUE _

ENTRY P _R _

Y_--

0945

-56-

ALIGN HORIZ ON RET +1 MKGMBL CHECK (T11lle Pentattlng)MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conflnn)cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FUMC - JV SETVHF RNGSET JV from chartE~S FUMC - JVEMS fODE - NOIDlAL

lV THRUST A - NORMALV37E 47E (THRUST fONITOR)

F 16 83 lVXYZ (1 fps)

0950

1000

NOTE For aborts durlng 1st mln of TLIKEY V82E F 16 44 (HaHpTff)Burn untll Hp lt 19NM

TRANS CONTR +X

THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN JV reqdJV THRUST (2) - OFFReport cutoff

cb SPS P2 Y2- closeGfBL MTRS (4) - OFF (LMP Confinn)TRANS CONT PWR - OFFTVC SERVO PWR (2) - OFFMN BUS TIE (2) - OFFcb SPS P1amp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREIf est time to EIltOl5500 omlt fCC andenter the SUPERCIRC CKLIST as early as pos-slb1e Pg ~2~3~ __If est time to EI)Ol5500 anticlpate afCC Enter the ENTRY PREP CKLIST at step 9pg 18

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

-2tl C

l I W gt- ~-4

z laquo I I- 0 -6

l- I J u gt- ~-8

z w w -10

~_ONSANT

9O

VER

SHO

OT

BOU

ND

ARY

LIF

TV

EC

TOR

OR

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TATI

ON

LIN

E

SH

ALL

OW

TAR

GE

TLI

NE

STE

EP

TAR

GE

TLI

NE 12

gU

ND

ERSH

OO

TBO

UN

DAR

Y

RE

EN

TRY

CO

RR

IDO

R

I ~ I

-12 24

26

28

30

32

34

RE

EN

TRY

VE

LOC

ITY

VE

1-F

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EC

Ch

art

1

36

3B

6-i

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CC

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73

8X

03

-i- rtREQUIRED PITCH GIMBAL ANG LETO OBTAIN HOR-IZON AT 317

DEGREES IN wiiiiDOW

260

z~I- ~ i5 24000

1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

-I

-1-

NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

I LU HD~-

LUHD

lt0 120UJ0

~

80 HOLD PRESENT TRIMgt LU HD013

~Y~HOIgtlt

TOP OF WINDOWa 40to

31 7 SCRIBEaaI

80 TTOM OF WINDOWi= 0

0--ltoa

-40t-z

~~~Uw w u lt0 -80

HOLO PRESENT TRIlJCl

LOHU0 lt0

J gt -120 HOLD 059 TRIMlt0 z

LDHUlt0 FIELD OF VI S10 NLDHU LIFT-DOWNHEADS -UPLUHD LIFT-UP HEADS-DOWN

~~H~-160 q - P63 LIMITI- NOrE-VALIO ONLY FO~t~--

LUNAR RETURN VELOCITY

plusmnl8020 244middot 8 12 16

TIME TO 400K FT ALTITUDE-MIN

4

P37

LONG

ITUD

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RREC

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TOOB

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1350

NM

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340

344

348

352

356

364

368

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Ch

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20 100 -40

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Ch

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0 90

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120

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320

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1968

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2627

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0080

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0060

0050

0040

0030

0020

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Cll-

41)

120

200

241)

320

400

441)

520

TlI

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-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 53: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

-50-

60 TLI ABORTS

TLI Aborts are conta~ned ~n the ESD s~nce the bulk of the funct~ons

concern entry preparat20ns and performance Th~s allows a s2nglesource of procedures for procedure rev2ew val~dat~on checkout andtra~n~ng These procedures ~ncorporate TLI preparat20ns as found ~n

reference 6 w~th the TLI Abort Procedures and these t~e 2nto normallunar return Entry Procedures found ~n sect20n 5 The guidel~nes

for th~s cont2ngency are spec2f2ed 2n reference 7

In2t2al preparat~ons for TLI pos2t20n the necessary system sW2tches2n add~t~on to perform~ng an EMS ~V test and a GDC al~gnment Afterthe DET ~s set for mon2tor2ng TB6 the CMP ~ncreases the 12ght levelof the LEB DSKY to max~mum and returns to the h2s couch Th2s 2Sdone so that the LEB DSKY can be observed ~n the event sunl~ght orreflect20ns wash out the ma2n d2splay panel DSKY dur2ng cr2t2calmaneuvers The crew then straps ~n and prepares for mon2tor~ng TB6as 2nd2cated by the SII SEP L~te The t2mes se~uence of procedures2S keyed on th~s d~splay and ~ncludes the DET START funct~on andSIVB IGNITION Dur2ng the burn the crew mon2tors the FDAIs foratt~tude excurs20ns and abnormal rates report~ng status checks toM~ss2on Control at d2screet t~mes dur2ng the maneuver Upon SIVBSHUTDOWN the eMP records the DSKY d~splayed performance parametersand awa2ts ground conf2rmat~on

The rat~onal for TLI aborts ~s descr~bed 2n reference 7 A summar2shyzat20n 2S extracted to prov2de background and gu2de12nes 2n th2sdocument The abort procedures cover aborts 10 m2nutes after conshyt2ngent SIVE shutdown and aborts 90 m2nutes after normal SIVE shutshydown t2me

The 10 m~nute TLI abort ~s des2gned to be used dur~ng TLI ~n theevent a spacecraft problem develops Wh2Ch can result 2n catastrophe2f ~mmed~ate act~on 2S not taken If the s~tuat20n perm~ts the crewshould always allow the SIVB to complete TLI at wh~ch t~me the groundand crew can perform a malfunct~on analys~s to determ~ne ~f an abort~s adv~sable If a fa~lure occurs that necess2tates the shutdown ofthe SIVB and the ~u~ck return of the crew to earth th~s abort ~s

des~gned to be as ~nsens~t~ve to execut~on errors as poss~ble andst21l be targeted to m2dcorr2dor The burn att~tude w~th the f~ed

hor~zon reference ~s a constant value for any shutdown t~me Theburn durat~on 2S a funct20n of shutdown t2me and 2S ava21able fromcrew charts S~nce the pr~mary purpose of th~s abort ~s to returnto earth as qU2ckly as poss2ble there are no restr2ct20ns as toland~ng locat~on However ~f the t~me to EI is greater than abouttwo hours a midcourse correct20n should be ant~c~pated

The 90 m2nute TLI abort 2S to be used 2f a cr2t2cal subsystem malshyfunct~on ~s determ2ned and the dec2s~on to abort ~s made after the

-51-

TLI cutoff and before TLI cutoff plus approxlmately 80 m1nutesTh1S allows suff1c1ent separatlon and procedural t1me to set upfor the SPS deorb1t burn performed at about TLI + 90 Note thatgenerally the deorb1t burns w1ll be performed a fe11 m1nutes beforeTLI + 90 accord1ng to crew charts shown In reference 8 The no-comm except10n requ1res that 90 m1nutes be the 1nput t1me of 19n1shytlon for P-37 (onboard return-to-earth abort program) so that onshyboard calculatlons can correspond w1th ground calculat10ns to computethe CM land1ng p01nt Th1S TLI abort lS des1gned so that returnfl1ght t1me does not exceed 18 hours and abort ~V does not exceed7000 fps ThlS abort can be performed uSlng chart ~Vs and attltudesand the earths hor1zon serves as a suff1c1ent reference The maneushyver lS targeted to ach1eve the mldcorr1dor entry target Ilne andtlmed to result 1n a deslgnated recovery area

It 1S ObV10US for abort deC1S1ons early 1n the TLI + 90 m1nute t1meshyframe that a GampN SPS burn should be performed In order to keep theTLI abort procedures cons1stent and w1th emphasls on slmpl1c1ty theprocedures here reflect a SCS SPS abort burn to cover the full abortdec1s1on t1meframe

A m1dcourse correct1on for corr1dor control after a TLI abort may bedeS1red 1f the SPS burn d1d not meet expectat1ons The TLIabortprocedures 1n th1S sect10n adapt to the normal lunar return tlmel1neand procedures pr10r to the f1nal MCC

-52-

61 TLI PREPARATION PROCEDURES

GET = 150

CRO AOS(___)

CRO LOS( )(22142)

5100

Don Helmets amp Gloves

XLUNAR - INJECT (verify)EDS PWR - on (venfy)EMS FUNC - OFF (verlfy)EMS MODE - STBYEMS FUNC - IW SETVHF RNGEMS MODE - NORMALSet ~V indo to +15868 fpsEMS FUMC - ~V Test

SPS THRUST Lt - onoff (10 sec)~V lnd stops at -01 to -415

EMS MODE - STBYEMS FUMC - ~V SETVHF RNGSet ~VC

EMS FUNC---~~V=----

GDC ALIGNFDAI Select - liZcb SECS LOGIC (Z) - close (verify)cb SECS ARM (Z) - closeSECS LOGIC (Z) - on (up)MSFN Conflrm GO for PYRO ARM (If pass)SECS PYRO ARM (Z) - on (up)TRANS CONTROL PWR - ONROT CONTR PWR NORMAL (Z) - ACDC(verlfy)ROT CONTR PWR DIRECT (Z) - MNAMNBLV INnGPI - SIISIVB (venfy)LV GUID - IU (venfy)cb DIRECT ULLAGE (Z) - closedSet EVENT TIMER to 5100Begin MONITOR For TB6

CMP to Couch

TB 6 - SII SEP Lt on (TIG-9 mln 38 sec)KEY V83E

SET ORDEALFDAI Z ORB RATE at 180 0 0SII SEP Lt out (38 sec later)Start DET COUNTING UPSC CaNT - SCS (verify)MONITOR LV TANK PRESS

~P lt 36 psid (OXID gt FUEL)~P lt Z6 psid (FUEL gt OXID)

EMERGENCY CSMLV SEP UP TLM CM - BLOCK (verify)UP TLM IU - BLOCK (venfy)

-53-

+45degPY))0middot sec PY

lOK nmltHAlt25K nm

Two phas~ng mnvrs two SPS mnvrs to circular~ze at 150 nmearth orb~t

CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ssion 4K nmltHAltlOK nm CSM amp1M - Two phasing mnvrs two SPS mnvrs to circularize at 150 nm earth orb~t CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ss~on

CSM amp 1M - Two phas~ng mnvrs APS burn todepletion th~rd phasing mnvrSPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn tosem~sync orb~t

25K nmltHAlt40K nm CSM amp 1M - Two phasmg mnvrs APS burn to depletion third phas~ng mnvr SPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn to sem~sync orbit HA)40K nm DPS ava~l - DPS LOll circularize with SPS

DPS not ava~l - Lunar flyby or CSM only to lunar orbit (if reqd gtV lt4000 fps)

V37E 47E (check b~as) Record -=--rshy(Limit 98 fpsmm)

( 1fps)tVXYZN62EVIHDOTHPAD (fpsfpslnm)MONITOR VI ( ) at ECO

SCS TVC SERVO PWR 1 - ACIMNA2 - OFF

TAPE RCDR - CMD RESETHBREMS MODE - NORMAL

SIr SEP Lt - ONTLI Inhib~t S~gnals w~11 not be honored after 5942

SIVB ULLAGE BeginsSII SEP Lt - off (TIG - 18 sec)SIVB FUEL LEADSIVB ULLAGE d~scont~nues

LV ENG I Lt - onSIVB IGNITION ( GETI)LV ENG I Lt - off - -shyMONITOR THRUST amp ATTITUDEMONITOR LV TANK PRESSSIVE ECO (Lt on) (BEGIN TB7)

EMER SIVE CUTOFF AT 6 SEC PAST BURN TIME IF VI ATTAINEDTHC CCW ampNEUTRAL IN 1 SEC or SIISIVB sW - LV STAGEPremature Shutdown HAlt4K nm CSM amp 1M -

5700

58205836

F 16 835800

F 16 62

5838594259525955595900000002SUNRISE(___)

HAW AOS(__=_) KEY VERB (freeze d~splay)

SIVB ATT HOLD 20 sec amp BEGIN VENTINGSIVB NNVR TO ORB RT (HDS DN) (3middot sec)

Record VI -c---HDOT _

HPAD _

KEY RLSEF 16 62

F 16 83

HAW LOS(__=-)

KEYmiddotRLSE~VXYZ (lfps)

Record ~VX---_

~vy

WZ--

AVC---_

TAPE RCDR - off (ctr)EMS MODE - STBYEMS FUNC - OFFSECS PYRO ARM (2) - SAFE

PRO

BURN STATUS REPORT

____--~TIG

BT------VGX____-R

-----P----_Y

REMARKS

_____VI

______--HDOT______--H______---AVC______---FUEL_______OXID

_______UNBAL

F 3708=00 OOEGOS AOS CMP TO LEB

(-=-=-)

0000

0003

0005

0014

0100

-55-

62 TLI 10 MIN ABORTSECS LOGIC (2) - on (up)SECS PYRO ARM (2) - ARM

TRANS CONTR - CGH (4 sec) amp +XDET RESET (verlfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS GMD-ON

TRANS GONTR - neutral then +X for10 sec

SIVBGPI s~ - GPIExcesslve rates 6V THRUST A - NORMAL SPS THRUST - DIRECT When rates damped 6V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

TRANS CONTR +X - OFFV37E OOE

PITGH UP to LOGAL VERT (+X axlSto~ard the earth)

RATE - LOWBMAG MODE (3) - ATTIRATE 2EDS PHR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SEGS ARM (2) - opencb EDS (3) - open

TRANS CONTR -X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (180deg)P (199deg)Y (0deg)

RETRO UPDATEGETI _

JV _VG

Jtb ---GET 400K _

05G _GET DROGUE _

ENTRY P _R _

Y_--

0945

-56-

ALIGN HORIZ ON RET +1 MKGMBL CHECK (T11lle Pentattlng)MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conflnn)cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FUMC - JV SETVHF RNGSET JV from chartE~S FUMC - JVEMS fODE - NOIDlAL

lV THRUST A - NORMALV37E 47E (THRUST fONITOR)

F 16 83 lVXYZ (1 fps)

0950

1000

NOTE For aborts durlng 1st mln of TLIKEY V82E F 16 44 (HaHpTff)Burn untll Hp lt 19NM

TRANS CONTR +X

THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN JV reqdJV THRUST (2) - OFFReport cutoff

cb SPS P2 Y2- closeGfBL MTRS (4) - OFF (LMP Confinn)TRANS CONT PWR - OFFTVC SERVO PWR (2) - OFFMN BUS TIE (2) - OFFcb SPS P1amp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREIf est time to EIltOl5500 omlt fCC andenter the SUPERCIRC CKLIST as early as pos-slb1e Pg ~2~3~ __If est time to EI)Ol5500 anticlpate afCC Enter the ENTRY PREP CKLIST at step 9pg 18

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

-2tl C

l I W gt- ~-4

z laquo I I- 0 -6

l- I J u gt- ~-8

z w w -10

~_ONSANT

9O

VER

SHO

OT

BOU

ND

ARY

LIF

TV

EC

TOR

OR

IEN

TATI

ON

LIN

E

SH

ALL

OW

TAR

GE

TLI

NE

STE

EP

TAR

GE

TLI

NE 12

gU

ND

ERSH

OO

TBO

UN

DAR

Y

RE

EN

TRY

CO

RR

IDO

R

I ~ I

-12 24

26

28

30

32

34

RE

EN

TRY

VE

LOC

ITY

VE

1-F

TS

EC

Ch

art

1

36

3B

6-i

~

5CM

CC

ON

ST

NT

DR

VI z gt

~

I4

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I

gtamp

J+

-I

-

J Cl z

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bull-1

+-

u ubullbull

~r

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)

2829

JOn

J23

33

43

5IN

ER

TIA

LR

EE

NTR

YV

ELO

CIT

YA

T4

00

00

0fl

VE

I-F

TS

EC

Ch

art

2

J63

73

8X

03

-i- rtREQUIRED PITCH GIMBAL ANG LETO OBTAIN HOR-IZON AT 317

DEGREES IN wiiiiDOW

260

z~I- ~ i5 24000

1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

-I

-1-

NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

I LU HD~-

LUHD

lt0 120UJ0

~

80 HOLD PRESENT TRIMgt LU HD013

~Y~HOIgtlt

TOP OF WINDOWa 40to

31 7 SCRIBEaaI

80 TTOM OF WINDOWi= 0

0--ltoa

-40t-z

