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NATIONAL AERONAUTICS AND SPACE ADMINISTRATION
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MANNED SPACECRAFT CENTERHOUSTON,TEXAS
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APOLLO II
APOLLO AS-506/CSM-IO7/LM-5
FINAL FLIGHT PLAN
JULY l, 1969
Flight Planning Branch
G. M. Col tonFlight Planning Branch
?. A. Guil!oryFlight Planning Branch
Aoproved by: /- y ,'--/ / <_:.-_--W. J. A#rthChief, Flight Crew Support Division
Donald_K. Slayton
Director of Flight Crev_lOperations
Concurrence: __'_Low _ _-'0_IJ'---@_-7"7Manager, ADollo Spacecraft Pro.qram
_ , _ _ 7 /
• S _T// ,/, , 2
Christo_hj_f _ C. Kraft,-d?._'"Director of Fligh_ Operations
Any con_ents or questions on this document should beforwarded to T. A. Guillory, Flight Planning Branch,mail code CF34, extensio_q 427l.
ACKNOWLEDGMENTS
Acknowledgment is made to Messrs. Richard Rogers, William Killian andSpencer Gardner for their technical support in the preparation of theApollo II Flight Plan.
Views of the earth and the P52 stars shown in the Flight Plan weretaken from the document, Views from the CM and LM During the Flightof Apollo II (Mission G).
The CSM and LM attitude information was taken from the document,Lunar Orbit Attitude Sequence for Mission G.
TABLE OF CONTENTS
Abbreviations iii
Introduction xi
SECTION I - GENERAL
I. Mission Description l-l
2. SummaryFlight Plan (TLC-TEC) I-5
3. Summary Flight Plan (Lunar Orbit) I-6
4. LM Power Descent Profile I-7
5. CSMBurn Schedule I-8
6. LM Burn Schedule I-9
7. Lunar Landing Site Data l-lO
8. Landmark Tracking Data l-lO
9. Flight Plan Notes 1-13
SECTION II - UPDATE FORMS
I. Update Forms Table 2-I
2. CSM Maneuver Update Pads 2-2
3. LM Maneuver Update Pads 2-27
SECTION III - DETAILED TIMELINE
I. LaunchPhase 3-I
2. TLI-T&D 3-3, 3-4
3. Translunar Coast Activities
a. Cislunar Navigation 3-7, 3-17
b. LM Familiarization 3-35
c. Lunar Orbit Insertion 3-47
4. Lunar Orbit Activities
a. Second LM Ingress 3-53
b. LM Activation and C/O 3-63
SECTION III CONT'D
c. Undocking 3-67
d. Touchdown 3-69
e. EVA 3-77
f. LMLiftoff 3-90
g. LMActive Docking 3-94
h. LMJettison 3-97
5. TEI-TEC 3-101
6. Entry 3-135
SECTION IV DETAILED TEST OBJECTIVES
I. Detailed Test Objectives 4-I
2. Test Objective/Mission Activity Cross Reference 4-2
3. TestObjectives 4-6
SECTION V - CONSUMABLES
I. RCSPropellant Usage 5-2
2. SMRCSBudget 5-3
3. CMRCSBudget 5-22
4. SPSBudget 5-23
5. LMRCSBudget 5-25
6. DPSBudget 5-31
7. APSBudget 5-32
8. CSMEPSBudget 5-36
9. LMEPSBudget 5-41
I0. LMECSBudget 5-45
II. PLSSBudget 5-50
SECTION VI - SUMMARYFLIGHT PLAN
SummaryFlight Plan 6-I
ii
ABBREVIATIONS
ACCEL AccelerometerACN AscensionACT ActivationACQ AcquisitionAEA Abort Electronics AssemblyAGS Abort Guidance SubsystemAH AmpereHoursALSCC Apollo Lunar Surface Close-up CameraALT AltitudeAMPor amp AmpereANG AntiguaANT AntennaAOH Apollo Operations HandbookAOS Acquisition of Signal or Acquisition of SiteAOT Alignment Optical TelescopeAPS Ascent Propulsion SubsystemARS Atmosphere Revitalization SystemATT AttitudeAUX AuxiliaryAZ Azimuth
BAT BatteryBDA BermudaBio Bio-Medical Data on Voice DownlinkBP Barber PoleBT Burn TimeBU BackupBW Black & WhiteBRKT Bracket
CAP COM Capsule CommunicatorCAL _ Calibration AngleCAM CameraCB Circuit BreakerCDH Constant Delta AltitudeCDR CommanderCDU Coupling Data UnitCEX Color ExternalCIN Color InternalCIRC CircularizationCK CheckCM CommandModuleCMC CommandModule ComputerCMD CommandCMP CommandModule PilotCNTL ControlC/O Check outCOAS Crew Optical Alignment SightCOMM CommunicationsCONFIG Configuration
iii
CONT ContinueCP Control PointCRO Carnarvon, AustraliaCRYO CryogenicCSC Contingency Sample CollectionCSI Coelliptic Sequence InitiationCSM Command Service ModuleC&WS Caution and Warning SystemCYI Grand Canary Island
DAP Digital Auto PilotDB DeadbandDCA Digital CommandAssemblyDEDA Data Entry and Display AssemblyDEGS DegreesDEPL DepletionDET Digital Event TimerDIFF DifferenceDOI Descent Orbit InsertionDPS Descent Propulsion SystemDS Documented SampleDSE Data Storage EquipmentDSKY Display and KeyboardDTO Detailed Test ObjectiveDUA Digital Uplink AssemblyDWN Down
E Erasable or EnterEASEP Early Apollo Scientific Experiment PackageECS Environmental Control SystemED Explosive DeviceEDT Eastern Daylight TimeEFH Earth Far HorizonEl Earth (atmosphere) InterfaceEL Elevation or ElectricEMS Entry Monitor SystemEMU Extravehicular Mobility UnitENH Earth Near HorizonEPO Earth Parking OrbitEPS Electrical Power SubsystemEQUIP EquipmentEST Eastern Standard TimeEVA Extravehicular ActivityEVAP EvaporatorEVT Extravehicular TransferE×T External
f F StopFC Fuel CellFDAI Flight Director Attitude Indicator
iv
FLT Flight_I Frequency ModulatedFOV Field of Viewfps or FPS Feet per secondFT or ft FeetFTO Flight Test ObjectiveFTP Full Throttle Position
GBI 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 Guidance Navigation Control SystemGNM GuamGYM Guaymas, Mexico
H2 HydrogenHA Apogee AltitudeHAW HawaiiHBR High Bit Rate (TLM)HD Highly DesirableHGA High Gain AntennaHI HighHp Perigee AltitudeHSK Honeysuckle (Canberra, Australia)HTR HeaterHTV USNSHuntsville
ICDU Inertial Coupling Data UnitID IdentificationIGA Inner Gimbal AngleIGN IgnitionIMU Inertial Measurement UnitINIT InitializationINT IntervalometerIP Initial Point
ISA Interim Storage AssemblyIU Instrumentation UnitIVC Intervehicular CommunicationsIVT Intravehicular Transfer
JETT Jettison
KM Kilometerkwh Kilowatt Hour
LA Launch AzimuthLAT LatitudeLBR Low Bit Rate (TLM)LBS or Ibs PoundsLCG Liquid Cooled GarmentLDG LandingLDMK LandmarkLEB Lower Equipment BayLEC Lunar Equipment ConveyorLFH Lunar Far HorizonLGC LM Guidance ComputerLH Left-handL/H Local HorizontalLHEB Left-hand Equipment BayLHFEB Left-hand Forward Equipment BayLHSSC Left Hand Side Storage ContainerLiOH Lithium HydroxideLLM Lunar Landing MissionLLOS 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 Launch VehicleL/V Local VerticalLVPD Launch Vehicle Pressure Display
M MandatoryMAD Madrid, SpainMAN ManualMAX MaximumMAXQ MaximumDynamic PressureMCC Midcourse CorrectionMCC-H Mission Control Center - Houston
or MCCMDC Main Display ConsoleMEAS MeasurementMER USNSMercuryMESA Modularized Equipment Stowage AssemblyMET Mission Event Timer
vi
MGA Middle Gimbal AngleM/I Minimum ImpulseMIN MinimumMLA Merrit Island, FloridaMNVR ManeuverMPS Main Propulsion SystemMSFN Manned Space Flight NetworkMTVC Manual Thrust Vector Control
N2 NitrogenNAV NavigationNM Nautical MilesNOM NominalNXX NounXX
02 OxygenOBS ObservationO/F Oxidizer to Fuel RatioOGA Outer Gimbal AngleOMNI Omnidirectional AntennaOPS Oxygen Purge SystemORB OrbitalORDEAL Orbit Rate Display Earth and LunarORIENT OrientationOVHD Overhead
P Pitch or ProgramPAD Voice UpdatePCM Pulse Code ModulationPC Plane ChangePDI Powered Descent InitiationPGA Pressure Garment AssemblyPGNCS Primary Guidance Navigation Control SectionPIPA Pulse Integrating Pendulous AccelerometerPLSS Personal Life Support SystemsPM Phase ModulatedPOL Polarity or PolarizingPRE Pretoria, South AfricaPREF PreferredPREP PreparationPRESS PressurePRIM PrimaryPROP ProportionalPSE Passive Seismic ExperimentPT PointPU Propellant UtilizationPUGS Propellant Utilization and Gaging System
vii
PTC Passive Thermal ControlPWR PowerPX× Program XX
Qty Quantity
R Roll or RangeR&B Red & BlueRAD RadiatorRCDR Recorder
RCS 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 XX
SA 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 LM AdapterSLOS Star Line-of-SightSM Service ModuleSPOT Spot MeterSPS Service Propulsion SystemSR SunriseSRC Sample Return ContainerSRX S-Band Receiver Mode No. XSS SunsetSTX S-Band Transmit Mode No. X
viii
S.V. State VectorSWC Solar Wind CompositionSw SwitchSXT Sextant
T EPHEM Time of Ephemeris UpdateTA Trunnion AngleTAN Tananarive, MadagascarTB Time Base
TCA Time of Closest ApproachTD&E Transposition Docking & LM EjectionTEC Trans Earth CoastTEl Transearth InsertionTEMP TemperatureTERM Terminate
TEX Corpus Christi, TexasTGT TargetTIG Time of IgnitionTLC Trans Lunar CoastTLI Translunar InsertionTLM or TM TelemetryTPF Terminal Phase FinalTPI Terminal Phase InitiationTPM Terminal Phase MidcourseT/R Transmitter/ReceiverTRANS TranslationTV TelevisionTVC Thrust Vector ControlTWR Tower
US United States
V VelocityVAN USNS VanguardVHF Very High FrequencyVLV ValveVI Inertial VelocityVOX Voice KeyingVXX Verb XX
W/O WithoutWRT With Respect toWTN USNSWatertown
XFER TransferXMIT Transmit or TransmitterXPONDER Transponder
Y Yaw
ix
aV Velocity Change (Differential)_VC Velocity Change at Engine Cutoff_R Position Change (Differential)
8-balls Flight Director Attitude Indicator (FDAI)
CAMERA NOMENCLATURE
EL/250/BW-BRKT Electric Hasselblad/250mm Lens/Black & White film-Camera Bracket
INT _f5.6,250,INF) Intervalometer 1(f-stop 5.6, shutterspeed=250 sec,
Infinity)
16mm/18/CEX-BRKT 16mm Camera/18mm Lens/Color FilmMIR (fS,250,INF) 6fps External-Camera Bracket
Mirror (f-stop 8, shutterspeed1
= _-5_O-sec, Infinity)6 frames per sec
SYMBOL NOMENCLATURE
LUNAR PENUMBRA(OCCURSPRE LOll)
SPACECRAFT SUNSET-HONEYSUCKLE 85FT D_SH COVERAGE
-DARKNESS (UMBRA)
-MSFN LOS
-SPACECRAFT SUNRISE
.LUNAR P,ENUMBRA(OCCURS PRE LOll)
J- LUNARSURFACE
/ WINDOWEARTH _----_" _/_ "7
(ALWAYS) i\_'_../j_7
_ DOWN \(5-_ S-BANDHGA
X, OPTICS--S-BAND STEERABLE
SUBSOLAR POINT
I MSFNAOS
'MADRID 85FT DISH COVERAGE
I .GOLDSTONE85FTD!S_COVERAGE
II
LUNAR TERMINATOR
SPACECRAFT SUNSET
DARKNESS
MSFN LOS
SPACECRAFT SUNRISE
LUNAR TERMINATOR
xi
INTRODUCTION
This Flight Plan has been prepared by the Flight Planning Branch, FlightCrew Support Division, with technical 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 trajectory parameters used in this Flight Plan are for July 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 Flight Plan is under the configuration control of the CrewProcedures Control Board (CPCB). All proposed changes to this documentthat fall in the following categories should be submitted to the CPCB viaa Crew Procedures 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 Flight Plan.
5. Items that require a change to the flight data file.
The Chief, Flight Planning Branch (FCSD) will determine what proposed changesfall in the above categories.
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.
xii
SECTION I - GENERAL
MISSION DESCRIPTION
I. Launch and EPO (Duration 2:44) LIFT OFF - 2:44 GET
(a) Nominal launch time is 9:32 EDT, July 16, 1969, with a launch
window duration of 4 hrs. 24 rain.
(b) Earth orbit insertion into a I00 nm circular orbit at II rain.
43 sec. after lift-off
(c) CSH systems C/O in earth orbit
(d) Optional IHU realign (P52) to the pad REFSrIHAT during the first
night period
(e) TLI occurs at 2:44:26 GET over the Pacific Ocean during the
second revolution. (See Table I-I for burn data).
2. Translunar Coast (Duration 73:10) 2:44 - 75:54 GET
After TLI, which places the spacecraft in a free lunar return trajec-
tory, the following major events occur prior to LOI:
(a) Transposition, docking and LH ejection, including SIVB photo-
graphy
(b) Separation fror.1 SIVB and a CSH evasive maneuver
(c) SIVB propulsive venting of propellants (slingshot)
(d) Two series of P23 cislunar navigation sightings, star/earth hori-
zon, consisting of five sets at 06:00 GET and five sets at 24:30
GET
(e) Four midcourse corrections which take place at TLI + 9, TLI + 24,
LOI - 22 and LOI - 5 hours with AV nominally zero (See Table I-I).
I-I
(f) Passive thermal control (PTC) will be conducted during all periods
when other activities do not require different attitudes.
(g) LM inspection and housekeeping
(h) LOI l , performed at 75:54:28 GET, ends the TLC phase.
3. Lunar Orbit (Duration 59:30) 75:54 - 135:24 GET
LOI Day (Duration 25:00) 69:00 - 94:00
(a) LOIl
(b) Photos of targets of opportunity
(c) LOI2
(d) Post LOI 2 LM entry and inspection. S-Band/VHF B Voice
tests will be conducted.
(e) Post LOI 2 Pseudo landmark tracking (one set of sightings)
(See Table I-4)
(f) Rest period of 9 hours
DOI and EVA Day (Duration 28:00) 94:00 - 122:00 GET
(a) Docked LM activation and checkout
(b) Docked landing site landmark sighting (one set of sightings)
(See Table I-3)
(c) Undocking and separation
(d) DOI thru landing (See Figure I-3 Powered Descent)
(e) LM post touchdown and simulated liftoff
(f) Rest period (LM) of 4 hours
(g) CSM plane change
(h) Rest period (CSM) of 4 hours
I-2
(i) EVA prep
(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
Ascent and TEl Day (Duration 25:00) 122:00 - 147:00 GET
(a) LM Lift-Off and Insertion
(b) LM active rendezvous
CSl
PC
CDH
TPI
Braking
(c) Docking
(d) LI.I jettison
(e) TEl
(f) Rest Period
4. Lunar Orbit Particulars (Average Values for a 60 x 60 nm orbit)
(a) Revolutions start at 180 ° longitude
(b) Revolution duration - l hr. 58.2 rain.
(c) S/C niqht period duration - 47 rain. ;.i;
(d) MSFNcoverage per rev. 72 rain.- #/
(e) Orbit inclination - 1.25 ° for July 16, 1969 launch ._
/
I-3 -_
(f) S/C orbital rate - 3°/min. (.05°/sec)
(g) Lighting change at fixed ground point - l°West/Rev.
(h) Horizon visibility + 20° selenocentric angle on the
lunar surface
(i) One lunar degree on lunar surface 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. Transearth Coast and Entry (Duration 59:39) 131:52 - 195:03 GET
Transearth coast begins with TEl at 135:24:34 GET and consists of
the following major events:
(a) Three midcourse corrections are scheduled at TEl + 15, El - 23
and E1 - 3 hours with AV nominally zero.
(b) CM/SM separation takes place at 194:51 GET and Entry Interface
occurs at 195:03 GET.
(c) Splashdown will occur in the Pacific Ocean at a longitude of
about 172.4 ° West at 195:17 GET. This will occur approximately
25 minutes prior to sunrise local time.
I-4
_'l
o
1-5
1-6
/.
i/
I_
8
/°
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1-8
TABLE I-3 LUNAR LANDING SITE DATA
DAY SITE DESIG LATITUDE LONGITUDE ILAUNCH AZIMUTH/ 2LAUNCH AZIMUTH/'SUN ELEVATION SUN ELEVATION
JULY 16 2(IIP6) 00°42'50"N 23°42'28"E 72°/10.5 ° 108c/13.5 °0932 EDT 00.71388889°N 23.70777778°E
(00.6914°N) (23.7169°E) 3
JULY i8 3(lIPS) O0°21'lO"N 01°17'57"W 89.295°/II ° I08°/13 °I132 EDT 00.35277778°N 01.29916667°W
JULY 21 5(IIPi3) O!°40'41"N 41"_53'57"W 94.6775/9.7 ° I08°/II.7 °1409 EDT 01.67805556°N 41.89916667°W
Data From TJ memo, Accuracy Estimates, Landing Site Landmarks,May 12, 1969, TJ-69-499o
i Sun Elevation Angles Are For Approximately 27 Hours After LOI, Ist Opportunity"r Tim!o
Lo Includes 2nd Opportunity TLI3 Data From MPAD memo, landing site coordinates for G,
June 12, 1969, 69-FM41-181.
