Apollo 12 Mission Operation Report

8/8/2019 Apollo 12 Mission Operation Report

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Report No. M-932-69- 12


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FOREWORD

MISS ION OPERATION REPORTS are published expressly for the use of NASA SeniorManagement, as required by the Administrator in NASA instruction 6-2-10, dated1.5 August 1963. The purpose of these reports is to provide NASA Senior Management

with timely, complete, and definitive information on flight m ission plans, and toestablish official mission objectives which provide the basis for assessment of missionaccomplishment.Initial reports are prepared and issued for each flight project just prior to launch.Following launch, updating reports for each missionare issued to keepGeneral Manage-ment currently informed of definitive mission results as provided in NASA Instruction6-2-10Primary distribution of these reports is intended for personnel having program/p roiectmanagement responsibilities which sometimes results in a highly technical orientation.The Office of Public Affairs publishes a comprehensive series of pre-launch and post-launch reports on NASA flight missions which are available for dissemination to thePress.

APOLLO MISSION OPERATION REPORTS are published in two volumes: theMISSIONOPERATION REPORT (MOR) ; and the MISSION OPERATION REPORT, APOLLOSUPPLEMENT. This format was designed to provide a mission-oriented document inthe MOR, with supporting equipmen t and facility description in the MOR, APOLLOSUPPLEMENT. The MOR, APOLLO SUPPLEMENT is a program-oriented referencedocument with a broad technical description of the space vehicle and associated equip-ment, the launch complex, and mission control and support facilities.

Published and Distributed byPROGRAM and SPECIAL REPORTS DIVISION (FP)

EXECUTIVE SECRETARIAT - NASA HEADQUARTERS


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LIST OF FIGURESFigure Title Page

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10111213141516171819202122232425262728293031

Apollo Flight Mission Development PhasesApollo/Saturn V Space Vehicle CountdownApollo 12 Landing SiteApollo 12 Flight ProfileLM Descent EventsLM Powered DescentLunar Surface Activity Timeline - EVA-lDeployed MESADeployed S-band AntennaApollo 12 Deployed TV Camera PositionsRadioisotope Thermoelectric Generator FuelingDeployed ALSEP IDeployed Passive Seismic ExperimentDeployed Solar Wind Spectrometer ExperimentDeployed Lunar Surface Magnetometer ExperimentDeployed Suprathermal Ion Detector/Cold Cathode Ion

Gauge ExperimentLunar Surface Activity Timeline - EVA-2Equipment Transfer Bag/Lunar Equipment ConveyorHand Tool CarrierSurveyor I I I ActivitiesSurveyor It1Sample Return ContainerLunar Surface Close-up CameraLM Ascent Through DockingLM Ascent Stage DeorbitApollo 12 Contingency OptionsApollo Earth Orbit Chart (AEO)Communications During Lunar Surface Operations with

Erectable Antenna DeployedPrimary Landing Area and Force DeploymentApollo 12 Prime CrewApollo 12 Backup Crew

27&81214192021222324252628282929313232343536363738424849515758

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Table1

6

LIST OF TABLESTitle

Apollo 12 Landing Sites/LaunchW i ndowsApollo 12 Mission SummaryApollo 12 TV ScheduleApollo 12 Weight SummaryComparison of Major Differences -Apollo 11 vs. 12

Network Configuration for Apollo 12Mission

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15161740

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PROGRAM DEVELOPMENTSince the first Saturn flight, the Apollo Program has been developing toward a lunarlanding and exploration of the lunar surface. Each successive flight has demonstratedthe performance capabilities of the space vehicle, crew, and ground support and hasverified operational techniques and procedures. The first Apollo flights, AS-201through Apollo 6 , were launch vehicle and spacecraft development flights. Apollo 7,the first manned flight, demonstrated Command/Service Module (CSM)/crew performanceand CSM rendezvous capabi Ii ty . The Apollo 8 Mission carried CSM operations furtherby successfully demonstrating CSM operations and selected backup lunar landing missionactivities in lunar orbit. Apollo 9 was an earth-orbital mission which demonstratedCSM/Lunar Module (LM) operations and LM/ crew performance of selected lunar landingmission activities in earth orbit. The final developmental mission before the actuallunar landing was Apollo 10. It evaluated LM performance in the cislunar and lunarenvironment and duplicated the lunar landing mission profile as closely as possiblewithout actually landing. The success of these missions finally culminated in theApollo 11 Mission, the first manned lunar landing and return mission. The success ofthe Apollo 11 Mission verified the performance of the space vehicle and support systemsand proved mans capability to accomplish a lunar mission enabling the Apollo Programto proceed with detailed exploration of the lunar surface. Figure 1 traces the Apolloflight mission development phases through the first lunar landing.

The final nine lunar exploration missions in the Apollo Program will be divided intotwo types of missions - H-series and J-series. The four H-series missions, Apollo 12through Apollo 15, will be flown with standard Apollo hardware and will provideincreased surface stay time with two extravehicular activity (EVA) periods, improvedlanding accuracy, development of CSM transport techniques, and will establish aseismic network. The last five missions, Apollo 16 through Apollo 20, will be J-seriesmissions and will be flown with modified Apollo hardware designed to extend missionduration and lunar surface stay time, to increase landed payload and sample return,to extend lunar surface EVA operations and increase mobility, and to provide forscientific experiments and mapping to be accomplished in lunar orbit.

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APOLLO 10 5/18/69 APOLLO 11 7/16/69

-UNMANNED ---*MANNEDAPOLLOFLIGHTMISSION DEVELOPMENTHASES


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NASA OMSF PRIMARY MISSION OBJECTIVES FOR APOLLO 12PRIMARY OBJECTIVES

. Perform seienological inspection, survey, and sampling in a mare area.

. Deploy and activate an Apollo Lunar Surface Experiments Package (ALSEP).

. Develop techniques for a point landing capability.

. Develop mans capability to work in the lunar environment.

. Obtain photographs of candidate exploration sites.

--zzL$?G,Rocco A. PetroneApollo Program Director P

eorge E. MuellerAssociate Administrator forManned Space Flight

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DETAILED OBJECTIVES AND EXPERIMENTSPRINCIPAL DETAILED OBJECTIVES1.2.3.4.5.6.7.8.9.

Contingency Sample Collection.Lunar Surface EVA Operations.Apollo Lunar Surface Experiments Package (ALSEP) I Deployment and Activation.Selected Sample Collection.PLSS Recharge.Lunar Field Geology (S-059).Photography of Candidate Exploration Sites.Lunar Surface Characteristics.Lunar Environment Visibility.

10. Landed LM Location.11. Selenodetic Reference Point Update .12. Solar Wind Composition (S-080).

13. Lunar Multispectral Photography (S-158).SECONDARY DETAILED OBJECTIVES14. Surveyor III Investigation.15. Photographic Coverage During Lunar Landing and Lunar Surface Operations.16, Television Coverage Through the Erectable S-band Antenna.

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LAUNCH COUNTDOWN AND TURNAROUND CAPABILITY. AS-507COUNTDOWNCountdown (CD) for launch of the AS-507 Space Vehicle (SV) for the Apollo 12 Missionwill begin with a precount starting at T-98 hours during which launch vehicle (LV) andspacecraft (S/C) CD activities will be conducted independently. Official coordinatedS/C and LV CD will begin at T-28 hours. Figure 2 shows the significant eventsbeginning with the official countdown start.SCRUB/TURNAROUNDTurnaround is the time required to recycle and count down to launch (T-O) in a subse-quent launch window. The following launch window constraints apply:

0 56 hours 09 minutes are available for turnaround between the opening of the14 November and the closing of the 16 November launch windows.

l 29 hours 13 minutes are available for turnaround between the opening of the14 December and the closing of the 15 December launch windows.

Scrub can occur at any point in the CD when launch support facilities, SV conditions,or weather warrant. For a hold that results in a scrub prior to T-22 minutes, turn-around procedures are initiated from the point of hold. Should a hold occur fromT-22 minutes (S-II start bottle chilldown) to T-16.2 seconds (S-IC forward umbilicaldisconnect), then a recycle to T-22 minutes, a hold, or a scrub is possible underconditions stated in the Launch Mission Rules. A hold between T-16.2 seconds andT-8.9 seconds (ignition) could result in either a recycle or a scrub depending uponthe circumstances. An automatic or manual cutoff after T-8.9 seconds will result ina scrub.Two basic cases can be identified to implement the required turnaround activities inpreparation for a subsequent launch attempt following a scrub prior to ignition command.These cases identify the turnaround activities necessary to maintain the same confidencefor subsequent launch attempts as for the original attempt. The scrub/turnaround timefor each case is the minimum time required to effect recycle and CD of the SV to T-O(liftoff) after a scrub. They do not account for serial times which may be required forrepair or retest of any systems which may have caused the scrub, nor do they includebuilt-in holds for launch window synchronization. The basic difference in the twocases is the requirement to reservice the spacecraft cryogenics, which necessitatesdetailed safety precautions and the reuse of the Mobile Service Structure.

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48-Hour Scrub/TurnaroundA 48-hour scrub/turnaround capability exists from any point in the launch CD up toT-8.9 seconds. This turnaround capability provides for reservicing all SV cryogenicsand resumption of the CD at T-9 hours.24-Hour Scrub/TurnaroundA 24-hour turnaround capability exists as late in the CD as T-8.9 seconds. Thiscapability depends upon having sufficient S/C consumables margins above redlinequantities stated in the Launch Mission Rules (or negotiated changes to these redlinequantities) for the period remaining to the next launch window. The CD would beresumed at T-9 hours.

