Download - Post Launch Report for Apollo Mission A-101 (BP-13)

8/6/2019 Post Launch Report for Apollo Mission A-101 (BP-13)

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MSC-R-A-64-2

r,',.: !-k-' -L *J

NATIONAL AERONAUTICS AND SPACE ADMINISTRATIONMANNED SPACECRAFT CENTER

HOUSTON, TEXASJune 18, 1964


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POSTLAUNCH REPORT FORAPOLLO MISSION A-101

( B P - l j )

Approved for Distribution:. /\ / I /Manager, 4pol ldSpacec ra f t Program Office

NATIONAL AERONAUTICS A,.!.! SPACE ADMINIS7RATIONMANNED SPACECRAFT CEN'IER

HOUSTON, TEXASJUNE 18, 1964


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CONTENTSSection

FRONTISPIECE . . . . . . . . . . . . . . . . . . . . . . iABBREVIATIONS AND SYMBOL3 . . . . . . . . . . . . . . . . VT A B U S . . . . . . . . . . . . . . . . . . . . . . . . . viiiFIGUR E3 . . . . . . . . . . . . . . . . . . . . . . . . . ix

1.0 SUMMARY . . . . . . . . . . . . . . . . . . . . . . . . . 1-12.0 INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . 2-13.0 FLIGHT TRAJECTORY . . . . . . . . . . . . . . . . . . . . 3-14.0 SPACECFUUT DESCRIPTION AND PERFORMANCE . . . . . . . . . 4-1

4.1 Spacecraft Description . . . . . . . . . . . . . . . 4-14.2 Instrumentation . . . . . . . . . . . . . . . . . . . 4-134.3 Communications . . . . . . . . . . . . . . . . . . . 4-344.4 Electrical and Sequential . . . . . . . . . . . . . . 4-394.5 Propulsion and Pyrotechnics . . . . . . . . . . . . . 4-444.6 Structures . . . . . . . . . . . . . . . . . . . . . 4-504.7 Heat Protection . . . . . . . . . . . . . . . . . . . 4-1114.8 Aerothermdynwics . . . . . . . . . . . . . . . . . k-U44.9 Equipment Cooling . . . . . . . . . . . . . . . . . 4-194.10 Acoustics . . . . . . . . . . . . . . . . . . . . . . 4-143

5.0 LAUNCH VMICLE DESCRIPTION AND PERFORMANCE . . . . . . . 5-16.0 MISSION OPERATIONS . . . . . . . . . . . . . . . . . . . 6-1

6.1 Prelaunch Operations . . . . . . . . . . . . . . . . 6-16.2 launch Operations . . . . . . . . . . . . . . . . . 6-15


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iv

Section Page6.3 Range O p e r a t i o n s . . . . . . . . . . . . . . . . . . 6-206.4 Data C o v e r a g e and Avai l a b i l i t y . . . . . . . . . . . 6-24. . . . . . . . . . . . . . . . . . . 7-1

8.0 REFEIiENCES. : . . . . . . . . . . . . . . . . . . . . . . 8-17.0 CONCLUD ING REMARKS


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Figure4.1-5

PageCommand module interior equipment layout for BP-13spacecraft (view through hatch). . . . . . , . . . . 4-9Command module interior equipment layout (view toright of hatch) , . . . . . . . . . . . . . . . . ..1-6 4-10

4-11.1-74.1-8

Command module exterior of BP-13 spacecraft . . . . .Cutaway view of BP-13 spacecraft service module,insert, and adapter . . . . , . . . . . . . . . . . . 4-12Instrumentation and communications subsystems on

BP-13 spacecraft . . . . . . . . . . . . . . . . ..2-1

4-274.2-2 Locations of vibration, acoustic, and accelerationtransducers f o r BP-13 spacecraft . . . . . . . . . 4-28

4-29.2-34.2-4

Strain gage locations on BP-13 spacecraft . . . . . . .Fluctuating pressure transducer locations on BP-13spacecraft . . . . . . . . . . . . . . . . . . . . 4-30

4.2-5 Static pressure locations in the command module onBP-13 spacecraft . . . . . . . . . . . . . . . . . 4-514-32eat-flux calorimeter locations on BP-13 Spacecraft. ..2-64.2-7 Launch-escape tower temperature transducer locationson BP-13 spacecraft . . . . . . . . . . . . . . . . 4-34

4.3-1 Location of telemetry transmitters and C-band trans-ponders on BP-13 spacecraft . . . . . . . . . . . . 4-37Location of telemetry omniantenna on command moduleof BP-13 spacecraft . . . . . . . . . . . . . . . ..3-2 4-38

4-41lectrical power subsystem for BP-13 spacecraft . . ..4-14.4-2 Electrical power subsystem components for BP-13spacecraft . . . . . . . . . . . . . . . . . . . . 4-424.4-3 Launch escape sequencer subsystem for BP-13spacecraft . . . . . . . . . . . . . . . . . . . . 143


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Figure

xi

Page4.5-14.5-24.5-34.5-44 .6-14.6-2

4.6-34.6-44.6-54.6-6

4.6-7

Bonding electrical w i r e harness t o LES motor casef o r BP-13 spacec raf t . . . . . . . . . . . . . . . 4-46

BP-13 spa cec raft launch escape tower je tt i so n motor . 4-47BP-13 s p c e c r a f t LES je t t is on motor ign i t ionlocat ions . . . . . . . . . . . . . . . . . . . . . 4- 48BP-13 s p c e c r a f t launch escape t o w e r separations y s t e m . . . . . . . . . . . . . . . . . . . . . . . 4-49Apollo BP-13 sp ac ec ra ft launch escape subsystems t ruc tu re . . . . . . . . . . . . . . . . . . . . . 4-62Detail of command module-service module interface(BP-13 spacecraft ) . . . . . . . . . . . . . . . . 4-63Rawinsonde atmospheric wind data a t Cape Kennedy,Fla. , May 28, 1964 . . . . . . . . . . . . . . . . . 4-64Comparison of predicted aq and Q-ball aq .(Apollom i s s i o n A-101) . . . . . . . . . . . . . . . . . . . 4-65Variation of angle of at tack with alt it ud e (Apollomission A-101) . . . . . . . . . . . . . . . . . . . 4-66S t a t i c pressu re f l i g h t measurement on BP-13 spacecraftcompared w i t h wind-tunnel measurements onmodel PSTL-1 (ref. 1)(a) @ = o 0 4-67(b) # = % " . . . . . . . . . . . . . . . . . . . . . 4-68( c ) #=180 4-69

. . . . . . . . . . . . . . . . . . . . .. . . . . . . . . . . . . . . . . . . .

