Apollo 11 Flight Plan July 1 1969

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MANNED SPACECRAFT CENTER HOUSTON,TEXAS

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.-t:.:.-.-.l.:.'.:.'.-. APOLLO II

APOLLO AS-506/CSM-IO7/LM-5

FINAL FLIGHT PLAN

JULY l, 1969

Flight Planning Branch

G. M. Col ton Flight Planning Branch

?. A. Guil!ory Flight Planning Branch

Aoproved by: /- y ,'--/ / <_:.-_-- W. J. A#rth Chief, Flight Crew Support Division

Donald_K. Slayton Director of Flight Crev_lOperations

Concurrence: __'_Low _ _-'0_IJ'---@_-7"7 Manager, 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 be forwarded to T. A. Guillory, Flight Planning Branch, mail code CF34, extensio_q 427l. ACKNOWLEDGMENTS

Acknowledgment is made to Messrs. Richard Rogers, William Killian and Spencer Gardner for their technical support in the preparation of the Apollo II Flight Plan.

Views of the earth and the P52 stars shown in the Flight Plan were taken from the document, Views from the CM and LM During the Flight of 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 Accelerometer ACN Ascension ACT Activation ACQ Acquisition AEA Abort Electronics Assembly AGS Abort Guidance Subsystem AH AmpereHours ALSCC Apollo Lunar Surface Close-up Camera ALT Altitude AMPor amp Ampere ANG Antigua ANT Antenna AOH Apollo Operations Handbook AOS Acquisition of Signal or Acquisition of Site AOT Alignment Optical Telescope APS Ascent Propulsion Subsystem ARS Atmosphere Revitalization System ATT Attitude AUX Auxiliary AZ Azimuth

BAT Battery BDA Bermuda Bio Bio-Medical Data on Voice Downlink BP Barber Pole BT Burn Time BU Backup BW Black & White BRKT Bracket

CAP COM Capsule Communicator CAL _ Calibration Angle CAM Camera CB Circuit Breaker CDH Constant Delta Altitude CDR Commander CDU Coupling Data Unit CEX Color External CIN Color Internal CIRC Circularization CK Check CM CommandModule CMC CommandModule Computer CMD Command CMP CommandModule Pilot CNTL Control C/O Check out COAS Crew Optical Alignment Sight COMM Communications CONFIG Configuration

iii CONT Continue CP Control Point CRO Carnarvon, Australia CRYO Cryogenic CSC Contingency Sample Collection CSI Coelliptic Sequence Initiation CSM Command Service Module C&WS Caution and Warning System CYI Grand Canary Island

DAP Digital Auto Pilot DB Deadband DCA Digital CommandAssembly DEDA Data Entry and Display Assembly DEGS Degrees DEPL Depletion DET Digital Event Timer DIFF Difference DOI Descent Orbit Insertion DPS Descent Propulsion System DS Documented Sample DSE Data Storage Equipment DSKY Display and Keyboard DTO Detailed Test Objective DUA Digital Uplink Assembly DWN Down

E Erasable or Enter EASEP Early Apollo Scientific Experiment Package ECS Environmental Control System ED Explosive Device EDT Eastern Daylight Time EFH Earth Far Horizon El Earth (atmosphere) Interface EL Elevation or Electric EMS Entry Monitor System EMU Extravehicular Mobility Unit ENH Earth Near Horizon EPO Earth Parking Orbit EPS Electrical Power Subsystem EQUIP Equipment EST Eastern Standard Time EVA Extravehicular Activity EVAP Evaporator EVT Extravehicular Transfer E×T External

f F Stop FC Fuel Cell FDAI Flight Director Attitude Indicator

iv FLT Flight _I Frequency Modulated FOV Field of View fps or FPS Feet per second FT or ft Feet FTO Flight Test Objective FTP Full Throttle Position

GBI Grand Bahama Islands GBM Grand Bahama (MSFN) GDC Gyro Display Coupler GDS Goldstone, California GET Ground Elapsed Time GETI Ground Elapsed Time of Ignition GLY Glycol GMT Greenwich Mean Time G&N Guidance and Navigation GNCS Guidance Navigation Control System GNM Guam GYM Guaymas, Mexico

H2 Hydrogen HA Apogee Altitude HAW Hawaii HBR High Bit Rate (TLM) HD Highly Desirable HGA High Gain Antenna HI High Hp Perigee Altitude HSK Honeysuckle (Canberra, Australia) HTR Heater HTV USNSHuntsville

ICDU Inertial Coupling Data Unit ID Identification IGA Inner Gimbal Angle IGN Ignition IMU Inertial Measurement Unit INIT Initialization INT Intervalometer IP Initial Point ISA Interim Storage Assembly IU Instrumentation Unit IVC Intervehicular Communications IVT Intravehicular Transfer

JETT Jettison

KM Kilometer kwh Kilowatt Hour LA Launch Azimuth LAT Latitude LBR Low Bit Rate (TLM) LBS or Ibs Pounds LCG Liquid Cooled Garment LDG Landing LDMK Landmark LEB Lower Equipment Bay LEC Lunar Equipment Conveyor LFH Lunar Far Horizon LGC LM Guidance Computer LH Left-hand L/H Local Horizontal LHEB Left-hand Equipment Bay LHFEB Left-hand Forward Equipment Bay LHSSC Left Hand Side Storage Container LiOH Lithium Hydroxide LLM Lunar Landing Mission LLOS Landmark Line of Sight LM Lunar. Module LMP Lunar Module Pilot LNH Lunar Near Horizon LOI Lunar Orbit Insertion LONG Longitude LOS Loss of Signal or Loss of Site LPO Lunar Parking Orbit LR Landing Radar LRRR or LR3 Laser Ranging Retro-Reflector LS Landing Site LT Light LTG Lighting LV Launch Vehicle L/V Local Vertical LVPD Launch Vehicle Pressure Display

M Mandatory MAD Madrid, Spain MAN Manual MAX Maximum MAXQ MaximumDynamic Pressure MCC Midcourse Correction MCC-H Mission Control Center - Houston or MCC MDC Main Display Console MEAS Measurement MER USNSMercury MESA Modularized Equipment Stowage Assembly MET Mission Event Timer

vi MGA Middle Gimbal Angle M/I Minimum Impulse MIN Minimum MLA Merrit Island, Florida MNVR Maneuver MPS Main Propulsion System MSFN Manned Space Flight Network MTVC Manual Thrust Vector Control

N2 Nitrogen NAV Navigation NM Nautical Miles NOM Nominal NXX NounXX

02 Oxygen OBS Observation O/F Oxidizer to Fuel Ratio OGA Outer Gimbal Angle OMNI Omnidirectional Antenna OPS Oxygen Purge System ORB Orbital ORDEAL Orbit Rate Display Earth and Lunar ORIENT Orientation OVHD Overhead

P Pitch or Program PAD Voice Update PCM Pulse Code Modulation PC Plane Change PDI Powered Descent Initiation PGA Pressure Garment Assembly PGNCS Primary Guidance Navigation Control Section PIPA Pulse Integrating Pendulous Accelerometer PLSS Personal Life Support Systems PM Phase Modulated POL Polarity or Polarizing PRE Pretoria, South Africa PREF Preferred PREP Preparation PRESS Pressure PRIM Primary PROP Proportional PSE Passive Seismic Experiment PT Point PU Propellant Utilization PUGS Propellant Utilization and Gaging System

vii PTC Passive Thermal Control PWR Power PX× Program XX

Qty Quantity

R Roll or Range R&B Red & Blue RAD Radiator RCDR Recorder RCS Reaction Control System RCU Remote Control Unit RCV Receiver RED USNSRedstone REFSMMAT Reference Stable Member Matrix REG Regulator REQD Required RH Right-hand RING Ringsite RLS Radius of Landing Site RNDZ Rendezvous RR Rendezvous Radar RSI Roll Stability Indicator RT Real Time RTC Real Time Command RXX Routine XX

SA Shaft Angle S/C Spacecraft SCE Signal Conditioning Equipment SCS Stabilization Control System SCT Scanning Telescope SEC Secondary SECO S-IVB Engine Cut-off SECS Sequential Events Control System SEP Separate SEQ Sequence S-IVB Saturn IV B(Third Stage) SLA Service Module LM Adapter SLOS Star Line-of-Sight SM Service Module SPOT Spot Meter SPS Service Propulsion System SR Sunrise SRC Sample Return Container SRX S-Band Receiver Mode No. X SS Sunset STX S-Band Transmit Mode No. X

viii S.V. State Vector SWC Solar Wind Composition Sw Switch SXT Sextant

T EPHEM Time of Ephemeris Update TA Trunnion Angle TAN Tananarive, Madagascar TB Time Base TCA Time of Closest Approach TD&E Transposition Docking & LM Ejection TEC Trans Earth Coast TEl Transearth Insertion TEMP Temperature TERM Terminate TEX Corpus Christi, Texas TGT Target TIG Time of Ignition TLC Trans Lunar Coast TLI Translunar Insertion TLM or TM Telemetry TPF Terminal Phase Final TPI Terminal Phase Initiation TPM Terminal Phase Midcourse T/R Transmitter/Receiver TRANS Translation TV Television TVC Thrust Vector Control TWR Tower

US United States

V Velocity VAN USNS Vanguard VHF Very High Frequency VLV Valve VI Inertial Velocity VOX Voice Keying VXX Verb XX

W/O Without WRT With Respect to WTN USNSWatertown

XFER Transfer XMIT Transmit or Transmitter XPONDER 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 Film MIR (fS,250,INF) 6fps External-Camera Bracket Mirror (f-stop 8, shutterspeed 1 = _-5_O-sec, Infinity) 6 frames per sec SYMBOL NOMENCLATURE

LUNAR PENUMBRA(OCCURSPRE LOll)

-HONEYSUCKLESPACECRAFT SUNSET85FT D_SH COVERAGE -DARKNESS (UMBRA)

-MSFN LOS

-SPACECRAFT SUNRISE

.LUNAR P,ENUMBRA(OCCURS PRE LOll)

J- LUNARSURFACE / WINDOW

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

_ DOWN \(5-_ S-BANDHGA X

, --S-BANDOPTICSSTEERABLE SUBSOLAR POINT

I MSFNAOS 'MADRID 85FT DISH COVERAGE

I .GOLDSTONE85FTD!S_ COVERAGE

I I LUNAR TERMINATOR SPACECRAFT SUNSET

DARKNESS

MSFN LOS

SPACECRAFT SUNRISE

LUNAR TERMINATOR

xi INTRODUCTION

This Flight Plan has been prepared by the Flight Planning Branch, Flight Crew Support Division, with technical support by TRW Systems.

