saturn v launch vehicle flight evaluation report - as-512 apollo 17 mission

8/7/2019 Saturn V Launch Vehicle Flight Evaluation Report - AS-512 Apollo 17 Mission

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- !

GEORGEC.

MPR-SAT-FE-73-1S LIUMCHREPOR_-ES-512295 p HC CSCL 22C

U NFEBRUARY8, 1973

N'73-33922

OncLa$G3/30 198_5

SATURNLAUNCHEHICLEFLIGHTVALUATIONEPORT-AS-512

APOLLO7MISSION

....'.- ' " '_V/Io _.._ ,; .. "iviO-iL

PmEPAREDY_TUH FLEHT_ALUATIOHWORKIHGGROUP

r_C - F,_' "'J ,'Rev Ocf :_,er |';;'bT)


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6EOKEC.HA|SHALLSPACEFLI6HTCENTE|

MPR-SAT-FE-73-1 FEBRUARY 28, 1973

SATURNLAUNCHEHICLEFLIGHTVALUATIONEPORT-S-512

APOLLO7MISSION

PlgAlll BY_11iJllflFLINTEVALUATIONOIIKIN STOUP

L


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MPR-SAT-FE-73-ISATU_ V LAUNCH VEHICLE FLIGHT EVALUATION REPORT - AS-512

APOLLO 17 MISSIONBY

Saturn Flight Evaluation Working GroupGeorge C. Marshall Space Flight Center

ABSTRACT

Saturn V AS-512 (Apollo 17 Mission) was launched at 00:33:00 EasternStandard Time (EST) on December 7, 1972, from Kennedy Space Center,Complex 39, Pad A. The vehicle lifted off on a launch azimuth of90 degrees east of north and rolled to a flight azimuth of 91.504degrees east of north. The launch vehicle successfully placed themanne_ spacecraft in the planned translunar coast mode. The S-IVB/I_ impacted the lunar surface within the planned target area.This was the third Apollo Mission to employ the Lunar Roving Vehicle(LRV) during Extravehicular Activity (EVA). The performance of theLRV was satisfactory and, as on Apollo 15 and 16 Missions, resulted ina significant increase in lunar exploration capability relative tothe lunar exploration missions made without the LRV. The averagedistance traversed with the LRV on the last three Apollo Missionswas approximate]y 30 kilometers, where the average distance traversedon the three Missions without the LRV was approximately 3 kilometers.The total distance traveled on the lunar surface with the LRV on thisMission was 35.7 kilometers (17 miles).All launch vehicle Mandatory and Desirable Objectives were acco_lishedexcept the precise determination of the lunar in_act point. It isexpected t_at this will be accon_}llshedat a later date. No failuresor anomalies occurred that seriously affected the mission.Any questions or comments pertaining to the information contained inthis report are invited and should be directed to:

Director, George C. Marshall Space Flight CenterHuntsville, Alabama 35812Attention: Chairman, Saturn Flight Evaluation WorkingGroup, SAT-E (Phone 205-453-1030)


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TABLE OF CONTENTS

PageTABLE OF CONTENTS tf!L|ST OF ,'LLUSTflATIOflS viiLIST OF TABLES J|aC_J_OWL_EMENT x 11IAeMYI&T IONS xlvMISSION PLAN xvllIFLIGHT _RV xxtNISSION O_CTIV(S ACCOPWI. ISIMEIIT xxvtllFAILUA(S _0 A_LIES xxvtxSECTION I - INTRODUCTION1. ] %rpose 1-11.2 Scape ]-1SCTIOfl 2 - EVENT TI_IES2.1 _ry of Events 2-12.2 Yet|able Ti_ and C_ 2-2

Switch Selector EventsS(CTION ) - LAUNCHOP(RATI011S3. I Summary 3-13.2 Pre] eunch _t teStS 3-13.2.1 S-IC Stage 3-13.2.2 S-IX Stage 3-33.2.3 S-iYB Stage 3-33.2.4 IU Sr.aqe 3...43.3 Ten, hal Coun_leum 3-43.4 Pro_l 1ant Loads ng 3-83.4.1 RP-I Loadtng 3-83.4.Z LOX Loading 3-83.4.3 LH2 Londt ng 3-93.5 Ground Support Equtmunt 3-93.5.1 Ground/Vehicle I n t4rface 3-93.S.2 MSFC Fur_tshed Grmmd Suitors 3-10[_t_wntSICTION 4 - TRAJ(CT0rt4.1 Suimry 41-,I4.2 TrIJector_ Ira|rattan 4-14.2.1 Ascent Phase 4-1

iii

4.2.24.2.34.2.4SECTION S5.1S.25.35.45.55.65.6.15.5.25.75.85.95.10SICTION 66.16.26.35.46.S6.i5.5.15.6.26.7

PagePark|nq Orbit Phase 4-2In_ectlon Phase 4-2Early Translunar Orbit Phase 4-9- S-IC P_OPULSI_S_q_ry S- 13-|C Igni tion Transient 5-1Per fofmance$-_C P_lln_lge Pe.rfocg_nce S-4S-:C n_tme Sbutdotm 5-7Transient Per for_r_eS-IC Staqe Propellant ._7/_i_g_mentS-IC Pressurization Systems 5.-7S-:C _'_xellYessurtzetIon 5.7Sys_e_S-IC LOX Pressur]zatton 5-83_ste_3-IC _tlc Control 5-9Pressure Syst lm$-IC Purge $.v'stl_S _,'_S-IC POGOSuppression S-i0Sys_m3-IC H_lr_ulSc S}_tem S-|I- $-I I PROPULSION_mmlry 6-IS-II Chtl ldoun aml i l_ llclh_ 6-ITrans 4t_nt Peqr'f'omnce3-II Mafnst_je Perfor_nce 608S-IX Shutdomm Transient 6-10PerfomnceS-IX Stage Prol_Tlant (w11Iq_nagement SystemS-IX Pressuriza;lon System 6-13S.-IIFuel Pressurlzatto_ 6013SystemS.-II LOX Pressurization 6-16SystemS-If Pneu_ttc C_trol 6-17Pressur_ System i"

t-


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TABLE OF CONTENTS (CONTINUED)

6.S

6.9

6.10

SECTI_7.17.2

7.)

7.4

7.S

7.6

7.7

7.B

7.97, tO7.10.17.10.2

7.11

7.12

7.137.13.17.19.27.13.37.13.47.13.57.13.67.13.77.147.11.I7.14.2SECTICII

: 8.18.2|.Z.t

P_S+I! _11up |njectlon 6-175_ tern

Suooress ton 6-19System$-II Mydriu14 c 6-19System7 - $-1V8 Pg_)P_L$IO_Su_ry 7- IS-frO Chllldove and Bvtldup 7-2:rftnSJ_qg. PPrfn_'Pin_e forr|_st _rnS-IV8 Patn$t4.ne Perfo_m4_e 7-2for First _urnS-IVg ShoL4ovn Transient 7-6P_rfOrm_r.ce for First 6urn_-IV8 Park_n_ Orbit Co4st 7-6P_Jse Con


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T._BLE OF CONTE_TS (CONT_NUED)

.... tt.4. t11.t.2

11.S11.ESECTXOm12.1":2.212.2.112.2.2

........... TZ.3SECTZO_I1:3.113.213.3

........ _3.1-

Page_.._ ry )7-3_It ,_o. 1, Te_era_ure_ncr4_asa_"ns:_n_ Un:_ Electrical 11-9Sys_.e-Sa_ur_ Y [_roe_Cy Oece_lo_ 11-1SSys*.e_ ,rns}

S_ry 12-1last _tss_ra$ 12-TS-:C _ase _ressu_es 12-1"-_: =.ese PreSsures _2-1

_3 - vI[_,'CLE_E_.vAL ._YIR(_qlTSv_ar_ TJ- IS-:C Base _eal'.1_ 13-1_-': _ase _ei:ln9 T3-2

13._ _.;C/S._.: Sega_l_,on Then'_.ll 13-3

14. ) .%w_ery 14-11&.2 _-:C _nv_ron_n_41 Contr91 1_-11A.3 S-:_ .r_y_ro_encal C_ntr_l 14-214.4 "._ (nv_ror_cm_il Control 14-2|4o4.1 T_e ._',41 C_ndf_lontn4 S.ys_:4_(TCS)14-214.4.2 G4s 8ear_n_ Sys_ _erfor_mce _-S_CTZOIZ 15 - _T,_ S_?T.-S15.1 Su_a_ 1S-115.2 Vehtcle ._eesure_'ent (valutt|e_ 16.1IS.3 &Irhorne V_F Te1_t_y Sys_es IS-I(velua_tonlS.4 C-_and Radar System (valuatt4a 16.SlS.S Secure _t_e SMety Com_nd 1S-5

S_szem Evalvatto_IS.I; Cc_n_r_ and C_m_at_o_s IS4

Sy__.m Evaluat_ c_15.i.1 S_Jr7 of _r_omtnce 16.8ls._.z _am_e _,;zsfs ls-_15.7 ;r_vr4 [ngtnee_ng CltraS 36-12_EL'TIOII 16 - _ DgUU_L'T_R|ST|_16.1 S_llm_7 16-1ll.2 Miss [yilu4ttOn 1_-1S_TIOI 17 - L_UUi 2RPACT17.1 S_m_ry 17-I17.Z Tninslun_r Coest _lnevvers 17-1I7.3 Tr_eCory Per_rbat 1(ms 17-317.3.1 lnt_u4uct4on 17-3

)7.3.2 TraJK:or_ ffec:s17.3.3 Per_ueb:n_ _ec_ant s_s17.3.4 T_a'.', ve Co.nclus_ons17.4 Tri'_eC:Ory _viTua_:7.5 :P__ Co_I_

SECT:O._18 * SP=CCR_I, S_'_-_BYSECT:0.q 19 - _SFC ::;FL!_

S[_ICX 20 - LL."_R_O'z:'._ '._H:G.20.2 Oep!ovum:Z0.3 L_'; ".o scored _y1044;n:er_ace

[_vt rO_en_20.5 _-ee: Soll :n_eracz_o__0._ Locc_: _on Per_omence_.7 Yec_a_cal Systrs20.7.1 _a_-on_c _r4ve

Z_.7.4 S:ab_ 1_:y20.7.5 Ha_d Ccn_rol",er20o7.6 Loads20._ E_ec:_tcll Syst_es_.8. | _::er:es2eJ.8.2 Trace:on Ortv_ (:SCare20.8.3 g_s_.rt _t .to_ S_S_.l_20.$.4 S:ee_20.8.5 _'_-_'4_r InteSra_.or23.g Con:_ol _nd OtsplayConsole29.10 ._av_ga '. ton Sy_eu29.1I Crew S_a_to_ 29.12 The_4129.13 S?.r_c_rtl20.14 Lunar Roving Vl_dcle_4guratlonfdq_EAO|X A - _.'_OS_(REA.1 Sen_lr_A.Z Generll At_S,._h_rtc C4_

dtttO_tS it Lwach TimA.3 Su_ace _.v'_tioms at

Launch TteeA.4 ;_er _f_ _eis_r_intsA.4.1 V_n_ SPeedA.4.2 Vtn_ _t re10_A.i.3 P_J_ Vfnd _q_nenZA.4.4 Yav gfnd (_epon4_A.4.S _. l itn4 Sh_mA.4.S _t_ Idtn4 _1_ ts t_eHtg_Oy_dc aegtm

_a_e:7-5_7*_:7-_.T7-g

17.-_.

19-:

20-:20-2_.0-22_-222-2

2_2_-2_-S20420--SZC42-720-72O-7Z3-ZZ04Z0-10Z0-I0

A-1A-1

A-I

A-t


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TABLEOF' CONTENTS(CONTINUED)

Pll_e

X.5 The_odvmPl _ta A-6A.S.|- Atrmsphertc T_n_rature J.:4A.S.2 At_osghert P_ssure A*IA.5.3 At_o$_l_ert Ocms t ty J-14A.S.4 OptJcal |nclex of A-14_efral_to_A.6 Ccw_r_son of Selectecl A-14A_o$:_hertc Oatl for

S4turn Lsuncl_es_[110lX II - AS..S_Z S_G_ZF_CJIKI'

C_:F ZF,U_T; ON CKUC_ $8.1 |nt_xk_t _on B-1

vt


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, .

-.