~~~Uw w u lt0 -80

HOLO PRESENT TRIlJCl

LOHU0 lt0

J gt -120 HOLD 059 TRIMlt0 z

LDHUlt0 FIELD OF VI S10 NLDHU LIFT-DOWNHEADS -UPLUHD LIFT-UP HEADS-DOWN

~~H~-160 q - P63 LIMITI- NOrE-VALIO ONLY FO~t~--

LUNAR RETURN VELOCITY

plusmnl8020 244middot 8 12 16

TIME TO 400K FT ALTITUDE-MIN

4

P37

LONG

ITUD

ECO

RREC

TION

TOOB

TAIN

1350

NM

ENTR

YRA

NGE

Ugt

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cgt

3z 0 I- u U

J0

0

0

2I

U~

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cgt

I

gtI- U

gt z 0 J ltJ

1 -0

340

344

348

352

356

364

368

x10

3

CMC

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TIAL

VELO

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TITU

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EC

Ch

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o

20 100 -40

-10

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30

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-BB

A+

lrBB

A

=----

-----

t~I

AB

SA_

-04

0A

AV

Z=

-()4

D_

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j

+

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plusmniff

--d~~tj

h-

Ir

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2030

NOTE

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NO

MIN

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RET

RB

=22

MIN

30

-40

-50

---------O

VE

RB

UR

N---------I------U

ND

ER

BU

RN

------I

~30

-20

-tD

010

20

AA

VX

FTS

EC

-60

Ch

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6

1000

0 90

00 70

00 60

00 i50

00 iMl

OO ilOO

O i20

00 10

00 o

040

120

200

EMS

6V-

FTS

EC

240

320

400

440

520

S-IV

BeO

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C

105

0

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LAUN

CHAZ

IMUT

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72r

rr

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+rmr)lfl~

GIM

BAL

ANGL

E

ROLL

=IS

OPI

TCH

=199

YAW

0

TLI

-10

MIN

ABO

RTLA

UNCH

DEC

21

1968

400050

z =gt co23

0on 3

~7 X ampJ V

gt ~ 6

2627

~B

~n

_n

INER

TIAL

VELO

CITY

ATAB

ORT

IS-IV

BC

UTO

FF)middot

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EC34

3536

Xllf

Ch

art

7

7

1000

0i

0-00

EMS

V-F

TSE

C90

0080

0070

0060

0050

0040

0030

0020

0010

000

II

II

II

II

S-IV

BBU

RNTI

ME

-M

INSE

Cll-

41)

120

200

241)

320

400

441)

520

TlI

-I0

MIN

ABOR

TlA

UNCH

-DE

C21

19

68

lAUN

CHA

ZIM

UTH

lllJ

72I ~ I

Z526

27~

~bull

DX

~IN

ERTI

ALVE

LOCI

TYAT

ABOR

T(5

-IVB

CU

TaF

l-

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EC

Ch

art

8

34l6

Xla

3

-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 54: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

-51-

TLI cutoff and before TLI cutoff plus approxlmately 80 m1nutesTh1S allows suff1c1ent separatlon and procedural t1me to set upfor the SPS deorb1t burn performed at about TLI + 90 Note thatgenerally the deorb1t burns w1ll be performed a fe11 m1nutes beforeTLI + 90 accord1ng to crew charts shown In reference 8 The no-comm except10n requ1res that 90 m1nutes be the 1nput t1me of 19n1shytlon for P-37 (onboard return-to-earth abort program) so that onshyboard calculatlons can correspond w1th ground calculat10ns to computethe CM land1ng p01nt Th1S TLI abort lS des1gned so that returnfl1ght t1me does not exceed 18 hours and abort ~V does not exceed7000 fps ThlS abort can be performed uSlng chart ~Vs and attltudesand the earths hor1zon serves as a suff1c1ent reference The maneushyver lS targeted to ach1eve the mldcorr1dor entry target Ilne andtlmed to result 1n a deslgnated recovery area

It 1S ObV10US for abort deC1S1ons early 1n the TLI + 90 m1nute t1meshyframe that a GampN SPS burn should be performed In order to keep theTLI abort procedures cons1stent and w1th emphasls on slmpl1c1ty theprocedures here reflect a SCS SPS abort burn to cover the full abortdec1s1on t1meframe

