Apollo 11 Final Flight Plan

8/6/2019 Apollo 11 Final Flight Plan

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APO LLO II

APOLLOAS-506/CSM-IO7/LM-5FINAL FLIGHT PLAN

JULY l, 1969

Fligh t P lanning Branch

G. M. Col tonFligh t P lann ing B ranch

?. A. Guil!oryFligh t P lann ing Branch

Aoproved by: /- y ,'--/ /


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ACKNOWLEDGMENTSAcknow ledgment is made to Messrs. R ichard Rogers, W illiam K illian andSpencer Ga rdner for the ir techn ica l support in the prepara t ion of theApollo II F ligh t P lan .View s of the ea rth and the P 52 s ta rs show n in the F ligh t P lan w eretaken from the documen t, Views from the CM and LM During the F ligh tof A po llo II (M iss ion G ).The CSM and LM attitude in formation was taken from the documen t,Lunar O rbit A ttitude Sequence for M ission G .


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TABLE OF CONTENTS

Abbreviations iiiIntroduction xi

SECTION I - GENERAL

I. MissionDescription l-l2. SummaryFlight Plan (TLC-TEC) I-53. Summary Flight Plan (Lunar Orbit) I-64. LM Power Descent Profile I-75. CSMBurnSchedule I-86. LM Burn Schedule I-97. Lunar Landing Site Data l-lO8. Landmark Tracking Data l-lO9. Flight Plan Notes 1-13

SECTION II - UPDATE FORMSI. Update Forms Table 2-I2. CSM Maneuver Update Pads 2-23. LM Maneuver Update Pads 2-27

SECTION III - DE TA ILED TIME LINEI. LaunchPhase 3-I2. TLI-T&D 3-3, 3-43. Translunar Coast Activities

a. Cislunar Navigation 3-7, 3-17b. LM Familiarization 3-35c. Lunar Orbit Insertion 3-47


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SECTION III CONT'Dc. Undocking 3-67d. Touchdown 3-69e. EVA 3-77f. LMLiftoff 3-90g. LMActive Docking 3-94h. LMJettison 3-97

5. TEI-TEC 3-1016. Entry 3-135

SE CTIO N IV DE TAILE D TE ST O BJE CTIVE SI. Detailed Test Objectives 4-I2. Test Objective/Mission Activity Cross Reference 4-23. TestObjectives 4-6

SE CTION V - CONSUMABLE SI. RCSPropellant Usage 5-22. SMRCSBudget 5-33. CMRCSBudget 5-224. SPSBudget 5-235. LMRCSBudget 5-256. DPSBudget 5-317. APSBudget 5-328. CSMEPSBudget 5-369. LMEPSBudget 5-41I0. LMECSBudget 5-45II. PLSSBudget 5-50

SE CTIO N VI - SUMMARYFLIGHT PLAN


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ABBREVIATIONS

ACCE L A cce le romete rACN AscensionACT ActivationACQ AcquisitionAE A A bort E lec tron ics A ssemblyAGS Abort G u idan ce Subsys temAH AmpereHoursALSCC Apollo Luna r Surface C lose-up CameraALT AltitudeAMPor amp AmpereANG AntiguaANT AntennaAOH Apollo O pera tion s H andbookAOS Acqu is ition of S igna l or A cqu is ition of S iteAO T A lignmen t O ptica l Te lescopeAPS Ascen t P ropu ls ion SubsystemARS A tmosphere Revita liza tion SystemATT AttitudeAUX AuxiliaryAZ AzimuthBAT BatteryBDA BermudaB io B io-Medica l D a ta on Voice Down linkBP Barber PoleBT BurnTimeBU BackupBW Black & WhiteBRKT BracketCAP COM Capsule Commun ica torCAL _ Ca lib ra tion A ng leCAM CameraCB Circuit BreakerCDH Constan t D e lta A ltitudeCDR CommanderCDU Coupling Data UnitCEX Color ExternalCIN Color InternalC IRC C ircu la r iza tionCK CheckCM CommandModuleCMC CommandModule ComputerCMD CommandCMP CommandModule Pilot


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FLT Flight_I Frequency ModulatedFOV Field of Viewfps or FPS Feet per secondFT or ft FeetFTO Flight Test ObjectiveFTP Full Throttle PositionGBI Grand Bahama IslandsGBM Grand Bahama (MSFN)GDC Gyro Display CouplerGDS Goldstone, CaliforniaGET Ground Elapsed TimeGETI Ground Elapsed Time of IgnitionGLY GlycolGMT Greenwich Mean TimeG&N Guidance and NavigationGNCS Gu idan ce N av ig a tion Con tro l S ys temGNM GuamGYM Guaymas, MexicoH2 HydrogenHA Apogee AltitudeHAW HawaiiHBR High Bit Rate (TLM)HD Highly DesirableHGA High Gain AntennaHI HighHp Perigee AltitudeHSK Honeysuckle (Canberra, Australia)HTR HeaterHTV USNSHuntsvilleICDU Inertial Coupling Data UnitID IdentificationIGA Inner Gimbal AngleIGN IgnitionIMU Inertial Measurement UnitINIT InitializationINT IntervalometerIP Initial PointISA Interim Storage AssemblyIU Instrumentation UnitIVC In te rveh icu la r Commun ica tion sIVT Intravehicular Transfer