LIST OF ILLUSTRATIONS

Figure2-I AS-SI2 Telemetry Tlme

. Olf fe_-e_3-1 Elect_ca! SupportE_u_e_ _arttal ScheNttc3-2 Olode C.h!__etall............ 4-1 _ AScent Tra_e_tOr7 PositiOn

_" 4-2 Ascent Tr_ectory S_ace-F_xed V_oclty ar_ Flt0ht

;- Pat_ Ar_'e Cormartsons, 4-3 Ascemt .'ra_ectar7Acceleration Comparl _n

;_ 4-4 0yna_ic _Ssure and ,_,ach_ur'berC_. arisons

4-S Laurch _'ealcleGrouncZtrack4-6 XnJecticr.Phase Space-

F(xed 7e:_Ity and Flightf " patll ;, _";, r_,e Coe_artsons4-7 I n.;ectie_ Phase

_. Acceleration C_ari_n51 S-IC L._I Start Box

_ Reout re_mt sS-2 S-:C E-xlinesThrust

._-3 _IC S:-_e Prnl_lsto_Performance-_.5-4 S-IC Fuel Tank UllagePressureS-S S-IC LOX Tank UllagePressure

_ 6-I S-If [mime Start TaWPerfor_mce:_ 6-2 S-11 E_me Holtum Tank._ Pressu_s:- 6-3 _II Ty_i_ml S_r_ Tank

b_Iti_mms Oum'l_ Hold

T 6-4 C_wrls_n of S-II Startv Tank Co_tttons During_/ COOT and LauecNqF 6-5 _-II S_,'_ Tank l_ill-_- Semm_e (Engine 1.:,_ i'ypi_1)_ 6-6 S-ll Englme P_ lnlet- Start _I m_tt

_r

Page Figure2-3 6-73-5 6-8

3-7 6-94-36-10

4-3

4-4 5-1244

6-134-8

_IO 6-14

4-10 7-IS-Z 7-Z5-3 7-3

7-4S-S 7-5S-9 7-6

7-76-36-4 ;4

7-96-47-10

6-57-11

6-7 7-13

vii

PaqeS-If Steady State 6-9O_erationS-:I Fuel Tank Ullage 6-14Prffssur_

S-II Fuel Fume Inlet 5-1S._ondt t!onsS-I: LOX Tank Ullage 6-15PressureS-I: LOX Pur_ Inlet 5-I8Co_dl tion$S-'i Center Engine LOX 6-20._ll_ Accumulator BleedSj__.em Perfor_nc.*S-If Center Er


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LIST OF ILLUSTRATIONS (CONTINUED)

Fggure7-147S7-167-17

....... 7-18 ....

Aceleratton at |U andDurtn_ Thrust Build-up and Launch

8-Z Loh_itu_IinaI Load_tstributlon st Time of.uax_ Bendlng ,_t,CICO a._d OECO

8-3 9endtna Moment and LoadFeb.tar Distribution atTfe_e of Kaxt_um Be_dtng_ment

8-4 AS-512 EnvelOpe ofCouOtned Loads Producfi_.I_tntmum _lfety ;qlrgtn$fm- S-IC Flights

8-S IU Vibration OurfngS-IC 8urn (Longttudtmll)

8-6 AS-S12 LongitudinalAcceleration at IU andOMDuring. Csmtof EngineCutoff

8-7 kS-S12 LongitudinalAcceleratlon at IU andoq Our4ng OutboardEngine Cutoff

8-8 A_512 Center EngfneChamfer Pressure andGimI_i PM Ar_elefat t_mO_eiml _-II Ibrm (8 ta20 _z FITter) c_mto AS-S11

Piqe Figure7-20 g-97-20

8-107-21

7-24 8-II7-24

7-25 8-127-27 8-13

9-18-2

9.28-3

9-38-4

9-48-5

9-5

8-6 9-68-7 10-I

10-28-8 10-3

10-48-g10-5TO4

AS-S12 Dynamic Responses_urina S-If Acc_mu;a_orF111 {1-1!0 Mz Ftlter)AS-S_Z S-IVB Gfm_al Block 8-10AcCelorat(nn _'_ur (n(J S-IfBurn - Longit_ina_ (8 tO20 HZ Filter}S-'V8 Gi.bal Block 8-11Acceleration and S-IfCen_er Enaine Thrust P_dAcceleration S.-'_,c_ra atT *'85 to 190 _oe_sr_i_e on S*!VB _lmbal &-1281c_k During S-;I Burn_S-51Z S-IVB LOX _mm 8-13In!et Pressure S_ec_raTra.tectory and ST-_24_ 9-2P_,at._om VeIoctty Corn-Perisons. Bo_$t-_o-EPO(Trajectory _,i_uS LVDC)Tra;ectory a_ ST-I.'4X 9-4Platform Velocity C_-;arisons, BoOSI- _-TLI(TraJe_.ory _im_s LVDC)Comparison of L_OC and 9-8Postf IIgh_ Tr_ectoryOur1n9 [POContfnuous Vent System 9-9(C:'_} Thrust . and _cceleritto__ur_ ng EPOSteering Coaw,"_IS, Ft_t 9-10S_rtng Cammmnd$, __ 9.ISPttch Plane D)m_wa|$Dw_in9 10-3S- IC Burntaw Plane O)_mqcs Ourtng 10-4S-It BurnPtt_l_ and Yav Plane Free 10-SStremm Angle of AttakDur ing S-ItPitch Plane Oy_mt$ Durt__ 10-8S.-II aw Plane 07_mfCS Owing 10-!1 -;I BurroPltch Plane Wcs O_-(m_ 10-10S-I8 First I1_

Pagu8-10

viii


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fr_

kr.

))o,

t

Ftgurt Page............... 1007 a_ Plane DynisicsDurtn9 1001G5-1VB first Burn

"I0-8 Pitch Plane Dynaplc= ,_uring lO-IZPark tmJ Orbit

10-9 Pi tch Plane Dynamics _rtng 10-13S-IVB Seemed10010 Yaw ?lane O)mamics O_n-tr_ I0-13

........ _-:v_"Sec_10011 Pitch Plane Dyr_nlcs Duff N 10-15

Tra_slunar CmIst (Sheet 1of 6)10012 AS-_12 S-IC-S-II _ep4ratlon 10-23

Otstancea.11-1 S-IVB Staae For_rd NO. 1 11-4

htter.v Vo;tage andCurrent11-2 S-IV8 Stage For_rd No. Z 11-S

Ilattery Voltage aM Current11-3 _.IVB Staee _'.ft ._o. I 11-6

httery (o_,tage an_ Current11-4 S-IV3 Staee Aft NO. 2 11-?

Battery Voltage and Curr_t!1-S S-IYB Aft hater7 _o. ! 1I-80at4114 S-Iv9 Aft htter_ .go. 1 11-10

Heawr Control Circuit11-7 IU 6010 httery Par_eWrs 1:-II11-41 |U 6029 htt_'y P,ramters II-1ZII-I IU _30 ht_ Parameters 11-1311-10 IU 6040 Battery Pirmeten 11-1412-1 S-If I1eatS_told Fc_rd IZ-ZFace Pressure12-2 S-II T_vst CAme Pressure 12-212-3 S-If He_t Skteld Aft IZ-]

Face P_sur_.13-1 5-IC ha R_tem To141 13-4

Heatl ng Rate13-2 S-IC M_tllllt r._ Tamp_rl- 13-413-3 S-II Heat Sktel4 Aft 13-SHeat late13-4 S-II Heat S_teN _ 13-6

Tmt_w_

iX

Ft_re13-5la-I14-214-314-4

14-S14-6

14-7IS-I

lf-2 IS-3lS-417-117-Z17o317-4

17-S17.817-717-820-i

2O-220-4

S-If _eat Shield AftRadtatto_ Heat LltiIU TCS Coolant CoetrolPara_e tc_'sIU S_bllmator P_rfCraanCeBurt_J A$C(._t_l_tK IU Cmq_ane_tIU TCS rr_r_llcPe_or_a_eIU "CS Sph_r Pr_ssvrtI_J :Hfttll Platfo@F"._res ;ure:u &m_SC,xz S_here P_ssvresV14FTelemetry _Isltl_and Loss "rimesC-Band Ac_tstt_on _1Loss TimCCS D_nltnk Phase LockTim (Ltftoff to TILl)COSCoverage (.'LI toLunar eaglet )Transluner Coast _0vervtev_elecl Translv_r Co_stHlnl_versGravtty-0niy Lunar ImpactTra_lL_trry Ra_aellLunar Impact TraJectm'ylltstduals wifJ! Pls,lurlilngInflut_ces Nodel_lEar ly PTC T_ie lesi411sLate FTC T_ble llestclv41sLunar Landm_ksTracking 04_ /l_lllMllltyApollo 11 UW _-3Trlvlrs4L_VPo_r UslglL_ Fender FtaLWhtt_ry no. I (Left)Tlnperil_re

Page13-614-)14-414-614-714.814-914-9I_-61S-715-915-1017-417-417-717-7

17-1017-11I7-1417-1S20-3

20-420-g2U-11

$i.


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4J


.................. 20-3 , L_V F.a_ery _. 2(Plaht) Tem_ra _re

A-I Surface ;leather _;)_c'proxtrate]y 6 |/2 HOurS_f:em Launch af AS-SlZ

A-2 SO0 _|l)_l_r _Ao_rQx_NCeT.v 6 TIZ HoursAfter Launch of _5-S|2La_u_cmTime of 13-S1Z

A-4 Id_nd DtrectJoct it LauflChTtm of AS.-SIZA-S Pitch Vtnd Veloc|ty_omone.t (W_) at Launch........ Tt_ 6f-l_S-512 ",L6 Ya_ ]_nd Velocity

ComDo_t (u z) aC LaunchTir,e of AS-.c12A-7 Ptt, Ch (Sx) and Tar (Sz)Comonent Vtnd S/tear5aC Laun(_ Ttm of 4S-51ZA-8 Relative Oevtattcn of

T_raturll and P_l_surllfr_ the I_UI- t_ I ReferenceAm_4_ere. AS-S12A*9 Rel;r.lve Oevtat4m of

Don_| ty and Absolt /t_nev_atlan of _e [_texof Refraction Finn theI_-63 Ref_e),tPnosl_,ere. AS-S12

Page20-11A-2

Ao4

A-7A-8A-9

A-IO

A-11

A-iS

_-16

X


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LIST OF TABLES

........... Table -I

....... PaaeIq $slon 0bJect 1yesAccomo1!s_me_t_ary Of SIQniftcentAn,_ I fesSumn'alry _f AnGmilfes

-T4_e- _se _wnn_ry - 2-i$|_|ffcant VL_._Ttmcs Z-4S_ma4ry1rtlbll TIN and Cam_Med Z-lO_ttch SelLqctor Events_S-S1Z/ApolIo 17 ere_aunch 3-2_|lesTOhes - "_'" -Cor_4rtr.o_ Of $'_mliflClflt 4-5TrajectOry EventsCompariSOn of Cutoff 4-6Events. r'_partson of _aratton 4-7I[ve_tsParktng Orbit Zasertto_ 4-0COnditionsTr4ns)u_r ln_ect to'_ dl-8ConditionF-I Ermine Sy_t_ns S-2k( IduG TimesS-IC Indt_|dual Standard S-6Sea Level Enqtne PerformanceS-IC Pro_Hlant _ss HistOry 5-8S-IX ENtne Perfor-4nce 5-.11AS-SIZ Flight 5-1| 6-'*_I_re_elhnt Pass HtsturyS-118 Steady St.lt_ 7.6Pa_,fori_imceFtrst Burn(STOY Open *13S-Seccmd T4_Sl1e at St_lndard AItftikeComities)S-I8 S_ody SUt_ 7-14Perfon_nce - _ Ikrn(STDV Open .17Z-SecondTtne Slice it St_nd4rdAltt_uMe Condftlons}Tv-ITB S_ h_'Ta_t 7-14I_ss W.storyS-llnlAPS Prope114mt 7-_Cansui_tten

2

3/T, - 2- I

2-22-3_"

_.: 4-I_, 4-2'_" 4-3

_. 4-S;" s-1tt;: s-2_. S-3g[i 6.'7-1i 7-2

7-3

i .

