AS-510 (Apollo 15)

313 Pages·2002·14.67 MB·English

SATURN
OCTOB28E,1R91 1
39) SATPBU 5 LAIJIICB II730330 19
B~ALOATIOI OBOOBT, AS-510,
IOB (MASA) 312 p
CSCL 22c Onclas
63130 19841
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SATURVW L AUIICHVE HICLE
FLIGHTE VALUATIORIEI PORT-AS-S10
APOLLO15 MISSlOW
?RE?ARfDBY
~~HI~116Hl~AlUAllO6WORRl166ROUR
N.VOb4.L AERONAUTICS .NO SPACE ADMINISTRATION
GEORGEC . MARSHALL SPACEf ’tbl CWER
MPR-SAT-FE-‘II-2
SATURNV LAUNCHV EHICLE
FLIGHTE VALUATIONR EPORT- AS-510
APOLLOI 5 Ml SSION
PREPAREDB Y
SATURN RIGHT EVALUATIONW ORKING GROUP
.
*
p
-.*r. _ :
MPR-SAT-FE-71-2
VEHICLE FLIGHT EVALUATION REPORT - AS-510
APOLLO 15 MISSION
BY
Flight Evaluation Working Group
2 C. Marshall Space Flight Center
ABSTRACT
I
1o 15 Mission) was launched at 9:34:OD Eastern
1 July 26, 1971, from Kennedy Space Center,
Complex 39, Pad A. "The vehicle lifted off on a launch azisrrth of
90 degrees east of north and rolled to a flight azimuth of 80.088 degrees
east of north. The launch vehicle successfully placed the manned space-
craft in the planned translunar coast mode. The S-IVB/IU impacted the
lunar surface within the planned target area.
This was the first Apollo Mission to employ the lunar Roving Vehicle
(LRV) during Extravehicular Activity (EVA). The performance of the LRV
was satisfactory and resulted in extended EVA, and greatly increased the
crews lunar exploration capabilities.
All Mandatory and Desirable Objectives of this mission for the launch
vehicle were accomplished except the precise determination of the lunar
impact point. It is expected that this will be accomplished at a later
date. No failures, anomalies, or deviations occurred that seriously
affected the mission.
Any questions or comments Gertaining to the information contained in
this report are invited and should be directed to:
Director, George C. Marshall Space Fltght Center
Huntsville, Alabama 35812
Attention: Chairman, Saturn Flight Evaluation Working
Group, S&E-CSE-LA (Phone [phone])
PRECEDINPGA GEBLANKNOT~
TABLE OF CONTENTS
Pa*
TABLE OF CWLNTS iii SECTION 5 - S-It PlDpUlSloll
LIST OF llllJsTnATlm Vi 5.1 f-w 5-1
LIST OF TABLES I 5.2 s-ic Ignltlen Translennt
ACK)(OYLEO6EMNT xii Perhmmco 5-Z
ABBREVIATIo)(S xlil 5.3 S-IC mslnstage Perfommce 5-3
NlSSloN PLAN rvl 5.4 5zlC EnpIne Shutdan Tmnslrt
Perfomce 5-6
FLIW SWIARV rlx
5.5 S-K ftaga Pnlpallant~t s-6
NlSSIo)( OOJECTIVES MC(ll9llSHENT XXV s-IC Pnssurlratlal systm!l
FAILURES. RWLIES All0 DEVIATI(wS Xxvi zl66.1 S-IC Fuel Pressurlzatlan 5ystm z;