This document schedules the AS-506/CSM-IO7/LM-5 operations and crew activities to 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, 1969 launch, with a 72° launch azimuth and were supplied by Mission Planning and Analysis Division as defined by the Apollo Mission G Spacecraft Operational Trajectory.

The Apollo II Flight Plan is under the configuration control of the Crew Procedures Control Board (CPCB). All proposed changes to this document that fall in the following categories should be submitted to the CPCB via a 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 activity day 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 changes fall in the above categories.

Mr. T. A. Guillory will act as co-ordinator for all proposed changes to the Apollo II Flight Plan.

Any requests for additional copies or changes to the distribution lists of this document must be made in writing to Mr. W. J. North, Chief, Flight Crew Support 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

(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

(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

(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)

(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

CDH

TPI

Braking

(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.

about 172.4 ° West at 195:17 GET. This will occur approximately

25 minutes prior to sunrise local time.

I-4 _' l

1-5 1-6 / .

i /

I _

/ ° I! 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 T im!o Lo Includes 2nd Opportunity TLI 3 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 DELTA DESIG. 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 000.00 l .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 -001.71 LDG SITE 2) 00.50527778°N 24.88888889°E

129 (Alternate Ol °17'06"N 23°44' 37"E -OOl .76 LDG SITE 2) 01.28500000°N 23.74361111°E

133 (Alternate D0°,17' 14"N 23°30' 55"E -OOl .68 LDG 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 DELTA DESIG. LATITUDE LONGITUDE ALTITUDESUNEL (nm)

IP(GI) O°I6'N 32°19'E 0.267°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'E O0.300°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 DELTA DESIG. LATITUDE LONGITUDE ALTITUDESUNEL (nm)

IP(GI) O°30'S 26°33'W O.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 -001.29 LDG 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 -001.23 LDG SITE 5) 02.05277778°N 42.22805556°W

1-12 FLIGHT PLAN NOTES

A. Crew I. Crew designations are as follows: Designation Prime Backup Co_nander (CDR) Armstrong Lovell Command Module Pilot (CMP) Collins Anders Lunar 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 CMP T&D thru Entry CMP CDR LMP MannedLM CMP CDR LMP

3. The crew will eat and sleep simultaneously throughout the mission. Eat periods will be normally l-hour duration, with additional activities held to a minimum during this time frame. Sleep periods will normally be 8 to lO hour duration with two 4 to 5 hour sleep periods while 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&G TLI to evasive mnvr PGA's with H&G TLC & LOI l&2 Constant wear garments LM activation & checkout PGAwithout H&G (CMP H&G donned for latch cocking & CDR/LMP H&G donned for pressure integrity check and cabin reg check) Undocking through touchdown PGA's with H&G except CMP without H&G after DOI Touchdown through pre lift-off PGA's without H&G except for CDR/LMP simulated count- down & EVA Liftoff through LM jettison PGA's with H&G (except H&G off after docking) LM jettison through splashdown Constant wear garmets

1-13 5. Two crew status reports via air-to-ground commmunications will be made by the flight crew during each activity day. The first report will be given after the first meal of the day and will concern the sleep obtained during the previous sleep period. The second report will be given following the final meal of the day and will concern the radiation dose received during the previous 24 hours and medication taken if any. The following information should be logged: a. Food Consumption b. Exercise c. Used fecal bags marked as to crewman and GET

6. Negative reporting will be used in reporting completion of each checklist.

7. Continuous CSM biomedical data are automatically transmitted to the ground.

8. LM biomedical switching is performed manually by the LMP from undocking 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 i Photographic requirements were derived from the following: a. Lunar Surface Operations Plan b. Photographic Operations Plan

Co Procedures I. CSM Crew procedures called out in the flight plan may be found in the following documents: ,{_ 1 a. Apollo Operations Handbook - CSM-I07 (AOH), Volume 2 b. Crew Checklist c. CSM Rendezvous Procedure d. Abort Summary Document e. Apollo Entry Summary Document f. Photographic Operations Plan g. Descent Procedures Document h. Ascent Procedures Document i. Lunar Landmark Tracking Attitude Studies j. Lunar Orbit Attitude Sequence for Mission G k. Data Priority Documents

l -14 2. LM Crew procedures called out in the flight plan may be found in the following documents: VC_,_ L a. Apollo Operations Handbook LM-5 Volume 2 b. Crew Checklist c. LM Rendezvous Procedures d. LM Descent/Ascent Summary Document e. Lunar Landing Phase Photographic Operations Plan f. Data Priority Documents g. EVA Procedures h. Apollo Lunar Surface Operations Plan

D. Communications I. General a. CSM and LM HBR data transmissions in lunar orbit will normally require the use of the high gain or steerable antennas b. 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) CSM TaT Uplink Mode 6 (Voice, PRN, and Updata) (b) Downlink Mode 2 (Voice, PRN, TLM-HBR) (2) LM Ta) Uplink Mode 7 (Voice, Updata) (b) Downlink Mode l (Voice, TLM-HBR) d. LM voice recorder has a maximum utilization of lO hours. This recorder will be used during LM operations to record all LM voice 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 to be used at the discretion of the crew as a voice recorder backup. This recorder will not be transferred to the LM for use during undocked operations. f. The S-band"squelch" will be on during the sleep periods in order to prevent MSFN fade-out noise from disturbing the crew.

2. DSE Operation a. The DSE will normally be operated via ground command except for special cases where the operation is time limited. In these cases the crew may be asked to rewind the tape. b. During the earth orbit period when the CSM is not over a MSFN station, CSMTLM-LBR data will be recorded on the DSE and will be dumped during the pass over the US and over CRO prior to TLI if possible. c. DSE will be used for CSM HBR and voice recording during all CSM engine burns. d. DSE data and voice recordings will be made in CSM LBR mode whenver possible in order to minimize the DSE dump time.

1-15 e. During PTC using the HGA REACQ communications mode the DSE will be used to record LBR data when the HGA is not in the MSFN field of view. f. During lunar orbit LM operations, the DSE will be used to record LM-TLM-LBR data during all docked LM activites that occur on the lunar farside. For undocked LM activites only DOI will be recorded as VHF ranging is required. g. DSE will be used to record all H_BRentry data during the blackout region.

3. Launch - Earth Orbit Phase a. 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 azimuth is less than 96° or OMNI C if the launch azimuth is greater than 96 ° . OMNI D will probably be the best antenna for earth orbit. b. VHF Duplex B will be used for launch, and Simplex A for earth orbit operations. c. VHF Simplex A will be used for entry to be compatible with recovery forces communications.

4. Translunar and Transearth Coast Phase The translunar and transearth sleep communications mode will be as follows. The CSM x-axis will be placed normal to the ecliptic plane. The CSM will be rolled at a rate of approximately three revolution per hour. During the near earth sleep periods prior to 30 hours GET (range less than 120Knm) omni antennas B and D will be used. During the other sleep periods (beyond 120Knm) the high gain antenna may be required (in the REACQmode). The REACQ configuration will provide approximately 210 degrees of HGA coverage per CSM/LM revolution or 35 minutes of MSFN coverage per hour. The REACQ configuration will also allow MCC-H to use real time control to select TLM HBR or LBR and to dump the DSE during each spacecraft revolution.

5. Lunar Exploration Phase a. 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 crewman and 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 of the Extravehicular Communication System (EVCS). The CDR will relay the LMP VHF voice and data to the LM which in turn will relay to MCC-H via S-Band.

1-16 E. CSMNotes I. Electrical Power System and Water Management a. Spacecraft lift-off switch positions are listed in the Apollo Operations 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 optics power-up as required). c. Fuel cell H2 and 02 purging is scheduled as follows H2 approximately every 48 hours and 02 approximately every 12 hours. d. The hydrogen and oxygen VAC ION pumps will be inactive throughout the mission. e. Potable water will be chlorinated once a day before each sleep period, 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 within one 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 preceding MCC maneuvers (7) In lunar orbit if dumping is required, dumps will be performed immediately prior to sleep periods (8) The water dump will not be operated in the automatic mode at anytime during the mission h. The cryogenic heaters will be in AUTO during the mission and the fans will be operated manually. The fans will be cycled for one minute before and after each sleep cycle. i. The batteries will be charged according to the following schedule: Time Battery 5:20:00 B 12:20:00 A 48:10:00 B 80:25:00 A 103:30:00 B 148:00:00 A 154:00:00 B 2. Environmental Control System and Cabin Pressurization a. One C02 odor absorber filter (LiOH canister) is changed approximately every 12 hours or if C02 partial pressure is greater than 7.6mm Hg. There are 20 filters (2 in the canisters onboard and 18 stowed).