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LA LaunchAzimuthLAT LatitudeLBR LowBit Rate (TLM)LBS or Ibs PoundsLCG Liquid Cooled GarmentLDG LandingLDMK LandmarkLEB Lower Equipment BayLE C Luna r E qu ipm en t ConveyorLFH Lunar Far HorizonLGC LMGuidance ComputerLH Left-handL/H Local HorizontalLHE B Left-h and E qu ipmen t B ayLHFEB Le ft-hand Forw ard E quipmen t BayLHSSC Left Hand S ide S torage Con ta inerL iO H L ith ium Hydrox ideLLM Lunar Landing MssionLLOS Landmark Line of SightLM Lunar.ModuleLMP Lunar Module PilotLNH Lunar Near HorizonLOI Lunar Orbit InsertionLONG LongitudeLOS Loss of Signal or Loss of SiteLPO Lunar Parking OrbitLR Landing RadarLRRR or LR3 Laser Ranging Retro-ReflectorLS Landing SiteLT LightLTG LightingLV LaunchVehicleL/V Local VerticalLVPD Launch Veh ic le P ressu re D isp la yM MandatoryMAD Madrid, SpainMAN ManualMAX MaximumMAXQ MaximumDynamic PressureMCC M idcou rse Correc tionMCC-H M ission Con trol Cen ter - Houstonor MCCMDC Main Display ConsoleMEAS Measurement


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MGA Mddle Gimbal AngleM/I Minimum ImpulseMIN MinimumMLA Merrit Island, FloridaMNVR ManeuverMPS Main Propulsion SystemMSFN Manned Space F ligh t Ne tworkMTVC Manual Thrust Vector ControlN2 NitrogenNAV NavigationNM Nautical MilesNOM NominalNXX NounXX02 OxygenOBS ObservationO/F Oxidizer to Fuel RatioOGA Outer Gimbal AngleOMN I Omn id irec tiona l A n tennaOPS Oxygen Purge SystemORB OrbitalORDEAL O rbit R a te D isp lay E a rth and Luna rORIENT O rien ta tionOVHD OverheadP Pitch or ProgramPAD Voice UpdatePCM Pulse CodeModulationPC Plane ChangePD I Powered Descen t In it ia tionPGA Pressure Garment AssemblyPGNCS Primary Guidance Navigation Control SectionP IPA Pulse Integra ting Pendulous AccelerometerPLSS Personal Life Support SystemsPM PhaseModulatedPOL Polarity or PolarizingPRE Pretoria, South AfricaPREF PreferredPREP PreparationPRESS PressurePRIM PrimaryPROP ProportionalPSE Passive Seismic ExperimentPT Point


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PTC Passive Thermal ControlPWR PowerPX Program XXQty QuantityR Roll or RangeR&B Red & BlueRAD RadiatorRCDR RecorderRCS Reaction Control SystemRCU Remote Control UnitRCV ReceiverRED USNSRedstoneREFSMMAT Reference Stable Member MatrixREG RegulatorREQD RequiredRH Right-handRING RingsiteRLS Radius of Landing SiteRNDZ RendezvousRR Rendezvous RadarRSI Roll Stability IndicatorRT Real TimeRTC Real Time CommandRXX Routine XXSA Shaft AngleS/C SpacecraftSCE Signal Conditioning EquipmentSCS Stabilization Control SystemSCT Scanning TelescopeSEC SecondarySECO S-IVB Engine Cut-offSECS Sequential Events Control SystemSEP SeparateSEQ SequenceS-IVB Saturn IV B(Third Stage)SLA Service Module LMAdapterSLOS Star Line-of-SightSM Service ModuleSPOT Spot MeterSPS Service Propulsion System


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S.V. State VectorSWC Solar Wind CompositionSw SwitchSXT SextantT EPHEM Time of Ephemeris UpdateTA Trunnion AngleTAN Tananarive, MadagascarTB TimeBaseTCA Time of Closest ApproachTD&E Transposition Docking & LM EjectionTEC Trans Earth CoastTEl Transearth InsertionTEMP TemperatureTERM TerminateTEX Corpus Christi, TexasTGT TargetTIG Time of IgnitionTLC Trans Lunar CoastTLI Translunar InsertionTLM or TM Te leme tryTPF Terminal Phase FinalTPI Terminal Phase InitiationTPM Terminal Phase MdcourseT/R Transmitter/ReceiverTRANS TranslationTV TelevisionTVC Thrust Vector ControlTWR TowerUS United StatesV VelocityVAN USNS VanguardVHF Very High FrequencyVLV ValveVI Inertial VelocityVOX Voice KeyingVXX Verb XXW/O WithoutWRT With Respect toWTN USNSWatertown


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aV Velocity Change (Differential)_VC Velocity Change at Engine Cutoff_R Position Change (Differential)8-balls Flight Director Attitude Indicator (FDAI)

CAMERA NOMENCLATUREEL/250/BW-BRKT Electric Hasselblad/250mm Lens/B lack & White film -Camera B racketINT _f5.6,250,INF) Intervalometer 1

(f-stop 5.6, shutterspeed=250 sec,Infinity)16mm/18/CEX-BRKT 16mmCamera/18mm Lens/Color FilmMIR (fS,250,INF) 6fps External-Camera Bracket

Mirror (f-s top 8, shu tterspeed1= _-5_O -sec, Infin ity)6 frames per sec


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SYMBOL NOMENCLATURELUNAR PENUMBRA (OCCURSPRE LO ll)

SPACECRAFT SUNSET-H ON EYSUCKL E 85FT D _SH COVERAGE-DARKNESS (UMBRA)