A m1dcourse correct1on for corr1dor control after a TLI abort may bedeS1red 1f the SPS burn d1d not meet expectat1ons The TLIabortprocedures 1n th1S sect10n adapt to the normal lunar return tlmel1neand procedures pr10r to the f1nal MCC

-52-

61 TLI PREPARATION PROCEDURES

GET = 150

CRO AOS(___)

CRO LOS( )(22142)

5100

Don Helmets amp Gloves

XLUNAR - INJECT (verify)EDS PWR - on (venfy)EMS FUNC - OFF (verlfy)EMS MODE - STBYEMS FUNC - IW SETVHF RNGEMS MODE - NORMALSet ~V indo to +15868 fpsEMS FUMC - ~V Test

SPS THRUST Lt - onoff (10 sec)~V lnd stops at -01 to -415

EMS MODE - STBYEMS FUMC - ~V SETVHF RNGSet ~VC

EMS FUNC---~~V=----

GDC ALIGNFDAI Select - liZcb SECS LOGIC (Z) - close (verify)cb SECS ARM (Z) - closeSECS LOGIC (Z) - on (up)MSFN Conflrm GO for PYRO ARM (If pass)SECS PYRO ARM (Z) - on (up)TRANS CONTROL PWR - ONROT CONTR PWR NORMAL (Z) - ACDC(verlfy)ROT CONTR PWR DIRECT (Z) - MNAMNBLV INnGPI - SIISIVB (venfy)LV GUID - IU (venfy)cb DIRECT ULLAGE (Z) - closedSet EVENT TIMER to 5100Begin MONITOR For TB6

CMP to Couch

TB 6 - SII SEP Lt on (TIG-9 mln 38 sec)KEY V83E

SET ORDEALFDAI Z ORB RATE at 180 0 0SII SEP Lt out (38 sec later)Start DET COUNTING UPSC CaNT - SCS (verify)MONITOR LV TANK PRESS

~P lt 36 psid (OXID gt FUEL)~P lt Z6 psid (FUEL gt OXID)

EMERGENCY CSMLV SEP UP TLM CM - BLOCK (verify)UP TLM IU - BLOCK (venfy)

-53-

+45degPY))0middot sec PY

lOK nmltHAlt25K nm

Two phas~ng mnvrs two SPS mnvrs to circular~ze at 150 nmearth orb~t

CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ssion 4K nmltHAltlOK nm CSM amp1M - Two phasing mnvrs two SPS mnvrs to circularize at 150 nm earth orb~t CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ss~on

CSM amp 1M - Two phas~ng mnvrs APS burn todepletion th~rd phasing mnvrSPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn tosem~sync orb~t

25K nmltHAlt40K nm CSM amp 1M - Two phasmg mnvrs APS burn to depletion third phas~ng mnvr SPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn to sem~sync orbit HA)40K nm DPS ava~l - DPS LOll circularize with SPS

DPS not ava~l - Lunar flyby or CSM only to lunar orbit (if reqd gtV lt4000 fps)

V37E 47E (check b~as) Record -=--rshy(Limit 98 fpsmm)

( 1fps)tVXYZN62EVIHDOTHPAD (fpsfpslnm)MONITOR VI ( ) at ECO

SCS TVC SERVO PWR 1 - ACIMNA2 - OFF

TAPE RCDR - CMD RESETHBREMS MODE - NORMAL

SIr SEP Lt - ONTLI Inhib~t S~gnals w~11 not be honored after 5942

SIVB ULLAGE BeginsSII SEP Lt - off (TIG - 18 sec)SIVB FUEL LEADSIVB ULLAGE d~scont~nues

LV ENG I Lt - onSIVB IGNITION ( GETI)LV ENG I Lt - off - -shyMONITOR THRUST amp ATTITUDEMONITOR LV TANK PRESSSIVE ECO (Lt on) (BEGIN TB7)

EMER SIVE CUTOFF AT 6 SEC PAST BURN TIME IF VI ATTAINEDTHC CCW ampNEUTRAL IN 1 SEC or SIISIVB sW - LV STAGEPremature Shutdown HAlt4K nm CSM amp 1M -

5700

58205836

F 16 835800

F 16 62

5838594259525955595900000002SUNRISE(___)

HAW AOS(__=_) KEY VERB (freeze d~splay)

SIVB ATT HOLD 20 sec amp BEGIN VENTINGSIVB NNVR TO ORB RT (HDS DN) (3middot sec)

Record VI -c---HDOT _

HPAD _

KEY RLSEF 16 62

F 16 83

HAW LOS(__=-)

KEYmiddotRLSE~VXYZ (lfps)

Record ~VX---_

~vy

WZ--

AVC---_

TAPE RCDR - off (ctr)EMS MODE - STBYEMS FUNC - OFFSECS PYRO ARM (2) - SAFE

PRO

BURN STATUS REPORT

____--~TIG

BT------VGX____-R

-----P----_Y

REMARKS

_____VI

______--HDOT______--H______---AVC______---FUEL_______OXID

_______UNBAL

F 3708=00 OOEGOS AOS CMP TO LEB

(-=-=-)

0000

0003

0005

0014

0100

-55-

62 TLI 10 MIN ABORTSECS LOGIC (2) - on (up)SECS PYRO ARM (2) - ARM

TRANS CONTR - CGH (4 sec) amp +XDET RESET (verlfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS GMD-ON

TRANS GONTR - neutral then +X for10 sec

SIVBGPI s~ - GPIExcesslve rates 6V THRUST A - NORMAL SPS THRUST - DIRECT When rates damped 6V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

TRANS CONTR +X - OFFV37E OOE

PITGH UP to LOGAL VERT (+X axlSto~ard the earth)

RATE - LOWBMAG MODE (3) - ATTIRATE 2EDS PHR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SEGS ARM (2) - opencb EDS (3) - open

TRANS CONTR -X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (180deg)P (199deg)Y (0deg)

RETRO UPDATEGETI _

JV _VG

Jtb ---GET 400K _

05G _GET DROGUE _

ENTRY P _R _

Y_--

0945

-56-

ALIGN HORIZ ON RET +1 MKGMBL CHECK (T11lle Pentattlng)MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conflnn)cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FUMC - JV SETVHF RNGSET JV from chartE~S FUMC - JVEMS fODE - NOIDlAL

lV THRUST A - NORMALV37E 47E (THRUST fONITOR)

F 16 83 lVXYZ (1 fps)

0950

1000

NOTE For aborts durlng 1st mln of TLIKEY V82E F 16 44 (HaHpTff)Burn untll Hp lt 19NM

TRANS CONTR +X

THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN JV reqdJV THRUST (2) - OFFReport cutoff

cb SPS P2 Y2- closeGfBL MTRS (4) - OFF (LMP Confinn)TRANS CONT PWR - OFFTVC SERVO PWR (2) - OFFMN BUS TIE (2) - OFFcb SPS P1amp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREIf est time to EIltOl5500 omlt fCC andenter the SUPERCIRC CKLIST as early as pos-slb1e Pg ~2~3~ __If est time to EI)Ol5500 anticlpate afCC Enter the ENTRY PREP CKLIST at step 9pg 18