1-17 b. A Pre TLI/LOI ECS redundant component check including the secondary evaporator operation, is performed prior to TLI and LOI. The secondary evaporator water control valves will be 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. Guidanceand Navigation ,_ a. During lunar orbit, the CSM and LM will utilize the same landing site REFSMMAT such that the gimbal angles would be 0,0,0 at landing with the LM sitting face forward on landing _ site number two and the CSM over the landing site pitched up 90 ° from local horizontal "heads up". b. During PTC the CSM/LM x-axis is Ditched up 90° (Nor for TLC and down 90° (South) for TEC with the Y-Z axes in the plane of the ecliptic. This change in x-axis pointing is to enable simultaneous viewing of the earth and moon through the side windows while maintaining a favorable high gain antenna position. c. The CSM tracking light will be on continuously from undocking to landing and from LM lift-off to docking.

4. Landmark Tracking The following ground rules were used for landmark tracking. a. IMU to be realigned on the dark side preceding each tracking period. b. MSFN is reacquired after each tracking period. The tracking data will be acquired by MSFN after all the marks 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 determine the altitude of an area in which the LM will be making altitude checks after DOI. The data will be processed during the sleep period after the trackings and relayed to the LM prior to undocking.

1 -18 o

d. In the docked configuration the CSM/LM _'__r_/_{_ approaches the landmark in an inertial hold attitude. This inertial attitude places the spacecraft 2° below the local horizontal at the 35 ° elevation angle point. At 35 ° elevation angle a pitch down of O.3°/sec is initiated. Five marks are then taken with the time between marks a minimum of 25

e. seconds.In the undocked(See trackingconfigurationprofile) the CSM /_r_. _22 ° approaches 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 a minimum of 25 seconds. ORB RATE is _'.\\\ ..... \\_ continued throughout the marking period. " \ will approach the LM in ORBRATEheads f. upIn andthe pitchedundockeddownCOAS40tracking° from thethe localCSM \ horizontal. When the LM is centered in the COASthe CSMwill initiate a 40° variable pitch rate to keep the LM centered in the COAS.

5. CSM/LM and CSM attitude maneuvers will normally be at a rate of 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 or as soon as MCCI is scrubbed and maintained throughout the mission (except in lunar orbit) until at least three hours before entry except for interruptions for midcourse corrections, communications orientation (maximum interruption of three hours). PTC will not be initiated before approximately 7:00 GET.

7. Service Propulsion System All SPS burns will be initiated on Bank A except LOll which will be initiated on Bank B.

F. LM Notes I. Entries into the LM a. Three entries into the LM are scheduled in the timeline at 56:30, 81:30 and 95:52 GET respectively.

1-19 b. The first entry (56:30 GET) will be for LM familiarization and will be performed by the CDR and LMP in the constant wear garments. During this period there will be approximately 5 minutes of VHF-B LBR data which will be recorded by the DSE in the CSM. The LM will remain on CSM power during the crew familiarization period. c. The second entry (81:30 GET) will be for LM housekeeping and will be performed by the LMP in constant wear ga_lents. During this period the LM will go to internal power for the S-Band/VHF B voice activation. d. The third entry into the LM (95:52 GET) will be performed by the LMP in LCG's to prepare the LM for undocking and descent to the lunar surface. During this period the LMP and CDR initially transfer to the LM in LCG's then return to the CSM for PGA donning. 2. Environmental Control System and Cabin Pressurization a. 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 periodically monitored. c. The LM will be pressurized prior to the first entry (LM familiarization) after which it will be isolated again for the remainder of the TLC period. d. Prior to the second entry (LM housekeeping) it will be pressurized again and will remain pressurized.

3. Guidance and Navigation a. Two LGC erasable memory dumps and MCC-H verifications will be accomplished prior to DOI. If a significant number of errors are found, memory correction and re-verification will be performed before DOI. b. The LM IMU will be manually aligned to the CSM IMU during the DOI Day LM activation and checkout. P52/AOT alignments will be performed as close to DOI as possible. c. All translations during the undocked manned LM operations will be under PGNCS control. d. The capability for MCC-H to update the LGC via uplink will normally be blocked by the LMP UP-DATA LINK switch (panel 12).

1 -20 4. RCS Operation and Interface Constraints a. During CSM/LMdocked checkout operations, the LM steerable and/or RR antennas will not be powered down once they have been activated. The SM B3 and C4 thrusters will be deactivated before the LM steerable and/or RR antennas have been unstowed in order to prevent SM-RCS impingement on these antennas. b. The CSMroll jets and LM yaw jets will be disabled when the probe is preloaded (docking latches are cocked} and the tunnel is pressurized prior to undocking. The jets will be activated after tunnel venting. c. LM RCS two jet ullaqe (System B) will be used for unstaged ullage maneuvers in order to prevent asymetrical RCS thrust caused by impingement on the descent stage. d. The RCS interconnect will be used during the APS lift-off and ascent, but will not be used during the rendezvous maneuvers.

5. Rendezvous a. The rendezvous radar will be pointed away from the sun and will be turned off when no functional use is required to prevent overheating of the antenna. b. The LM tracking light will be on continuously between separation and touchdown and between launch and docking except during PGNCS/AOTalignments. During PGNCS/AOTalign- ments (LM P52), the tracking light would interfere with the alignments. (dark adaption)

1-21 1-22 Z I.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 --I r-" .._1 X X TB6p _- X X X X X X R X X X X X X P TLI X X X _X X 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', ',O O_

.-I

2-2 TLI PAD

TB 6p X:XX:XX PREDICTEDTIMEOF BEGINNINGOF (HR:MIN:SEC) S-IVB RESTARTPREPARATIONFOR TLI (TB6 = TLI IGN -578.6 SEC)

R XXX(DEG) PREDICTEDSPACECRAFTIMU p XXX(DEG) GIMBALANGLESATTLI y XXX(DEG) IGNITION

BT X:XX (MIN:SEC) DURATIONOFTLI BURN

_VC XXXX.X(FPS) NOMINALTLI _V SETINTO EMS AV COUNTER

VI +XXXXX(FPS) NOMINALINERTIALVELOCITY DISPLAYED ON DSKY AT TLI CUTOFF

R SEP XXX(DEG) PREDICTEDSPACECRAFTIMU P SEP XXX(DEG) GIMBALANGLESAT COMPLETION Y SEP XXX (DEG) OF S-IVB MNVRTO CSM/S-IVB SEP ATTITUDE

R EXT XXX(DEG) PREDICTEDSPACECRAFTIMU P EXT XXX(DEG) GIMBALANGLESATTIME Y EXT XXX (DEG) OF CSM EXTRACTION OF LM FROM S-IVB

2-3 P37 BLOCK DATA ' I. ! O T, X l il X t _VT X [_ X ' LONG GET400K ! GETI X X _VT X X LONG GET400K GETI X X AVT X X LONG GET400K GETI eo X X AVT X I X LONG B T GET400K GETI X X AVT X X LONG GET400K o-. GETI _O O _. X X AVT X X LONG -- GET400K <1: GETI X X AVT X X LONG GET400K

2-4 P37 BLOCK DATA

GETI XXX:XX DESIREDTIMEOFIGNITION (HR:MIN)

ZVT XXXX(FPS) TOTALVELOCITYOF MNVR

LONG +XXX(DEG) LONGITUDEOFTHELANDING POINT FOR ENTRY GUIDANCE

GET400K XXX:XX TIMEOF ENTRYINTERFACE (HR:MIN)

2-5 P27 UPDATE

PURP V V VIn GF T •

304 .)1 INDEX INDEX INDEX O2 O3 O4 O5 O6 "_ 07 bo

11 12 13 14 15 16 17 2O 21 O'_ 22 O_ . 23 •_ 24

N34 HRS X X X X X X MIN 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 TYPEOFDATATOBE RECEIVED (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. OFCOMMAND WORDS 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) LATITUDEFORGROUND TRACK CONFIRMATION

LONG XXX.XX(DEG) LONGITUDEFORGROUND TRACK CONFIRMATION

ALT XXX.X(DEG) ALTITUDEFORGROUND TRACK CONFIRMATION

2-7 P30 MANEUVER PURPOSE

SET STARS I p PROP/GUID + WT N47

RALIGN 0 0 PTRIMN48 co"o PALlGN 0 0 YTRIM e0o o + 0 0 I HRS GETI " YALIGN__ + 0 0 0 MIN N33 + 0 SEC

ULLAGE. z_VX N81 AVy Z_V7 X X X R X X X P X X X Y

+ HA N42 Hp + Z_VT X X X BT HORIZO N/M/INDOW X _VC X X X X SXTS + 0 SFT

+ I 0 0 TRN 0"- o,.-o X X X BSS X X SPA ._ X X X SXP p./ _- 0 LAT N61 _: OTHER LONG + RTGO EMS + VIO GET 0. 050

2-8 P30 MANEUVER

PURPOSE XXXXX TYPEOF MNVRTO BEPERFORMED

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) P30 VELOCITYTO BEGAINED _V¥ TXXXX.X(FPS) COMPONENTSIN LOCALVERTICAL _VZ TXXXX.X(FPS) COORDINATES