5.6.2 S-It LOX Pmssurizatlan 5ystam 5-a
SECTIOII 1 - lNTRo&JCTlo1
5.7 S-K PnLmat1c Cmtrol PmsuvB
1.1 Pulplm l-l syS- 5-9
1.2 SCOP l-1 5.6 s-IC cutge systas 5-10
SECTIOII 2 - EVENT TlllES 5.9 s-xc Pm SLppresslm system 5-12
2.1 Smy of Events 2-l 5.10 S-IC Hydnullc Systa 5-13
2.2 Varlrblc Tim mnd Cm&d SECTIOW 6 - S-11 PIDpl,UI(II
Switch Selector Events 2-l
6.1 6-l
SECTIOII 3 - UINol WEMTImS 6.2 5-11 ChlllQln md ruil~
3.1 S-W 1rens1entPerf0mcr 6-2
3.2 Pmlamch ffllcstona 6.3 s-11 IlrlnsUge hrfommce 6-4
3.3 Comtdoun Events 6.4
6-9
Propellant :ording
:*t 1 W-1 Lordlng 6.5 s-11 stag Prqmllnt
3:4:2 LOX Loedlng -t 6-9
3.4.3 L&f LoeYng 6.6 5-11 Plrssurlzrtial 5 OI Cl0
3.5 S-II Insulrtlon 6.6.1 3-11 Fual PI#surlzatan r
systm Cl0
Grand Sloport Equlpmt 6.6.2 S-II Lox Pmsurlzatlm sysol Cl2
i-66 1 GmawJ/Vehlclr Interface
3:6:2 ~~fS~lshed6mmd Support 6.7 s-11 Clwlut1c contm1
3-6 Pressure systm Cl6
6.8 5-11 Ikllu InJectlen 5ystm Cl6
SEcTIan 4 - TRUECTORV
6.9 W605uvpressla5ysta 6-16
4.1 S-rY 4-l
6.10 s-11 Hy&ellllc 5ysa c-16
Trejectoy Eveluetlon
t-f 1 Ascent Phase t:: SLCTIOW 7 - s-~n~lopusIa
41212 Patilng Olbit Phase
4.2.3 !rjec)lon Phase t:: 7.1 S-W 7-l
4.2.4 Post TLI Phase 4-9 7.2 S-IV6 tlrllldam UU Dull*
TranslmtClrFoma for
Flrat &NW 7-2
iii
\
TABLE OF CONTENTS (CONTINUED)
Page Page
7.3 S-IV8 Mainstage Performance SEC'ION 10 - CWTRDL MD SEPARATIOI
for First Bum i-2 ID.1 s-v 10-l
7.4 S-IVB Shutdown Transient 10.2 S-IC Control Systm Evaluation 10-Z
Performance for First Bum 7-6
10.3 S-II Control System Evaluation 10-S
7.5 S-IVB Parking Orbit Coast
Phase Conditioning 7-7 10.4 s-IVB Control system
Evaluation 10-7
7.6 S-IVB Chilldarn and Buildup 10;4.1 Cmtrol System Evaluation
Transient Performance for During First Bum 10-10
Second Bum 7-0 10.4.2 Control System Evaluation
7.7 S-IV8 Mainstage Performance Curing Parking Orbit lo-10
for Second Bum 7-12 10.4.3 Cmtrol System Evaluation
During SecondBum lo-13
7.0 S-IVB Shutdwn Transient 10.4.4 Control System Evaluation
Performance for Seccmd Bum 7-15 After S-IVB Second dum 10-16
7.9 S-IVB Stage Propellant 10.5 InstMent Ullt Ctmtml
Management 7-15 Components Evaluation lo-26
7.10 S-IV0 Pressurization System 7-16 10.6 Separation lo-26
7.10.1 S-IVB Fuel Pressurization
Sys tern 7-16 SECTIOn 11 - ELECTRICAL NETUDRKS AMD
7.10.2 S-IVB LOX Pressurization EIERGENCV DETECTIDK SYSTEM
sys tern 7-18
7.11 S-IVB Pneumatic Control 11.1 s-v 11-l
Pressure system T-22 11.2 S-IC Stage Electrical Systcl 11-l
7.12 S-IVB Auxiliary Propulsion 7-27 11.3 S-11 Stage Electrical Systm 11-Z