-MSFN LO S-SPACECRAFT SUNRISE

.LUNAR P ,E N UMBRA ( OC CU RS P RE LO ll)J- LUNARSURFACE/ WINDOW

EARTH _----_" _/_ "7(ALWAYS) i\_'_../j_

_ DOWN \(5-_ S-BANDHGAX, OPTICS--S -BAND STEERABLE

SUBSOLAR PO INTI MSFNAOS

'MADRID 85FT DISH CO VE RAG E

I .GOLDSTONE5FTD!S_COVERAGE

LUNAR TERMINATORSPACECRAFT SUNSETDARKNESS


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INTRODUCTION

Th is Fligh t P lan has been prepa red by the Fligh t P lann ing B ranch , F ligh tCrew Support D ivis ion , w ith techn ica l support by TRW Systems.This document schedules the AS-506/CSM-IO7/LM-5 operations and crew activitiesto fulfill, when possible, the test objectives defined in the Mission Re-quirements, G Type Mission Lunar Landing.The tra jec tory pa rameters used in th is F ligh t P lan a re for Ju ly 16, 1969launch, with a 72 launch azimuth and were supplied by Mission Planning andAnalysis Division as defined by the Apollo Mission G Spacecraft OperationalTrajectory.The Apollo II F ligh t P lan is under the con figura tion con trol o f the CrewProcedures Control Board (CPCB). All proposed changes to this documentthat fall in the following categories should be submitted to the CPCB viaa Crew P rocedures Change Request:I. Items that impose additional crew training or impact crew procedures.2. Items that impact the accomplishment of detailed test objectives.3. Items that result in a significant RCS or EPS budget change.4. Items that result in moving major activities to a different activityday in the F ligh t P lan .5. Items that require a change to the flight data file.The Chief, Flight Planning Branch (FCSD) will determine what proposed changesfa ll in the above ca tegories.Mr. T. A. Guillory will act as co-ordinator for all proposed changes tothe Apollo II Flight Plan.Any requests for additional copies or changes to the distribution lists ofthis document must be made in writing to Mr. W. J. North, Chief, Flight CrewSupport Division, MSC, Houston, Texas.


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SECTION I - GENERAL


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M IS SION D ESCR IP TION

I. Launch and EPO (Duration 2:44) LIFT OFF - 2:44 GET(a ) Nom ina l launch time is 9 :32 E DT , Ju ly 16, 1969, w ith a laun ch

w indow dura tion of 4 h rs. 24 ra in .(b) Earth orbit insertion into a I00 nm circular orbit at II rain.

43 sec . a fter lift-off(c) CSH systems C/O in earth orbit(d) O ptiona l IHU rea lig n (P 52) to th e pad RE FS rIH AT durin g the firs t

n ight period(e ) TL I occu rs a t 2 :44 :26 G E T over the P ac ific O cean durin g the

second revolu tion . (S ee Table I-I fo r bu rn da ta ).

2 . T ran s luna r Coast (D u ra tion 73 :10) 2 :44 - 75:54 G E TA fter TLI, wh ich p laces the spacecraft in a free luna r return tra jec-tory, the fo llow ing major even ts occur prior to LO I:(a ) Transposition, docking and LH ejec tion , inc luding S IVB photo-

graphy(b) Separation fror.1 SIVB and a CSH evasive maneuver(c) S IVB propu ls ive ven ting of prope llan ts (s ling shot)(d) Two series of P23 cislunar navigation sightings, star/earth hori-

zon , cons isting of five sets a t 06:00 GE T and five sets a t 24 :30GE T


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(f) Passive thermal control (PTC) will be conducted during all periodswhen other activ it ies do not require differen t a ttitudes.

(g ) LM inspec tion and housekeep ing(h ) LO I l , pe rformed a t 75:54 :28 GE T, ends the TLC phase .

3. Lunar Orbit (Duration 59:30) 75:54 - 135:24 GETLOI Day (Duration 25:00) 69:00 - 94:00(a) LOIl(b) P hotos of ta rge ts of opportun ity(c) LOI2(d) Post LOI 2 LM entry and inspection. S-Band/VHF B Voice

tests w ill be conducted.(e ) P ost LO I 2 P seudo landma rk track ing (one se t of s igh ting s)

(See Table I-4)(f) Rest period of 9 hours

DO I and E VA Day (D u ra tion 28 :00 ) 94 :00 - 122 :00 G E T(a ) Docked LM ac tiva tion and checkou t(b) Docked land ing s ite landmark s ig h tin g (one se t of s igh ting s)

(See Table I-3)(c ) Undocking and sepa ra tion(d) DO I th ru land in g (S ee F ig ure I-3 P ow ered D escen t)(e ) LM post touchdown and s imu la ted lifto ff


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(i) EVAprep(j) EVA for 2 hours 40 minutes(k) Post EVA(1) Rest period (LM) 4 hours 40 minutes(m) Rest period (CSM) 4 hours 50 minutes

Ascen t and TE l D ay (Dura tion 25:00) 122 :00 - 147 :00 G E T(a ) LM L ift-O ff a nd Inse rtion(b) LM ac tive rendezvous

CSlPCCD HTP I

Braking(c) Docking(d) L I.I je ttison(e) TEl(f) Rest Period

4. Lunar Orbit Particulars (Average Values for a 60 x 60 nm orbit)(a ) Revolu tions s ta rt a t 180 long itude(b) Revolution duration - l hr. 58.2 rain.


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(f) S/C orbital rate - 3/min. (.05/sec)

(g) Lighting change at fixed ground point - lWest/Rev.(h ) Horizon v is ib ility + 20 se lenocen tr ic ang le on the

lunar surface(i) O ne luna r deg ree on luna r su rfa ce is 16.35 nm(j) Site 2 will be visible (3 sun angle) at REV. 7(k) S/C subvehicle point to horizon 327 nm.

5. T ran sea rth Coas t a nd E n try (D u ra tion 59:39) 131:52 - 195:03 G E TTransea rth coast beg ins w ith TE l a t 135:24 :34 GET and consists ofthe follow ing major even ts:(a ) Th ree m idcourse correc tions a re schedu led a t TE l + 15, E l - 23

and E 1 - 3 hours w ith AV nom ina lly zero.(b) CM/SM separation takes place at 194:51 GET and Entry Interface

occurs a t 195:03 GET.(c ) Sp lashdown w ill occu r in th e P ac ific O cean a t a long itude of

about 172.4 West a t 195:17 GE T. Th is w ill occur approx ima te ly25 m inutes prior to sunrise loca l time.