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

-2tl C

l I W gt- ~-4

z laquo I I- 0 -6

l- I J u gt- ~-8

z w w -10

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ALL

OW

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STE

EP

TAR

GE

TLI

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ND

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OO

TBO

UN

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26

28

30

32

34

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73

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03

-i- rtREQUIRED PITCH GIMBAL ANG LETO OBTAIN HOR-IZON AT 317

DEGREES IN wiiiiDOW

260

z~I- ~ i5 24000

1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

-I

-1-

NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

I LU HD~-

LUHD

lt0 120UJ0

~

80 HOLD PRESENT TRIMgt LU HD013

~Y~HOIgtlt

TOP OF WINDOWa 40to

31 7 SCRIBEaaI

80 TTOM OF WINDOWi= 0

0--ltoa

-40t-z

~~~Uw w u lt0 -80

HOLO PRESENT TRIlJCl

LOHU0 lt0

J gt -120 HOLD 059 TRIMlt0 z

LDHUlt0 FIELD OF VI S10 NLDHU LIFT-DOWNHEADS -UPLUHD LIFT-UP HEADS-DOWN

~~H~-160 q - P63 LIMITI- NOrE-VALIO ONLY FO~t~--

LUNAR RETURN VELOCITY

plusmnl8020 244middot 8 12 16

TIME TO 400K FT ALTITUDE-MIN

4

P37

LONG

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344

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352

356

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00 i50

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120

200

EMS

6V-

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240

320

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1968

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0030

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Cll-

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120

200

241)

320

400

441)

520

TlI

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-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 55: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

-52-

61 TLI PREPARATION PROCEDURES

GET = 150

CRO AOS(___)

CRO LOS( )(22142)

5100

Don Helmets amp Gloves

XLUNAR - INJECT (verify)EDS PWR - on (venfy)EMS FUNC - OFF (verlfy)EMS MODE - STBYEMS FUNC - IW SETVHF RNGEMS MODE - NORMALSet ~V indo to +15868 fpsEMS FUMC - ~V Test

SPS THRUST Lt - onoff (10 sec)~V lnd stops at -01 to -415

EMS MODE - STBYEMS FUMC - ~V SETVHF RNGSet ~VC

EMS FUNC---~~V=----

GDC ALIGNFDAI Select - liZcb SECS LOGIC (Z) - close (verify)cb SECS ARM (Z) - closeSECS LOGIC (Z) - on (up)MSFN Conflrm GO for PYRO ARM (If pass)SECS PYRO ARM (Z) - on (up)TRANS CONTROL PWR - ONROT CONTR PWR NORMAL (Z) - ACDC(verlfy)ROT CONTR PWR DIRECT (Z) - MNAMNBLV INnGPI - SIISIVB (venfy)LV GUID - IU (venfy)cb DIRECT ULLAGE (Z) - closedSet EVENT TIMER to 5100Begin MONITOR For TB6

CMP to Couch

TB 6 - SII SEP Lt on (TIG-9 mln 38 sec)KEY V83E

SET ORDEALFDAI Z ORB RATE at 180 0 0SII SEP Lt out (38 sec later)Start DET COUNTING UPSC CaNT - SCS (verify)MONITOR LV TANK PRESS

~P lt 36 psid (OXID gt FUEL)~P lt Z6 psid (FUEL gt OXID)

EMERGENCY CSMLV SEP UP TLM CM - BLOCK (verify)UP TLM IU - BLOCK (venfy)

-53-

+45degPY))0middot sec PY

lOK nmltHAlt25K nm

Two phas~ng mnvrs two SPS mnvrs to circular~ze at 150 nmearth orb~t

CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ssion 4K nmltHAltlOK nm CSM amp1M - Two phasing mnvrs two SPS mnvrs to circularize at 150 nm earth orb~t CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ss~on

CSM amp 1M - Two phas~ng mnvrs APS burn todepletion th~rd phasing mnvrSPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn tosem~sync orb~t

25K nmltHAlt40K nm CSM amp 1M - Two phasmg mnvrs APS burn to depletion third phas~ng mnvr SPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn to sem~sync orbit HA)40K nm DPS ava~l - DPS LOll circularize with SPS

DPS not ava~l - Lunar flyby or CSM only to lunar orbit (if reqd gtV lt4000 fps)

V37E 47E (check b~as) Record -=--rshy(Limit 98 fpsmm)

( 1fps)tVXYZN62EVIHDOTHPAD (fpsfpslnm)MONITOR VI ( ) at ECO

SCS TVC SERVO PWR 1 - ACIMNA2 - OFF

TAPE RCDR - CMD RESETHBREMS MODE - NORMAL

SIr SEP Lt - ONTLI Inhib~t S~gnals w~11 not be honored after 5942

SIVB ULLAGE BeginsSII SEP Lt - off (TIG - 18 sec)SIVB FUEL LEADSIVB ULLAGE d~scont~nues

LV ENG I Lt - onSIVB IGNITION ( GETI)LV ENG I Lt - off - -shyMONITOR THRUST amp ATTITUDEMONITOR LV TANK PRESSSIVE ECO (Lt on) (BEGIN TB7)

EMER SIVE CUTOFF AT 6 SEC PAST BURN TIME IF VI ATTAINEDTHC CCW ampNEUTRAL IN 1 SEC or SIISIVB sW - LV STAGEPremature Shutdown HAlt4K nm CSM amp 1M -

5700

58205836

F 16 835800

F 16 62

5838594259525955595900000002SUNRISE(___)

HAW AOS(__=_) KEY VERB (freeze d~splay)

SIVB ATT HOLD 20 sec amp BEGIN VENTINGSIVB NNVR TO ORB RT (HDS DN) (3middot sec)

Record VI -c---HDOT _

HPAD _

KEY RLSEF 16 62

F 16 83

HAW LOS(__=-)

KEYmiddotRLSE~VXYZ (lfps)

Record ~VX---_

~vy

WZ--

AVC---_

TAPE RCDR - off (ctr)EMS MODE - STBYEMS FUNC - OFFSECS PYRO ARM (2) - SAFE

PRO

BURN STATUS REPORT

____--~TIG

BT------VGX____-R

-----P----_Y

REMARKS

_____VI

______--HDOT______--H______---AVC______---FUEL_______OXID

_______UNBAL

F 3708=00 OOEGOS AOS CMP TO LEB

(-=-=-)

0000

0003

0005

0014

0100

-55-

62 TLI 10 MIN ABORTSECS LOGIC (2) - on (up)SECS PYRO ARM (2) - ARM

TRANS CONTR - CGH (4 sec) amp +XDET RESET (verlfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS GMD-ON

TRANS GONTR - neutral then +X for10 sec

SIVBGPI s~ - GPIExcesslve rates 6V THRUST A - NORMAL SPS THRUST - DIRECT When rates damped 6V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

TRANS CONTR +X - OFFV37E OOE

PITGH UP to LOGAL VERT (+X axlSto~ard the earth)

RATE - LOWBMAG MODE (3) - ATTIRATE 2EDS PHR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SEGS ARM (2) - opencb EDS (3) - open

TRANS CONTR -X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (180deg)P (199deg)Y (0deg)

RETRO UPDATEGETI _

JV _VG

Jtb ---GET 400K _

05G _GET DROGUE _

ENTRY P _R _

Y_--

0945

-56-

ALIGN HORIZ ON RET +1 MKGMBL CHECK (T11lle Pentattlng)MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conflnn)cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FUMC - JV SETVHF RNGSET JV from chartE~S FUMC - JVEMS fODE - NOIDlAL

lV THRUST A - NORMALV37E 47E (THRUST fONITOR)

F 16 83 lVXYZ (1 fps)

0950

1000

NOTE For aborts durlng 1st mln of TLIKEY V82E F 16 44 (HaHpTff)Burn untll Hp lt 19NM

TRANS CONTR +X

THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN JV reqdJV THRUST (2) - OFFReport cutoff

cb SPS P2 Y2- closeGfBL MTRS (4) - OFF (LMP Confinn)TRANS CONT PWR - OFFTVC SERVO PWR (2) - OFFMN BUS TIE (2) - OFFcb SPS P1amp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREIf est time to EIltOl5500 omlt fCC andenter the SUPERCIRC CKLIST as early as pos-slb1e Pg ~2~3~ __If est time to EI)Ol5500 anticlpate afCC Enter the ENTRY PREP CKLIST at step 9pg 18

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

-2tl C

l I W gt- ~-4

z laquo I I- 0 -6

l- I J u gt- ~-8

z w w -10

~_ONSANT

9O

VER

SHO

OT

BOU

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LIF

TV

EC

TOR

OR

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TATI

ON

LIN

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SH

ALL

OW

TAR

GE

TLI

NE

STE

EP

TAR

GE

TLI

NE 12

gU

ND

ERSH

OO

TBO

UN

DAR

Y

RE

EN

TRY

CO

RR

IDO

R

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-12 24

26

28

30

32

34

RE

EN

TRY

VE

LOC

ITY

VE

1-F

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EC

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3B

6-i

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CC

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5IN

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LR

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73

8X

03

-i- rtREQUIRED PITCH GIMBAL ANG LETO OBTAIN HOR-IZON AT 317

DEGREES IN wiiiiDOW

260

z~I- ~ i5 24000

1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

-I

-1-

NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

I LU HD~-

LUHD

lt0 120UJ0

~

80 HOLD PRESENT TRIMgt LU HD013

~Y~HOIgtlt

TOP OF WINDOWa 40to

31 7 SCRIBEaaI

80 TTOM OF WINDOWi= 0

0--ltoa

-40t-z

~~~Uw w u lt0 -80

HOLO PRESENT TRIlJCl

LOHU0 lt0

J gt -120 HOLD 059 TRIMlt0 z

LDHUlt0 FIELD OF VI S10 NLDHU LIFT-DOWNHEADS -UPLUHD LIFT-UP HEADS-DOWN

~~H~-160 q - P63 LIMITI- NOrE-VALIO ONLY FO~t~--

LUNAR RETURN VELOCITY

plusmnl8020 244middot 8 12 16

TIME TO 400K FT ALTITUDE-MIN

4

P37

LONG

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ECO

RREC

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TOOB

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1350

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340

344

348

352

356

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AA

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120

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6V-

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240

320

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1968

400050

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0060

0050

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0030

0020

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II

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BBU

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Cll-

41)

120

200

241)

320

400

441)

520

TlI

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ABOR

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-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 56: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

-53-

+45degPY))0middot sec PY

lOK nmltHAlt25K nm

Two phas~ng mnvrs two SPS mnvrs to circular~ze at 150 nmearth orb~t

CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ssion 4K nmltHAltlOK nm CSM amp1M - Two phasing mnvrs two SPS mnvrs to circularize at 150 nm earth orb~t CSM only - SPS phas~ng mnvr MCCs low earth orb~t m~ss~on

CSM amp 1M - Two phas~ng mnvrs APS burn todepletion th~rd phasing mnvrSPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn tosem~sync orb~t

25K nmltHAlt40K nm CSM amp 1M - Two phasmg mnvrs APS burn to depletion third phas~ng mnvr SPS burn to sem~sync orb~t

CSM only - Two phas~ng mnvrs SPS burn to sem~sync orbit HA)40K nm DPS ava~l - DPS LOll circularize with SPS

DPS not ava~l - Lunar flyby or CSM only to lunar orbit (if reqd gtV lt4000 fps)

V37E 47E (check b~as) Record -=--rshy(Limit 98 fpsmm)

( 1fps)tVXYZN62EVIHDOTHPAD (fpsfpslnm)MONITOR VI ( ) at ECO

SCS TVC SERVO PWR 1 - ACIMNA2 - OFF

TAPE RCDR - CMD RESETHBREMS MODE - NORMAL

SIr SEP Lt - ONTLI Inhib~t S~gnals w~11 not be honored after 5942

SIVB ULLAGE BeginsSII SEP Lt - off (TIG - 18 sec)SIVB FUEL LEADSIVB ULLAGE d~scont~nues

LV ENG I Lt - onSIVB IGNITION ( GETI)LV ENG I Lt - off - -shyMONITOR THRUST amp ATTITUDEMONITOR LV TANK PRESSSIVE ECO (Lt on) (BEGIN TB7)

EMER SIVE CUTOFF AT 6 SEC PAST BURN TIME IF VI ATTAINEDTHC CCW ampNEUTRAL IN 1 SEC or SIISIVB sW - LV STAGEPremature Shutdown HAlt4K nm CSM amp 1M -

5700

58205836

F 16 835800

F 16 62

5838594259525955595900000002SUNRISE(___)

HAW AOS(__=_) KEY VERB (freeze d~splay)

SIVB ATT HOLD 20 sec amp BEGIN VENTINGSIVB NNVR TO ORB RT (HDS DN) (3middot sec)

Record VI -c---HDOT _

HPAD _

KEY RLSEF 16 62

F 16 83

HAW LOS(__=-)

KEYmiddotRLSE~VXYZ (lfps)

Record ~VX---_

~vy

WZ--

AVC---_

TAPE RCDR - off (ctr)EMS MODE - STBYEMS FUNC - OFFSECS PYRO ARM (2) - SAFE

PRO

BURN STATUS REPORT

____--~TIG

BT------VGX____-R

-----P----_Y

REMARKS

_____VI

______--HDOT______--H______---AVC______---FUEL_______OXID

_______UNBAL

F 3708=00 OOEGOS AOS CMP TO LEB

(-=-=-)