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FLIGHT MISS ION DESCRIPTIONLANDING SITESApollo Lunar Landing Site 7 is the prime site for the Apollo 12 Mission. This site islocated entirely within relatively old (Imbrian) mare material and also shares thecharacteristic distribution of large subdued 200-600 meter (m) diameter craters as wellas the characteristic lower density of 50-200 m diameter craters. This site includesthe crater in which Surveyor III landed in April 1967. One of the primary scientificobjectives of landing at this site is to sample a second mare for comparison withApollo 11 and Surveyor data in order to learn the variability in composition and ageof the lmbrium mare unit.Apollo Lunar Landing Site 5 is the recycle site for this mission and is located withinrelatively young (Eratosthenian) mare material. In contrast to Tranquility Base andLanding Site 7, the area of this site displays a large number of intermediate sizecraters 50-200 m in diameter and a small number of larger subdued craters 200-600 min diameter. The site is surrounded by well-developed crater clusters of the Keplersystem. Small, weakly developed crater clusters and Iineaments radial to Kepleroccur within the site. Thus some material derived from depth at Kepler may be pre-sented in the surficial material, and fine-scale textural details related to the Keplerrays may also be present. There are more resolvable blocks (greater than 2 m) aroundcraters than in the three s ites to the east (Landing Sites 1, 2, and 3) suggesting thatthe surficial material isLAUNCH WINDOWSThe launch windows for

generally coarser grained.

both Site 7 and Site 5 are shown in Table 1.

TABLEl,APOLLO12 LANDINGSITES/1AUNCHWINDOWS,NOV (EST) DEC (EST)

SITE LONG. LAT. DATE OPEN-CLOSE SEA* DATE OPEN-CLOSE SEA7 23024'W.t 2059% 14 1122-1428 5.l'O 14 1334-1658 lp5 4154'W. 104l'N. 16 1409-1727 10.70 15 15131847 5.3Ob

*SUN ELEVATION ANGLE

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HYBRID TRAJECTORYThe Apollo 12 Mission will use a hybrid trajectory that retains most of the safetyfeatures of the free-return trajectory, but without the performance limitations. Thespacecraft will be injected into a highly eccentric elliptical orbit (perilune altitudeof approximately 1850 nautical miles (NM), which has the free-return characteristic,i.e., the spacecraft can return to the entry corridor without any further maneuvers.The spacecraft will not depart from the free-return ellipse until after the Lunar Module(LM) has been extracted from the launch vehicle and can provide a propulsion systembackup to the Service Propulsion System (SPS). After approximately 28 hours fromtranslunar injection, a midcourse maneuver will be performed by the SPS to place thespacecraft on a lunar approach trajectory (non-free-return) having a lower perilunealtitude.The use of a hybrid trajectory will permit:

Daylight launch/Pacific iniection. This would allow the crew to acquire thehorizon as a backup attitude reference during high altitude abort, wouldprovide launch abort recovery visibility, and would improve launch photo-graphic coverage.Desired lunar landing site sun elevation. The hybrid profile facilitatesadjustment of translunar transit time which can be used to control sun angleson the landing site during lunar orbit and on landing.Increased spacecraft performance. The launch vehicle energy requirementsfor translunar injection into the highly eccentric elliptical orbit are less thanthose for a free-return trajectory from which lunar orbit insertion would beperformed. . Th is allows for an increase in spacecraft payIoad/SPS propellant.The energy of the spacecraft on a hybrid lunar approach trajectory is relativelylow compared to what it would be on a full free-return trajectory thus reducingthe differential velocity (AV) required to achieve lunar orbit insertion.

LUNAR MODULE POINT LANDINGThe LM point landing capability of Apollo 12 is being enhanced in two significantareas. The first is concerned with improving the ground targeting of the PrimaryGuidance Navigation and Control System (PGNCS), i .e., updating the LM guidancecomputer with the LMs current position and velocity, and the landing site position.The second is concerned with reducing the in-orbit perturbations during the last threeorbits before descent orbit insertion.

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Significant improvements in ground targeting of the PGNCS include:a Adding one more term to the computer program coverage of the lunar potentialmodel in the Real-Time Computer Complex. This permits a significant improve-

ment in LM .orbit determination and descent targeting during a single LM orbit.l Updating the PGNCS with the LMs position after undocking to avoid thedegrading effect of this maneuver on the LM state vector.0 Updating the LM downtrack position relative to the landing site duringpowered descent.

Steps taken to reduce in-orbit perturbations include:0l

000000

Water and waste dumps will be avoided 8-10 hours before landing.LM Reaction Control System (RCS) checkout will be done with rotationalmaneuvers and with cold fire instead of nulled translational maneuvers.Command/Service Module (CSM) will perform undocking maneuver.LM undocking will be done radially to avoid downrange AV.Soft undocking will be performed.Landing gear inspection will be deleted if indications are nominal lCSM rather than the LM will be active in station keeping.CSM wil I perform separation maneuver.

Figure 3 shows the Apollo 12 landing site. Targeting will be to Surveyor III and manualcontrol will be used to fly to the actual landing area.

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1O/29/69APOLLO12 LANDING SITE

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FLIGHT PROFILELaunch Throuah Earth Parkina OrbitThe AS-507 Sp ace Vehicle for the Apollo 12 Mission is planned to be launched at11:22 EST on 14 November 1969 from Launch Complex 39A at the Kennedy SpaceCenter, Florida, on a launch azimuth of 72. The Saturn V Launch Vehicle willinsert the S-IVB/lnstrument Unit (IU)/LM/CSM into a 103-NM, circular orbit. TheS-IVB and spacecraft checkout will be accomp lished during the orbital coast phase.Figure 4 and Tables 2 through 4 summarize the flight profile events and space vehicleweight.Translunar lniectionApproximately 2.8 hours after liftoff, the launch vehicle S-IVB stage will be reignitedduring the second parking orbit to perform the translunar injection (TLI) maneuver,placing the spacecraft on a free-return trajectory having a perilune of approximately1850 NM.Translunar CoastThe CSM will separate from the S-lVB/lU/LM approximately 3.2 hours Ground E lapsedTime (GET), transpose, dock, and initiate ejection of the LM. During these maneuvers,the LM and S-lVB/IU will be photographed to provide engineering data.An S-IVB evasive maneuver will be initiated by ground comm and approximately 1.6hours after TLI. This maneuver will be performed by the Auxiliary Propulsion System(APS) of the S-IVB to impart a AV of approximately 10 feet .per second (fps) and pre-vent recontact with the spacecraft. Shortly thereafter, an S-IVB slingshot maneuverwill be perform ed to place the S-lVB/IU onto a trajectory passing the moons trailingedge and into solar orbit. This maneuver will be performed by a combination ofcontinuous hydrogen venting, liquid oxygen (LOX) dumping, and an APS ullagemaneuver. The total AV imparted to the S-lVB/IU by the slingshot maneuver willbe approximately 115 fps.The spacecraft will be placed on a hybrid trajectory by performing an SPS maneuver atthe time scheduled for the second midcourse correction (MCC) approximately 31 hoursfrom liftoff. The CSM/LM combination will be targeted for a pericynthion altitude of60 NM and, as a result of the SPS maneuver, will be placed on a non-free-returntrajectory. The spacecraft will remain within a LM Descent Propulsion System (DPS)return capability.

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CSWLM -SEPARATION

CM/SM SEPARATION

FREE-RETURN TRAJECTORYS/C SEPARATION,TRANSPOSITION,DOCKING, & EJEC TION S-IVB APSEVASIVE MANEUVER

yn, /CSM 60 NM

INITIATION

S-IVB RESTARTDURING 2ND OR3RD ORBITS-IVB 2ND BURN CUTOFFTRANSLUNAR INJECTION (TLI)

n-.ca.P APOLLO12 FLIGHTPROFILE

RBIT


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TABLE2APOLLO12MISSION SUMMARY .EVENT GET DATE/EST BURN DURATIONDAY:HR:MIN HR:MIN (APPROX. SEC.) REMARKS

LAUNCH 0:OO:DO 14/11:22 WINDOW LOSES 1428 ESTTRANSLUNAR NJECTION (TLI) 0:02:47 14/14:09 345 (S-IVB) PACIFIC OCEANMIDCOURSECORRECTION MCC-2) l:D6:53 15/18:15 10 (SPS) HYBRID TRANSFERLUNAR ORBIT INSERTION (LOI-1) 3:11:25 17/22:47 355 (SPS) ORBIT: 59 X 169 MILESLUNAR ORBIT INSERTION (LOI-2) 3:15:44 18/03:06 18 (SPS) ORBIT: 53 X 65.MILESUNDOCK 4:11:54 18/23:16 16 (CSM-RCS)DESCENTORBIT INSERTION (DOI) 4:13:23 19/00:45 28 (DPS) LM ORBIT: 59X8 MILESPOWE RED ESCENT NITIATION (POI) 4:14:20 19/01:42 679 (DPS)LANDING 4:14:31 19/01:53BEGIN EXTRAVEHICULAR CTIVITY(EVA-l) 4:18:33 , 19/05:55 3 HOURS 0 MINUTESBEGIN EVA 2 5:13:07 20/00:29 3 HOURS 0 MINUTESLM LIFTOFF 5:22:01

~20/09:23 430 (APS) LM ORBIT 8 X 45 MILES

DOCKING 6:01:40 20/13:02LUNAR ORBIT PLANE CHANGE 6:15:02 21/02:24 18 (SPS)TRANSEARTH NJECTION (TEI) 7:04:21 1 21/15:43 129 (SPS)LANDING 10:04:35 24/15:57 LATITUDE = 16OSLONGITUDE = 165"WLOCAL TIME 09:57 (SUN RISE + 5 HR.MISSION DURATION: 244 HR. 35 MIN.


