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-" NATIONAL AERONAUTICS AND SPACE ADMINISTRATION _4
::::: APOLLO 14 (JAN 31 1971)::::::::::::::::::::::: !.:.:.:.:.:°:.:.:.:.:.:.
iii!!ii!iiiiiiiiiiiiiii"'""'"'"'"'"'"'" AS 509/C5M ll0/LM 8::::::::::::::::::::::: - - -•°o- .o. -°o°-°..o.°°°-o- °°, -.oo°,°.°...°..--o°o.°° °°°°°°o.o°,.°°...o°....°°.°.....°.°..o°°.o...-.-.-.,,-.,.-
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:_ :::::::::::::::::::::::..,ooo. .... ,,°.°.,°.°o...
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iiiiiiiiiiiiiiiii;;iiiiFLIGHT PLANiiiiiiiiiiiiiiiiiiiiiii:::::::::::::::::::::::
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• °.°°.- • • .o-°,°..-°.°°. ,°°°. ,.°..-°°.°.,
":':'::'::':':':':':"":':':':':':':':':':':"
i!iii??iiii!iiiii!?!iii PREPARED BY
::::::::::::::::::::::::::::::::::: FLIGHT CREW SUPPORT DIVISION• ,.°. - • -.-o-.-.-.
_, 2_ MANNED SPACECRAFT CENTERHOUSTON.TEXAS
'° CHANGED..°
-...-.-...°.%,°.°°..°,°.,.. °.° °°. -°-...,
i:i:!:i:!:!:!:!:!:!:!:!_N_×_,_,_T^ _-JANUARY 18, 1971 :_:::::::::::::::::::::::DATE @?R # T NM SUP_JECT StGNATOR LOC__""""'"'"""'"'" ct /_ 7/ _ ._ _ /!_9 ( _,_ _ _5__ _>79_._.
00001-HSI-209261
APOLLO14
(January 31, 1971)
FLIGHT PLAN
January 18, 1971
C. L. STOUGHBOOKMANAGER
APPROVEDBY: "_--'
J- IO'NEILL,CHIEFFLIGRT PLANNINGBRANCHFLIGHT CREW SUPPORTDIVISION
It is requestedthat any organizationhaving comments,questions,or suggestionsconcerningthis documentcontactC. L. Stough,Flight PlanningBranch,CF62,Building4, room 231, telephone483-4271.
This documentis under the configurationcontrol ofthe Crew Procedures Control Board (CPCB). All pro-posed changes should be submitted to the Apollo FlightData File Manager T. W. Holloway, CF62, Building 4,room 230, telephone483-4271.
Distributionof this documentis controlledbyW. J. North, Chief, FlightCrew Support Division.
00003-HSI-209261
FLIGHT DATA FILE PENAND INK CHANGES
The enclosed pen and ink changes are included with change B to theApollo 14 Flight Plan dated 1/11/71. The list of effective pages forchange B reflect these pen and ink changes.
/
_. Page 1-16: Under CST and GETfor Friday 5, FEB. Change"8:20 AM" to 8:06 AM" and "113:40" to "113:43".
./ 2. Page 1-16: Under CST and GET for Saturday 6, FEB. Change"3:59AM" to "3:56 AM" and "133:31" to "133:33".
j 3. Page 3-78: Change CSMIMU roll angle for LOI +2 hr DPSabortfrom "301" to "121"
/
_v/4. Page 3-78: Change LM FDAI angles for LOI +2 hr DPSabortfrom "10,81,1" to "170,261,359".
/
L/_55. Page At bottom of page change edition from "FINAL (JAN)"3-79:
to "CHANGEB (JAN)" and Date from "DECEMBER2, 1970"to "JANUARYII, 1971".
' //_ Page In the Notes column under S-IVB LUNARIMPACTchange3-79:
"LONG33.250" to "LONG-33.250"./
\/7., Page 3-82: Change "AOS to LOS : 874 SEC" to "AOS TO LOS : 450 SEC"./
_-_. Page 3-86: At bottom of page change edition from "FINAL (JAN)" to"CHANGEB (JAN)" and Date from "DECEMBER2, 1970" to
/ "JANUARYII, 1971".//
/
_/9. Page 3-86: Delete "V48 (21111)(XIIII)" and "/21111_" at thebottom of the page. \XIIIIJ
i"
'_10. Page 3-87: At bottom of page change edition from "FINAL (JAN" to"CHANGEB (JAN)" and Date from "DECEMBER2, 1970" to"JANUARYII, 1971".
00004-HSI-209261
/'/
/
_i. Page 3-87: Change DAP LOAD STATUS at top of time column from
"21111" to "21101". "f21101_" at bottomDelete "V48 (21101)(XIIII)" and \XIIII)of page.
j,"/"
',_i2,---- Page 3-106: At bottom of page change edition from "CHANGEA (JAN)"L/ to "CHANGEB (JAN)" and date from "DECEMBER23, 1970"
to "JANUARYII, 1971".
Page 3-106: Under CSMLOWALTITUDE LANDMARKTRACKINGPROFILE change"AOS TO LOS : 72 SEC" to "AOS TO LOS : 52 SEC"
j/"
!_/q/4. Page 3-128: At bottom of page change edition from "CHANGEA (JAN)"to "CHANGEB (JAN)" and date from "DECEMBER23, 1970"to "JANUARYII, 1971".
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_5_ Page 3-128: At 111:58 add "TERMINATEWASTEWATERDUMP".
J_6. Page 3-136: At bottom of page change edition from "FINAL (JAN)" to"CHANGEB (JAN)" and date from "DECEMBER2, 1970" to
"JANUARYII, 1971"/
"_I/7. Page 3-136: At 114:32 in the time column change"(lOlOl)" "(lllOl)"(X1111) to (Xllll)
_48. Page 3-148: At bottom of page Change edition from "CHANGEA (JAN)"" to "CHANGEB (JAN)" and date from "DECEMBER23, 1970"to "JANUARYII, 1971"
//
_I_. Page 3-148:f_iI18:24 change "CM4/DC/80/VHBW-BRKT-IVL(f2.8/I/60,=)FR)" to "CM4/DC/80/VHBW-BRKT,IVL, PCMCABLE(f2.8,1/60,_) (51 FR)".
r 20. Page 3-214: At bottom of page change edition from "FINAL (JAN)" toL j/" "CHANGEB (JAN) and date from "DECEMBER2, 1970" to
"JANUARYII, 1971"
00005-HSI-209261
/J
/"
_Y._ Page 3-214: At 144:16, delete the following: "REMOVEDECOMTAMINATIONBAGS(A8) UNSTOWANDASSEMBLE:VACUUMCLEANER,PWRCABLE,HOSE, AND BAG (SIDE AI2, SIDE A8)
- CONNECTPWRCABLE (PNL 201)".
I//_2. Page 3-216: At 144:32, change "DECONTAMINATIONBAGS(A8, UI)" to"DECONTAMINATIONBAGS".
_23. Page 3-216: At bottom of change edition from "CHANGEA (JAN)"page
to "CHANGEB (JAN)" and date from "DECEMBER23, 1970"to "JANUARYII, 1971".
_/24. Page 3-225: At bottom of page change edition from "CHANGEA (JAN)"to "CHANGEB (JAN)" and date from "DECEMBER23, 1970"to "JANUARYII, 1971".
/
22_. Page 3-225: In the LM LUNARIMPACTBOXchange "LONG1929°W'' to"LONG19.27°W".
f
Page 3-225: In Notes column change "LAT 3.32°S '' to "LAT 3.04°S ''and "LONG23.38°W '' to "LONG24.64°W ''.
00006-HSI-209261
-- Flight Plan (January 31, 1971 Launch)Pen & Ink 1/18/71
Flight Data File Pen and Ink Changes
-- The enclosed pen and ink changes are included with change C to theApollo 14 Flight Plan dated 1/18/71. The list of effective pagesfor change C reflect these pen and ink changes.
I. Page 3-142: At bottom of page change edition from LI"Final (Jan)" to "Change C (Jan)" andDate from "December 2, 1970" to"January 18, 1971."
2. Page 3-142: At 116:50 change "(000,114,045) LHGA P -84, Y 356" to"(184,2-0-2,045_GA P 3, Y 229"
I
3. Page 3-196: At bottom of page change edition from i J"Change A (Jan)" to "Change C (Jan)"and date from "December 23, 1970" to"January 18, 1971"
4. Page 3-196: At 139:55 change /- "CM/EL/250/CEX (flI,I/250,_)(31FR)"
to "CM/EL/250/CEX (f8,1/250,_)(31FR)"J
J
5. Page 3-198: At bottom of page change edition from _/"Final (Jan)" to "Change C (Jan)" anddate from "December 2, 1970" to"January 18, 1971"