7.13 S-IVB Orbital Safing Operations 7-27 11.4 S-IV8 Stage Electrical Systa 11-3
7.13.1 Fuel Tank Safing 7-27 11.5 lnstnnent Wt Electrical
7.13.2 LOX lank Dueping and Safing 7-29 system 11-3
7.13.3 Cold Helium Dunp 7-32 11.5.1 Suay lT-3
7.13.4 Ambient Helium Dunp 7-32 11.5.2 Battery 6D!O and 6D3D Load
7.13.5 Stage Pneumatic Control Sphere Sharing Analysis 11-8
Safing 7-Y
7.13.6 Engine Start Tank Safing 7-32 11.6 Saturn V Emtgency Detection
7.13.7 Engine Cmtrol Sphere Safing 7-33 Systm (EDS) 11-14
7.14 Hydaulic System 7-33 SECTIDN 12 - VEHICLE PRESSURE ENVIRDMNT
SECTION 8 - STRUCTUiES 12.1 S-Y 12-1
8.1 SUl?lldl-j a-1 12.2 Base Pressures 12-l
17.2.1 S-K Base Pressures 12-1
8.2 Total Vehicle Structures 12.2.2 S-II Base Pressures 12-1
Evaluation
8.2.1 Longitudinal Loads 12.3 S-lC/S-II Separation Press~wes 12-l
0.2.2 Bending Hacents
8.2.3 Vehicle Dynamic Characteristics SECTION 13 - VEHICLE THERMAl ENV!rDmENT
8.2.3.1 Longitudinal Dynamic 1.i.l Subnay 13-l
Characteristics
8.2.4 Vibration 13.2 S-IC Base Heating 13-1
8.3 S-11 POGO Limiting Backup :.:.3 S-11 Base Heating 13-1
Cutoff System 13.4 Vehicle Aeroheating Themal
Envinwncnt 13-6
SECTIOK 9 - GUIDANCE XND NAVIGATIW
13.5 S-IC/S-II Separation Themal
9.1 Sumlay 9-l Envimmnt 13-6
9.2 Guidance Coqarisons 9-1
YCTIDN 14 - ENVIROWENTAL CIWRDL SVST'W
9.3 Navigation and Guidance Scheme
Evaluation 9-12 14.1 S-WY 14-1
9.3.1 Navigation Evaluation 9-12 14.2 S-IC Enviromntal Control T4-1
9.3.2 Guidax: Schetme Evaluatioa 9-16
9.3.2.1 First Coo-t Period 9-16 14.3 S-II Envirormental Control 14-3
9.3.2.2 Earth Parking Orbit 9-16 14.4 IU Environmcntai Control 14-3
9.3.2.3 Second Boost Period 9-19 14.4.1 Themal Conditioning System 14-3
9.3.2.4 Post TtI Period 9-19 14.4.2 ST-124U-3 Gas Bearing
9.4 Guidance System Conponent sys- (US) 14-5
Evaluatiw 9-21
9.4.1 LVDC and LVJA g-21 SECTlOW 15 - MTA SVSTES
9.4.2 ST-124H Stabi I!red Platform
Subsystem 9-21 15.1 s-w 15-1
15.2 Vehicle Measurement Evaluation 15-1
iv
TABLE OF CONTENTS( C~NTIN~D)
Plgc
15.3 Airborne VHF Tel-try 20.13 Structum 20-27
15.3.1 PSysetemr formance EvaluationS mty 1155--22 20.14 Lmar Roving Vehicle
15.3.2 SIC Telemetry tktr Loss oescriptim M-27
After Separation 15-s 2200..1144..21 SLRubVs ystOemve rall LksDccsrclrplptttoban ZD-27
15.4 C-Band k&r System Evaluation 15-6 20.14.2~1 T4sbility S&system ET -
15.5 Secure Range Sifety CoPmnd 20.14.2.2 Electrical Parr Stisystam
20.14.2.3 Control sod Display Console 2%
Systems Evaluation 15-6
20.14.2.4 Ravigatioo Subsystem