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TABLE3APOLLOlZW SCHEDULEDAY DATE EST GET COVERAGEI ,

FRIDAY NOV. 14 14:42 03:25 TRANSPOSITION / DOCKINGSATURDAY NOV. 15 17:47 30:25 HYBRID TRAJ. / SPACECRAFT INTERIORMONDAY NOV. 17 02:52 63:30 EARTH, IVT, S/C INTERIOR

20:52 81:30 r' PRE LOI-1, LUNAR SURFACE23:22 84:00 LUNAR SURFACE

TUESDAY NOV. 18 23:12 107:50 UNDOCKING FORMATION FLYINGWEDNESDAY NOV. 19 06:02 114:40 LUNAR SURFACE EVATHURSDAY NOV. 20 00:42 133:20 EVA - 2, EQUIPMENT JETTISON

12:37 145:15 DOCKINGFRIDAY NOV. 21 16:17 172:55 POST - TEI / LUNAR SURFACESUNDAY NOV. 23 18:37 223:15 MOON EARTH - S/C INTERIOR


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TAGE/MODULE INERT WEIGHT-1C Stage-IC/S-IInterstage-II Stage-II/S-IVBnterstage-1VB Stagenstrument Unit

pacecraft-LMdapter#unar Moduleervice Moduleommand Moduleaunch Escapeystem

TABLE4APOLLO12WEIGHT SUMMARY(Weight in Pounds)

287,850 4,742,86511,465 m-m80,220

8,035980,200-we

25,0504,275

235,020---

TOTALEXPENDABLES

Launch Vehicle at Ignition

4,0609,635 23,690

10,510 40,59512,365 e-e8,945

Spacecraft At Ignitionpace Vehicle at Ignition-1C Thrust Builduppace Vehicle at Liftoffpace Vehicle at Orbit Insertion

* CSM/LM Separation.

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TOTAL WEIGHT5,030,715

11,4651,060,420

8,035

FINALSEPARATIONWEIGHT363,465Be-

94,440we-262,070 28,440

4,275 e-m6,374,980

4,060 ---33,32551,10512,365

8,945

*33,74011,84011,145(Landing)

v-s109,800

6,484,780(-185,3206,399,300

300,269


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The earth will be photographed several times each day during this coast phase foroceanographic, global weather, and documentation purposes as the spacecraft attitudeand crew time permit. The moon will also be photographed. MCCs will be made asrequired, using the Manned Space Flight Network (MSFN) for navigation.

Lunar Orbit InsertionThe SPS will insert the spacecraft into an initial lunar orbit (approximately 60 x 170 NM)83.4 hours from liftoff (Figure 4). Following insertion and systems checks, a second SPSretrograde burn will be made to place the spacecraft in an elliptical orbit 54 x 66 NM.This orbit is planned to become Grcular at 60 NM by the time of LM rendezvous.

Because lunar orbit insertion (LOI) Iwa y s occurs behind the moon, the crew will berequired to evaluate the progress of the maneuver without ground support. Althoughtwo LOI burns are required to produce a near circular orbit, the monitoring requirementsprimarily impact the first burn (LOI-1), b ecause the second burn (LOI-2) lasts for onlyapproximately 18 seconds. The horizon and several stars should be visible from theCommanders (CDRs) rendezvous window and may be used as a backup to the opticsfor the orientation check prior to SPS ignition.

Lunar Orbit CoastAfter LOI- the Lunar Module Pilot (LMP) and the CDR will enter the LM to performhousekeeping and the initial LM activation. Subsequently, a rest and eat period ofapproximately 8.5 hours will be provided for the three astronauts prior to LM activationand checkout.The CSM will separate radially upward from the LM at approximately 20.7 hours fromLOI- using the soft undocking technique. The docking probe capture latches will beused to minimize separation AV perturbations. After undocking, the CSM will maintaina distance of 40 feet from the LM. The LM will not perform any inspection maneuvers(e.g., landing gear inspection), unless there is a real-time indication that the landinggear did not deploy properly.Lunar Module Descent

The DPS will be used to perform the descent orbit insertion (DOI) maneuver approxi-mately 1.5 hours after CSM/LM separation. This maneuver places the LM in a 60-NMby 50,000-foot orbit as shown in Figure 5.

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CSM ""',/.a~-,>/ LM DESCENT\

ORBIT (60 N MIBY 50,000 FT)

SU = STATE VECTORRLS = RADIUS LANDING SITEEARTH

LM DESCENTEVENTS

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Fig. 5Powered descent initiation (PDI) will occur near the pericynthion of the descent orbit(Figure 6). The vertical descent portion of the landing phase will start at an altitudeof approximately 100 feet for an automatic approach. Present plans provide for manualtakeover by the crew at an altitude of 500 feet.

During descent the lunar surface will be photographed to record LM movement, surfacedisturbances, and to aid in determining the landed LM location.Lunar Surface Operations

PostlandingImmediately upon landing, the LM crew will execute the lunar contact checklistand reach a stay/no-stay decision. After reaching a decision to stay, the InertialMeasurement Unit will be aligned, the Abort Guidance System gyro calibrated andaligned, and the lunar surface photographed through the LM window. Followinga crew eat period all loose items not required for extravehicular activity (EVA)will be stowed.EVA 1The activity timeline for EVA 1 is shown in Figure 7. Both crew members will donhelmets, gloves, Portable Life Support Systems (PLSS), and Oxygen Purge Systems(OPS) and the cabin will be depressurized from 3.5 pounds per square inch (psi).

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SUMMARYEVENTS

A ULLAGEB POWERED DESCENT INITIATIONC THROTTLE TO FTP0 LANDING RADAR (LR)

ALTITUDE UPDATEE THROTTLE RECOVERYF LR VELOCITY UPDATEG HIGH GATE

TFI - Time From IgnitionFTP - Full Throttle Position

LMPOWERED ESCENT


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ACTIVITY TI MELINE -EVA I M-932-69-12

Fig. 7


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The CDR will move through the hatch, deploy the Lunar Equipment Conveyor(LEC), and move to the ladder where he will deploy the Modularized EquipmentStowage Assembly (MESA), F gure 8, which initiates television coverage fromthe MESA. He will then descend the ladder to the lunar surface. The LMP willmonitor and photograph the CDR using a 70mm and a sequence camera (16mm DataAcquisition Camera).

DEPLOYEDMESA Fig. 8Environmental Familiarization/Contingency Sample Collection - After stepping tothe surface and checking his mobility, stability, and the Extravehicular MobilityUnit (EMU), the CDR will collect a contingency sample. This would make itpossible to assess the differences in the lunar surface material between the Apollo 11and 12 landing sites in the event the EVA were term inated at this point. The samplewill be collected by quickly scooping up a loose sample of the lunar material(approximately 2 pounds), sealing it in a Contingency Sample Container, andtransferring the sample in the Equipment Transfer Bag (ETB) along with the lithiumhydroxide (LiOH) canisters and PLSS batteries into the LM using the LEC. TheLMP will then transfer the 70mm cameras to the surface in the ETB.

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Contingency Photography - The CDR will photograph the contingency sample area,deploy and photograph the color chart in the sunlight, and photograph the descentof the LMP to the surface.S-band Antenna Deployment - The S-band antenna will be removed from the LMand carried to the site where the CDR will erect it as shown in Figure 9, connectthe antenna cable to the LM, and perform the required alignment.

DEPLOYED -BAND ANTENNA Fig. 9Flag Deployment - The CDR will then unstow the American flag and carry it tothe deployment site and implant it in the lunar surface.Lunar TV Camera Deployment - While the CDR deploys the S-band antenna, theLMP will unstow the TV camera and deploy it on the tripod approximately 20 feetfrom the LM in the 10 oclock position (Figure 10). The LMP will then obtain TVpanorama and special interest views after which he will point the camera at theS-band antenna/flag deployment/MESA area.

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TVCameraPosition2O,OUIL8 OClockPosition

APOLLO12 DEPLOYED V CAMERAPOS TIONS10/29/69

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After offloading the ALSEP packages, theRadioisotope Thermoelectric Generator(RTG), which provides the ALSEP electricalpower, will be fueled (Figure 1 l), theALSEP subpackages will be attached toa one-man carry bar for traverse in abarbell mode, as shown on the cover,and the TV will be positioned to view theALSEP site . RAD OlSOTOPETHERMOELECTRICGENERATORUELING

Fig. 111O/29/69 Page 25

- The LMP will next unstow and deploy theriment which uses a 4-square foot aluminum

foil area for entrapment of solar wind particles. It will be carried to the deploy-ment site where the foil will be unfurled and the staff implanted in the lunarsurface. As in the Apollo 11 Mission, the SWC detector will be brought back toearth by the astronauts. However, on Apollo 12 the detector will be exposed tothe solar wind flux for approximately 17 hours instead of 2 hours and will be placeda sufficient distance away from the LM to protect it from lunar dust kicked up byastronaut activity.LM Inspection - After repositioning theTV to view the Scientific Equipment Baydoor area, the LMP will inspect andphotograph the LM footpads and quadrants(QUADs) I, II, Ill, and IV with his 70m mcamera. Concurrently the CDR willobtain panorama and close-up photographs.ALSEP Deployment - Both crew memberswill offload, deploy, and activate theApollo Lunar Surface Experiments Package(ALSEP) which will obtain scientific dataconsisting of lunar physical and environ-mental characteristics and transmit thedata to earth for determination of (1) themagnetic fields at the moon, (2) the lunaratmosphere and ionosphere and the lunarseismic activity, and (3) the properties ofthe solar wind plasma as it exists at thelunar surface. The ALSEP is stowed andoffloaded in two subpackages. The fuelcask (part of the electrical power sub-system) is attached to the LM.