6. Page 3-198: At 140:06 change"Photo TGT 7, North (flI,I/250,_)" , 7to "Photo TGT 7, North (f8,1/250,_)"
7. Page 1-16: Delete TV show on Thursday 4, February7:23 pm CST.
8. Page 3-96: At bottom of page change edition from _i"CHANGEA (JAN)" to "CHANGEC (JAN)" anddate from "DECEMBER23, 1970" to s
"JANUARY 18, 1971" /L/
9. Page 3-96: At 100:58, delete TV callout "CM5/TV-AVG (f22)TV (GDS) I01:00 - 101:14"
I0. Page 3-98: At bottom of page change edition from
"CHANGEA (JAN)" to "CHANGEC (JAN)" and .j,-date from "DECEMBER23, 1970" to"JANUARY 18, 1971"
j=
II. Page 3-98: From I01:00 to 101:14 delete TV show j
NASA-- MSC--Coml . Houston, Texas
00007-HSI-209261
i
FLIGHT PLAN(January 31, 1971 Launch)
FINAL DATE 12/2/70CHANGE DATE 12/23/70CHANGE DATE 1/11/71CHANGE DATE 1/18/71
* INDICATES CURRENTCHANGE
PAGE NUMBER CHANGE DATE
*i thru iia ........ 1/18/71iii thru vi ....... 12/23/70vii thru xx ....... FINALl-I thru 1-15 ...... FINAL
"I-16 ........... 1/18/711-17 thru 1-27 ...... FINAL2-I thru 2-5 ....... FINAL3-I thru 3-8 ....... FINAL3-9 thru 3-14 ...... 12/23/703-15 thru 3-31 ...... FINAL3-32 ........... 12/23/703-33 thru 3-36 ...... FINAL3-37 ........... 12/23/703-38 thru 3-49 ...... FINAL3-50 ........... 12/23/703-51 ........... FINAL3-52 ........... 12/23/703-53 thru 3-76 ...... FINAL3-77 ........... 12/23/703-78 and 3-79 ..... I/ll/713-80 thru 3-81 ...... FINAL3-82 ........... I/ll/Tl3-83 thru 3-85 ...... FINAL
*3-86 ........... 1/18/713-87 ........... I/ll/713-88 thru 3-95 ...... FINAL*3-96 ........... 1/18/713-97 ........... FINAL*3-98 ........... 1/18/71
00008-HSl-209261
-IVNI-I"""E;O_-E;n._q%66L-EL£/BL/L...........86L-E;_IVNI-I...........L6L-E;
LL/SL/L...........96L-E;_IVNI_-I......C]6L-E;n,_qq.LBL-E;
OL/E;_I_L...........OOL-E;IVNI.:I......6LL-E;nJq:l.LLL-E;
OL/E;_/_L...........9LL-E;]VNI_...........SLL-E;
OL/E;g/gl...........IzLL-E;]VNI-I......E;LL-E;nJqq.SSL-E;
OLIE;gI_L...........IzSL-E;-IVNI3...........E;§L-E;
OL/E;_/_L...........gSL-E;IVNI_...........LSL-E;
OLIE;_/gL...........OSL-E;-IVNI_-I...........6_L-E;
LLILL/L...........917L-E;1VNI4...........LtzL-E;
OL/E;Z/_L...........9_L-E;-IVNI:I.......SlztnJqq.E;IzL-E;
LL/OL/L..........._IzL-E;_IVNI_......LIzL-E;pu_OIzL-E;
OL/E;_/ZL...........6E;L-E;-IVNI3......BE;L-E;pueLE;L-E;
LL/LL/L...........9E;L-E;OL/E;Z/_L"..........5E;L-E;
IVNI3......_E;L-E;pueE;E;L-E;OL/E;g/ZI............_E;L-E;
IVNI3......LE;L-E;nJq:_6_L-E;LL/LL/L...........B_L-E;
"IVNI3......LgL-E;pue9ZL-E;OL/E;g/gL...........SgL-E;
lVNIJ..........._gL-E;OL/E;glgL......E;gL-E;nJq:l.LgL-E;
IVNI_...........Ogl-£OZ/E;g/_l...........6LL-E;
]VNI_...........8LI-E;OZ/E;_/_l...........LIt-E;
]VNI_......9LL-E;nJq:TELL-E;OL/E;_/_L...........OLL-E;
IVNI3......60L-E;nJqcT/0L-E;LL/LL/L...........90L-E;IVNI3...........50L-E;
OLIE;glgL...........1/0L-E;"IVN[4......E;OL-E;nJq:_66-E;
(IN03)S39Vd3AII3343330J.SI-1
.L.L
00009-HSI-209261
iia
LIST OF EFFECTIVEPAGES(CONT)
3-204 ........... 1/11/713-205 ........... FINAL3-206 ........... 12/23/703-207 ........... FINAL3-208 ........... 12/23/703-209 and 3-210 ...... FINAL3-211 ........... 12/23/703-212 and 3-213 ...... FINAL3-214 ........... 1/11/713-21 5 ........... FINAL3-216 ........... 1/11/713-217 ........... 12/23/703-218 ........... 1/11/713-219 ........... FINAL3-220 thru 3-225 ...... 12/23/703-226 ........... FINAL3-227 thru 3-232 ...... 12/23/703-233 thru 3-239 ...... FINAL3-240 ........... 12/23/703-241 thru 3-243 ...... FINAL
*3-244 and 3-245 ...... 1/18/713-246 and 3-247 ...... FINAL
*3-248 ........... 1/18/713-249 thru 3-260 ...... FINAL3-261 ........... 12/23/703-262 thru 3-268 ...... FINAL3-269 and 3-270 ...... 12/23/703-271 ........... FINAL3-272 ........... 12/23/703-273 thru 3-280 ...... FINAL3-281 and 3-282 ...... 12/23/703-283 thru 3-288 ...... FINAL4-I thru 4-4 ........ 1/11/714-5 thru 4-13 ....... 12/23/70
"4-14 ............ 1/18/714-15 ............ 12/23/70
"4-16 ............ 1/18/714-17 thru 4-32 ....... 12/23/705-I thru 5-18 ....... FINAL6-I and 6-2 ........ FINAL
00010-HSI-209261
iii
CONTENTS
Page
I. LIST OF TABLES .................... iv
2. LIST OF CHARTSAND GRAPHS .............. v
3. ABBREVIATIONS .................... vii
4. PHOTOGRAPHICNOMENCLATURE .............. xviii
5. SYMBOL NOMENCLATURE ................. xx
6. FLIGHTPLAN NOTES .................. l-l
7. MISSIONOBJECTIVES.................. 2-I
8. EARTH ORBIT PHASE .................. 3-I
9. TRANSLUNARINJECTION................. 3-5
lO. TRANSLUNARCOAST PHASE
a. Transposition,Docking,and Ejection ....... 3-6b. CislunarNavigation ............... 3-14,
3-29c. LM Familiarization................ 3-61d. Lunar Orbit Insertion .............. 3-79
II. LUNAR ORBIT/DESCENTPHASE
a. CandidateLandingSite Photos .......... 3-89b. LM Activationand Checkout ............ 3-99c. Undockingand Separation............. 3-I05d. Touchdown .................... 3-I19e. CandidateLandingSite Photos .......... 3-176
12. LUNAR SURFACEPHASE
a. First EVA .................... 3-133b. Second EVA .................... 3-183c. LM Lift-Off ................... 3-207
00011-HSI-209261
iv
CONTENTS (CONT)
Page
13. RENDEZVOUS/TEI
a. Docking ..................... 3-214b. LM Jettison ................... 3-222c. LM Impact .................... 3-225d. TransearthInjection............... 3-227
14. ENTRY INTERFACE ................... 3-288
15. CONSUMABLESANALYSIS ................. 4-I
16. ABBREVIATEDTIMELINE ................. 5-I
17. ALTERNATEMISSIONTIMELINES ............. 6-I
TABLES
Table Page _
l-l MSFN COVERAGE .................. 1-13
I-2 TV SCHEDULE ................... 1-16
I-3 FUEL CELL PURGE AND WATER DUMP SCHEDULE ..... 1-17
I-4 LiOH CANISTERCHANGESCHEDULE .......... 1-18
1-5 CSM BURN SCHEDULE ................ 1-19
I-6 LM BURN SCHEDULE ................. 1-20
I-7 BLOCK DATA SCHEDULE ............... 1-21
I-8 DSEA SCHEDULE .................. 1-22
I-9 BATTERYCHARGE SCHEDULE ............. 1-23
l-lO LANDMARKTRACKING ................ 1-24
l-ll P23 CISLUNARNAVIGATION ............. 1-25
1-12 MISSIONACTIVITYSUF_4ARY............. 1-27
2-I MISSIONOBJECTIVE/ACTIVITYREFERENCE....... 2-2 _
i i
00012-HSI-209261
V
TABLES (CONT)
Table Page
_ 3-I TLI BURN TABLE .................. 3-4
3-2 MCC-I BURN TABLE ................. 3-16
3-3 MCC-2 BURN TABLE ................. 3-31
3-4 MCC-3 BURN TABLE ................. 3-58
3-5 MCC-4 BURN TABLE ................. 3-72
3-6 LOI BURN TABLE AND ABORT CHART .......... 3-78
3-7 DOI BURN TABLE .................. 3-84
3-8 TEl BURN TABLE .................. 3-226
3-9 MCC-5 BURN TABLE ................ 3-242
3-I0 MCC-6 BURN TABLE ................. 3-266
3-11 MCC-7 BURN TABLE ................. 3-284
4-I APS PROPELLANTSUMMARY .............. 4-2
4-2 DPS PROPELLANTSUMMARY .............. 4-4
4-3 ASCENT STAGE EPS SUMMARY ............. 4-5
4-4 DESCENTSTAGE EPS SUF_MARY ............ 4-8
4-5 LM RCS PROPELLANTLOADINGAND USAGE SUMMARY . . . 4-II
4-6 LM ECS SUMMARY .................. 4-14
4-7 APOLLO 14 CRYOGENICSUMMARY ........... 4-20
- 4-8 APOLLO 14 SPS PROPELLANTSUMMARY4-24 ...... 4-24
4-9 SM RCS PROPELLANTLOADINGAND USAGE ....... 4-26
4-I0 CM RCS PROPELLANTSUMMARY ............ 4-32
00013-HSI-209261
vi
CHARTSANDGRAPHS
Figure Page
I-I LUNAREXPLORATIONCOMM- ONECREWMANEVA ..... I-II
I-2 LUNAREXPLORATIONCOMM- BOTHCREWMENEVA .... 1-12
3-I CSMLANDMARKTRACKINGPROFILE(60 X 170) ..... 3-82
3-2 LUNARORBIT RESTATTITUDE ............ 3-88
3-3 POST-TEl PHOTOSEQUENCE(TEl + 26) ........ 3-228
3-4 POST-TEl PHOTOSEQUENCE(TEl + 42) ........ 3-229
3-5 POST-TEl PHOTOSEQUENCE(TEl + 1:40) ....... 3-230
4-I LM-8 ASCENTSTAGEA-H REMAINING ......... 4-7
4-2 LM-8 DESCENTSTAGEA-H REMAINING......... 4-9
4-3 LM RCSPROPELLANTPROFILE ............ 4-12
4-4 ASCENTTANK1 02 REMAINING............ 4-15
4-5 DESCENTSTAGE02 REMAINING............ 4-16
4-6 ASCENTH20 REMAINING............... 4-17
4-7 DESCENTH20 REMAINING .............. 4-18
4-8 CSMOXYGENREMAINING............... 4-21
4-9 CSMHYDROGENREMAININGIN ONETANK ........ 4-22
4-10 TOTALSM RCSPROPELLANTUSAGEPROFILE ...... 4-27
4-11 SMRCSQUADA USAGEPROFILE ........... 4-28
4-12 SMRCSQUADB USAGEPROFILE ........... 4-29 _
4-13 SMRCSQUADC USAGEPROFILE ........... 4-30
4-14 SMRCSQUADD USAGEPROFILE ........... 4-31
i
00014-HSl-209261
vii
ABBREVIATIONS