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TABLE I-3 LUNAR LAND ING SITE DATA

DAY SITE DESIG LATITUDE LONGITUDE ILAUNCH AZIMUTH/ 2LAUNCH AZIMUTH/'SUN ELEVATION SUN ELEVATION

JULY 16 2(IIP6) 0042'50"N 2342'28"E 72/10.5 108c/13.5 0932 EDT 00.71388889N 23.70777778E(00.6914N) (23.7169E) 3

JULY i8 3(lIPS) O021'lO"N 0117'57"W 89.295/II I08/13 I132 EDT 00.35277778N 01.29916667WJULY 21 5(IIPi3) O!40'41"N 41"_53'57"W 94.6775/9.7 I08/II.7 1409 EDT 01.67805556N 41.89916667WData From TJ memo, Accuracy E stimates, Landing S ite Landmarks,May 12, 1969, TJ-69-499oi Sun E leva tion Ang les A re For Approx ima te ly 27 Hours A fte r LO I, Is t O pportun ity"r T

im!oLo Inc ludes 2nd Opportun ity TL I3 Da ta From MPAD m emo, landing site coordina tes for G ,June 12, 1969, 69-FM41-181.

TABLE I-4 LANDMARK TRACK ING DATAJu ly 16 Launch

LANDMARK DELTADESIG. LATITUDE LONGITUDE ALTITUDESUNEL(nm)

A1(Pseudo) 2N 65 30' 000.00 432.000N 60.500EIP(130) l 53'N 28o42E 000.00l .885N 28.726E130(Prime 0115'56"N 23o40'44 '' -OOl.68 8.5 LDG SITE 2) 01.26555556N 23.67888889El(Ol .24307N) (23.6880E)123(Alternate 0030'I 9"N 2453'20E -001.71LDG SITE 2) 00.50527778N 24.88888889E


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TABLE I-4 LANDMARK T RACK ING DATA (CO NT 'D )Ju ly 18 Launch

LANDMARK DELTADESIG. LATITUDE LONGITUDE ALTITUDESUNEL(nm)IP(GI) OI6'N 3219'E0.267N 32.317EGI(129) 0117'06"N 2344'37"E -001.97 2601.28500000N 23.74361111EIP(143) O0I8'N 323'EO0.300N 3.383E143(Prime 0036'51"N 0104'39"W -O01.Ol 9LDG SITE 3) 00.61416667N 01.07750000W150(Alternate 0016'59"N 0125'43"W -001.01 -LDG SITE 3) 00.28305556N 01.42861111W147(Alternate 0003'42"N 0116'36"W -000.99 -LDG SITE 3) 00.06166667N 01.27666667W


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FLIGHT PLAN NOTES

A. CrewI. Crew designa tions are as follows:

Designation Prime BackupCo_nander (CDR) Armstrong LovellCommandModule Pilot (CMP) Collins AndersLunar Module Pilot (LMP) Aldrin Haise2. Crew positions during the mission are as follows:CSM LM

Left Center Right Left RiqhtLaunch thru TLI CDR LMP CMPT&Dthru Entry CMP CDR LMPMannedM CMP CDR LMP

3. The crew will eat and sleep simultaneously throughout the mission.Eat periods will be normally l-hour duration, with additional activ-ities held to a minimum during this time frame. Sleep periods willnormally be 8 to lO hour duration with two 4 to 5 hour sleep periodswhile the LM is on the lunar surface.

4. Activity PGAConfigurationLaunch to insertion PGA's with helmet & gloves (H&G)Insertion to TLI PGA'swithout H&GTLI to evasive mnvr PGA'swith H&GTLC& LOI l&2 Constant wear garmentsLM activation & checkout PGAwithout H&G(CMP H&G donned for la tchcocking & CDR/LMP H&Gdonned for pressure in tegritycheck and cab in reg check)Undock in g th rough touchdow n PGA 's w ith H&G excep t CMPw ithout H&G a fter DO ITouchdown th rough p re lift-off PGA 's w ithou t H&G excep tfor CDR/LMP simulated count-

down & E VALiftoff through LMjettison PGA's with H&G (exceptH&G off a fte r docking )LM je ttison th rough sp lashdown Constan t wear ga rmets


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5. Two crew sta tus reports via a ir-to-g round commmunica tions w ill bemade by the flig h t c rew during each ac tiv ity day. The firs t re -port w ill be g iven a fte r the firs t mea l of the day and w ill con -cern the sleep obta ined during the previous sleep period. Thesecond report w ill be g iven follow ing the fina l mea l of the dayand w ill concern the radia t ion dose rece ived during the prev ious24 hours and medica tion taken if any. The follow ing in forma tionshould be logged:a. Food Consumptionb. E xerc isec . Used feca l bags marked as to crewman and GE T

6. Negative reporting will be used in reporting completion of eachchecklist.7. Continuous CSM biomedical data are automatically transmitted to the

ground.8. LM biomedica l sw itch ing is performed manua lly by the LMP from undock-ing to docking as scheduled in the timeline .