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The LMP will th en carry the ALSEP subpackages in the barbell mode to thedeployment site approximately 300 feet from the LM while the CDR carries asubpallet of ALSEP. U pon arriving at the deployment site they will survey thesite and determine the desired location for the experiments. The followingindividual experiment packages will then be separated, assembled, connected tothe ALSEP cabling, and deployed to their respective sites (Figure 12).

LM ASCENT BLAST AND THERMAL CONSIDERATIONS - ----\

100% SAFETY FACTOR

\ ER. -OhCRT

CENTRAL STATION(WITH DUST DETECTOR) _~~PASSIVE SEISMIClOFT+

MAGNETOMETERSOLAR WINDSPECTROMETER

dr

SUPRATH ERMALION DETECTOR

COLD CATHODE ION GAUGE

DEPLOYEDALSEPI~-

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Passive Seismic Experiment (Figure 13) - This experiment is designed tomonitor seismic activity and affords the opportunity to detect meteoroidimpacts and free oscillations of the moon. It may also detect surface tidaldeformations resulting in part from periodic variations in the strength anddirection of external gravitational fields acting upon the moon .Solar Wind Spectrometer Experiment (Figure 14) - This experiment willmeasure energies, densities, incidence angles, and temporal variations ofthe electron and proton components of the solar wind on the surface of themoon.Lunar Surface Magnetometer Experiment (Figure 15) - This experiment willmeasure the magnitude and temporal variations of the lunar surface equatorialfield vector.Suprathermal Ion Detector (Lunar Ionosphere Detector) Experiment (Figure 16) -This experiment will measure the flux, number, density, velocity, and energyper unit charge of positive ions in the vicinity of the lunar surface.*Cold Cathode Ion Gauge (Lunar Atmosphere Detector) Experiment - Thisexperiment will determ ine the density of any lunar ambient atmosphereincluding variations either of a random character or associated with lunarlocal time or solar activity. In addition, the rate of loss of contaminantsleft in the landing area by the astronauts and the Lunar Module will bemeasured. *Lunar Dust Detector Experiment - This experiment will obtain data for theassessment of dust accretion on ALSEP to provide a measure of the degradationof thermal surfaces.

Following the deployment of experiments, the ALSEP will be activated, datareceipt by MSFN confirmed, and the ALSEP site and deployed experimentsphotographed. The ALSEP site will also be photographed from the LM area.Selected Sample Collection - During the return traverse to the LM, both crewmenwill collect a selected sample of geologically interesting materia l, including rocksamples and fine-grained fragmental material, which will be carried in a side bagon each crewman. Approximately three-fourths of the quantity will be rock sampleswith the remaining one-fourth fine-grained materia l. The samples and the immediatesample site will be photographed.

* On ALSEP I, the suprathermal ion detector and cold cathode ion gauge will beintegrated together in one experiment system.

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DEPLOYED ASSIVESEISMIC EXPERIMENTFig. 13

DEPLOYED OLARWINDSPECTROMETERXPERIMENT

Fig. 14


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The LMP will carry the TV back to the LM area and position it to view the MESAand surrounding area from the 2 oclock position shown in Figure 10. The LMPwill then assemble the core tube and handle, and collect a core sample. Aftercollecting the core sample, the sample will be capped and stowed in SampleReturn Container (SRC) 1.Upon return to the LM, the CDR will unstow the selected SRC, attach the scaleto the MESA, finish filling the CDR and LMP side bags with loose materia l, sealthe organic control sample, pack the samples, and seal the SRC.After helping the CDR with the selected sample collection, the LMP will cleanhis EMU, ingress the LM, check LM systems, switch to the erectable S-bandantenna, and make a communications check. The CDR will attach the LEC tothe SRC 1 and transfer it into the LM with the assistance of the LMP.Post-EVA 1 OperationsAfter configuring the LM systems for post-EVA 1 operations, the PLSSs will berecharged. This includes filling the oxygen system to a minimum pressure of875 psi, filling the water reservoir, and replacing the battery and LiOH cannister.The PISSs and OPSs will be doffed and stowed, followed by an eat period, a -9-hour rest period, -Kother eat perio.EVA 2After pre-EVA configuring of the EMUs and LM systems, the cabin will bedepressurized from 3.5 psi and the CDR will descend to the surface for EVA 2(Figure 17). Upon transferring the 70mm Lunar Surface Cameras to the surfaceusing the ETB and LEC (Figure 18), and turning on the 16mm Data AcquisitionCamera (Sequence Camera) in the LM, the LMP wil I descend to the surface.Lunar FieldGeology Experiment - Both crewmen will participate in the conductof the Lunar Field Geology Experiment, which is to provide data for use in theinterpretation of the geologic history of the moon. A team of earth-basedgeologists will be available to advise the astronauts in real-time.Geology traverse preparations will include stowing several contrast charts, ahammer, an extension handle, a small and a large scoop, core tubes and caps,sample bag dispenser, and a gnomon on the Hand Tool Carrier (HTC) (Figure 19);attaching side bags; stowing the cutting tool in the CDRs Surveyor parts bag;attaching a 70mm Lunar Surface Camera to each EMU; tethering tongs to theCDRs EMU; deploying contrast charts; and repositioning the TV for geologytraverse.

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EQUIPMENTTRANSFERAG/LUNAREQUIPMENTCONVEYORFig. 18

HANDTOOLCARRIERFig. .19


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The geology traverse for this experiment will cons ist of documented samplecollection, core tube sample collection, trench site sample collection, and gasanalysis sample collection. A typical documented sample collection will includephotographing the sample and its site and describing and stowing the sample in asample bag. A typical core tube sample collection will include photographingthe sample site cross sun, driving the core tube into the surface and photographingthe core tube down sun, and pulling and capping the core tube. Trench s itesample collection will include digging a trench along the sunline, filling thespecial environmental sample container with surface material and sealing it,photographing the trench both down and up sun, collecting a core sample fromthe trench, and stowing the samples in the HTC. Gas analysis sample collectionwil I include photographing the sample both cross and down sun, collecting.thesample using tongs, and placing it in and sealing the gas analysis samplecontainer which will be stowed in the HTC.Surveyor site and vehicle investigation will precede the geology return traverse.Surveyor Site Activity - As a secondary objective, it is planned that the CDR andLMP will walk to the Surveyor Ill site for an investigation of the site and theSurveyor vehicle (Figure 20). The CDR and LMP will descend into the cratercontaining the Surveyor Ill and collect samples of lunar material including lunarbedrock, layered rock, and rounded rocks in ray patterns. The LMP will obtainphotographs of lunar material in the vicinity of and deposited on the Surveyor IIIspacecraft as well as several photographs of the Surveyor spacecraft equipment(Figure 21). The CDR will read the LMPs checklist during the LMPs photographyand then cut the TV camera, a piece of the TV camera electrical cable which willbe dropped untouched into the special environmental sample container, and apolished aluminum tube from the Surveyor using the cutting tool. The LMP willassist the CDR in the cutting task and will stow the equipment in the Surveyorparts bag on the CDRs PLSS. In addition, if feasible and safe, the CDR andLMP will collect pieces of glass from the Surveyor Ill spacecraft mirrors andreport on the extent of debonding.Post-Geology Activity - After completion of the geology return traverse, the TVcamera will be repositioned to view the MESA and the ladder; the SWC will beretrieved and stowed in the SRC; the 70mm lunar surface cameras wil I be stowedin the ETB; the side bag samples, the core tubes, special environmental samplecontainer, gas analysis sample container, and documented samples will betransferred in the SRC (Figure 22); and the LMP will obtain surface close-upphotographs with the Apollo Lunar Surface Close-up Camera (Figure 23). Afterboth EMUs have been checked and cleaned, the LMP will ingress the LM andassist the CDR in transferring the SRC, ETB, and the Surveyor parts bag into theLM.

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11-.(D.0

-N-

SCOOP

SUNSCOOP IMPRINTAR fA FOOTPAD 2 AREA/

0 -


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SURVEYOR llFig. 21

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EVA-2 Termination - After completing equipment transfer to the LM, the CDRwill clean his EMU, ascend the ladder and ingress into the LM. Expendableequipment will be jettisoned and the cabin repressurized terminating the secondEVA.

CSM Lunar Orbit OperationsLunar Mul tispectral PhotographyDuring the period of lunar surface operations, the Command Module Pilot (CMP)will obtain simultaneous multispectral photographs of the lunar surface at threewidely separated wavelengths. This photography will provide data on lunarsurface co lor variations (at an order of magnitude higher resolution than obtainablefrom earth) which will be useful in geologic mapping. For example, the sharpnessof the color boundaries will give a good indication of the compositional differences.In addition, it will provide data for correlation with the spectral reflectanceproperties of the returned lunar samples from Apollo 11 and thus will allow possibleextrapolation of compositional information on other areas of the moon on which nolandings will occur. Finally, it will define areas of interest for future correlationwith the returned samples.

Lunar Module AscentThe LM ascent (Figure 24) will begin after a lunar stay of approximately 31.5 hours.The Ascent Propulsion System (APS) powered ascent is divided into two phases. Thefirst phase is a vertical rise which is required to achieve terrain clearance, and the

EVENT1. LIFTOFF2. INSERTION3. CSI4. PLANE CHANGE5. CDH6. TPI7. BEGIN BRAKJNG*8. STATION KEEPING9. DOCKING

I

,....=...=....Rendezvous radar tracking--a---=MSFN tracking * A TOTAL OF 4 BRAKING MANEUVERS RE PLANNED.