TABLE I-4 LANDMARK TRACKING DATA
July 16 Launch
LANDMARK DELTADESIG. LATITUDE LONGITUDE ALTITUDESUNEL
(nm)
A1(Pseudo) 2°N 65° 30' 000.00 43°2.000°N 60.500°E
IP(130) l °53'N 28o42'E 000.00l .885°N 28.726°E
130(Prime 01°15'56"N 23o40'44 '' -OOl .68 8.5 °LDG SITE 2) 01.26555556°N 23.67888889°E
l(Ol .24307°N) (23.6880°E)
123 (Alternate 00°30'I 9"N 24°53'20°E -001.71LDG SITE 2) 00.50527778°N 24.88888889°E
129 (Alternate Ol °17'06"N 23°44' 37"E -OOl .76LDG SITE 2) 01.28500000°N 23.74361111°E
133 (Alternate D0°,17' 14"N 23°30' 55"E -OOl .68LDG SITE 2) 00.78722222°N 23.51527778°E
l Data from HPAD memo, landing site 2 position,June 20: 1969, 69-FM41-199.
l-lO
TABLE I-4 LANDMARKTRACKING DATA (CONT'D)
July 18 Launch
LANDMARK DELTADESIG. LATITUDE LONGITUDE ALTITUDESUNEL
(nm)
IP(GI) O°I6'N 32°19'E0.267°N 32.317°E
GI(129) 01°17'06"N 23°44'37"E -001.97 26°01.28500000°N 23.74361111°E
IP(143) O0°I8'N 3°23'EO0.300°N 3.383°E
143(Prime 00°36'51"N 01°04'39"W -O01.Ol 9°LDG SITE 3) 00.61416667°N 01.07750000°W
150(Alternate 00°16'59"N 01°25'43"W -001.01 -LDG SITE 3) 00.28305556°N 01.42861111°W
147(Alternate 00°03'42"N 01°16'36"W -000.99 -LDG SITE 3) 00.06166667°N 01.27666667°W
I-II
TABLE I-4 LANDMARKTRACKING DATA (CONT'D)
July 21 Launch
LANDMARK DELTADESIG. LATITUDE LONGITUDE ALTITUDESUNEL
(nm)
IP(GI) O°30'S 26°33'WO.5OO°S 26.550°W
Gl I°42'N 32°I0'W -001.77 8°1.696°N 32.162°W
IP(180) 0°36'N 36°34'W _0.608°N 36.567°W
180(PRIME 01°30'37"N 41°49'05"W -001.25 8.9 °LDG SITE 5) 01.51027778°N 41.81805556°W
171(Alternate 01°20'04"N 40°47'34"W -001.29LDG SITE 5) 01.33444444°N 40.79277778°W
178(Alternate 01°45'33"N 41°34'12"W -001.22 -LDG SITE 5) 01.75916667°N 41.57000000°W
184(Alternate 02°03'I0"N 42°13'41"W -001.23LDG SITE 5) 02.05277778°N 42.22805556°W
1-12
FLIGHT PLAN NOTES
A. CrewI. Crew designations are as follows:
Designation Prime BackupCo_nander (CDR) Armstrong LovellCommand Module Pilot (CMP) Collins AndersLunar Module Pilot (LMP) Aldrin Haise
2. Crew positions during the mission are as follows:CSM LM
Left Center Right Left Riqht
Launch thru TLI CDR LMP CMPT&Dthru Entry CMP CDR LMPMannedLM 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 PGAConfiguration
Launch to insertion PGA's with helmet & gloves (H&G)Insertion to TLI PGA's without H>LI to evasive mnvr PGA's with H>LC & LOI l&2 Constant wear garmentsLM activation & checkout PGAwithout H&G
(CMP H&G donned for latchcocking & CDR/LMP H&Gdonned for pressure integritycheck and cabin reg check)
Undocking through touchdown PGA's with H&G except CMPwithout H&G after DOI
Touchdown through pre lift-off PGA's without H&G exceptfor CDR/LMP simulated count-down & EVA
Liftoff through LM jettison PGA's with H&G (exceptH&G off after docking)
LM jettison through splashdown Constant wear garmets
1-13
5. Two crew status reports via air-to-ground commmunications will bemade by the flight crew during each activity day. The first re-port will be given after the first meal of the day and will con-cern the sleep obtained during the previous sleep period. Thesecond report will be given following the final meal of the dayand will concern the radiation dose received during the previous24 hours and medication taken if any. The following informationshould be logged:a. Food Consumptionb. Exercisec. Used fecal bags marked as to crewman and GET
6. Negative reporting will be used in reporting completion of eachchecklist.
7. Continuous CSM biomedical data are automatically transmitted to theground.
8. LM biomedical switching is performed manually by the LMP from undock-ing to docking as scheduled in the timeline.
9. All onboard gage readings will be read directly from the gages.and will not be corrected by the appropriate calibration factors,
B. Photograph iPhotographic requirements were derived from the following:
a. Lunar Surface Operations Planb. Photographic Operations Plan
Co ProceduresI. CSM
Crew procedures called out in the flight plan may be found in thefollowing documents: ,{_ 1a. Apollo Operations Handbook - CSM-I07 (AOH), Volume 2b. Crew Checklistc. CSM Rendezvous Procedured. Abort Summary Documente. Apollo Entry Summary Documentf. Photographic Operations Plang. Descent Procedures Documenth. Ascent Procedures Documenti. Lunar Landmark Tracking Attitude Studiesj. Lunar Orbit Attitude Sequence for Mission Gk. Data Priority Documents
l -14
2. LMCrew procedures called out in the flight plan may be found in thefollowing documents: VC_,_ La. Apollo Operations Handbook LM-5 Volume 2b. Crew Checklistc. LM Rendezvous Proceduresd. LM Descent/Ascent Summary Documente. Lunar Landing Phase Photographic Operations Planf. Data Priority Documentsg. EVA Proceduresh. Apollo Lunar Surface Operations Plan
D. CommunicationsI. General
a. CSM and LM HBR data transmissions in lunar orbit will normal-
ly require the use of the high gain or steerable antennasb. During communications, the spacecraft will be referred to
by name (Apollo II) and MCC-H will be referred to as Houston.c. The preferred S-Band communications 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. Thisrecorder 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 operations.
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 Operationa. The DSE will normally be operated via ground command except for
special 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 CSM HBR and voice recording during all CSMengine burns.
d. DSE data and voice recordings will be made in CSM LBR modewhenver possible in order to minimize the DSE dump time.
1-15
e. During PTC using the HGA REACQ communications mode the DSEwill be used to record LBR data when the HGA is not in theMSFN field of view.
f. During lunar orbit LM operations, the DSE will be used to recordLM-TLM-LBR data during all docked LM activites that occur on thelunar farside. For undocked LM activites only DOI will be record-ed as VHF ranging is required.
g. DSE will be used to record all H_BRentry data during the blackoutregion.
3. Launch - Earth Orbit Phasea. OMNI B and VHF LEFT will be selected for lift off. OMNI D will
be selected by the crew during boost phase if the launch azimuthis less than 96° or OMNI C if the launch azimuth is greater than96° . OMNI D will probably be the best antenna for earth orbit.
b. VHF Duplex B will be used for launch, and Simplex A for earthorbit operations.
c. VHF Simplex A will be used for entry to be compatible withrecovery forces communications.
4. Translunar and Transearth Coast PhaseThe translunar and transearth sleep communications mode will be asfollows. The CSM x-axis will be placed normal to the eclipticplane. The CSM will be rolled at a rate of approximately threerevolution per hour. During the near earth sleep periods priorto 30 hours GET (range less than 120Knm) omni antennas B and Dwill be used. During the other sleep periods (beyond 120Knm)the high gain antenna may be required (in the REACQmode). TheREACQ configuration will provide approximately 210 degrees of HGAcoverage per CSM/LM revolution or 35 minutes of MSFN coverage perhour. The REACQ configuration will also allow MCC-H to use realtime control to select TLM HBR or LBR and to dump the DSE duringeach spacecraft revolution.
5. Lunar Exploration Phasea. Normal CSM communications between MSFN/LM will be by S-Band
during the lunar exploration period.b. If additional communications capability is required the
S-Band erectable antenna will be deployed by the EVA crewmanand will be utilized for all LM/MSFN/CSM communications.
c. During periods when both crewmen are EVA, the "AR" position(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 will relay to MCC-H via S-Band.
1-16
E. CSMNotesI. Electrical Power System and Water Management
a. Spacecraft lift-off switch positions are listed in the ApolloOperations Handbook (Volume 2) for CSM 107.
b. The CSM will remain fully powered up throughout the mission(CMC, IMU and SCS in the "operate" configuration and opticspower-up as required).
c. Fuel cell H2 and 02 purging is scheduled as follows H2 approx-imately every 48 hours and 02 approximately every 12 hours.
d. The hydrogen and oxygen VAC ION pumps will be inactive through-out the mission.
e. Potable water will be chlorinated once a day before each sleepperiod, starting with the First sleep period (GET 13:30).The POT H20 inlet valve will be opened prelaunch.
f. FC purges and waste water dumps will not be scheduled withinone hour prior to optical sightings.
g. Waste H20 dumpin9 will be managed to allow:-(T)---Maximum QTY:85-90%(2) Minimum QTY:25%(3) At LOI:QTY : 75%(4) At CM-SMSEP:QTY = 90% to 100%(5) No dumping after MCC3 until after LOI(6) Dumps will be performed (if required) within 2 hours pre-
ceding MCC maneuvers(7) In lunar orbit if dumping is required, dumps will be per-
formed immediately prior to sleep periods(8) The water dump will not be operated in the automatic mode
at anytime during the missionh. The cryogenic heaters will be in AUTO during the mission and
the fans will be operated manually. The fans will be cycledfor one minute before and after each sleep cycle.
i. The batteries will be charged according to the followingschedule:
Time Battery5:20:00 B
12:20:00 A48:10:00 B80:25:00 A
103:30:00 B148:00:00 A154:00:00 B
2. Environmental Control System and Cabin Pressurizationa. One C02 odor absorber filter (LiOH canister) is changed
approximately every 12 hours or if C02 partial pressure isgreater than 7.6mm Hg. There are 20 filters (2 in thecanisters onboard and 18 stowed).
1-17
b. A Pre TLI/LOI ECS redundant component check including thesecondary evaporator operation, is performed prior to TLIand LOI. The secondary evaporator water control valves willbe turned "OFF" after the check.
c. The evaporator operation will be as follows:(I) Launch - primary loop operation(2) Earth Orbit - primary loop operation and secondary
loop test plus redundant operation test prior to TLI.(3) Post TLI - deactivate both evaporators(4) Pre LOI-ECS pre TLI/LOI redundant component check and
primary evaporator activation(5) Post TEl - deactivate primary evaporator(6) Entry interface minus 1 hour - activate primary and
secondary evaporator.
3. GuidanceandNavigation ,_a. During lunar orbit, the CSM and LM
will utilize the same landing siteREFSMMAT such that the gimbal angleswould be 0,0,0 at landing with theLM sitting face forward on landing _site number two and the CSM overthe landing site pitched up 90 °from local horizontal "heads up".
b. During PTC the CSM/LM x-axis is Ditched up 90° (Norfor TLC and down 90° (South) for TEC with the Y-Z axesin the plane of the ecliptic. This change in x-axispointing is to enable simultaneous viewing of the earthand moon through the side windows while maintaining afavorable high gain antenna position.
c. The CSM tracking light will be on continuously from undock-ing to landing and from LM lift-off to docking.
4. Landmark TrackingThe following ground rules were used for landmark tracking.a. IMU to be realigned on the dark side preceding each track-
ing period.b. MSFN is reacquired after each tracking period. The
tracking data will be acquired by MSFN after all themarks have been made and while N49 (AR,AV) is displayed.MSFN will give a GO when data acquisition has been verified.
c. The pseudo landmark tracking (AI) will be used to determinethe altitude of an area in which the LM will be making al-titude checks after DOI. The data will be processed duringthe sleep period after the trackings and relayed to the LMprior to undocking.
1 -18
o
d. In the docked configuration the CSM/LM _'__r_/_{_approaches the landmark in an inertialhold attitude. This inertial attitudeplaces the spacecraft 2° below thelocal horizontal at the 35 ° elevationangle point. At 35 ° elevation angle apitch down of O.3°/sec is initiated.Five marks are then taken with thetime between marks a minimum of 25
seconds. (See tracking profile) /_r_. _22 °e. In the undocked configuration the CSMapproaches the landmark in ORB RATE and _ /_pitched down 22° from the local horizon -/ _ir_/_'--_tal. At 35° elevation angle five marks 0 \ _o_,,_are taken with the time between marks aminimum of 25 seconds. ORB RATE is _'.\\\ ..... \\_
continued throughout the marking period. " \
f. In the undocked COAStracking the CSM \will approach the LM in ORBRATEheadsup and pitched down 40 ° from the localhorizontal. When the LM is centeredin the COASthe CSMwill initiate a 40°
variable pitch rate to keep the LMcentered in the COAS.
5. CSM/LM and CSM attitude maneuvers will normally be at a rateof O.2°/sec or O.5°/sec. unless other rates are required.NOTE: At 0.2°/sec,15 minutes is required to maneuver 180° .
At O.5°/sec, 6 minutes is required to maneuver 180° .
6. Passive thermal control mode will be initiated after MCCl oras soon as MCCI is scrubbed and maintained throughout themission (except in lunar orbit) until at least three hoursbefore entry except for interruptions for midcourse corrections,communications orientation (maximum interruption of threehours). PTC will not be initiated before approximately 7:00GET.
7. Service Propulsion System All SPS burns will be initiatedon Bank A except LOll which will be initiated on Bank B.
F. LM NotesI. Entries into the LM
a. Three entries into the LM are scheduled in the timelineat 56:30, 81:30 and 95:52 GET respectively.
1-19
b. The first entry (56:30 GET) will be for LM familiarizationand will be performed by the CDR and LMP in the constantwear garments. During this period there will be approxi-mately 5 minutes of VHF-B LBR data which will be recordedby the DSE in the CSM. The LM will remain on CSM powerduring the crew familiarization period.
c. The second entry (81:30 GET) will be for LM housekeepingand will be performed by the LMP in constant wear ga_lents.During this period the LM will go to internal power for theS-Band/VHF B voice activation.
d. The third entry into the LM (95:52 GET) will be performedby the LMP in LCG's to prepare the LM for undocking anddescent to the lunar surface. During this period the LMPand CDR initially transfer to the LM in LCG's then returnto the CSM for PGA donning.
2. Environmental Control System and Cabin Pressurizationa. The LM cabin will contain ambient air at lift off and will
bleed down to zero pressure psi during the launch.b. The LM will be pressurized for transposition and docking
after which it will be isolated and the pressure periodicallymonitored.
c. The LM will be pressurized prior to the first entry (LMfamiliarization) after which it will be isolated againfor the remainder of the TLC period.
d. Prior to the second entry (LM housekeeping) it will bepressurized again and will remain pressurized.
3. Guidance and Navigationa. Two LGC erasable memory dumps and MCC-H verifications will
be accomplished prior to DOI. If a significant number oferrors are found, memory correction and re-verificationwill be performed before DOI.
b. The LM IMU will be manually aligned to the CSM IMU duringthe DOI Day LM activation and checkout. P52/AOT alignmentswill be performed as close to DOI as possible.
c. All translations during the undocked manned LM operations willbe under PGNCS control.
d. The capability for MCC-H to update the LGC via uplink willnormally be blocked by the LMP UP-DATA LINK switch (panel 12).
1 -20
4. RCS Operation and Interface Constraintsa. During CSM/LMdocked checkout operations, the LM steerable
and/or RR antennas will not be powered down once they havebeen activated. The SM B3 and C4 thrusters will bedeactivated before the LM steerable and/or RR antennas havebeen unstowed in order to prevent SM-RCS impingement on theseantennas.
b. The CSMroll jets and LM yaw jets will be disabled when theprobe is preloaded (docking latches are cocked} and the tunnelis pressurized prior to undocking. The jets will be activatedafter tunnel venting.
c. LM RCS two jet ullaqe (System B) will be used for unstagedullage maneuvers in order to prevent asymetrical RCS thrustcaused by impingement on the descent stage.
d. The RCS interconnect will be used during the APS lift-offand ascent, but will not be used during the rendezvous maneuvers.
5. Rendezvousa. The rendezvous radar will be pointed away from the sun
and will be turned off when no functional use is requiredto prevent overheating of the antenna.
b. The LM tracking light will be on continuously betweenseparation and touchdown and between launch and docking ex-cept during PGNCS/AOTalignments. During PGNCS/AOTalign-ments (LM P52), the tracking light would interfere with thealignments. (dark adaption)
1-21
1-22
ZI.L
-23
SECTION II - UPDATE FORMS
UPDATE FORMS
This section contains the update pads which are in the
Flight Data File onboard the spacecraft.
The CSM forms are as follows:
I. TLI Maneuver
2. P37 Block Data
3. P27 Update
4. P30 Maneuver (External _V)
5. P76
6. CSM Rendezvous Rescue
7. Lunar Entry
8. Earth Orbit Entry
9. Earth Orbit Block Data
The LM forms are:
!. P27 Update
2. AGS State Vector Update
3, Phasing P30 LM Maneuver
4. P30 LM Maneuver
5, DOI Data
6. PDI Data
7. Lunar Surface
8. LM Ascent
9. CSI Data
I0. CDH Data
II. TPI Data
2-I
TLI--Ir-" .._1
X X TB6p _-
X X X X X X R
X X X X X X P TLI
X X X _XX X Y
X X X X X X BT
_VC'
+ + VI
X X X X X X R
X X X X X X p SEP
X X X X X X Y
X X X X R
X X X X P EXTRACTION
X X X X Y
O',',OO_
.-I
FI
2-2
TLI PAD
TB 6p X:XX:XX PREDICTEDTIMEOFBEGINNINGOF(HR:MIN:SEC) S-IVB RESTARTPREPARATIONFOR
TLI (TB6 = TLI IGN -578.6 SEC)
R XXX(DEG) PREDICTEDSPACECRAFTIMUp XXX(DEG) GIMBALANGLESATTLIy XXX(DEG) IGNITION
BT X:XX (MIN:SEC) DURATIONOFTLI BURN
_VC XXXX.X(FPS) NOMINALTLI _V SETINTOEMS AV COUNTER
VI +XXXXX(FPS) NOMINALINERTIALVELOCITYDISPLAYED ON DSKY AT TLICUTOFF
RSEP XXX(DEG) PREDICTEDSPACECRAFTIMUP SEP XXX(DEG) GIMBALANGLESAT COMPLETIONY SEP XXX (DEG) OF S-IVB MNVRTO CSM/S-IVB
SEP ATTITUDE
REXT XXX(DEG) PREDICTEDSPACECRAFTIMUP EXT XXX(DEG) GIMBALANGLESATTIMEY EXT XXX (DEG) OF CSM EXTRACTION OF
LM FROM S-IVB
2-3
P37
BLO
CK
DA
TA
'I.