Table9"I

@-2

9-39-49*5

|0-I

10-2

10-3

10-4I1-111-211-3;" .41S-1IS,-21S-.31S-41S-S

15-2lt-316-4

P_eIner:tal Platfom Velocity 9"SC_lr| sons ( PAC$S-12Coordih4 te Syst_)_v_ga_fon Co_p4r_ so_s 9.6(PACSS-13}State 'Lector U_fferen_es 9-11it Translun_r |n_ect;o_AS*SIZ End Conditions 9-1ZCoas_ I_ase Gutdance 9"13Steeri_ Cmmae,_$ at Major[ve_tsA5-$12 ::ts_ltgn_mt ,nd 10-2Liftoff Conditions S_4ryv4_n_J_ Control Par3meter5 I0-6_rtn9 S-IC 6urnP_xlmu* Cont-_! F_rm_ers 10-7Ourlng S-IC 8urnI(axt_uu Ce.*trol Parameters 10-11Oveing S-IVB First BurnS-IC Stage &_ttc_/ Power 11-1Concept tcm$-II Stage Battery Power 11-2Co_sumPtSenS-IVS Sta_e Battery Power 11-qConSumt.tonIU 8_tery Power Consumption 11-10AS-_IZ ;qeasureNmt S4amuury 15-2AS-S12 Fltght J4e_svrene_tS i5k(iived Prior to FlightA5-$32 Xe*sur_unt I_lfv..-ct_ons IS-3AS-S12 Launc_ Ye_tr.le Tele- 15-4ue_r7 LinksC_mancl and Co_u:tatton 1S-llSystem _nd mstor_,AS-512To_11 Ye_lcle _iss - S-;C 1&-3lk_ Phase - 1(41ogrmTo_al lte_tcle _s - S-,C 16-4P_ase - PondsTotal Ye_tcle hiss - S-II !6.5Bvr_ Pl_se * [tlogrmsTotal Vehicle Mass - S-f1 16-6krn Iq_se - Pomds

xi


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LIST OF TABLES (CONTINUED)

Table Page16-S Toul Vehtcle Mass - S-IV tq 16-7

FtrsL _u_f_ Pb45e- Kilograms16-6 Tot4| Veflfcte _ss - Soly8 16-8

F_,rst Burn Phase * PoundsM4SS

16-7 Total Vehtcle Pass * S-IY8 16-9Second _rn Pl_se - I{tlegra_

16-8 Total Vehtcle Wass - S*IV8 16-10..... Secoq_ 8uTn Phase - PovndsMass16*9 F11ght Seeuence Mass 16-11Summary16-10 Mass Ct_aeacter_s&_cs 16-13Comoaristm17-1- Tran_lunar COe_L Naneuvers 17-217-2 Trajectory Parameters 17-9After JPS-Z 8urn17-3 Lunar !mp4_ Conditions 17-1217-4 Lunar Im_ct Ttme$ 17-1317-S S-IYS/IU Tracking Stations 17-1S20-1 _ollo 17 LRV Performance 20-S

Sumary20-2 Apoi lo Lunar EVA S_mary 20-S20-3 LRY Stentftcant Configurattcm 20-12

(:twingesA-I Surface (_servattons a A-3

A5-$12 Launch TtmeA-Z Sola_ Radtit$on at AS-S12 A-S

Ldq_ch Tim*, La_mCh Pad 3_q4-3 System Used to Flnsure A-SUpper Atr _11_ Data forAS-S12A-4 MazlJdun Wtnd _ 11i Wt_li_ A-lZOy_mric P_ssure Regtonfor Apello/S4turn f_)l

throvgl_ AIx)llo/Satvrn51Z vehtclesA-S xtr_e WtM S_e4r Yalm A-13

tn the mgh Oy_JJiC Presser*Regto_ for Al_ello/_4tvrAso, ,,o,,ols,,,,.,,I:P

TableA*6

6-18-28-38-4

PageA-17elected AtmospheriC ObS4L_-

vat |ons for ApollolSatvr_501 through Apollo/Satu_512 Veh_:le Launches atKennedy Space Center,Flort4aS-IC Sfgntftcant Co_flgur itto_ 11-1S*lI Significant ConflgvrltlOll 8-1Cha.noes$-IVlJ S|g_llrtcint Configura- I1-1tton C_n?e_IU Significant Co_flgvratlon I_ZChan_e5

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ACknOWLEDGEMENT

This report is published by the Saturn Flight Evaluation Working Group,composed of representatives of Marshall Space Flight Center, John F.Kennedy Space Center, and MSFC's prime contractors, and in cooperationwith the Manned Spacecraft Center. Significant contributions to the

.......evaluation have been made b).George C. Marshall Space Flight Center

Science and EngineeringAero-Astrodynamics LaboratoryAstrionics LaboratoryComputation LaboratoryAstronautics LaboratorySpace Sciences Laboratory

Saturn Program OfficeJohn F. Kennedy Space CenterManned Spacecraft Center

The Boeing CompanyMcDonnell Douglas Astronautics CompanyInternational Business Machines CorporationNorth American RockwellJSpace DivisionNorth American Rockwell/Rocketdyne DivisionGeneral Electric Company

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ABBREVIATIONS

.AC_......scension Island CT4ACS Alternating Current Power CVS

Supply CYIALSEP Apollo Lunar Surface DAC............ Experiments Package DDASANTAOSAPS.ARIAASC

ASI--AVPBDABSTCCS

C&DCCDDTCDRCECOCIFCGCMCNVCROCRPCSM

AntiguaAcquisition of Signal DEEAuxiliary Propulsion System DGUApol.l_Range.lnstrument DOAircraftAccelerometer Signal DOMConditioner DTS-Augmented Spar..Igniter EBWAddress Verification Pulse ECOBermuda ECPBoost ECSCommand and Communications EDSSystem EMRControl and Display Console EMUCountdown Demonstration TestCommander EPOCenter Engine Cutoff ESCCentral Instru_ntation ESTFacility ETCCenter of GravityCommand Module ETWCape Kennedy EVACarnarvon FCCComputer Reset Pulse FM/FMCommand and Service Module

xiv

Cape Telemetry 4Continuous Vent SystemGrand Canary IslandData Acquisition CameraDigital Data AcquisitionSystemDigital Events EvaluatorDirectionalGyro UnitDesirable ObjectiveData Output MultiplexerData TransmissionSystemExploding Bridge WireEngine CutoffEngineering Change ProposalEnvironmental Control SystemEmergency Detection SystemEngine Mixture RatioExtra-VehicularMobilityUnitEarth Parking OrbitEngine Start CommandEastern Standard TimeGoddard ExperimentalTestCenterError Time.WordExtra-Vehicular ActivityFlight Control Coa_uterFrequency Modulation/Frequency Modulation


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-

ABBREVIATIONS (CONTINUED)FMR Flight Mission RuleFRT Flight Readines_ TestGBI Grand Bahama IslandGBS Gas Bearing SystemGDS GoldstoneGDSW "-'Goldston_ WingGG Gas GeneratorGOXGRRGSEGSFCGTKGWMHAW,HDAHEHFCVHSKleoIGMIMUIUKSCLCRULETLH2LITLM

LMPLMRLOILOSLOXLRVLSSLUTLVLVDA

Gaseous OxygenGuidance Reference ReleaseGround-Supl_brtEqufpmentGoddard Space Flight CenterGrand Turk Island LVDCGuam ............... LVGSEHawaiiHolddown Arm MADHe1ium MADWHelium Flow Control Valve MAPHoneysuckle Creek MCC-HInterface Control Document MESAIterative Guidance ModeInertial Measurement Unit MFVInstrument Unit MILAKennedy Space Center MLLunar Communication Relay 140Unit MOVLaunch Escape Tower MRLiquid Hydrogen MRCVLunar Impact Team MSCLunar Module

Lunar Module PilotLaunch Mission RuleLunar Orbit InsertionLoss of SignalLiquid OxygenLunar Roving VehicleLunar Soil SimulantLaunch Umbilical TowerLaunch VehicleLaunch Vehicle DataAdapterLaunch Vehicle DigitalComputerLaunch Vehicle GroundSupport Equipn_ntMadridMadrid WingMessage Acceptance PulseMission Control Center -HoustonModularized EquipmentStorage AssemblyMain Fuel ValveMerritt Island Launch AreaMobile LauncherMandatory ObjectiveMain Oxidizer ValveMixture RatioMixture Ratio Control ValveManned Spacecraft Center

XV

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ABBREVIATIONS (CONTINUED)MSFC Marshall Space FlightCenterMSF)I.....'_a_,me


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SVTCSTCSTD&ETElTEXTLCTLITMTMRTSMTVCUCR .

USAEUSBUTVAVANVHFWES

ABBREVIAT[ONS (CONTINUED)Space VehicleTn.erm_a.l_ondit.ioningSystemTerminal Countdown SequencerTransportation, Dockingand EjectionT,_a_searth Injection - "Corpus Christi (TexasTranslunar CoastTranslunar InjectionTelemetry...............Triple Module RedundantTail Service MastThrust Vecto.r.Con_tro!.....Unsatisfactory ConditionReportU. S. Army EngineerUnilied S-BandUniversal TimeVolt An_oeesVanguard (ship)Very High FrequencyWaterways ExperimentalStationlulu Time (equivalent totiT)

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MISSION PLAN

.

The AS-Si2-fiight'{Apoil-o17 mission) to the Taurus-Llttrow site isthe twelfth flight in the Apollo/Saturn V flight program, the seventhmission planned for lunar landtng, and the third mission planned forthe Lunar Roving Vehicle. The Apollo 17 mission ts the first Apolloflight planned for night launch and for translunar injection over theAtlantic Ocean. The primary mission objectives are: a) perfomselenologtcal inspection, survey, and sumpltng of mterta!s and sur-face features in a preselected area of the Taurus-Ltttrow region; b)deploy and activate surface experiments- and c) conduct tnfltghtexperiments and photographic tasks_. The crew consists of E. A. Cernan(Hisston Commander), R_ EL Evans (CommandHodule Ptlot), andIt. H. Schmttt (Lunar Hodule Ptlot).The AS-512 Launch Vehtcle (LY) ts composed of the S-IC-12, S-II-12,S-IVB-512, and Instr_uent Unit (lU)-512 stages. The Spacecraft (SC)consists of SC/Lunar H(xluie Adal_t_ (SLA)-21), CoIand Rodule (O1)-114, Service Hodule (SH)-114, and Lunar Hndule (U1)-12. The UI hasbeen modified to carry the Lunar Roving Vehicle (LRY)-3. .Yehtcle launch from Complex 39A at Kennedy Space Center (KSC) ts plannedalong a g0 degree azimuth followed by a roll to flight aztmth of ,-approxtmtely 72 degrees measured east of true north. : Yehtcle mss atignition Is nollnally 6,530,819 111.-- ....:::..:::.-:..__.,_.: _,......The S*IC stage powered flight )nets approxletely-162 seconds; the ":'::S-I 1 stage provides powered fltght for approximately 395 seconds..The S-lYe stage first burn of approxheately 146 Seconds inserts the". _ ;:S-IVB/IU/SLA/IJt/ C_mand and Service Nodule(C_l) Into ctrcular _" m " ' '.90 n rot. altttude (referenced to the earth's equatorial radius) .i_;:-?-._:.L:.-:."Earth Parking 0rblt (EPO). ;_Vehtcle mass at Orbtti_tnserUon_;ls ,_.._ :.-:_-_-- .:-306 791 Ihe."-;_/. :_':--_,;.i'_:'::--":'-_:-;.___::._.G:':.:::/-_-_/__."t_.-_?__,.'_\:_r"._::::..- " " - . "'.-- _.._. -".,-'Z -_ --'--'L-*-," _ i>"_ _.'_;._.,_ _:_.._.-. - .'_ _'_" _ l_- " ,;.-':-_ "L. . -.... .--_......,,_.__,',:._,..,._._:.._,,_:.o_.._._-,,-__-:-._-._-_,..,._._,-..-._.,_-. .At approxtmtely 10 seconds oft_,._.l_. ;.|m_tiopi" the Vehicle is _.:.'_" 'altgned _i t_ the local :hor_z0ntal:_Cent!_s ._en i/enttng ' m ! _i" ' " " 4is initiated shorUy afta-_ .F_O.|iiserltl_i'i_l;_the-LV!alM!... _Sl_ft_)._:_-! "(SC) systems Are ch_ed:.In.'Fr_raUm :for.the :Traml_r.."Imd_Uon _.::._;..-._(TLT) burn. Shortly/mfter_[_gtm|ng _tJIme.Udrd._irwoluUm_tm; _i_. ;_;;_,i_/!4;;_the S-lYe stagel$ restlarbM_iuMl_rns_for'a_lm1_,:.lY._34T_co_ls,_:_]"_-.. : .This burn inserts the S-IyB/IU/_CSM tnto_an,mr__,_.'.,;-;__,-;- :..._-____. _.-, _-.:_a.._.-" -: -": _. -::.. * :- _ -_' ,-: -.',_,,-'_._...'_-_-i._i_J;_-_: "._"; ",'.'" _.... -