15.6 Camand and Comumication 20.14.2.5 Crew Station ill::
systsn Evaluation 15-6 20.14.2.6 Them1 Cmtml 20-W
15.7 Ground Engineertng Crrras 15-8 20.14.2.7 Space SIlpport Equlpocnt Lo-35
SECTlOW 16 - MASS CHARACTERISTICS APPENDIX A - ATlloSpHERL
16.1 SUilWl~ i6-1 A.1 SunWy A-l
16.2 Mass Evaluation 16-1 A.2 Crneral Atmspheric
Conditions rt hmch Tim A-l
SECTIOh 1: - LINAR IWACT A.3 surfxl? mcrvat1ons at
17.1 Sumnary 17-1 Launch Tim A-l
17.2 Translunar Coast Maneuvers 17-2 AA..44 .1 UYipnpde r StAeeird Ilcasurea~t~ ;::
17.3 Trajectory Perturbing A.4.2 Wind Direction A-2
influences 17-4 A.4.3 Pitch Wind Caponent
17.4 Trajectory Evaluatlm 17-10 A-4.4 Yaw Yind Cmpment ;::
A-4.5 Corpannt Yfnd Shows A-4
17.5 lunar Impact Condftim 17-12 A.4.6 Emma Mind Data in the
17.6 Tracking Data 17-13 High Dyomtlc Rcglon A-4
TherroQnulc Data
SECTTOW 18 - SPACECRAFT Sv)IARV la-1 i-z 1 Tcrpcratue z
A:S:Z Atmospheric Pmsur,
SECTIOW 19 - A$&D$ ;N$I@iT A.5.3 Atmospheric Dmslty A%
i 19-1 A.5.4 @tical In&x of Nefractloo A-15
SECTIQI 20 - LINAR ROVING VEHICLE A.6 Cogarison of Selected
Ataospherlc Data for Srtum V
20.1 Smly 20-l ; l mchs A-15
20.2 Deployment 20-l
APPERDIXE - U-510 SlMTFlCADT )(IIFIGUMlIOI
20.3 LRVtoStcwdp~Toad cJtyltxs
Interfaces 20-Z 8.1 Introdctlm 8-l
2D.4 ;~~~:icability
20-Z
20.5 hhecl-Soil lnteractfm 20-7
to.6 Locomotirn Pcrfcmce 20-11
20.7 khanical Systems 20-17
20.7.1 Hamanic Drirc
23.7.2 hheels tind Srspcnsloe ii-:3
20.7.3 Brakes 20117
20.7.4 Suspension nd St&ility x-17
20.7.5 Har.d Controller 20-18
20.7.6 Loa& 20-M
20.8 Electrical System ZO-;8
i5.8.1 Batteries 2D-;8
20.8.2 Traction Driwt Systa to-i9
20.63 Distribution Sgtm 20-19
20.8.4 Steering
20.86 &vp-Hour Integrator EL::
20.9 Control and Display CmsoTe 20-71
29.10 Navigation System 20-21
20.11 Crew Statton 20-21
tu.12 ThcrU! 20-23
20.12.1 sknneiy 20-23
20.12.2 Transportation Phase 20-23
29;12.3 Ertranhlcular Acttvlty
Periods 20-23
LIST OF ILLUSTRATIU’lS
FlguFc Page Figure PmJe
2-l Ground Station lime to 6-6 ~--I;,;~1 lank Ullaga
Yehirl: Time Cmversim 2-2 6-11
4-l Ascent Trajectory Position 6-7 S-11 Fuel Plunp Inlet
CC#!lpariSOll 4-2 Cmdi:ims 6-13
4-2 Ascent rrajectury Space-Fixe.‘ 6-8 S-II LOX lank Ullaga Pressure 6-14
CVaerlpoacritisyo ns and Flight Psti Angle 4-2 6-9 SCo-In: ditlnnsL OX Pmp inlet 6-15
4-3 Ascent Trajectory Acceloratim
6-10 S-:1 CeMer Engine LOX
Cmarism 4-3
Feeulinn Accwlator
4-4 Oynamic Pressure and Hach Bleea Systcn Performance 6-17
Nuder Cmparisms 4-4
6-11 S-11 Cexer Engine LOX
4-5 Launch Vehicle Ground Track 4-8 Feedline Accuulator Fill