0000

0003

0005

0014

0100

-55-

62 TLI 10 MIN ABORTSECS LOGIC (2) - on (up)SECS PYRO ARM (2) - ARM

TRANS CONTR - CGH (4 sec) amp +XDET RESET (verlfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS GMD-ON

TRANS GONTR - neutral then +X for10 sec

SIVBGPI s~ - GPIExcesslve rates 6V THRUST A - NORMAL SPS THRUST - DIRECT When rates damped 6V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

TRANS CONTR +X - OFFV37E OOE

PITGH UP to LOGAL VERT (+X axlSto~ard the earth)

RATE - LOWBMAG MODE (3) - ATTIRATE 2EDS PHR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SEGS ARM (2) - opencb EDS (3) - open

TRANS CONTR -X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (180deg)P (199deg)Y (0deg)

RETRO UPDATEGETI _

JV _VG

Jtb ---GET 400K _

05G _GET DROGUE _

ENTRY P _R _

Y_--

0945

-56-

ALIGN HORIZ ON RET +1 MKGMBL CHECK (T11lle Pentattlng)MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conflnn)cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FUMC - JV SETVHF RNGSET JV from chartE~S FUMC - JVEMS fODE - NOIDlAL

lV THRUST A - NORMALV37E 47E (THRUST fONITOR)

F 16 83 lVXYZ (1 fps)

0950

1000

NOTE For aborts durlng 1st mln of TLIKEY V82E F 16 44 (HaHpTff)Burn untll Hp lt 19NM

TRANS CONTR +X

THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN JV reqdJV THRUST (2) - OFFReport cutoff

cb SPS P2 Y2- closeGfBL MTRS (4) - OFF (LMP Confinn)TRANS CONT PWR - OFFTVC SERVO PWR (2) - OFFMN BUS TIE (2) - OFFcb SPS P1amp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREIf est time to EIltOl5500 omlt fCC andenter the SUPERCIRC CKLIST as early as pos-slb1e Pg ~2~3~ __If est time to EI)Ol5500 anticlpate afCC Enter the ENTRY PREP CKLIST at step 9pg 18

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

-2tl C

l I W gt- ~-4

z laquo I I- 0 -6

l- I J u gt- ~-8

z w w -10

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9O

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SH

ALL

OW

TAR

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TLI

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STE

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TAR

GE

TLI

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gU

ND

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OO

TBO

UN

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CO

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26

28

30

32

34

RE

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03

-i- rtREQUIRED PITCH GIMBAL ANG LETO OBTAIN HOR-IZON AT 317

DEGREES IN wiiiiDOW

260

z~I- ~ i5 24000

1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

-I

-1-

NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

I LU HD~-

LUHD

lt0 120UJ0

~

80 HOLD PRESENT TRIMgt LU HD013

~Y~HOIgtlt

TOP OF WINDOWa 40to

31 7 SCRIBEaaI

80 TTOM OF WINDOWi= 0

0--ltoa

-40t-z

~~~Uw w u lt0 -80

HOLO PRESENT TRIlJCl

LOHU0 lt0

J gt -120 HOLD 059 TRIMlt0 z

LDHUlt0 FIELD OF VI S10 NLDHU LIFT-DOWNHEADS -UPLUHD LIFT-UP HEADS-DOWN

~~H~-160 q - P63 LIMITI- NOrE-VALIO ONLY FO~t~--

LUNAR RETURN VELOCITY

plusmnl8020 244middot 8 12 16

TIME TO 400K FT ALTITUDE-MIN

4

P37

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-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 57: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

HAW AOS(__=_) KEY VERB (freeze d~splay)

SIVB ATT HOLD 20 sec amp BEGIN VENTINGSIVB NNVR TO ORB RT (HDS DN) (3middot sec)

Record VI -c---HDOT _

HPAD _

KEY RLSEF 16 62

F 16 83

HAW LOS(__=-)

KEYmiddotRLSE~VXYZ (lfps)

Record ~VX---_

~vy

WZ--

AVC---_

TAPE RCDR - off (ctr)EMS MODE - STBYEMS FUNC - OFFSECS PYRO ARM (2) - SAFE

PRO

BURN STATUS REPORT

____--~TIG

BT------VGX____-R

-----P----_Y

REMARKS

_____VI

______--HDOT______--H______---AVC______---FUEL_______OXID

_______UNBAL

F 3708=00 OOEGOS AOS CMP TO LEB

(-=-=-)

0000

0003

0005

0014

0100

-55-

62 TLI 10 MIN ABORTSECS LOGIC (2) - on (up)SECS PYRO ARM (2) - ARM

TRANS CONTR - CGH (4 sec) amp +XDET RESET (verlfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS GMD-ON

TRANS GONTR - neutral then +X for10 sec

SIVBGPI s~ - GPIExcesslve rates 6V THRUST A - NORMAL SPS THRUST - DIRECT When rates damped 6V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

TRANS CONTR +X - OFFV37E OOE

PITGH UP to LOGAL VERT (+X axlSto~ard the earth)

RATE - LOWBMAG MODE (3) - ATTIRATE 2EDS PHR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SEGS ARM (2) - opencb EDS (3) - open

TRANS CONTR -X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (180deg)P (199deg)Y (0deg)

RETRO UPDATEGETI _

JV _VG

Jtb ---GET 400K _

05G _GET DROGUE _

ENTRY P _R _

Y_--

0945

-56-

ALIGN HORIZ ON RET +1 MKGMBL CHECK (T11lle Pentattlng)MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conflnn)cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FUMC - JV SETVHF RNGSET JV from chartE~S FUMC - JVEMS fODE - NOIDlAL

lV THRUST A - NORMALV37E 47E (THRUST fONITOR)

F 16 83 lVXYZ (1 fps)

0950

1000

NOTE For aborts durlng 1st mln of TLIKEY V82E F 16 44 (HaHpTff)Burn untll Hp lt 19NM

TRANS CONTR +X

THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN JV reqdJV THRUST (2) - OFFReport cutoff

cb SPS P2 Y2- closeGfBL MTRS (4) - OFF (LMP Confinn)TRANS CONT PWR - OFFTVC SERVO PWR (2) - OFFMN BUS TIE (2) - OFFcb SPS P1amp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREIf est time to EIltOl5500 omlt fCC andenter the SUPERCIRC CKLIST as early as pos-slb1e Pg ~2~3~ __If est time to EI)Ol5500 anticlpate afCC Enter the ENTRY PREP CKLIST at step 9pg 18

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

-2tl C

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z laquo I I- 0 -6

l- I J u gt- ~-8

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TAR

GE

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gU

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TBO

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26

28

30

32

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RE

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-i- rtREQUIRED PITCH GIMBAL ANG LETO OBTAIN HOR-IZON AT 317

DEGREES IN wiiiiDOW

260

z~I- ~ i5 24000

1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

-I

-1-

NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

I LU HD~-

LUHD

lt0 120UJ0

~

80 HOLD PRESENT TRIMgt LU HD013

~Y~HOIgtlt

TOP OF WINDOWa 40to

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80 TTOM OF WINDOWi= 0

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HOLO PRESENT TRIlJCl

LOHU0 lt0

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LDHUlt0 FIELD OF VI S10 NLDHU LIFT-DOWNHEADS -UPLUHD LIFT-UP HEADS-DOWN

~~H~-160 q - P63 LIMITI- NOrE-VALIO ONLY FO~t~--

LUNAR RETURN VELOCITY

plusmnl8020 244middot 8 12 16

TIME TO 400K FT ALTITUDE-MIN

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0030

0020

0010

000

II

II

II

II

S-IV

BBU

RNTI

ME

-M

INSE

Cll-

41)

120

200

241)

320

400

441)

520

TlI

-I0

MIN

ABOR

TlA

UNCH

-DE

C21

19

68

lAUN

CHA

ZIM

UTH

lllJ

72I ~ I

Z526

27~

~bull

DX

~IN

ERTI

ALVE

LOCI

TYAT

ABOR

T(5

-IVB

CU

TaF

l-

FTlS

EC

Ch

art

8

34l6

Xla

3

-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 58: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

0000

0003

0005

0014

0100

-55-

62 TLI 10 MIN ABORTSECS LOGIC (2) - on (up)SECS PYRO ARM (2) - ARM

TRANS CONTR - CGH (4 sec) amp +XDET RESET (verlfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS GMD-ON

TRANS GONTR - neutral then +X for10 sec

SIVBGPI s~ - GPIExcesslve rates 6V THRUST A - NORMAL SPS THRUST - DIRECT When rates damped 6V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

TRANS CONTR +X - OFFV37E OOE

PITGH UP to LOGAL VERT (+X axlSto~ard the earth)

RATE - LOWBMAG MODE (3) - ATTIRATE 2EDS PHR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SEGS ARM (2) - opencb EDS (3) - open

TRANS CONTR -X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (180deg)P (199deg)Y (0deg)

RETRO UPDATEGETI _

JV _VG

Jtb ---GET 400K _

05G _GET DROGUE _

ENTRY P _R _

Y_--

0945

-56-

ALIGN HORIZ ON RET +1 MKGMBL CHECK (T11lle Pentattlng)MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conflnn)cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FUMC - JV SETVHF RNGSET JV from chartE~S FUMC - JVEMS fODE - NOIDlAL

lV THRUST A - NORMALV37E 47E (THRUST fONITOR)

F 16 83 lVXYZ (1 fps)

0950

1000

NOTE For aborts durlng 1st mln of TLIKEY V82E F 16 44 (HaHpTff)Burn untll Hp lt 19NM

TRANS CONTR +X

THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN JV reqdJV THRUST (2) - OFFReport cutoff

cb SPS P2 Y2- closeGfBL MTRS (4) - OFF (LMP Confinn)TRANS CONT PWR - OFFTVC SERVO PWR (2) - OFFMN BUS TIE (2) - OFFcb SPS P1amp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREIf est time to EIltOl5500 omlt fCC andenter the SUPERCIRC CKLIST as early as pos-slb1e Pg ~2~3~ __If est time to EI)Ol5500 anticlpate afCC Enter the ENTRY PREP CKLIST at step 9pg 18

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

-2tl C

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DEGREES IN wiiiiDOW

260

z~I- ~ i5 24000

1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

-I

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NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

I LU HD~-

LUHD

lt0 120UJ0

~

80 HOLD PRESENT TRIMgt LU HD013

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TOP OF WINDOWa 40to

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80 TTOM OF WINDOWi= 0

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HOLO PRESENT TRIlJCl

LOHU0 lt0

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~~H~-160 q - P63 LIMITI- NOrE-VALIO ONLY FO~t~--

LUNAR RETURN VELOCITY

plusmnl8020 244middot 8 12 16

TIME TO 400K FT ALTITUDE-MIN

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120

200

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320

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-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 59: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

0945

-56-

ALIGN HORIZ ON RET +1 MKGMBL CHECK (T11lle Pentattlng)MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conflnn)cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FUMC - JV SETVHF RNGSET JV from chartE~S FUMC - JVEMS fODE - NOIDlAL

lV THRUST A - NORMALV37E 47E (THRUST fONITOR)

F 16 83 lVXYZ (1 fps)

0950

1000

NOTE For aborts durlng 1st mln of TLIKEY V82E F 16 44 (HaHpTff)Burn untll Hp lt 19NM

TRANS CONTR +X

THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN JV reqdJV THRUST (2) - OFFReport cutoff

cb SPS P2 Y2- closeGfBL MTRS (4) - OFF (LMP Confinn)TRANS CONT PWR - OFFTVC SERVO PWR (2) - OFFMN BUS TIE (2) - OFFcb SPS P1amp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREIf est time to EIltOl5500 omlt fCC andenter the SUPERCIRC CKLIST as early as pos-slb1e Pg ~2~3~ __If est time to EI)Ol5500 anticlpate afCC Enter the ENTRY PREP CKLIST at step 9pg 18

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

-2tl C

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DEGREES IN wiiiiDOW

260

z~I- ~ i5 24000

1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

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NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

I LU HD~-

LUHD

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~

80 HOLD PRESENT TRIMgt LU HD013

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TOP OF WINDOWa 40to

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80 TTOM OF WINDOWi= 0

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HOLO PRESENT TRIlJCl

LOHU0 lt0

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LDHUlt0 FIELD OF VI S10 NLDHU LIFT-DOWNHEADS -UPLUHD LIFT-UP HEADS-DOWN

~~H~-160 q - P63 LIMITI- NOrE-VALIO ONLY FO~t~--

LUNAR RETURN VELOCITY

plusmnl8020 244middot 8 12 16

TIME TO 400K FT ALTITUDE-MIN

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2627

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MIN

ABOR

TlA

UNCH

-DE

C21

19

68

lAUN

CHA

ZIM

UTH

lllJ

72I ~ I

Z526

27~

~bull

DX

~IN

ERTI

ALVE

LOCI

TYAT

ABOR

T(5

-IVB

CU

TaF

l-

FTlS

EC

Ch

art

8

34l6

Xla

3

-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 60: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

63TLI+25

0000

0003

0005

-57-

TLI 90 MIN ABORT PROCEDURESNormal CSMLV Separatlon- If declslon

to abort made before TLI+25 mlnabort at this time If abort declshysion occurs after separatlon startwith V37E OOE at 0014

SEGS LOGIC (2) - on (up)MSFN Confirm GO for PYRO ARMSECS PYRO ARM (2) - ARM

TRANS CONTR - CCW (4 sec) amp +XDET RESET (venfy)SIVBCSM SEPLV ENG 1 Lt - out

CSMLV SEP PB - PUSH RCS CMD-ON

TRANS CONTR - neutral then +X for 10 sec

SIVBGPI sw - GPIExcesslve rates ~V THRUST A - NORMAL SPS THRUST - DIRECTWhen rates damped ~V THRUST (2) - OFF SPS THRUST - NORMAL

cb MNA BAT C - closecb MNB BAT C - close

lt

0014

0100

TRANS CONTR +X - OFFV37E OOE

PITCH UP to LOCAL VERT (+X axistoward the earth)

RATE - LOWBMAG MODE (3) - ATT1RATE 2EDS PWR - OFFSECS PYRO ARM (2) - SAFESECS LOGIC (2) - OFFcb SECS ARM (2) - opencb EDS (3) - open

TRANS CONTR +X (8 to 10 sec)

RATE - HIGH

MNVR TO RETRO ATTR (Block Data)P (Block Data)Y (Block Data)

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

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-i- rtREQUIRED PITCH GIMBAL ANG LETO OBTAIN HOR-IZON AT 317

DEGREES IN wiiiiDOW

260

z~I- ~ i5 24000

1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

-I

-1-

NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

I LU HD~-

LUHD

lt0 120UJ0

~

80 HOLD PRESENT TRIMgt LU HD013

~Y~HOIgtlt

TOP OF WINDOWa 40to

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80 TTOM OF WINDOWi= 0

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HOLO PRESENT TRIlJCl

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~~H~-160 q - P63 LIMITI- NOrE-VALIO ONLY FO~t~--

LUNAR RETURN VELOCITY

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TIME TO 400K FT ALTITUDE-MIN

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-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 61: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

-58-

RETRO UPDATE (NO COMM - use Block Data)GET 05G _

tN __VC

ntb -shyGET 400K __

GET DROGUE _ENTRY P _

R _

Y_--

XXXX

5945

Set DET count~ng up to GETIALIGN HORIZ ON RET +1 0 MKGMBL CHECK (T~me Penutt~ng)

MN BUS TIE (2) - ONGMBL MTRS (4) - ON (LMP Conf~rm)

cb SPS P2Y2 - openRATE - LOWEMS MODE - STBYEMS FlINC - nV SETVHF RNGSET nV from chartEMS FUNC - nVEMS MODE - NORMALTAPE RCDR - CMD RESETHBRRCDFHD

llV THRUST A - NORMALV37E 47E (THRUST MONITOR)

F 16 83 nVXYZ (1 fps)

5959 THRUST ON PB - PUSHTRANS CONTR +X - OFFBURN IW req dnV THRUST (2) - OFFReport cutoff

cb SPS P2Y2 - closeGMBL MTRS (4) - OFF (LMP Confirm)TRANS CONT PWR - OFFTVC SERVO PlfR (2) - OFFMN BUS TIE (2) - OFFcb SPS Plamp2 Ylamp2 - open

F 37 OOE

Go to ENTRY PREP amp SUPERCIRC ENTRY PROCEDUREStep 9 pg _ 1-1__

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

-2tl C

l I W gt- ~-4

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l- I J u gt- ~-8

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ALL

OW

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TAR

GE

TLI

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gU

ND

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OO

TBO

UN

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26

28

30

32

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03

-i- rtREQUIRED PITCH GIMBAL ANG LETO OBTAIN HOR-IZON AT 317

DEGREES IN wiiiiDOW

260

z~I- ~ i5 24000

1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

-I

-1-

NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

I LU HD~-

LUHD

lt0 120UJ0

~

80 HOLD PRESENT TRIMgt LU HD013

~Y~HOIgtlt

TOP OF WINDOWa 40to

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80 TTOM OF WINDOWi= 0

0--ltoa

-40t-z