: - ; -.- :-. : -_::.."" ..- " -- _-::._ _c_e;,'_._--_._"._:i_-


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/

At 15 minutes after TLI,the vehicle initiates a maneuver to andholds inertia]-a.t1_itudeor CSM separation and docking, and CSM/LMejection. Following attitude acquisition the SLA panels arejettisoned and the SM separates from the LV. The CSM then trans-poses and docks with the LM. After ducking and latching, tile CSM/LMis spring ejected from the S-IVB/IU. Following separation of thecombined CSlVIJ1.fromthe S-IVB/IU, the S-IVB/IU performs a yawmaneuver and then an 80-second burn of the S-IVB Auxiliary PropulsionSystem (APS) ullage engines as an evasive maneuver to decrease theprobability of S-IVB/IU recontact with the spacecraft. Subsequentto the completion of the S-IVB/IU evasive maneuver, the S-IVB/IU Isplaced on a trajectory such that it wlll impact the lunar surfacein a targetarea Iocated.betlweenthe Apollo 14 and 16 landing sites.The lunar impact target Is 7.05 latitude and 8.OW longitude. Theimpact trajectory is achieved by propulsive venting of hydrogen {11_),dumping of residual liquid oxygen (LOX), and by ground-commanded --firing of the APS ullage engines. The S-IYB/IU impact will berecorded by the.setsmograph_dep19_ed durtng the Apollo 12. i4. 15and 16 missions S-IVS/IU lunar impact ts predicted to occur atBg hours 16 minutes 08 seconds after launch for nominal fltght.Several tnflight experiments wtll be flmm on Apollo 17 Includingexperiments conducted by use of tie Scientific Instrument Mndule. ,. (SIX) located in Section ! of the SM, arid flight expertmnts duringearth orbit, translunar coast, lunar orbit, and t_-ansearth coastmission phases. " _-_rtng the.85-hour ._'anslunar coast, the astronauts willstar-earth landmrk sightings, Inertial Measurement Unit _e_u_m:.alignments, general lunar navigation procedures, and mtdc_rse *corrections. At approxtmatoly 88 bours and SOmtnutes, a $orvtce :Propulsion System (SPS), Lunar Orbit Insertion (LOI) burn of 'approxtmtely 395 seconds ts initiated to insert the CSM/UI tnto a51 by 171 n at. altitude parklng orbtt. _Approxtmately two re_olu- _:_"ttons after LOI, a 22.9 secor_,, burn vlli--acLlust the orbtt .to IS by_:i!5g n mi. altitude: .The UI is entail by astronauts Cer_n and _:- /,,.:_,."Schmttt. aM checlu_Jt ts:'aC_pltshed.-: Dur|ng the itwelfth "rtvolu_-:_tL:tlon In orbit, at 110 hour_ 28 Irl_t_s;ithe IJ1Sei_rat_s f*_rm_t_)_'_:_CSMand prepares :for the lunar, des_mt..;,The _CSNts_then tnsert4d j;_(:_'.tnto an appr0xtma rely:62 n mri_:ai U .t_de)ctrcular_brMt_u*tng a/4.0 *ic_*_*.second SPS burn. The.LHDescent)_lsto_*Sysl_m'ts'_used ._ brake-?',*the LM tnto the proper landing 1Ta_ectory and to maneuver the LN ':--_during descent to the lunar 'surface. Landing at Taurus-Ltttrovts scheduled to occur at 113 hours 2 minutes., The landing stte ts .- :

r . _.

. - . ,. ;"..!_.

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sttuated at 20o10 ` North latttude and 30%5' East longitudeFollo_ng lunar landtng, three. EVALine per|_ds of 7 hours each arescheduled during-which the-astronauts _ill exnlore the lunar surfacein the LRV, collect surface samples, photograph the lunar surface.and d_ploy sc|entlflc Instrmn_ts. Sor.tles in the LAYv111 be1trotted tn red!us such that the 11fe support system capebtllty villnot be exceeded tf LRV fatlure necessitates the astronauts walktngback to the IJ.- Total stay ttm on the lunar surface ts open-ended,wtth a planned maxtmumof 75.0 hours depen_,tng upon the outcmm ofcurrent lunar surface operaUons piannlng and of real-tlme operation-al declslons.The CSH performs an orbttal plane change approxtmtely 8 hours beforerendezvous, LH 11ftoff nomtnallyoccurs at 183 hours 3 ,_tnutesinto the mtsston. The ascent stage Insertion tnto a 9 by 48 n ms1,_Itltude lunar orblt occurs approxlmtely 7 mlmJtos later. Atapproxtmtely 190.0 hours the rendezvous and docktng vith thets accompllshedoFollowlng. docktng, equipment transfer, and de_ontamqnaUon procedures,the IJq ascent stage Is JetttsoMd and targeted to tmpact the lunarsurface at a potnt approxtmtoly 9 Im from the Apollo 17 landtngstte. Tr=nsearth Injection (TEl) ts accomplished at the end of -revolution 75 at approximtely 236 h_rs and 40 mtnutes wttha 142.2second SPS burn, */--. , :,:_ ._Durtng the 68-hour trinsearth coast, the astronauts vii1 perform -.navtgaUon procedures, stor-earth-mon _tghttegs, the electro--_ . " -phorettc separation dmonstnl_lon, and as tony as three rldcem'se _correcUons. The Commnd .qodule r|lot vtl! also perform an EVA to _"retrteve ftla cassettes fr_ the SDI bays.". The_l seperates from _:the CH before re-entrjf. 5plL_dOMI Occurs- In .the Pac]ftc Ocean . _,;'*304 hours 31 mtnutes after 11flbsf.f, ':_.'. _:-- _ -"_ .*: ..... '- , -.-After the recovery qperatto.s, a-b|Ological quaruttM ts mt ]qxlesed -on the crew and OI. However, btotogtcml tsolaUon garments rill bea'vallable for use In the event of unexplained crew 111hess.

_ , _i,::_-.::- :__... . : , _

xxt ! xxll

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FLIGHT SUMMARY

!:

The tenth manned Saturn Apollo space vehtcle, AS-512 (Apollo 17 Mtsston)was launched at 00:33:00 Eastern Standard Ttme on December 7, 1972, fromKennedy Space Center, Complex 39, Pad A. The performance of the launchvehtcle and Lunar Rovtng Vehicle was satisfactory and al1 HSFCMandatoryand Desirable Objectives were accomplished except the precise deter_na-tton of the S-IVB/IU lunar |mpact point. Pre11,rinary assessments |ndtcatethat the final Impact solutt6n will sattsfy the mission objective.The ground system supporting the countdown and launch performed satis-factorily wtth the exception of the Termtnal Countdmm Sequencer (TCS).The TCS malfunct|on resultedtn'a Zh_r 40 _nute unscheduled hold.Damage to the pad, Launch Umbilical Tower and support equipment was con-sidered wintmal.The vehtcle was launched on an azimuth 90 degrees east of north, k rollmaneuver was Initiated at 13 "second that'placed the vehtcle on a flightaztmuth of 91.504 degrees east of north. In accordance with preflighttargeting objectives, the transluemr Injection maneuver shortened thetranslunar coast pertod by 2 hours and 40 minutes to compensate for thelaunch delay so that the lunar landing could be made with the same light-]ng conditions as originally planned. Available C-Gand radar and Untf]edS-Bend tracktng data plus tolemetered guldence velocity data were used tnthe trajectory reconstruction. Because the veloctty at S-I! OuUmrdEngtne Cutoff was htgher than r_ldnal, earth parking orbit Insertion con-d_ttons uere achteve_ 4.08 seconds earlier than nondnal. TranslunarInjection candtttons were achieved 2.11 seconds later than nmdnal withalt]tude 5.8 k]lameters greater than nominal and velocll_ 5.1 meters persecond less than n_tnal. CSMsepant|on m Comander Initiated S7.g :seconds earlier than nominal resulting tn an altitude 306.1 kilometersless than nemtnal and velocity 91.7 meters per.second greater,than retain al.A11s-I p p.lslon spurn parro,ed i.;.propulslon performnce was very clme'to.the predicted e_mleml. Overall stage s|to thrust m 0.310 percent hlglmr than pred]cted.;Tota] pro_. ;_-:_pellant cmsm_tlon rate m 0.16 Femmt Mgher than prea_c11_l and thetotal cmsmmd udxt.re rat]o m-O.OO2 .percent h11gher than predictS..;.5pectf|c 1repulse was 0.1.4 percent ktglm'_than predlcted._Total proFellantconsmetim frm Holddom Am release :to O.tt_ Enflnes cvtoff (0C0)"_as lou by 0.14 percent. _*Center Eaglne Cutoff (CECO) vas tntUated by'.the Instrmant Un]t at 139.30 seconds, O.OZ seconds earlier l_an:plamaed.

.' .. . "_ .; -"k. 3"

-,, - . . .

xxttt

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.. P

0EC0 was initiated by the fuel deplet|on sensors at 161.20 seconds, 0.47seconds earlier than predicted. This is well within the +5.99, -4.22second 3-sign_ limits. At OECO, the LOX restdual was 36,479 lbd comparedtO the predicted 37,235 1bin and the fuel restdu[1 _as 26,305 lbn ca_aredto the predicted 29,956 lb_. ........The S-I! propu]ston systems performed satisfactorily throughout theflight. The 5-|1 Engine Start Comnand(F.SC), as sensed at the engines,occurred at 163.6 seconds. Center Engine Cutoff (CECO) qas Initiatedby the Instrument Untt (IU)-at 461,21 seconds, 0.47 seconds earl iLr thanplanned. Outbnard Engine Cutoff (OECO), tn|ttated by LOX depletionsensors, occurred at 559.68 seconds gtvlng an outboard engtne opar_ttngttme of 396.1 seconds. Engine mtnstage performance was satisfactorythroughout f'ltght. The total stage thrust at the standard ttme sltce(61 seconds after S-II ESC)was 0,14 per_:ent below predicted. Totalpropellant flo_rate, Including pressurtzat|on flov, was 0.19 percentbelcw predtc+_l, and the stage spectftc tnpulse ws 0.05 percent abovepredicted at the standard ttm slice. Stage propellant mixture rattowas 0.36 percent below predicted. Eng|ne thrust butldup and cutofftransients were vrlthth the predicted envelopes. The propellant manage-ment system perfomance was sattsfacl_ory-thr0ugRout loadtng and fltght,and all parameters were wtthtn expected 11atts except the LOX ftne rossIndication. Propellant residuals at OECOwere 1401 1be LOX, as Iwedtctedand 2752 1tin LIt2, 107 1be less than predicted. Control of engtne wixtoreratto was acco_plfshed with the tvo-posftton pnemattca]ly operated RixbreRatton Control Valves, Relattve to ESC, the lever Engtne RIxtore Rattostep occurred 1.6 seconds eorller than predicted. The performmce of t#_LOX and LH2 tank pressurlzat|on system ms satisfactory. Ullage pressuretn both tanks was adequate to lat or exceed engine tnlet Net PostttveSuctton Pressure wintmm .rL,q_relents threughout mtnstage.The S-IVB propulsion systm perfomed satisfactorily throughout the opera-ttonal phase of ffrst and second burns and had norm1 star*,, and cutofftransients. 5-|1t3 ftrst burn ttae ms 138.8 seconds, 3.7 seconds shorterthan predicted for the actuel fltght aztmth uf 91 .S degrees. Thts d|f-ference ts composed of -4,1 seconds due to the htgher than exFectod S-II/S-IYB separation veloctty and +0.4 second due to lomr than predictedS-IYB performance. The enflne performnce durlng ftrst burn, as deter-wined from standard altitude reconstructfm analysts, devtated from thepredicted Start Tank Dtscherge Valve (STgV) open +135-seca_ ttae s11ceby -0.68 percent for. thrust and -0,14 percent for spectflc+.tqmlse, .... *The S-IVB stage ftrst burn F.._lmCtd_l_ (ECO) ms Initiated by the +-_++Launch Vehtcle Dt.crltal Cemlmter (LVOC) It 702.65 secmds. The CmttnuousVent System adeouately +regul_tt_t _ tank ullage pressure at an _tsage "level of 19.1 psta during orb t a the Ox)_e_q_-ogen lamm_ sat s-factortly achteved LH2 and LOX tank rewessurtzat|on for restart. Enflmrestart conditions vere withtn specified 1twits. S-lY8 secoml bet1 tlae .+ws 351.0 seconds, 4.0 seconds l,oa_r _ predicted for the 91.S . -+*degree flt oht aztmth. Th|s dtffereEe ts prtmm_17 dueto the l_er :+.++++,:++s-tw performnceandheavter vehicle--ss ,m,q,,j second.+. Imm,,..++'n,e iy