bans lent B-17
4-6 Injection Phase Space-Fixed
Velocity md Flight Path Angle 6-12 S-II Center Eng!ne LOX
Comparisons 4-9 Feedline Accuulator Ueliu
Supply Systm Perfomance B-18
4-7 Injection Phase Acceleration
Cmparism 4-10 7-l S-IVB Start 80x and Rm
RquireRnts - First Bum 7-3
5-l S-:C LOX Start 80x Requimaents S-2
5-2 S-IC Engines Thrust Buildup 5-3 7-2 SPe-IrVfo8m anceS tea@ - StaFtiers t Rum 7-4
5-3 S-IC Stage Prcpulsim
Perfomance 5-4 7-3 S-MU5 Perforunco-
Coast Phase 1-7
5-4 Nomalized AS-510 Outboard
7-4 S-IVB Ulla* Cmditims
Engine Thrust Oecw
Durlq RepmsurlutJon'
Clbaracterlstic 5-7 Using 82/H2 Burner 7-P
5-5 S-It Fuel lank Ullage Pressure 5-9
7-5 S-Iv8 &/IQ Burner lhrIst
5-6 S-IC LOX Tank Ullage Pressure 5-10 and Pmssurmt Flawa& 7-10
5-7 S-K Purge Systcns Storage 7-6 S-IVB Start Bar and Rm
Sphere PRSSUR 5-11 Rcqulm&s - Second Rum 7-11
5-R r-l Engine Turbep~ LOX Purge 7-? S-IVB Engine Turbine Inlet
Pressure at Statim 109. Teiquratum tcqarlson -
Engine No. 1 5-12 First Bum 7-12
6-l S-11 Engine Sbrt lank 7-8 S-IVB Engine Turbine Inlet
Perfomance 6-3 Tclpcmtum Coaparism -
SecondBum 7-13
6-2 AS-510 CUM Start lank Bechili
Perfornilnce (Engine No. 3) 6-5 7-9 S-Iv8 steady State
Perfomance - Secmd Bum 7-14
6-3 AS-510 COOT Start Tank Pm-
cmdttimfng (Engine No. 3) 6-5 7-10 S-Iv8 Ltl2 UllZge Pmsurc -
First Bum and ParLtq OrbIt 7-17
6-4 S-11 Engine Pugr Inlet Start
Requl mmnts C6 7-11 S-M Lli2 Ullage Fmssurr -
6-5 S-11 Steady State Operatlm 6-7 Scaescto nd Bum and lrmslmar 7-w
vi
LIST OF ILLUSTRATItXlS (CONTINUED)
Figum FigW
?-12 S-IV8 Fuel Purp Inlet 9-5 LVOC/21 OaylBPTRadlus mC
Conditions - First Bum 7-19 Velocity cceprrisan aL EPO g-9
7-13 S-Iv9 Fuel Punp Inlet g-6 AS-SIG Acceleration and CVS
Condltlms - Second Bum 7-20 Thrust During EPO 9-10
7-M S-IV0 LOX Tank Ullage Pmssure- 9-)-I L&al Ilcasumd Velocities
First Bum and Earth Parking at liftoff 9-14
wit 7-21
9-8 2 Accelemrrter Float
I-15 S-IV8 LoI( Plpp Inlet Oeflectlen Befom Liftoff 9-14
Conditions - First Bum 7-23
g-9 2 Inertial Velocity - Manuel
7-16 C-IV8 13X Pup Inlet Pulse Comt 9-1s
Conditions - Sccmd Bum 7-24
9-10 Rate-Li=lted PI tch S6nrlng
7-17 S-IW Cold Hellu Supply Colrnd - AS-510 First Bum 9-17
HIStOry 7-25 9-11 Rate-Li~lted Vr Steering
I-18 Pncwtic Regulator Discharge Cound - AS-510 First Bum 9-12
Pmssure 7-26
9-12 Rate-Llalted Pitch Steering
7-19 S-IV6 LOX Dup andorbital Cawed - AS-510 Second Bum 9-20
Safing Sequence 7-29
9-13 Rate-Lldted V*r Steering
7-20 S-IW LOX Tmk Ullage PITSSUR. Cwmand - AS-510 Second Bum 9-20