S t a t i c pre ssu re co ef fi ci en t over t he command moduleconical surface (EP-13 spacecraft )( a ) Angular location, approximately 9" . . . . . 4-70(b) Angular loc ati on , 1800 . . . . . . . . . . . . . 4-71(c ) Angular locatio n, 357" . . . . . . . . . . . . . 4-72


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x i v

Pageigure4.6-24 Fluc tua t ing pressure t rends for c i rcumferen t i a llocat ions on BP-13 spacecraft service module a tXA974

( a ) M = 0.80 and M = 0.85 . . . . . . . . . . . . . .(b) M = 0 . 9 and M = 0.95 . . . . . . . . . . . . . .( c ) M = 1.00 and M = 1.50 . . . . . . . . . . . . . .(d) M = 2.00 and M = 2.50 . . . . . . . . . . . . . .

4.6-25 Spectrogram of BP-13 spac ecra ft ser vice module f l uc tu-Ia t i n g pressures (- o c t a v e b an d a n a l y s i s ) . . . . . .3Command module heat pro tec t ion f o r BP-13 spacecraf t . . 4-1104-112.7-1

4.7-2 Bond-line U S ower temperatures measured duringf l i g h t (BP-13 spacec ra f t ) . . . . . . . . . . . . .Top view of BP-13 spacecraft command module showingca l o r i m et e r l oc a t i ons . . . . . . . . . . . . . . .

4-1134.8-1 4-1194.8-2 Development view of BP-13 spac ecra ft serv ice module,

i n s e r t , and adap te r cmpartme nt showing calor ime terl oca t ons . . . . . . . . . . . . . . . . . . . . . 4-1204.8-3 Launch con fi gu ra tio n environment i n terms of Machnumber (M ) and Reynolds number (ReD) f o r BP-13

spacec ra f t . . . . . . . . . . . . . . . . . . . . 4-1214.8-4 Heating r a t es measured on BP-13 spacecraft commandmodule during f l i g h t

4-1224-1234-1244-125

(a ) Calorimeters 1, 5 , and 10 . . . . . . . . . . . .( b ) Calorimeters 2, 4 , and 11 . . . . . . . . . . . .(c) Calorimeters 3, 9, and 12 . . . . . . . . . . . .(d) Calorimeters 6, 7, and 8 . . . . . . . . . . . .

4.8-5 Comparison of heating re te h i s t o r i e s a t Xc = 74 for4-126pacecraft .


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xv

Paseigure4.8-6

4.8-7

4.8-8

4.8-94.8-104.8-114.8-124.9-14.9-2

4.9-3

4.9-45.0-1

6.1-1

6 e l - 2

Comparison of h e a ti n g r a t e h i s t o r i e s a t Xc = 52 Ifor s ix c i r cumferen ti a l l oca t ions o n BP-13spacecraf t . . . . . . . . . . . . . . . . . . . . . 4-127

Comparison of heat ing r a t e h i s t o r i e s a t X = 27Cfo r two c i rcum ferent ia l loca t ions on BP-13spacecraf t . . . . . . . . . . . . . . . . . . . . . 4-128Comparison of hea t ing r a te h is to r i es a t 9 = 180". o rth ree long i tud ina l loca t ions on BP-13spacecraf t . . . . . . . . . . . . . . . . . . . . 4-129Comparison of heat ing rate h i s t o r i e s a t $ = 319" f o rth ree long i tud ina l loca t ions on BP-13 spacecra f t . . 4-130Comparison of h e at in g r a t e h i s t o r i e s a t = 5' f o rth ree long i tud ina l loca t ions on B P - l 3 spacecra f t . . 4-131Heating rates measured on the BP-13 spacecra f t se rv icemodule during f l i g h t . . . . . . . . . . . . . . . . 4-132Heating rates measured on th e BP-13 spacecra f t adap te rd u r i n g f l i g h t . . . . . . . . . . . . . . . . . . . 4-133Environmental cont ro l subsystem schematic f o r

BP-13 spacecraf t . . . . . . . . . . . . . . . . . 4-139S e c t i o n a l v i e w of coolant-pump assembly forBP-13 spacecraft . . . . . . . . . . . . . . . . . 4-140

spacecraf t ) . . . . . . . . . . . . . . . . . . . . 4-1414-142

Command module cabin a i r temperature (BP-13

Command module cab in p ressu re (BP-13 sp a c e c r a f t ) . . .Apollo mission A - 1 0 1 space vehicle shuwing cutaway

Schedule miles tones for BP-13 spacecraf t a tviews of launch vehicle . . . . . . . . . . . . . . 5-4Downey, California, AT0 . . . . . . . . . . . . . . 6-10Cape Kennedy, Florida . . . . . . . . . . . . . . . 6-11Schedule milestones for BP-13 spacecraf t i n Hangar AF,


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Figure Page6.1-3 BP-13 spacecraft mating in Hangar AF, Cape Kennedy,Florida . . . . . . . . . . . . . . , . . . . . . . 6-126 1-4 BP-13 spacecraft loaded on vertical transport priorto mating with the launch vehicle . . . . . . . . . 6-136.1-5 Schedule milestones f o r BP-13 spacecraft at launchcomplex 37B, Cape Kennedy, Florida . . . . . . . . . 6-146.2-1 Apollo mission A-101 precount activities on F-1 day,May 25, 1964 . . . . . . . . . . . . . . . . . , . . 6-176.2-2 Apollo mission A-101 countdown activities on postponedlaunch day, May 26, 1964 . . . . . . . . . . . . . . 6-186.2-3 Apollo mission A-101 f i n a l countdown activities,F day, May 28, 1964 . . . . . . . . . . . . . . . . 6-19


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1-2

Po st fl i gh t examination of str qi n gage, pr essure , and acc ele rati onValues of angle of at ta ck and dpmnicdata indicated t h a t th e spa cecra ft st ruc tur e performed adequately i n thef l i g h t environment encountered.press ure encountered during th e powered phase of f l i g h t were withinallowable l i m i t s and compare well with tho se pred ict ed befor e launch.The wind-tunnel st at ic -p re ss ur e measurements used i n load s analyses werei n agreement with t h e fl ight-measured s t a t i c pressures. The in t e rn a l

p ressures wi th in the SM were within an a llowable range and ve r i f i ed t heventing method.no evidence of severe dynamic loads.&amination of t h e ava i lab le acce le ra t ion data revealed

The ground se rv ic e equipment performed s a t i s f a c t o r i l y during pre-launch and countdown operations.