'+ . .+ -_.;+++,+._r:+.+. . ,++.._....-,,r._+',+ .-.+:_., .+ .+'+ .,.+.+,+ .... + ;+., - ....?.:.. o + .-+ .-+,,+_+_._..._ +XXiV

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performance durtn9 second burn, as deter_ined froB the standard alti-tude reconstruction analys|s, devtated from the STOVopen +172-secondttme s]tce by -0.77 percent for thrust and -0.16 percent for speclftc1repulse. Second burn ECOwas Initiated by the LVDCat 11,907.64 seconds,(08:51:27.64). Subseouent--to-second burn, the stage _ropollant tanksand hellum spheres were safed satisfactorily. _Jfftctent impulsewas dertved from LOXdump, LHZ CVS operation and auxtl]ar7 propulsionsystem (APS) ul;ape burn to achteve a successful lunar Impact. Two sub-seauent planned AP_ burns were used to tlprove lunar tmpact targeting.The APS operatJon Ms no_nal throughout the flight. No heltuE or pro-pellant lea[s were observed and the regulators functioned nefinally.The structural loads experter_ed durtng the S-IC boost phase were wellbelow design values. The mxtaue bendtng moment was 96 x 106 lbf-tnat the S-IC LOX tank (less than 36 percent of the destgn value).Thrust cutoff transt._nts expertcnced byAS-512 uere st_tlar to those ofI_'evtous fltghts. The mxtmt longttudtna] dynafic respnnses at theInstrument Untt (IU) _ere +0.20 g and +0.27 g at S-IC Center EngtneCutoff and Outboard Engt.he-Cutoff (OECO), respectively. The mgnttudesof the thrust cutoff responses are considered norm1. During S--ICstage boost, four to ftve hertz osottlattens _mpe detected begtnntn9at approximately 100 .seconds. The mxtmm aWlltude measured at the IUtins +0.06 g. 0sctllattons tn the four to ftve hertz range have beenobserved on prevtous fltghts and are considered to be norm1 vehtcleresponse to fl|oht envtrommnt. _ d|d not occur durtng S-IC boost.The 5-II stage center engtne L0X feedltne accmmlator successfully|nhtbttnd the 16 hertz PO60 oscillations. A peak response of +0.4 gIn the 14 to 20 hertz frequency range was measured on engine II_. Satmbal pad durin9 sto_ly-state engine operation. Ps on prevteus flights,lew a_11tude 11 hertz oscillations were experienced near the end ofS-TI burn. Peak enatne No. 1 gtuhal pad mpense vas -_0.0_ g. POGOdtdnot occur du;rng S-II beost. The POGO11udttng backup cutoff systemperforued satisfactorily durt_j the prelaunch and Irl Ight q_er_t_ons.The system dtd not produce any dtscrete outputs and sheuld not havestnce there ms no POG_. The structural loads experienced during theS-IVB st_,oe burns vere yell baler destgn values. 9urtng ftrst burn theS-IVB experienced 1or mplltude, -0,14 g, 16 to 20 hertz oscillations.The a_plltudes measured on the gtJal block were ce_parable to p_vtousfltohts and vtthtn the expected range of values. S||rllarly, S-IV8second burn produced tntor_ritte_ 1or mplltode oscillations of ,0.10 gtn the 11 to 16 hertz frequency range vhtch peaked near second burncutoff. _The Stabilized Platfom and the Gutdanc_ _ successfully supportedthe acc_pltslment of all getchmce and mvtgatton _sstm d_ecttves vithno discrepancies tn _ of the harclwre. The end conditions atParktng Orbit Insertion and Trensluna_ In_ectton ve_e at_atned vtth tnstgoMftr_rt navigation _.rrOr. Tvo anomlles related to the fl_gl_ progrm dtdoccur. At aPlmexlmtely 5421 seconds range ttm (T5 44718,8) _nor looperror tel_etry Indicated at unreasmmble change tn the jew gt_al angle ...dwlng one wlnor loop. At the re-tnttlaltzatt_ of boost ivtgatlon for

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S-XVBsecondburn the extra accelerometer readtngs nomally teleuetered fr,_,GRR to 11ftoff plus 10 seconds _ere restarted and continued throughc_t secondburn boost navtgat|on. Neither of these anomltes significantly impactednavigation, widance and control. A minor discrepancy occurred duringS-II burn, when the yaw gtmbal angle failed the zero reasunablenesstest twice, resulting tn minor loop error telewetry at 478.3 seconds(T3 +317.2) and 55g.4 seconds (T3 +398.2).All control functions and separation events occurred as planned. Enginegtmbal deflections were nomtnal and APS ftrtngs predictable throughoutpowered fltoht. All d_mamtcs were within vehtcle capability, and bend-tng and slosh modes were adecluately stabilized. The AP5 providedsatisfactory orientation and stabilization durtng parking orbit and .*rmntranslunar Injection through the S-IVB/IU passive themal control mneuver.APS _ropellar.t consumption for attttude control and propellant settltngprior to the APS burn for luner target impact _s lower than the manpredicted reoutre_ents. All separation seouences were performed asplanned. Transients due to spacecraft Separation, docking, and LunarI_xlule eJectton vere nmtnal.The launch vehtcle electrical system and EmergencyOe_ctton Systemperformed satisfactorily thr_.jghout the r_u_red period of flight.ever, the temperature of the S-IVB Aft Battery !1o. 1 Unit No. 1,increased significantly _x_e t:_ nominal control l:Mt (90F) at approxi-mately 9 hours due to mlfunctton of the prtmry heater control system.Operation of the Aft Battery No. I remtned nminal as dtd operationof all other batteries, _power supplies, tnverters, Exploding BridgeWtre firtng units, and swttch selectors.The _-IC and 5-1! ba_e pressure envtroments were conslstont vlth trends andmgnttudes observed on previous f11ghts. The S-11 base pressure en_ron-ments were consistent with trends seen on previous fltghts, althoughthe magnitudes were higher than seen on pre_ous fltghts. The pressureenvt_t _urtng S-1C/S-I) separation was yell belov mxtmm nlues.The S-IC base region therml envtroments exhibited trends and magnitudesst_lar to those seen on prevtous f11ghts except that the ambient tempera-ture under Engtne No. 4 cocoon rose mmxpectutly and at about 50 secoMs andms approxtmtel 13"C above the level eXpe_ended during previous flights.Ourt_ t.he later I_rtton of the S-IC boost, the temereture returned toherin1. T.he mxlmum cocoen temperature reached ws yell I_low the upperupper 11adt of the components under the cocoon. The base themal mtron-rants on the S-!! stage were consistent v'-_h the trends and mgnttudesseen on pr_tous fltohts and _re well belou destgn 11Mrs. Aernd3mmtcheating envtroments and S-IVB base thereto1 _lrommts were notmeasured.The S-!C stage forlrd compartaent themul envtremmt ms adequatelymlntatned although the temperature v_ lover than expe_enced duringprevious rl|ghts. The S-IC stage aft cmpart_nt e_vtrommtal condt.ttontng system performed s_tlsfactorlly. The S-II stage, emjtne caupart-L, nt conditioning system mtnta_ned the _btent _ature and thrust

xxvl


28/294

cone surface temperatures vithtn design ranges thri.'Jghout the launchcountdown. No eauipment container temperature .mea-t_rements were taken;however, stnce the external temperature were sat_fa:tor_; and therewere no problems vtth the equipment- .tn-the- containers, the thermalcontrol system apparently performed adequately. The IU stage Environ-mental Control System exhibited satisfactory performance for the durattonof the IU nrlsston. Coolant temperatures, pressures, and t'lo_ates werecontfn_ously mtntatned vJe.htn the reoulred ranaes and design ltmtts.At 20,998 seconds the weter valve logic was pUrl_sely Inhibited (wtththe valve closed)o SubseQuent temperature increases were as predictedfor this condition. -A11 data systems performed satisfactorily thr_ugheut the flight. F11_htmeasurements from onboard telemetry were 99.8 percent _el_able. Tele-metry performance was normal except for noted problems. Radio Frequencypropagation was satisfactory, though the usual tntertrerer--e due to f_ameeffects and st_g_.ng were experienced. Usable YHF data were recetvedunttl 36,555 seconds (10:09:15). The Secure Range Safety CommandSystems on the $-[C, $-II, and S-IYS stages were ready _C perform theirfunctions properly, on co_Bnd, tf flight conditions dbr4ng- launchphase had required destruct. _he s_tem properly sated the S-IVBdestruct s_tem on a connand transmritted from Bemuda (BOA) at 72_.1seconds. The performance of the Comand and Comuntcattons System (COS)was satisfactory from ltftoff through lunar |mpact at 313,181 secends(86:59:41). Madrtd, Goldstone mere receiving CC._sf_al carrier atlunar tnq_c_. Good tracking data vere rece|ved from the C-Band radar,vtth BOA tndfcattng final Loss of $|gnal at 48,4_1} seconds (13:.'_7:00).Total vehicle mess, determtne_ from postfli.aht _nalysfs, ms v#thin &.68percent of predicted from around tgnttton through S-IVB stage ftnalsht_mm. This stall variation fndicates that h_rdvare _.fghts, p_o-pellant loads, ar_l propellant utfltzatton were close to predictedvalues during fllght.The S-IW/IU Lunar Impact Iqsston objectives wre to t_pact the st_evithtn 350 I_ of the (_l_get, detendne the Impact t_me _rith_n 1 second,_nd determine the tmpect potnt Mthtn S lore. The first tm ob,lectlves _have been met. Further analysls ts required to satisfy the thtrd objective.Pased on anslysqs to date, the S-IVBIIU Imlmctad the moo_ l)ecmter 10,1972, 20:32:40.g9 (;iqT {313,180._J seconds after range zero) a*. 4.33degrees south latqtude and 12.37 degrees vest longqtude. Thqs locatqo,fs 155 ka (M n _i) froa the target Of 7 _ south latftude and 8degrees vest longitude. TI_ veloctty of the _IVBIIU at twact relattve .to the lunar surface _es 2,544 a_s _.8,346 ft/s). The tn:mrlng headtngangle yes 83.0 degrees vest of north and the angl_ relattve to the localverttcal m 35.0 degrees. T._e total ross tnpecttng the moon msapproxtmtely 13,931 kg (alqxmxtmtely 30,712 lira). Real-Mine targeting

x_ ,:t


29/294

o

activities modified the planned i'irstAPS lunar impact burn to reduce theAPS ullage burn duration. A second APS burn was performed to minimizethe trajectory dispersion from the targeted impact point.Three HSFC Inflloht Demc-stratlons _re conducted during trans!unar coast.The purpose of the Demonstrations were to obtain data in a low g environ-ment on:a.

b.Convection in a Liquid Caused by Surface Tension Gradients.Heat Flow and Convection in a Confined. Gas..........

c. Heat Flow and Convection in a Llo_Jid.The Demonstrations were conducted as planned. The data were collectedby movie camera and crew observation, was of good oualtty, and is presentlybeing analyzed. ..................The Lunar Rovtno Vehicle (LRV) satisfactorily supported the Apollo 17Taurus-Llttrow iunar surface exploration objectives. The total odometerdistance traveled durtno the three EVA's was 35.7 kilometers at anaverage velocity of 7.75 kmlhr on traverses.. The _aximum velocity .attained was 18.0 km/hr and the maximum slopes neoottated _ere 18 degreesup and 20 degrees down. The average LRV energy cons_ptton rate was 1.64amp-hours/kin with a total consumed energy of 73.4 map-hours (including14.8 amp-hours used by Lunar Communication Relay Unit) out of an approxi-mate total available energy of 242 am-hours. The navigation system _-odrift and closure error were negligible.Controllability was good. There were no problem with steering, braking,or obstacle negotiation. Brakes were ur_d at least partially on alldownslopas. Driving down sun was difficult because the concealed sha-dows caused poor obstacle visibility.lihtle the LRV had no problems vlth the dust, stowed payload mechentcalparts attached to the LRV tended to bind up. The crew described dust -as being an anti-lubricant and reported.thatthere .ms no EVA-4 capabilityin many of the stowed payload items becuse_of dust intrusion. Largetolerance mechanical items such as locking bags on the gate and the palletlock had problems toward the end of EYA-3. Only those ttem vhtch hadbeen protected from the dust performed vlthout degradatlon. _All interfaces between Cr_,'LIW a'ml ;_ "_iOa'd _re satisfactory:,The following LRV system anomalies wre noted:. : .......a. At i.ltlal -up, theUWhat ..,-yi.t/ wereht r

predicted.b. Battery No. 2 temperature indication ms off scale low at start ofEVA-3.

xandll


30/294

B..e

Ce The rtght rear fender extension was broken off at the Lunar I_dulestte on EVA-] prior to driv|ng to the Apollo Lunar Surface Expert-mnts Package stte.