9. A ll onboard gage readings w ill be read direc tly from the gages.and w ill not be corrected by the appropria te ca libra tion factors,B . Photog raph iPhotographic requirements were derived from the follow ing:a . Lunar Surface O pera tions P lanb. Photograph ic Opera tions P lanCo P roceduresI. CSM

Crew procedures ca lled out in the fligh t p lan may be found in thefollowing documents: ,{_ 1a . Apollo O pe ra tions Handbook - CSM-I07 (AOH ), Volume 2b. Crew Checklis tc . CSM Rendezvous P rocedured. Abort Summary Documente. Apollo Entry Summary Documentf. Photographic Operations Plang. Descent Procedures Documenth. Ascent Procedures Documenti. Lunar Landmark Tracking A ttitude S tudiesj. Lunar Orbit Attitude Sequence for Mission Gk. Data P riority Documents


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2. LMCrew procedures ca lled out in the fligh t p lan may be found in thefollowing documents: VC_,_ La. Apollo O pera tions Handbook LM-5 Volume 2b. Crew Checklis tc. LM Rendezvous P roceduresd. LM Descent/Ascent Summary Documente. Luna r Landing Phase Photograph ic Opera tions P lanf. Da ta P riority Documentsg. E VA P roceduresh. Apollo Lunar Surface Opera tions P lan

D . Communica tionsI. Genera la . CSM and LM HBR da ta transm iss ions in luna r orbit w ill norma l-

ly requ ire the use of the h igh ga in or steerab le an tennasb. During commun ica tions, the spacecra ft w ill be referred toby name (Apollo II) and MCC-H w ill be re fe rred to as H ous ton .c. The preferred S-Band communica tions are:Tl) CSMTaT Uplink Mode 6 (Voice, PRN, and Updata)

(b) Downlink Mode 2 (Voice, PRN, TLM-HBR)(2) LMTa) Uplink Mode 7 (Voice, Updata)(b) Downlink Mode l (Voice, TLM-HBR)d. LM voice recorder has a maximum utilization of lO hours. This

recorder will be used during LM operations to record all LMvoice data during undocked operations (27 hours 42 minutes).This recorder will be operated in the VOX mode.e. A small portable voice recorder will be carried in the CM tobe used at the discretion of the crew as a voice recorder back-up. This recorder will not be transferred to the LM for useduring undocked opera tions.f. The S-band"squelch" will be on during the sleep periods in or-der to prevent MSFN fade-out noise from disturbing the crew.

2 . DSE O pera tiona. The DSE will normally be operated via ground command except forspecial cases where the operation is time limited. In these casesthe crew may be asked to rewind the tape.b. During the earth orbit period when the CSM is not over a MSFNstation, CSMTLM-LBR data will be recorded on the DSE and will bedumped during the pass over the US and over CRO prior to TLI ifpossible.c. DSE will be used for CSMHBR and voice recording during all CSM


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e. During PTC using the HGA REACQ commun ica tions mode the DSEw ill be used to record LBR da ta when the HGA is not in theMSFN field of view.f. D uring luna r orbit LM opera tions , the DSE w ill be used to recordLM-TLM-LBR data during a ll docked LM activ ites tha t occur on theluna r fa rs ide. For undocked LM ac tiv ites on ly DO I w ill be record-

ed as VHF rang ing is requ ired.g . DSE w ill be used to record a ll H _BRen try da ta du rin g the bla ckou t

region.3. Launch - Earth Orbit Phasea . OMN I B and VHF LE FT w ill be se lec ted fo r lift o ff. O MN I D w ill

be se lec ted by the crew during boost phase if the launch azimu this less than 96 or OMN I C if the launch azimuth is g rea ter than96 . OMN I D w ill p robably be the best an tenna for ea rth orb it.b. VHF Dup lex B w ill be used for launch , a nd S imp lex A for ea rth

orbit operations.c. VHF Simplex A will be used for entry to be compatible withrecovery forces communica tions.4. Trans lunar and Transearth Coast Phase

The translunar and transea rth s leep commun ica tions mode w ill be asfo llows. The CSM x-ax is w ill be p laced norma l to the ec lip ticp lane. The CSM w ill be ro lled a t a ra te of approx ima te ly th reerevolu tion per hour. During the nea r ea rth sleep periods priorto 30 hours GE T (ra nge less th an 120K nm ) omn i a n tennas B and Dw ill be used. D uring the othe r s leep pe riods (beyond 120K nm)th e h igh ga in an tenna may be requ ired (in the RE ACQ mode). TheREACQ configura tion w ill provide approximate ly 210 degrees of HGAcoverage per CSM/LM revolution or 35 minutes of MSFN coverage perhour. The REACQ con figura tion w ill a lso a llow MCC-H to use rea ltime con tro l to se lec t TLM HBR or LBR and to dump the DSE duringeach spacecraft revolution.

5. Lunar E xplora tion Phasea. Normal CSMcommunications between MSFN/LMwill be by S-Bandduring the lunar exploration period.b. If additional communications capability is required theS-Band erectable antenna will be deployed by the EVA crewmanand will be utilized for all LM/MSFN/CSMcommunications.c. Durin g periods when both crewmen are EVA , the "AR" pos ition(Relay Mode) will be the normal communication mode on each ofthe Extravehicular Communication System (EVCS). The CDRwill relay the LMP VHF voice and data to the LM which inturn w ill re lay to MCC-H via S-Band.


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E . CSMNotesI. Electrical Power System and Water Managementa. Spacecra ft lift-off switch positions are listed in the ApolloOpe ra tions Handbook (Volume 2) for CSM 107.b. The CSM will remain fu lly powered up throughout the m iss ion(CMC, IMU and SCS in the "opera te" configuration and opticspower-up as required).c. Fuel ce ll H2 and 02 purg ing is scheduled as follows H2 approx-imately every 48 hours and 02 approximate ly every 12 hours.d. The hydrogen and oxygen VAC ION pumps w ill be inactive th rough -out the mission.e. Potable wa ter w ill be ch lorina ted once a day before each sleepperiod, sta rting w ith the First sleep period (GET 13:30).The POT H20 inle t valve w ill be opened pre launch.f. FC purges and waste water dumps will not be scheduled withinone hour prior to optica l sightings.g. Waste H20 dumpin9 will be managed to allow:-(T )---Max imum QTY :85-90%(2 ) M in imum QTY:25%(3) At LOI:QTY : 75%(4 ) A t CM -SMSE P :QTY = 90% to 100%(5) No dumping a fter MCC3 un til a fte r LO I(6) Dumps w ill be performed (if requ ired) w ith in 2 hours pre-ceding MCC maneuvers(7 ) In luna r orbit if dump ing is required, dumps w ill be per-formed immediately prior to sleep periods(8) The wa te r dump w ill not be opera ted in the au toma tic modeat anytime during the missionh . The cryogen ic heate rs w ill be in AUTO during the m ission andthe fans w ill be opera ted manua lly. The fans w ill be cycledfor one minu te before and afte r each sleep cycle .