ABB abbreviation or abbreviated,_ AC alternatingcurrent
ACCEL accelerometerACN AscensionACT activationACQ acquisitionor acquireAEA abort electronicsassemblyAGS abort guidancesubsystemAH ampere hoursALSCC Apollo lunar surfaceclose-up cameraALSD Apollo lunar surfacedrillALSEP Apollo lunar surfaceexperimentpackageALT altitudeAM amplitudemodulationAMP or amp amperesAMPL amplifierANG AntiguaANT antennaAOH Apollo OperationsHandbookAOL Atlantic Ocean lineAOS acquisitionof signalor acquisitionof siteAOT alignmentoptical telescopeAPS ascent propulsionsubsystemARIA Apollo range instrumentationaircraftARS atmosphererevitalizationsystemASC ascentA/T alignmenttechniqueATT attitudeAUX auxiliaryAZ azimuth
BAT batteryBEF blunt end forwardBD bandBDA BermudaBIOMED bio-medicaldataBP barber poleBRKT bracketBSLSS buddy secondarylife supportsystemBT burn timeBU backupBW black and white (Film 3400)BWD backwardBWI black and white (Film 3401)
00015-HSI-209261
viii
ABBREVIATIONS(CONT)
CAP COM capsulecommunicatorCALIB calibration ___CAM cameraCB circuitbreakerCCGE cold cathodegage experimentCCIG cold cathode ion gageCCW counterclockwiseCDH constantdelta altitudeCDR Commander
CDU couplingdata unitCEX color external (S0358)CIN color internal (S0168)CIRC circulationCK checkCKT circuitC/L centerlineor checklistCM commandmoduleCMC commandmodule computerCMD commandCMP CommandModule PilotCNTL controlC/O check outCOAS crew opticalalignmentsightCOMM communicationsCONFIG configurationCOMP compareCONT continue or contingencyCP control pointCPLEE charged particle lunar environment experimentCRO Carnarvon, AustraliaCRYO cryogenicCS contingency sampleCSC close-up stereo cameraCSl coelliptic sequence initiationCSM commandand service modulesCST central standard timeC/S central stationC&WS cautionand warningsystem _-CW clockwiseC_EA cautionand warning electronicsassemblyCYI Grand Canary Island
DAC data acquisitioncameraDAP digitalauto pilotDB deadbandDC direct currentor data camera (70mm) _
00016-HSl-209261
ix
ABBREVIATIONS(CONT)
DCA digital commandassemblyDEDA data entry and display assemblyDEG degreesDEPL depletionDES descentDET digital event timerDIFF differenceDIR directDK dockedDO detailed objectiveDOI descentorbit insertionDPS descentpropulsionsystemDRT dome removaltool
DS documentedsampleDSE data storageequipment(CSM)DSEA data storageequipmentassembly (LM)DSKY displayand keyboardDTO detailedtest objectiveDUA digitaluplink assemblyD_N down
E erasableor enterECS environmentalcontrolsystemED explosivedeviceEDT easterndaylighttimeEFH earth far horizonEI earth (atmosphere)interfaceand entry interfaceEKG electrocardiogramEL electric HasselbladcameraELEV elevation
EMER emergencyEMS entry monitor systemErIU extravehicular mobility unitENG engineENH earth near horizonENT entryE.O. earth orbit
_-_ EOM end of missionEPO earth parking orbitEPHEM EphemerisEPS electrical power subsystemEQUIP equipmentERECT erectableEST eastern standard time
_ ETB equipmenttransferbagEVA extravehicularactivity
00017-HSI-209261
ABBREVIATIONS(CONT)
EVAP evaporatorEVCS extravehicularcommunicationssystemEVT extravehiculartransfer IEXT external I
f f-stopFAM familiarizeor familiarizationFC fuel cell
FCS fecal containmentsystemFDAI flight directorattitudeindicatorFLT flightFM frequencymodulatedFOV field of viewFPS feet per secondfps frames per secondFR frame(s)FT or ft feetFTO flight test objectiveFTP full throttlepositionFTT fuel tranfertool -4FWD forward
G.A. gas analysisGA gimbal angleGBI Grand Bahama IslandsGBM Grand Bahama (MSFN)GDC gyro displaycouplerGDS Goldstone,CaliforniaGET ground elapsed timeGETI ground elapsed time of ignitionGETIL ground elapsed time of landingfor TIG time of abort burnGLY glycolGMT Greenwichmean timeG&N guidanceand navigationGNCS guidance,navigationand control system (CSM)GWM GuamGYM Guaymas,Mexico
H2 hydrogenHA apogee altitudeHAW HawaiiHBR high bit rate (TLM)HD highly desirableHFE heat flow experimentHGA high-gainantenna 4HI high (switchposition)
00018-HSl-209261
xi
ABBREVIATIONS(CONT)
HOR horizon
H20 waterHP perigeealtitudeHR hour(s)HSK Honeysuckle(Canberra,Australia)HTC hand tool carrierHTR heaterHTV USNS Huntsville
ICDU inertialcouplingdata unitID identificationIGA inner gimbal angleIGN ignitionI_ inertialmeasurementunitIND indicatorIHIT initializationINT intervalIP initialpointISA interimstowageassembly
IU instrumentationunitIVC intervehicularcommunicationsIVL IntervalometerIVT intravehiculartransfer
iR inclinationof the ascendingreturn
JETT jettison
KM kilometerkwh kilowatthour
LA launch azimuthLAT latitudeLBR low bit rate (TLM)LB or Ib pound(s)LCG liquid cooled garmentL/D lift/dragLD lunar day (TV lens)LDG landingLDMK landmarkLEB lower equipmentbayLEC lunar equipmentconveyorLEVA lunar extravehicularvisor assemblyLFH lunar far horizonLGC LM guidancecomputerLH left-handL/H local horizontal
00019-HSI-209261
xii
ABBREVIATIONS(CONT)
LHEB left-hand equipment bayLHFEB left-handforwardequipmentbayLHSSC left-handside storagecontainerLiOH lithiumhydroxideLLM lunar landingmissionLLOS landmarkline of sightLM lunar moduleLMP Lunar Module PilotLNH lunar near horizonL/O lift-offLOI lunar orbit insertionLONG longitudeLOS loss of signal or loss of siteLPD landingpoint designatorLPO lunar parkingorbitLPM lunar portablemagnetometerLR landingradarLRRR or LR3 laser rangingretro-reflectorL/S landingsite or lunar surfaceLSM lunar surfacemagnetometer _LT lightLTC lunar topographiccameraLTG lightingLV launch vehicleL/V local verticalLVPD launch vehiclepressuredisplay
M mandatoryMAD Madrid,SpainMAG magazine (camera)MAN manualMAX maximumMAXQ maximumdynamic pressureMBW medium black and white filmMCC midcourse correctionMCC-H Mission Control Center - HoustonMDC main display consoleMEAS measurement _,MESA modular experimentstowageassemblyMET mission event timerMGA middle gimbal angleM/I minimum impulseMIN minimum or minutes(s)MIR mirror
MLA Merrit Island,Florida,launch area _mmor MM millimeter
00020-HSI-209261
xiii
ABBREVIATIONS(CONT)
MNAor MNB main electrical bus A or BMNVR maneuverMON monitorMPL mid-Pacific lineMPS main propulsion systemM/R mixture ratio (fuel to oxidizer)MSFN Manned Space Flight NetworkMTVC manual thrust vector control
N2 nitrogenNAV navigationNM nautical milesNO, numberNOM nominalNXX Noun XX
02 oxygenOBS observation
___ O/F oxidizer to fuel ratioOGA outer gimbal angleOID octal identifierOMNI omnidirectional antennaOPR operateOPS oxygen purge systemOPT optionORB orbitalORDEAL orbit rate display earth and lunarORIENT orientationOVBD overboardOVHD overhead
P pitch or programPAD voice updatePCM pulse code modulationPC plane change or chamberpressurePDI powereddescentinitiation
f_ PER PericynthionPGA pressuregarmentassemblyPGNCS primaryguidance,navigationand control system (LM)PGNS primaryguidancenavigationsystem (LM)PHOTO photographPIPA pulse integratingpendulousaccelerometerPKG packagePLSS portablelife supportsystem
" PM phase modulatedPOL polarityor polarizing
00021-HSI-209261
xiv
ABBREVIATIONS(CONT)
PRE Pretoria, South AfricaPREF preferredPREP preparationPRESS pressurePRIM primaryPROP proportionalPRN pseudo random noisePRPLNT propellantPSE passive seismicexperimentPSIA pounds per square inch absolutePSID pounds per square inch differentialPSIG pounds per square inch gagePT pointPTC passivethermalcontrolPU propellantutilizationPUGS propellantutilizationgaging systemPWR powerPXX Program XXPYRO pyrotechnic
QTY quantityQUAD quadrant
R roll or rangeR&B red and blueRAD radiator,radial,or radiationRCDR recorderRCS reaction controlsystemRCU remote control unitRCV receiverREACQ reacquireREFS_AT referencestablemember matrixREG regulatorREQD requiredREV revolutionRH right-handRHC rotationalhand controller
RING ringsite ....RLS radius of landingsiteRNDZ rendezvousRNG range or rangingRR rendezvousradarRSI roll stabilityindicatorRSLV resolverRT realtimeRTC realtimecommand _._RTG radioisotopethermoelectricgeneratorRXX RoutineXX
00022-HSl-209261
XV
ABBREVIATIONS(CONT)