!O
T,
Xl
ilX
t_V
TX
_X
'L
ON
G[
GET400K
!G
ETI
XX
_V
T
XX
LON
G
GET400K
GETI
XX
AV
T
XX
LON
G
GET400K
GE
TI
eo
XX
AV
T
IX
LO
NG
XBT
GE
T400K
GETI
XX
AVT
XX
LON
G
GET400K
o-.
GE
TI
_OO_.
XX
AV
T
XX
LO
NG
--
GE
T400K
<1:
GE
TI
XX
AV
T
XX
LO
NG
GET400K
2-4
P37 BLOCK DATA
GETI XXX:XX DESIREDTIMEOFIGNITION(HR:MIN)
ZVT XXXX(FPS) TOTALVELOCITYOFMNVR
LONG +XXX(DEG) LONGITUDEOFTHELANDINGPOINT FOR ENTRY GUIDANCE
GET400K XXX:XX TIMEOF ENTRYINTERFACE(HR:MIN)
2-5
P27 UPDATE
PURP V V VInGF T •
304 .)1 INDEX INDEX INDEX
O2
O3
O4
O5
O6
"_ 07bo
11
12
13
14
15
16
17
2O
21O'_
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 X
N43 LAT 0 0
LONG [I
ALT + 0 + 0_i
2-6
P27 UPDATE - CSM
PURP XXX TYPEOFDATATOBERECEIVED (SUCH AS:CMC TIME)
V XX(VERB) TYPEOFCOMMANDLOAD(70-71-72-73)
GET XXX:XX:XX TIMEDATARECORDED(HR:MIN:SEC)
304 Ol XX(OCTAL) INDEXNO. OFCOMMANDWORDS IN LOAD
02-24 XX (OCTAL) CORRECTIONIDENTIFIERS
N34 NAVCHECK XXX:XX:XX.XX TIME FORCONFIRMATION(HR:MIN:SEC) OF GROUNDTRACK
N43
LAT XX.XX(DEG) LATITUDEFORGROUNDTRACK CONFIRMATION
LONG XXX.XX(DEG) LONGITUDEFORGROUNDTRACK CONFIRMATION
ALT XXX.X(DEG) ALTITUDEFORGROUNDTRACK CONFIRMATION
2-7
P30 MANEUVER
PURPOSE
SET STARS I p PROP/GUID
+ WT N47
RALIGN 0 0 PTRIMN48
"o PALl 0 0 YTRIM oco GN e0o + 0 0 I HRS GETI "YALIGN__
+ 0 0 0 MIN N33
+ 0 SEC
z_VX N81ULLAGE.
AVy
Z_V7
X X X R
X X X P
X X X Y
+ HA N42
Hp
+ Z_VT
X X X BTHORIZO N/M/INDOW
X _VC
X X X X SXTS
+ 0 SFT
+ I 0 0 TRNI
0"--o X X X BSSo,.
X X SPA
._ X X X SXPp./_- 0 LAT N61_: OTHER
LONG
+ RTGO EMS
+ VIO
GET 0. 050
2-8
P30 MANEUVER
PURPOSE XXXXX TYPEOFMNVRTOBEPERFORMED
PROP/GUID XXX/XXX PROPULSION SYSTEM (SPS/RCS)/GUIDANCE (SCS/G&N)
WT +XXXXX(!bs) PREMANEUVERVEHICLEWEIGHT
P TRIM +X.XX(DEG) SPSPITCHGIMBALOFFSETTO- PLACETHRUSTTHROUGHTHECG
Y TRIM +X.XX (DEG) SPSYAWGIMBALOFFSETTO- PLACE THRUST THROUGHTHE CG
GETI XX:XX:XX.XX TIMEOFMNVRIGNITION(HRS:MIN:SEC)
aVX +XXXX.X(FPS) P30VELOCITYTOBEGAINED_V¥ TXXXX.X(FPS) COMPONENTSIN LOCALVERTICAL_VZ TXXXX.X(FPS) COORDINATES
R XXX(DEG) IMUGIMBALANGLESOFp XXX(DEG) MANEUVERATTITUDEy XXX(BEG)
HA XXXX.X(NM) PREDICTEDAPOGEEALTITUDEAFTER MANEUVER
HP +XXXX.X(NM) PREDICTEDPERIGEEALTITUDEAFTER MANEUVER
&VT +XXXX.X(FPS) TOTALVELOCITYOF MANEUVER
BT X:XX (MIN:SEC) MANEUVERDUPJ_TION
&VC XXXX.X(FPS) PREMANEUVER&VSETTINGINEMS &V COUNTER
SXTS XX (OCTAL) SEXTANTSTARFORMANEUVERATTITUDE CK
SFT +XXX.X(DEG) SEXTANTSHAFTSETTINGFORMANEUVER ATTITUDE CK
TRN +XX.X (DEG) SEXTANTTRUNNIONSETTINGFORMANEUVER ATTITUDE CK
BSS XX (OCTAL) BORESIGHTSTARFORMANEUVERATTITUDE CK USING THE COAS
2-9
SPA +XX.X(DEG) BSSPITCHANGLEONCOASFORMANEUVER ATTITUDE CK
SXP +X.X (DEG) BSSX POSITIONONCOASFORMANEUVER ATTITUDE CK
LAT +XX.XX(DEG) LATITUDEANDLONGITUDEOFTHELONG YXXX.XX(DEG) LANDINGPOINTFORENTRY
GUIDANCE
RTGO +XXXX.X(NM) RANGETOGOFOREMSINITIALIZATION
VIO +XXXXX(FPS) INERTIALVELOCITYAT .05G FOREMS INITIALIZATION
GET(.05G) XXX:XX:XX.XX TIMEOF .05G(HRS:MIN:SEC)
SETSTARS XX (OCTAL) STARSFORBACKUPGDCALIGNXX (OCTAL)
R, P, Y XXX(BEG) ATTITUDETOBESETIN(ALIGN) XXX(DEG) ATTITUDESETTWFORBACKUP
XXX(DEG) GDCALIGN
ULLAGE X (jETS) NO.OFSMRCSJETSUSEDANDXX.X (SEC) LENGTHOF TIME OF ULLAGE
HORIZON/WINDOW XX.X (DEG) WINDOWMARKINGAT WHICHHORIZON IS PLACED AT ASPECIFIED TIG (ATT CK)
OTHER ADDITIONALREMARKSVOICEDUP BY MCC-H
2-10
THIS PAGE INTENTIONALLY LEFT BLANK.
P76 UPDATE PAD
PURPOSE
+ 0 0 j + 0 0 HR N33+ 0 0 0 j +1 0 0 0 MIN TIG
i
+ 0 _, + 0 SEC
AVX N84[
AVY
AVZi
PURPOSE -oo,. i'_
+ 0 0 ' [ + 0 0 HR N33 o_
+ 0 0 0 + 0 0 0 MtI'4 TIG, j ! , ,
+ 0 I + 0 SEC
AVX 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 AVY
AVZ._ I
PURPOSE
_: + 0 0 + 0 0 HR N33
+ 0 0 0 + 0 0 0 MIN TIG
+ 0 + 0 SEC
AVX N 84
AVY
AVZ
2-11
P76 UPDATE PAD
PURPOSE XXXXX PURPOSEOFMANEUVER
N33TIG XX:XX:XX.XX TIMEOF IGNITION(HR:MIN:SEC)
N84
&VX XXXX.X(FPS) COMPONENTSOF_VY XXXX.X(FPS) &VAPPLIEDALONG_VZ XXXX.X(FPS) LOCALVERTICALAXIS
AT TIG (LM)
2-12
-,(x
a•
i
•O
0p
IOIO
OO
....N
+N
*_
Dooooe
_o,ooo*gO
.•
•O
O_
___
+
V_e-4
2-1
3_
-_"_
__
-__-
v
CSM SEP PAD
33 GETI XXX:XX:XX. XX GET OF CSM/LM SEPARATION(HRS:MIN:SEC) BURN
81 DELTAVX +XXXX.X(FPS) LOCALVERTICALDELTAVY +XXXX.X (FPS) VELOCITYCOMPONENTSDELTAVZ +XXXX.X(FPS) OF SEPBURN
22 R XXX(DEG) SEPARATIONBURNP XXX(BEG) INERTIALGINBALANGLESY XXX(BEG)
DOI PAD
84 DELTAVX XXXX.X(FPS) LM LOCALVERTICALDELTAVY XXXX.X (FPS) VELOCITYCOMPONENTSDELTAVZ XXXX,X(FPS) FORDOI BURN
33 GETI XXX:XX:XX.XX GETOFDOI BURN(HRS:MIN:SEC)
PDI + 12 ABORT PAD
84 DELTAVX XXXX.X (FPS) LMLOCALVERTICALVELOCITYDELTAVY XXXX.X(FPS) COMPONENTSFORFIRSTDELTAVZ XXXX.X(FPS) OPPORTUNITYPDI
PLUS 12 MIN ABORT
33 GETI XXX:XX:XX.XX GETOF PDI + 12(HRS:MIN:SEC) MIN ABORTBURN
"CSM RESCUE" PAD
PHAS 33 GETI XXX:XX:XX.XX GETOF CSM(HRS:MIN:SEC) ABORTPHASINGBURN
TPI 37 GETI XXX:XX:XX.XX GETOFTPI FOR(PDI lO) (HRS:MIN:SEC) LMABORTSBETWEEN
PDI AND PDI + lO MIN
TPI 37 GETI XXX:XX:XX.XX GETOFTPI FOR(PDI lO) (HRS:MIN:SEC) LMABORTSAFTER
PDI + lO MIN
"CSM RESCUE UPDATE" PAD
PHAS 33 GETI XXX:XX:XX.XX GETOF CSM(HRS:MIN:SEC) ABORTPHASINGBURN
FOR 2ND OPPORTUNITY(l REV DELAY)
2-14
TPI (PDI 14.5) GETI XXX:XX:XX.XX GETOF TPI37 (HRS:MIN:SEC) FORLMABORTS
BETWEEN PDI ANDPDI + 14.5 MINFOR 2ND OPPORTUNITY
TPI (T2) GETI XXX:XX:XX.XX GETOF PREFERRED37 (HRS:MIN:SEC) LMLIFTOFFTIME
RESCUE TWO PAD
47 WT XXXX.X(Ibs) PREMANEUVERCSM WEIGHT
48 P TRIM X.XX(DEG) SPSPITCH& YAWGIMBAL OFFSET TO
Y TRIM X.XX (DEG) PLACETHRUSTTHROUGH THE CG
33 GETI XXX:XX:XX.XX GETOFRESCUE(HRS:MIN:SEC) BURN
81 DELTAVX XXXX,X (FPS) LOCALVERTICALDELTAVY XXXX,X (FPS) VELOCITYCOMPONENTSDELTAVZ XXXX.X(FPS) OF RESCUEBURN
22 R XXX(DEG) RESCUEBURNP XXX(DEG) GIMBALANGLESY XXX(BEG)
_Vc _Vc XX.X(FPS) VELOCITYTOBESET IN EMSCOUNTER FOR RESCUEBURN
II GETI XXX:XX:XX.XX GETOFCSI(HRS:MIN:SEC) BURNBASEDON
RESCUE BURN
37 GETI XXX:XX:XX.XX GETOFTPI(HRS:MIN:SEC) BURNBASEDON
RESCUE BURN
N X THEFUTUREAPSIDALCROSSING (APOLUNEOR PERILUNE) OFTHE ACTIVE VEHICLEAT WHICH CDH SHOULDOCCUR
2-15
CSI ONE
II GETI XXX:XX:XX.X GETOFCSI OnE(HRS:MIN:SEC) BURN
81 DELTAVX XXXX.X(FPS) LOCALVERTICALDELTAVY XXXX.X (FPS) VELOCITYCOMPONENTSDELTAVZ XXXX.X(FPS) OFCSI ONEBURN
N X THEFUTUREAPSIDALCROSSING (APOLUNEOR PERILUNE) OFTHE ACTIVE VEHICLEAT WHICH CDH SHOULDOCCUR
CSI TWO, THREE, FOUR
SAME AS ABOVE EXCEPT CSI TWO, THREE, FOUR
CDH
13 GETI XXX:XX:XX.X GETOFCDH(HRS:MIN:SEC BURN
81 DELTAVX XXXX.X (FPS) LOCALVERTICALDELTAVY XXXX.X (FPS) VELOCITYCOMPONENTSDELTAVZ XXXX.X(FPS) OF CDHBURN
TPI
37 XXX:XX:XX.X GETOFLMTPI(HRS:MIN:SEC BURN
81 DELTAVX XXX(FPS LOCALVERTICALDELTAVY XXX(FPS VELOCITYCOMPONENTSDELTAVZ XXX(FPS OFTPI BURN
59 _V (LOS) XXX(FPS VELOCITYCOMPONENTSALONG THE LINEOF SIGHT TO TARGET
LOSBT X:XX MIN:SEC BURNDURATIONALONGTHE LINE OF SIGHT
P22 PAD
T1 XXX:XX:XX.XX GETATWHICH(HRS:MIN:SEC) LANDMARKAPPEARS
ON HORIZON
2-16
T2 XXX:XX:XX.XX GET AT WHICH(HR:MIN:SEC) LANDMARKLOS IS
35° ABOVE LOCALHORIZONTAL
NM(NORS) XX.X(NM) DISTANCEOFLANDMARK NORTH ORSOUTH OF ORBITALTRACK
89 LAT +XX.X(DEG) LATITUDEOF LANDMARKLONG 7XX (DEG) LONGITUDEOF LANDMARKALT ALTITUDEOFLANDMARK
ABOVE OR BELOW MEANLUNAR RADIUS
NOMINAL LM IGNITION TIMES
CSI II GETI XXX:XX:XX.X NOMINALGET(HRS:MIN:SEC) OF LMCSI BURN
PC33 GETI XXX:XX:XX.XX NOMINALGET(HRS:MIN:SEC) OF LM PLANECHANGE
BURN
TPI 37 GETI XXX:XX:XX.XX NOMINALGETOFLM(HRS:MIN:SEC) TPI BURN
2-17
THIS PAGE INTENTIONALLY LEFT BLANK.
LUNAR ENTRY
AREA
X X X X X X R 0.05G
X X X X X X P 0.05G
X X X X X X Y 0.05G
GET HORCK
X X X X X X P
0 ' 0 LAT N61
LONG
X X X X X X MAX G
+ + V400K N60
0 0 - 0 0 ¥400K
+ + RTGO EMS
+ + VIO
RRT
X X X X RET0.05G
+ 0 0 + 0 0 DL MAXN69
mr- + 0 0 + 0 0 DLMIN _:"-ZC --Z + + VLMAX Z_--- zDZ
+ + vLMIN._X_X X X X X DO
X X X X RETVCIRC
X X X X RETBBO
X X X X RETEBOo,,,4Do. X X X X RETDRO
X X X X X X X X SXTS
-- _ 0 + 0 SFT
<: + 0 0 + 0 0 TRN
X X X X X X BSS
X X X X SPA
X X X X X X SXP
X X X X X X X X LIFTVECTOR
2-18
LUNAR ENTRY PAD
AREA XXXXX SPLASHDOWNAREADEFINEDBYTARGET LINE
R .05G XXX(DEG) SPACECRAFTIMUGIMBALANGLESP .05G XXX(DEG) REQUIREDFORAERODYNAMICY .05G XXX(DEG) TRIMAT .05G
GET XXX:XX:XX TIMEOFENTRYATTITUDE(HORCK) (HRS:MIN:SEC) HORIZCHECKAT E! -17 MIN.
P XXX(DEG) PITCHATTITUDEFORHORIZON(HORCK) CHECKATEl -17 MIN.
LAT +XX.XX(DEG) LATITUDEOFTARGETPOINT
LONG +XXX.XX(DEG) LONGITUDEOFTARGETPOINT
MAXG XX.X (G's) PREDICTEDMAXIMUMREENTRYACCELER_,TION
V4OOK +XXXXX(FPS) INERTIALVELOCITYAT ENTRYINTERFACE
400K -X.XX (DEG) INERTIALFLIGHTPATHANGLEATENTRY INTERFACE
RTGO +XXXX.X(NM) RANGETO GOFROM.05GTOTARGETFOR EMS INITIALIZATION
VIO +XXXXX(fps) INERTIALVELOCITYAT ,05GFOR EMS INITIALIZATION
RRT XXX:XX:XX REENTRYREFERENCETIME BASED(HRS:MIN:SEC) ON GET OF PREDICTED400K
(BET START)
RET.05G XX:XX TIMEOF .05GFROM400K(RRT)(MIN:SEC)
DL MAX +X.XX (G's) MAXIMUMACCEPTABLEVALUEOFPREDICTED DRAG LEVEL (FROM CMC)
DL MIN +X.XX (G's) MINIMUMACCEPTABLEVALUEOFPREDICTED DP,AG LEVEL (FROM CMC)
VL MAX +XXXXX(FPS) MAXIMUMACCEPTABLEVALUEOFEXIT VELOCITY (FROM CMC)
2-19
VL MIN +XXXXX(FPS) MINIMUMACCEPTABLEVALUEOFEXIT VELOCITY (FROM CMC)
DO X.XX(G's) PLANNEDDRAGLEVELDURINGCONSTANT G
RET VCIRC XX:XX TIME FROMEl THAT S/C VELOCITY(MIN:SEC) BECOMESCIRCULAR
RETBBO XX:XX TIMEFROMEl TOTHEBEGINNING(MIN:SEC) OFBLACKOUT
RETEBO XX:XX TIMEFROMEl TOTHEENDOF(MIN:SEC) BLACKOUT
RETDRO XX:XX TIMEFROMElTO DROGUEDEPLOY(MIN:SEC)
SXTS XX(OCTAL) SEXTANTSTARFORENTRYATTITUDECHECK
SFT +XXX.X (DEG) SEXTANTSHAFTSETTINGFORENTRY ATTITUDE CHECK
TRN +XX.X(DEG) SEXTANTTRUNNIONSETTINGFORENTRY ATTITUDE CHECK
BSS XXX(OCTAL) BORESIGHTSTARFORENTRYATTITUDE CHECK USING THE COAS
SPA +XX.X(DEG) BSSPITCHANGLEONCOASFORENTRY ATTITUDE CHECK
SXP +X.X(DEG) BSSX POSITIONONCOASFORENTRY ATTITUDE CHECK
LIFT VECTOR XX (UP/DN) LIFT VECTORDESIREDAT .05G'sBASED ON ENTRY CORRIDOR
2-20
THIS PAGE INTENTIONALLY LEFT BLANK.