i. The batteries w ill be charged according to the follow ingschedule:Time Battery5:20:00 B12:20:00 A48:10:00 B80:25:00 A103:30:00 B148:00:00 A154:00:00 B

2. E nvironmenta l Control System and Cabin Pressurizationa . One C02 odor absorber filte r (L iOH canister) is changedapproximately every 12 hours or if C02 partia l pressure is


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P37 BLOCK DATAGETI XXX:XX DESIREDIMEOFIGNITION

(HR:MIN)ZVT XXXX(FPS) TOTALVELOCITYFMNVRLONG +XXX(DEG) LONGITUDEFTHELANDINGP OINT FOR ENTRY GUIDANCEGET400K XXX:XX TIMEOFENTRYINTERFACE

(HR:MIN)


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P 27 UP DA TEPURP V V VIGF T 304 .)1 INDEX INDEX INDEX

O2O3O4O 5O6

"_ 07bo

1 11 21 31 41 51 61 72O2 1

O '_ 22O_. 23_ 24

N34 HRS X X X X X XMIN X X X X X X X X i

NAV CHECK SEC X X X XN43 LAT 0 0LONG [

IALT + 0 + 0_i


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SPA +XX.X(DEG) BSSPITCHANGLENCOASFORMA NE UVE R A TTITUD E CK


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SXP +X.X(DEG) BSSXPOSITIONONCOASFORMA NE UVE R A TTITUD E CKLAT +XX.XX(DEG) LATITUDEANDLONGITUDEFTHELONG YXXX.XX(DEG) LANDINGPOINTFORENTRYGUIDANCERTGO +XXXX.XNM) RANGEOGOFOREMSINITIALIZATIONVIO +XXXXXFPS) INERTIALVELOCITYAT .05G FOREMS INITIAL IZAT IONGET(.05G) XXX:XX:XX.XX TIMEOF .05G(HRS:MIN:SEC)SETSTARS XX (OCTAL) STARSFORBACKUPGDCALIGN

XX (OCTAL)R, P, Y XXXBEG) ATTITUDEOBESETIN(ALIGN) XXX(DEG) ATTITUDEETTWFORBACKUPXXX(DEG) GDCALIGNULLAGE X(jETS) NO.OFSMRCSJETSUSEDANDXX.X (SEC) LENGTHOFTIMEOF ULLAGEHORIZON/WINDOW XX.X (DEG) WINDOWMARKINGAT WHICHHOR IZON IS PLACED AT A

SPE CIF IE D T IG (ATT CK )OTHER ADDITIONALEMARKSOICEDUP BY MCC-H


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P76 UPDATE PAD

PURPOSE+ 0 0 j + 0 0 HR N33+ 0 0 0 j +10 0 0 MIN TIG+ 0 _, + 0 SEC

AVX N84[ AVYAVZPURPOSE -oo. i'_+ 0 0 ' [ + 0 0 HR N33 o_

+ 0 0 0 + 0 0 0 MtI'4 TIG, j ! , ,+ 0 I + 0 SECAVX N84I AVY

i i _ AVZ', I / PURPOSE+ 0 0 + 0 0 HR N33+ 0 0 0 + 0 0 0 MIN TIG+ 0 + 0 SEC

o. ! AVX N84.o io I AVYAVZ._ I PURPOSE

_: + 0 0 + 0 0 HR N33+ 0 0 0 + 0 0 0 MIN TIG+ 0 + 0 SEC

AVX N84AVYAVZ


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P76 UPDATE PADPURPOSE XXXXX PURPOSEFMANEUVERN33TIG XX:XX:XX.XX TIMEOFIGNITION

(HR:MIN:SEC)N84&VX XXXX.X(FPS) COMPONENTSF_VY XXXX.X(FPS) &VAPPLIEDLONG_VZ XXXX.X(FPS) LOCALVERTICALXIS

AT TIG (LM)


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CSI ONE


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II GETI XXX:XX:XX.X GETOFCSIOnE(HRS:MIN:SEC) BURN

81 DELTAVX XXXX.X(FPS) LOCALVERTICALDELTAVY XXXX.X (FPS) VELOCITYCOMPONENTSDELTAVZ XXXX.X(FPS) OFCSI ONEBURN

N X THEFUTUREPSIDALCROSSING (A POLUNEOR PE RILUNE ) OFTHE ACTIVE VE HICLEAT WHICH CDH SHOULDOCCUR

CSI TWO , THREE , FOURSAME AS ABOVE EXCEPT CSI TWO , THREE , FOUR

CDH13 GETI XXX:XX:XX.X GETOFCDH

(HRS:MIN:SEC BURN81 DELTAVX XXXX.X (FPS) LOCALVERTICALDELTAVY XXXX.X (FPS) VELOCITYCOMPONENTSDELTAVZ XXXX.X(FPS) OFCDHBURNTP I