~~~Uw w u lt0 -80

HOLO PRESENT TRIlJCl

LOHU0 lt0

J gt -120 HOLD 059 TRIMlt0 z

LDHUlt0 FIELD OF VI S10 NLDHU LIFT-DOWNHEADS -UPLUHD LIFT-UP HEADS-DOWN

~~H~-160 q - P63 LIMITI- NOrE-VALIO ONLY FO~t~--

LUNAR RETURN VELOCITY

plusmnl8020 244middot 8 12 16

TIME TO 400K FT ALTITUDE-MIN

4

P37

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120

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320

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-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 62: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

-59-

70 ENTRY PADS

Data PADS are used by the crew to record voice callups from them~ss~on control center The PAD formats are a funct~on of the datatransm~tted and the form the fl~ght crew finds to be effic~ent ~n

perform~ng the~ tasks after extens~ve tra~n~ng The PADS presented~n th~s sect~on are ~ncluded as examples and tra~n1ng a~ds

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

-2tl C

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DEGREES IN wiiiiDOW

260

z~I- ~ i5 24000

1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

-I

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NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

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~~H~-160 q - P63 LIMITI- NOrE-VALIO ONLY FO~t~--

LUNAR RETURN VELOCITY

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TIME TO 400K FT ALTITUDE-MIN

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-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 63: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

-60-

P27 UPDATE

PURP

GET

v V

bull bull bullbullbullbull bullbull

V

bull bullbull bull304 0 I IN~EX IN~~~ IN ~~I I

I - 02 -1 i I I J I I03 _ -_I --~~-1---t ------Ir---t--l

~ ----t---r----r+H 1-1 1 ~- -m----l---C-i--- L-06 -----I------~ -~L~----+-- I 4-~~ --+-j-l--- -- --1- -I r-- -~--+--~I

- --rr-I- -+ -1 rl i ---+--+-H--I I I i I I I -l~_1 I-~--~---- ~ltfF- l-j---4-1I4 _1 --11 I TI -----------+_I15 I I I I

I I I I I~ -]=I~t-t--~m 1-l~I-+-ir-l20_ ~I--I r-T-~_L 1--1--~-l-r I I2 I --i--Llte-Jti+ i i22 -1 I L _~_I_- i I ~23 i i i I I I I I I i-1 I I --- I-- -j_1_~- -t--- r--I---+-24 I I I I I I

N34 HRS ~ IX i xl-i---i X ix X i I L~MIN ~lampX X XJX IX IX

NAV CHECK SEC X Xi 1 X xii-

N43 LAT 0 I U ~ I ILONG --- Ill IALT + or r i T--+-+-+--o+-+-I--+-+l-f

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

-2tl C

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DEGREES IN wiiiiDOW

260

z~I- ~ i5 24000

1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

-I

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NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

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LUNAR RETURN VELOCITY

plusmnl8020 244middot 8 12 16

TIME TO 400K FT ALTITUDE-MIN

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-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 64: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