R XXX(DEG) IMUGIMBALANGLESOF p XXX(DEG) MANEUVERATTITUDE y XXX(BEG)

HA XXXX.X(NM) PREDICTEDAPOGEEALTITUDE AFTER MANEUVER

HP +XXXX.X(NM) PREDICTEDPERIGEEALTITUDE AFTER MANEUVER

&VT +XXXX.X(FPS) TOTALVELOCITYOF MANEUVER

BT X:XX (MIN:SEC) MANEUVERDUPJ_TION

&VC XXXX.X(FPS) PREMANEUVER&VSETTINGIN EMS &V COUNTER

SXTS XX (OCTAL) SEXTANTSTARFORMANEUVER ATTITUDE CK

SFT +XXX.X(DEG) SEXTANTSHAFTSETTINGFOR MANEUVER ATTITUDE CK

TRN +XX.X (DEG) SEXTANTTRUNNIONSETTINGFOR MANEUVER ATTITUDE CK

BSS XX (OCTAL) BORESIGHTSTARFORMANEUVER ATTITUDE CK USING THE COAS

2-9 SPA +XX.X(DEG) BSSPITCHANGLEONCOASFOR MANEUVER ATTITUDE CK

SXP +X.X (DEG) BSSX POSITIONONCOASFOR MANEUVER ATTITUDE CK

LAT +XX.XX(DEG) LATITUDEANDLONGITUDEOFTHE LONG YXXX.XX(DEG) LANDINGPOINTFORENTRY GUIDANCE

RTGO +XXXX.X(NM) RANGETOGOFOREMS INITIALIZATION

VIO +XXXXX(FPS) INERTIALVELOCITYAT .05G FOR EMS INITIALIZATION

GET(.05G) XXX:XX:XX.XX TIMEOF .05G (HRS:MIN:SEC)

SETSTARS XX (OCTAL) STARSFORBACKUPGDCALIGN XX (OCTAL)

R, P, Y XXX(BEG) ATTITUDETOBESETIN (ALIGN) XXX(DEG) ATTITUDESETTWFORBACKUP XXX(DEG) GDCALIGN

ULLAGE X (jETS) NO.OFSMRCSJETSUSEDAND XX.X (SEC) LENGTHOF TIME OF ULLAGE

HORIZON/WINDOW XX.X (DEG) WINDOWMARKING AT WHICH HORIZON IS PLACED AT A SPECIFIED TIG (ATT CK)

OTHER ADDITIONALREMARKSVOICED UP 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 AVZ i PURPOSE -o o,. i'_ + 0 0 ' [ + 0 0 HR N33 o_ + 0 0 0 + 0 0 0 MtI'4 TIG , j ! , , + 0 I + 0 SEC AVX N84 I AVY ',i Ii _ AVZ / PURPOSE + 0 0 + 0 0 HR N33 + 0 0 0 + 0 0 0 MIN TIG + 0 + 0 SEC o. ! AVX N84 .o i o. 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) &V APPLIEDALONG _VZ XXXX.X(FPS) LOCALVERTICALAXIS AT TIG (LM)

2-12 -, (x a • i

• O0 p IOIOOO

.... N + N gO. * • • OO _ ___ Dooooe _o,ooo*

_ e-4 2-13 _-_ "_ _ _- v__- CSM SEP PAD

33 GETI XXX:XX:XX. XX GET OF CSM/LM SEPARATION (HRS:MIN:SEC) BURN

81 DELTAVX +XXXX.X(FPS) LOCALVERTICAL DELTAVY +XXXX.X (FPS) VELOCITYCOMPONENTS DELTAVZ +XXXX.X(FPS) OF SEPBURN

22 R XXX(DEG) SEPARATIONBURN P XXX(BEG) INERTIALGINBALANGLES Y XXX(BEG)

DOI PAD

84 DELTAVX XXXX.X(FPS) LM LOCALVERTICAL DELTAVY XXXX.X (FPS) VELOCITYCOMPONENTS DELTAVZ 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) LM LOCALVERTICALVELOCITY DELTAVY XXXX.X (FPS) COMPONENTSFORFIRST DELTAVZ 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 TPI 37 (HRS:MIN:SEC) FORLM ABORTS BETWEEN PDI AND PDI + 14.5 MIN FOR 2ND OPPORTUNITY

TPI (T2) GETI XXX:XX:XX.XX GETOF PREFERRED 37 (HRS:MIN:SEC) LMLIFTOFFTIME

RESCUE TWO PAD

47 WT XXXX.X(Ibs) PREMANEUVER CSM WEIGHT

48 P TRIM X.XX(DEG) SPSPITCH& YAW GIMBAL OFFSET TO Y TRIM X.XX (DEG) PLACETHRUST THROUGH THE CG

33 GETI XXX:XX:XX.XX GETOFRESCUE (HRS:MIN:SEC) BURN

81 DELTAVX XXXX,X (FPS) LOCALVERTICAL DELTAVY XXXX,X (FPS) VELOCITYCOMPONENTS DELTAVZ XXXX.X(FPS) OF RESCUEBURN

22 R XXX(DEG) RESCUEBURN P XXX(DEG) GIMBALANGLES Y XXX(BEG)

_Vc _Vc XX.X (FPS) VELOCITYTOBE SET IN EMS COUNTER FOR RESCUE BURN

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 THEFUTUREAPSIDAL CROSSING (APOLUNE OR PERILUNE) OF THE ACTIVE VEHICLE AT WHICH CDH SHOULD OCCUR

2-15 CSI ONE

II GETI XXX:XX:XX.X GETOF CSI OnE (HRS:MIN:SEC) BURN

81 DELTAVX XXXX.X(FPS) LOCALVERTICAL DELTAVY XXXX.X (FPS) VELOCITYCOMPONENTS DELTAVZ XXXX.X(FPS) OF CSI ONEBURN

N X THEFUTUREAPSIDAL CROSSING (APOLUNE OR PERILUNE) OF THE ACTIVE VEHICLE AT WHICH CDH SHOULD OCCUR

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) LOCALVERTICAL DELTAVY XXXX.X (FPS) VELOCITYCOMPONENTS DELTAVZ XXXX.X(FPS) OF CDHBURN

TPI

37 XXX:XX:XX.X GETOFLMTPI (HRS:MIN:SEC BURN

81 DELTAVX XXX(FPS LOCALVERTICAL DELTAVY XXX (FPS VELOCITYCOMPONENTS DELTAVZ XXX(FPS OFTPI BURN

59 _V (LOS) XXX(FPS VELOCITYCOMPONENTS ALONG THE LINE OF SIGHT TO TARGET

LOSBT X:XX MIN:SEC BURNDURATIONALONG THE 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 LOCAL HORIZONTAL

NM (NORS) XX.X(NM) DISTANCEOF LANDMARK NORTH OR SOUTH OF ORBITAL TRACK

89 LAT +XX.X(DEG) LATITUDEOF LANDMARK LONG 7XX (DEG) LONGITUDEOF LANDMARK ALT ALTITUDEOF LANDMARK ABOVE OR BELOW MEAN LUNAR RADIUS

NOMINAL LM IGNITION TIMES

CSI II GETI XXX:XX:XX.X NOMINALGET (HRS:MIN:SEC) OF LM CSI 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 HOR CK 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-ZC --+ 0 0 + 0 0 DLMIN _:"- Z --+ + VLMAX zDZZ _- + + vLMIN ._X_X X X X X DO X X X X RETVCIRC X X X X RETBBO X X X X RETEBO o,, ,4D o. 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 SPLASHDOWNAREADEFINEDBY TARGET LINE

R .05G XXX(DEG) SPACECRAFTIMUGIMBALANGLES P .05G XXX(DEG) REQUIREDFORAERODYNAMIC Y .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) PREDICTEDMAXIMUMREENTRY ACCELER_,TION

V4OOK +XXXXX(FPS) INERTIALVELOCITYAT ENTRY INTERFACE

400K -X.XX (DEG) INERTIALFLIGHTPATHANGLEAT ENTRY INTERFACE

RTGO +XXXX.X(NM) RANGETO GOFROM.05GTOTARGET FOR EMS INITIALIZATION

VIO +XXXXX(fps) INERTIALVELOCITYAT ,05G FOR 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) MAXIMUMACCEPTABLEVALUEOF PREDICTED DRAG LEVEL (FROM CMC)

DL MIN +X.XX (G's) MINIMUMACCEPTABLEVALUEOF PREDICTED DP,AG LEVEL (FROM CMC)

VL MAX +XXXXX(FPS) MAXIMUMACCEPTABLEVALUEOF EXIT VELOCITY (FROM CMC)

2-19 VL MIN +XXXXX(FPS) MINIMUMACCEPTABLEVALUEOF EXIT VELOCITY (FROM CMC)

DO X.XX(G's) PLANNEDDRAGLEVELDURING CONSTANT 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 TIMEFROMEl TO DROGUEDEPLOY (MIN:SEC)