SA shaft angleSC spacecraftSCE signalconditioningequipmentSCS stabilizationcontrol systemSCT scanningtelescopeSE southeastor subearthSEC secondarySECO S-IVB engine cutoffSECS sequentialevents control systemSEF sharp end forwardSEL selectSEP separateSEQ sequenceSHUT shutterspeed,TOPO cameraSIDE suprathermalion detector experimentSII Saturn II (secondstage)S-IVB Saturn IVB(thirdstage)SLA servicemodule LM adapterSLOS star line-of-sightSM servicemoduleSPOT spot meterSPS servicepropulsionsystemSR sunriseSRC sample return containerSRX S-Band receivermode no. XSS sunset or subsolarSTBY standbySTX S-Band transmitmode no. XS.V. state vectorSW switch
SWC solar wind compositionSWE solar wind experimentSXT sextantSYS system
T EPHEM time of EphemerisupdateTA trunnionangle
_-- TAN Tananarive, MadagascarTB time base or talkbackTCA time of closest approachTD touchdownT&D transposition and dockingTD&E transposition docking and LM ejectionTDS thermaldegradationsampleTEC transearthcoastTECH technique
00023-HSI-209261
xvi
ABBREVIATIONS(CONT)
TEl transearth injectionTEMP temperatureTERM terminateTEX Corpus Christi,TexasTGT targetTHC translationhand controllerTIG time of ignitionTLC translunarcoastTLI translunarinjectionTLM or TM telemetryTPF terminalphase finalTPI terminalphase initiationTPM terminalphase midcourseT/R transmitter/receiverTRANS translationTRK track or trackingTRUN trunnionTV televisionTVC thrust vector controlTWR tower
UCTA urine collectiontransferassemblyUHT universalhand toolULC utilitylight clampULL ullageUHB umbilicalUNBAL unbalance(meter)UNDK undockUS UnitedStates
V velocity
VGIMU velocityto be gained as relatedto IMU orientationVGX velocityto be gained (X-bodyaxis)VGY velocityto be gained (Y-bodyaxis)VGZ velocityto be gained (Z-bodyaxis)VR resultantvelocityVX velocityalong the X-axisVY velocityalong the Y-azis -VZ velocityalong the Z-axisVAN USNS vanguardVHBW very high speed black and white filmVHF very high frequencyVLV valveVOX voice keyingVXX Verb XX
00024-HSl-209261
xvii
ABBREVIATIONS(CONT)
WRT with respectto
X time of closest approach (symbol)XDOT rate of change along the X-axisXFER transferXMIT transmitor transmitter
XPNDER transponder
Y yawYDOT rate of changealong the Y-axis
ZDOT rate of changealong the Z-axisZPN impedancepneumogram
AAz azimuthchange (difference)AH altitudechange (difference)AP pressurechange (difference)AR positionchange (difference)AV velocitychange (difference)AVC velocitychange at engine cutoffAVT velocity change loaded pre-burn
# frame number(s)(for camera data)
latitude
X longitude
00025-HSI-209261
xviii
PHOTOGRAPHICNOMENCLATURE
AAA/BBB/CCClDDD- EEE, EEE, (fGG, HHH, III) JJ fps or (JJ FR) (KK% MAG)
AAA - Locationfrom which photographyis to be accomplished
BBB - Camera
CCC - Lens (film type on LTC camera only)
DDD - Film Type (directionof flight of CM, i.e., SEF, BEF, for LTCcamera only)
EEE - Photographyaids (i.e.,brackets,intervalometer,mirror, etc.)
fGG - Lens ApertureSetting
HHH - ShutterSpeed
III- Focus Distancein Feet
JJ - Number of frames for DC, LTC, EL orJJ - Frame Rate for the DAC only _
KK - Hagazinepercentfor the DAC only
CODE EXAMPLE:
I. CM4/DAC/18/CEX-BRKT,SPOT (fGG,l/250,_)IZ fps (50% MAG)
Meaning:Photos are taken from CM right hand rendezvouswindow usingthe DAC with 18mm lens and S0368 film. The camera will bebracketmountedwith the followingcamera settings:f-stop from spotmeterreading,shutterspeed 1/250 ofa second,focus at infinity,12 frames per second,and50% of MAG to be used.
2. CM4/EL/80/BW-BRKT,IVL (f6.5,1/125,_)(I0 FR)
Meaning:Photos are taken from CM right hand rendezvouswindow usingthe ElectricHasselbladcamerawith the 80mm lens and black _& white film (3400). The camerawill be bracketmountedwith the followingsettingsf-stop (aperture)f6.5, shutterspeed 1/125, and focus at infinity. The operationof theshutterwill be controlledby the intervalometer. Ten frameshave been allotedfor this sequence.
00026-HSI-209261
xix
PHOTOGRAPHICNOMENCLATURE(CONT)
3. CM3/LTC/BW/SEF- SHUT-I/IO0,RNG - 74.2, INT 66.0) (164 FR)
Meaning:Photos are taken from the hatch window of the CM with theLunar Topographiccamera,with black and white film. TheSC is oriented such that the sharp end (+X axis) is forward(in the directionof flight)and the camera is mountedwiththe "arrow"pointingin the directionof flight. The con-trols are set for a shutterspeed of I/lO0 of a second,therange to the calculatedcountersettingof 74.2 and the in-tervalof 66.0 frames per minute. One hundredand sixty four(164) frames have been allotedfor this photographicsequence.
CAMERA LOCATIONS
COMMANDMODULE
CM-I LH Side WindowCM-2 LH RendezvousWindowCM-3 Hatch Window
i--- CM-4 RH RendezvousWindowCM-5 RH Side Window
LUNAR MODULE
LM-I LH WindowLM-2 DockingWindowLM-3 RH Window
CAMERAMOUNTS
CSM
CM4 - Electric Hasselblad (EL) +X axis +12°
CM4- Electric Hasselblad reseau (DC) +X axis +12°
CM4- Electric Hasselblad (EL) with 500mmlens only +X axis +I0 °
f- CM2 or 4 - Data AcquisitionCamerawith right angle mirror (DAC) +X axis
SXT - Data AcquisitionCamera with SXT Adapter - same as SXT shaft &trunnion
CM3 - Lunar TopographicCamera - (perpendicularto hatch window)+Xaxis +57°
CM3 - ElectricHasselblad(EL) +X axis +57°
CM3 - ElectricHasselblad(DC) +X axis +57°
00027-HSI-209261
XX
SYMBOLNOMENCLATURE
"LANDINGSITE (TCA)
M LUNARTERMINATOR
SPACECRAFTSUNSET
MSFNLOS
_START OF INDICATEDREVOLUTION
DARKNESS
-SPACECRAFTSUNRISE
LUNARTERMINATORMSFNAOS
" _SCHEDULED TELEVISION
SUBSOLARPOINT
B
00028-HSl-209261
SECTIONI - FLIGHT PLANNOTES
00029-HSI-209261
FLIGHT PLAN NOTES
I. Crew
A. Crew designationsare as follows:
Designation Prime BackupCommander(CDR) Shepard CernanCommandModule Pilot (CMP) Roosa EvansLunar Module Pilot (LMP) Mitchell Engle
B. The nominalCM couch positionsare:
Activity Left Center RightLaunch thru TLI CDR CMP LMPT&D thru Entry CMP CDR LMP
C. The PGA's will be worn as follows:
PRESSURIZED SUITED PARTIALSUIT SHIRTACTIVITY HARD SUIT (SOFT SUIT) WITHOUT SLEEVES
HELMET & GLOVES
LAUNCH ALL
EARTH ORBIT ALL_-_ THRU S-IVB
EVASIVEMNVR
TLC & TEC ALL
LM ACTIVATION ALL
UNDOCKING CDR & LMP CMPTHRU CIRC
CIRC TO TD CDR & LMP CMP
LUNAR STAY VARIES ACC(IRDINGTO CHECKLISTFOR CDR & LMP CMPEXCEPTEVA
SURFACE EVA CDR & LMP CMP
LIFT-OFFTHRU CDR & LMP CMPDOCKING
LM JETTISON ALLTHRU TEI
ENTRY ALL
l-l
00031-HSI-209261
D. Crew status reportswill be voiced to MCC-H beforeand after crewsleep periods. After waking, the crew will report sleep obtainedduring the last 24 hours and personaldosimeterreadings. Beforegoing to sleep, the crew will reportmedicationused and any otherpertinentinformationon activitiesperformed. Beforeascent prep,the LM crew will report personaldosimeterreadingsand medicationused.
E. Negative reportingwill be used in reportingcompletionof eachchecklist.
F. All onboardgauge readingswill be read directlyfrom the gaugeswith no calibrationbias applied.
II. CSM Systems
A. Communications
I. The preferredS-Band communicationmodes are:
l_I Uplink Mode 6 (Voice,PRN, and Updata)DownlinkMode 2 (Voice,PRN, TLM-HBR)
2. OMNI B and VHF LEFT will be selectedfor lift-off. OMNID will be selectedby the crew during boost. OMNI D will _probably be the best antennafor earth orbit.
3. VHF Duplex B will be used for launch, and SimplexA willbe used for earth-orbitoperations.
4. During TLC and TEC, OMNI antennaswill normallybe used.The CSM X-axiswill be pitchedup 90° (north)for TLC andpitcheddown 90° (south)for TEC with the Y&Z axes in theplane of the ecliptic. These attitudespermit high-gainantennacoverageand simultaneousviewingof the earth andmoon throughside windows.
5. MSFN relay will be used for LM/CSM communicationduringdescentand ascent frontsidepasses. Communicationsduringlunar stay periodswill be throughMCC-H.
6. Table l-l is a summaryof the MSFN coverageavailableforthe CSM.
7. Table I-2 contains a summaryof the scheduledCSM TV trans-missions.
I-2
00032-HSl-209261
8. During PTC, the OMNI antennaswill be switchedvia groundcommand. During periodsof attitudecontrolother thanPTC, the crew will manage antennaoperations.
B. DSE
I. The DSE will be normallyoperatedvia ground commandexceptfor specialcases where the operationis time-limited. Inthese cases, the crew may be asked to rewind the tape.
2. During the earth-orbitphase, the CSM LBR data will be re-corded when the CSM is not within MSFN coverage. The DSEwill be dumped during the pass over the US and over CROprior to TLI if possible.