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2- 3

Figure 2.0-1. - Saturn-Apollo space vehicle f3r !ri ss.s 3n


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2- 4

120-

100-Q)

adcd04c,7

2 8 0 -

6 0 -

G . e . t . t i m e , s e cPlanned Actual

aQ,a7c,.rl4

40

20

0 200 400 600 800 1000

1. Saturn S-I l i f t - o f f 0 02 . Sat urn S-I shutdown

Inboard engin es 140 .1 142 .8146 .1 148 .8utboard engines

3 . Separat ion 146 .5 149 .24. Saturn S-IV i g n i t i o n 1 4 8 .2 1 5 0 . 95 . Launch escape tower j e t t i s on 1 5 8 . 5 1 6 1 . 26. Saturn S-IV shutdown 62 5.8 62 4.5

Range, n a u t i c a l m i l e

Figure 2.0-2.- Sequence of major events f o r Apollomiss ion A-101.


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3 -3

TABLE 3.0-1.- MISSION EVENT TDIES

Event

Lif t -offri l t ar res tImcoOECOUllage rocke t s i gn i t i onSeparat ion of S - I and S - I VS - I V i gn i t i onUl lage rocke t j e t t i sonLaunch escape tower je t t i sol

s-IV cutof f

-~Planned,sec-~0

154.0140.1146.1146.4146.5148.2.158.5158.5625.76

Actual ,sec0

134.0142.8148.8149.1149.2150-9161.2161.2

624.5

l i f ference,' sec

002.72.72.72.72.72.72.7-1.26


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Condition Planned ActualITABLE 3.0-11.- COMPARISON OF PLANNEDAND ACTUAL

TRAJECTORY PARAMETERS - ConcludedDifference-

Perigee altitude, statute miles . .Perigee altitude, nautical miles .Apogee altitude, statute miles . .Apogee altitude, nautical miles . .Period, min . . . . . . . . . . . .Inclination angle, deg . . . . . .k Maximum conditionsAltitude, statute miles . . . . . . . 140.2 1 4 1 . 0 0.aAltitude, nautical miles . . . . . . 121.8 122.5 0.7Space-fixed velocity, f t / s e c . . . . 25,634.2 25,633.5 -0.7Earth-fixed velocity, ft/sec . . . . 24,301.0 24,303.8 2.8Exit acceleration, g . . , . . . . . 5.80 4.89 -0.91Exit dynamic pressure, l b / s q ft . . . 805.0 8d.8 3.8

113.198.3

140.2121.831.7688.59

113.298.4141.0122.588.6231.78

0 . 10 .10 .8c.7

0.030.02


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3-12

nQ)W


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4-A tub ula r forward bulkhead t os i m l a t e the egress tunne l o f the product ion spacecraf t .of aluminum al lo y provided access t o the cab'in.

hatch was b ol te d t o t h e CM ex ter ior s t r uct ure and sealed wi th epoxy.A main hatchPr ior t o launch , the

External protuberances of th e product ion spacecr aft configuration,inc lud ing th e a i r vent , umbil ical f ai ri ng , and two sc imi tar antennas,shown i n f ig ur e 4.1-7,were simulated for a b e t t e r de fi ni t io n of aerody-namic parameters.The CM aft hea t sh ie ld w a s similar i n sLze and shape t o the opera-t i o n a l h ea t s h i e l d . It w a s composed of an inner and outer layer oflaminated fiber glass over an aluminum honeycomb core and w a s at tachedt o t h e CM by four adjustable s t r u t s . No abla t ive mater i a l w a s used be-cause t h e a f t heat sh i e l d w a s not exposed t o t h e launch environment and

no recovery of the spacecraft w a s planned.The lower port ion of t h e forward compartment w a s c o n s t r u c t e d ofaluminum covered with cork insu lat i on , and the upper por t ion w a s a

f iber -g less honeycomb radome containing t h e VHF telemetry omriiantenna.(See f igs . 4.3-2 and 4.7-1.)The bo il er pl at e se rv ic e module assembly cons isted of t h e f a i r i ng ,

The SM assembly andser vic e module stru ctu re , and SM insert which were bol t ed toge ther .b o i l e r p l a t e adapter was b o lt e d t o t h e SM i n s e r t .t h e i ns er t , shown i n f igur e 4.1-8, were of semimonocoque aluminum con-s t r u c t i o n . F or f u r t h e r s t r u c t u r a l d e t a i l s , see sec t i on 4.6.

The

A pneumatical ly actuated umbil ical assembly w a s loc ate d approximately18 inches below th e to p of t h e SM and 58" from the -&axis tuward the+ Y - a x i s . E xt e rna l e l ec t r i ca l pa re r , GSE sign als , and coolant f l ui d wereobtained through t h i s assembly pr io r t o launch.Dunrmy quadrant packages fo r the r ea ct io n co ntr ol subsystem (RCS)

I nere a t tached t o th e upper port ion of th e SM ex t e r i o r , 90" apa r t .order t o dupl ica te the aerodynamic cha rac ter i s t ics of th e product ionu n it s , t h e dumqy packages were t h e same s i z e and shape and were arrangedon the SM i n t h e same l oca t i on as t h a t of th e opera t ive un i t s on theproduct ion spacecraft .In addi t ion , t he SM and adapter contained instrumentat ion trans-ducers and associated components and w i r i n g and e l ec t r i ca l w i r e harnessest h a t i n t e r f a c e d w i t h th e launch vehicle inst rument uni t f o r t h e Q-balls ign als , th e two tower je t t i s o n comand signals , and GSE s igna l s .The to t a l weigh t inse r t ed i n t o or b i t w a s 17,023 pounds. Due t o ar e s t r i c t i on i n t he l aunch veh ic l e pay load capab i li t y, t he o r i g i n a l


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4-4

TABLE 4.1-1.- SPACECRAFT BP-13 MASS CHARACTERISTICS

I I Weight,

Command module 973004,172

SM i n s e r t a nd a d ap t eService module

17,023otal in o r b i t

~ ~~~~~

Center of grav ity,i n

xA1,041.2

951.1785 . 5965.8

1,294.7

hes4-yA-2.4

1 . 4-3.21 .0

b o . O-0.7-

-AZ

5 .1-0 .8-1.52 . 3

-0 ..2

-

1

1 . 6-

~ ~~ -~Moment o f i n e r t i a ,slug-f et2

Rol lIXX

15,364

P i t c h4y37 98247 187'5,733

48,464'8,778

167,350See f igure 4.1-2 fo r re fe rence axis system and f i g u r e 4.1-3 f o r

X reference point .A

_.YawIZZ379064,1485 , 7 5 2

48,3508 ,781

167,253


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4-5

Launch escapesubsystem26 d ia399.7

I761.1

Figure 4.1-1. Apollo BP-13 spacecraft.