EARTH ORBIT ENTRY UPDATE
X [ I X Z AREA
X X - X X - _VTO
I X X X R 0.05G EMSX X X IX X X I X X X P 0.05G
X X X X X X Y 0.05G
+ + RTGO EMSI
+ + I VlO1
X ,IX X X RET0.05G
0 0 LAT N61
! LONGi
X X II X X RET0.2Go',,
o-,'° I DRE f55°) N66-- j
/ ••,o" R R ' / R R, / BANK AN
j X X X X RETRB
_: X X X X RETBBQ<
X X X X RETEBO
X X X X RETDRQG
X X X X X X (90°/fps) CHART
X X X X DRE (90°) UPDATE
POST BURN
X X X X X X P 0.05G
+ + RTGO EMS
+ + VIO
X X X X RET0.05G
X X X X RET 0.2Gr'n . _.
Z _ _] DRE::kl00nmN66 O _-
_O R R [ /' R R // BANK AN _ Z
X X i X X RETRBX X X X RETBBO
X X X X RETEBO SECX X X X RETDROGTOMAIN
2-21
EARTH ORBIT ENTRY UPDATE
AREA XX×-X RECOVERYAREA- FIRST3 DIGITS DENOTES REVIN WHICH LANDING OCCURS.LAST DIGIT DENOTESRECOVERY AREA AND SUPPORTCAPABILITIES
AVTO XX.X(FPS) AVDUETOENGINETAILOFF
EMS
RO,05G XXX(DEG) SPACECRAFTIMUP O.05G XXX(DEG) GIMBALANGLESREQUIREDY O.05G XXX(DEG) FORAERODYNAMICTRIM
AT 0.05G.
EMS
RTGO XXXX.X(NM) RANGETOGOFROM.05G TO TARGET
VIO XXXXX(FPS) INERTIALVELOCITYAT .05G FOR EMSINITIALIZATION
RETO.05G XX:XX (MIN:SEC) TIME FROMRETROFIRETO .05G
N61
LAT +XX.XX(DEG) LATITUDEOFIMPACTLANDINGPOINT
LONG +XXX.XX(DEG) LONGITUDEOF IMPACTLANDINGPOINT
N66
RET XX:XX(MIN:SEC) TIMEFROMRETROFIRE.2G TO.2G
DRE(55° ) +XXXX.X(NM) DOWNRANGEERRORAT .2G
BANK AN XX/XX (DEG/DEG) BACKUP BANK ANGLEFOR SCS ENTRY:ROLL RIGHT/ROLL LEFT
2-22
RETRB XX:XX(MIN:SEC) TIME FROMRETROFIRETO REVERSE BACKUPBANK ANGLE
RETBBO XX:XX (MIN:SEC) TIME FROMRETROFIRETOBEGINNING OF COMMUNICATIONSBLACKOUT
RETEBO XX:XX (MIN:SEC) TIME FROMRETROFIRETO ENDOF COMMUNICATIONS BLACKOUT
RETDROG XX:XX (MIN:SEC) TIME FROMRETROFIRETODROGUE CHUTE DEPLOYMENT
CHART UPDATE
90°/FPS ÷XX VALUES USED TO RE-PLOTDRE(90° ) _XXX BACKUPENTRYCHART-
_V AND DOWNRANGE ERROR(DRE) @ 90° BANK ANGLE
POST BURN
P O.05G XXX(DEG) PITCHANGLE@ENTRYINTERFACE
EMS
RTGO +XXXX,X(NM) RANGETOGOFROMO.05GTO TARGET FOR EMS COUNTER
VIO +XXXXX(FPS) [email protected]
RETO.05G XX:XX (MIN:SEC) TIME FROMRETROFIRETO O.5G
RET02G XX:XX (MIN:SEC) TIME FROMRETROFIRETO O.2G
DRE +XXXX.X(NM) DOWNRANGEERROR
BANK AN XX/XX (DEG/DEG) BACKUP BANK ANGLE FOR SCSENTRY: ROLL RIGHT/ROLL LEFT
RETRB XX:XX(MIN:SEC) TIME FROMRETROFIRETOREVERSE BACKUP BANK ANGLE
2-23
RETBBO XX:XX(MIN:SEC TIME FROMRETROFIRETOBEGINNING OF COMMUNICATIONSBLACKOUT
RETEBO XX:XX(MIN:SEC TIME FROMRETROFIRETOENDOF COMMUNICATIONS BLACKOUT
RETDROG XX:XX(MIN:SEC TIME FROMRETROFIRETODROGUE CHUTE DEPLOYMENT
2-24
EARTH ORBIT BLOCK DATA
X X B X X AREA' I
X X X X X X L o LATI _ ! LONGX X [ _, X X , .I |
I
* _ GETI
X X X ! X X X ! I ±VC
i AREAxix j xx .1 , iIX[X X i X X X ' LAT
I LONGX X ! X X .
* l i GETI
.o X X X %Vcxxx ! , I ,
,-" X X X X I j AREAI
_-- X X X X X X LAT
< X X . X X 1 _, LONG• _ ' GETI: t 'xx x xx x 1
• I I'X X X X ' _ AREA,,
X X X ! X X X _ LATIX X X X 1 LONG
I
'T ! GETIX X X X X X ' z_VC
x'< r x x T,-'-m 1 I AREA v°b x x x , x x x LAT d_.o
L.U ._J
:_" X X ! X X I LONG
GETI
, AVCX X X X X X f
REM AR KS:
2-25
EARTH ORBIT BLOCK DATA
AREA XXX-X RECOVERYAREAFIRST 3 DIGITS -LANDING REVOLUTIONLAST DIGIT -RECOVERY AREA ANDSUPPORTCAPABILITIES
LAT +XX.XX(DEG) COORDINATESOFTHELONG TXXX.X(DEG) DESIREDLANDINGAREA
GETI XXX:XX:XX.XX DEORBITIGNITIONTIME(HR:MIN:SEC) FORTHE DESIRED
LANDING AREA
&VC XXX.X (FPS) DEORBITMANEUVER&V TO BE LOADED INTO THEEMS COUNTER.
2-26
LM P27 UPDATE
PO,_ ',1 I ,' I "1 IGET • • • • • •
• ' 1174 01 INDEX INDEX INDEX
O2
03"_4 a-
O4
O5
O6
O7
10
11
12
13
14
15
16
17
o. 20•,OO--
21
"_ 22
"_ 23a_
•,< 24
N34 HR X X X X X X
MIN X X X X X X X X
NAVCHECKSEC X X X X
N43 LAT 0 0 IIII
LONG
ALT + 0 + 0
li
2-27
P27 UPDATE-LM
PURP XXX TYPEOFDATATOBERECEIVED (SUCH AS:LDG TIME)
V XX(VERB) TYPEOFCOMMANDLOAD (70-7]-72-73)
GET XXX:XX:XX TIMEDATARECORDED(HR:MIN:SEC)
I174 Ol XX(OCTAL) INDEXNO.OFCOMMANDWORDSIN LOAD
02-24 XX(OCTAL) CORRECTIONWORDIDENTIFIERS
N34 NAVCHECKTIME XXX:XX:XX.XX TIME FORCONFIRMATION(HR:MIN:SEC) OF GROUNDTRACK
N43
LAT XX.XX(DEG) LATITUDEFORGROUNDTRACK CONFIRMATION
LONG XXX.XX(DEG) LONGITUDEFORGROUNDTRACK CONFIRMATION
ALT XXX.X(NM) ALTITUDEFORGROUNDTRACK CONFIRMATION
2-28
AGS STATE VECTOR UPDATE
PURP
240
241
242
260
261
262
+ + 254
244
245
246
264
265
266
o. + + 272',,0o-
REMARKS:
-J
2-29
AGS STATE VECTOR UPDATE
PURP PURPOSEFORAGSSTATEVECTOR UPDATE
240 +XXXXXI00 FT) LM STATEVECTOR-POSITION- COMPONENTS
241 +XXXXXlO0 FT)
242 +XXXXXlO0 FT)
260 +XXXX.X FPS) LMSTATEVECTOR-VELOCITY- COMPONENTS
261 +XXXX.XFPS)
262 +XXXX.XFPS)
254 +XXXX.X(MIN) LMTIMEFORWHICHTHE STATE VECTOR ISACCURATE
244 +XX×XX(I00 FT) CSMSTATEVECTOR-POSITIONCOMPONENTS
245 +XXXXX(I00 FT)
246 +XXXXX(I00 FT)
264 +XXXX.×(FPS) CSMSTATEVECTOR-VELOCITY- COMPONENTS
265 +XXXX,X(FPS)
266 +XXXX.X(FPS)
272 +XXXX.X(MIN) CSMTIMEFORWHICHTHE STATE VECTOR ISACCURATE
2-30
O7
_.J
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XX
XX
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++
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_
2-31
PHASING
N33 PHASINGTIG XXX:XX:XX.XX IGNITION TIME OF(HR:MIN:SEC) LM MANEUVER
N81 LOCAL VERTICAL AV
AVX +XXXX.X(FPS) LOCALVERTICALAVCOMPONENTS- OFTHEMANEUVER
AVY +XXXX.X(FPS)
AVZ +XXXX.X (FPS)
N42 ORBITAL PARAMETERS
HA +XXXX.X(NM) PREDICTEDAPOGEERESULTINGFROM MANEUVER
HP +XXXX.X(NM) PREDICTEDPERIGEERESULTINGFROM MANEUVER
AVR +XXXX.X(FPS) TOTALAVREQUIREDFORTHE MANEUVER
BT X:XX (MIN:SEC DURATIONOFTHEMANEUVER
FDAI
R XXX(DEG) INERTIALFDAIANGLESAT THE BURN ATTITUDE
P XXX(BEG)
AGS AV
AVXAGS +XXXX.X(FPS LOCALVERTICALAVAVYAGS +"-XXXX.X(FPS COMPONENTSOFTHEAVZAGS _XXXX.X(FPS MANEUVERTO TARGET
- THEAGS
BSS XX(OCTAL) BSSSTARFORMANEUVERATTITUDE CHECK
SPA +XX.X (DEG) BSS PITCH ANGLE ONSXP TXX.X(DEG) COAS,& BSSX POSITION
ON COAS FOR MANEUVERATTITUDE CHECK
2-32
P30 LM MANEUVER13 0LO eq
o !PURPOSE a_
+ 0 0 + 0 0 HR N33
+ 0 0 0 + 0 0 0 MIN TIG
+ 0 + 0 SEC
AVX N81
AVY LOCAL
AVZ VERT
+ + Ha N42
HD
+ + AVR
X X X X X X BT
X X X X X X R FDAI
X X X X X X P INER
AVX AGS N86
AVY AGS
AVZ AGS
X X X X X X BSS
X X X X SPA
X X: X X X X: SXP
PEMARKS:
2-33
P30 LM MANEUVER
PURPOSE XXXXX PURPOSEOFMANEUVER(SUCH AS DOI TARGETING)
N33 TIG OF MANEUVER XXX:XX:XX.XX IGNITION TIME FORTHE MANEUVER(HR:MIN:SEC)
N81 LOCAL VERTICAL AV
AVX +XXXX.X(FPS) LOCALVERTICALAV- COMPONENTSOFTHE
AVY +XXXX.X(FPS) MANEUVER
AVZ +XXXX.X(FPS)
N42 ORBITAL PARAMETERS
HA +XXXX.X(NM) PREDICTEDAPOGEEANDPERIGEE RESULTING FROM
HP +XXXX.X(NM) THEMANEUVER
AVR +XXXX.X(FPS) TOTALAV REQUIREDFORTHEMANEUVER
BT X:XX(MIN:SEC) DURATIONOFTHEMANEUVER
FDAI
R XXX(DEG) INERTIALFDAIANGLESATP XXX(DEG) THEBURNATTITUDE
N86 AGS AV
AVXAGS +XXXX.X(FPS) LOCALVERTICALAV-- COMPONENTSOF THE
AVYAGS +XXXX.X(FPS) MANEUVERUSEDTO- TARGETTHEAGS
AVZAGS +XXXX.X(FPS)
BSS XX(OCTAL) BSSSTARFORBURNATTITUDE CHECK
SPA +XX.X(DEG) BSSPITCHANGLEON- COAS, & BSS X POSITION
SXP +XX.X(DEG) ONCOASFORMANEUVERATTITUDE CHECK
2-34
-QO
Q-
00
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i+,i+
++
×
2-35
DOI DATA CARD
N33 DOI TIG XXX:XX:XX.XX IGNITIONTIMEOF(HR:MIN:SEC) LM MANEUVER
N81 LOCALVERTICALAV LOCALVERTICALAVCOMPONENTSOF THE MANEUVER
AVX +XXXX.X(FPS)
AVY +XXXX.X(FPS)
AVZ +XXXX.X(FPS)
N42 ORBITAL PARAMETERS
HA +XXXX°X(NM) PREDICTEDAPOGEERESULTINGFROM MANEUVER
HP +XXXX.X(NM) PREDICTEDPERIGEERESULTINGFROM MANEUVER
AVR +XXXX.X(FPS) TOTALAVREQUIREDFORTHE MANEUVER
BT X:XX (MIN:SEC) DURATIONOFTHEMANEUVER
FDAI
R XXX(DEG) INERTIALFDAIANGLESAT THE BURN ATTITUDE
P XXX(BEG)
N86 AGS AV
AVXAGS +XXXXoX(FPS) LOCALVERTICALAVAVY AGS +-XXXX.X (FPS) COMPONENTSOF THEAVZ AGS +--XXXX.X (FPS) MANEUVERTO TARGET
THE AGS
BSS XXX (OCTAL) BSS STAR FOR MANEUVERATTITUDE CHECK
SPA +XX.X(DEG) BSSPITCHANGLEONSXP TXX.X(DEG) COAS,& BSSX POSITION
-- ONCOASFORMANEUVERATTITUDE CHECK
2-36
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2-37
PDI DATA CARD
PDI PAD
TIG PDI XXX:XX:XX°XX PDI IGNITIONTIME(HR:MIN:SEC)
TGO XX:XX(MIN:SEC) TIMETOHIGHGATE
CROSSRANGE +XXXX.X(NM) OUT-OF-PLANEDISTANCEBETWEEN THE INITIAL LMORBITAL PLANE AND THELANDING SITE (POSITIVEINDICATES LANDING SITEIS NORTH OF ORBITAL PLANE)
FDAI AT TIG
R XXX(DEG) INERTIALFDAIANGLESP XXX(DEG) ATIGNITIONY XXX(BEG)
DEDA231 XXXXX(I00 FT) LUNARRADIUSATTHE(IF REQ'D) LANDINGSITE
PDI ABORT <I0 MIN
TPI TIG XXX:XX:XX.XX TPI IGNITIONTIME(HR:MIN:SEC)
PDI ABORT >lO MIN
PHASINGTIG XXX:XX:XX,XX TIME OF IGNITIONOF(HR:MIN:SEC) LM PHASINGMANEUVER
TPI TIG XXX:XX:XX,XX TPI IGNITIONTIME(HR:MIN:SEC)
2-38
NO PDI +12 ABORT
N33 ABORTTIG XXX:XX:XX.XX IGNITION TIME FOR(HR:MIN:SEC) ABORTBURN
N81 LOCAL VERTICAL AV
AVX +XXXX.X(FPS) LOCALVERTICALAVCOMPONENTSOF THE
AVY +XXXX.X(FPS) PHASINGMANEUVER
AVZ +XXXX.X(FPS)
N42 ORBITAL PARAMETERS
HA +XXXX.X(NM) PREDICTEDAPOGEERESULTING FROM HANEUVER
HP +XXXX.X(NM) PREDICTEDPERIGEERESULTING FROM MANEUVER
AVR XXXX.X(FPS) TOTALAVREQUIREDFOR THE MANEUVER
BT X:XX (MIN:SEC) DURATIONOFMANEUVER
FDAI
R XXX(DEG) INERTIALFDAIANGLESAT THE BURN ATTITUDE
P XXX(DEG)
N86 AGS AV
AVXAGS +XXXX.X(FPS) LOCALVERTICALAVCOMPONENTS OF THE
AVYAGS +XXXX.X(FPS) MANEUVERTO TARGETTHE AGS
AVZAGS +XXXX.X(FPS)
Nil CSl TIG XXX:XX:XX.XX TIME OF IGNITION(HR:MIN:SEC) FORCSI BURN
N37 TPI TIG XXX:XX:XX.XX TIME OF IGNITION(HR:MIN:SEC) FORTPI BURN
2-39
THIS PAGE INTENTIONALLY LEFT BLANK.
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2-40
LUNAR SURFACE DATA CARD
T2 ABORT
T2 TIG XXX:XX:XX.XX LIFTOFFTIME-(HR:MIN:SEC) SECONDPREFERRED
TIME AFTER TOUCH-DOWN(_T.D. +12 MIN.)