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.

second phase is orbit insertion. After orbit insertion the LM will execute the coellipticrendezvous sequence which nominally consists of four major maneuvers: concentricsequence initiation (CSI), constant de lta height (CDH), terminal phase initiation(TPI), and terminal phase finalization (TPF). A nominally zero plane change maneuverwill be scheduled between CSI and CDH, and two nominally zero midcourse correctionmaneuvers will be scheduled between TPI and TPF; the TPF maneuver is actuallydivided into several braking maneuvers. All maneuvers after orbit insertion will beperformed with the LM RCS . 0 nce docked to the CSM, the two crewmen will transferto the CSM with equipment, lunar samples, Surveyor Ill parts, and exposed film.Decontamination operations will be perform ed, jettisonable items will be placed in theInterim Stowage Assembly and transferred to the LM, and the LM will be configuredfor deorbit and lunar impact.LM Ascent Stage DeorbitThe ascent stage will be deorbited for lunar surface impact near the newly deployedALSEP, rather than sent into solar orbit, to provide a known perturbation for theseismic experiment..(Figure 25). The CSM in a heads-up attitude will be separated

CSM

JETTISON (RADIAL)EARTH

LM ASCENT STAGE DEORBIT1O/29/69 Page 38

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radially from the ascent stage with a Service Module (SM) RCS retrograde burnapproximately 2 hours after docking to the CSM. Following the LM jettison maneuver,the CSM will perform a pitchdown maneuver. The LM deorbit maneuver will be aretrograde APS burn initiated by ground control and the LM will be targeted to impactthe lunar surface approximately 5 NM south of the Apollo 12 landing site. The ascentstage jettison, ignition, and impacted lunar surface area will be photographed fromthe CSM.CSM Orbit Operations

Photonraphv of Candidate Exoloration SitesAfter ascent stage deorbit the CSM will execute an orbital plane change forapproximately 11 hours of lunar reconnaissance photography. Stereoscopic andsequence photographs in high resolution will be taken of Descartes , Fra Mauro,Lalande, and other candidate sites, as feasible, prior to transearth injection.

Transearth Injection and CoastThe SPS will be used to inject the CSM onto the transearth trajectory. The return flightduration will be approximately 72 hours (based on a 14 November launch) and the returninclination ( to the earths equator) will not exceed 40 degrees. Midcourse correctionswill be made as required, using the MSFN for navigation.

Entry and RecoveryPrior to atmospheric entry, the CSM will maneuver to a heads-up attitude, theComm and Module (CM) will jettison the SM and orient to the entry attitude (headsdown, full lift). The nominal range from entry interface (El) at 400,000 feet altitudeto landing will be approximately 1250 NM. Earth landing will nominally be in thePacific Ocean at 16OS latitude and 165OW longitude (based on a 14 November launch)approximately 244.6 hours after liftoff. Immediate recovery is planned.QuarantineFollowing landing, the Apollo 12 crew will don the flight suits and face masks passedin to them through the spacecraft hatch by a recovery swimmer wearing standard scubagear. The flight suit/oral-nasal mask combination will be used in lieu of the integralBiological Isolation Garments (BIGS) used on Apollo 11. The BIGs will be availablefor use in case of an unexplained crew illness. The swimmer will swab the hatch andadjacent areas with a liquid decontamination agent. The crew will then be carried byhelicopter to the recovery ship where they will en ter a Mobile Quarantine Facility(MQF) and all b qu se uent crew quarantine procedures will be the same as for theApollo 11 Mission.

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The spacecraft will be returned to port by the recovery ship where a team will deactivatepyrotechnics, and flush and drain fluid systems (except water). This operation will beconfined to the exterior of the spacecraft. The spacecraft will then be flown to theLunar Receiving Laboratory (LRL) and placed in a special room for storage. Lunarsample release from the LRL is contingent upon spacecraft sterilization. Contingencyplans call for sterilization and early release of the spacecraft if the situation so requires.Apollo 1 l/12 M ission Differences

. The major differences between the Apollo 11 and 12 flight missions are summarized inTable 5. TABLE5COMPARISONOF MAJORDIFFERENCESAPOLLOllvs. APOLLO12I EVENT I APOLLO 111. LAUNCH AZIMUTH

2. TRAJECTORY

3. EVASIVE MANEUVER4. NAVIGATION5. EVA6. EVA RADIUS (MAX)7. LUNAR SURFACE STAYTIME8. LUNAR ORBIT STAYTIME9. EXPERIMENTS

10. PHOTOGRAPHY

11. SLEEPING (LM)12. LUNAR SURFACE TV13. ASCENT STAGE14. TRANSEARTH FL IGHT15. TOTAL MISSION TIME

72 - 108

FREE-RETURN

CSM

1: (2 HR 32 MIN)250 FT21.6 HR59.6 HREASEP

BLACK & WHITEIN ORBIT59.4 HR195.3 HR

APOLLO 1272 - 96

HYBRID

S-IVB APSPROCEDURAL CHANGES2: (3 HR 30 MIN EACH)OPS PURGE CAPABILITY

~31.5 HRv89 HRALSEPMULTI-SPECTRAL TERRA IN500MM LENS LUNARLANDING SITESHAMMOCK ARRANGEMENTCOLORDEORBIT72.2 HR244.6 HR

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CONTINGENCY OPERATIONSGENERALIf an anomaly occurs a fter liftoff that would prevent the space vehicle from followingits nominal flight plan, an abort or an alternate mission will be initiated. Aborts willprovide for an acceptable flight crew and Command Module (CM) recovery whilealternate missions will attempt to maximize the accomplishment of mission objectivesas well as provide for an acceptable flight crew and CM recovery. Figure 26 showsthe Apollo 12 contingency options.ABORTSThe following sections present the abort procedures and descriptions in order of themission phase in which they could occur.

LaunchThere are six launch abort modes. The first three abort modes would result in terminationof the launch sequence and a CM landing in the launch abort area. The remainingthree abort modes are essentially alternate launch procedures and result in insertion ofthe Command/Service Module (CSM) into earth orbit. All of the launch abort modesare the same as those for the Apollo 11 Mission.Earth Parking OrbitA return to earth abort from earth parking orbit (EPO) will be performed by separatingthe CSM from the remainder of the space vehicle and performing a retrograde ServicePropulsion System (SPS) burn to effect entry. Should the SPS be inoperable, theService Module Reaction Control System (SM RCS) will be used to perform the deorbitburn. After CM/SM separation and entry, the crew will fly a guided entry to a pre-selected target point, if available.Translunar InjectionTranslunar injection (TLI) will be continued to nominal cutoff, whenever possible, inorder for the crew to perform malfunction analysis and determine the necessity of anabort.Translunar CoastIf ground control and the spacecraft crew determine that an abort situation exists,differential velocity (AV) targeting will be voiced to the crew or an onboard abort pro-gram wil I be used as required. In most cases, the Lunar Module (LM) will be jettisonedprior to the abort maneuver if a direct return is required. An SPS burn will be

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initiated to achieve a direct return to a landing area. However, a real-time decisioncapability will be exploited as necessary for a direct return or circumlunar trajectoryby use of the several CSM/LM propulsion systems in a docked configuration.For a nominal spacecraft trajectory, an abort at TLI plus 90 minutes will requireapproximately 5160 feet per second AV to return the spacecraft to a contingencylanding area.Lunar Orbit InsertionAn early shutdown of the SPS may result from a manual shutdown due to critical SPSproblems or from an inadvertent shutdown. If an inadvertent shutdown occurs earlyin the first lunar orbit insertion (LOI) b urn, an immediate restart of the SPS should beattempted provided specified performance limits are not exceeded. If restart of theSPS is not required, the LM Descent Propulsion System (DPS) will be the primary abortpropulsion system. The LM Ascent Propulsion System (APS) will be required to supplementthe DPS in order to meet the propulsion requirements of some abort conditions when ahybrid trajectory is used.

Mode I (LOl-1 ignition to 90 seconds): Initiate a DPS abort at 30 minutes after-ignition. If a satisfactory transearth coast is not achieved because of DPSAV limitations, initiate an SPS burn 2.5 hours after LOI ignition. If the SPS isnot available, the APS should be used.

Mode II (90-i70 seconds after LOI- ignition): initiate a DPS first burn under-me Computer Complex (RTCC) control 2 hours after LOl-1 ignition.Initiate a DPS second burn after one revolution in an intermediate ellipse.Between 90 and 144 seconds after the LOI burn, the second DPS burn will befollowed by an APS burn to inject the spacecraft into the desired transearthtraiectory.Mode III (170 seconds to end of LOI): bitiate a DPS abort (RTCC) after one1ev0 utton.

Transearth lniectionAn SPS shutdown during transearth injection (TEI) may occur as the result of aninadvertent automatic shutdown. Manual shutdowns are not recommended. If anautomatic shutdown occurs, an immediate restart will be initiated. If immediatereignition of the SPS is not possible, the following aborts apply if the SPS problemscan be resolved.

Mode I (93 seconds to end of TEI burn): Initiate one SPS burn 2 hours after TEIignition. The preabort trajectory will be a hyperbola.

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Mode II (80 to 93 seconds into TEI burn): Two SPS burns are required. Initiatethe burn 2 hours after TEI ignition. The preabort trajectory will be a hyperbola,Mode III (TEI ignition to 80 seconds): Initiate one SPS burn after one or morerevolutions. The p reabort trajectory will be a stable ellipse.

ALTERNATE MISSION SUMMARYThe two general categories of alternate missions that can be performed during theApollo 12 Mission are (1) earth orbital, and (2) lunar. Both of these categories haveseveral variations which depend upon the nature o f the anomaly causing the alternatemission and the resulting systems status of the LM and CSM. A brief description ofthese alternate missions is contained in the following paragraphs.Earth Orbital Al ternate Missions

Contingency: No TLI or partial TLI.Alternate Mission: The first day in earth orbit w ill consist of extraction and crewentry of the LM, separation of the CSM and S-IVB maneuver, and performance ofa photographic mission in the CSM/LM docked configuration.During the second day, the LM will be deorbited for ocean impact and a CSM planechange along with a maneuver to achieve an elliptical orbit will be made. Thephotographic mission will continue during the third through the fifth day in orbit.If the photographic mission is complete by 100 hours Ground Elapsed Time (GET),the spacecraft will enter and land.