: o -


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MISSION OBJECTIVES ACCOMPLIS_tMENT

Table I presents the MSFCMandatory Objectives and Desirable Objectivesas def|ned in the "Saturn V Apollo 17/AS-512 Mtsston Implelntatton Plan,"MSFCDocument PM-SAT-8OIO.IOA, dated September_29, 1972. An assessmentof the degree of accomplishment of each object|re |s show,. Discussionsupporting the assessment can be found tn other sectto.ns of th|s reportas shmm tn Table 1.

Table 1. Mtsston O_ecttves Accompltsbuent

I "

3

4

S

aO. DESlllmLE ". JrJ:l_wtlSmEIrl 01SOEPNiG'I_ _lali i

Lamch _ flight Utmtb betm 7Z i _lem .lm _ md 4inert t im I-I II IWICtm_ N pll l_lie N_ _W_q ,_lt. (nO) .... -.

q_ _ me AtliRlc md 1,_,t " " - . -- -- ,./ m S-lt_l_/S cute me plm trmskmmr ::.- - , _"' trtt_-tor_, fro) ..... _ ;- , . i_.

7

6

_k* ."- ,d.-.

. ,. -

.-_. . ..

_. ,'-_

4.1

. 4 .Z.3.7.1

_.4.4

_.4.4

17.4

htend_e ml II_ _ u l_d n J Ir lle -,, : Aml;rs_Isnet ,-., -'--':" : 17.4

: vltldm | -,_- ' *Afar 15=,ILv/s_u_wu_, _nt and_, 7.4

mlu4ul _ wmllam W s_ _ ..S-ll/lg. . .- . -'- ,: .n n m

..... . _ .,. -./ ', PI


32/294

FAILURES ANDANO_LIES

Eval_tton of the La_h Vehicle and Lunar Rovtng Vehtcle data _vealedntne anomalies, one of whtch ts considered significant. "The signi-ficant an_aly ts summrtzed In Table 2, and the other anmaltes aresumar4zed in Table 3. . ................

z,


33/294

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34/294

SECTION 1INT RODUCT ION

1.1 PURPOSE

This report provides the National Aeronautics and Space Administration(NASA) Headquarters, and other interested agencies, wi.th .the.__launchvehicle and Lunar Roving Vehicle (LRV) evaluation results of the AS'512flight (Apollo 17 Mission). The basic objective of flight evaluation isto acquire, reduce, analyze, evaluate and report on flight data to theextent required to assure future mission success and vehicle reliability.To accomplish this objective, actual flight problems are identified, theircauses determined, and recommendations made for appropriate correctiveacti on.

1.2 SCOPEThis report contains the performance evaluation of the major launch vehiclesystems and LRV, with special enl)hasis on problems. Summaries of launch _-- ....operations and spacecraft performance are included.The official George C. Marshall Space Flight Center (MSFC) position atthis time is represented by this report. It will not be followed by asimilar report unless continued analysis or new information should provethe conclusions presented herein to be significantly incorrect.

l-Ill-?

t

L

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SECTION 2

EVE,_IT TIMES

2.1 SUMMARY OF EVENTS

Range zero occurred at 00:33:00 Eastern Standard Time (EST) (05:33:00Universal Time [LIT]) December 7, 1972. Range time is the elapsed timefrom range zero, and is the time used throughout this report-un_ess 6ther-wise noted. Time from base time is the elapsed time from the start of theindicated time base. Table 2-I presents the time bases used in the flightsequence program.

Table 2-I. Time Base Summary

TIME BASE

TOTI

T2

T3T4T5

16

T7

T8

VEHICLE TIME"SECONOS

(HR:MIN:SEC)

-16.960.63

139.44

161.22559.65702.87

GROUND TIME**SECONDS

(HR:MIN:SEC)

10,978.65(03:02:58.65)

11,907.87(03:18:27.87)

18,179.88(05:02:59.88)

-16.960.63

139.44

161.22559.65702.87

10,978.65(03:02:58.65)

11,907.87(03:18:27.87)

18o180.00(0S:03:00.00)

SIGNAL START

Gutdance Reference ReleaseIU Umbilical DisconnectSensed by LVDCInitiated by LVOC 0.013Seconds after T1 +138.8SecondsS-IC OECO Sensed by LVDCS-II OECO Sensed by LVDCS-IVB ECO (Velocity)Sensed by LVDCResOrt EQuation Solutton

S-IV8 ECO (Velocity)Sensed by LYOC

Initiated by GroundCommand

*Range Time of occurrence as indicated by uncorrected LVDC clock,i.e., the time of event as tagged onl_ard, converted _.o range time.**Range Time of Ground receipt of telometered signal from vehicle.Includes telemetry transmission time and LVOC cIock correction.Figure 2-1.

2-1

6

i 1


36/294

The start of Time Bases TO, Tl, and T2 were nominal. T3, T4 andT5 were initiated approximately 0.5 seconds early, 0.4 secor_Is early,and 4.1 seconds early, respectively, due to variations in the stage burntimes. These variations are discussed in Sections 5, 6 and 7 of thisdocument. Start times of T_ and T7 were l.g seconds early and 2.l secondslate, respectively, T8 was initiated by the receipt of a grob_o'-.......command.

Figure 2-I shows the mean difference between ground station receipt timeand vehicle tagged time which may be used for precise comparisons betweenonboard guidance and navigation data that is time-tagged on6_a-?d and ....other data that is time-tagged by time of telemetry signal receipt at aground station.A summary of significant event times for AS-512 is given in Table 2-2.The preflight predicted times were _djusted to match the actual firstmotion time. The predicted times for establishing actual minus predicted ..........times in Table 2-2 were taken from 40M33627D, "Interface Control Docu_w_ntDefinition of Saturn SA-Sll, 512 and 514 Flight Sequence Program" a;idfrom the AS-SI2 Postlaunch Operational Trajecto_, (OT). The postlaunchoperational trajectory, MSFC Memorandum S&E-AERO-MFT-200-72, correctingthe earlier OT for the adjusted flight azimuth, was used because of the.-- - ......launch delay.2.2 VARIABLE TIME AND COMMANDED SWITCH SELECTOR EVENTS

Table 2-3 lists the switch selector events which were issued during theflight, but were not programmed for specific times.

2-2


37/294

-.o

300'_

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zoo,Z

_J=> 15o," !

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30.000RANGETILE, S[COlOS

, l ,, I l I2:00:00 4:00:00 5:00:00 8:00:00RANGETIME, HOURS:MINUTES:SECOMDS

* RANGETIRE OF GROUNORECEIPTOF TELEMETEREDSIGIM4.FROMVEHICLE. * RANGETIME OF OCCURRENCES INDICATEDBY UNCORRECTEDVDCCLOCK.

Figure 2-1. /6-512 Telemetry Time Difference

2-3

1


38/294

ap

Table 2-2. Significant Event Times Summarj

|Trm _v_r _:SC=IPT Ir_i|

I F.UlCSNC _- I;l_lrFwr4Ct _:1 _aSFtGPm)

Cl'uuJ_._ ICur).NE)3 S-I_ F_r.I_F 'w_.'_ TTA_T

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39/294

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%

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%

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ITEN

24

Table 2-2.

EVENT DE_C_IPv|O_

START S-II LM7 TANK MIGHPmESS_a( VE_T _C_

Significant Event Times Sunmary (Cont'd)

25 S-If LM2 eFCIRCULaTI_N PUNPSOFF

Z6 S-|CIS-|| fEPAPIt|ON COPMIN0TC FIPF SFP4_aTICN CfVICFSAk_ g_IgO W_TCR_

27 Sl ENGINF SCL_(IC JCTIVaT-ION |AV_OA_E CF FI_E|

28 S-II ENGINE SVART bGUNC(CCPWaNO |ESC)

2q S-II IG_ITI_N-ST0V CPE_

30 S-I| WIINSTaGE31S.-I! CFILLOCNN VILVES CLOSE31 S-il _IGH i_.5l _p_ NC. ! OH33 S-II HIGM 15.51EPR N_, Z ON3q S-ll S_CONO _LANE SEPARATION

COwliNg IJTTISCN S-If l_TINTERSTIGtl

35 LAUNCN ESCAPE TOWER IL_TIJETTISCN

36 ITERITIV GUIOINCE uCOE IIGI_IP_kSl I I_ITIAT[D

17 S-ll CENTER NGINI CUTOFFICECC)

38 START CF 6RTIFICIIL TAU _QQE39 S-II LOW ENGINE NIXTURE RATIO

IEffn| S_IFT IACTUILJ60 ENO CF ARTIFICIAL TAU PQO_

41 $--'I! C_TBCARC ENCINE CUTOFFIOECCI4_ S-Jl EkG|NE CUTOFF INTEPRUPTt

START OF T|_E @ASE _ |T6143 S-iV8 ULLAGE POTGR IGNITIQN4_ S-I|#S-|VB SEPARATION CC;mqANO

TC FIRE SEPARATION OEYICESANG tlTtO POTOPS

*Data not available.

eA_C_IC TuIL

iI+I.+

I+I.4

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0.0

-0.47

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2-5


40/294

Table 2-2. Significant Event Times Summary (Cont'd)

lIE,+ Ev_f f'F %t*.l; I P I Irv_,

Irla+I F_() 6 fueL C+ILtF+(mN p_jwo ,_E+I $-)vm |+_I1iP_ lSl_v P_+_)_ S-IvP wa_m_i++ srair ++ ++riICi+i PiE -U(,+50 S-IV_ UlLaGE FJSF JETTIS(N+1EmC Cr ++tl+lClat tall "CCE!Z mEGlm IEm+l_At GLJILA_CF5+ FN_ IG. P_aSE +54 BEGIN CMI FQEEI C55 S-IVB vELCCITV CblrFF

KCPPA_D _r. I trI_ST ECOI56 $-1_ VFLCCIIV CbVrFr

SP $-IVR EkRIk_ CUICCF I%IE_AbPT_START _F Time Bt_ 5 ITSI

50 g-lV6 SP5 ULLAGE ENGI_ _C. 1f_&/TICN CO-_a_{

59 $-|VO IPS ULLIG_ ENCI_ c h_. ZIG_ITICN CC-'I_C

6_ LCX T_ _ESSU_I?_11C_ rFF41 eae+IkG C++IT I&SE_riC_6Z _GI_ _SNkUVF_ ro LOCAL

H_RIZC_TAL ATTITUCE63 S-IV_ CCNTI&UCUS VENT

SYSXEW CVSI CN6_ S-lie APS VLL'_.. F'_INE N_. l

E_TCFF C(_a_L65 _-lYe APS ULLAGE EkGl_E _G. Z

CuTCFF CCPWINGb6 BEGIN ORBITAL NAVIG&T|GN

67 BEGIN .c-,.IYB nESTanT PREPIAS-TICN$_ SYJiY (F TJPE faSE 6ITBI

S_C

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*Data not available. 2-6

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41/294


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IGNITION CO_NANC00 S-JVR APS ULLAGE LkGI_,E kC. 2