N33 PHASINGTIG XXX:XX:XX.XX TIME OF IGNITION(HR:MIN:SEC) FORPHASINGBURN
Nil CSI TIG XXX:XX:XX.XX TIME OF IGNITION(HR:MIN:SEC) FORCSI BURN
N37 TPI TIG XXX:XX:XX,XX TIME OF IGNITION(HR:MIN:SEC) FORTPI BURN
T3 ABORT
T3 TIG XXX:XX:XX,XX LIFT OFFTIMEAFTER(HR:MIN:SEC) FIRST CSMREVOLUTION
CSMPERIOD XXX:XX:XX.XX CSMORBITALPERIOD(HR:MIN:SEC)
P + AT XXX:XX:XX.XX CSMPERIODPLUSTHE(HR:MIN:SEC) TIME INTERVAL BETWEEN
CLOSEST APPROACH ANDLIFTOFF TIMES
Nil CSI TIG XXX:XX:XX.XX TIME OF IGNITION FOR(HR:MIN:SEC) CSI BURN
N37 TPI TIG XXX:XX:XX°XX TIME OF IGNITION FOR(HR:MIN:SEC) TPI BURN
2-41
LM ASCENT PAD
+ 0 0 + 0 0 HRS
+ 0 0 0 i + 0 0 0 MIN TIGL
+ 0 I + 0 SECI
+ _ + V(NOR)+ + V (VERT)N76
0 0 *CROSSRANGE
DEDA 047
DEDA 053
DEDA225/226
j DEDA 231
2-42
LM ASCENT PAD
ASCENTTIG XXX:XX:XX.XX TIMEOF APS IGNITION(HR:MIN:SEC FOR LM ASCENT
N76 INSERTION TARGET
V(HOR) XXXX.X(FPS HORIZONTALVELOCITYAT ORBIT INSERTION
V(VERT) XXXX.X(FPS VERTICALVELOCITYATORBIT INSERTION
CROSSRANGE +XXX.X(NM) CROSSRANGEDISTANCEAT ORBITAL INSERTION
DEDA047 XXXXXX(OCTAL) SINEOFLANDINGAZIMUTH ANGLE
DEDA053 XXXXXX(OCTAL) COSINEOFLANDINGAZIMUTH ANGLE
DEDA225 XXXXXX(I00 FT) LOWERLIMIT OF _AT ORBIT INSERTION
DEDA226 XXXXXX(lO0 FT) UPPERLIMIT OFG_AT ORBIT INSERTION
DEDA231 XXXXXX(lO0 FT) RADIALDISTANCEOF LAUNCH SITEFROM CENTER OFMOON
2-43
2-44
CSI DATA CARD (P32 LM MANEUVER)
N!l CSI TIG XXX:XX:XX.XX CSl IGNITIONTIME(HR:MIN:SEC)
N37 TPI TIG XXX:XX:XX.XX TPI IGNITIONTIME
(HR:MIN:SEC)
N81
AVX XXX.X(FPS LOCALVERTICALAVCOMPONENTS OF THE
AVY XXX.X(FPS CSl MANEUVER
FDAIPITCH XXX(DEG) FDAI INERTIALPITCHANGLE AT THE CSlBURN ATTITUDE
DEDA373 XXXX.X(MIN) AGSIGNITIONTIMEOFNEXT MANEUVER
DEDA275 XXXX.X(MIN) DESIREDTPI TIG (FORCSl CALCULATION ONLY)
N86 AGS AV
AVXAGS XX°XX(FPS) LOCALVERTICALAVCOMPONENTSOF CSl USED
AVYAGS XX.XX(FPS) TOTARGETAGSEXTAV
AVZAGS XX.XX(FPS)
2-45
2-46
CDH DATA CARD
NI3 CDHTIG XXX:XX:XX.XX IGNITIONTIME FOR(HR:MIN:SEC) CDHMANEUVER
N81 LOCAL VERTICAL AV
AVX +XXX.X(FPS) LOCALVERTICALAVAVY TXXX.X(FPS) COMPONENTSOFCDHAVZ TXXX.X(FPS) MANEUVER
PLMFDAI XXX(DEG) FDAIINERTIALPITCH ANGLE ATCDH BURN ATTITUDE
DEDA373 XXXX.X(MIN) AGSIGNITIONTIMEOFNEXT MANEUVER
N86 AGS AV
AVXAGS +XXX.X(FPS) LOCALVERTICALAV_VYAGS _XXX.X(FPS) COMPONENTSOFCDH&VZAGS TXXX.X(FPS) USEDTOTARGETAGS
EXT AV
2-47
2-48
TPI DATA CARD
N37 TPI TIG XXX:XX:XX,XX IGNITIONTIME FOR(HR:MIFI:SEC) THE TPI HANEUVER
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SECTION IV - DETAILED TEST OBJECTIVES
SECTION 4
DETAILED OBJECTIVE ACTIVITIES
This section contains the activity summaries which reflect the testobjectives for Mission G as described in "Mission 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.
Each activity summary provides the following information:
A. TEST OBJECTIVES. This is the listing of the Functional TestObjectives (complete or partial) which relate to theparticular activity;
B. TEST REQUIREMENTS. Here the special test prerequisites (andmission phase if necessary) are presented in addition to briefstatements 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; and
D. DATA REQUIREMENTS. This part of the summary identifies thegross data which are needed for evaluation of test resultsin terms of flight crew and ground support requirements.
Cross references for relating Detailed and Functional 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.
4-I
TABLE 4-IMISSION ACTIVITY AND
TEST OBJECTIVE CROSS REFERENCE
ACTIVITY FTO
LMDescent D-l, G-l, G-3, H-l, M-I
Lunar Surface Navigation G-l, G-2, G-3, L-4, M-2
EVA Preparation and Egress B-l, B-2, C-l, C-2, C-3, L-l
Surface Sample Collection A-l, E-l, F-l, F-2, I-3, J-2, J-3,J-4, M-3
External LM Observations and Photography D-l, D-2, D-3, D-4, L-2, M-3
Lunar Surface Observations and Photography E-l, E-2, E-3, H-2, J-5, L-3, L-4,M-3
Experiment Deployment/Conduct S-031, S-078, S-080
Post EVA Operations B-l, C-l, C-2
Contamination Prevention I-l, I-2
4-2
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4-5
LM DESCENT
A. Test Objective
D-l LM Landing Gear Performance Under Landing ConditionsG-l Location of the Landed LM from LM DataG-3 Capability of Locating the Landed LM in Real Time from
LM/CSM/MSFN DataH-l Data on Landing Aids and Final Approach VisibilityM-l Photograph Lunar Surface During LM Descent
B. Test Requirements
I. Determine landing site visibility, extent of washout and visibilityof landing site landmarks. [H]
2. Photograph the landing site during the approach through the LM pilot'swindow with the data acquisition camera. [G, H, M]
3. Evaluate landing aids, i.e., Landing Point Designator, maps, photo-graphs. [G, H]
4. Assess visual phenomena during LM landing which are significantly differentfrom expected. [H]
5. Voice anotate location and identity of features during final descent.[m]
6. Determine landing location in real time by description of terrainfeatures during descent. [G]
7. Assess LM landing conditions on the lunar surface. [D]
C. Procedures/Checklist
I. Photographic and Television Operations Plan.
2. Descent Procedures Document.
D. Data Requirements
I. Flight Crew Reports/Logs/Photographs
a. LM crew comments on landing site visibility during final approachand landing phases and on effectiveness of the Landing Point Desig-nator and landing site recognition aids. [H] (M)
b. GET at start of data acquisition camera photographs during LMfinal approach. [H] (M)
c. Voice track regarding observations of surface features during thedescent phase. [G] (M)
d. Photographs of the landing site and surrounding lunar surfacefeatures taken through a LM window during descent. [G, M] (M)
4-6
e. Data Acquisition Camera photographs of the landing site fromhigh gate to touchdown. [H, M] (M)
f. Photographs of the landing site and surrounding lunar surfacefeatures taken through a LM window during descent. [G, M] (N)
g. Comments on any lunar dust observed during the final approach,the severity of the landing and vehicle stability after touchdown.[D] (M)
2. Ground Support
a. LM TM HBR. [D, G, H] (I,1)
b. LM TMLBR. [D, G] (M)
c, LM BET from DOi through touchdown. [G, H] (M)
d. MSFN tracking data of LM from acquisition of signal throughtouchdown. [G] (F4)
4-7
LUNAR SURFACE NAVIGATION
A. Test Objectives
G-I Determine the Location of the Landed LM from LM DataG-2 Determine the Location of the Landed LM from CSM DataG-3 Determine Capability of Locating the Landed LM in Real Time
from LM/CSM/MSFNDataL-4 Panoramic Coverage of Distant Terrain FeaturesM-2 Photograph Lunar Surface Post Touchdown/Pre EVA
B. Test Requirements
I. Correlate lunar surface features surrounding the landing site withphotomaps and mark the LM location. [G, L, M]
2. Photograph terrain features thru the LM window to correlate LM location.[G, M]
3. Obtain two sets of LM IMU alignments after landing [G]
4. Provide TV coverage of prominent terrain features. [G, L]
5. Track the landed LM from the CSM during two orbital passes. Markon a landmark near the landed LM. [G] - (Only one pass is implemented.)
6. Track the CSMwith LM RR during one pass. [G] - (Not Implemented.)
7. Obtain 70 MM photographs of the landed LM or its shadow and the sur-rounding lunar features. [G]
8. Assist MCCHin determining the landing LM location in real time. [G, L]
C. Procedures/Checklist
I. Photographic and Television Operations Plan.
2. LM AOH, "PGNCS Lunar Surface Align Program (P57)".
3. LM AOH, "Lunar Surface Navigation Program (P22)"
4. CSM AOH, "Orbital Navigation (P22)".
D. Data Requirements
I. Flight Crew Reports/Logs/Photographs
a. Estimate of the landed LM location on lunar photomaps. [G] (M)
4-8
b. Comments by LM crew regarding any difficulties encountered inestimating the location of the LM with respect to lunar surfacefeatures. [G] (HD)
c. Comments by LM crewman on location of landed LM with respectto prominent terrain features. [G] (M)
d. Obtain high resolution photographs of the landing area from theCSM. [G] (M)
e. Photographs of the landing site and surrounding lunar surfacefeatures taken through a LM window after landing. [G, M] (M)
f. Provide TV coverage of the lunar surface as viewed from the LM.[G, L] (M)
2. Ground Support
a. LM TLM HBR. [G] (M)
b. LM TLM LBR. [G] (M)
c. BET of CSM during the lunar surface phase. [G] (M)
d. BET of LM from DOI through touchdown. [G] (M)
e. Photographs of the landing area obtained during previous lunarmissions. [G] (M)
f. Post-scan conversion video tape of all TV coverage. [L] (M)
g. Estimate solar illumination established by mission geometry. [L] (M)
h. Reflectivity and geometry of surfaces contributing to indirectillumination. [L] (HD)
4-9
EVA PREPARATION AND EGRESS
A. Test Objectives
B-l Demonstrate Egress-to/Ingress-from the Lunar SurfaceB-2 Evaluate Crew Lunar Surface EVA CapabilityC-l EMU Capability to Provide a Habitable EnvironmentC-2 EMU Effects on Crew Mobility/Dexterity/ComfortC-3 Data/Voice Communications Capability During EVAL-I TV Coverage of an Astronaut Descending to the Lunar Surface
B. Test Requirements
I. Perform EVA preparations. [C]
2. Release the MESA pallet with pre-mounted TV camera and turn camerapower on prior to descent to the lunar surface. [L]
3. Egress to the lunar surface. [B, C]
4. Deploy and set the TV camera to provide TV coverage of the lunar surfaceEVA. [L]
5. During EVA, communicate with MSFN via the EVA-LM-MSFN two way voicerelay. [C]
6. Two-way voice communications to be performed between two EVA crewmen.[c]
7, EMU and biomedical data from two EVA crewmen will be simultaneouslytransmitted to MSFN via EVA-LM-MSFN one-way relay, [C]
C. Procedures/Checklist
I. EVA Procedures Document.
2. Lunar Surface Operations Plan.
D. Data Requirements
I. Flight Crew Reports/Logs/Photographs
a. Notify MSFN of the initial and final positions of the PLSS waterdiverter valve, primary oxygen shutoff valve and water shutoff/relief valve each time they are changed. [C] (M)
b. Notify MSFN when PLSS; High 02 flowrate, low vent flow, low feedwater pressure or PGA pressure low remote control unit statusindicators and audible warning tone come on, [C] (M)
4-10
c Record EMU radiation dosimeter readings just prior to the EVA.[c](M)
d Notify MSFN if noxious odors occur or any condensation on thevisor assembly. [C] (HD)
e Comment on the adequacy of procedures and difficulties encounteredduring donning of EMU equipment. [C] (HD)
f Comment on time required and adequacy of the EMU checkout pro-cedures. [C] (MD)
g Comment on the adequacy of EMU thermal environment when walkingfrom a sunlit area to shadow and vice versa. [C] (_)
h Comment on estimated energy expenditure and comfort as comparedto simulation experience. [C] (HD)
i Provide data on the adequacy of hardware and procedures, and thetime required to perform the egress from the LM. [B] (M)
j. Comment on voice quality for EVA-EVA and EVA-LM-MSFN communications.[C] (M)
k. Provide sequence camera coverage and TV camera coverage of: [B, M](M)
l) A crew member descending to the lunar surface.
2) A crew member walking on the lunar surface.
3) A crew member performing lunar surface EVA operations.
2. Ground Support
a. LM TM FM. EB, C] (M)
b. Ground recorded TV signals. [B] (HD)
c. LM TM LBR. [k] (HD)
d. Post-scan conversion video tape of all TV coverage. ILl (M)
e. Record of S-band signal strength during video transmission. ILl (HD)
f. GET at beginning and end of TV transmission. [L]
g. Time period, if any, when LBR TM (in lieu of HBR TM) transmittedsimultaneously with TV data. [L] (M)
4-1i
h. Identity of ground station(s) used to record video transmissionfrom LM. [L] (M)
i. Time period, if any, when erectable antenna used to transmitTV data. [L] (M)
j Estimate of incident illumination. [L] (M)
k. LM position on lunar surface. [H] (HD)
I. MSFN recording of EVA-LM-MSFN voice. [C] (M)
4-12
SURFACE SAMPLE COLLECTION
A. Test Objectives
A-I Provide a Contingency Lunar Surface SampleE-I Behavior and Characteristics of the Lunar SurfaceF-I Collect Rock Samples and Fine Grained MaterialF-2 Photograph Collection Area of SamplesI-3 Obtain a Lunar Sample for Quarantine TestingJ-2 Obtain a Core Sample of the Lunar SurfaceJ-3 Collect Lunar Geologic SamplesJ-4 Collect a Lunar Environment SampleM-3 Obtain Photographs of Geologic Inspection & Sampling
B. Test Requirements
I. Contingency Sample - Obtain upon first descending to the lunar surface.[A]
2. Bulk Material - Obtain 30 pounds consisting of I/3 fragmentary and 2/3loose samples. [F]
3. Core Sample - Obtain with the drive tube. [I, J]
4. Geologic Samples - Obtain using tools stowed in the MESA. Photographsample areas. [J, M]
5. Lunar Environment Sample - Seal in gas analysis container. [J]
C. Procedures/Checklist
I. Lunar Landing Mission Flight Plan.
2. Lunar Surface Operations Plan.
3. Photographic and Television Operations Plan.
D. Data Requirements
I. Flight Crew Reports/Logs/Photographs
a. Record areas in relation to LM where samples were collected.[A, F, a] (M)
b. Record unusual lunar surface observations. [A, F, J] (M)
c. Comment on soil behavior during collection of Bulk Sample. [E] (M)
d. Comment on soil behavior during collection of Documented Sample.[E] (HD)
e. Estimates of volume of fine grained material collected in onebag of the Documented Sample. [E] (HD)
4-13
f. Take photographs during sample collection. [A, F] (HD)
g. Photograph the lunar surface sample areas and of the samples asdefined in the Photographic Operations Plan. [J] (M)
2. Ground Support
a. LM position on lunar surface. [J] (M)
b. MSFN recordings of all MSFN/EVA voice conferences. [J] (M)
4-14
EXTERNAL LM OBSERVATIONS AND PHOTOGRAPHY
A. Test Objectives
D-I Effects of Landing on LM Landing GearD-2 Effects of Landing on LM Structure and ComponentsD-3 Descent Engine Skirt Damage and Clearance After LandingD-4 Effects of RCS Plume Impingement on LM Structure and ComponentsL-2 TV Coverage of External Landed LMM-3 Obtain Photographs of Landed LM
B. Test Requirements
I. Operate the TV camera to provide an external view of the LM. [L]
2. Photograph any observed LM external structural damage. [D, M]
3. Determine descent engine skirt ground clearance. [D, M]
4. Photograph any effects of RCS plume impingement observed. [D, M]
5. Obtain photographs of any lunar material collected on the LM. [D, M]
C. Procedures/Checklist
I. Mission G Photographic and Television Operations Plan.
D. Data Requirements
I. Flight Crew Reports/Logs/Photographs
a. Comment on any LM component damage to include any visible dis-coloration or lunar soil accumulation. [D] (M)
b. Comments describing any descent engine skirt damage and estimateof any skirt ground clearance. [D] (M)
c. If the landing gear strut assembly photographs cannot be obtained,estimate the amount of stroking of each primary and secondary strutassembly. [D] (M)
d. Photograph the landing gear to show the stroking of the primary andsecondary strut assemblies. [D, M] (M)
e. Photograph the LM exterior showing any structural damage. [D, M] (M)
f. Photograph each landing gear assembly along the Z axis and theY axis. [D, M] (HD)
4-15
g. Photograph the descent engine skirt. [D, M] (HD)
h. Photograph the LM base heat shield. [D, M] (HD)
i. Photograph the LM exterior, i.e., structure antenna, RCS jets,windows and foot pads. [D, M] (HD)
j. Photograph soil accumulation on the LM. [D, M] (HD)
k. Photographs by the close up stereo camera of lunar materialadhering to LM surfaces. [M] (HD)
2. Ground Support
a. kM TM HBR. [D] (M), [L] (HD)
b. LM Mass, center of gravity and mass moment of inertia calculations.[E] (M)
c. Video tape of all TV coverage. [L] (M)
d. Record of S-band signal strength during TV coverage. ILl (HD)
e. GET at beginning and end of TV operations.
f. Time period of simultaneous LBR TM and TV transmission. [L] (M)
g. Identification of ground station(s) used to record video transmission.[L] (M)
h. Time period when erectable antenna was used to transmit from lunarsurface. [L] (M)
4-16
LUNAR SURFACE OBSERVATIONS AND PHOTOGRAPHY
A. Test Objectives
E-I Behavior and Characteristics of the Lunar SurfaceE-2 Erosion of Lunar Surface by DPS Plume ImpingementE-3 Effect of Any DPS Venting on the Lunar SurfaceH-2 Crew Performance of Visual Tasks on the Lunar SurfaceJ-5 Study and Description of Lunar Topography FeaturesL-3 TV Coverage of Lunar Surface Near LM[o-4 TV Panoramic Coverage of Distant Terrain FeaturesL-5 Coverage of Astronaut Activities on the Lunar SurfaceM-3 Obtain Photographs During EVA
B. Test Requirements
I. Provide TV coverage of the lunar surface in the vicinity of theLM and panoramic scenes of distant terrain features. [L]
2. Photograph the lunar terrain at various azimuths with respect to the sunincluding 9, 90 and 180 degrees. Comment on ability to see terrainfeatures in these areas. LH, M]
3. Estimate the distance to prominent terrain features within the fieldof view of photographs taken. [H]
4. Observe lunar surface characteristics including texture, consistency,compressibility, cohesiveness, adhesiveness, density and color. [E]
5. Study and photograph the mechanical behavior of the lunar surfacefrom interactions of astronauts boots and equipment with the lunarsoil, erosion by DPS plume impingement and DPS venting. [E, M]
6. Describe and photograph field relationships such as shape, size,range, pattern of alignment or distribution of all accessible typesof lunar topographic features. [J,M]
7. Photograph the structure of lunar surface material in its naturalstate. [M]
C. Procedures/Checklist
I. Mission G Photographic and Television Operations Plan.
D. Data Requirements
I. Flight Crew Report/Logs/Photographs
a. Report condition of the temperature indicator viewing portson the TV camera at the beginning and the end of the TVoperations. [L] (M)
4-17
b. Position of the TV camera scan rate switch at start of TVoperation. [L] (M)
c. Comments describing the interaction between astronaut boots andlunar surface while walking. [E] (M)
d. Comments on slope and roughness characteristics of the landingterrain to include descriptions of craters, depressions, embank-ments or other obstacles. [E] (M)
e. Comments on the color and texture of both undisturbed andmechanically disturbed areas of the lunar surface. [E] (M)
f. Comments on lunar soil conditions adjacent to DPS vents to includeany discoloration. [E] (M)
g. Comments describing the lunar surface penetration by the SolarWind Composition Staff and core sample tool under their own weightand the estimated force. [E] (Mandatory for either the staff or thecore sample tool: highly desirable for the other.)