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4-7

.ti-eai00r ir(aicd


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4-

Bal las t enc losurecoverQ-ballassembly

Pi t c h c ont r o lmotor nozz le\Tower j e t t i s o nmotor ( l ive)Inters tage\1dapterLaunch escapemotor ( i n e r t )

Launch escapetower

T o w e r e xp l os i veb o l t s

P i t c h controlmotor ( i n e r t )

Tower j e t t i s o n/ otor nozzleLES wire harness

T o we rsequencers//-Structurals k i r tLaunch escapemotor noz z l e

Power systems andinstrumentationwire harness

Figure 4.1-4.- Launch escape subsystem for BP-13 spacecraft.


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4-66

Angle of attack, degFigure 4.6-5.- Variation of angle of a t t a c k wi th a l t i t u d e(Apollo mission A-101).


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4-68

0

ei.-00tn.-cc

QX


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4-72

c.--c0uc0-

0c-I nK\

kcd

n0W

!dl-


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4-73

ParachutecompartmentMain hatch

Command modulePurging tube-A f t heatcompartment

Service module-

Insert-----\*

7dapterPressurevent h o l e s - _8 p l a c e s )

t. -JL, - - J,- - - - - -

@ B O (0 Near s i d e0 ar s i d e

Figure 4.6-8.- Pressure venting scheme f o r BP-13 spacec ra f tse rv ic e module, in s er t, and ada pte r compartment.


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4-74

dmWQ,k3rnrnQ,kPI

!


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4-75


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4-79OS

.0 7

.06

.05

.04

.03

.02

.01

. oFrequency, cps

( a ) LES Y - a x i s a t Q-bal l i n t e r f aceFigure 4.6-13. Digi ta l spect rum est imat ion of l a t e r a lbending accelerat ion (BP-13 spacecraf t ) .


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4-81

Sensor CA0005 AY-axis CM acce lTime s l i c e 51.50 t o 56.50 se cLow-pass filter 25 c p sF i l t e r BW

.0006

\ .M@a

0005

0004

0003

0002

0001

0 0 5 10 1 5 20 25Frequency, cps

( c ) Command module Y - a x i s .Figure 4.6-13. - Continued.


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4-83

idkUa,


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4-84

(a ) LES Z-axis a t Q-ball i n t e r f a c eFigure 4.6-15. - D i g i t a l spectrum es t ima t ion o f first bending

mode a c c e l e r a t i on of BP-13 s p ac ec ra ft a f t e r i g n i t i o n of S-IV s tage .


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4-85

8\Mhl

Frequency, cps( b ) LES Y-axis a t Q-ba l l i n t e r f a c e .

Figure 4.6-13. Concluded.


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4-87

0u1

dE

nrl

E-Oca,k5mIDa,kPI

h0

I


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4-88

00cu0..0dcd0..0 0c u Q' 0 Cad *.

Swo w0 0

' 0 Ir ( c ,o w4r(

O . l-!3

O.S1

O k* wO Q

c,vQ,o wN Q

0 ' cd04O M

..

00

00e.

0cv..%n 0 uad d Iq s d 'aanssaJC6

5co0alkpcb r '+,mI


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4-89

I

f


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4- 0

M r a d i a l v i b 3T i m e s l i c e 4 0 . 0 0 t o 4 3 . 7 0Low-pass f i l t e r 1050 cpsS l i c e RMS v a l u e 1 2 . 0 0 2

400 600 80 0 1000 1200Frequency, cps

( a ) Instrument SA0086DFigure 4.6-20. - Digital spectrum estimation of BP-13 spacecraf t service m o d u l eradial vibrat ion.


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4-91

Frequency, cps

(b) Instrument sAOO87DFigure 4.6-20. - Concluded.


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4- 92

No strain gagedata during this40x 103I

0 Axial loadQ aAxial loado Bending momentv 'Bending moment

(s trai n gage)(other f l i gh t data)(s trai n gage)

120

100

802i0d2 60-rlK Oe vf b

e05CU

I B c01

01U

cLCr(

cp.

c4.rl

vd ldI

Yl Yac

Yhb s.= b

C- 4C C0V h* Ea a lYm

aleYW Uc

hPPc..I

vd

UC a2 adLacWhala4m

3\h+aa4

u cPIhald4n

vchmcl-4C

- eal aa l vV a lr:e:05% alr(010m

h xO Y.r(a d4m e

YhL

m-1


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6-12

Figure 6.1-3.- BP-13 spacecraf t mating i n Hangar AF,Cape Kennedy, Florida.


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-13

Figure 6.1-4.- P-13 spacecraft loaded on ver t i ca l t rav l spor tp r i o r t o mating w i t h t h e launch vehicle .


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6.2 Launch OperationsThe launch countdown was planned to require 1 7 hours and 15 minutesto complete.

precount (F-1 day) of 8 ours and 10 minutes and a final count (F day)of 9 hours and 5 minutes.A rest period of 12 hours and 15 minutes was provided forthe launch team by dividing the count into two portions consisting of a

'

The F-1 precount began as scheduled on b y 5, 1964, at T-1035 min-utes ( 3 :50 a.m. e. s. t. ) and proceeded normally until a launch-vehiclehold was called at T-795. (Refer to fig. 6.2-1. ) Spacecraft ordnancework continued during this time and was completed before the count wasresumed at 10: 0 a.m. e. s. t. At the direction of the Eastern TestRange (ETR) Range Safety Officer, post-installation resistance measure-ments of the initiators were rescheduled for the hold period at T-545minutes, when the launch complex could be cleared of all personnelexcept the seven members of the spacecraft ordnance team.