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*0. t


42/294

Table 2-2. Significant Event Ti_s Summary (Cont'd)

iTEm EVENT UFS_ ivv I_,i

90 E'4GINF ul;.TLP_ QaT/G |E-r.|cr_rmFL valVE '_t-lF? I'FGI_,

ql S-IV a LPZ ITFP PwF_,GI/OIt4TIC_,

92 _, l;GIF. ' l'Em_l_At GHILa",I('r:,_3 REGIN Cl-I FI;;EIcZ,;94 S-IVB $_CCP,,._ _LJlC_CF CL_Tf'FI r

'I_P'_AND _0. I (S;-[IN_ _%rjl;.5 S-IItR IECCNC (,UI_._.Cz- CUTCIrF

4;_ S-f_ ENGINF C_TCF_ r INTE_WUPT.STIi_IT ,'IF tf"f A.,S_;t I 11"71


43/294


ITEH

111

112113114

115

116

117

118

119

120

121

122

123

124

1ZS

IZ6127

E';E_;T DESCRIPT 1,_;;

Initiate Vaneuver to LOX Ou_Att itudeS-IVB CYS _NS-IVB CVS _FFEnd tOX Dump Required forS-IVB APS Burn_IVB APS Ullage Engine _o. IIgnition Co_a_S-IVB APS Ullage En_tne _o. 2IgnitionS-IVB APS Ullage Engine _o. lCutoff CommandS-IVB APS Ullage Era. inn _o. 2Cutoff Command2rid Lunar Impact @(aneuverCo=endS-:YB APS Ulla_e [_ine 1_o. 1Ignition ContendS-IVB APS Ullage Engine .'(o. 2Ignition Coerar_S-IVB APS Ullage ngtne _o. ICutoff ComRandr_-IVB APS Ullage Ermine No. 2Cutoff CmndPassive Thermal ControlI_n_verFlight Contr_1 Co_ter PowerOff

CCS _arrter OffS-IVBIIU Lunar Isct (Hl_rs)(le:elN:SEC)

ACTUALSEC

I IP,,76n.Ol Ig,179.8

19,480.019,507.9

22,199.8

22,200.0I 22,297.8)

22,298.0

39,760.0I 40,499.8

40,500.0

I 40,601.8

40,60Z.0

: 41,510

41,532

49,26086.99586:5g:41

,we

Qt

Iet

tt

Tl_ FOR BASEACTUAL ACT-PffDSEC SEC40.1 0.0

IO00.O 0.01300.0 O.O1328.0 0.0

4020.0

4020.2

4118.0

4118.2

103.951

"Predictions not available., i i i

2-9 9


44/294

Table 2-3. Variable Time and C_nmanded Switch Selector Events

FI_CTIONm

L_ (4.8) EMR No. I 0.'Low (4.8) EMItNo. 2 ONWater Coolant ValveClosedTelemetr 7 Cal tbratorInfligi_tCalibrate 0.4TM Calibrate ON

TM Calibrate OFF

Tele,metry CalibratorInflight Calibrate OFFWater CooTant ValveOpenTelemetry Calibratorinflignt Calibrate O_TM Calibrata ON

TH Calibrate OFF

Telemetry CalibratorInflignt Calibrate OFFTelemetry CalfbratorInflight Calibrate ONTM Calibrato ON

TIN Calibrate OFF

Tele.,etr 7 CaltbratorInfliCt C.mltbrate OFF

STAGE

S-I;S-IfIU

lU

S-:V8

IU

lU

IU

S-IVB

S-I'm

iU

IU

S-Ilfl$

S-IV_

lU

RA)GETI..vE(SEC)489.0489.2780.5

3216.1

3216.5

3217.5

3221.1

3_80.5

471Z.]

471Z.S

4713.5

4717.1

5344. l

5344.5

5345.5

5349. I

TI_E FRO,_BASE(SEC)i i

T3 +327.8T3 +3280T5 +77.6

T5 "2513.2

T5 +2513.6

TS *2514.6

T5 "2518.2

TS +2777.6

TS *4009.2

T5 .4009.6

T5 +4010.6T5 +4014,Z

T5 +4641.Z

T5 "4641.6

T5 464Z.6

Ts +4646.2

REMARKSi

LV_C FunctionLVDC FunctionLVCC Function

Acquisition by C_rnarvonRevolution 1Acquisition by CarnarvonRevolution 1Acquisition by CarnarvonRevolutfon IAcouisition by CarnarvonRevolution 1L',/'DCFunction

Acquisition byHawaii Rev. IAcquisition byHawaii Rev. 1Acquisition byHawaii Rev. lAcquisition byGoldstone Rev. 1Acquisition byGoidst_e Rev. IAcquisition byGoldstc_e Rev. IAcquisition byGo!ctstone Rev. 1Acquisitlmby_oldstc_e J_v. 1

r

2-I0


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Table 2-3. Variable Time and Commanded Switch Selector Events (Contd

FI_CT !Ott

Telemetry CalibratorInfltght Calibrate ONTM Calibrate ON

TM Calibrate OfF

Telemetry Calibratorlnflight Calibrate OFFTel_etry CalibratorInf119ht ONTM Calibrate ON

TM Calibrate OFF

Telemetry Calibratorinfltght OFFTetemet_j CalibratorInfUght Calibrate ONTlqCallbrate ON

TM Calibrate OFF

Telemetry Calibra_orinfltg_t Calibrate OFF,Tel_try CalibratorIInf119ht Calibrate ONTlq Calibrate ON

LTR Calibrate OFF

Te1_try Calibratorlnf119ht Calibrate OFF

STAGE

IU

S-IVB

S-IVB

IU

lU

S-IVB

S-[VB

IU

IU

S-IV8

S-IVB

IU

IU

S-IVB

S-IVB

Iu

R_IG[ TIME(SEC)

6928. i

6928.5

6929.5

6935.1

8808. I

8808.5

8809.5

8813.1

10264.1

10264.5

10265.5

10269.1

10888.1

10888.5

10889.5

10893.1

TIME FROM BASE(SEC)

TS +6225.2

T 5 +62L5.6

T5 _226.6

T5 +6232.2

T5 +8105.2

T5 +8105.6

T5 +8106.6

T5 +8110.2

T5 +9561.2

T5 +9561.6

T5 +9562.6

T5 +9566.2

T 5 +10185.2

T5 +10185.6

T$ +10186.6

TS +10190.2

REMARKS

Acquisition byAscenslon Rev. ZAcqui$itioe byAscension Rev. 2Acquisition byAscensiOn Rev. ZAcquisition byAscension Rev. 2Acquis|tion byCarnarvon Rev. 2Acqo|$1tl_ byCarnar_ Rev. ZAcquisition byCarnarvon Rev. 2Acquisition byCarnarvoa Rev. ZAcquisition byHawaii Rev. 2Acquisition byHawaii Rev. 2Acqulsltim byXawati Rev. 2Acquisition byHawaii Rev. 2Acquisition byGol_stone Rev. 2Acqu|sJtionbyGoldstone Rev. 2AcquJsltl_ byGol_stone Rev. 2Acquisition byGoldstoem Rev. 2

2-11


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Table 2-3.

FUNCTIUN

Variable Time and Commanded Switch Selector Events (Cont'd)

Telu_try CalibratorInflight Calibrate ONTM Calibrate ON

TM Calibrate OFF

Telemetry Calibrator|nflight Calibrate OFFWater Coolant ValveClosedS-IVB Ullage EngineNo. 1 ONS-IVB Ullage EngineNo. 2 ON$-IVB Ullage EngineNo. ] OFF .S-IVB Ullage EngineNo. 2 OFFS-IVB Ullage EngineNo. I ONS-IVB Ullage EngineNo. 2 ONS-IVB Ullage EngJmeNo. I OFFS-IV8 Ullage EngineNo. 2 OFFFlight Control ComputerPower OFF AFlight Control ComputerPower OFF 9Water Coolant ValveOpen

STAGE RAr(GETIME(SEC}IU lZl7S.Z

S-IVB 12175.6

S-IVB C 12176.6

IU 1218C.2

IU 19079.8

S-IVB 22199.8

S-IV8 22200.0

S-IV8 22297.8

S-IV8 22298.0

$-lV8 40499.8

S-IV8 40500.0

S-IV8 40601.0

S-[Vg 4O602.0

IU 41521.0

IU 41532.1

IO 41554.3

TI_E FROM BASE($EC)

L

T7 267.3

T7 *267.7

T7 +268.7

T7 +272.3

T8 +899.9

T8 +4020.0

T8 *4020.2

Ts +4118.0

T8 +4118.2

T8 -22320.0 IT8 +22320.1

T8 +22421.9

T8 .22422.1

T8 +23341.1

T8 +23352.2

T8 +23374.4

REMARKS

Acquisition byAscension TLCAcquisition byAscension TLCAcquisition byAscension TLCAcquisition byAscension TLCLVDC Function

Lunar Impact BurnNo. 1Lunar l_act BurnNo. ILunar Impact BurnNo. 1Lunar Impact 8urnNo. 1Umar l_act BurnNo. 2Lunar Impact 8urnNo. 2Lunar Impact BurnNo. 2Lunar Impact BurnNo. 2CCSComand

CCS Cemwmd

LVOC Funct Ion

2-12

k

!i

t


47/294

SECTION 3LAU_:CHOPERATIONS

3.1 SUMM_RYThe around systems supportina the FS-512/Apollo 17 countdown and launchperformed satisfactorily with the exception of the Terminal CountdownSeauencer (TCS). The TCS malfur_Lion, which is discussed (n paragramh3.3, resulted in a 2 hour and 40 minute launch delay. The space vehiclewas launched at 00:33:00 Eastern Standard Time (EST) (05:33:00 UT) onDecember 7, 1972, from Pad 3gA of the Kennedy Space Center, SaturnComplex. Damage to the pad, Launch Umbilical Tower (LUT) and supnortequipment was considered minimal.3.2 PRELAUNCH MILESTONESA chronological sun_naryof prelaunch milestones for the AS-SI2 launch iscontained in Table 3-I.3.2.1 S-IC StageS-IC stage and _SE systems performed satisfactorilyduring countdownwith the exception of three failures which were subseouentlv corrected.The failures were 1_;"_- tl ........._,) C,_o a_ _.._.. Devices fS&A) (2) Remote DigitalSub-Multiplexer, and (3) F-I Engine _Io.2 Gas Generato- Igniter. TheSafe and _rm Device failed to respond to a safe command. Possiblecauses for the failure were determined to be low voltaoe, i_properinstallation, or a defective unit. The Safe and Arm Device and its mountingblock were replaced and the replacement unit performed satisfactorily.Bench tests of the suspect unit failed to duplicate the problem and dimen-sional ana;ysis of the unit and mounting block was satisfactory. Analysisdid reveal, however, that output toroue of the solenoid at the lower endof the voltage curve was marginal with respect to the toraue requirementsof the mechanical linkage of the S&A device. As a precautionary measure,the countdown procedure was changed to arm the device at T-33 minutesinstead of T-S minutes to eliminate the need for recycling to T-22minutes in the event of a hold. In addition, the provision was made toincrease the stage bus voltaae to 30 V if the unit should fail to armduring the count.At the T-9 hour scheduled hold the Remote Digital Sub-Multiplexer (RDSM)failed and an 8 ampere current surge of one minute duration was recorded.The RDSM was replaced and satisfactorily retested. The cause wasisolated to shorted ceramic capacitor (C7) in the power supply card.As a result of failure analysis it was concluded that the failure wasrandem and no corrective action is anticipated.