Lunar Orbit Al ternate MissionsContingency: Failure to eject LM from S-IVB.Alternate Mission: Perform landmark tracking and photographic mission with theCSM with special emphasis on obtaining photographs of the bootstrap sites of thenominal mission.The first activity day in lunar orbit will consist of LOI-1, LOI-2, landmarktracking, and high resolution and vertical stereo photography followed by a6-hour sleep cycle.

The second activity day will consist of two plane changes with landmark tracking,vertical stereo photography, and high resolution photography of selected sciencesites followed by a IO-hour sleep cycle.


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The third activity day will consist of one plane change, landmark tracking,vertical stereo photography, high resolution photography of selected sciencesites, and S-158 strip photography for two revolutions.TEI will then be performed and the nominal mission timeline will be reentered.Contingency: DPS No-Go for burn (DPS is only failure).Alternate Mission: The Commander and Lunar Module Pilot will return to theCSM and the LM will be jettisoned. A CSM plane change will be initiated atapproximately 116 hours GET which will move the line of nodes backward allowingphotographic and landmark tracking of Apollo science sites. During the CSMcoast in this orbit, the crew will obtain coverage of eight sites. TEl will beperformed on the 41st revolution.

Contingency: LM No-Go for undocking (system failure, not connected with DPS,is discovered during LM checkout).Alternate Mission: A DPS plane change wil I be performed. The LM will bejettisoned and landmark tracking and photography of the Apollo science sites willbe started. A plane change by the CSM will be initiated at approximately 136hours GET which will move the line of nodes westward and will allow additionalphotographic and landmark tracking. This alternate mission will cover ten sitesand TEI will be performed on the 40th revolution.

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MISSION SUPPORTGENERALMission support is provided by the Launch Control Center (LCC), the Mission ControlCenter (MCC), the Manned Space Flight Network (MSFN), and the recovery forces.The LCC is essentially concerned with prelaunch checkout, countdown, and withlaunching the SV; while the MCC, located at Houston, Texas, provides centralizedmission control from tower clear through recovery. The MCC functions within theframework of a Communications, Command, and Telemetry System (CCATS); Real-TimeComputer Complex (RTCC); Voice Communications System; Display/Control System;and a Mission Operations Control Room (MOCR) supported by Staff Support Rooms(SSRs). These systems allow the flight control personnel to remain in contact with thespacecraft, receive telemetry and operational data which can be processed by theCCATS and RTCC for verification of a safe mission, or compute alternatives. TheMOCR and SSR's are staffed with specialists in all aspects of the mission who providethe Mission Director and Flight Director with real-time evaluation of mission progress.MANNED SPACE FLIGHT NETWORKThe MSFN is a worldwide communications and tracking network which is controlledby the MCC during Apollo missions (Table 6). The network is composed of fixedstations (Figure 27) and is supplemented by mobile stations. Figure 28 depictscommunications during lunar surface operations.The functions of these stations are to provide tracking, telemetry, updata, and voicecommunications both on an uplink to the spacecraft and on a downlink to the MCC.Connection between these many MSFN stations and the MCC is provided by NASACommunications Network. More detail on mission support is in the MOR Supplement.

Page 461O/2 9/69

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ACNANTARIA(4)ASCAOCCBDACNVCR0CYIGBIGDSGDS-XGTKGWMGYMHAWHSKHSK-XMADMAD-XMARSMILMLAPATTEXVANPARKES

TABLE6NETWORKCONFIGURATIONORAPOLLO12MlSSION

TRACKING T fi8a3 8i:?

X

X

XXX

x xX

-2X

XXX

Xxx-Xx x

X

X-x!t x

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x xxx

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xcxxXXXX-XXx xK xx-xx

xxIixxX

I DATAPRO-

1. TLI and reentq2i Post TLI coverage

X x x x INOTE 3

3. Lunar surface operations only

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RECOVERY SUPPORTGENERALThe Apollo 12 flight crew and Command Module (CM) will be recovered as soon aspossible after landing, while observing the constraints required to maintain biologicalisolation of the flight crew, CM, and materials removed from the CM. After locatingthe CM, first consideration will be given to determining the condition of the astronautsand to providing first-level medical aid when required. Unlike previous spacecraft,the Apollo 12 CM wil I not deploy the sea dye into the water after landing. The seadye container and swimmer interphone connector are permanently attached to theupper deck o f the CM. If a sea dye marker is requested by the recovery forces, theflight crew will deploy a tethered container of dye through the side hatch of the CM.The container will emit a yellow-green streak in the wake o f the CM for approximately1 hour. The crew has two markers that may be deployed. If the Apollo swimmer radiofails and it becomes necessary to use the interphone to communicate with the crew,the swimmer will have to climb to the top of the CM to reach the interphone connector.The second consideration wil I be recovery of the astronauts and CM. Retrieval of theCM main parachutes, apex cover, and drogue parachutes, in that order, is highlydesirable if feasible and practical. Special clothing, procedures, and the MobileQuarantine Facility (MQF) will be used to provide biological isolation of the astro-nauts and CM. The lunar sample rocks will also be isolated for return to the MannedSpacecraft Center.PRIMARY LANDING AREAThe primary landing area, shown in Figure 29, is that area in which the CM will landfollowing circumlunar or lunar orbital trajectories that are targeted to the mid-Pacificrecovery I i ne . The target po int will normally be 1250 nautical miles (NM) downrangeof the entry point (400,000 feet altitude). If the entry range is increased to avoid badweather, the area moves along with the target point and contains all the high probabilitylanding points as long as the entry range does not exceed 2000 NM.Recovery forces assigned to the primary landing area are:

0 The USS HORNET will be on station at the end-of-mission target point.

0 Four SARAH-equipped helicopters, two carrying swimmer teams to conductelectronic search, will be provided. At least one of the swimmers on eachteam will be equipped with an underwater (Calypso) 35mm camera. Stationassignments for these helicopters are:

0 One helicopter will be stationed 10 NM uprange from the target pointand 15 NM north of the CM ground track.

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0 One helicopter will be stationed 10 NM downrange from the target pointand 15 NM north of the CM ground track.

0 One helicopter will be provided for astronaut recovery in the viethe USS HORNET.

inity of

0 One helicopter carrying photographers as designated by the NAS ARecovery Team Leader will be stationed in the vicinity of the USSHORNET.

One aircraft will fly overhead of the primary recovery ship to functionas on-scene commander.

One aircraft will be on station in the vicinity of the USS HORNET to functionas on-scene relay o f the recovery commentary.

Two HC-130 aircraft, each with operational AN/ARD-17 (Cook Tracker),three-man pararescue team, and complete Apollo recovery equipmen t, willbe stationed 100 NM north of the CM ground track. One will be stationed165 NM uprange, the other 165 NM downrange from the target point.Prior to CM entry, two EC-135 Apollo Range Instrumentation Aircraft willbe on station near the primary landing area for network support.

The recovery forces will provide the following access and retrieval times:

0 A maximum access time of 2 hours to any point in the area.

0 A maximum crew retrieval time o f 16 hours to any point in the area.

0 A maximum CM retrieval time of 24 hours to any.point in the area.Recovery forces will also be provided for support of the launch abort landing area, thesecondary landing area, and the contingency landing area. The secondary landingarea and the contingency landing area would be used for landing from the earth parkingorbit and following aborts during the deep space phase of the mission.

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Lunar Module (LM-6) (Descent Stage)

0 Reduced landing gear and plume Reduces vehicle weight by approximatelydeflector thermal insulation. 3.6 lb.

0 Modified extravehicular activity Provides for current mission requirements.(EVA) equipment stowage.

0 Replaced Early Apollo Scientific Provides for current mission requirements.Experiments Package (EASEP) withApollo Lunar Surface ExperimentsPackage (ALSEP)/RadioisotopeThermoelectric Generator (RTG).

Spacecraft-LM Adapter (SLA-15). (No significant differences.)LAUNCH VEHICLE

Instrument Unit (S-IU-507)

0 Added underwater location devices. Increases recovery potential.S-IVB Stage (SA-507)

a Changed the telemetry system for Provides for 12 acoustic and 3 vibrationthe S-IVB stage of vehicle SA-507 measurements to S-IVB 507 which necessitatesto consist of one SSB/FM link and the use of a Saturn MSFC-designed singleone PCM/DDAS link - SA-506 sideband/FM system similar to those usedconsisted of one PCM/DDAS link. on research and development flights.

S-II Stage (S-11-507)l (No significant differences.)S-IC Stage (SA-507)l (No significant differences.)

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MANNED SPACE FLIGHT NETWORKC-Band Radar

a Deleted PAFB, GBI, GTI, ANT, Eliminates unnecessary duplication ofASC, PR E, TAN, HAW, CAL. unified S-band.

Unified S-Band

l Deleted GBM, ANG.

0 Added pulse modu lation capabilityto PARKES.

0 Added capability to handle LMcolor TV.

VHF Telemetry

0 Deleted GBM, ANG, TAN.

A/G Voice (VHF)

0 Deleted GBM, ANG, CAL (GDSbeing added), TAN.

Instrumenta tion Ships and Aircraft

0 Deleted USNS REDSTONE,MERCURY, and HUNTSVILLE.

0 Deleted four Apollo RangeInstrumentation Aircraft.

Eliminates unnecessary coverage beyond96O launch azimuth.Required to support LM descent.

Provides for color TV transmission.

Eliminates unnecessary coverage beyond96O launch azimuth.