37 XXX:XX:XX.X GETOFLMTPI(HRS:MIN:SEC BURN81 DELTAVX XXX(FPS LOCALVERTICAL

DELTAVY XXX(FPS VELOCITYCOMPONENTSDELTAVZ XXX(FPS OFTPI BURN59 _V (LOS) XXX(FPS VELOCITYOMPONENTSALO NG THE LINE

OF S IGHT TO TARGETLOSBT X:XXMIN:SEC BURNDURATIONLONGTHE L INE OF SIGHTP22 PAD

T2 XXX:XX:XX.XX GET AT WHICH


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(HR:MIN:SEC) LANDMARKLOS IS35 ABOVE LOCALHORIZONTAL

NM(NORS) XX.X(NM) DISTANCEFLANDMARK NORTH ORSOUTH OF ORBI TALTRACK

89 LAT +XX.X(DEG) LATITUDEFLANDMARKLONG 7XX(DEG) LONGITUDEFLANDMARKALT ALTITUDEFLANDMARK

ABOVE OR BELOW MEANLU NAR R AD IU SNOMINAL LM IGNITION TIMESCSI II GETI XXX:XX:XX.X NOMINALET

(HRS:MIN:SEC) OFLMCSI BURNPC33 GETI XXX:XX:XX.XX NOMINALET

(HRS:MIN:SEC) OFLMPLANECHANGEBURNTPI 37 GETI XXX:XX:XX.XX NOMINALGETOFLM

(HRS:MIN:SEC) TPI BURN


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THIS PAGE INTENTIONALLY LEFT BLANK .


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LUNAR ENTRYAREA

X X X X X X R0.05GX X X X X X P 0.05GX X X X X X Y 0.05G

GET HORCKX XX X X X P0 ' 0 LAT N61

LONGX X X X X X MAX G+ + V400K N600 0 - 0 0 400K

+ + RTGO EMS+ + VO

RRTX X X X RET0.05G+ 0 0 + 0 0 DL MAXN69

mr- + 0 0 + 0 0 DLMIN _:"-C --Z + + VLMAX Z_-- zDZ+ + vLMIN

._X_X X X X X DOX X X X RETVCIRCX X X X RETBBOX X X X RETEBOo ,,,4 Do. X X X X RETDROX X X X X X X X SXTS

-- _ 0 + 0 SFT


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TARGE T L IN E

R .05G XXX(DEG) SPACECRAFTMUGIMBALANGLESP .05G XXX(DEG) REQUIREDORAERODYNAMICY.05G XXXDEG) TRIMAT.05GGET XXX:XX:XX TIMEOFENTRYATTITUDE(HORCK) (HRS:MIN:SEC) HORIZCHECKATE! -17 MIN.P XXXDEG) PITCHATTITUDEORHORIZON(HORCK) CHECKTE -17MIN.LAT +XX.XX(DEG) LATITUDEOFTARGETOINTLONG +XXX.XX(DEG) LONGITUDEFTARGETPOINTMAXG XX.X (G's) PREDICTEDMAXIMUMEENTRYACCELER_,TIONV4OOK +XXXXXFPS) INERTIALVELOCITYATENTRY

INTERFACE400K -X.XX (DEG) INERTIALFLIGHTPATHANGLEATE NTRY IN TE RF ACERTGO +XXXX.X(NM) RANGEOGOFROM05GTOTARGETFOR EMS IN IT IA LIZA TIONVIO +XXXXXfps) INERTIALVELOCITYT ,05G

FOR EMS IN IT IA LIZA TIONRRT XXX:XX:XX REENTRYEFERENCEIMEBASED

(HRS:MIN:SEC) ONGETOF PREDICTED400K(B ET S TA RT )RET.05G XX:XX TIMEOF.05GFROM00K(RRT)(MIN:SEC)DLMAX +X.XX (G's) MAXIMUMCCEPTABLEALUEOFP RE DICT ED D RA G L EVE L (F RO M CM C)DLMIN +X.XX (G's) MINIMUMCCEPTABLEALUEOF

P RED IC TE D D P,AG LE VE L (FROM CMC)


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E ARTH O RBIT E NTRY UP DATE


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AREA XX-X RECOVERYREA FIRST3 D IG ITS DENOTES REVIN WHICH LANDING O CCURS.LAST DIG IT DENOTESRE CO VE RY A RE A A ND SUP PO RTCAPABILITIES

AVTO XX.X(FPS) AVDUETOENGINEAILOFFEMS

RO,05G XXXDEG) SPACECRAFTMUPO.05G XXX(DEG) GIMBALANGLESEQUIREDY O.05G XXX(DEG) FORAERODYNAMICRIMA T 0.05G .EMSRTGO XXXX.XNM) RANGEOGOFROM.05G TO TARGETVIO XXXXXFPS) INERTIALVELOCITYAT .05G FOR EMS

INITIALIZATIONRETO.05G XX:XX (MIN:SEC) TIME FROMRETROFIRETO .05GN61LAT +XX.XX(DEG) LATITUDEOFIMPACTLANDINGPOINTLONG +XXX.XX(DEG) LONGITUDEF IMPACTLANDINGPOINTN66RET XX:XX(MIN:SEC) TIMEFROMETROFIRE.2G TO2GDRE(55) +XXXX.XNM) DOWNRANGERRORAT .2G

RETRB XX:XX(MIN:SEC) TIMEFROMRETROFIRETO RE VE RSE B ACK UP


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BA NK A NG LERETBBO XX:XX (MIN:SEC) TIME FROMRETROFIREOB EG IN NING O F COMMUN ICA TIO NS

BLACKOUTRETEBO XX:XX (MIN:SEC) TIME FROMRETROFIREOENDOF COMMUNIC AT IONS B LACKOUTRETDROG XX:XX (MIN:SEC) TIME FROMRETROFIREODROGUE CHUTE D EPLOYMENTCHART UPDATE90/FPS XX VALUES USED TO RE-PLOTDRE90) _XXX BACKUPNTRYHART_V AND DOWN RANG E E RRO R

