consumables analysis for the apollo 10 s/c operational ... · •msc internal note no. 69-fm-76...
TRANSCRIPT
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. \ .NATIONAL AERONAUTICS AND SPACE ADMINISTRATION
MSC INTERNAL NOTE NO. 69-FM-76
April 7, 1969
CONSUMABLES ANALYSISFOR THE APOLLO 10 (MISSION F)
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SPACECRAFT OPERATIONALTRAJECTORY
•I Guidance and Performance Branch,
MISSION PLANNING AND ANALYSIS DIVISION •
Unclas16454
N74-70735
00/99
.:~~~
'i •••~...••~.~~.;·7) MANNED HS:U~~OEN~T~~~TCENTER~'. :!I~"!I
CNASA-TM-X-69384) CONSUMABLESAN AL YSIS~FOB THE APOLLO 10 (MISSION F) SPACECBAFT:::.OFERATIONAL TRAJECTORY (NASA) 64 p
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MSC INTERNAL NOTE NO. 69-FM-76
PROJECT APOLLO
CONSUMABLES ANALYSIS FOR THE APOLLO 10 (MISSION F)SPACECRAFT OPERATIONAL TRAJECTORY
April 7, 1969 "
By Martin L. Alexander, Sam A. Kamen, Arnold J. Loyd,Samuel O. Mayfield, Dwight G. Peterson,
and Walter Scott, Jr. ,Guidance and Performance Branch~
MISSION PLANNING AND ANALYSIS DIVISION
NATIONAL AERONAUTICS AND SPACE ADMINISTRATION
MANNED SPACECRAFT CENTER
HOUSTON, TEXAS
•
••
Appro.ede~a-.J)w M::OWe:eassetti, Chiefo Gui c and ance Branch
•FOREWORD
The following table summarizes the consumables requirements forthe Apollo 10 mission. Percentages refer to nominal usage only and donot include dispersions and contingencies.
•
Consumable
CM RCS
SM RCS
SPS
M~ 18 launchM~ 17 launch
1M RCS
DPS
~S
CSM02
1M descent battery
1M ascent battery
Percentage of available consumableused for mission planning
15
60
9289
65
5
100
66
77
36
73
••
These results were obtained from detailed consumables analysesperformed on the Apollo 10 RCS, SPS, ~S, DPS, and EPS. A time historyof total consumables weight loss is also presented. The ECS analysiswill be supplied when the detailed operational trajectory time line isavailable.
The principal sources of data were the data books (refs. 1, 2,and 3). The Res and EPS analyses were based on the Apollo 10 roughdraft preliminary flight plan (ref. 4). The operational proceduresdescribed in this study are not intended to define mission rules or
iii
crew procedures but are merely an attempt to establish an estimate ofthe consumables requirements.
Support was obtained from TRW Systems Group, from North AmericanRockwell, from Grumman Aircraft Engineering Corporation, from theApollo Spacecraft Program Office, and from the Instrumentation andElectronics Systems Division.
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II
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Section
1.0
2.0
3.0
4.0
5.0
6.0
7.0
8.0
9.0
10.0
11.0
12.0
CONTENTS
THE CM RCS ANALYSIS
THE SM RCS ANALYSIS •
THE SPS ANALYSIS
THE 1M RCS PROPELLANT ANALYSIS
THE DPS ANALYSIS
THE APS ANALYSIS
ASSUMPTIONS AND RESULTS OF THE EPS ANALYSIS .
THE CSM ECS ANALYSIS
THE 1M EPS ANALYSIS
THE 1M ECS ANALYSIS . . . •
TIME HISTORY OF CONSUMABLES WEIGHT LOSS .