-61-

-MANEUVER

- - IX

PURPOSE gt

SET STARS PROPGUIDz

+ WT N47 E

R ALIGN 0 0 PTRIM N48--- - bullP ALIGN 0 0 - YTRIM- --Y ALIGN - + 0 0 HRS GETI- --

+ 0 0 0 MIN N33

+ 0 SEC

ULLAGE I--tNX N81bull

I-- bull tNy

- tNz

X X X RX X X PX X X Y

+ HA N44

I bullHp

- + tNTbullX X X bull BTHORIZONWINDOW bullX - INC

X X X X SXTS

+ 0 SFTbull

+ 0 0 TRN

X X X BSS

X XI SPAbullX X X I SXP

OTHER 0 LAT N61- bull- LONG

+ RTGO EMSbull+ VIO

I bull bull GET 05G- - bull bull

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

-2tl C

l I W gt- ~-4

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NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

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TIME TO 400K FT ALTITUDE-MIN

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-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 65: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

-62-

ENTRY

AREA

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

bull bull bull bull GET HORbull bull ~ bull bullI--X X X X X X P CK

0 0 LAT N61I--- bull - bull

LONGgt-

X X X X X X MAX Gc _ middot bull~z + + V400K N60w

- 0 0 - o 0 bull T4 00Kbull+ + bull RTGO EMSbull+ + VIO

bull bull bull bull RRTbull bull bull bullX X bull X X bull RET 05G-bull bull+ 0 0 + 0 0 DL MAXbull - bull

DL M 1NJ469+ 0 0 + 0 0bull bull+ + VL MAX

+ + VL MIN

X X X X X X DObull bullX X bull XX bull RET VCIRCbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDRObull bullX X X X X X X X SXTS

+ 0 + 0 SFTbull bull+ 0 0 + 0 0 TRN

X X X X X X BSS

X xl X XI SPAbull bullX X X I X X X I bull SXP

X X X X X X X X LIFT VECTOR

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

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NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

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TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

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-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 66: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

-63-

EARTH ORBIT ENTRY UPDATEX - X - AREA

X X - X X - - A V TO

X X X X X X R 05G

X X X X X X P 05G

X X X X X X Y 05G

+ + RTGO EMSbull bull

+ + VIO

X X bull X X bull RET 05Gbull bull0 0 LAT N61

- bull - bullLONG

X X bull nX bull RET 02G

lbull bull

- ORE (55deg) N66

R R R R BANK AN

X X bull X X bull RET RBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bullX X bull X X bull RETDROGbull bullX X X X

~n(90 0 fps) CHART

xD--

X X ORE (90deg) uPDATE

POST BURN

X X X X X X R 05G

+ + RTGO EMSbull bull+ + VIO

X X bull X X bull RET 05Gbull bullX X bull X X bull RET o 2Gbull bull1 - n ORE t lOOnm N66

R R R R BANK AN

X X bull X X bull RETRBbull bullX X bull X X bull RETBBObull bullX X bull X X bull RETEBObull bull bull bull RETDROG f~3~fnX X bull X )( bull

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

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DEGREES IN wiiiiDOW

260

z~I- ~ i5 24000

1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

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NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

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TOP OF WINDOWa 40to

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LUNAR RETURN VELOCITY

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TIME TO 400K FT ALTITUDE-MIN

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-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 67: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

-64-

3deg ENTRY CHARTS AND TLI CHARTS

Crew charts prov~de addltional onboard capab21~ty for mon2tor~ng

m2SS20n events and supply 2nformation to perform spec~f2c funct20ns2f commun~cat20nw2th MSFN have failed Presented ~n th2s sect20nare s~x onboard crew charts appl~cable to the reentry phase of theApollo 8 m2SS20n as presented 2n reference 9 and two TLI abort chartsas presented ~n reference 7

The f~rst chart presents the reentry corr~dor dynam~c 1~m2t l~nes andreference 12nes as a funct~on of reentry veloc2ty (VEl) and f12ghtshypath angle (YEI ) at 400000 ft alt2tude The purpose of th2s chart2S to lnsure for the no commun2cat20n case that a proper VEl - ~EI

comb2natlon w211 be atta2ned at reentry interface

The dynamlc 12mlt llnes the constant g overshoot and 12 g undershyshoot boundar2es are based on aerodynamic and reentry condltlonswhlch result In the most restr2ct2ve corr2dor Three reference12nes are also lncluded on the chart and they are the 11ft vectoror~entatlon (LVO) llne the shallow target 12ne and the steep target12ne The 11ft vector orlentat2on llne and the steep target llneare both stored In the onboard computer and are ut212zed 2n programs63 and 37 respectlvely For a reentry veloclty and fllght-pathangle located above the LVO llne the onboard computer will commanda lift vector down roll att2tude at 005 g and wlll ma2ntain thatatt2tude to about 1 3 g Below the LVO 12ne the computer wlllcommand a 11ft vector up att2tude to approxlmately 13 g

If program 37 2S used ln conJunct2on w2th return-to-earth target2ngor m2dcourse correct20ns the program wlll target automat2cally tothe steep target 12ne unless the f12ght-path angle overr2de opt2on2S des2red If the fllght-path angle overr2de opt20n 2S used thedes2red f12ght-path angle at 400000 ft alt2tude (reentry 2nterface)2S 2nput lnto the CMC w2th the CMC determ2n2ng the result2ng reentryveloclty It 2S recommended that the steep target 12ne be used forall onboard return-to-earth target2ng and m2dcourse correct2onsThls steep target 12ne w211 also be used for M2ss10n Control Center(MCC) targetlng for reentry veloc2tles greater than 31000 ftsecFor reentry velocltles below 31000 fps the MCC wlll utl12ze theshallow target 12ne In order to lncrease the maneuver capabl12ty ofthe spacecraft

The second chart dep2cts the CMC commanded constant drag value DOas a funct20n of reentry veloc2ty at 400000 ft alt2tude Durlngthe reentry program 64 the guidance logic lS generat2ng roll commandswh2ch will attempt to drlve the spacecraft to the commanded constantaerodynam2c drag value DO During thlS program (164) the EMS V-gtrace and the 2ndependent G meter wlll be mon2tored to lnsure thatthe spacecrafts actual drag level lS converglng to DO If the

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

-2tl C

l I W gt- ~-4

z laquo I I- 0 -6

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-12 24

26

28

30

32

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03

-i- rtREQUIRED PITCH GIMBAL ANG LETO OBTAIN HOR-IZON AT 317

DEGREES IN wiiiiDOW

260

z~I- ~ i5 24000

1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

-I

-1-

NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

I LU HD~-

LUHD

lt0 120UJ0

~

80 HOLD PRESENT TRIMgt LU HD013

~Y~HOIgtlt

TOP OF WINDOWa 40to

31 7 SCRIBEaaI

80 TTOM OF WINDOWi= 0

0--ltoa

-40t-z

~~~Uw w u lt0 -80

HOLO PRESENT TRIlJCl

LOHU0 lt0

J gt -120 HOLD 059 TRIMlt0 z

LDHUlt0 FIELD OF VI S10 NLDHU LIFT-DOWNHEADS -UPLUHD LIFT-UP HEADS-DOWN

~~H~-160 q - P63 LIMITI- NOrE-VALIO ONLY FO~t~--

LUNAR RETURN VELOCITY

plusmnl8020 244middot 8 12 16

TIME TO 400K FT ALTITUDE-MIN

4

P37

LONG

ITUD

ECO

RREC

TION

TOOB

TAIN

1350

NM

ENTR

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344

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352

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364

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CMC

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AT40

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TITU

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Ch

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5

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20 100 -40

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t~I

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0A

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NO

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30

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---------O

VE

RB

UR

N---------I------U

ND

ER

BU

RN

------I

~30

-20

-tD

010

20

AA

VX

FTS

EC

-60

Ch

art

6

1000

0 90

00 70

00 60

00 i50

00 iMl

OO ilOO

O i20

00 10

00 o

040

120

200

EMS

6V-

FTS

EC

240

320

400

440

520

S-IV

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RN-

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105

0

I 1- I

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LAUN

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+rmr)lfl~

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BAL

ANGL

E

ROLL

=IS

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TCH

=199

YAW

0

TLI

-10

MIN

ABO

RTLA

UNCH

DEC

21

1968

400050

z =gt co23

0on 3

~7 X ampJ V

gt ~ 6

2627

~B

~n

_n

INER

TIAL

VELO

CITY

ATAB

ORT

IS-IV

BC

UTO

FF)middot

FTIS

EC34

3536

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art

7

7

1000

0i

0-00

EMS

V-F

TSE

C90

0080

0070

0060

0050

0040

0030

0020

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000

II

II

II

II

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BBU

RNTI

ME

-M

INSE

Cll-

41)

120

200

241)

320

400

441)

520

TlI

-I0

MIN

ABOR

TlA

UNCH

-DE

C21

19

68

lAUN

CHA

ZIM

UTH

lllJ

72I ~ I

Z526

27~

~bull

DX

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8

34l6

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3

-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 68: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

-65-

computer lS not generatlng the rlght roll commands during thlSperlod a manual takeover lS executed and the backup mode flownFor the lunar reentry return veloclty DO lS about 4 gs

The thlrd chart presents the pltch glmbal angle necessary to acqulrethe horlzon at the 31 7 degree mark ln the commanders rendezvousand docklng wlndown ThlS chart was generated assUffilng that the 005g predlcted trlm pltch glmbal angle was 1522 degrees consequentlylt lS dependent on the glven traJectory and vehlcle parameters fromWhlCh lt was obtalned However the chart lS relatlvely lnsensitlveto both the traJectory and vehlcle parameters and could be used wltha one to two degree accuracy throughout the reentry corrldor for thelunar return velocltles Should the pltch trlm glmbal angle at 005g change durlng the mlsslon real tlme update of this chart can beaccompllshed by blaslng the chart by the dlfference between the nomshylnal and updated 05 g trlm angle AlSo the pltch angle necessaryto get the horlzon at the 31 7 degree mark at 17 mlnutes prlor toEI wlll be v01ceu to the crew and can be used as a second data pOlntto update thlS chart

The fourth chart can be used to determlne the requlred magnltude ofpltch from some glven reference to locate the horlzon at a prescrlbedelevatlon on the commanders rendezvous and docklng wlndow le atthe 31 7 degree mark Included are data for two dlfferent modes ofapproachlng entry lnterface (400000 feet altltude) each mode belnglllustrated for a 11ft vector up and a 11ft vector down eM attltudeThe two modes are brlefly deflned as follows (1) malntaln thelnertlal attitude necessary to achieve aerodynamlc trlm conditlonsat the predlcted tlme the spacecraft wlll experlence a load factorof 005 g or (2) contlnually maneuver the CM to cause lt to betrlmmed to ltS present posltion vector at all tlmes assUffilng thatthe atmosphere eXlsted beyond entry lnterface (thlS is what lS doneby the CMC) Wlth elther mode belng chosen the requlred pltch toobtaln the hOrlzon at some locatlon in the wlndow lS shown for anytlme up to twenty mlnutes prlor to entry lnterface ThlS can bedone by subtractlng the deslred horlzon posltlon 1n the w1ndow fromthe pltch angle from chart 4 For example lf the CM lS ln a liftup 005 g trlm attltude (top SOlld llne) and the horlzon lS deslredto be at the 317 degree mark in the wlndow 12 mlnutes before entrylnterface subtract 317 degrees from the value of cent from the chartapproxlmately 943 degrees The range of usable angles lS shown onthe chart by the cross hatched area representlng the fleld of Vlewfor an 80th percentlle pllot

The two sets of dashed llnes lndlcate the attltude reglon wlthlnWhlCh the angle of attack wlll be not greater than 45 degrees forelther 11ft up (top set) or 11ft down (bottom set) ThlS lS slgnlshyflcant Slnce the crew could llkely see a sharp Jump of the roll and

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

-2tl C

l I W gt- ~-4

z laquo I I- 0 -6

l- I J u gt- ~-8

z w w -10

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OW

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TRY

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26

28

30

32

34

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TRY

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LOC

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1-F

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1

36

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2829

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J23

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J63

73

8X

03

-i- rtREQUIRED PITCH GIMBAL ANG LETO OBTAIN HOR-IZON AT 317

DEGREES IN wiiiiDOW

260

z~I- ~ i5 24000

1-0shyo 220 tl-- 0lii -- 200Ishym~z-0xiuli ~ 180

-70-

~ I

-I

-1-

NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

I LU HD~-

LUHD

lt0 120UJ0

~

80 HOLD PRESENT TRIMgt LU HD013

~Y~HOIgtlt

TOP OF WINDOWa 40to

31 7 SCRIBEaaI

80 TTOM OF WINDOWi= 0

0--ltoa

-40t-z