SXTS XX(OCTAL) SEXTANTSTARFORENTRYATTITUDE CHECK

SFT +XXX.X (DEG) SEXTANTSHAFTSETTINGFOR ENTRY ATTITUDE CHECK

TRN +XX.X(DEG) SEXTANTTRUNNIONSETTINGFOR ENTRY ATTITUDE CHECK

BSS XXX(OCTAL) BORESIGHTSTARFORENTRY ATTITUDE CHECK USING THE COAS

SPA +XX.X(DEG) BSSPITCHANGLEONCOASFOR ENTRY ATTITUDE CHECK

SXP +X.X(DEG) BSSX POSITIONONCOASFOR ENTRY ATTITUDE CHECK

LIFT VECTOR XX (UP/DN) LIFT VECTORDESIREDAT .05G's BASED ON ENTRY CORRIDOR

2-20 THIS PAGE INTENTIONALLY LEFT BLANK. EARTH ORBIT ENTRY UPDATE X [ I X Z AREA X X - X X - _V TO

X X X I X X X R 0.05G EMS X X X I X X X P 0.05G X X X X X X Y 0.05G + + RTGO EMS I

+1 + I VlO X ,IX X X RET0.05G 0 0 LAT N61 ! LONG i X X I X X RET0.2G o',, 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 0.2G r'n . _. Z _ _] DRE::kl00nmN66 O _-

_O R R [ /' R R // BANK AN _ Z X X i X X RETRB X X X X RETBBO

X X X X RETEBO SEC X X X X RETDROGTOMAIN

2-21 EARTH ORBIT ENTRY UPDATE

AREA XX×-X RECOVERYAREA- FIRST 3 DIGITS DENOTES REV IN WHICH LANDING OCCURS. LAST DIGIT DENOTES RECOVERY AREA AND SUPPORT CAPABILITIES

AVTO XX.X (FPS) AVDUETOENGINETAILOFF

EMS

R O,05G XXX(DEG) SPACECRAFTIMU P O.05G XXX(DEG) GIMBALANGLESREQUIRED Y O.05G XXX(DEG) FORAERODYNAMICTRIM AT 0.05G.

EMS

RTGO XXXX.X(NM) RANGETOGOFROM .05G TO TARGET

VIO XXXXX(FPS) INERTIALVELOCITY AT .05G FOR EMS INITIALIZATION

RETO.05G XX:XX (MIN:SEC) TIME FROMRETROFIRE TO .05G

N61

LAT +XX.XX(DEG) LATITUDEOF IMPACTLANDING POINT

LONG +XXX.XX(DEG) LONGITUDEOF IMPACTLANDING POINT

N66

RET XX:XX(MIN:SEC) TIMEFROMRETROFIRE .2G TO.2G

DRE(55° ) +XXXX.X(NM) DOWNRANGEERROR AT .2G

BANK AN XX/XX (DEG/DEG) BACKUP BANK ANGLE FOR SCS ENTRY: ROLL RIGHT/ROLL LEFT

2-22 RETRB XX:XX(MIN:SEC) TIME FROMRETROFIRE TO REVERSE BACKUP BANK ANGLE

RETBBO XX:XX (MIN:SEC) TIME FROMRETROFIRETO BEGINNING OF COMMUNICATIONS BLACKOUT

RETEBO XX:XX (MIN:SEC) TIME FROMRETROFIRETO END OF COMMUNICATIONS BLACKOUT

RETDROG XX:XX (MIN:SEC) TIME FROMRETROFIRETO DROGUE CHUTE DEPLOYMENT

CHART UPDATE

90°/FPS ÷XX VALUES USED TO RE-PLOT DRE(90° ) _XXX BACKUPENTRYCHART- _V AND DOWNRANGE ERROR (DRE) @ 90° BANK ANGLE

POST BURN

P O.05G XXX(DEG) PITCHANGLE@ENTRY INTERFACE

EMS

RTGO +XXXX,X(NM) RANGETOGOFROMO.05G TO 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 SCS ENTRY: ROLL RIGHT/ROLL LEFT

RETRB XX:XX(MIN:SEC) TIME FROMRETROFIRETO REVERSE BACKUP BANK ANGLE

2-23 RETBBO XX:XX(MIN:SEC TIME FROMRETROFIRETO BEGINNING OF COMMUNICATIONS BLACKOUT

RETEBO XX:XX(MIN:SEC TIME FROMRETROFIRETOEND OF COMMUNICATIONS BLACKOUT

RETDROG XX:XX(MIN:SEC TIME FROMRETROFIRETO DROGUE CHUTE DEPLOYMENT

2-24 EARTH ORBIT BLOCK DATA X X B X X AREA ' I X X X X X X L o LAT X X [I _, X X ,_ .! LONG I I | * _ GETI X X X ! X X X ! I ±VC i AREA xixI j xx .1 , i X[X X i X X X ' LAT I LONG X X ! X X . * l i GETI .o X X X %Vc xxx ! , I , ,-" X X X X I j AREA I _-- X X X X X X LAT

< X X . X X 1 _, LONG : t '• _ ' GETI x x x • x x x 1I I' X X X X ' ,,_ AREA

X X X I! X X X _ LAT X X X X 1 LONG I 'T ! GETI X 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 L.Ud_.o._J :_" X X ! X X I LONG GETI

X X X X X X f, AVC REM AR KS:

2-25 EARTH ORBIT BLOCK DATA

AREA XXX-X RECOVERYAREA FIRST 3 DIGITS - LANDING REVOLUTION LAST DIGIT - RECOVERY AREA AND SUPPORTCAPABILITIES

LAT +XX.XX(DEG) COORDINATESOFTHE LONG 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 THE EMS COUNTER.

2-26 LM P27 UPDATE PO,_ ',1 I ,' I "1 I GET • • • • • •

• ' 1174 01 INDEX INDEX INDEX O2 03 "_4 a- O4 O5 O6 O7 10 11 12 13 14 15 16 17 o. 20 •,O O-- 21 "_ 22 "_ 23 a_ •,< 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 II II LONG ALT + 0 + 0 li

2-27 P27 UPDATE-LM

PURP XXX TYPEOFDATATOBE RECEIVED (SUCH AS: LDG TIME)

V XX(VERB) TYPEOFCOMMAND LOAD (70-7]-72-73)

GET XXX:XX:XX TIMEDATARECORDED (HR:MIN:SEC)

I174 Ol XX(OCTAL) INDEXNO.OFCOMMAND WORDSIN LOAD

02-24 XX(OCTAL) CORRECTIONWORD IDENTIFIERS

N34 NAVCHECKTIME XXX:XX:XX.XX TIME FORCONFIRMATION (HR:MIN:SEC) OF GROUNDTRACK

N43

LAT XX.XX(DEG) LATITUDEFORGROUND TRACK CONFIRMATION

LONG XXX.XX(DEG) LONGITUDEFORGROUND TRACK CONFIRMATION

ALT XXX.X(NM) ALTITUDEFORGROUND TRACK CONFIRMATION

2-28 AGS STATE VECTOR UPDATE

PURP

240 241 242 260 261 262 + + 254 244 245 246 264 265 266 o. + + 272 ',,0 o- REMARKS:

-J

2-29 AGS STATE VECTOR UPDATE

PURP PURPOSEFORAGSSTATE VECTOR 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) LMTIMEFORWHICH THE STATE VECTOR IS ACCURATE

244 +XX×XX(I00 FT) CSMSTATEVECTOR-POSITION COMPONENTS

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) CSMTIMEFORWHICH THE STATE VECTOR IS ACCURATE

2-30 O7

_.J

0 0 _ X X X X X X .,_1 (D + + + +j + X X X X X X

= = = • o_ ; -e = = I • = ! to-

_:_ x _: x x x xl ..t- 7t- ..4-

_ z

•-F _'- v_ <1 ,,::;I <:1 -r -.r-. <1 e,_ e.¢" o.. _ "_ _ "_ v_ _

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) PREDICTEDAPOGEERESULTING FROM MANEUVER

HP +XXXX.X(NM) PREDICTEDPERIGEERESULTING FROM MANEUVER

AVR +XXXX.X(FPS) TOTALAVREQUIREDFOR THE MANEUVER

BT X:XX (MIN:SEC DURATIONOFTHEMANEUVER

FDAI

R XXX(DEG) INERTIALFDAIANGLES AT THE BURN ATTITUDE

P XXX(BEG)

AGS AV

AVXAGS +XXXX.X(FPS LOCALVERTICALAV AVYAGS +"-XXXX.X(FPS COMPONENTSOFTHE AVZAGS _XXXX.X(FPS MANEUVERTO TARGET - THEAGS

BSS XX (OCTAL) BSSSTARFORMANEUVER ATTITUDE CHECK

SPA +XX.X (DEG) BSS PITCH ANGLE ON SXP TXX.X (DEG) COAS,& BSSX POSITION ON COAS FOR MANEUVER ATTITUDE CHECK

2-32 P30 LM MANEUVER 13 0 LO 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 PURPOSEOF MANEUVER (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) PREDICTEDAPOGEEAND PERIGEE RESULTING FROM HP +XXXX.X(NM) THEMANEUVER

AVR +XXXX.X(FPS) TOTALAV REQUIREDFORTHE MANEUVER

BT X:XX(MIN:SEC) DURATIONOFTHEMANEUVER

FDAI

R XXX(DEG) INERTIALFDAIANGLESAT P 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) BSSSTARFORBURN ATTITUDE CHECK

SPA +XX.X(DEG) BSSPITCHANGLEON - COAS, & BSS X POSITION SXP +XX.X(DEG) ONCOASFORMANEUVER ATTITUDE CHECK

2-34 -QO

Q- 0 0 X

+i+ ',i+ + li+ × "