REFERENCES . . . . . . • . . . . • . . .
v
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Page
1
2
23
27
33
35
36
43
44
4t1
4~
51
•TABLES
Table Page
1-1 CM RCS PROPELLANT SUMMARY . · · · · . . . . . 1 •2-1 GROUND RULES AND ASSUMPTIONS FOR THE SM ReSANALYSIS . . . . · · · · . · . . . 2
..2-II SM RCS PROPELLANT LOADING AND USAGE SUMMARY 3
2-III SM RCS PROPELLANT BUDGET · · · · 4•
3-1 ASSUMPTIONS FOR THE SPS ANALYSIS 24
3-II SPS PROPELLANT SUMMARY
(a) May 17 launch, 72° launch azimuth, firstopportunity injection · · . · . 25
(b) May 18 launch, 72° launch azimuth, firstopportunity injection 26
4-1 GROUND RULES AND ASSUMPTIONS 27 •4-II 1M RCS PROPELLANT SUMMARY 27
4-III 1M Res PROPELLANT BUDGET 28
5-1 ASSUMPTIONS FOR THE DPS ANALYSIS 33
5-II DPS PROPELLANT SUMMARY · · · 34
6-1 ASSUMPTIONS FOR THE APS ANALYSIS 35
6-II APS PROPELLANT SUMMARY 35 ..7-1 ASSUMPTIONS FOR THE CSM EPS ANALYSIS 37
7-II CRYOGENICS SUMMARY 38 ". . . · · · ·9-1 ASSUMPTIONS FOR THE LM EPS ANALYSIS . 44 •ll-I TIME HISTORY OF CONSUMABLES WEIGHT LOSS 4~
vi •
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Figure
2-1
7-1
7-2
7-3
7-4
9-1
9-2
11-1
FIGURES
SM RCS propellant profile
(a) Total.(b) Quads A and C(c) Quads Band D •
Total spacecraft current versus time
Hydrogen remaining for mission for one tank versustime .•.. . . . . . . . . .
Oxygen remaining for mission for one tank versustime . . . .. . . . . .
Total DC energy profile versus time
Descent electrical power profile for an F missionflight plan . . •. .... . . . .
Ascent electrical load analysis for an F missionflight plan . • .. ...•...
Spacecraft weight versus ground elapsed time
vii
Page
202122
39
40
41
42
AGS
APS
CDH
CM
COAS
CSI
CSM
DB
DAP
DOl
DPS
ECS
EECOM
EPS
F.T.P.
H2
IMU
I fc
I sp
LM
LOI
LOS
ABBREVIATIONS
abort guidance system
ascent propulsion system
constant differential height
command module
crew optical alinement sight
concentric sequence initiation
command and service modules
deadband
digital autopilot
descent orbit insertion
descent propulsion system
environmental control system
electrical, environmental, and communications
electrical power system
full throttle position
hydrogen
inertial measurement unit
fuel cell current
specific impulse
lunar module
lunar orbit insertion
line of sight
viii
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..
•
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••..
•
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LPO
MCC
MI
MPAD
MSFN
NR
ORDEAL
°2
PGNCS
PTC
RCS
REV
RR
SCS
SEP
SLA
SM
SPS
SPS-n
T, D, andE
TEC
TEI
TLC
TIMC
lunar parking orbit
midcourse correction
minimum impulse
Mission Planning and Analysis Division
Manned Spaceflight Network
North American Rockwell
orbital rate display, earth and lunar
oxygen
primary guidance and navigation control subsystem
passive thermal control
react ion control system
revolution
rendezvous radar
stabilization and control subsystem
separation
spacecraft/1M adapter
service module
service propulsion system
number of the SPS burn; n = 1, .•• ,8
transposition, docking, and extraction
transearth coast
transearth inj ection
translunar coast
translunar midcourse correction
ix
TPI
TPF
t
WT
terminal phase initiation (of rendezvous)
terminal phase finalization (of rendezvous)
time
weight
x
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'CONSUMABLES ANALYSIS FOR THE APOLLO 10 (MISSION F)
SPACECRAFT OPERATIONAL TRAJECTORY
By Martin L. Alexander, Sam A. Kamen, Arnold J. Loyd,Samuel O. Mayfield, Dwight G. Peterson,
and Walter Scott, Jr.