3-I


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Table 3-I. AS-512/Apollo 17 Prelaunch MilestonesDATE ACTIVITY OR EVEIiI

October 27, ).70december 21, 1970June 16, 1971June ;7, ;;7,",arch 24, 1972:_arCh Z4, 1772_oa,l11. 1972may 1S. 1972_ay 19. 1972June 2. 1972June 7. 1972Tune 2P,, 1972Jun_ 23, 1'J72July IZ, 1_7ZA_just 1. 1972

;,uqust 13, 197ZAu,lust 23, I.u72At_ust 28, 1972,October ]l, ]972October ]2, )972OC%o_er 20, )972._ovember I0, 1972,';ovem_er 20. !972";ovember 2_. 1972Dece_er f, 1972 I,_cen_er 7, "972 (EST)_

S-II-12 Stage A.rivalS-IVB-SI2 Stare ArrivalLunar Module (LM)-I2 Ascent Stage ArrivalL,._cr :-_o_-';_.e,t_)-12 Descent Stage ArrivalSpacecraft/Lunar .U,_lule Adapter (SLA)-21 ArrlvalCo.m,and and Service Module (C5M)-114 ArrivalS-IC-12 Staqe ._rr|valS-IC Erection on Jw_ile kaunctmr (M_.)-3S-IT ErectionLunar Rosin 9 Vehicle (LRV)-3 ArrivalInstrurw_nt Unit (I0)-512 ArrivalIU ErectionS-IV3 ErectionLauncn Vetlicle (LV) Electrical Systems Test CompletedLV Propellant OisperslonlMalfu_tion Overall Test (OAT)Co._le teL'V Service Arm OAf CompleteLRV InstallationSpacecraft (SC) ErectionSpace Vehicle (SV)/RL Transfer to Pad 39ASV _.Iectrica) Mlat_SV OAT ";o. 1 (Plugs In) _leteSY Fligh[ Readiness Test (FRT) Cm_letedRP-I LoadingCountdown D_onstraf .i_ Test (CJ)I]T) C_leCed (Wet)CDDT Completed (O_)S_,'Terminal Countdown Started (T-28 Hours)$I/ Launc_

3-2 .'.


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The F-, Eneine r:o. 2 Gas _enerator (GG) igniter installed indication waslost at T-23 hours. Both GG igniters on Engine No. 2 were replaced andthe problem was determined to be due to igniter failure. Failureanalysis revealed an error in manufacture in that solder had beenomitted from an electrical pin in the igniter, allowing intermittentcontact. The lack of solder was seen in the X-ray nicture which ism_de during receiving inspection. Corrective action taken was to reviewall remaining igniter X-ray pictures to assure no more omissions exist.3.2.2 S-II StageThe S-ii stage and GSE performed satisfactorily during the countdown.As a result of the unscheduled hold caused by the Terminal CountdownSequencer (TCS) malfunction, some systems such as the J-2 engine starttank system were required to remain active.During the first unscheduled hold at 02:52:30 tiT(T-30 seconds), S-llstage systems were safed and recycled successfully during this 65.2minute hold duration. At 03:57:41 LIT (T-22 minutes), the countdownwas resumed and continued to T-8 minutes when another hold occurred toresolve the TCS corrective action. This hold lasted 73.3 minutes andcontingency hold Option 2 was utilized. S-If systems remaining activethrough this hold were LOX system helium injection, engine actuationhydraulic system temperature control, and engine helium and hydrogenstart tanks pressurized. It was necessary to manually control enginehelium tank venting as temperature changes di tated. The engine starttanks were chilled, pressurized, and then required one rechill cycleat 05:12:00 LITfor proper temperature conditions. At 05:25:00 UT,the countdown resumed at T-8 minutes and proceeded without furtherproblems to liftoff. Electrical batteries on the S-II stage were oninternal power about 20 seconds longer than previous vehicles and wereslightly more discharged at liftoff as a result of the repeatedcountdown.3.2.3 S-IVB StageOverall performance of the S-IVB stage and GSE was satisfactory duringthe countdown operations.A hazardous gas detection sensor located at the LH2 tank vent disconnecton Swing Arm No. 7, showed an intermittent indication of GH 2 for approxi-mately l-I/2 hours from T-3 hours 30 minutes. The leak was not largeenough to cause a problem and was dispositioned acceptable for launch.To keen the engine control helium sphere pressure below the redlinelimit of 3400 psia, the sphere was vented six times using the emergencyvent during the hold period.Prior to resuming the countdown at T-8 minutes, the start tank wasrechilled to bring the te_erature below the maximun limit acceptablefor launch. After rechilling, the start tank emergency vent valve wascycled three times to keep the start tank pressure below the maximum limit.

3-3 r


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A long term decay was noted on Forward Battery No. 2, open circuitvoltaae. The open circuit voltage at the time of inst_llation was 34.74V. The voltage decayed 1.50 V over a 24-hour period. During the holdat T-9 hours, a power transfer test was performed to verify battery per-formance under loaded conditions. Battery performance was normal. AtT-8 hours 53 minutes, Battery Monitor EnaBle was turned on to providea small load in order to stabilize the battery. The battery voltagestabilized at T-4 hours. The voltaee decay was attributed to a greaterthan nominal silver-peroxide level in the battery cells. The batterymet all specifications and criteria.3.2.4 IU StageThe IU stage performed satisfactorily during the countdown.3.3 T_RMINAL COUNTDOWNThe AS-Sl2/#pollo 17 Terminal Countdown was picked up at T-38 hours onDecember 5, 1972. Scheduled holds were initiated at T-g hours fnr aduration of g hours, and at T-3 hours 30 minutes for a duration of one hour.At T-167 seconds the Terminal Countdown Seouencer (TCS) failed to issuethe "S-IVB LOX Tank Pressurization" command. When it was visually observedt_t the S-IVB LOX Tank was not being pressurized, the console operatorinitiated action to manually control S-IVB LDX Tank Pressurization. Thetank was pressurizeo, but because an interlock relay was not energizedwhen the TCS failed to issue the T-167 second command, a countdown holdwas experienced at T-30 seconds. This hold lasted for 2 hours and 40minutes during which time the TCS failure was confirmed, a "Work-Around"was investigated, and the "Work-Around" was verified at the MSFC SaturnV System Development Facility (SDF). Also during this hold the countdownwas recycled to T-22 minutes. After investigation of the failure andverification of the "Work-Around" it was concluded that the countdowncould be successfully and safely accomplished by using a jumper to bypassthe "S-IVB LOX Tank Pressurized" interlock relay and manually pressurizingthe LOX tank from the LCC. The countdown sequence w_s restarted at T-22minutes and completed successfully.Figure 3-I shows the electrical circuits associated with this anomaly andthe following is a description of the functional operation of the circuits.The T-167 second command from the TCS (Channel 3) is supplied to theMobile Launcher (ML) Integration Patch Distributor to energize relayK3 which supplies a 28V signal to the ML S-IVB Patch distributor. Thi_signal is used to initiate l) S-IVB LOX tank vent closed, 2) S-IVBLOX tank pressurization valve open, and 3) energize relay K577 "TiM forLOX Tank Pressurization." Without relay K577 energized the "S-IVBLOX Tank Pressurized" interlock relay K536 cannot be energized even if

3-4

f-T


51/294

LI_.L.,,,I:-: " _T,....__.,_loql I1 ell _'11_"_"

I'

Figure 3-I. [lectrical Support [quiF_nent Partial Schematic

3-5

Ii'


52/294

/

relay K492 "LOX Tank Minimum Low Pressure OK" is energized by manuallypressurizing the LOX tank. When K536 is not energized the "S-IVBReady for Launcn" relay K607 will not provide a signal to the ML S-ICPatch Distributor "S-IVB Ready for Launch" relay K972 to complete theinterlock chain to allow relay K465 "Swing Arm _Io.l Retract Prepara-tion Complete" to be energized. If K465 is not energized when theT-30 second TCS command (Swing Arm No. I Carrier Retract) is received,a cutoff con_nand will be initiated and a countdown hold will occur.When the above condition occurred, the absence of the TCS T-167 second com-mand was confir=,.edon the Digital Events Evaluator-6 (DEE-6) printout.Investigation of the DEE-6 printout disclosed that the T-176 second spareoutput from the TCS also did not occur. After investigation of variouscombinations of lost outputs and associated fixes, it was determined thatthe "LOX Tank Pressurized" relay K536 could be bypassed by moving the "LOXTank Pressurized Bypass" jumper from "INHIBIT" to "ON" position. Thisjumper is located on S-IVB Patch Distributor in the LCC. The failurewas simulated and the "Work-AFound" was verified at the MSFC Saturn VSDF and a decision was made to proceed with the launch using the inter-lock bypass and manual pressurization. During the successful launchall TCS outputs were obtained except the T-176 second spare output.Therefore, the bypass and manual pressurization procedures were actuallyredundant to the normal circuitry.Investigation of this failure at KSC subsequently centered on two diodeslocated in the logic circuitry of the TCS. One of these diodesinhibited the T-167 second S-IVB LOX Tank Pressurization command andthe other inhibited the spare output. The two failures are functionallyunrelated in the TCS circuitry. Excessive reverse current leakagethrough the partially shorted diodes caused intermittent operation ofTCS outputs. The two failed diodes had been in service six years.Each TCS contains 1,827 of these diodes with approximately 1500 ofthese capable of causing a launch hold or scrub if they failed betweenCDDT and launch.Testing of all similar diodes is being conducted where feasible. Of2196 diodes tested, 7 additional diodes exhibited reverse currentleakage in excess of the spezification. The diodes that failed alongwith a number of non-failed diodes from the same printed circuitboards were subjected to extensive analysis. The following four causesof failure have been postulated: I) inversion layer formation, 2)accumulation layer formation, 3) metallic precipitates in the depletionlayer cr 4) contamination in cracks partially or completely across thedepletion layer'.Since deposition of contamination in microscopic cracks (Figure 3-2)was consistently observed in the failed diodes, this is considered tobe the most probable failure mode. However, the investigation as tothe cause of the cracks and subsequent contamination deposition isstill underway and cannot be considered conclusive at this time.

3--6


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tt_o

L_4c

_ CRACKS

_%ANODE SILVERUTTON COfFFACT

_ \_t

l" 20 MILS

Figure 3-2.

GE SIN444gDIODE

Diode Chip Detail

.I

3-7


54/294

The "Work-Around" with the TCS at KSC that resulted in a satisfactoryterminal countdown would not be acceptable if a problem occurred withthe TCS during the Skylab-2, -3, and -4 countdowns due to the shortlaunch windows.The following activities will be accomplished prior to the Skylablaunches in order to eliminate the possibility of another failure.a, The diodes will be tested and replaced as required in each of the

existing TCS's to assure reliable performance.b Pad 39A and Pad 39B will be modified to provide three TCS's in each

launch vehicle ESE rather than the present one.c. Incorporate voting logic so that any t_o of the three TCS's will

assure that the proper signals are provided.d. All unused signals from each TCS will be unp_tched and grounded so

there will be no possibility of them causing problems.The above activities will reduce the probability of a false commandbeina initiated and also assure that no single electrical failurewill result in loss of the proper terminal countdown co--rid.

3.4 PROPELLANT LOADING3.4.1 RP-I LoadingThe RP-1 system successfully supported countdown and launch withoutincident. Tail Service Mast (TSM) 1-2 fill and replenish was accom-plished at T-I3 huurs and S-IC level adjust and fill line inertoccurred at about T-60 minutes. Both operations were satisfactory, therewere no failures or anomalies. Launch countdown support consumd 213,304gallons of RP-I.3.4.2 LOX LoadingThe LOX system supported countdown and launch satisfactorily. Thefill seauence began with S-IVB fill command at 12:34 EST, Decee_er 6,1972, and was completed 2 hours 40 minutes later with all stage replenishnormal at 15:15 EST. Replenishment was automatic through the firstTerminal Countdown Sequence but was switched to manual when S-IVBflight mass began cycling shortly before final countdown. This con-dition has been experienced during some previous loading operationsand is a result of trapped LOX warming in the S-IVB inlet line. TheLH2/LOX Auto Load allows for manual replenishment when such cyclingoccurs.Men LOX loading was reinitiated shortly before recycling to T-22minutes, LOX system loaic did not reestablish replenish operations as

3-8


55/294

expected. Instead, it sequenced into a dual mode configuring simul-taneously for both "vehicle replenishment" and "S-IC chilldown." Inthis posture, the S-IC slew fill valve was opened allowing LOX to bepumped directly into the stage resulting in a slight overfill. Thesystem was manually reverted to prevent further overfill. Subse-quent investigation reve_led that an S-IC discrete necessary fnrnor-hal replenishment was ,_issing when loading operations werer_su_l.A real time procedure charge to LOX/LH2 auto load, was prepared to ini-tiate the discrete manuall

saturn v launch vehicle flight evaluation report - as-512 apollo 17 mission

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