The final count on F day began approximtely 20 minutes late onk y 26, 1964, as a result of a failure of "critical" power at the block-house.and the operations were essentially completed 23 minutes early at T-293minutes. Failure of the launch-vehicle environmental control subsystem(ECS) compressor caused the countdown to be postponed at T-113 minutes(9:40a.m. e. s.t.> ,fter a hold of 2 hours and 10 minutes. Spacecraftrecycling operations consisted of hatch removal, battery disconnect,and disarming of the launch escape subsystem (LES) initiator. In addition,the nitrogen bottles used for c o m n d module purging were refilled, theinstrumentation batteries were recharged and makeup electrolyte added,new hatch screws were obtained and the hatch secured and sealed, placingthe spacecraft in the correct configuration to begin the countdown againat T-545 minutes.

(Refer to fig. 6.2-2. ) Spacecraft testing proceeded normally,

The launch countdown began again on May 27, 1964, at T-545 minutes(11: 5 p.m. e. s. t. ) . (Refer to fig. 6.2-3. ) When the onboard ECS pumpwas initially activated at T-522 minutes, it was noisy but was otherwisenormal. The time required to change this pump was estimated to be 8 ours,and the decision was made to continue the count but to monitor closelythe communications package temperatures.Spacecraft testing operations were normal and were completed13 minutes early at T-283 minutes.37 minutes at T-95 minutes, and 61 minutes at T-70 minutes did not affectswcecraft operations.given in the launch-vehicle count at T-41 seconds (10: 7 a.m. e. s.t),causing a recycle to T-l ' j minutes.

Holds for, he launch vehicle ofThe terminal count was norm1 until "cutoff" was

The spacecraft LES was disarmed,


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th e power was t ra ns fe rr ed t o ext ern al power f o r bat tery conservat ion,and the communications systems were shut down t o reduce th e heat load.After a Tbminute hold, the launch count was resumed a t 11:52 a.m. e . s . t . ,and it proceeded n o m l l y t o t h e l aun ch a t U:O7 p. m. e. s. t. onMay 28, 1964.


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I

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6.3 Range OperationsThe network which provided telemetry and radar support f o r t h e m i s -

s ion cons i s t ed pr imar i ly o f s t a t ion s of th e Eas te rn Tes t hnge, augmentedby Department of Defense and NASA st at io ns , The coverage provided by t h es t a t i o n s i s shown i n t ab le 6.3-1.was committed to support t he m ission with th e exception of t h e FPS-16radars a t Bermuda and H a w a i i which were being modified f o r Gemini programsupport.

The inst rumentat ion of t h e s e s t a t i o n s

During the countdown, the Cal i fornia and Grand Turk s t a t i ons r epo r t edmalfunctions.p l i f i e r power supply in t h e ~ps-16adar a t T-250 minutes,reported a complete parer fa i lure f o r 60 seconds a t T-15 minutes with noapparent damage t o t h e TPQ-18 radar o r other systems.major problems existed a t any of the network stat ions.

Cal i fo rn ia rep laced a defec t ive tube i n the parametr ic am-Grand TurkA t l i f t - o f f , n o

During th e mission, t e l e m e t r y coverage was obtained on th e f i r s tt h r ee o r b i t a l passes and part of the fourth .was obtained during the f i r s t f'ull o r b i t a l pass and nea r l y a l l of t h esecond pass, a f t e r which no further signals were received from t h e tr an s-ponders,sk in t racked t h e veh icle throughout i t s l i f e t i m e o f 54 o r b i t a l passes.

"he times of acqui s i t ion and l o s s of te lemetry recept io n f o r each

Radar t ransponder t racking

m e r the t ransponder stopped operat ing, many of t h e s t a t i o n s

s t a t i o n are given i n t a b l e 6.3-1.horizon-to-horizon rece ptio n on a l l three spacecraft l inks. The lasts t a t i o n t o repor t recep t ion of links A and B was Pre toria , South Africa ,on the four th pass , Thenex t s t a t i on in view, Hawaii, searched from @:53:OO,to 06:O7:OO g.e.t.but was unabl e t o de t e c t any t r a ce of a signal. The l as t s t a t ip n t o re-ce ive l i nk C was Cal i forn ia on the second or b i t a l pass . Loss of signalwas recorded a t O3:06:26 g.e.t. No s t a t ion repor t ed recep t ion of link Ct el eme t ry a f t e r t h i s time.

In general , each s t a t io n repor t ed

Loss of' signal was recorded a t 05:21:02 g.e.t.I

The only known te lemetry anomaly occurred a t t h e Cape Kennedy Te le -metry Stat ion 2 on both th e h un ch phase and th e f i r s t o r b i t a l p as s.Rather severe spiking was noted on s ev er al of th e continuous channels ona l l three links, but t he most sever e was on l i n k C.on the osci l lograph records made from t h e Cape Kennedy Telemetry Sta-t i o n 3 t ape , bu t it was not nearly as severe as that noted i n t h e Tele-metry Stat ion 2 data.a t Telemetry S ta ti on 2.

Spiking was noted

The problem i s pre sen t ly be ing f u l l y i nves t i ga t ed

The t imes of ac qu is i t i on and loss of C-band radar r ecep ti on a re p re -sented in tab le 6.3-II.t ransponders was White Sands during t he second o rb i t a l pass.C-band rec ep tio n occurred a t 03:08: 36 g. e. t., which i s approximately theThe l a s t s t a t i o n t o r e po r t t r a ck i n g of t h e C-bandb s s of


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same tim e t ha t t he loss o f s i g n a l from t h e l i n k C telem etry occurred.The following anomalies were noted i n th e performance of th e networkradar:(1) A t White Sands Missile Range, New Mexico, on the f i r s t o r b i t a lpass , the ms-16 t r a n s m i t t e r f a i l e d a t t he po i n t o f cl os es t approach,which was a t t r ib u t e d t o a parer surge.( 2) A t Fg lin Air Force Base, Flo rid a, on th e f i rs t o r b i t a l p as s,severe countdown was experienced on the transponder r ep ly which resulted

i n a loss of ,Fminutes of v a l i d t racking,2( 3 ) Antigua Island, on th e second o r b i t a l pass, d i d no t acqu i r et rack a l though it received th e t ransponder reply.returns prevented lock-on. Possibly, s ide-lobe(4) Cal i forn ia , on t he second o rb i t a l pass, d id not acqui re va l idt r ack due t o a 50-percent reduction i n tr an sm it te r power, which was causedby an opera tor e r r or i n p roperly pos i t ion ing a switch.The network stations that repor ted sk in t rack ing of t he veh ic l e a tvarious t imes throughout i t s orb i t a l l i f e t i m e i nc l uded Pa t r i ck A i r ForceBase, F lo ri da ; Grand Turk Island; Antigua Island; Ascension Island;Pr eto ria , South Africa; Carnarvon, A u t r a l i a ; California; White SandsMissile Range, New Mexico; and Egli n A i r Force Base, Florida. Carnsrvon

reported t he most e xtensive coverage, having s kin t racked th e sp ace craf ton passes 1, 12, 13, 14, 15, 16, 26, 27, 28, 29, 30, 31, 42, 43, 44, 45,46, and 47.