1.0 THE CM RCS ANALYSIS
The CM RCS propellant data were taken from reference 1. Usagedata were taken from reference 5. The CM RCS propellant summary ispresented in table I-I .
TABLE I-I. - CM RCS PROPELLANT SUMMARY
ItemRCS propellant RCS propellant
used, Ib remaining, Ib
Loaded -- 245.0
Trapped 36.4 208.6
Available for mission -- 208.6planning
Nominal usage 30.8 177.8
Margin -- 177 .8
2
2.0 THE SM RCS ANALYSIS
TABLE 2-1.- GROUND RULES AND ASSUMPTIONS FOR THE SM RCS ANALYSIS
The following ground rules were used to calculate theSM RCS budget.
1. The transposition and docking phase of the missionincludes an SPS evasive maneuver.
2. The first and third MCC's (translunar) are executedas SPS burns with the third MCC followed by an RCS trim.
3. Passive thermal control is assumed to be in thePGNCS wide deadband control mode and to require 1 Ib/hr,compared with 1.1 to 1.T Ib/hr requirement on Apollo 8 inthe SCS control mode, except for the test periods undermanual control which required ~ 5 Ib/hr on the Apollo 8mission.
4. The sixth MCC (transearth) is executed as an RCSburn of 5 fps.
5. The SM ReS propellant allocation for a CSM-active il
rescue of the 1M is currently under study. The data is tobe included in revision 1 to this document.
6. The propellant profiles shown in figure 2-1 arebased on usable propellant remaining as a function of missiontime.
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TABLE 2-11.- SM RCS PROPELLANT LOADING AND USAGE SUMMARY
•..
•
••
Nominal loaded propellant, Ib •..•.
Initial outage caused by loaded mixtureratio, Ib . • • . • . .
Total trapped propellant, Ib
Gaging inaccuracy, Ib ..
Deliverable SM RCS propellant, Ib .
Nominal propellant used, Ib . . . .
Propellant used for translunar phase, Ib
Propellant used for transposition anddocking, Ib . .. . • . . . . .
Propellant used for midcourse corrections,lb . . . .. .. . . . . . . . . . .
Propellant used for passive thermalcontrol, Ib . . . . . .
Propellant used for other items, Ib
Propellant used for lunar orbital phase(LOI-TEl inclusive), Ib . . . . • . •
Propellant used for docked CSM activities,Ib . . . .. .. . . . . . . . . . .
Propellant used for undocked CSM activitie~,
lb . . . . . . . . . . . .
Propellant used for trans earth phase, Ib
Propellant used for midcourse corrections,Ib . . . .. .... . . . .. . . . .
Propellant llsed for passive thermal control,Ib . . . . . . . . . .
Propellant used for other items, Ib •
Outage caused by mission duty cycle mixtureratio, Ib . . • • . . • • .
Nominal propellant remaining, Ib
1342.4
15.6
26.480.4
1220
730
334
90
35
106
103
221
96
125
134
24
7436
41490
4
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•
•5
TABLE 2-III.- SM RCS PROPELLANT BUDGET - Continued
• 1 p1E. EvE" T SIC liT SM ReS SM Res S'"I HR l 'lBSl UsED L.EfT RC,
I L.8S' (L.BS' L.En'i,
'1.'1 ORIENT TO MONITr R 5L.INGSHOT 957'16. '1.3 12'1B'2 93.0.2 OEG/SEe pGNeS
5.0 P:'2 IMU AL.IGN 9,7'12. '1.2 12'1'10 U 93.
5.:. ORIt:NT fOR NAV "lbHTING5 9<,7311. '1.3 1239.7 92.
5.6 ORIEf\jT fOR NAv ... I b HT I ;, G5 95733. '1.2 123,.!> '12.
5. 7 ORIt.NT fOR NAJ c.1"'HT1NGS 9,,729. '1.3 1231.2 '12.