Secmd Bum and Translunar
coast 7-30 9-14 ST-12411 kcelerater and
Sym Plckoff Oeflectlons
7-21 S-NE LOX aY, Par-w Aear Liftoff g-22
Histories 7-31
10-l Pitch Plane Dyn.&a During
8-l longltudlnal Accelwatim at S-It Bum 10-3
IU and 01 Owing Thrust Buildup
andLawxh a-2 lo-2 van Plme oynaics lhlrlng
S-K Bum 10-4
B-2 lmgltinal Loed at Time of
10-3 z$-Of-Attack lhwlng S-K
Ma;l~mBendlng tkmnt. CECO
10-6
g-3
8-3 kndlng~ntanJNoma~ load IO-4 ~l;;h,tl~ne Dynwlcs Ikrlng
Factor Distributia, at Tlrr of 10-a
Haxlnr8cnding mt 0-4 lo-5 ',aw,P:z @n&a Ourlq
a-4 IU Accelemrter Rsponsc s lo-9
Owing Peak 4-5 Hertz Respunse l&6 Pitch Plane -a Ikrlng
(Longltudlnal) U-5 S-11 Flnt Bum IO-11
8-S IU nd CM Lengltudtnal 10-l VW Plme @#n&a Owing
Acceleration After S-K CEO0 8-5 S-IVB Fint Eum 10-12
8-6 IU and M Lengltudlnal lo-8 Pitch Plam Dynmlcs During
Acceleration After S-IC OECO 8-6 Parking Orbit lo-13
8-7 AS-HO/AS-509 Acceleration and lo-9 Pitch Plane Dyn~ics hwlng
Pressum Osclllatlons bring S-IV6 Second Bum 10-M
S-11 Bum (8 to 20 Hz Filter) B-7
10-15 V-Plm Bynalcs &wing
B-8 AS-510 Pig Inlet Pvessura md S-1W Second Bum W-15
Thrust Pad Acceleration
Oscillotlans During Accwlator lo- 11 Pitch Plnc Gynalcs ckwlng
Fill Transient (1 to 110 Hz lrmslmar Coast (Wet 1 lo-17
of 5)
Filter) 0-0
10-12 AveragePItch Contml
a-9 S-M Stage Vibration Ennlepes a-10
Thruster Thrust After
9-1 lmjectoy and ST-12W? Lox m lo-23
Platfom Velocity C-risen. 10-13 Pltcb. Vrr. md Roll Plme
Boost-To-W0 (Trejectoy lllnus t@IaiCS hWiq Tf3(S hlct 1
NW 9-2 of 2) 10-24
9-2 LVOC/21 nsy CWT x Posltlm 10-14 Saturn V Staging Motlan IO-27
and Velocity Caparlsans at
EFO 9-6 lo-15 AS-510 Separatim Mstance lo-28
9-3 LVa/Zl Day -1 v PosItIOn lo-16 AS-510 Thrust Decay lo-28
end Velocity Coparlsons at 10-17 SIC Lox m Pmsum and
EPO Themal tnvirolmt 10-29
9-4 lVOC/21 OqV QOT 2 Position IO-18 S-K/S-II Scparetim Olstmce
f~a Velocity Colperlsans et Yltb mm? Retrolbton lo-29
vii
LIST OF ILLUSTl?ATIONS (CONTINUED)
Figure Figure Pdge
11-l S-Ii% Stage rorrard No 1 17-5 Real lime and Postflight
Battery Voltage and Current II-4 Lunar Impact Points 17-9
11-Z S-IVU Stage Forward No. 2 17-6 TCS and APS lhrust
Battery Voltage and Current 11-5 Perturbations 17-10
II-3 S-IVB Stage Aft No. 1 Battery Ii7 Early Tracking Inconsistency
Voltage and Current 71-6 and Passive Thcnnal Control
Oscillattons 17-11
11-4 S-IV8 Stage Aft No. 2 Battery
Voltage and Current 11-7 17-9 Lunar Lantirhs of Scientlflc
Interest 17-l)
11-5 6010 battery Measurements 11-10
li-9 Lunar Inpact Targeting