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0


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6-24

6.4 Data Coverage and A v a i l a b i l i t yData fo r evaluat ion of t he Apol lo A - 1 0 1 t e s t mission inclu ded pre-launch hard line t o ground, telemetry, radar, opt ica l , me teoro log ica l ,and environmental information (t ab le 6.4-1) . These da ta were o btai ned

from both the Eastern T e s t Range and t h e Manned Space Fl i g h t Networkthrough t h e Goddard Space F li g ht Center (GSFC) snd thr oug h th e KennedySpace Center (KSC). W t a were a ls o provided by th e U, S. Weather Bureau,The recorded da ta were reduced a t.C ape Kennedy Telemetry St a ti on 2,Manned Spacecraft Center Computation and Analysis Division in Houston,

Texas, Marshall Space Fl ig ht Center i n Hunts vil l e, Alabama, and the con-t r a c t o r ' s f a c i l i t y a t Downey, California,

The Operations Support, Plans, and Programs Office (OSPPO)of MSC-Flor ida Operat ions p rov ided ac t iv e l i a i s on support fo r data redlictionand data evaluation.The de li ve ry of m a n y data i t e m s t o OSPPO was delayed, as ind ica ted

The data l i a i son suppor t by OSPPO caused no de-i n table 6.4-1, because of t h e new lo gi s t ic s channels establishes f o rt h i s s p e c i f i c m is sion ,lay .erences j o >.or a complete ou tl in e of coverage planned f r o m the range, see r e f -

The data l i s t e d i n t a b l e 6.4-1 i l l be on f i l e a t t h e &nned Space-c r a f t Center, Houston, Texas. Requests may be addr esse d t o t h e Manager,Apollo Spa cec raf t Program Off ice.Eastern T e s t Range and Kennedy Space Center.- Data were de l ive red

Oscil lograph charts and magnetic tape recordingst o OSPPO and the evaluation team from ETR and from KSC v i a t h e K3C h t aCoordination Office.o f te lemetry received a t Cape Kennedy were made available approximately3 hours a f t e r l i f t -off . Quick- look 4020 p l o t s were provided in 35mm filmformat i n T+8 hours.by MSC on th e day a f t e r launch, and t h e f i r s t p a r t o f t h e f i n a l t ra j e c t o ryda ta w a s ava i lab le i n 4 alendar days.metry received f o r o r b i t a l p as se s were a v a i l a b le i n 4 t o 6 days a f t e rlaunch. F i r s t sig na l st re ng th reco rds from Cape Kennedy were received7 days a f t e r t h e f l i g h t .

Quick-look t ra je c t o r y tabu la ted data were obtainedMagnetic tape recordings of t e le -

Ehgineering sequential f i lm w a s planned f o r support of th e miss ionfrom th re e fi xe d cameras and fo ur tr ac ki ng cameras. They were t o provide16m and 35mm photographic coverage of the BP-13 spacecraf t .f rom three of the tracking cameras w a s a v a i l a b le f o r study by the evalua-t i o n team, the o ther four eng ineer ing sequen t ia l f i l m being missent t oanother organizat ion,coverage of tower j e t t i s o n as requested,of t h e spacecraf t was provided pr io r t o and fol lowing tower j e t t i so n.

Only the f i l m

The Vero Beach ROT1 t racking film did not provideHowever, good qu a li ty co v e r k e


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6-25Goddard Space Flight Center.- The GSFC network s t a t i o n s rec orded

telemetry data and t racked th e sp acecraf t during the mission.data from th e Bermuda network s t a t i o n were used i n c a l cu l a ti n g o r b i t a lt r a j e c t o r y data and in se rt io n parameters.were presented from calculations made a t Greenb elt, Maryland, and weremade available in 2 days a f t e r launch.telemetry (magnetic tapes) from down range st at io ns a rr iv ed a t MSC-Florida Operat ions 6 days af%er t h e f l i g h t .

TrackingCorrec ted t ra j ec tory data

The f i r s t s i g na l s t r eng t h and

I G C Houston.. Sp ac ec ra ft tel em etr y data were pr oc es se d by th e Compu-t a t i o n and Analysis Division, MSC, Houston, with support from Instrumenta-t i on and Ele ct r i ca l Systems Divis ion, MSC, Houston. A tape copy fromTelemetry Stat ion 2 (Tel 11)w as rec eive d i n Houston a t T + 10 hours, anda copy from Antigua, a t T + 20 hours,ana lys i s p lo t s f rom these data t apes was provided t o th e eva lua t ion teama t T -1- 4 ays. The p a ch g e contained t ime-histor y data of acce l e ra t i ons ,e l ec t r i c a l i n format ion , t empera tures, hea t flux, s t ra in gages , and RMS oflow-frequency acce lera t ions , f lu ctu at i ng pressu res , and radia l v i b ra t i ons .These data were reduced by using telemetry tapes from both T e l If andAntigua,contained th e t ime his to ri es of conical pressure c oef f ic ien ts and powersp ec t r al densi ty (PSD) of low-frequency acce lera t ions , s t r a in gages, andr a d i a l v i b ra t io n s ,th e measured co nic al s urf ac e pre ssu re and th e dynamic pres sur e based ont h e measured atmospheric densi ty a t t h e time of launch.p lo t t e d by us ing th e T e l I1 and Antigua tapes and w a s produced by adigital-computer process. The t h i r d package, which w a s ava i l ab l e w i t h i n7 days a f t e r launch, contained PSD plots of the same parameters includedi n t h e second package.Antigua tapes and w a s produced by an analog process with equipment oper-ated by t h e General Instrumentation Branch of the Inst rumentat ion andElectrical Systems Division.