2-35 DOI DATA CARD

N33 DOI TIG XXX:XX:XX.XX IGNITIONTIME OF (HR:MIN:SEC) LM MANEUVER

N81 LOCALVERTICALAV LOCALVERTICALAV COMPONENTS OF THE MANEUVER

AVX +XXXX.X(FPS)

AVY +XXXX.X(FPS)

AVZ +XXXX.X(FPS)

N42 ORBITAL PARAMETERS

HA +XXXX°X(NM) PREDICTEDAPOGEERESULTING FROM MANEUVER

HP +XXXX.X(NM) PREDICTEDPERIGEERESULTING FROM MANEUVER

AVR +XXXX.X(FPS) TOTALAVREQUIREDFOR THE MANEUVER

BT X:XX (MIN:SEC) DURATIONOFTHEMANEUVER

FDAI

R XXX(DEG) INERTIALFDAIANGLES AT THE BURN ATTITUDE P XXX(BEG)

N86 AGS AV

AVXAGS +XXXXoX(FPS) LOCALVERTICALAV AVY AGS +-XXXX.X (FPS) COMPONENTSOF THE AVZ AGS +--XXXX.X (FPS) MANEUVERTO TARGET THE AGS

BSS XXX (OCTAL) BSS STAR FOR MANEUVER ATTITUDE CHECK

SPA +XX.X(DEG) BSSPITCHANGLEON SXP TXX.X (DEG) COAS,& BSSX POSITION -- ONCOASFORMANEUVER ATTITUDE CHECK

2-36 - _ • ... --41. !L- !i L -. _ ii--I'" ._. l o ' I IC, ' x x x ! ,=_,c:, O!C, o (:_ 0 _ J x x x o c=, _ C, 0

o+ o+ + i i F-]" _+ x xi:,< Ii _ ÷ o+ ; + +i+: ÷ i _ ! ' i

• _ i . 0 0 o o i i × _I_ ; o o olo' " o o o ' x x i'-x ; _ .... I' i i c_io c, oi_, o + + + 11 + 1i-I- X X'X II "_i '+ _ + +: ÷ I-:

,_,I ,'_ ...s _ .',- _ <_ ,.o ,- ,-:, ,-, ,-, __

",.0 (.'0 _

,=_

I"-

÷ : x '_ °°°°°°-I- -F, -F- +, + + ! i , • --- F

40 .... _ -- Z

o c_: x!x x oio'

0 010 x x x:x A C _ 0 0 010 + +I+ x X x x + + + i -{-÷ -F- ,.,., c.O r"-,

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-PLANEDISTANCE BETWEEN THE INITIAL LM ORBITAL PLANE AND THE LANDING SITE (POSITIVE INDICATES LANDING SITE IS NORTH OF ORBITAL PLANE)

FDAI AT TIG

R XXX(DEG) INERTIALFDAIANGLES P XXX(DEG) ATIGNITION Y XXX(BEG)

DEDA231 XXXXX(I00 FT) LUNARRADIUSATTHE (IF REQ'D) LANDINGSITE

PDI ABORT

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) LOCALVERTICALAV COMPONENTSOF THE AVY +XXXX.X(FPS) PHASINGMANEUVER

AVZ +XXXX.X(FPS)

N42 ORBITAL PARAMETERS

HA +XXXX.X(NM) PREDICTEDAPOGEE RESULTING FROM HANEUVER

HP +XXXX.X(NM) PREDICTEDPERIGEE RESULTING FROM MANEUVER

AVR XXXX.X(FPS) TOTALAV REQUIRED FOR THE MANEUVER

BT X:XX (MIN:SEC) DURATIONOF MANEUVER

FDAI

R XXX(DEG) INERTIALFDAIANGLES AT THE BURN ATTITUDE P XXX(DEG)

N86 AGS AV

AVXAGS +XXXX.X(FPS) LOCALVERTICALAV COMPONENTS OF THE AVYAGS +XXXX.X(FPS) MANEUVERTO TARGET THE 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. I 'I 1 I 'I , _+o • l _+o • ° o oo oEo_ ° °° ° °'_ °l° oo_._ oo + + + + +.+ +!+ + + + + + + + ' _ 0 I i 0 <:nl 0 + ..... : ' t + + + + + +++ + +!+ + _- + i + :t + +I ,.+.+_ _ o,'--+-4-- :-+°+ _ _+ e o __.oj_ ___o + :.+o o _o+ . ._o o+ot oo' ++o+ o+ - + o:o o+o o o , o+ ooo oo+oo+ :(+- oooo:oo.....ol+oi+-_,0.....:++o; . ++ +- + + + +++:++ Ii+ +++++i + +++0+@+ +i+ + +°++i+t+ +++++ +:+"++ + +i+ I---_-. c._o.. _ z I--- _/_/+/+/+/+/+/_ c +---_'- ]I c'_°" --

m_ =_:+.'+, :,: _ _, :=:_ <.':, _ m_ = +.'+,:,: _, = '.,+,=: <.':, + ++ _,+

, I I .... ,..... , - : I .... i...... i .+ + + . + + ; , + " +o+" _ -" + + _- " + o <:::>+oo o o o+ot i o _ ° <:::>+oo ° o o+ot o do o,o o 0+o'0 o' 0 +++ [ CD C_ 0 0[0 +C_ 0 0 0 0 0 to, ++ , i 'i i , : L ,///+//+/+/] i i ,

+ , ..... + _- '_ +" +o:".....+++"o" + +o:" o o+...... o+,=++--o o+...... o o,+.... I _ o +...... o+,o Io o, + + +o o oo o o0 O%Io- + o o'o otoo o o o]O%Io- ++ + + + + +! +_++-+ + ++++_+_+++ l , l

_ _ _ ,..-. P_ _ _, ,_ ¢..u_ ,.-.-_

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 OFFTIME AFTER (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 AND LIFTOFF 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 TIG L + 0 I + 0 SEC I + _ + 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 HORIZONTALVELOCITY AT ORBIT INSERTION

V(VERT) XXXX.X(FPS VERTICALVELOCITYAT ORBIT INSERTION

CROSSRANGE +XXX.X(NM) CROSSRANGEDISTANCE AT ORBITAL INSERTION

DEDA047 XXXXXX(OCTAL) SINEOFLANDING AZIMUTH ANGLE

DEDA053 XXXXXX(OCTAL) COSINEOFLANDING AZIMUTH ANGLE

DEDA225 XXXXXX(I00 FT) LOWERLIMIT OF _ AT ORBIT INSERTION

DEDA226 XXXXXX(lO0 FT) UPPERLIMIT OFG_ AT ORBIT INSERTION

DEDA231 XXXXXX(lO0 FT) RADIALDISTANCE OF LAUNCH SITE FROM CENTER OF MOON

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 LOCALVERTICALAV COMPONENTS OF THE AVY XXX.X(FPS CSl MANEUVER

FDAI PITCH XXX(DEG) FDAI INERTIALPITCH ANGLE AT THE CSl BURN ATTITUDE

DEDA373 XXXX.X(MIN) AGSIGNITIONTIME OF NEXT MANEUVER

DEDA275 XXXX.X(MIN) DESIREDTPI TIG (FOR CSl CALCULATION ONLY)

N86 AGS AV

AVXAGS XX°XX(FPS) LOCALVERTICALAV COMPONENTSOF 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) LOCALVERTICALAV AVY TXXX.X(FPS) COMPONENTSOFCDH AVZ TXXX.X(FPS) MANEUVER

PLMFDAI XXX(DEG) FDAIINERTIAL PITCH ANGLE AT CDH BURN ATTITUDE

DEDA373 XXXX.X(MIN) AGSIGNITIONTIME OF NEXT MANEUVER

N86 AGS AV

AVXAGS +XXX.X(FPS) LOCALVERTICALAV _VYAGS _XXX.X(FPS) COMPONENTSOF CDH &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

NSi LOCAL VERTICAL _V

_VX +XX.X(FPS LOCALVERTICAL£V Z4Y ¥>',X.X (FPS COMPONENTSOF THE _'/Z TXX.X (FPS TPI MANEUVER

N42_VR +XX.X (FPS TOTAL&V REQUIRED FOR THE MANEUVER RLM XXX(DEG) ROLLANDPITCH PLM XXX(DEG) FDAIANGLESATTPI BURN ATTITUDE

N54 TIG-5

R TPI XX.XX(FT) RANGEATTPI TIG - B MIN

TPI +XXX.X(FPS) RANGERATEAT TP! TIG - 5 MIN

N59 A V LOS

F/A +XX.X (FPS) LINE-OF-SIGHT &V R/L YXX.X (FPS) COMPONENTSOF THE D/U TXX.X (FPS) TPI MANEUVER

BT XX:XX (MIN:SEC DURATIONOFTHEMANEUVER

2-49 SECTION Ill - DETAILED TIMELINE Z

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DETAILED OBJECTIVE ACTIVITIES

This section contains the activity summaries which reflect the test objectives 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 in the 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 Test Objectives (complete or partial) which relate to the particular activity;

B. TEST REQUIREMENTS. Here the special test prerequisites (and mission phase if necessary) are presented in addition to brief statements of the requirements for performing the activity;

C. TEST PROCEDURES/CHECKLISTS. These are the procedural references for the performance of the activity as far as the test objectives are concerned; and

D. DATA REQUIREMENTS. This part of the summary identifies the gross data which are needed for evaluation of test results in terms of flight crew and ground support requirements.