3. CSM HBR DATA for stereo and LTC photographicstripsare re-quired for a minimum of 5 minutes at the beginningand atthe end of the strip. If HGA coverage is not available,these data will be recordedon the DSE.
4. During the lunar-orbitphase, the CSM LBR data will be re-corded when the CSM is not within MSFN coverage. The DSE
_-_ will normally be dumped at AOS.
5. CSM LBR data will be recordedduring all P24 landmarktracking.
6. CSM HBR will be recordedduring all CSM engine burns.
7. LM LBR data will be recordedduring LOS periodsbefore PDI.
8. All entry data will be recordedin HBR during the blackout.
9. All HGA activationswill be recordedon DSE.
C. ElectricalPower
I. The CSM will normallyremain poweredup throughoutthemission.
--- 2. Table I-3 lists the fuel cell purges and waste water dumps.
3. Based on cryo purity and performance,the time betweenfuel
cell 02 purges will be increasedto coincidewith water
dump times. The 02 purge at 6 hours will allow a judgementto be made on the defined purge schedule.
I-3
00033-HSl-209261
4. The cryogenicheaterswill be managed such that the planned
usage is obtainedout of each 02 tank. The H2 heaterswill
be in AUTO during the mission. The H2 fans will be operated
manually for one minute before and after each sleep cycle, -_prior to SPS or S-IVB thrustingand pre-CSM/LMejection.
5. Table I-9 containsthe batterycharge schedule.
D. ECS and Water Management
I. Potablewater will be chlorinatedonce a day after the eatperiod prior to each sleep period.
2. Waste water dump and fuel cell purge criteria:
(a) Waste water dumps and fuel cell purgeswill be scheduledas follows:
(1) Once during each 24 hours, if possible,followingtheinitialdump and purge
(2) H2 fuel cell purges will be scheduledat every other
02 fuel cell purge after the first 02 fuel cell purge
(b) The most opportunetime to performwaste water dumps andfuel cell purges are as follows:
(1) Immediatelyafter the sextantstar check in maneuverpreparationor cTslunar navigation
(2) Behind the moon, with completionof dump or purgebefore AOS
(c) If possible,dumps and purges will not be scheduledduringthe followingperiods:
(1) Ten hours before MCC-2 or a TLC P23
(2) Eight hours beforeMCC-5 or a TEC P23
(3) MSFN trackingperiodsduring two lunar orbits beforeTEl
I-4
00034-HSI-209261
(d) Dumps and purges will not be scheduled during thefollowing MSFN tracking periods:
(I) Ten hours before MCC-4 until after LOI
(2) Four hours before DOI until six hours after PDI
(3) Six hours before ascent from the lunar surface untilafter LM jettison
(4) Ten hours before MCC-7 until entry
(e) All waste water dumps will be manual.
3. Only one CO2 absorber filter (LiOH canister) is changedat a time. Table I-4 lists the LiOH canister change schedule.There are 20 filters on board, with 18 stowed at launch.
4. At lift-off, the cabin will contain 60% 02 and 40% N2. TheCM will be purged after launch. The purge is terminatedprior to LM pressurization after TLI. After the LM is con-
._- figured for ejection, it will be isolated and the CM willbe purged for eight more hours.
5. CSM 02 will be used to pressurize the LM after transpositionand docking; and repressurizing the LM before TLC LM entry,LOI and LM activation.
E. Guidance and Navigation
I. REFSMMATDefinitions
(a) The "Launch Pad" REFSMMATwill be used for launch, TLI,and TD&E. This REFSMMATplaces the IMU X-axis alongthe launch azimuth at the pad and the Z-axis along thenegative radius vector. The FDAI, at launch, will dis-play roll 162° (launch azimuth +90°), pitch 90° , andyaw 0° .
(b) The "PTC" REFSMMATwill be used for all midcourse maneu-vers (except MCC-7) and for other operations during TLC
I-5
00035-HSI-209261
and TEC. This REFSMMATplaces the X-axis in the eclipticplane and perpendicular to the earth-moon line projectionin the ecliptic plane at the average time of transearthinjection for the monthly launch window and azimuthrange. The Z-axis is then perpendicular to the eclipticand directed south. At the beginning of the PTC Mode,during TLC, the spacecraft will maneuver to an FDAIdisplay of pitch 90° . During TEC, the pitch attitudewiI1 be 270 ° .
(c) The "Landing Site" REFSMMATwill be used for LOI, DOI,PDI, landing, and CSM lunar orbit activities up to thefirst plane change. This REFSMMATplaces the CSM IMUX-axis along the positive lunar radius vector at thelanding site at the predicted landing time and placesthe Z-axis in the direction of flight parallel to theCSMorbital plane. At nominal touchdown, the LM FDAIwill display roll 0 °, pitch 0°, and yaw 0°.
(d) A "Preferred" REFSMMATwill be used by the CSMfor alllunar-orbit plane changes, and TEl. The CSM IMU X-axiswill normally be aligned with the spacecraft X-body axisat the vehicle attitude for ignition with the thrustdirected through the center of gravity. In the case _"of large plane change maneuvers, the IMU X-axis maybe aligned 45 ° from the spacecraft body axis at ig-nition attitude. The Z-axis will be in the planeformed by the X-axis and the position vector and di-rected up away from the moon for plane changes. Atburn ignition, the FDAI will display roll 0° (180 °for TEl), pitch 0°, and yaw 0°.
(e) The "Lift-Off" REFSMMATwill be used for all lunaractivities after plane change I, through rendezvous,and LM jettison. This REFSMMATplaces the CSM IMUX-axis along the positive lunar radius vector at thelanding site at predicted lift-off time, with theZ-axis parallel to the CSM orbital plane. At nominallift-off time, the LM FDAI will display roll 0°, pitch0 °, and yaw 0° with slight differences reflecting actual
touchdown yaw and slope tilt angles. ._
(f) The "Entry" REFSMMATaligns the IMU X-axis in the localhorizontal plane in the direction of flight at entry in-terface. The entry REFSMMATis used for MCC-7 and all
I-6
00036-HSl-209261
remainingactivities. The Z-axis is down along the ne-gative radius at entry interface. At entry interface,with wings level, local horizontal,heat shieldfor-ward, lift up, heads down, the FDAI will displayroll0°, pitch 180°, and yaw 0°.
2. The CSM externallightingwill be operatedduring the ren-dezvousfrom lift-offto docking. The runninglightsonlywill be on from CSM/LM separationto PDI.
3. The time tags on maneuversin Section3 indicatethe com-pletion time of the maneuversunless otherwisestated. Allmaneuverangles are the angles read on the FDAI after themaneuver has been completed.
4. CSM/LM and CSM attitudemaneuverswill normallybe at therate of O.2°/sec (O.5°/secafter rendezvousand docking)unlessother rates are required.
5. Undockingwill be done radially,CSM below, using the soft-undockingprocedure. The probe will be extendedits fulllengthwith the LM held on by the capturelatches. Whenthe rates are nulled,the CSM will then releasethe LM.
_-_ The separationmaneuverwill then be performedimmediately.
6. LM jettisonwill be done radially,CSM below, with jettisonprovidingapproximately0.4 foot per second thrust radial.The separationburn will be performedfive minutes afterjettison,providingone foot per second thrust retrograde.
F. PropulsionSystems
I. In order to conserveSM RCS, the SPS engine will be usedto "back-up"all LM rendezvousburns. The SPS gimbalmotors will not be turnedon during the normal maneuverpreparation.
2. The SPS will always be startedusing a single bank, how-ever, the other bank will be opened 2 to 5 secondsafterignitionfor burns longer than 6 seconds. The first en-glne Ignitionwill be startedon bank A.
3. Table I-5 lists the CSM propulsionburns.
I-7
00037-HSI-209261
IIl. LM Systems
A. Communications
I. The preferredS-Band communicationsare:(1) UplinkMode 7 (Voice,Updata)(2) DownlinkMode l (Voice,TLM-HBR)
2. The LM voice recorder (DSEA)will be used to record LMvoice. Table I-8 is a scheduleof LM voice recorderusage.
3. Figure l-l shows the communicationsmode for the firstpart of the EVA (CDR EVA only) and for the one-mancon-tingencyEVA. Figure I-2 shows the nominaltwo-manEVAcommunicationsconfiguration.
B. ECS
I. The LM will containambientair at lift-off. During
launch the pressurewill bleed to zero psia. CSM 02will be used to pressurizethe LM after T&D. AfterT&D, the LM will be isolatedand allowedto bleed downvia leakage. After the first LM egress,the LM will beisolatedand allowedto leak down. For the entry into
the LM before undocking,the CSM 02 will be used topressurizethe LM. This procedureinsuresa higher per-centageof oxygen in the LM at the first EVA.
2. LM 02 will be used to pressurizethe LM three times; after
EVA-I and EVA-2, and after equipmentjettison.
C. GuidanceSystems
I. The LGC and CMC will use the same landingsite and lift-off REFS_ATS.
2. The AGS will be placed in standbyafter the "GO" isgiven for lunar stay.
3. The RR will be powereddown after TD plus 2 hours untillift-offpreparation.
4. The IMU will be powereddown and the LGC placed in stand-by approximately3 hours and 25 minutes after TD untilafter the eat period followingsleep on the lunar surface.
I-8
00038-HSl-209261
5. To preventoverheatingof the antenna, the rendezvousradar will be pointedaway from the sun and will be turnedoff when no functionaluse is required.
D. PropulsionSystems
I. The APS/RCS interconnectwill be used during the lunarlift-offand ascent only.
2. Table I-6 lists the LM propulsionburns.
IV. Procedures
A. CSM - Crew procedurescalled out in the flight plan may be foundin the followingdocuments:
I. Apollo OperationsHandbook - CSM llO (AOH),Volume 22. Crew Checklists3. CSM RendezvousProcedures4. Photographicand TV Procedures5. Lunar LandmarkTracking AttitudeStudies6. Lunar Orbit AttitudeSequencefor MissionH-3
B. LM - Crew procedurescalled out in the flight plan may be foundin the followingdocuments:
I. Apollo OperationsHandbook LM-8, Volume 22. Crew Checklists3. LM RendezvousProcedures4. LM Descent/AscentProcedures5. Photographicand TV Procedures6. OrbitalEVA Procedures7. Lunar SurfaceProcedures
V. MedicalData Durin9 Sleep Periods
A. During translunarand transearthcoast phases,and in lunarorbit when all three crewmembersare in the CSM, an EKGand ZPN will be transmittedcontinuouslyfrom at least onecrewman.