The f i r s t package of engineering

The second package, which w a s ava i l ab l e w i t hi n 3 calendar days,The pressure coef f i c i e n t s were determined by using

The PSD w a s

The PSD was plo t t e d by us ing th e T e l I1 and

Lift-off (T-0) w a s es tab l i shed as 12:07:00:42 a.m. e. s. t.(17: 7:00: 42 G.m. t . >.recorded for th e continuous and high-le vel commutator param eters, werewithin 1percen t of t h e o r b i t a l v a lu es .a r e s u l t of R and Z ca l ib ra t io n changes because the change t o th e datawould not have been significant .Z ca l i b ra t i on va l ues were a l s o checked f o r th e low-level commutator andwere found t o be gr eat er than 1percent .o f ca l ib ra t io n c i r cu i t u t i l i ze d , no changes were made t o th e ca l ib r a t io ncurves t o co r rec t f o r t h e R and Z cal ibrat ion changes.

Prelaunch R and 2 cal ibr at i on values, which wereNo correc t ions were made as

The changes from the original R andHowever, becau se of t h e typ e

All pressure measurements were biased t o read ambient pressure a tlaunch, and th e acceler at ion s were b i a sed t o r ead lg on the X - a x i s andzero-g on the Y- and Z-axes.


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6-26In process ing the BP-13 data, a n e d i t r o u t i n e was used t o determinechanges of 2 percent or g r e a t e r of te lemetry full sc al e i n t he commutator

data and 3 percent o r gre a te r o f t e lemet ry f u l l sca le i n the con tinuousdata.r a t e , a poin t w a s tabula ted and plot ted for each change greater than thepredetermined values of 2 and 3 percent.I n a dd it on t o t h e data being tabula ted and plot ted a t a basis

Telemetry tape from T e l 11was used for reduced data from T + 400 sec-onds through insertion,t h e t i m e of launch-vehicle staging.i n se ct io n 4.2, Instrumentation. The v a lu e s p r i n t e d f o r all parametersduring t h i s time were considered t o be inval id ,te lemetry tapes provided data f o r t h i s 2.7-second period.

The T e l I1 tape showed t h e 2.7-second dropout a tReasons for the dropout are discussedNone of t he av ai la bl e

The engineering scales were es tab l i shed fo r most of t h e p l o t s t obe i n accordance with t he cal ibr a te d ins trument range and t o provide areading accuracy of approximately 2 percent o f telem etry f u l l scale .Tabulation and plots w e r e produced for a l l parameters that w e r e plannedb ef o re t h e f l i g h t , e xc ep t for those parameters whose instruments fa il edt o opera te proper ly .Instrumentation. These f a i l u r e s a re discussed i n s e c t i o n 4.2,

Data were processed from th e Ant igua tape f o r th e second pass ; th a ti s , as the spacecraf t began i t s second pas s and w a s within telemetry con-t a c t . No o th er o r b i t a l data processing was planned t o suppor t th i s re-po rt , but supplemental processing w i l l be done t o include orbi ta l - passdata a t a l a t e r date.

The data reduct ion operat ion w a s planned t o provide data t o t h eanalysts as r a p id ly as pos sib le by ut i l iz in g high-speed reproductionmethods. Speci a l p l ot s requested dur ing th e evaluat ion and repor t -wr i t ing per iod were provided a f t e r t h e system analysts had revieweddata i n i t i a l l y p r oc es se d.

Addi t ional copies of th e engineer ing pl ot s processed by MSC Houstonar e av ai la bl e through t h e Apollo Spacecraft Program Office.Data trans mitte d by th e launch-vehicle telem etry from instrumenta-t i o n i n t h e s p ac e c ra f t were processed by MSFC i n accordance wit h previous

arrangements made between MSC and MSFC. IBM compatible tape copies wereforwarded t o MSC Houston and reduced engineering pl o t s t o t he t e s t eval-uat ion team a t MSC FO a t T + 13 days.Engineering plots received from MSFC included adap te r ra d i a l v ib ra -t io ns , servic e module acous t ic , &-bal l , and launch vehic le a t t i tu de gyrodata.