Eliminates unnecessary coverage beyond96 launch azimuth.

Eliminates unnecessary real-time coverageof translunar injection (TLI) and recovery.Eliminates unnecessary real-time coverageof TLI.

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FLIGHT CREWFLIGHT CREW ASSIGNMENTSPrime Crew (Figure 30)

Commander (CDR) - Charles Conrad, Jr. (Commander, USN)Command Module Pilot (CMP) - Richard F . Gordon, Jr. (Commander, USN)Lunar Module Pilot (LMP) - Al an L. Bean (Commander, USN)

Backup Crew (Figure 31)Commander (CDR) - David R. Scott (Colonel, USAF)Command Module Pilot (CMP) - Alfred Merrill Worden (Major, USAF)Lunar Module Pilot (LMP) - J ames Benson Irwin (Lieutenant Colonel, USAF)

The backup crew follows closely the training schedule for the prime crew and functionsin three significant categories. One, they receive nearly complete mission trainingwhich becomes a valuable foundation for later assignments as a prime crew. Two,should the prime crew become unavailable, they are prepared to fly as prime crew upuntil the last few weeks prior to launch. Three, they are fully informed assistants whohelp the prime crew organize the mission and check out the hardware.During the final weeks before launch, the flight hardware and software, ground hard-ware and software, and flight crew and ground crews work as an integrated team toperform ground simulations and other tests of the upcoming mission. It is necessarythat the flight crew that will conduct the mission take part in these activities, whichare not repeated for the benefit of the backup crew. To do so would add an additionalcostly and time consuming period to the prelaunch schedule, which for a lunar missionwould require rescheduling for a later lunar launch window.PRIME CREW DATACommander

NAME: Charles Conrad, Jr. (Commander, USN)EDUCATION: Bachelor of Science degree in Aeronautical Engineering from

Princeton University in 1953; Honorary Master of Arts degree from PrincetonUniversity in 1966.

EXPERIENCE: Commander Conrad was selected as an astronaut by NASA inSeptember 1962.

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DAVID R. SCOTT ALFREDM. WORDEN JAMES B. IRWINCOMMANDER COMMANDMODULEPILOT LUNARMODULEPILOT


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In 1957, he attended the Navys Test Pilot School at Patuxent River, Maryland,and served as a flight test pilot until 1960. During this tour of duty he didflight test work on the F8U Crusader, Fll F Tigercat, FJ Fury, and A4DSkyhawk and was the first project test pilot for the F4H Phantom II.He served as a flight instructor in the F4H with Fighter Squadron 121 at theMiramar, California, Naval Air Station and was also flight safety officer,assistant operations officer, and ground training officer for Fighter Squadron 96at Miramar.He was also a student at the U.S. Naval Postgraduate School at Monterey,California.

Lunar Module PilotNAME: Alan L. Bean (Commander, USN)

EDUCATION: Bachelor of Science degree in Aeronautical Engineering from theUniversity of Texas in 1955.EXPERIENCE: Commander Bean was one of the third group of astronauts selected

by NASA in October 1963.APOLLO: Bean served as backup Lunar Module Pilot for the Apollo 9 Mission.GEMINI: Bean served as backup Command Pilot for the Gemini 10 Mission.OTHER: Bean, a Navy ROTC student at Texas, was commissioned in 1955upon graduation from the University. After completing his flight training, hewas assigned to Attack Squadron 44 at the Naval Air Station in Jacksonville,Florida, for 4 years. He then attended the Navy Test Pilot School atPatuxent River, Maryland, and was assigned as a test pilot at the Naval AirTest Center, Patuxent River. Commander Bean participated in the trials ofboth the A5A and the A4E iet attack airplanes. He then attended theAviation Safety School at the University of Southern California and was nextassigned to Attack Squadron 172 at Cecil Field, Florida.

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BACKUP CREW DATACommander

NAME: David R. Scott (Colonel, USAF)

EDUCATION:. Bachelor of Science degree from the United States MilitaryAcademy; degrees of Master of Science in Aeronautics and Astronautics andEngineer of Aeronautics and Astronautics from the Massachusetts Institute ofTechnology.

EXPERIENCE: Colonel Scott was one of the third group of astronauts selected byNASA in October 1963.APOLLO: Scott served as Command Module Pilot for Apollo 9, 3-13 March1969. The lo-day flight encompassed completion of the first comprehensiveearth-orbital qualification and verification tests of a fully configuredApollo spacecraft and provided vital information previously not availableon the operational performance, stability, and reliability of Lunar Modulepropulsion and life support systems.GEMINI: On 16 March 1966, h e and Command Pilot Neil Armstrong werelaunched into space on the Gemini 8 Mission - a flight originally scheduledto last 3 days but terminated early due to a malfunctioning spacecraft thruster.The crew performed the first successful docking of two vehicles in space anddemonstrated great piloting skill in overcoming the thruster problem andbringing the spacecraft to a safe landing.OTHER: Scott graduated fifth in a class of 633 at West Point and subsequentlychose an Air Force career. He completed pilot training at Webb Air ForceBase, Texas, in 1955 and then reported for gunnery training at Laughlin AirForce Base, Texas, and Luke Air Force Base, Arizona.He was assigned to the 32nd Tactical Fighter Squadron at Soesterberg AirBase (RNLAF), Netherlands, from April 1956 to July 1960. He then returnedto the U.S. and completed work on his masters degree at MIT. His thesis atMIT concerned interplanetary navigation.After completing his studies at MIT in June 1962, he attended the Air ForceExperimental Test Pilot School and then the Aerospace Research School.

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Command Module Pi lotNAME: Alfred Merrill Wo rden (Major, USAF)EDUCATION: Bachelor of Military Science from the United States Military

Academy in 1955; Master of Science degrees in Astronautical/AeronauticalEngineering and Instrumentation Engineering from the University of Michiganin 1963.

EXPERIENCE: Major Worden was one of the 19 astronauts named by NASA inApril 1966.APOLLO: Worden served as a member of the astronaut support crew for theApollo 9 Mission.OTHER: Major Worden received flight training at Moore Air Base, Texas;Laredo A ir Force Base, Texas; and Tyndall Air Force Base, Florida.Prior to his arrival for duty at the Manned Spacecraft Center, he served as aninstructor at the Aerospace Research Pilots Schoo l, from which he graduatedin 1965. He is also a graduate of the Empire Test Pilots School in Farnborough,England, and completed his training there in February 1965.He attended Randolph Air Force Base Instrument Pilots Instructor School in1963 and served as a Pilot and Armament Officer from March 1957 to May1961 with the 95th Fighter Interceptor Squadron at Andrews Air Force Base,Maryland.

Lunar Module PilotNAME: James Benson Irwin (Lieutenant Colonel, USAF)EDUCATION: Bachelor of Science degree in Naval Sciences from the United

States Naval Academy in 1951; Master of Science degrees in AeronauticalEngineering and instrumentation Engineering from the University of Michiganin 1957.

EXPERIENCE: Lt. Colonel Irwin was one of the 19 Astronauts selected by NASAin April 1966.

APOLLO: Irwin was crew Commander of Lunar Module LTA-8; this vehiclefinished the first series of thermal vacuum tests on 1 June 1968. He alsoserved as a member of the support crew for Apollo 10.

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OTHER: Irwin was commissioned in the Air Force on graduation from theNaval Academy in 1951 and received his flight training at Hondo Air Base,Texas, and Reese Air Force Base, Texas.He also served with the F-12 Test Force at Edwards Air Fo rce Base, California,and with the AIM 47 Project Office at Wright-Patterson Air Force Base, Ohio.

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MISSION MANAGEMENT RESPONSIBILITYTitle

Director, Apollo ProgramDirector, Mission OperationsSaturn Program ManagerApollo Spacecraft ProgramManagerApollo Program Manager KSCMission Director

Assistant Mission DirectorDirector of Launch OperationsDirector of Flight OperationsLaunch Operations ManagerFlight Directors

Spacecraft Commander (Prime)Spacecraft Commander (Backup)

Name OrganizationDr. Rocco A. Petrone NASA/OMS FMai. Gen. John D. Stevenson (Ret) NASA/OMSFMr. Roy E. Godfrey NASA/MS FCCol . James A. McDivitt NASA/MSC

Mr. Edward R. Mathews NASA,KSCCapt. Chester M. Lee (Ret) NASA/OMS FCol . Thomas H. McMullen NASA/OMSFMr. Walter J. Kapryan NASA/KSC

Dr. Christopher C. Kraft NASA/MSCMr. Paul C. Donnelly NASA/KSCMr. Gerald D. Griffin NASA/MSCMr. M. P. FrankMr. Glynn S. LunneyMr. Clifford E. CharlesworthCdr. Charles Conrad, Jr. NASA/MSCCol. David R. Scott NASA/MSC

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PROGRAM MANAGEMENT

NASA HEADQUARTERSOffice of Manned Space Flight

Manned Spacecraft CenterMarshall Space Flight Center

Kennedy Space Center

I ILAUNCH VEHICLE

Marshall Space Flight Center Manned SpacecraftThe Boeing Co. (S-IC) CenterNorth American Rot kwe I I North American

Corp. (S-l I) Rockwel I (LES,McDonne ll Douglas Corp. CSM, SLA)

(S-IVB) Grumman AerospaceIBM Corp. (IU) Corp. (LM)

SPACECRAFT TRACKING AND DATAACQUISITION

Kennedy Space CenterGoddard Space Flight CenterDepartment of Defense

MSFN

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ACNA/GAGSALSEPANGANTAPSAPSARIAASASCBDABIGCALCCATSCDCDHCDRCMCMDCMPCNVCR0CSICSMCYIDDASDODDO1DPSDSKYEASEPEIEMUEPOESTETBEVAFMfpsFTFTPGBIGBMGDSGETGTIGTKGYM