B. Duringlunar orbit, when the CMP is the sole occupantofthe CSM, the CMP's EKG and ZPN will be transmittedto MCC-H.
C. While on the lunar surface,an EKG will be transmittedcon-tinuouslyfrom at least one crewman.
It-
I-9
00039-HSI-209261
VI. Sxnchronizationof Ground ElapsedTime (GET)
The realtimeGET will be synchronizedwith the flight planGET if the differenceis more than + l minute. The time changeswill occur approximately30 hours before the secondlunar or- 4bit, and prior to LOS on the tenth orbit. The time changeswill be based on the expecteddifferencebetweenrealtimeandflight plan GET's at the start of lunarorbit revs 2 and 20.The synchronizationis performedby a V70 uplink from theground followedby the crew synchronizingthe mission time tothe CMC clock.
VII. Miscellaneous
A. Table I-7 containsa summaryof the expectedblock data up-date times.
B. Table l-lO is the LandmarkTrackingTable.
C. Table l-ll is a scheduleof the P23 cislunar navigationsightings.
D. Table 1-12 is the MissionActivitySummary. __
l-lO
00040-HSl-209261
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00046-HS
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TABLE I-3
FUEL CELL PURGE AND WATER DUMP SCHEDULE
02 FUEL CELL PURGE H2 FUEL CELL PURGEAND WATER DUMP
GET, ATIME, ATIME,HR:MIN NUMBER HR:MIN NUMBER HR:MIN REMARKS
05:55 1 05:55 IF NOMCC-I
11:30 1 11:30 IF MCC-I PERFORMED
30:15 2 24:20/18:45 1 30:15 MCC-2
60:20 3 30:05 MCC-3
84:50 4 24:30 2 54:35 LOI+2HR
111:40 5 26:50 LOS MIDPOINT
139:20 6 27:40 3 54:30
166:00 7 26:40 MCC-5
193:10 8 27:10 53:50 IF NOMCC-6
194:10 8 28:10 4 54:50 IF MCC-6PERFORMED
216:12 23:02/22:02 CM/SMSEPARATION
'_ 1-17
00047-HSI-209261
f_
TABLE I-4
LiOH CANISTERCHANGESCHEDULE
CHANGE APPROXIMATE APPROXIMATE INSTALL REMOVE& STOWNO. GET, AT, CANISTER STOWAGE
HR:MIN HR CANISTER POSITION NO. LOCATION
1 12:00 3 A 1 B514
2 26:10 4 B 2 B512
3 38:00 5 A 3 B513
4 51:10 6 B 4 B513
5 64:12 7 A 5 B612
6 76:10 8 B 6 _B614
7 90:15 9 A 7 B6 --13
8 103:38 I0 B 8 B616
9 119:30 II A 9 A327
I0 147:05 12 B I0 A315
II 162:10 13 A II A312
12 174:00 14 B 12 A313
13 187:00 15 A 13 A412
14 199:00 16 B 14 A4II
15 210:00 17 A 15 A4
1-18
' 00048-HSI-209261
TABLE I-5
CSMBURN SCHEDULE
BURN GETI AVT, ULLAGE RESULTANTMNVR BURNTIME FPS AV,FPS REFSMMAT HA & HP REMARKS
02:30:38TLI 5 MIN 55.6 SEC 10353.1 PAD S-IVB BURN
CSM/LM 03:56EJECTION 3.u SEC 0.4 ......... PAD ......... ;RCS BURN
MCC-I 11:36:33 ................. PTC ......... NOMZERO
30:36:07MCC-2 11.08 SEC 73,40 NOT REQ'D PTC ......... SPS BURN
MCC-3 60:3_:14 ................. PTC ......... NOM ZERO
MCC-4 77:3u:14 ................. PTC ......... NOM ZERO
82:38:14 HA 170.00LOI 6 MIN:U6.6 SEC 2986.0 NOT REQ'D LDG SITE HP 57.14 SPS BURN
86:56:57 4 JET HA 58.44DOI 21.38 SEC 206.6 14.0 SEC LDG SITE HP 9.77 SPS BURN
BAILOUT 87:27:31 4 JETBURN 10.17 SEC I00.0 14.0 SEC LDG SITE SPS BURN
UNDOCK& 104:27:31 HA 59.48SEP 3.07 SEC 1.00 ......... LDG SITE HP 8.23 RCS BURN
CIRC 105:46:48 4 JET HA 63.51BURN 3.7_ SEC 72.46 II.0 SEC LDG SITE HP 56.04 SPS BURN
118:09:40 4 JET iPLANE HA 61.71PC-I 18.4 SEC 360.7U II,0 SEC CHANGE HP 57.41 SPS BURN
;SM SEP HA 58.26 3 AXISBURN 146:28:31 1.00 LIFT-OFF HP 60.24 RCS BURN
149:14:50 4 JETTEl 2 MIN 27.4 SEC 3449.55 12 SEC TEl ......... SPS BURN
f
MCC-5 166:14:50 ................. PTC ......... NOMZERO
MCC-6 194:26:59 ................. PTC ......... NOMZERO
MCC-7 213:26:59 ................. ENTRY ....................
NOTES: I. HA & HP ARE HEIGHTSABOVE LANDING SITE RADIUS (937.73488 NM).2, BURNTIME DOESNOT INCLUDE ULLAGE OR TAILOFF BT.
1-19
00049-HSI-209261
TABLE 1-6
LM BURNSCHEDULE
BURN GETI AVT, ULLAGE RESULTANT _MNVR BURNTIME FPS AV,FPS REFSMMAT HA & HP REMARKS
108:42:01 2 JETPDI II MIN 31.5 SEC 6637.7 7.5 SEC LDG SITE ......... DPS BURN
142:24:29 HA 50,96ASCENT 7 MIN 10.7 SEC 6053.4 NONE LIFT-OFF HP 9.14 APS BURN
143:09:40 2 JET HA 61.0TPI 4.0 SEC 92.2 13 SEC LIFT-OFF HP 44.6 APS BURN
LM 147:52:58.9DEORBIT 1 MIN 17 SEC 183.7 LIFT-OFF N/A RCS BURN
NOTES: HA & HP ARE HEIGHTS ABOVELANDING SITE RADIUS (937.73488 NM).21 BURNTIME DOESNOT INCLUDE ULLAGE OR TAILOFF BT.
1-20
00050-HSI-209261
TABLE I-7
FINAL APOLLO 14 RETURN TO EARTHBLOCK DATA SCHEDULE
PASSED DATA,GET, GETI, AV, GETIL, 1R, PAD TYPE
BLOCK DATA HR:MIN HR:MIN FPS HR:MIN DEG
TLI + 90 MIN 1:40 4:00 7488 12:12 32.8°D COMPLETE P3OL/O + 8 HR 1:40 8:00 3209 46:29 32.8°A P37L/O + 15 HR 6:00 15:00 5557 45:56 32.8°A P37L/O + 25 HR 14:00 25:00 4873 70:03 33.0 A P37L/O + 35 HR 14:00 35:00 7376 69:28 33.3 A P37L/O + 45 HR 14:00 45:00 5630 93:49 34.] A P37L/O + 60 HR ]4:00 60:00 5166 I17:53 36.9 A P37LOI-5 FLYBY 35:00 77:38 403 165:57 40.0 D COMPLETE P30(DOCKED)PC + 2 76:00 84:36 1519 141:42 30.1D ABB P30 (DOCKED)TEI 4 79:30 91:15 3955 141:47 40° A ABB P30TEI 5 85:05 92:30 3220 166:14 40° A ABB P30TEl 12 89:20 I05:54 3630 ]66:24 40° A ABB P30TEI 19 I00:45 I19:38 3326 19l:]3 40° A ABB P30TEI 34 (PRELIM) If5:00 149:15 3451 216:40 40° A COMPLETE P3OTEI 34 (NOM) 147:40 149:15 345] 216:40 40° A COMPLETE P3OTEI 35 147:40 151:14 3523 216:16 40° A ABB P30
NOTES:
I. The TLI + 90 minute abort is to the AOL. All other block data maneuvers are to theMPL line [Nominal TEI (REV 34) is to EOM @,_].
2. Lift-off + 15 hours abort assumes no MCC-I.3. Lift-off + 35 hours abort assumesMCC-2.4. Update flyby early if pericynthionis not clear of moon.5. Pericynthion+ 2 hours fast return to MPL assumes MCC-4.6. TEI 4 assumes LOI and no DOI.7. TEI 5 assumes DOI.8. TEI 12 assumes no circularizationmaneuver.9. TEl 19 assumes circularizationand no plane change maneuvers.lO. TEI 34 (PRELIM) assumes the plane change maneuver.
If. All TEI's are iR = 40° ascending returns.