h. Comments on lunar soil erosion as caused by the DPS plume im-pingement during landing. [E] (M)
i. Record vent valves opened. [E] (M)
j. Photograph the lunar surface showing DPS plume impingement erosiveeffects. [E, M] (M)
k. Photograph the lunar surface adjacent to DPS vents if soil discolora-tion is observed. [E, M] (M)
I. Photograph an astronaut footprint showing interaction betweenastronaut boots and lunar surface. [E, M] (M)
m. Photograph the Solar Wind Composition Experiment Staff and coresampling tool after being inserted to their maximum depth aspenetrometers. [E, M] (HD)
n. Photograph the natural slopes, crater walls and embankmentsin the vicinity of the landing site. [E,M] (M)
o. Photograph from the CSM of the lunar surface surrounding the LM.[E, M] (HD)
p. Comments on the visibility of the lunar terrain as a function ofthe sun/viewing angle and on their ability to perform visual taskswhile on the lunar surface. [H] (M)
4-18
q. Comments on color/contrast perception. [H] (M)
r. Comments on and significant unexpected visual phenomena. [H] (M)
s. Estimate of distance to at least one prominent terrain feature withinthe field of view of the photographs in item t below. [HI (M)
t. Photograph the lunar terrain at various sun azimuths to include 0degrees, 90 degrees and 180 degrees. [H, M] (M)
u. Photograph any unexpected visual phenomena. [H, M] (HD)
v. Photograph a representative depression caused by use of thescoop in collecting fine grained fragmental material. [E, M] (M)
w. Photograph one scoop of fine grained fragmental material placed inone of the pre-numbered bags. [E, M] (HD)
x. Photograph of each LM foot pad and surrounding lunar soil exhibitingevidence of LM foot pad-lunar soil interaction. [M] (HD)
2. Ground Support
a. LM TM HBR. [m, L] (HD)
b. Estimate of incident illumination. [D] (M)
c. Video tape of all TV coverage. [L] (M)
d. Record of S-band signal strength during TV transmission. [L] (M)
e. GET at beginning and end of TV transmission. [L] (M)
f. Time period when LBR TM was transmitted simultaneously with TV.ILl (m)
g. Identity of ground station(s) used to record LM video trans-mission. [L] (M)
h. Time period when erectable antenna was used to transmit from thelunar surface. [L] (M)
4-19
EXPERIMENT DEPLOYMENT/CONDUCT
A. Test Objectives
S-031 Deploy the Passive Seismic Experiment PackageS-078 Deploy the Laser Ranging Retro-Reflector ExperimentS-080 Conduct the Solar Wind Composition Experiment
B. Test Requirements
I. Emplace, level and orient the Passive Seismic Experiment Package(PSEP). Deploy the solar panels and aim the antenna at the earth.[S-031 ]
2. Photograph the deployed PSEP and deployment area. [S-031]
3. Remove the Laser Ranging Retro-Reflector (LRRR) from the descentstage and carry it to the deployment site. [S-078]
4. Emp-lace, level and orient the LRRR to the alignment marks correspondingto she landing site. [S-078]
5. Remove the Solar Wind Composition Experiment from the LM MESA anddeploy it on the lunar surface. [S-080]
6. After one hour operation, disassemble the Solar Wind CompositionExperiment, place the reel and foil in a teflon bag and store in asample return container. [S-080]
C. Procedures/Checklist
None
D. Data Requirements
I. Flight Crew Reports/Logs/Photographs
a. Comment on deployment of experiment. [S-031] (M)
b. Photograph deployment area. [S-031, S-078, S-080] (HD)
c. Comment on location of deployed experiment with respect to theLM, attitude of deployed foil with respect to the sun and totaltime foil was deployed. [S-080] (M)
d. Retrieve reel and foil from the Solar Wind Composition Experiment.IS-080] (M)
e. Comments on orientation and elevation setting used for deployment.[S-078] (HD)
2. Ground SuDport
a. Experiment TLM Data [S-031] (M)
4-20
POST EVA OPERATIONS
A. Test Objectives
B-l Demonstrate Egress-to/Ingress-from the Lunar SurfaceC-l EMU Capability to Provide a Habitable EnvironmentC-2 EMU Effects on Crew Mobility, Dexterity/Comfort
B. Test Requirements
I. Perform post EVA preparations and ingress. [B]
2. Perform PLSS shutdown. [C]
C. Procedures/Checklist
I. EVA Procedures Document.
D. Data Requirements
I. Flight Crew Reports/Logs/Photographs
a. Notify MSFNof the initial and final positions of the PLSS waterdiverter valve, primary oxygen shutoff valve and water shutoff/relief valve each time they are changed. [C] (M)
b. Notify MSFNwhen PLSS; High 07 flowrate, low vent flow, low feedwater pressure or PGA pressur_ low remote control unit statusindicators and audible warning tone come on. [C] (M)
c. Provide data on the adequacy of hardware and procedures, and thetime required to perform the ingress to the LM. [B] (M)
d. Comment on the adequacy of procedures and difficulties encounteredduring doffing of EMUequipment. [C] (HD)
e. Record quantity of water drained from PLSS at end of EVA period.[C] (M)
f. Record EMU radiation dosimeter readings after completion of the EVA.[C] (M)
g. Provide sequence camera coverage and TV camera coverage of a crewmember ascending the LM ladder. [B] (M)
4-21
Contamination Prevention
A. Test Objectives
I-l Prevent Earth Contamination by Lunar Exposed MaterialsI-2 Minimize Crew/CM Contamination by Lunar Exposed Materials
B. Test Requirements
I. All contamination related operations from the initial astronautegress to the lunar surface until postflight crew/cm quarantinewill be completed per procedures contained in _he documents listedbelow. [I]
C. Procedures/Checklist
I. Lunar Surface Operations Plan
2. EVA Procedures Document
3. Quarantine Procedures
D. Data Requirements
I. Flight Crew Reports/Logs/Photographs
a. Crew comments on the adequacy of Biological Isolation Garment,sample return containers, Mobile Quarantine Facility and relatedequipment and procedures used to prevent back contamination. [I] (M)
b. Photograph boots, clothing and equipment showing adhesion ofparticles. [I, M] (HD)
2. Ground Support
a. Deliver samples, CM and Mobile Quarantine Facility to the LunarReceiving Laboratory. [I] (M)
b. Comment on ground procedures and hardware used for retrieval,biological isolation and CM transfer to the Lunar ReceivingLaboratory. If] (M)
c. Report on the existence of contamination of the crew on CM. [I] (M)
4-22
SECTION V - CONSUMABLESANALYSIS
NOTE
Acknowledgement is made to the Consumables Analysis Section (CAS) of theMission Planning and Analysis Division (MPAD) for their work in thepreparation of the consumable analysis presented herein and to the CrewSystems Division for the PLSS Consumables.
5-i
CSM-IO7/LM5 PROPELLANT BUDGET
The results of the Propellant Budget Analysis are summarized in thefollowing Tables and Figures:
TABLE 5-I SM RCS Propellant Loading And Usage Summary
TABLE 5-2 SM RCS Budget
TABLE 5-3 CM RCS Propellant Summary
TABLE 5-4 SPS Propellant Summary
TABLE 5-5 SPS Assumptions
TABLE 5-6 LM RCS Propellant Loading And Usage Summary
TABLE 5-7 LM RCS Budget
TABLE 5-8 DPS Propellant Summary
TABLE 5-9 DPS Assumptions
TABLE 5-10 APS Propellant Summary
TABLE 5-11 APS Assumptions
FIGURE 5-I Total SM RCS Propellant Profile
FIGURE 5-2 Quad A SM RCS Propellant Profile
FIGURE 5-3 Quad B SM RCS Propellant Profile
FIGURE 5-4 Quad C SM RCS Propellant Profile
FIGURE 5-5 Quad D SM RCS Propellant Profile
FIGURE 5-6 Total LM RCS Propellant Profile
5-I
S<-RCS }UDOET
_';ROU}_D P!ff,E8 and ASS_Z;PTiONS
I. _'he transposition and dccking pkase of tke mission includes
am SPS evasive maneuver.
2. _qke first an_ _hird milccurse eorrectiors (trans!Rnar _ are
executed as SP8 burns with the C_ird kCC fol!owei by an _qS tri,L.
}. To SY RCS propellant is req_ired durin.- R_-'Cor lunar orTit
c:_ast.
£. %}le sixL__i :Rideotlrse c_rre_'tiou (transeart}) is execute_l as
an RCS %urn cf 5 fps.
p. Qle individual ouad plots are included for reference en!//
as ouart mana;emer_t is determined %2," the flijkt controllers dur!n S
she mission.
TABLE 5-1
.$Y RC$ PPOPEL!A'rT LOADIN3 AND ,,rSANE SL%KARY
Kominal loadel 1}42._ lb
Initial outage due to loaded mixture ra¢io 15.6
Totaltrapped _6.4
<augin6inaccuracy $0.4
Seliverable SX-RCS propellant 122C.0
Nominalusage 590
Translunar phase (through LOI-2) 204
Lunaroreitphase _II
Transearth Phase (includes TEl) 75
Nominalremaining 6,30ib
5-2
TABLE 5-2
TIME LV_T _/C _[ _M-Rc_ _,_-_C_ _m.
(Ld_} (LB_I LLFF
• U MI_$|OI_ _ 63_7, o_ 122Uou U_,
,O |N_T[A_I_ PROP _UAU|N_ 6_4_Io ,U IZZ_,u U_,
÷X U._ FP_
PITCH 1_0 _6 A[ 1,5 _E_/bLC
_,Z ROLL C_M 6_ DEG 2 DE6/$EC _Jg, 1,3 1202,_ 9_.
3.2 !NL_L R_LATIVL D_L V b_J_e _.U I l?_.I 9_.0,_ FP_
3._ IN_E_ A_ DOC_ _3_U9. _6,U I IZ2_l 96,
_,_ .M [JECTIUN _67|7, 1._ 1164.6 9_,-X 5 _LC _ JE|
_.5 _P_ _UKN IU LVAo_ 5IVfi 96Z_. _,_ I I60_& 9_.ORIENT AT 0.2 D_/_LC
_,_ AITIIUP_ _O_b 0.5 DEG DB P@NLS 9671Z, ,B 1159._ VS.
q*_ STAKT TRANSIE_T CONTRO_ 96710o 1,3 ||_.I 95,
_,_ _P_ _URN 96707_ .0 I I_B.I 95'BUILD uP
q._ STEADY _TATE BURN 965U_, ,J l[_l,_ 9B.
(a) Sgececraft _eights ere Bpp_oximBte Bnd are ±meluded for _eference omly.
(b) liote: These refe_ to _sable SM RCS propellsnt.
TABLE 5-2 (CONT'D)
SM-RC_ PRoPELlANT BUPGLT
lIME EVENT S/C _T SM-RcS SM-MC_ SM.
(HR| ILB_) V_LQ LEFT _Cb
(_S} (LBS} LEFT
_._ TAiLoF_ 96_67e ,l I|61t& 95,
_._ OAMP SHUTUO_N I_AN_|LNT 96N66, Iol _Ib6,A 9bo
O_I_NI AT D.2 OE_/sLC
6,1 NAV_AIION _I_HTIN_S 90_57, _,_ 11_7.) 9N,ORIENT AT O,Z DE_/SEC
1.U O_IENT FO_ PIC 96_53, _,I II_3,U 9_,3AXIS _,2 QEG/_C
7,0 AITITU_L HO_D U,5 D_G OB P_NC5 96N5_.! ,8 IIN_,_ 9N,
7,0 ROLL. 0,3 DE_/SEC 96N51, ,N I_I,Si 9q,
|O._ T_R_INAT_ PIC 96_7. _,_ I137,_ 93,DAMP _AT[S
ID,/ Pb_ IMU AL.IGN 96_7. ,2 1)37.1 9_,
ll,b MI_COURSE CO_R_CI ION NO I 96_, _,N 1132,] 93,3 AXIS ORIENT P_NCS
I 1.5 ATTITU_ HOLD U,5 DEG Dd P_NC_ 96_2, .6 I131.9 93,
tl,5 START T_ANS|ENT CONINO_ 96NNO,. _,3 ll30,b 93,
11.5 Sp5 8UHN 96_37. .0 1130,0 93,BUILD uP
ll.b SIEAD¥ STATE B_N 3 FPS P_NCS 96_0_. .I I130.5 93.
5-4
TABLE 5-2 (CONT'D)
5H-ME5 PMOPELLAI_T buDGET {
|IME EVEN| 5/C ,_[ 5M-_L_ 3M-_C_ 3M.
(HR I (LB_) U_E_ 6LFT _Lb(LdS) (L_S) LE_ T
li,b TA_LOFF 9636io ,_ 1129,1 93,
I 1,5 DAMP SHUf,_U_N T_AN_IENT 963S9. i,l I |2_,o 93o
12,d PSZ LMU A_|bN 963_Vo ,_ I12_,5 9Z,
1Z,5 O_|E_WI _O_ PTc 963=b, 4,1 llZS,_ _,3AXI$ U,_ OEb/SEC
|2._ AT_|IUJL H_LD _e5 OEb D_ P_NLb 9035_, ,_ I |_30= 9_,
I2,b ROLL U,3 DEb/3EC 96355, .5 t123,l 9Z,
2g,z TERM|NATE PTC Vb3_9, 9,5 li_'l 9Z'_AMP _ATE_
Z4,3 Pb_ IMU A_IbN 903_V_ ,_ I I _@,_ 9_.
2_,5 CIbLUNAR NAVIGATION 9639_= 5,5 I I l_,Z 91,STAR/_A_T_ HORIZON U_|EN[
Z5,7 _AVIGATIUN _I_HTI_G$ 96351, 5,5 I IUg,0 91,
ORIENT AT O,_ _EG/sLC
2b.b MIUCQ_RSE CORRECTION NO Z V6330, 5.5 I Ib=,_ 9i,MNv_ TO BuN_ aTT
26,b ATTIIUu_ HOLo U_b D_b D_ _NL3 V6_3}, ,B |lgq,l 91.
ZG. I DELTA _EL = NUMINAL_Y ZErO Yo33_, ,U I |bg. I 91 * •]
#27,U ORIENT FO_ PTC 9_331, 5.2 ll_.b 9d, 1
3A_15 U.Z _EG/_LE
Z7,U ATIIIU_E mO_D O,b _Lb _ PbN_ _bJJU, ,8 10_,/ 9b,
5-5
TABLE 5-2 (CONT'D)
_M-RCS PMUPLLLANI mUOGET
IIM: LV_NI S/C a[ _-RLS 5M-RC_ _M.
{MR) {L_I V$:U LEFI _L5
27,U ROLL 0,_ _b/bEL 9633_o *N L099,_ 9U,
SZ,_ T_RMINAT_ PI_ 963_bo _.5 |09N,9 Yu,DAmP _AIE_
b3,_ PS_ iMU ALibN 963_b, ,_ 109_,; 9U,
53.6 M|dCU_SE LO_R_Cr|_N NO 3 963ZI,! _,_ 1090,3 dg,MNvR IO 6_RN ATT
53.6 ATTITUde HOLD _,5 OEb O_ P_NL_ 9632U, ._ |Obg,_ Ug,
b3,O SIART T_ANSIENT CONTROL 9631_, 1,3 IOB_,Z _9,
53,b _P3 dUNN 96JlO, _U lOB6oZ o_e
53,b TA|LOFF 9bZ39, ,6 IDB/,3 _9"
53,b DAMP 5_UI.DU_N I_AN_IENT _6z3b. i.l IOBb,Z BV.
5_,b _Cb I_|M i FP_ 9oz_/, II,2 _O/b,U B_,
SN._ d_|ENT FUK PIC 96ZZ3, _.i I_/0,9 _,3AXIS _.2 D_b/SLC
_Se_ AI II /UOg _0_0 _.b DL_ D_ PbiWL_ 9622d, ._ _7_ei 00_
69,5 ILRMINAT_ PTC /bZll. _,N 1065,3 _},DAMP RA_E5
5-6
TABLE 5-2 (CONT'D)
_-RCS PRuPLLLANT _UObET
TIME EVENT 5/C _{ 5M-RLSI 5M-_C_ _m.
|MR| (Lb_} uSLu LEFT RC5(Lb_) (LB_) LEFT
/O,U PSZ _MU ALI@N 9621}, .2 1065,1 B_,
70,5 MI_CUU_SL COHRLcT|oN NO _ Vb£_3e _,_ iObU,l u/,MNV_ TO BURN ATT
7D,5 ATT|TU_ HU_D U,5 DEb Ub P_NCb 96212e e_ l_go_ _1,
70o5 DEE VEL • NOM ZERO 96212o ,U IO69,_ BT,
7Z,7 P$Z IMU AL|_N 9b_12o o2 _059_/ B]t
7qeO ORIENT ANU SXT STAR CHECK 9bZU/, _._ IOb_,Z _b,
7_,b O_IENT ANd OBSERVE LUNAR SURFACE 96203+ _.N IO50,_ B_.
75,5 LU{WA_ OR_i_ _NSEMTION BUrN I 9b19a, _._ lO_b,_ _b,3 AX|_ R ENT PbNC_
75,5 ATT|TU_i HOLD 0e6 DEG D_ PbNC_ 9bigB, ,B lO_5,t _b,
75,5 SIART TRANSIENT CONTROL 96196, 1o3 IOHH,_ @6,
75o9 LO| BO_N 9b193, 00 |_ Bb,BUILo uP
75,9 STEA_Y sTATE BURN 72357o ,S 10_3,9 _b,
75,9 TAILoFF 72316, ,O I0_3.9 B6,
F.......
75,9 IOAMP 5"uT Qo_N-TRAN_|_NT 723|_, |,| IO_Z,_ @b,
7602 REV l ATT|TUD_ NOLO _|D_ D_AD_A_w_ 7Z312e J,O 1039*_ _bo
5-7
TABLE 5-2 (CONT'D)
_M-RC$ PROP_LLANI _DGET
'rim L LVENT S/C _T SM-_C_ SM-RC_ _M.