Cross references for relating Detailed and Functional Test Objectives with the activity summaries and relating activities to Functional Test Objectives, are provided 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 constrain the timeline of the crew _rocedures.

B. Post-flight debriefing requirements which are fulfilled by real time transmission of data per the DATA REQUIREMENTSsections may be deleted from the post-flight debriefing.

All of the Test Requirements have not been totally implemented into the mission 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-I MISSION 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

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4-5 LM DESCENT

A. Test Objective

D-l LM Landing Gear Performance Under Landing Conditions G-l Location of the Landed LM from LM Data G-3 Capability of Locating the Landed LM in Real Time from LM/CSM/MSFN Data H-l Data on Landing Aids and Final Approach Visibility M-l Photograph Lunar Surface During LM Descent

B. Test Requirements

I. Determine landing site visibility, extent of washout and visibility of landing site landmarks. [H]

2. Photograph the landing site during the approach through the LM pilot's window with the data acquisition camera. [G, H, M]

3. Evaluate landing aids, i.e., Landing Point Designator, maps, photographs. [G, H]

4. Assess visual phenomena during LM landing which are significantly different from expected. [H]

5. Voice anotate location and identity of features during final descent. [m]

6. Determine landing location in real time by description of terrain features 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 approach and 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 LM final approach. [H] (M)

c. Voice track regarding observations of surface features during the descent phase. [G] (M)

d. Photographs of the landing site and surrounding lunar surface features taken through a LM window during descent. [G, M] (M)

4-6 e. Data Acquisition Camera photographs of the landing site from high gate to touchdown. [H, M] (M)

f. Photographs of the landing site and surrounding lunar surface features 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 TM LBR. [D, G] (M)

c, LM BET from DOi through touchdown. [G, H] (M)

d. MSFN tracking data of LM from acquisition of signal through touchdown. [G] (F4)

4-7 LUNAR SURFACE NAVIGATION

A. Test Objectives

G-I Determine the Location of the Landed LM from LM Data G-2 Determine the Location of the Landed LM from CSM Data G-3 Determine Capability of Locating the Landed LM in Real Time from LM/CSM/MSFNData L-4 Panoramic Coverage of Distant Terrain Features M-2 Photograph Lunar Surface Post Touchdown/Pre EVA

B. Test Requirements

I. Correlate lunar surface features surrounding the landing site with photomaps 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. Mark on 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 surrounding 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 in estimating the location of the LM with respect to lunar surface features. [G] (HD)

c. Comments by LM crewman on location of landed LM with respect to prominent terrain features. [G] (M)

d. Obtain high resolution photographs of the landing area from the CSM. [G] (M)

e. Photographs of the landing site and surrounding lunar surface features 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 lunar missions. [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 indirect illumination. [L] (HD)

4-9 EVA PREPARATION AND EGRESS

A. Test Objectives

B-l Demonstrate Egress-to/Ingress-from the Lunar Surface B-2 Evaluate Crew Lunar Surface EVA Capability C-l EMU Capability to Provide a Habitable Environment C-2 EMU Effects on Crew Mobility/Dexterity/Comfort C-3 Data/Voice Communications Capability During EVA L-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 camera power 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 surface EVA. [L]

5. During EVA, communicate with MSFN via the EVA-LM-MSFN two way voice relay. [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 simultaneously transmitted 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 water diverter 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 feed water pressure or PGA pressure low remote control unit status indicators 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 the visor assembly. [C] (HD)

e Comment on the adequacy of procedures and difficulties encountered during donning of EMU equipment. [C] (HD)

f Comment on time required and adequacy of the EMU checkout procedures. [C] (MD)

g Comment on the adequacy of EMU thermal environment when walking from a sunlit area to shadow and vice versa. [C] (_)

h Comment on estimated energy expenditure and comfort as compared to simulation experience. [C] (HD)

i Provide data on the adequacy of hardware and procedures, and the time 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) transmitted simultaneously with TV data. [L] (M)

4-1i h. Identity of ground station(s) used to record video transmission from LM. [L] (M) i. Time period, if any, when erectable antenna used to transmit TV 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 Sample E-I Behavior and Characteristics of the Lunar Surface F-I Collect Rock Samples and Fine Grained Material F-2 Photograph Collection Area of Samples I-3 Obtain a Lunar Sample for Quarantine Testing J-2 Obtain a Core Sample of the Lunar Surface J-3 Collect Lunar Geologic Samples J-4 Collect a Lunar Environment Sample M-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 2/3 loose samples. [F]

3. Core Sample - Obtain with the drive tube. [I, J]

4. Geologic Samples - Obtain using tools stowed in the MESA. Photograph sample 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 one bag 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 as defined 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 Gear D-2 Effects of Landing on LM Structure and Components D-3 Descent Engine Skirt Damage and Clearance After Landing D-4 Effects of RCS Plume Impingement on LM Structure and Components L-2 TV Coverage of External Landed LM M-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 discoloration or lunar soil accumulation. [D] (M)

b. Comments describing any descent engine skirt damage and estimate of 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 strut assembly. [D] (M)

d. Photograph the landing gear to show the stroking of the primary and secondary 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 the Y 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 material adhering 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 lunar surface. [L] (M)

4-16 LUNAR SURFACE OBSERVATIONS AND PHOTOGRAPHY

A. Test Objectives

E-I Behavior and Characteristics of the Lunar Surface E-2 Erosion of Lunar Surface by DPS Plume Impingement E-3 Effect of Any DPS Venting on the Lunar Surface H-2 Crew Performance of Visual Tasks on the Lunar Surface J-5 Study and Description of Lunar Topography Features L-3 TV Coverage of Lunar Surface Near LM [o-4 TV Panoramic Coverage of Distant Terrain Features L-5 Coverage of Astronaut Activities on the Lunar Surface M-3 Obtain Photographs During EVA

B. Test Requirements

I. Provide TV coverage of the lunar surface in the vicinity of the LM and panoramic scenes of distant terrain features. [L]

2. Photograph the lunar terrain at various azimuths with respect to the sun including 9, 90 and 180 degrees. Comment on ability to see terrain features in these areas. LH, M]

3. Estimate the distance to prominent terrain features within the field of 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 surface from interactions of astronauts boots and equipment with the lunar soil, 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 types of lunar topographic features. [J,M]

7. Photograph the structure of lunar surface material in its natural state. [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 ports on the TV camera at the beginning and the end of the TV operations. [L] (M)

4-17 b. Position of the TV camera scan rate switch at start of TV operation. [L] (M)

c. Comments describing the interaction between astronaut boots and lunar surface while walking. [E] (M)

d. Comments on slope and roughness characteristics of the landing terrain to include descriptions of craters, depressions, embankments or other obstacles. [E] (M)

e. Comments on the color and texture of both undisturbed and mechanically disturbed areas of the lunar surface. [E] (M)

f. Comments on lunar soil conditions adjacent to DPS vents to include any discoloration. [E] (M)

g. Comments describing the lunar surface penetration by the Solar Wind Composition Staff and core sample tool under their own weight and the estimated force. [E] (Mandatory for either the staff or the core sample tool: highly desirable for the other.)

h. Comments on lunar soil erosion as caused by the DPS plume impingement during landing. [E] (M)

i. Record vent valves opened. [E] (M)

j. Photograph the lunar surface showing DPS plume impingement erosive effects. [E, M] (M)

k. Photograph the lunar surface adjacent to DPS vents if soil discoloration is observed. [E, M] (M)

I. Photograph an astronaut footprint showing interaction between astronaut boots and lunar surface. [E, M] (M) m. Photograph the Solar Wind Composition Experiment Staff and core sampling tool after being inserted to their maximum depth as penetrometers. [E, M] (HD) n. Photograph the natural slopes, crater walls and embankments in 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 of the sun/viewing angle and on their ability to perform visual tasks while 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 within the field of view of the photographs in item t below. [HI (M)

t. Photograph the lunar terrain at various sun azimuths to include 0 degrees, 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 the scoop in collecting fine grained fragmental material. [E, M] (M)

w. Photograph one scoop of fine grained fragmental material placed in one of the pre-numbered bags. [E, M] (HD)

x. Photograph of each LM foot pad and surrounding lunar soil exhibiting evidence 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 transmission. [L] (M)

h. Time period when erectable antenna was used to transmit from the lunar surface. [L] (M)

4-19 EXPERIMENT DEPLOYMENT/CONDUCT

A. Test Objectives

S-031 Deploy the Passive Seismic Experiment Package S-078 Deploy the Laser Ranging Retro-Reflector Experiment S-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 descent stage and carry it to the deployment site. [S-078]

4. Emp-lace, level and orient the LRRR to the alignment marks corresponding to she landing site. [S-078]

5. Remove the Solar Wind Composition Experiment from the LM MESA and deploy it on the lunar surface. [S-080]

6. After one hour operation, disassemble the Solar Wind Composition Experiment, place the reel and foil in a teflon bag and store in a sample 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 the LM, attitude of deployed foil with respect to the sun and total time 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 Surface C-l EMU Capability to Provide a Habitable Environment C-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 water diverter 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 feed water pressure or PGA pressur_ low remote control unit status indicators and audible warning tone come on. [C] (M)

c. Provide data on the adequacy of hardware and procedures, and the time required to perform the ingress to the LM. [B] (M)

d. Comment on the adequacy of procedures and difficulties encountered during 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 crew member ascending the LM ladder. [B] (M)

4-21 Contamination Prevention

A. Test Objectives

I-l Prevent Earth Contamination by Lunar Exposed Materials I-2 Minimize Crew/CM Contamination by Lunar Exposed Materials

B. Test Requirements

I. All contamination related operations from the initial astronaut egress to the lunar surface until postflight crew/cm quarantine will be completed per procedures contained in _he documents listed below. [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 related equipment and procedures used to prevent back contamination. [I] (M)

b. Photograph boots, clothing and equipment showing adhesion of particles. [I, M] (HD)

2. Ground Support

a. Deliver samples, CM and Mobile Quarantine Facility to the Lunar Receiving Laboratory. [I] (M)

b. Comment on ground procedures and hardware used for retrieval, biological isolation and CM transfer to the Lunar Receiving Laboratory. 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 the Mission Planning and Analysis Division (MPAD) for their work in the preparation of the consumable analysis presented herein and to the Crew Systems Division for the PLSS Consumables.