5.8 Oi;It.NT fOR NAv c;IGHTING5 95725. '1.2 1227.0 Ii I.
:..9 ORIt::N1 fOR NAV <,lr.HTINGS 95721. '1.2 1222.7 9 I •
• ,.9 MINIMUM IMPUL.Sl MIlRKINb fOR S1(,5 9~715. 5.2 1217.6 'II •
b.O O~IC.NT fOR PTe 'I! 7 I 1 • 3.9 12 I 3.7 90.~AX 1S U.l OEc;/SEC
6.U ATTITUDE HOL.'~ <.l.2 DEG Oil sec:; 9:. 7 I I. .11 1212.9 90.
!l.U lST. 0.3 :>E,,/5Ee ROL.L. 'f5710. • 'I 1212., 9U.
6.U "ITCH A'~O 1 A., eO'HkUL. 9;708. 2.7 12U9.8 90.
II. 7 ~~2 J MU ALtr.N 9570S. 2. 'I 1207. 'I 90.
9.l "'IOeOURSE eo""ErTIVN NO I 95101. '1.3 12U3'1 Yo.J AXI 5 Oli/IE'lT ,,(iNes
9.2 ATTITUDE HOL.I) 5 OE" DB 95701. • 'I 1202.7 90.
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6
•TABLE 2-111.- SM RCS PROPELLANT BUDGET - Continued
TIME EVE .. T SiC .T SM ItCS SM RCS SM
•I Hit I 11851 USED LEFT ItCS(L.SS' 11.851 L.Ef'T
II,
•• 2 SI'S BUItN .,•• a. .0 IZU2., '0.IIUILD UI'
•• 2 STEADY STATE 8UltN II 'i•• 2. • I IZOZ •• 'd.
•• 2 TAILO"" "'21. .1 120 I.' '0.
,.2 OAMP SHUT.oOAtIi TRANSIENT 95'20. I • I IZOO.8 8'.
10. I 1'52 I'IU HI GN 'i·18. 2.3 II ,a. s .,.10.'1 OR I EI';T FOR PTC 95'1", 3.9 II' .... 8'.
lAUS 0.2 oE(;/5[C
10." ATTITUDE HOL.I'l 0.2 DEG 08 SC5 ''i'll. .8 1193.A a,.
10. 'I EST. 0.1 DEc;,/SEC RoL.I. '5'12. ... 1191 ... it" •10 ... PITCH AND '(A,. CONTltOL. "'01. ••• 11e3 •• •••zo.o PS2 IMU HI CiN '55". 'f.Z 117' •• its.
20.'f ORIENT Fa" NAV C;IGI1TtNCiS 'sS''f. ".2 I"!il ... 8e.
20.8 O~IENT FOR NAY 51 CiMT IIHiS 955,0. ... Z I I 7 I • I 87.
21.2 ORIt:NT FOR NAY 51 GHT P-lGS '55••• '1.2 11 ..... 87.
21 •• ORIENT FOR NAY slCiHTINliS 'SSAZ. 'f.Z 11.2.7 '7.
21 •• MINIMUM I"'PULSE "'A"K ""G 'S!l78. 3." II!I'·) a ••
••
•
•
7
8
•TABLE 2-III.- SM RCS PROPELLANT BUDGET - Continued
TIM£. £.VE,,1 SIC *T SM RCS SM RCS S" •I HR I I LBs I USED LEFT RCSILFISI ILISI LtFT
III
.. 7.0 fOTe TEST WIO ATT C"1)1tT1t01. 'SSII. 12.0 1O"., 12.
",.u fOTc TEST */0 ATT CONUOL 'SSO'. 12.0 1017.2 II.
!i I. U fOTe TEST W/O ,TT CONTROl. 'S"'''. .2.0 1075.' 80.
53.0 1052 IMU ALIGN '!tl'l'O. ... 2 1071.0 110.
5 ... 1 MIDCOVRSE CORRECTION NO 3 's"e'. '1.2 10".1 7'.MNVR TO BURN ATT
5'1.1 ATTITUDE HOln '5'1.'. .'1 10"''1 7'.