11-C hD20 Battery Rearurements li-11 Considerations 17-15
il-7 6030 Battery Measurenents 11-12
17-10 Tracking Data Avalldbllity 17-15
11-e 6D4D battery Heasurewntr 11-13
2D-1 LRV Traverses 20-3
12-I S-IC Dase Heat Shield
29-2 EVA 1 Slope Distribution 20-5
Differential Pressure 12-t
20-3 EVA 2 Slope Oistribution 20-5
12-Z S-11 Heat Shield Fonrrd
Face Pressure 12-Z 20-4 EVA 3 Slope Distribution 20-6
12-3 S-11 Thrust Cone Pressure 12-3 20-5 SW of EVA's 1, 2 and 3
Slope Distribution 20-6
12-4 S-11 Heat Shield Aft Face
. Pressure 12-3 20-L Grain Size Distribution
curves from Apollo 15 Lunsr
13-l S-IC Sase Region Total
Heating Rate i3-2 Soil Sampler and LSS (YES
Mix) 20-7
13-Z S-lr Base Region Gas
20-7 LRV Energy Cons-d 29-12
Temwra ture 13-2
20-g Lundr Surface Roughness 20-13
13-3 S-IC kbient tas Temperature
Under Engine Cocoon 13-3 20-9 MSFC CaputerHodel Lstiu&
of Maximm LRV Speed an
13-4 S-Ii Heat Shield Aft Heat
%lOOth ndi2 LW Range PSO
Rate 13-4
Surface 20-14
13-S S-11 Heat Shield Gas
29-10 MSFC Computer Model EstiuW
Recovery Temperature 13-4 of Maximun LRV Speed on
13-6 S-11 Heat Shield Aft Perfectly Smooth Surface 20-14
Radiation Heat Rate 13-5
20-11 MSFC ColputerProgrm
13-7 Forward Location of Separated Estimates on LRV Yheel
Fla on S-IC Stage 13-6 Slip Versus Slope Angle
14-l IU TCS Coolant Control lClder Full Throttle
Paraznsters 14-Z (Maxiaura Velocity)
Conditions 20-15
14-Z IU Sublimator Perfonance
20-12 LRV Battery Temperatures
During Ascent 14-4
for EVA-l 20-24
14-3 IU TCS Hydrauiic uerfonuance 14-5
20-13 LRV Battery Temperatures
14-4 Ill TCS GN2 Sphere Pressure 14-6 for EVA-2 20-24
14-5 Selected IU Canponent 20-14 LRV Battery Tcapcratures
Temperatures 14-6 for EVA-3 20-25
14-6 IU Inertial Platfon jw2 20-15 LRV Battery Tenpcratures
Pressuras 14-7 During Cooldam 1 20-25
14-7 IU GBS GY2 Sphere Pressure 14-7 20-16 LRV Battey TeDperatwes
Dving Cooldcnm 2 20-26
15-l VHF Tellcaety Coverage
S-rY 15-5 20-17 Deployed LRV Ylthout Staed
Payload 20-28
15-2 C-Band Radar Coverage
Sumnary 15-7 20-18 Control dnd Display Cms~le 20-31
15-3 CCS Coverage Smary 15-9 20-19 Deployrrnt Sequence 20-36
17-l lranslunar Coast Maneuvers A-l Surfdce kather !l~g
Overvieu 17-5 &worimdtely 1 i/Z Houn
17-2 Docking and LM Ejection Before Launch Jf AS-510 A-2
Maneuvers 17-S A-2 500 Millibar Mdp Approximately
17-3 First Lunar Impact Targetinfl 1 :/2 kWrS kfOR Ldtdlch Of
rbneuvers 17-7 AS-510 A-3
A-3 SCa’dr Wind Speed dt Launch
17-4 Cawarison of Accwwlated
Lw:Jitudina? Velocity Change 17-8 T'a of AS-510 A-6
viii