5-i CSM-IO7/LM5 PROPELLANT BUDGET

The results of the Propellant Budget Analysis are summarized in the following 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

Seliverable SX-RCS propellant 122C.0

Nominalusage 590

Translunar phase (through LOI-2) 204

Lunar oreitphase _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{WA3_ AX|_OR_i_ R _NSEMENT TION BUrN I PbNC_ 9b19a, _._ lO_b,_ _b,

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_0 SEP 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,

I I2beb 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,} 5bo MNVK 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 [:RHINADATKMF _ATEPTC5 2743Z= 1,3 682,3 58,

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 _.

i 19_,_ 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 O N

= __ _'E m R

"-"I _- O t_

3,uaaJad'6u!6e6P_0qu0 II I I I I I I _8 8 8 8 8 _ o

ql '6U!U!_LUaJ_,Uellad0JdS3a WSalqesn 0 0

0 O0

I i

! -,=

! £

(:D LL- i

c- 0_- 0 _'_

0 M_

0 0 0 0 _' 0

}ua0Jad '6u!6_6 pJ_0quo I I I I I I I I I 0 0 0 C:_ 0 0 0 0

ql '6u!u!euJaJ _Uellad0Jd $3_t WS alqesfl i I 4 I I I ..J

_,ua3Jad '6u!6e6 pJeoquo I I I I I I I I I

ql '6u!u!euJaJ _,UelladoJd 53_1 WS alqesN 0 0

0 O0

t- 0

0 _-

0 N

0 0 0 0 0 0

)_ua_a'gdu!6eBp_eoquo I I I 1 I I I I I

ql 'lSu]u!eu.laJ ]UelladoJd$3_IWSalqeSl-I 0

cD ----

r-- 0

iuaoJed'6u!6e6pJe0quo I I I I I I I I I

0 O0 _ C;, "_ ¢xJ CO

ql '6u!u!euJaJ ),UelladoJd$3_1 WS alqeSrl 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 -- 208.6 mission 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 injection, _.a = hour lunar parking orbit, and fast earth re_uz<,_. The assumn- tions use(_ in >,_'-_=--*o_,a_'ir=_this budget are _oresented in table 5-5. AV recuirements were coordinated with I2,1&B in MPAD.

It should be noted that the mission flexibility allowance c!' _,CC fps n_s beeK used in ...... _-'d:_it'_nto t Pe fast return. _Tn real time however, it is higkly _,±ke'" _/ 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 propellant re!,;¢i£in:_ ne.Ttlr_al!y and a total propellant t__ar_in (accounting _:

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

a Loaded " _'_'_

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

LOI-I (__o,__4_ fps, 9 rain. 59 see. ,'I o=_<_._,_,,__.,7 k 1517_. 7

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!ant- margin -- 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

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 SPS budget 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

TankedSPS • ° • • ° ° . , . • 4C o_0.7f_ !b

...._i,=(unmanne d) ...... ° • jx__ 276• 5 ib

Total 96 nnn _ Ib 4. Lu_nar Orbit Activity Total 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 encre=en_a=.... + 7 Weight Lcss_ Ib

EL to _±_JiC_ . .... ° . • . o 191._ 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 was 216 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 I J TIfF FV;I_I TTTI F a q/C WT ! M I M b I M b 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 97.3 i 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_. b RCS propellant remaining of total loaded 5-27 TABLE 5-7 (CONT'D)

LIe " #tCS PKqPELLAh.T _%UIC-F'[ P_(_F. 2 •,. _1 D iO I:_L EVEN! ]Jli_E [q/C ,_]_ I N LM LN ili

~~,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 _9.7 I /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~~

~~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 85.5 APS j_N.,_C_Oj!4 i_E C _~~

~~12q _ P___ ,_ _0 _ ' 5969, ,9 526.7 8;5.2 CS/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_~~

~~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 [~~

~~125 Z6 IvAII_TAIN LOS 5920. 3.3 477.2 75.q~~

125 '4-4 i,NVR lo PLAi'i| E CI-iANGE ATTITUDh 5919. .4 476.8 75.3 These weights were used for analysis only and do not reflect the actual weight after consumables loadin_. b RCS 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 b HRS 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 ..... [_ --- .•-J "-.~~

~~._Iy++I:_++÷++'::++I:.5±I+++SFL:_[{_+I+?+...... Y:_I-LL__z,3._:,-_..=--_+-+:++,+::::, oo~~

~~V- o • -,D __ +++?i++++:+++++:++++i:++_I_i+_++:++i_t_++'_i+?_++?+;++_+=+++°+ . _ % o~~

~~(M m m~~

~~0 0~~

~~0 0 0 0 0 0 0 O0 _C) _' luao_ad 'papeo I le_Oi I I I I I I I I~~

~~Or_ 0 0 0 0 0 0~~

~~ql 'Pap_ol lelO_l. DESCENT PROPULSION SYSTEM PROPELL_NT BUDGET~~

~~Descent Pronu!sion Subsystem (DPS) - The DPS budget is shown in table 5-8 and the gro_u_ rules and assumptions in table 5-9.~~

Previously, the _ncertainty in the low-level sensor (65.7 !b) has been sho_n as 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 (90 sec) 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 residual propellants are from Volume III_ SODB. Engine performance da_a and AV requirements !ave been coordinated with LAB in P_AD.

~~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 ib from DOI to touchdown~~

~~ASCENT PROPULSION SYSTEM PROPELL&NT BUDGET~~

Ascent Propulsion Subsystem (APS) - Tables 5-10 and 5-11 present the ascent propellant 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 or about 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._ PSNCS tc 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 the following 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 two inverters.~~

~~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, parachute descent_ and postlanding time. Each battery was assumed to have 40 A-h capacity until splashdo-_m, at which time the capacity was uprated 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 three on battery B.~~

~~5-35 TABLE 5-12 APOLLO ii CRYOGENIC SD%9,_RY~~

~~I. PlanningAllowance K2_ ib 027 ib 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 i A. 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 (Incl Cabin Purge) - 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~~

~~RSS Subtotal 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 i KSC Supplied Data 5-36 lu_o.l_ "6UlU!etLl_J ua6/_x0 il I I I I I I I I I I I I I I i I~~

~~ql"6u!u!e_aJua6/_O l.i i~~

~~_.uaaJad'6u[u!ewaJua_._p,_H I[ 1 I I I I I I I I I I I I ]~~

~~ql '6u!u!ewaJuaBeJp,_H oe_ N~~

~~:11o^'a6ellOAsn8 L_,IEPS AN_iLYSIS~~

~~GROU_Z} RUI_ES AND ASSU_[PT!ONS i. The descent stage batteries go on the line ]< minutes pricr to earth liftoff.~~

~~2. A 9.8 hour checkout was assumed for llomar orbit.~~

~~7. Ascent and descent batteries were paralleled for the powered descent burn and prior to liftoff from the lunar surface.~~

~~4. %_:!eS-band equipment was assumed on !GC percent from initial activation in lunar orbit until completion of the mission.~~

~~_._ TT:e rendezvous radar electronics _._asassumed to be operational for the period of time dictated hy the current 3 Mission flight p]an.~~

~~6, _:Le primary navigation and {uidance subsystem (PCNCS) was left in the operate mode for the entire lunar stay.~~

~~7. __:e fom_,ard window heaters were left off for the entire mission.~~

~~5-41 00 ..-I~~

~~'ml" ..-I~~

~~o ,-I~~

~~o o ,.-..I~~

~~,,0 o,.~~

~~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 02~~

~~f o. _L_0 consumed because of sublimator cooling was total heat removed divided by 1040 (btu per ib) of H20~~

~~7. HI2 0 lost due to urination was 0.ii Ib/hr per man~~

~~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 may change 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 I I[!tl I!lllll ! J I k i I I I i I I I I [ II_l i J lliill IIIIIIt I I ] I L I I i I L I } I I I I E IL_ I I ( I I i I_1 I I I [ I I I I1_1 E ( I I I I i I I I I I I I I I ILeal I I I I I i I ] I I I t 1 I I I I1_1 I I I I I F t I I | I I ] I I I I_%_ I I I I I i i I I I i I E I I [ I_ I I I I I i I I I I I I I I I I I[_M E I I I I I I I I I I I I I I I I i_l

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