(LBS) (LB$) LEFT
77,bI Pb& 1NU A_|_N l_3I_e ,| I039,_ _e
7B,Z. _V 2 ATTJTuOE _OLD 72_09e _,U 103beb mSe
79,Z Pb( I_U ALIGN /Z_09, el IO_b,} _Se
80,J LOi 2 _PO CIRC IZSOe, J,5 I033,U 8b,MNV_ TU B_RN All
BD,_ ATTIIUO£ NOLO U,5 DEe DB PeNC_ 72S05, ,8 I032,Z fib,
80,U 8"D U_LA_ 7zzg_, 15,1 IO17,A _S,
BO,I _Pb eu_N Z2261, ,U |Otl*I 83,BUILD UP
BO,_ 5TLA_Y 5TAIE 6gNi4 I|_Ib, ,2 I017,_ _,
BO,I TAILDFF 71Z76, ,_ iOl7,d 8_,
B[1,,l DAMP _t'_UTDO#N TNANS|LNI 71.21_, I,| 1015,,9 6._,
60,2 NEV } ATT|IubE HOLD 7127_ 3,0 ID12,9 _,
8O,H RLAC_IR_ msFN ZIZTZ, ,| _012.8 8_,
82,Z ME¥ _ ATTiTuDE MOLD - 71269, _,O 1009,_ 83,
...... i
_2e_ MNVR TO L_b 51T_ OBb ATT 712b_, _,5 IOO6o_ BZ_
g2,S LDb SIT6 OBb[RVAT|ON tlZ6b. ,q 1B05,8 _,
5-8
TABL_ 5-2 (CONT'D)
_M-_CS _U_LLLANT :UUGL T
fIML LVLNT S/C ,vl 5M-NC5 _M-_C_ _M.
_HR} IL_} US_U 6EFT _L_
(L_) {L_S) LLF T
8Z,J _LO_i_NI ll_lo _,5 lOUZ,J _Z,
82,_ NEACQuLRL m_FN /I_61, ,Z IDUZ,I _,
_40Z MANEUV_ [U _L_P ATI|TUuL ll_b_, 3,5 99B,_ _Z,3 AXI_ U,Z O_I_LC
9_04 bAMP _AI_ 71_b4* J,5 99b,U oZo
940_ HEAC_UIN_ M_FN 7[Z_o ,I 994,9 OZ,
960Z _V II AIIITU_ mUL_ ll_q/o JoO 9_b,_ _10
98,_ _EV I_ AT/ITuD_ mUL_ /1_44, J._ 9_04 _l,
98,B LU_ SITE UBSEKVA[IoN _IZ_U, ,4 9_I,H _U,
9B,9 N_CwuIRL I_FN 71_u0 ,L 9bl oJ bu,MULL 0,2 UEb/bEC
99,8 M_I_EUV_ TU AG_ CAL ATI|Iu_L 11_31, 3,5 9/]01 dd,
IO0,U PKE _NOOCKING AULOCATION Timid, _,0 9_3.1 ]_0
_O0oU ORIENT TO UNUUCKING ATTITuU_ 7IZIZ, ,& 953,u 7_,
IOOeZ L_i_ ACTIV_ UNQUC_ 37_93, 40_ 94900 7_0SEP ANp NULL VEL U,b FP_
5-9
TABLE 5-2 (CONT'D)
5M-RC5 HRoPELLANI =V_GLI
[|ME _VLNI 5/C aT 5M.RCS 5M-HC5 _M.
SHR[ ILB_I U_Q _LFI RCs(L6_) LB_) L_FI
$00,2 FoKMATIoN FLYING 37@B3, [U,_ 937,0 77,
IOO,_ REACWUIRL MSFN 3/BBJ, ,1 93_,9 77,
|OO,b ORIENT FU_ 5EP B_RN 3/8d_e _=| 935*= 17*
100,7 _L3 5EPARAI|UN BURN Z,b FP5 37860, [|,Z 9Z_,o /O*
$00,1 HEY [3 AI[LTUDL _OLu 316bb,! 3,0 9Z_,b 7b,
IUI ,5 MA_EUVEH [U 5XT [RALKIN_ 376bZo 3, [ 9[8,0 75*
lO2,O _tA_WEUVLR iU 5X1 [RACKING 37_59t 3.[ 915._ 7=,
[ON,q RLAC_U|_E M_FN 37Bb9 o ,3 9[5,3 iS,HULL U,_ UEb/_EC
iO_,_ _ANEUV_H Id _Xr [RaCK|Nb _7_5b_ 3,[ 91_,Z I_,
I0_,o R_V IN AT IITUDL _OLO _7663, 3,_ 9ug,z 75,
[ON,b MNVH [0 _Ub 51T_ UB5 AIT 3165U,_ _o| 906,1 7if,
10_,o L_ 5I T_ 065 _785_ ,4 9U5,7 7_,
&O_,/ THACK L_ J7_Nb_ 3el 9UZ*O 1_*
i0_=9 _LaC_UiRE MSFN 37_o_ *3 9UZ*3 7_,ROLL U,_ DEb/3EC
LOS,u, HEV i_ ATTITUDE _OLO 37B_3, 3,0 _99,J 7_,
5-I0
TABLE 5-2 (CONT'D)
5M-WC5 PRuPELLAN_ oOD_CT
IIH_ EVLN[ +SIc _l _M-_CS SM-MCa _M_._HR_ (_B_) USeD LLFT I H_
IO5.U RKACWOINE dSFN _76_3 .3 899. I l_._OLL B,S _EG/SLL
IU7.U PLANE CHAN_E 3/b_ _.| ugb._ 13.M+_VK TO _UM_ ATT
I07._ ATT|TUPE _OLO O+_ QE_ Ob P_NL_ 31839. ,8 895,_ 7j,
|DTeU ULLAbL _I_Z_ _*3 B_U,V lZ.
_07,_ 3P_ _O_ 37BZ2, .0 88U,9 1Z=+U|_O UP
|07.U _TEA_y blATE 3/Ibm, e_ 8_O,_ l_,
I07,U TAILoFF _71AJe L,U 879,_ IZ,
|Ol,_ QAMP Sm_TOO_N T_ANS|:NT _711_, _,i 678,1 /_*
_ol.2 PS_ IMU A_|GN 377_2, *_ BTB,b I_
SOl,_ _A_E,JVER lO SLEEP ATIITU_E S7/l_, i,l 878,9 7_
II|.S DAMP RATES 31101+ S,_ 873,9 1_
A12,Z REV L9 ATI£TUDE _OLO 317_, 3'0 870.9 /A
AAM.Z REV 20 ATIITUOE dOLD SllOi, S+U 867,9 I|
| |N,3 ORAENT FO_ SEXIANT TRACKING 37698, 3,_ 86q, l|
_15.0 NANEUVER TO SLEEP ATT 37697, ,7 86_, l_
5-11
TABLE 5-2 (CONT'D)
5H-RC$ PRuPEL_ANT oU_6_|
lIME EVENT 5/C _T 5M-Rc5 5M-Rc5 5M-
|MR) (LB_} Ub_D LEFT RC_
(_$J (LBS) uEfT
120,U _AFIP _AT_ 3/6971 tl Bb3*_ ]_,
I
IZO,U 5_AIA_| T_CKIN_ 31696, 1,3 86Z,¢ I 7i,
J_O,O R_ACWU|RE M$FN 3)69_e ,i 6b_,_ ;I,
12Q,g _LV g3 ATTITUDL HO_ 3769_, 3,0 859,1 ;O,
_22,Z] RE_ 2_ A[I|TUDE _OLb NA_O_ OEAO_ANo J76_7, _,_ 863.9 /U*
L2q,_ 5oPPORT _H LIFT OFF 3766Vs I_eO 835_9 o_s
12_,b MAnEOVL_ TO TRAC_ LM pO_T _|FI_FF 3/6_be 3,| B3_*d 6_,
_25,b MA_EOV_ TU SUPPORt LM C_L dURN 37663o 3, I 82V.7 b_,
i25,b MA_EUVE_ I0 TRACK LM P_T C5! 37660, 3,I 826,b bO,
125,6 REV 2b ATIITUDE _OLQ NARRU_ _EA_AN_ 31bbH, 5,2 82|,_ 67,
&26,_ MANEUVER |U _UPPDRT LM COM bURN 37b_ . 3,0 818,_ 67,
126,6 MANEUVER IO TRACK LM POST CDM 376N_, 3,1 815,3 07,
t26,b RNPZ HAw 37b_, 3,J 612,2 67,
II2beb RE,NIT]ATE _NDZ NAV 376_2, 3,11 8U9,1 bb,
t27,U MANEUVER gO SUPPONT _M TPL BURN 37639, 3.t B06*| bb*
5-12
TABLE 5-2 (CONT'D)
_M-RES PROPELLAN[ oUUGET
TIME EVENT _/C _T _M-RC_ _M-RC_ _M-
(_o5) iLdS) _FT
$27,I MANEUVER TO IRAC_ LM pO_T TPI 3163_, 3,1 8U3.U 66,
127,I MANEUVER lu COAs I_ACK 3]b33e 3.1 799,v 6b,
_27.1 MANEUVER IU Sxr IRACK|N_ 3763U. 3.1 796,V Oh.
|27,Z MA_EUVE_ TO _UPPORT LM MCLI BURN 37bZ/= 3.I 7_3,o bb,
|27,_ MANEUVER [O _r IRALKIN_ 37b_o J,[ l_O*_ bbo
127,_ MAI_EU_LR IU SUPPORT LM _CLZ BONN 37bZ| , 3._ 7o2,1 o_.
_ZT,b MANEUVER TU 5UPpUR| LM TPF BURN 31b[_, J,_ 1_4,1 b_.
127*_ MAI_LOVL_ TO 5XT TRACKINu _761b, _, | 1_1.o b_°
IZl._ ORIENT 10 QOCKIN_ ATTI TOPL _Ibl_, 3,1 17_._ b_,
_Z7,d ALLOCAIIOiw FUR TLR_INAL RDL U_AbE 3/511° Jb,U 7_3°_ bl,FROM PO_TFLI_H[
127°9 MAINTALN _UR_SI@_T 37b1_o 3,1 I_U,_ _I°
_Z@,U OOCKINb _32I_, ZO,U 71_,b by,
_31,5 MNVR TO JLITI$ON AIT H3ZI_, l.l lI3°_ be,
I32.U JETTISON UM [ FPS _Tb_Z, _*1 /Ue°O _*
[32,U ORIENT [O TRACKING ATT 375_U_ [*b /UT*O _=
5-13
TABLE 5-2 (CONT'D)
_M-RC_ _RuP_L_AIxl _UP_LT
TIML LVLNI $/C nT SM-_C$ $M-RC_ 5M-
{LBSI (LBS) LLFT
132,_ TRACK L_ 315_Q, ,i 7_6o_ 58+
L32,b HO_ I_RT|AI. ATT 37539, ,_ 108,I _8,
$_208 P_ |HU AL|_N _75J9. o7 70beb b@o
i3_,b bxT 5TAM CNLCK 3763/, ,_ lO_,_ 5_,
135,_ THAN_-EARTH INJECTION 31536, |,6 7_2,} 5boMNVK TU _UR_ ATT
135,u AIT|TUO_ HOLD U,5 DE_ DB PGNL_ _75_b_ ,_ 70Z,U b_,
|35,U UL_A_L 37bZi, I_,3 687,_ b_,
_35,b bP_ bURN 375_8, ,0 68_._ 56,BOILO u_
135,b TA|LOFP _7_J7, ,_ _BIo_ _b*
135,3 DAMP 5_OTPO.N T_ANS|_NI Zlff3b, 1.1 68_,J 5b,
136,0 Pb_ |M_ A_bN Z7_3_, _6 685,1 5_,
136,0 OR|SNT FOR PTC _7_3b, 1,I 6BN,b _6,
636,U ATTITU_L _OLO 0,5 pEb b_ P_N_ Zl_J_, ,8 6@3,_ _,
5-14
TABLE 5-2 (CONT'D)
5M-_CS P_OPELLAN[ buDGET
$IM_ J iVLNT 5/C .T 5M-_C5 5M-_C5 5M-
|HR) 1 IL_5) USLU LEFT _C5(L_I i lidS} LEFI
_360U M_LL O,_ uEb/$EC Z1_34, *l 683,7 _b,
j 147,b [:RHINATK PTC 2743Z= 1,3 682,3 58,DAMF _ATE5
147,b!Pb_ IMU ALIGN 2743_* *8 68| _ 56,
15O,U MIDCOURSE LORREC] |ON NO b 27Q3_, 1,3 880,6 5b,Mi_VR TO oURN ATT
IbO,U ATT|TUDL HOLo 0._ OEU OB PGNLb 27430, ,8 679,1 56,
|50,0 DEL VEL " NOM ZERO 2"/430, ,0 679,7 _6,
$50,5 ORIENT FO_ PTE 2742_, 1,1 678®_ 56,I
I I_50.5 ATTITU_L HOLo O,b O_G D_ PGNC_ _742_, ,8 677,_ _b,
|7|,O TERMINATE PTC 2742_, 1,3 676,3 55,
$72,0 PS_ IMU ALIGN 274_b, ,6 675,_ _b,
172,5 _I_CUu_SL LO_REc/IgN NO b 2]424, _,3 674*5 5b,MNVM [0 6URN ATT
17Z,5 ATTITUD_ HOLD 0.5 OEb 0_ P@NLb 274£4_ ,8 b73_1 55,
_72,b MC_ -X THAi_5 b Fp_ 27408, _5,9 657,8 54,
|73,D ORIENT FO_ PTC 27407, l,| 66b,b 54,
5-]5
TABLE 5-2 (CONT'D)
_M-MC5 PMQP_LLANT OUP_LT
I|ME I EVENT 5/_ ,T SM-MC_ 5M-RC_ _M-
|MR) (L_S_ U_D LEFT RE5(LS_) (LBS) L_FT
173,_ ATTITU_ hObO U._ DE_ Ob P_N_5 21QJ_ . .B bbS._ _.
173.J RULE U.3 OE_I_EC _7_. .I 65b.7 _.
i19_,_ TLR_I_ATL PTC ZIQO_. |03 b_._ _*
LgI.Z Pb4 |M_ ALI_N 27ffUQ. .b 653._ _.
192._ MIUCUU_SE CQRM_CT|ON NO 7 27_Z. 1.3 b6Z.5 _3.MNV_ TO _U_N ATT
_92.U ATT|TUUE HOLD 0.5 OE_ _B P_NL5 27QUa. .8 6b|.i 53.
_72.0 5TAR CHECR ZTQU_. ._ 65|._ _.
193,D MAtwEuV_ TO _E_T_Y ATT|TO_L _7_99, Z,b 6_8,7 b_,
|93,U ATTITUOE MO_D 0,5 DE_ DB PGNL_ Z7390, 8,6 6_U,L 5Z,
|9_,B MkNCUVER TO 5EP ATT|TUPE 273B7, _.6 6_7,Q 5Z"
_9_,_ CM/SM SLPAMAT|ON 1500L, /,9 629,b 52,DELTA V_L=3 FP5
5-16
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TABLE 5-3
CH RCS Propellap_t S_r_ar_,;
2rooellant Propellant
required: remaining_item lb. lb.
Loa_ed -- 245.0
l_'apped 36 4 _8.o
Availablefor -- 208.6mission planning
Nozcinalusage 39.3 !69.3
Nominal remaining -- 169.3
5-22
SERVICE PROPULSION SYSTE4
SERVICE PROPULSION SYST_{ (SPS). - The budget presented in table 5-4
is for a July !0 !auneh_ 72 degree launch azimuth_ first opportur_ity in-
jection, _.a = hour lunar parking orbit, and fast earth re_uz<,_. The assumn-
tions use(_ in >,_'-_=_,a_'ir=_--*o this budget are _oresented in table 5-5. AV recuirementswere coordinated with I2,1&Bin MPAD.
It should be noted that the mission flexibility allowance c!' _,CC fps n_s beeK
......... _,±ke_/used in _-'d:_it'_nto tPe fast return. _Tn real time however, it is higkly '"
that a slower earth return _ou:u be perfornted in the missicn flexibiliLy ,%;l r,,
had already been =sed ,,e,g., for _r,_rescu<). Table 5-h shows 3906 ibs of pro-
pellant re!,;¢i£in:_ ne.Ttlr_al!y and a total propellant t__ar_in (accounting _:<bk. for
t_'e _....___nl:,_,,=_, and the fast re%urn) cf _oKh_ lb.
TABLE 5-4 - APOLLO Ii SPS PROPELLM[T S_N_9,1S_Y
PRCPELLANC PRCRELL__T
I-m:=< n=qNIRKm _ T a nm.'ATNI: q LP
aLoaded " _'_'_
Trapped and unavailable L,#J.L 4C_61./
Outage 59.5 40]C2.!
Untalanccmeter !CO.C 402C2.1
Availab2e for A_V -- 4C202.!
Required for AV
T!_,.IC(120 fps)b 1166.4 _9'3_5.7
_o _ , o _._,_,7 k 1517_. 7LOI-I (_,__4 fps, 9 rain. 59 see. 'I =_<,,__.
L01-2 (i_7.4 fp% 16.4 sec.) 1115.4 148:$7.9
!.OPC (16.6 fps_ .9 sec.'] '-(_.8 Ij9_4.1
TEI (_'3292.7 fps, !L 9 sec.) 10077.8 3906._<
Nominalrer,_aining -- xcO6
Mission flexibility (900 fps) 2212.4 169_.9
Dispersiens (-_ _) 426.0 i_o_,.9
Prooel!antmargin _- -- i_o I•9
a 1971=.O_-_ ]b of fuel and 25091.0 ib of oxidizer; this is loaded on _'_'__-ib._7
b includes 19.7 fps for evasive maneuver
5-23
TABLE 5-5 - ASSUi'.'IPTIO['_S FOR THE _A°0LL0 I1 SPS PROPELLAI<T BUDCET
l. There is a non-propulsive propellant loss of IL.4 Ib for each engine
start. LM rescue assumed three engine starts.
2. A mission flexibility _V of 900 fps has been included in the SPSbudget to provide the capability to perform a worst case LM rescue,
or to handle several other contingencies (such as loss of PGNCS)_
or to perform a quicker earth return.