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6-28

~~~ -~Data type

TABLE 6.4-1.- D U A AVAlLABlLlTy - Continued___

Anticipated DateP r e se n ta t i on a v a i l a b i l i t y r e c ei v eda ) [a )

R e a l t ime recordings

Telemetry engineering data :Commutated channels

Continuous channels

~ ~~

O sc il lo grap h ro l l sMagnetic tapes

35mm f i lmP l o t s35m f i l mP l o t s

Impact p red ic ter data(S p ec ia l t r a j ec to ry an daerodynamic parameters )P o s i t io n d a ta

Velocity data

Accelera t ion data

Spec a 1 t r a e c tory parameters

A t t i tu d e dataLaunch escape tower positionand veloci ty

B es t e s tima te of t r a j ec t o ry

RadarTab printoutcomputer output tape

Computer tapet a b p r i n t o u tComputer t a pet a b p r i n t o u tComputer tapet a b p r i n t o u tComputer tapet a b p r i n t o u tTab printoutTab printout

Tab printout

3 H8 H8 H

3 H6 a

1 CD1 CD

aKey :H - HOWCD - Calendar Cay ASAP - As soon as p o ss ib leWD - Working Day

1 CD(b )4 D4 CD4 CD4 CD4 CD4 CD

(Requirementsubmittedto o l a t e t obe supportedby range)

b k t a requested but not rece ived during the postlaunch rep orti ng period


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r

TABLE 6.4-1.- DATA AVAILABILITY - ContinuedCata type

6-29

Anticipated DateP resen ta t o n av a i l ab i l i t y r eceiv ed(a ) a

Final ca lcu la t ions o f posi t ionand velocit y from ins ert i on t ocompletion of f i r s t passF inal ca lcu la t ions o f specia lt r a j ec to ry items from insert iont o completion of f i r s t passOrb i ta l f l ig h t parameters (perl e t t e r from MSC/FO t o GSFC,1-13-64)Radar beacon log Cape KennedyRadar data sheet (uprange ETR)Radar data sheet (downrange EJ!R)Radar data sheet a l l non-lDR, DOD!and NASA s t a t i o n sRadar event record (uprange ETR)Radar event record (downrangeETR)Plo tt i ng board charts (copies ofcharts made by KS C from station1 nd IcC 3 7 )Pl ot ti ng board cha rt s (downrange)Aerodynamic parameters (velocityof sound, dynamic pr es su re , Machnumber, Reynolds number )

R a d a r event record from a l lnon-ETR, DOD, and NASA s t a t i o n s

~ ~~~aKey :H - H O WCD - Calendar Llay

RadarTab printoutTape

Tab printoutTape

Teletype message

Log formatLog formatLog formatrag fonnat

S t r ip ch a r tS t r ip char t

C h a r t

Charth b u l a r

s t r i p c h a rt

3 CD3 CD3 CD

ASAP

1 CD1CD4 CDASAP

1 CD6 CD3 H

2 CD3 CD

ASAP

3 H

4 CD6 CD6 CD7 CD

Sta. 1-4HLCC-37-4 H

7 CDWorking papernot submittedin t ime fo rcomputer pro-graming; shouldbe avai lab le b jJune.

7 CD

ASIS' - A s soon as possib leWD - Working Dayblhta requested but not received during the postlaunch repo rting periodCIn i t i a l t ra jecto ry cond i t ions o n l y have been received to perfo m analys is fo rsec t io n 3.


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Anticipated( a )

I s t a t ype Presen t a t ion ava i l ab i l i t y

TABLE 6,4-I. - DATA AVAILABILITY - ContinuedDatereceived( a )

Radar function record , S t r i p c h a rt 4 CD(xprange ETR)R a d a r func ti on r ecord S t r i p cha r t 4 CDR a d a r function record from d l S t r i p C h a r t ASAP(downrange ETR)

non-ETR, DOD, an d NASA s t a t i ons

Seque ntial events ( t imes derivedfrom optics from l i f t -off , S -Iburnout, S-IV ignition, and LESj e t t i s o nSpacecraft umbil ical disconnectS t ruc t u r a l su rve i l l ance ofspacecraft during launchLift-off and early f l i g h tLong fo ca l l ength opt ica lt racking

6 CD

(b1(b1

'Pab pr i n t ou t

Engineering prints 16rmn

Pre f l i gh tand launch

Engineering prints l6mm

As required

Engineering prints 16nrm1h Vero Beachengineer ing pr in t~ ~ I I I U I Melbourne Beachengineer ing pr in t

Cloud coverage and v is ib i l i t yfrom T-O (uprange)

k t e o r o l o g i c a l data

I l C D 1 8 HTabular

IWeather forecasts:Forecasts w i l l be made bySpace Flight Weather (U.S.Weather Bureau ass ig ne d toNASA)Surface weather observationfo r T-0 (temperature, press ures ,R.D., wind direction, andveloci ty and dens i ty)

1 CD

5 CD .5 CD5 CD5 CD

Tabular 1 CD 8 H

I IaKey :H -Hour

CD - Calendar Iky ASAP - As soon as poss i b l eWT - Working DaybIs ta requested but not received during th e postlaunch report ing period


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6-31

Anticipated(a,)

Data type Presen ta t ion av ai la b i l i ty

-TABLE 6.4-1. - DATA AVAILABILITY - Concluded

Datereceived(a )

Cloud coverage and visibilityf o r T-0 (downrange)Upper a i r weather observationf o r T-0 (temperature, pressure,R.H . , wind direction, andveloc ity and dens ity) . (Bothuprange and downrange )Prelaunch upper a i r observation(temperature, pressure, R.H.,wind direction and velocity).(wrange and downrange)su r face to 40 kmPrelaunch upper a i r observations(temperature, pressure, density ,wind direction and velocity)(Uprange and downrange25 t o 90 k m )

Meteorological dataTabular

Tab printoutcomputer output tapes

Tab printout

Tab printout

1 CD

1 CD

4 H( a f t e rre l ease )

4 H( a f t e rre l ease )

Ground and environmental measurementsFlash reports from groundand environment (G and E )measuring programGround and environmental(G and E ) measuring numbersl2CD3-Water-glycol

ucD4-Water-glycol12CW-Air temperature a t13C Dg-Ai r temperature a t22C29-Vibration deck22C30-Vibration deck22C3LVibration deck25Cll-Acoustic a t

in le t temperatureou t le t temperature268-f t l e v e l188-ft l e v e l188-ft l e v e l v e r t i c a l188-ft level (58-238 deg)188-ft level (148-328 deg)188-ft level umbilical tower

aKey :H - HOUCD - Calendar C ay

Report As av a i l ab le

S t r i p c h a rtS t r i p c h a r tS t r i p c h a r tS t r i p c h a rtS t r i p c h a r tS t r i p chartS t r i p chartS t r i p chart

ASAP - As soon as possib leWD - Working I.by

2 CD

(b 1

bIhta requested but not receive d during the postlaunch reporti ng period


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7.0 CONCLUDING RENARKS

A l l of t h e spacecraf t t e s t object ives for the Apol lo mission A - 1 0 1w ere fu l f i l l ed :1. The bo i le rp la te spacecraft BP-13 mated s at i s f ac to ri ly w i t h t he

SA-6 launch vehicle and a l l systems and interfaces w e r e compatible underpre f l ig h t , l aunch , and or b i t a l condi tions .2. Sat i s f ac t ory engineer ing data covering designated parametersof spacecraft launch environment were obtained fo r use i n ver i fy ing ordete rmin ing spacecraf t des ign c r i t e r i a fo r Apol lo e ar th or b i t a l miss ions .3. The launch environment conditions measured d i d not exceed t h ec r i t e r i a used i n t he des ign of the bo i l e r p la t e spacecraf t.4. The tower j e t ti s o n motor prope lled launch escape subsystemc l e a r o f t he spacec ra ft as required.5. The launch escape subsystem st ru ct ur e performed sa t i s f a c to r i l yunder f l i g h t loading condi t ions.6. Ground support handling equipment and procedures were usedsuc ces sf ull y .during prelaunch and countdown oper ations.The f l i g h t t r a j e c t o r y of the mission provided t h e launch environ-ment required.Spacecraft subsptems including instrumentation, performed thefunct ions requi red for a sa t i s fa c t or y miss ion.


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1. Anon.: An Inves t iga t ion of Aerodynamic Noise Measured on a0.055-Scale Apollo/Saturn Vehicle i n th e NASA Ames 14-FootTransonic and 9 X 7-mot Supersonic Wind Tunnels.[NAS 9-1301, North American Aviation, In c. , Dec. 31, 1963.SLD 63-1480I:PSTL-11

2 . Staff of Saturn Flight Evaluation Working Group: R e s u l t s of t h eSixth Saturn I Launch Vehicle T e s t F l i g h t .

Download - Post Launch Report for Apollo Mission A-101 (BP-13)

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