M-932-69-12

ABBREVIATIONS AND ACRONYMSAscension IslandAir To GroundAbort Guidance SystemApollo Lunar Surface Experiments PackageAntigua Island (MSFN)Antigua Island (DOD)Ascent Propulsion System (LM)Auxiliary Propulsion System (S-IVB)Apollo Range Instrumentation AircraftApollo/SaturnAscension IslandBermudaBiological Isolation GarmentPoint Arguello, CaliforniaCommunications, Command, and Telemetry SystemCountdownConstant Delta HeightCommanderCommand ModuleCommandCommand Module PilotCape CanaveralCarnarvonConcentric Sequence InitiationCommand/Service ModuleGrand Canary IslandDigital Data Acquisition SystemDepartment of DefenseDescent Orbit InsertionDescent Propulsion SystemDisplay and Keyboard AssemblyEarly Apollo Scientific Experiments PackageEntry InterfaceExtravehicular Mobility UnitEarth Parking OrbitEastern Standard TimeEquipment Transfer BagExtravehicular ActivityFrequency ModulationFeet Per SecondFeetFull Throttle PositionGrand Bahama Island (USAF)Grand Bahama Island (NASA)Goldstone, CaliforniaGround Elapsed TimeGrand Turk Island (NASA)Grand Turk Island (DOD)Guaymas, Mexico

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HAWHRHTCIMUIUIVTKSCLCCLECLESLH2LiOHLMLMPLO1LOXLPOLRLRLLVmEDMAXMCCMCCMESAMHzMILMLAMINMOCRMORMQFMSCMSFCMSFNNASANASCOMNMOMSFOPSPAFBPATPCMPDIPGNCSPLSSPREPRN

Kauai, HawaiiHourHand Tool CarrierInertial Measurement UnitInstrument UnitIntravehicular TransferKennedy Space CenterLaunch Control CenterLunar Equipment ConveyorLaunch Escape SystemLiquid HydrogenLithium HydroxideLunar ModuleLunar Module PilotLunar Orbit InsertionLiquid OxygenLunar Parking OrbitLanding RadarLunar Receiving LaboratoryLaunch VehicleMeterMillimeterMadridMaximumMidcourse CorrectionMission Control CenterModularized Equipment Stowage AssemblyMegahertzMerritt Island (NASA)Merritt Island (DOD)MinuteMission Operations Control RoomMission Operations ReportMobile Quarantine FacilityManned Spacecraft CenterMarshall Space Flight CenterManned Space Flight NetworkNational Aeronautics and Space AdministrationNASA Communications NetworkNautical MileOffice of Manned Space FlightOxygen Purge SystemPatrick Air Force BasePatrick AFBPulse Code ModulationPowered Descent InitiationPrimary Guidance, Navigation, and Control SystemPortable Life Support SystemPretoriaPseudorandom Noise

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psi Pounds Per Square InchQUAD QuadrantRCS Reaction Control SystemRLS Radius Landing SiteRNLAF Royal Netherlands Air ForceRTCC Real-Time Computer ComplexRTG Radioisotope Thermoelectric Generators/c SpacecraftSEA Sun Elevation Angles-IC Saturn V First StageS-II Saturn V Second Stages-IVB Saturn V Third StageSLA Spacecraft-LM AdapterSM Service ModuleSPAN Solar Particle Alert NetworkSPS Service Propulsion SystemSRC Sample Return ContainerSSB Single Side BandSSR Staff Support Roomsv Space Vehicleswc Solar Wind CompositionTAN Tananarive, Malagasy RepublicTEI Transearth InjectionTEX Corpus Christi, TexasTFI Time From IgnitionTLM TelemetryTLI Translunar InjectionTPF Terminal Phase FinalizationTPI Terminal Phase InitiationTRAJ TrajectoryT-time Countdown Time (referenced to liftoff time)TTY TeletypeTV TelevisionUSB Unified S-bandUSN United States NavyUSAF United States Air ForceVAN VanguardVHF Very High FrequencyAV Differential Velocity

GPO 884 048

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Post LaunchMission Operation ReportNo. M-932-69-12

TO: A/Administrator 25 November 1969

FROM: MA/Apollo Program Director

SUBJECT: Apollo 12 (AS-507) Mission Post Launch Mission Operation Report # 1

The Apollo 12 Mission was successfully launched from the Kennedy Space Center onFriday, 14 November 1969 and was completed as planned, with recovery of the space-craft and crew in the Pacific Ocean recovery area on Monday, 24 November 1969.Initial review of the flight indicates that all mission objectives were attained. Furtherdetailed analysis of all data is continuing and appropriate refined results of the missionwill be reported in the Manned Space Flight Centers technical reports.Attached is the Mission Directors Summary Report for Apollo 12 which is hereby sub-mitted as Post Launch Mission Operation Report # 1. Also attached are the NASAOMSF Primary Mission Objectives for Apollo 12. I recommend that the Apollo 12Mission be adjudged as having achieved all the established Primary Objectives andbe considered a success.

z-d==Rocco PetroneAPPROVAL:

(GeorgeI E . MuellerAssociate Administrator forManned Space Flight


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NASA OMSF PRIMARY MISSION OBJECTIVES FOR APOLLO 12

PRIMARY OBJECTIVES

. Perform selenological inspection, survey, and sampling in a mare area.

. Deploy and activate an Apollo Lunar Surface Experiments Package (ALSEP).

. Develop techniques for a point landing capability.

. Develop mans capability to work in the lunar environment.

. Obtain photographs of candidate exploration sites.

-zL $ p&Rocco A. PetroneApollo Program Director F


RESULTS O F APOLLO 12 MISSIONBased upon a review of the assessed performance of Apollo 12, launched 14 November1969 and completed 24 November 1969, this mission is adjudged a success in accordancewith the objectives stated above.

LS?&Rocco A. PetroneApollo Program Director P


Date: 25 November 1969 Date: 25 November 1969

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IN REPLY REFER TO: MAO

NATIONAL AERONAUTICS AND SPACE ADMINISTRATIONWASHINGTON, D.C. 20546

25 November 1969

TO: DistributionFROM: MA/Apollo Mission DirectorSUBJECT: Mission Directors Summary Report, Apollo 12

INTRODUCTIONThe Apollo 12 Mission was planned as a lunar landing mission to: perform selenologicalinspection, survey, and sampling in a mare area; deploy and activate an Apollo LunarSurface Experiments Package (ALSEP); develop techniques for a point landing capability;develop mans capability to work in the lunar environment; and obtain photographs ofcandidate exploration sites. Flight crew members were: Commander (CDR), Cdr. CharlesConrad, Jr .; Command Module Pilot (CMP), Cdr. Richard F. Gordon, Jr.; Lunar ModulePilot (LMP), Cdr. Alan L. Bean. Significant detailed mission information is containedin Tables 1 through 11. Initial review of the flight indicates that all mission ob jectiveswere attained (Reference Table 1). Table 2 lists Apollo 12 mission ach ievements.PRELAUNCHAn unscheduled 6-hour hold occurred at T-17 hours (spacecraft cryogenic loading) inorder to replace Service Module (SM) liquid hydrogen tank No. 2 which had beenleaking. The weather conditions at launch were: peak ground w inds of 14 knots, lightrain showers, broken clouds at 800 feet, and overcast at 10,000 feet with tops at about21,000 feet.LAUNCH AND EARTH PARKING ORBIT

The Apollo 12 space vehicle was successfully launched on schedule from Kennedy SpaceCenter, Florida, at 11:22 a.m. EST on 14 November 1969. All launch vehicle stagesperformed satisfactorily, inserting the S-lVB/IU/LM/CSM combination into an earthparking orbit with an apogee of 102.5 nautical miles (NM) and a perigee of 99.9 NM(103 NM circular planned). All launch vehicle systems operated satisfactorily exceptfor two minor off-nominal conditions which were noted in the launch vehicle digitalcomputer. During the ascent (36.5 to 52 seconds ground elapsed time (GET)) a number

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of spacecraft electrical transients also occurred. The tentative conclusion is that thecause of these events was an electrical potential discharge from the clouds through thespace vehicle to the ground.After orbital insertion, launch vehicle and spacecraft systems were verified, preparationswere made for translunar injection (TLI) as planned, and the second S-IVB burn wasinitiated on schedule (Reference Tables 3, 4, and 5). All major systems operatedsatisfactorily and all end conditions were nominal for a free-return circumlunar tra-jectory. The prelaunch planned height of closest approach of the spacecraft after theTLI maneuver was 1851 NM prior to the second midcourse correction, MCC-2 , as shownin Table 5. The actual height of closest approach, after TLI and prior to MCC-2 , wasestimated to be 457 NM, the spacecraft still being injected on CI free-return trajectory.This difference appears to be due to a state vector error in the Saturn Instrument Unit (IU).The error was known before TLI, but because of time limitations, the decision was madeto ignore it and not change the TLI targeting.TRANSLUNAR COASTThe Command/Service Module (CSM) separated from the LM/IU/S-IVB at about 3:18(hr:min) GET. Onboard television was initiated shortly thereafter and clearly showeddocking with the Lunar Module (LM) at 3:27 GET. Ejection of the CSM/LM wassuccessfully accomplished at about 4:14 GET and an S-IVB Auxiliary PropulsionSystem (APS) evasive maneuver was performed (and observed on television) at 4:27GET. All launch vehicle safing activities were performed as scheduled.

The S-IVB slingshot maneuver was initiated on schedule. The total APS burn time was570 seconds of which 270 seconds were due to a commanded burn. Due to the same IUstate vector errors that affected the TLI result, the slingshot maneuver did not achieve

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