_. Spacecraft weight:
CM .............. 12 260.0 ib
S_,:.............. iC 551.3 !b
SLA Ring ........... 9_.0 ib
• ° • • ° ° . , . • f_TankedSPS 4C o_0.7!b
....( d) 2765_i,= unmanne x_ ib.... . . ° • j_ •
Total 96 nnn _ Ib
4. Lu_nar Orbit ActivityTotal weight transfer (C_7,ito If_) = 436. 7 ib
Total weight transfer (_._to C_!) = [email protected] ib
5. _,[ BCS, EPS, and ECS weight losses:
HissionPeriod .... + 7encre=en_a= Weight Lcss_ Ib
ELto_ _ 191._±_JiC . .... ° . • . o
TI2_Cto LOI-I ........ 327.!
LOI-I to LOI-2 ........ 92.0
LOI-2 to LOPC ........ 146.5
LOPC to TEI ........ 216.1
6. SM RCS usage (above nominal rendezvous requirement) for !3_ rescue was216 lb.
5-24
LH RCS BUDGET
Ground Rules and Assumptions
i. _ata for the _4 RCS engine performance and propellant requirements
were obtained from the Spacecraft Operational Data Book and postfli_ht
analysis from Apollo 9 and Apollo i0.
2. All orientation maneuvers were assumed to be made at 2.C °/sec.
>. All orientation maneuvers were assumed to be three-axis maneuvers.
5-25
TABLE 5-6
!/,4RCS Propellant Loading and Usage Stur=_mry
Loade_ 6_3.0
Trapped 40.6
!ominaldelivera%!e _92.4
Gaging Inaccuracy an_ loading tolerance 39.5
_Ciztureratio uncertainty 17.0
Usable _35.9
Uominal mission requiremen_ 252.7
i_ominalremaining 25_.2
5-26
TABLE 5-7
I _ - RCS PRhPFI [ ANT _HI}GPT PA_F IJ
a q/C WT I M b I M bTIfF FV;I_I TTTI F ! M
HKS _ (LBS) RCS RCS RCS
(L3S) (LBS) (%)
O u OGTPUI PROPELLANT LOADINGS 33714. .0 633,0 i00-0
99 _5 RCS hOT FIRE 53709, 5,0 628.0 99.2
I00 _Iv Ui_DOCKiN_ 53709, ,0 628,0 99.2
i00 ISINuLL uNCOCKI_G VELOCITY 35707. 1.9 626.1 98.9
i00 _0 LNi N_h_h FOR I_SPECTION YA_ 53705. 1.7!624.@ 98.6
I00 20 LN MhV;i FOR INSPECTIOI_ PITCH 33703. 2,0 622,@ 98.3
• 00 25 LM MNV_ FOR INSPECTION YAW 53702. ,8 621,6 98,2
I00 _ FOEMAIION FLYING 35690. 2.0 619.6 97.9
I00 bO Rk LOCK Oh _N_R 33687. 5.6 616.0 97.3i
101 O [MU REALIGN STAR I 33683. 3.6 612,q 96,7
I01 C IMb RLALIGN STAR 2 _680. _.6i608.8 96,2
xO1 u I_!u REALIGN SIAR 3 33676, 5,6 605,2 95,6
lO1 52 _NVR TO DOI BURN AITIIUOE 33672. 5.6 601.6 95,0
ZOl 02 ATTITb_E NOLD 53672. .1 601.5 95.0
i01 _b 2 _ET ULLAGE 35667, 5.9 595.6 9W,I
I01 _ _GI BUrN 3_W19, ,0 595.8 9W,I
101 o_ _OI, EI_T CONTROL DCI BURN 33W14. 5,0 590,6 93,3
101 a6 TEI_ hGRIZONTAL RESIDUAL 55W07. 7.6 583,0 92,1
i01 _b ATTIToOE hOLD 33W07. .3 582,8 92,1
lOl _o PITCH L:OWN 33W06. 1.0 581,8 91.9
101 W2 RR LOCK ON NNVR _3602, 3.6 578.2 91,3
i01 =51PITCH DOWN 33W01. ,6 577,6 91.3
lOl 55 YA_ LEFT 33W01, ,6 577,0 91,2
102 0 ALIGNNENT CHECK 33400. 1.2 575,8 91.0
102 IU Rlt LOCK 01_ MNVR 33396. 3.6 572.2 90.4
a
These wezghts were used for analysis only and do not reflect the actual weight_fter consumables loadin_.
bRCS propellant remaining of total loaded 5-27
TABLE 5-7 (CONT'D)
LIe " #tCS PKqPELLAh.T _%UIC-F'[ P_(_F. 2
•,. _1 D iOI:_L EVEN! ]Jli_E [q/C ,_]_ I N LM LNili<S t (LBS) RCS RCS RCS
_ _LEFJL_ILLS) (LBS) (%)
,L(,.J_.14 _, 4_R lO PUI AIlI[UbE 55392. 3.6 568.6 89.8
iO& 1_, i._iN,AIN LOS 33591 i.O 567.6 89.7
lu2: 2_IATTITLIE hOLD 53391. .1 567.5 _9.7I
/02 _ 2 ,:ET bLLAGE 33385. 5,9 !561,7 8_.7
102 05 POI 5bAN 16753, .O 561,7 88.7
102 ,35 Pb_,Ei<EC i::ESCEI;'i 16710. 54.1 52.7.5 83.3
102 47 IObgHbtwl, 16710. .0 527.5 83.5
ll2 q O AD[; LGi,AR S,_%PLES i16580. .0 527.5 83.5
/.24 ,3 L.UI';AF, LIFI OFF L0840. .0 527.5 85.3
lZq Z5 P_EREC ASCEI,;I PHASE wIfH RCS/ 6087. ,0 527,5 85.5APS j_N.,_C_Oj!4 i_E C_
12q _ P___ ,_ _0 _ ' 5969, ,9 526.7 8;5.2CS/APS Ii4TERCOi_F:ECT
12W -'5 R_< LCCK ON MNVR 5969. .q 526.2 83.1
124 .50 I,,;SERTiGI_, BURN CONTROL 5967. 1.8 524.4 82.8
12q aO TRIM OUT OF PLANE ERROR 59614. 3.3 521.2 £2.5
12,4 _6 AlllfUCE HOLD 5962. 1.3 519.9 82.1
J,2q -_7 :IP,U REAL16N STAR 1 5962. .4 519.5 82.1
IZq a? li4b RLALIGN _IAR2 5961. .4 519.0 82.0
124 _7 IMU REALIGN STAR5 5961. .4 518.6 81.9
i2q 55 R_<LOCK 01_MNVR 5961. .4 518.1 81,9
12W 55 iv,AINT,_IN LOS 5958. 2.7 515,5 81.4
125 15 ATTITLCE HOLu 5957, 1.3 514.2 81.2
125 21 CSI BbRN [<C5 +Z 5923. 33.6 q.80.6 75.9
125 Z6 IvAII_TAIN LOS 5920. 3.3 477.2 75.q
125 '4-4 i,NVR lo PLAi'iE CI-iANGE ATTITUDh 5919. .4 476.8 75.3|
These weights were used for analysis only and do not reflect the actual weightafter consumables loadin_.
bRCS propellant remaining of total loaded 5-28
TABLE 5-7 (CONT'D)
IP - i_C._ P_:_;hPFI LAI,,T i_iilLl:rT PaGF .l
TI_.'.- EVt:TI4I__ I*!TI_F c:/C WP I_:',' LF b LM bHRS r (L_S) RCS RCS RCS
i iqFFI I _-lrT I FF T
(L]S) ( L::_S) (_)
_.25 _:, ,_llllbbE r, OLU 5918. 1.3 475,5 75.1
125 bL. I_CS PL.':i'.E C_Ai",GE buRN 5914, q,l 471,4 74,5
120 _ FK LCCF. _GF. kNvF 5913, .4 !471,0 74,4
z_[. O 4Alhlt\IN LOS 5911. 2,0 469,0 7_,I
I_[ J._ AflI[b. E _OuO 5910, i,_ 467,7 73,9
126 l; _.UI'__{_-5 __.UHI!, 5906, 4.0 465.7 7D.3
1£_ J,:, _ A1 TAIN LuS 5902. _.0 459.7 72.6
126 a3 AITIIL_,E #OLO 5901, 1,5 458.q 72.4
12_ 3c I_CS TP% UCFLi., 5884. 17.0 441.q 69.7
12b bO ;,I, INTAIf, l-OS 5883, 1.3 440,1 69.5
i27 36 ;-CC l',i,L_ U_AFI,_,., 5849. ,_4,.5.9 #06.3 6_.2
127 36 AI"[ITLCE _I_ LOS CONTECL 5833. 16.0 390,5 61,7
±28 O0 "U-t CCI_TRGL CS_', ACTZVE OOCKi_,6 " 5823. 10.0 _580._5 60.1
a
These weights were used £oz ama]v_iq only s_a _n _n% _p?l_e+ &he 9ct_3_! _[e_zh +after consumables loading.
nu_ propellant remaining of _otal loaaea
5-29
L_+
_..L•
l.....
[_---
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I:_++
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++
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++
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DESCENT PROPULSION SYSTEM PROPELL_NT BUDGET
Descent Pronu!sion Subsystem (DPS) - The DPS budget is shown in table 5-8and the gro_u_ rules and assumptions in table 5-9.
Previously, the _ncertainty in the low-level sensor (65.7 !b) has been sho_nas a contingency allowance. Tnis is now included as part of the unusah!es.Also, there has previously been a contingency allowance for manual hover to
allow for 2 minutes of burn time from 500 feet to touchdown, uT__epresent
budget shews a nominal AV which includes a manual allowance of 47 _ fps (90sec) from 500 feet to touchdown. Any additional hover time will be used
from the propellant margin (unassigned capability). The rate of use for
hover is approximately 9.1 !b/see.
Propellant loads are those actually loaded on _'_-5, and trapped and residualpropellants are from Volume III_ SODB. Engine performance da_a and AV re-quirements !ave been coordinated with LAB in P_AD.
_<ree sigma dispersions represent _otal Fropellant cost due to ) _ uncertaintiesin proDe!lant Icading_ trapped_ Isp _ AV_ separation weight_ non-AV consumables
weight, and mixLure ratio. TT_ere is a total propellant margin of 669 ib orapproximately 7) seconds of hover time.
TABLE _-8 - APOLLO Ii DPS PROPELLANT SU_IARY
PROPELL#j[T PROPEEE_JT
ITE'4 REQUIRED_LB PE_Z,!!NC,LI:a
Loaded -- 18184.2
Trappedand unavailable 223.5 17960.7
Outage 14.0 17946.7
Low-Level Sensor Uncertainty 68.7 1767_.0
Available for AV -- 17_78.0
Nominal Required for AV of 6725.6 fps 16799.7 1078._
Dispersions(-_7) 224.7 853.6
Contingencies
Engine Valve-Pair Malfunction (Z_R=J.CI6) 81.i 772.5
Redesignation(60fps) 104.0 66_.5
Margin (73 sec. hover) -- 665.5
a 6974.8 Ib fuel and 11209.4 ib oxidizer; this is loaded on the _4-5 spacecraft.
5-31
TABLE 5-9 - ASSUMPTIONS FOR THE APOLLO ii DES PROPELLANT BUDGET
I. Integrated average Isp = 901.9 _ 9.54 seconds
2, LM separation weight _ 33746. Ib
9. Mixture ratio = 1.596 _ 0.0108
4. Nominal _V = 6728.6 + 96 fps
_. _n-_V consumables of 47.4 ib from separation to DOI and 106.1 ibfrom DOI to touchdown
ASCENT PROPULSION SYSTEM PROPELL&NT BUDGET
Ascent Propulsion Subsystem (APS) - Tables 5-10 and 5-11 present the ascentpropellant budget for the current mission. Propellant loads are those actually
on LH-5. Mission _V was coordinated with LAB in HPAD. The budget shown in
table 5-10 accounts for an engine valve-pair malfunction, a PGNCS to AGS switch-over_ and a touchdown abort. 'ITlereis a total propellant margin of 68 ib orabout 6 seconds of bu_-. time.
TABLE 5-10 - APOLLO ii APS PROPELL_'_T SU_J_,_RY
PROPELL_T PROPELL_,IT
IT_ REQUIRED_LB P_INING_ LB
Loadeda -_ 5238.4
Trappedand Unavailable 48.9 5189.5
Outage 17.5 5172.0
_sailableforhV -- _172.0
NolainalRequired for AV of 6072._ fps L96_.8 206.2
Dispersions (-9 c) 57.8 148.4
Contingencies
_no_._e_i_Valve-oair_ Halfunction (_,R_.OI6 19.6 125._
PSNCStc A6S _;itchover(40 flss) 2).$ lOp.C
Touchdown Abort (S¢=+99.9 !b, _a3/=-lSfps _6.8 68.2
74argin(6seconds) -- 68.2
a Includes 2019.9 1% _'ue! and 52!_.p !b oxidizer; this is loaded on the LM-_
spacecraft.
5-32
TAHLE 5-11 - ASSUMPTIONS FOR THE APOLLO ii APS PROPELh&NT BUDGET
I, Isp --508.97+ 5.555 seconds
2. Mixture ratio = 1.602 + 0.0225
5- Wominal Z_V = 6072.5 + 35-5 fps
4. Ascent stage lift-off weight i087_.o ib
5-33
CSM-IO7/LM5 CRYOGENIC/EPS AND ECS BUDGET
The results of the Cryogenic, EPS, and ECS analysis are summarized in thefollowing tables and figures:
TABLE 5-11 CSM Cryogenic Loading And Usage Summary
TABLE 5-13 LM EPS Summary
TABLE 5-14 LM ECS Summary
FIGURE 5-7 CSM 02 PROFILE
FIGURE 5-8 CSM H2 PROFILE
FIGURE 5-9 CSM POWERPROFILE
FIGURE 5-10 CSM BUS VOLTAGE VS TIME
FIGURE 5-11 LM DESCENT POWERPROFILE
FIGURE 5-12 LM ASCENT POWERPROFILE
FIGURE 5-13 LM TOTAL CURRENTPROFILE
FIGURE 5-14 LM DESCENT 02 PROFILE
FIGURE 5-15 LM ASCENT 02 PROFILE
FIGURE 5-16 LM DESCENT H20 PROFILE
FIGURE 5-17 LM ASCENT H20 PROFILE
5-34
CSM EPS BUDGET
ASSUMPTIONS AND GROUND RULES
i. The system was assumed to operate v_ith three fuel cells and twoinverters.
2o Fuel cell purging is included in the EPS requirements.
3. 100_p fill for both H2 and 02 .
4. _nmee entry and postlanding batteries were considered available
to supply the total spacecraft power required for entry, parachutedescent_ and postlanding time. Each battery was assumed to have
40 A-h capacity until splashdo-_m, at which time the capacity wasuprated to 45 A-h.
5. Two batteries were considered to be in parallel _dth the fuel
cells during ascent and for each SPS maneuver.
6. No cryogenic venting was assumed in flight.
7. The EPS hydrogen consumption rate (ib/hr) = 0.00257 x Ifc
8. The EPS oxygen consumption rate (lb/bre) = 7.936 x "L
9. Six battery charges were ass_ed: three on battery A and threeon battery B.
5-35
TABLE 5-12
APOLLO ii CRYOGENIC SD%9,_RY
I. PlanningAllowance K2_ ib 027ib
A. TotalLoaded 58.60 660.20
B. LessResidual 2.32 13.00
C. Less InstrumentationError 1.50 17.50
Available for Hission Plarming 54.75 629.70
Ii. Predicted Usages
iA. Prelauneh
i. in!ine KTR + Pressure Relief 1.61 18.60
(T-2 to T-3 (Incl 12.5 hol ))
2. Power Production (plus ECS 0o) .57 6.96
(T-3 to liftoff)
Total Prelaunch requirements 2.18 25.50
B. Flight
i. EPS Requirements (Incl FC Purge) 36.60 288.33
12. CN ECS (InclCabinPurge) - 72.40
3. _ Pressurizations - 10.35
Total Flight Requirements 36.60 371.08
!If. Nominal Reserves (RSS)
EPS Uncertainty(5 percent) 1.83 14.42
ECS Uncertainty (.08 ib/hr) - 15.60
TankUnbalance(AOH) .80 12.90
LaunchWindow .86 10.20
RSSSubtotal 2.17 26.87
IV. 0_erational Reserves
A. Available for Hission Planting 54.78 629.70
B. Less Nominal Predicted Usage 38.78 396.58
C. Less NominalReserves 2.17 26.87
OperationalReserve 13.83 206.25
iKSC SuppliedData 5-36
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i. The descent stage batteries go on the line ]< minutes pricrto earth liftoff.
2. A 9.8 hour checkout was assumed for llomar orbit.
7. Ascent and descent batteries were paralleled for the powereddescent burn and prior to liftoff from the lunar surface.
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5-41
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LM ECS BUDGET
GROU_D RULES AND ASSUMPTIONS
i. Cabin 02 leakage rate was 0.2 ib/hr v_ile pressurized
2. Metabolic rates were varied according to Volume 2 of the
Spacecraft Operational Data Book
3. _letabolic 02 consumed was (1.643 x 10-4 ) x (metabolic rate)
4. _ pressurization requires 6.62 ib of 02
5. Cabin pressure regulator check requires 2.65 Ib of 02f
o. _L_0 consumed because of sublimator cooling was total heat
removed divided by 1040 (btu per ib) of H20
7. HI 0 lost due to urination was 0.ii Ib/hr per man2
8. Cabin temperature control was set to 72° F
9- Average glycol flow rate was 250 ib/hr
i0. Pudget was performed on the operational trajectory and maychange when the revision i is analyzed.
TABLE 5-13
LM ECS Su_ary
(a) Descent Sta6e
Description O2_ib H20_ ib
Loaded ................. L$.OO 210.6
Unusable................ 3.40 16.4
Available for mission.......... 44.60 194.2
Required for mission .......... 26.17 142.4
Usable remaining in tanks ......... 18.43 51.8
(b) Ascent Sta_e
Loaded ................. 4.86 85.00
Unusable................. 74 4.20
Available for mission ......... 4.12 80.80
Required for mission ......... 1o95 45.48
Usable remaining in tanks ........ 2.17 35.32
5-45
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THE RESULTS OF THE PLSS BATTERY, OXYGEN, WATER AND LiOH CONSUMABLEANALYSIS ARE SUMMARIZED IN THE FOLLOWING FIGURES:
FIGURE5-18 LMPANDCDRPLSSBATTERY PROFILE
FIGURE5-19 CDROXYGENPROFILE
FIGURE5-20 LMPOXYGENPROFILE
FIGURE5-21 CDRH20 PROFILE
FIGURE5-22 LMPH20 PROFILE
FIGURE5-23 LMPANDCDRLiOH CO2PROFILE
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