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TABLE I-9
BATTERYCHARGESCHEDULE
GET,HR:MIN BATTERY
04:25 B
26:15 A
32:20 A
53:00 B
I06:15 B
112:30 A -q
132:20 B
136:15 A
:._ 166:18 B
186:25 A
1-23
00053-HSI-209261
TABLE I-I0
LANDMARKANDLANDINGSITE DATA
SITE REV LATITUDE LONGITUDE *ALTITUDE (NM)
MOSTINGA 2 3.250°S 5.283°W 000.00 _
H-3 3 3.691°S 7.542°W 000.00
14-I 12, 13, 15 4.046°S 15.600°W -000.4414-2 3.610°S 15.317°W -000.1514-3 3.919°S 15.139°W -000.3814-4 3.470°S 14.890°W -000.87
RP3 15 3.533°S 131.700°E 000.00RP5 15 I0.567°S 99.400°E 000.00DAGUERRE66 15 II.717°S 33.200°E 000.00
LDGSITE 17 3.672°S 17.463°W -000.76
RP2 18 0.283°S 141.250°E 000.0012-I 18 5.736°S I12.309°E 000.00DOLLONDE 18 I0.433°S 15.733°E 000.00FHI 18 3.246°S 17.317°W 000.00 --_
RP4 29 5.850°S 120.250°E 000.00ANSGARIUSN 29 II.633°S 81.067°E 000.00DE2 29 9.250°S 19.592°E 000.00ENKEE 29 0.283°N 40.300°W 000.00
*Difference between landmark radius vector and 938.4935 NM (meanlunar radius)
1-24
00054-HSl-209261
TABLE I-II
P23 CISLUNARNAVIGATION
GET STAR/HORIZON COMMONNAME
9:30 72/EFH GACRUX236/ENH DELTAOPHIUCHI53/EFH GAMMACENTAURI
202/ENH ZETAOPHIUCHI
28:30 202/ENH ZETAOPHIUCHI165/EFH ETA CENTAURI33/ENH ANTARES
172/EFH BETALIBRAE
164:00 40/ENH ALTAIR212/EFH DELTASAGITTARII33/EFH ANTARES35/EFH* RASALHAGUE
211/EFH* BETAOPHIUCHI
214/ENH* ZETA SAGITTARII
166:45 16/MFH PROCYON(TEl+f7.5) 50/MFH POLLUX
22/MNH REGULUS
167:15 40/ENH ALTAIR(TEI+I8) 212/EFH DELTASAGITTARII
33/EFH ANTARES
173:00 40/ENH ALTAIR(TEl+24) 212/EFH DELTASAGITTARII
33/EFH ANTARES35/EFH* RASALHAGUE
211/EFH* BETAOPHIUCHI42/ENH* PEACOCK
188:27 37/EFH NUNKI_- (EI-28) 33/EFH ANTARES
120/ENH AL NA'IR40/ENH* ALTAIR35/EFH* RASALHAGUE
211/EFH* BETAOPHIUCHI
*Constraint Stars
1-25
00055-HSI-209261
TABLE I-II
P23 CISLUNARNAVIGATION(CONT)
GET STAR/HORIZON COMMONNAME
192:27 37/EFH NUNKI(EI-24) 33/EFH ANTARES
120/ENH AL NA'IR
196:27 37/EFH NUNKI(EI-20) 33/EFH ANTARES
120/ENH AL NA'IR40/ENH* ALTAIR
211/EFH* BETAOPHIUCHI214/EFH* ZETA SAGITTARII
208:27 44/ENH ENIF(EI-8) 212/EFH DELTASAGITTARII
213/EFH LAMBDASAGITTARII45/ENH FOMALHAUT
211:27 22/MFH REGULUS(EI-5) 64/MNH ALHENA
23/MFH DENEBOLA151/MFH GAMMA-PRIMELEONIS16/MNH PROCYON
213:57 22/MFH REGULUS(EI-2.5) 23/MFH DENEBOLA
16/MNH PROCYON
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1-26
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00056-HSI-209261
0005
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61
SECTION2 - MISSION OBJECTIVES
00059-HSI-209261
SECTION 2
MISSION OBJECTIVES
This section contains an activity summary, reflecting the objectives
for Apollo 14 as described in "Mission Requirements H-3 Type Mission."
Table 2-I provides a functional breakdown of the objectives and in-
dicates the page(s) in the timeline where the activity occurs. The
alphanumeric listing presented in Table 2-I is not intended to repre-
sent a priority or a sequential listing.
Details of the implemented test requirements are adequately covered
in the Mission Requirements Document, the Lunar Surface Procedures Plan,
and the Photographic and TV and Procedures Document.
2-I
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I-209261
00356-H81-209261
SECTION 4 - CONSUMABLES
00357-HSI-209261
ASSUMPTIONSFOR THE APS ANALYSIS
Propellantloadingdata were obtainedfrom the Apollo 14 preflightdata and were optimizedfor the nominalmission. The LM-8 data wereused for engine performance,and AV requirementswere coordinatedwiththe Landing AnalysisBranch and the OrbitalMissionAnalysis Branch.The AV requirementfor the lunar ascent differs from that in the Opera-tionalTrajectoryand Flight Plan because of an increasein the inertvehicle weight.
The budget shown in table 4-I accounts for an APS TPI, engine valve-pair malfunction,and balanced couples. A touchdownabort was not con-sideredbecause the nominallift-offweight is heavierthan the abortweight. The followingdatawere used.
a. Isp = 309.97 _+3.77 seconds
b. Mixtureratio = 1.605 +_.0258
c. Lift-offweight = lO 841.5 _+38.7 pounds
4-I
00359-HSI-209261
TABLE 4-I
APS PROPELLANTSUMMARY
Item Total propellant,lb f-_
Loaded ................ 5224,8
Trapped and unavailable .... -51.8
Outage ............. -10.3
Availablefor AV ........ 5162.7
Requiredfor ascent (6057,7fps) -4931,I
Remaining ........... 231.6
Requiredfor APS TPIa (70.2 fps) -41.4
Remaining .............. 190.2
Dispersions(-3o) .......... -66.2 f_
Pad ................. 124.O
Contingencies
En_ine valve-pair malfunction(AMR = +.01 or -.018) ...... -24,5
Balancedcouples ........ -56.9
Half-degreeout of plane(18 fps) ............. -I0.6
Margin ............. 32.0
aThe total TPI AV Is 92.2 fps. It is assumedthat 22 fps isobtained by 10-sec, 4-jet ullage.
4-2
00360-HSI-209261
ASSUMPTIONSFOR THE DPS ANALYSIS
Propellantloadingdata were obtainedfrom the Apollo 14 preflightdata and were optimizedfor the nominalmission. The LM-8 data wereused for engine performance,and AV requirementswere coordinatedwiththe LandingAnalysis Branch. The AV requirementfor lunar descentdiffers from that in the Operationaltrajectoryand Flight Plan becauseof an increase in the inert vehicleweight.
The 3_ dispersionsrepresenttotal propellantcost based on 30
uncertaintiesin propellantloading,trappedpropellant,Isp, AV, sep-arationweight, non-AV consumablesweight, mixtureratio, and physicallocationof the low-levelsensor.
The followingphilosophychangeshave been included in the budget.
a. A flying time of 2 minutes and 20 secondsbelow low gate willbe called a nominal requirement.
f-_ b. A contingencyof 5 secondshas been included for a possibleearly low-levellight based on a GrummanAircraft Corporationpresenta-tion to a September17, 1970, meetingof the ConfigurationControlBoard.
c. The separationweight is 34 lOl.O ± 36.9 pounds.
d. Integratedaverage Isp is 302.5 ± 4.65 seconds.
e. Mixtureratio is 1.598 ± .0225.
f. Non-AV consumablesfrom separationto PDI are 83.2 pounds.
4-3
00361-HSI-209261
F-
TABLE 4-2
DPS PROPELLANTSUMMARY
Total HoverItem propelIant, time,
Ib sec
Loaded ................. 18 414.7 --
Trapped and unavailable ........ -213.1 --
Outage ................. -33.4 --
Availablefor AV ............ 18 168.2 --
Requiredfor AV (140-secflying timefrom low gate, AV = 6957.8) ..... -17 332.5 --
Remaining ............ . . . 835.7 90
Dispersions(-30) ........... -318.6 -- _.
Pad ................. 517.l 56
Operationalallowances
Low-level (5 sec, 26.5 fps) ..... -44.7 --
Abort reserve (20 sec, I06 fps) . . . -179.5 --
Margin (hovertime before abortdecision point) ........... 292.9 31
4-4
00362-HSI-209261
12/8/70 Final _
Ground Rules and Assumptions for the LM EPS Analysis
I. Energy available from the descent batteries is 1600 A-h and fromthe ascent batteries is 592 A-h.
2. Energy unusables caused by lack of continuous MSFN coverage forthe descent and ascent stages are 6 and 3 A-h, respectively.
3. Energy unusables caused by TM inaccuracies for the descent andascent stages were 77 and II A-h, respectively.
4. Energy unusables caused by checklist deviations (dispersion) forthe descent and ascent stages were 25 and 4 A-h, respectively. This dis-persion is obtained by calculating 2 percent of the energy used.
5. In accordance with the flight plan, the PGNCSwas in standby modefrom 1.3 hours following surface powerdown until 9.75 hours before powerup.
6. The RCS heaters were assumed to have a I00 percent duty cycle for15 minutes after initial activation and then to decrease to a 7 percent
duty cycle until undocking. From undocking until lunar landing plus2 hours, the heaters were assumed to cycle at 0 percent, but, from landingplus 2 hours until lunar lift-off, the duty cycle was assumed to be4.5 percent.
7. At the beginning of the analysis, it was assumed that a totalof I0 A-h had been used from the descent batteries between 30 minutesbefore launch and the conclusion of transposition and docking.
8. The CDR and LMP forward window heaters were assumed not to beneeded.
9. All floodlights were turned off at the beginning of EVA-I andon again at powerup.
I0. No duty cycle was assigned to the portable utility lights.
II. The liquid cooled garment pump was cycled as dictated by the timeline.
12. _he short (M=l) rendezvous was considered nominal.
13. The TV camera was assumed to be on from the beginning of EVA-Iuntil surface powerup.
4-5
00363-HSI-209261
TABLE 4-3
ASCENT STAGE EPS SUmmARY
Item A-h required A-h remaining
Initialcapacity -- 592
Total unusables 18 574
Availablefor missionplanning -- 574
Total requirementthroughcrew 216 358transfer
Total usablemargin -- 358 (60%)
4-6
00364-HSI-209261
00365-HS
I-209261
TABLE 4-4
DESCENTSTAGE EPS SUMMARY
Item A-h required A-h remaining
Initialcapacity -- 1600
Total unusables I08 1492
Availablefor mission planning -- 1492
Total missionrequirement 1229 263
Total usablemargin -- 263 (16%)
4-8
I I
00366-HSI-209261
00367-HS
I-209261
ASSUMPTIONSAND GROUNDRULES FOR THE LM RCS PROPELLANTANALYSIS
I. Data for the LM RCS engine performance and propellant re-quirements were obtained from the SODB, Volume II, and from postflightanalyses of Apollo 9-12 missions.
2. It is assumed that there will be an RCS burn (tweak burn) of30 fps following LM insertion. The tweak burn is nominally zero.