~~~Uw w u lt0 -80

HOLO PRESENT TRIlJCl

LOHU0 lt0

J gt -120 HOLD 059 TRIMlt0 z

LDHUlt0 FIELD OF VI S10 NLDHU LIFT-DOWNHEADS -UPLUHD LIFT-UP HEADS-DOWN

~~H~-160 q - P63 LIMITI- NOrE-VALIO ONLY FO~t~--

LUNAR RETURN VELOCITY

plusmnl8020 244middot 8 12 16

TIME TO 400K FT ALTITUDE-MIN

4

P37

LONG

ITUD

ECO

RREC

TION

TOOB

TAIN

1350

NM

ENTR

YRA

NGE

Ugt

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0

2I

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cgt

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340

344

348

352

356

364

368

x10

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TIAL

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Ch

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5

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20 100 -40

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=----

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t~I

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-04

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40

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30

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------I

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-20

-tD

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AA

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FTS

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-60

Ch

art

6

1000

0 90

00 70

00 60

00 i50

00 iMl

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040

120

200

EMS

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240

320

400

440

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=IS

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=199

YAW

0

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ABO

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DEC

21

1968

400050

z =gt co23

0on 3

~7 X ampJ V

gt ~ 6

2627

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~n

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INER

TIAL

VELO

CITY

ATAB

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IS-IV

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FF)middot

FTIS

EC34

3536

Xllf

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art

7

7

1000

0i

0-00

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0080

0070

0060

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0030

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000

II

II

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INSE

Cll-

41)

120

200

241)

320

400

441)

520

TlI

-I0

MIN

ABOR

TlA

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-DE

C21

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68

lAUN

CHA

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lllJ

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-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 69: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

-66-

yaw error needles on the FDAI Jf the entry DAP were actJve and theang~e of attack Jncreased to a va~ue greater than 45 degrees AsthJs occurs the DAP converts from a O~ second samp~Jng DAP to atwo second predJctJve DAP and Jnterchanges the yaw and roll errorsJgnals on the FDAI

If onboard return-to-earth targetJng JS requJred the target long~shy

tude and latJtude obtaJned from program 37 w~ll need to be correctedto obtaJn the nomJnal 1350 n mJ reentry range The fifth chartshows the ~olg~tude correctJon (the sol~d ~Jne) whJch JS to be addedor sUbtracted depen~ng on whether the target ~ongJtude from theDSKY JS west (minus sign) or east (plus sJgn) a~ a functlon oflnert1al veloc1ty at 400000 ft alt1tude The dashed 11nes on thechart depJct the longitude correctJons to be used for the fast andslow lunar return traJectories

CorrespondJng to the 10ngJtude correctJon a lat1tude correct10nmust also be made The ~at1tude correctJon JS determ1ned by cal~Jng

up program 2l and Jnputing varJous m1SSlon e~apsed times The outputfrom thJs program is then used to plot a ground track A lat1tudecorrectJon can then be determlned for the correspondlng change 1n~ongJtude This ~atJtude correctJon may then be used to modJfy thetarget ~atJtude obtaJned from F37

The slXth chart is to be used as a backup chart Jn the case of anearth orb1t a~ternate mission The chart shows two curves Wh1Chare (1) backup bank angle (BM) versus burn error 1n the X-duecshyt10n (~~VX) (2) downrange error at 2 g (P67) versus backup bankang~e An equation JS shown on the chart to correct the backupbank ang~e for burn errors In the Z-dlrectlon In order to obta1nthe correct burn res1duals (errors) from the DSKY the SiC must be~n the retro-fJre attJtude The nomJnal retro elapsed t~me to reshyVerse the bank ang~e (RETRB) J8 noted on the chart and J8 to becorrected by ~ RETRB shown on the rlght scale 1f burn errors are1ncurred The Use of thls chart can be best shown by an exampleSuppose a deorbJt maneuver was performed and burn errors resultedIn

~~VX ~ + 100 fps

~6VZ ~ 70 fps

From the BM curve the backup bank angle for a ~6Vx of + 100 fps1S about 660 bull The backup bank angle correctlOn (~BM) for theZ-ax1S error JS (-040) (_70)0 or +280 The total backup bankangle (BRAT) JS then BEA + aoBM or 6880 bull For a BEAT of 688deg theexpected downrange error display on the DSKY at 0 2 g JS about shy150 n ffiL US1ng th1S BMT a LlRETRB of about +14 sec lS obtaJnedThJs value JS then added to the nomJnal RETRB of 22 mJn whJch

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

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41)

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200

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-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 70: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

-67-

results In a corrected RETRB of 22 mln 14 sec Thls crew chartwlll be updated Vla VOlce 1 to 3 hours prlor to all earth orbltreentrles to compensate for deviatlons from the nOffilnal end ofmlssion orbltal elements The data pOlnts to update these twocurves wlll be voiced up and recorded on the earth orblt entrypad message shown In sectlon 70

Charts 7 and 8 are onboard crew charts necessary to perform a10 ffilnute abort from TLI These charts provlde the SPS burnattltude SPS ~V requlrement and tlffieuro to entry lnterface asfunctlons of the lnertlal veloclty at S-IVB cutoff Charts foraborts after nOffilnal TLI durlng the translunar coast phase areunnecessary Slnce block data wlll be relayed to the crew forthese cases whlle the crew lS stlll In earth parking orblt

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~ I

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NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

I LU HD~-

LUHD

lt0 120UJ0

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plusmnl8020 244middot 8 12 16

TIME TO 400K FT ALTITUDE-MIN

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-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 71: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

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~ I

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NOTE VALID ONLY FOR LUNARRETURN VELOCITYBASED ON PITCH TRIM GIMBAL ANGLE A1 0 05 g OF 15 bull

160 bull

+

140o 4 a 12 16

TIME TO 400K FT ALTITUDE-MIN

20 24

-71-

160HO LD 059 TRIM I) ~~ i _L

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lt0 120UJ0

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80 HOLD PRESENT TRIMgt LU HD013

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LDHUlt0 FIELD OF VI S10 NLDHU LIFT-DOWNHEADS -UPLUHD LIFT-UP HEADS-DOWN

~~H~-160 q - P63 LIMITI- NOrE-VALIO ONLY FO~t~--

LUNAR RETURN VELOCITY

plusmnl8020 244middot 8 12 16

TIME TO 400K FT ALTITUDE-MIN

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-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 72: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

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-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 73: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

-i- rtREQUIRED PITCH GIMBAL ANG LETO OBTAIN HOR-IZON AT 317

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-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 74: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

-71-

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-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 75: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

4

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-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

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90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 77: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

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-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 78: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

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-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969

Page 79: NATIONAL AERONAUTICS AND SPACE ......At 45 m~nutes before EI the CMC update program P27 can be selected to permit update of the landing po~nt locat~onand the state vector. The entry

-76-

90 REFERENCES

1 Apollo M~ss~on Techn~ques M~ss~ons F amp G TransearthInJect~on M~dcourse Correct~ons and Entry MSCInternal Note S-PA-9T-040 dated February 24 1969

2 Apollo Entry Summary Document ~ss~on F Prel~m~nary

Copy MSC Internal Note MSC-CF-P-69-1 dated January20 1969

3 M~ss~on F Fl~ght Plan Prel~m~nary Copy dated March12 1969

4 Apollo Operat~ons Handbook Command and Serv~ce

Modules Volume II Operat~onal Procedures Block IIdated February 20 1969

5 Apollo M~ss~on Techmques Earth Parkwg Orb~t Retroshyf~re and Entry Procedures (M~ss~ons C Pr2me D Fand G) MSC Internal Note s-PA-8M-035 dated December16 1968

6 Apollo Abort Summary Document M~ss~on F MSC InternalNote Msc-p-69-4 dated February 3 1969

7 Apollo M~ss~on Techn~ques M~ss~ons F amp G Cont2ngencyProcedures Draft copy MSC Internal Note S-PA-9T-043dated March 3 1969

8 Operational Abort Plan for the Apollo 8 M~ss~on MSCInternal Note 68-FM-209 dated November 26 1968

9 Un2ted States Government Memorandum Apollo 8 ReentryCrew Charts 68-FM23-216 dated December 12 1968

10 Reentry Crew Br~ef~ng Handout F M~Ss2on Lunar Returnheld February 24 1969