(DRE) @ 90 BANKANGLEPO ST B URNPO.05G XXX(DEG) PITCHANGLE@ENTRYINTERFACEEMSRTGO +XXXX,XNM) RANGEOGOFROMO.05GTO TARGE T FO R E MS COUNTE RVIO +XXXXXFPS) [email protected] XX:XX (MIN:SEC) TIME FROMRETROFIRETOO.5GRET02G XX:XX (MIN:SEC) TIME FROMRETROFIREOO.2GDRE +XXXX.XNM) DOWNANGERROR

BANK AN XX/XX (DEG/DEG) BACKUPBANK ANGLE FOR SCSENTRY: ROLL RIGHT/ROLL LEFTRETRB XX:XX(MIN:SEC) TIMEFROMRETROFIREORE VE RSE B ACK UP B AN K A NG LE

RETBBO XX:XX(MIN:SEC TIMEFROMETROFIREOBEGINNING OF COMMUNICAT IONS


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BLACKOUTRETEBO XX:XX(MIN:SEC TIMEFROMETROFIREOENDOF COMMUN ICATIONS BLACKOUTRETDROG XX:XX(MIN:SEC TIMEFROMETROFIREODROGUE CHUTE DEPLOYMENT


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EARTH ORB IT BLO CK DATAAREA XXX-X RECOVERYREA


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FIRST 3 D IG ITS -L ANDING REVO LUTIONLAST D IG IT -R ECOVE RY ARE A ANDSUPPORTCAPABILITIESLAT +XX.XXDEG) COORDINATESFTHELONG TXXX.X(DEG) DESIREDANDINGREAGETI XXX:XX:XX.XX DEORBITGNITIONTIME

(HR:MIN:SEC) FORTHEDESIREDLANDING ARE A&VC XXX.X(FPS) DEORBITANEUVER&V TO BE LOADED INTO THEEMS COUNTE R.

LM P27 UPDATE


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PO,_ ',1 I ,' I "1 IGET ' 1174 01 INDEX INDEX INDEX

O203_ 4 a-O4O 5O6O71 01 11 21 31 41 51 61 7

o. 20, OO -- 21"_ 22"_ 23a_,< 24

N34 HR X X X X X XMIN X X X X X X X X

NAVCHECKSEC X X X XN43 LAT 0 0 IIIILONG

ALT + 0 + 0


71/340

AGS STATE VECTOR UPDATE


72/340

PURP240241242260261262

+ + 254244245246264265266

o. + + 272' , , 0o- REMARKS:-J

AG S STATE VE CTO R UPDA TEPURP PURPOSEORAGSSTATEVECTOR UPDA TE


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240 +XXXXXI00 FT) LMSTATEVECTOR-POSITION- COMPONENTS241 +XXXXXO0FT)242 +XXXXXO0FT)

260 +XXXX.X FPS) LMSTATEVECTOR-VELOCITY- COMPONENTS261 +XXXX.XFPS)262 +XXXX.XFPS)

254 +XXXX.XMIN) LMTIMEFORWHICHTHE STATE VECTOR ISACCURATE

244 +XXXXI00 FT) CSMSTATEVECTOR-POSITIONCOMPONENTS245 +XXXXXI00 FT)246 +XXXXXI00 FT)

264 +XXXX.(FPS) CSMSTATEVECTOR-VELOCITY- COMPONENTS265 +XXXX,XFPS)266 +XXXX.XFPS)

272 +XXXX.XMIN) CSMTIMEFORWHICHTHE STATE VECTOR ISACCURATE

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SECTION IV - DETA ILED TEST OBJECTIVES


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SE CTIO N 4D ETA ILE D O BJE CTIVE A CTIVITIE S

This section contains the activity summaries which reflect the testobjectives for M ission G as described in "M ission Requirements G Type Mission",SPD9-R-038, Change A dated May l, 1969. These activity summaries are presented inthe approximate sequence in which they are planned to occur during the mission.E ach ac tivity summary provides the follow ing in formation:A . TEST OBJECTIVES . Th is is the lis ting of the Functiona l Tes tObjectives (comple te or pa rtia l) wh ich re la te to theparticular activity;B . TE ST REQUIREMENTS . Here the specia l test prerequis ites (andmission phase if necessary) a re presen ted in addition to brie fstatements of the requirements for performing the activity;C. TEST PROCEDURES/CHECKLISTS. These are the proceduralreferences for the performance of the activity as far asthe test objectives are concerned; andD . DATA REQUIREMENTS . Th is part of the summary identifies thegross da ta wh ich are needed for eva lua tion of test resultsin terms of flight crew and ground support requirements.


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Cross references for re lating Deta iled and Functiona l Test Objectives withthe activity summaries and relating activities to Functional Test Objectives, areprovided as the initial part of this section.The following ground rules are to be used in implementing data requirements:A. The collection of highly desirable (HD) data should not constrainthe timeline of the crew _rocedures.

B. Post-flight debriefing requirements which are fulfilled by real timetransmission of data per the DATA REQUIREMENTSsections may be deletedfrom the post-flight debriefing.All of the Test Requirements have not been totally implemented into themission timeline. These items are identified in this section as "Not Implemented"or with the conditions by which they will be implemented.

TABLE 4-IMISSION ACTIVITY ANDTE ST O BJE CTIVE CRO SS RE FE RE NCE

ACTIVITY FTOLMDescent D-l, G-l, G-3,H-l, M-ILunar Surface Navigation G-l, G-2, G-3, L-4, M-2EVA Preparation and Egress B-l, B-2, C-l, C-2, C-3, L-lSurface Sample Collection A-l, E-l, F-l, F-2, I-3, J-2, J-3,J-4, M-3External LM Observations and Photography D-l, D-2, D-3, D-4, L-2, M-3Lunar Surface Observations and Photography E-l, E-2, E-3, H-2, J-5, L-3, L-4,M-3Experiment Deployment/Conduct S-031, S-078, S-080Post EVA Operations B-l, C-l, C-2Contamination Prevention I-l, I-2


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