3. It is assumed that there will be a I0 fps trim following theAPS TPI maneuver.
4. The ullage for PDI was defined, subsequent to this analysis,to be an 8-second, four-jet ullage. The increase in RCS propellantusage is approximately 1.0% and is negligible in view of the nominal _RCS propellant remaining.
4-I0
I •
00368-HSl-209261
TABLE 4-5
LM RCS PROPELLANTLOADINGAND USAGE SUMMARY
Propellant PropellantItem required,Ib remaining,Ib
Loaded 633.0
Trapped 40.6 592.4
Gaging inaccuracyandloadingtolerance 43.5 548.9
Mixture ratio uncertainty 17.0 531.9
Usable 531.9
Nominalusage throughlunar landing 158.8 373.1
Nominal usage from landingthroughdocking 121.O 252.1
Nominalusage from dockingthroughimpact llO.O 142.1
Usable propellantremaining 142.1
4-11
00369-HSI-209261
00370-HS
I-209261
LM ECS Assumptions
a. The oxygen analyses were calculated using a cabin leak rate of0.06 Ib/hr based on previous Apollo postflight analyses.
b. Metabolic rates were varied using the time line of reference 4and table 4.3-11 of reference 2.
c. Metabolic oxygen consumed was calculated by(1.643 x 10-'_ Ib/Btu);< (metabolic rate, Btu/hr).
d. The cabin regulator check and the suit integrity check wereassumed to require 0.5 pound of oxygen.
e. The cabin was pressurized three times with 5.5 pounds requiredfor each pressurization.
f. The dispersion in the oxygen profile was calculated as 5 percentof the nominal oxygen requirement.
g. The PLSS refill requires 15 pounds ofwater and 1.7 pounds ofoxygen.
h. Water lost through crcw micturition vtas 0.II Ib/hr per man.
i. Water required for thermal control was calculated by dividingthe total spacecraft heat load by 1040 Btu/Ib.
j. The dispersien in the water profile was calculated as 10 percentof the nominal usage.
k. The average glycol flow rate used in this analysis was252 Ib/hr.
I. It was assumed that the liquid cooled garments were used through-out the LM-active periods.
4-13
00371-HSI-209261
TABLE 4-6
LM ECS SUMMARY
(a) Water
Description Descent, Ascent,ib ib
Loaded ..... 266.0 85.0
Sampling .................. 16.0 --
Residual ............... 6.7 1.7
Loading uncertainty ............ 7.7 2.5
Available for mission ......... 235.6 80.8
Required to lunar landing ......... 35.h 0.0
Required to lunar llft-off ......... 108.1 O.0
Required to I,M/CSM docking ......... 0.0 8.7
Required to LM close-out .......... O.0 6.0
Remaining in tank(s) ............ 92.1 66.1
Dispersion ................. 14.3 1.5
Margin ................. 77.8 6h.6
(b) OxygenJ . _, .
Description Descent, Ascent l, Ascent 2,lb lb ib
Loaded ............ hl.3 2.h 2.h
Residual ............. 0.8 0.I 0.1
Loading uncertainty ....... 1.5 0.I 0.i
Available for mission ...... 39.0 2.2 2.2
Required to lunar landing .... 2.2 0.0 0.0
Required to lunar lift-off .... 2h.2 0.0 0.0
Required to LM/CSM docking .... 0.0 0.h 0.0
Required to IM close-out ..... 0.0 0.5 0.0
Remaining in tank(s) ....... 12.6 1.3 2.2
Dispersion ..... 1.3 0.I 0.0
Margin .............. 11.3 1.2 2.2
4-14
00372-HSI-209261
NA
SA
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00373-HS
I-209261
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00376-H81-209261
12/8/7 0 Final
GROUND RULES AND ASSUMPTIONSFOR THE CSM CRYOGENICS
I. Three 02 tanks and two H2 tanks are available.
2. Fuel cell purgingis includedin the EPS requirements.
3. Both H2 tanks and two of the three 02 tanks are assumedto be
fully loaded. The third 02 tank is to be off-loadedto approximately62 percentat lift-off.
4. No cryogenicventingwas assumedin flight.
5. The EPS hydrogenconsumptionrate (H2) (Ib/hr)= 0.00257x Ifc
when Ifc is the total fuel cell current.
6. The EPS oxygen consumptionrate (62) (Ib/hr)= 7.936 x H2"
7. The launch redlinesfor 02 are definedas points on the curve.These points are contingentupon accomplishingDTO 4.6 which is greaterthan a tank loss requirement. However,if lift-offwere to occur atthese points,a somewhatdifferenttank managementschemewould haveto be employed,even if no tank failed. If a tank failurewere to occurthen a nominal40 Amp returnlevel plus ECS would be employedon theremainingtwo tanks.
4-19
00377-HSI-209261
f_
TABLE4-7
APOLLO14 CRYOGENICSUMMARY[31 Jan, 1971 Launch]
H2(Ibs) 02(Ibs) _
Planningallowance
Total loaded 58.6 990.3Less residual 2.3 19.8Less instrumentationerror 1.5 21.8
Availablefor mission planning 54.8 948.7
Prelaunchrequirement 3.7 130.4"
Flight requirement
EPS (incl.F/C purge) 39.2 310.5ECS (includingcabin purge + EVA) -- 87.5LM pressurization -- 12.5
Nominalreserves
EPS uncertainty(2.5_) l.O 7.8ECS uncertainty(.08 #/hr) -- 17.3
Total requirement 43.9 566.0
Margin T = 0 (fill/launch) 10.9 382.7
Prelaunchrequirementincludesoff-loadingof tank 3.
4-20
00378-HSI-209261
00379-HS
l-209261
00380-HS
l-209261
THE SPS ANALYSIS
Assumptions for the SPS Propellant Analysis
I. The 3o dispersions are the RSS of the penalties imposed on theSPS margin by 3o dispersions in propellant loading, mixture ratio, engine
Isp, maneuver AV, spacecraft weight, and consumable weight losses. The
engine Isp and dispersion utilized in this analysis were taken fromTable II of the Apollo Mission H3/CSM-IIO/SPS Preflight PerformanceReport, NAS 9-8166, dated November 1970. All spacecraft weights andconsumable losses are from Volume III, Amendment 88, of the SpacecraftOperational Data Book, dated October 5, 1970.
2. The allowance for the TLMC is now debited from the nominalremaining propellant along with the 30 dispersions. It is only a formatchange, not a budgeting technique change.
3. The ground rule for a contingency allowance is to budget foreither a LM rescue or a maneuver to avoid adverse weather conditions atentry, whichever produces the least SPS propellant margin. The AV forthe LM rescue allowance is 600 fps. The AV for weather avoidance forprevious missions has been 500 fps. However, for this mission, the AVrequirement for weather avoidance has been reduced to 300 fps. Thepropellant margin when considering either contingency, LM rescue or the300 fps for weather avoidance, is approximately the same.
/
4-23
00381-HSI-209261
TABLE 4-8
APOLLO 14 SPS PROPELLANTSUI_ARY
[Jan. 31, 1971, launch;72° launch azimuth]
Item Propellant Propellantrequired,Ib remaining,Ib
Total loaded 40 796.0
Trapped and unavailable 441.4 40 354.6
Outage 59.8 40 294.8
Unbalancemeter lO0.O 40 194.8
Availablefor AV 40 194.8
Requirementfor AV
Hybrid (73.4 fps) 724.2 39 470.6LOI (2986 fps) 24 777.8 14 692.8DOI (206.6fps) l 470.8 13 222.0CIRC (72.5 fps) 272.8 12 949.2LOPC (360.7fps) l 269.2 II 680.0TEI (3449.5fps) lO 059.4 l 620.6
Nominalremaining l 620.6
Dispersions _
-30 performance 473.0 l 147.6TLMC(33 fps) 346.2 801.4
Contingency (326 fps) 301.4 0.0
Propellant margin 0.0
Available for weather avoidance.
4-24
00382-HSI-209261
_._ SM RCS BUDGET
Ground Rules and Assumptions
I. Following transposition and docking, the S-IVB performs theevasive maneuver.
_ 2. Two midcourse corrections (translunar) are executed as SPSburns with one MCCfollowed by an RCS trim.
3. One midcourse correction (transearth) is executed as an RCSburn of 5 fps.
4. Quad management is to be determined during the mission.
5. Redlines have been defined by the Flight Control Division as anaid in assuring that mission rules are not violated during the mission.They are subject to review during the mission as mission phases arecompleted and systems capabilities are evaluated. In the event the res-cue redline is violated prior to rendezvous, lunar orbit photographyactivities can be curtailed to conserve propellant. The lunar orbitredline includes a nominal transearth coast phase (with all navigationalsightings) plus a 3 sigma G&N TEl cutoff error MCC. If a rescue isrequired and the lunar orbit redline is violated prior to the nominalTEl, TEl can be performed early and navigational sighting activity cur-
f-_ tailed during the transearth phase. The rescue redline is based on theminimized activity during the transearth phase.
_ 4-25
00383-HSI-209261
TABLE4-9
SMRCSPROPELLANTLOADINGAND USAGESUMMARY ....
Propellant PropellantItem requi red, remai ni ng,
Ib Ib
Expected loading ........... -- 1342.4
Initial outage caused by loadingmixture ratio ........... 15.6 --
Total trapped ............ 26.4 --
Gaging inaccuracy .......... 80.4 --
Deliverable ............. -- 1220.0
Nominal usage
Translunar coast .......... 199 --Lunar orbit ............ 431 --Transearth coast .......... 220 --Total ............... 850 --
Nominal remaining usablepropellant ............. -- 370
4-26 _
00384-HSI-209261
00385-HS
l-209261
00386-HS
l-209261
00387-HS
l-209261
II
00388-HS
I-209261
00389-HS
l-209261
TABLE 4-10
CM RCS PROPELLANTSUMMARY
Propellant PropellantItem required, remaining,
Ib Ib
Loaded ............... -- 245.0
Trapped .............. 36.4 208.6
Available for mission planning . -- 208.6
Nominal usage ........... 38.9 169.7
Nominal remaining ......... -- 169.7
4-32 _
J F
00390-HSI-209261
SECTION 5 - ABBREVIATED TIMELINE
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