5". I SPS BURN 'S'Ie3. .0 10"''1 7'.BUIL.O UP •5'1.1 STEADY STATE eUHN II 'S'IS7. .0 10"'" 7,.
5 ... 1 TAII.OFf' '5111'. .' 106"5 7' •
5'1. I DAMI" SHUT.OO ... N TRANSllNT '5'11". I • I 10' ..... 7'.
5".1 Hes TRIM I "PS '5"03. I 1.0 IOS3.5 7••
5".5 ORIENT "OR PTc '!O3". '1.0 10'1'." 7••JAXIS 0.2 oEc;/SEC
S'I.!O ATTITUOE HOL.o 0.2 DEro 08 scs '53". .8 10".'7 7s.
5'1.5 EST. 0.3 oEc;/SEC ROI.L. '53'1. ... 10'1.'3 7••
S".§ I"ITeH AND TAW CDNTROI. '53'0. 7.1 "'''0.5 7S.
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•9
TABLE 2-III.- 8M RC8 PROPELLANT BUDGET - Continued
• TP~E E'JE~' 1 SiC ... T SM ReS SM RCS 5'"I HR I ILBSI usED L. EF" T ReS
1L.~SI IL8S1 U.FTIII
62.0 PITCIo4 AND "A~ CONTROL 95383. 7.8 1032.7 77.
70. I P52 IMU ALIGN 95378. '4.2 1028.'1 77.
7 I • 1 MIOCouRSE CORHEcTION t'.O 'I 9~37lf. If.2 102".2 7,.MNVR TO BURN 1 TT
7 I • 1 ATT HOL.D 0." [;,EG Db PulloCt.; Y;37't. .If 1023.' 7,.
71 • 1 LlEL. vEL • NOM ZERo 9537'1. .0 1023.8 7,.
• 71 • ~ ORIENT FOR PTe 9~37U. '1.0 10U.tt 76..lUIS 0.2 OE.r,ISEC
71.5 ATTITUDE HOLr: 0.2 OEG 08 SCs 9.369. .8 1019.0 7,.
7 1.5 lST. 0.3 OE(~/~EC ROL.L 9S369. .If 1018. , 7,.
7 I .!» PITCH AND YA .. CONTHOL 95366. 1 • a 1017., 76.
71 • ~ I/EON I EN T 9i36S. 2.'1 1015.2 7,..
7 1.5 HEOHIENT 9!363. 2.'1 1012.8 75.
75." P~2 IMU ALIGN 95359. '1.2 1008 •• 7S.
• 7~." SExTANT SUR CHF(I\.INc;,MIN IMPULSE 91;358. .'1 1008·Z 75.
76.2 LUNAR ORBIT I~Stlq ION 8UF<~ 9535'1. '1.2 10"'4.0 75.3-AXIS ORIENT PGNCS
76.2 ATTITUDE ~OLI1 9535'4. .'4 1003.' 75.
•
10
•
•11
TABLE 2-111.- SM RCS PROPELLANT BUDGET - Continued
• TIME EVE",T SiC NT SM FjCS 51'1 ~CS 51'!(HRI I LBs I u-;EO L.EF T ReS
IL.ASI (l.b51 LEFTI ~ I
80.~ TA1\.O'" 706,,8. .0 '11 ... 8 72.
80.' DAMP 5HUTOO't1li TRANSIENT 706,,7. I • 1 1f63.7 72.
81. a REORlt.NT FOR Mc;FN ACloIUISITION 7nll63. 3.'+ '60'3 72.
83.!:t PS2 IMU AL.IGN 7QII6U. J.'+ 9~6.' 7 1 •
83.S REOItIENT 706C;7. 3." '53." 71 •
• 8J.~ HEOHIENT 71)6~3. 3.'+ ,SO.U 71.
83.S MINIMUM t I'IPllL Sf MARKING 7n653. .tt ,.. ,." J I •
8'+.S ORIENT FOR I'1<;Fr. 706,+Y. 3.'+ '''''2 70.
8!:t.!:t MANt.UVER To ORO, fAL SLEEP MODE 706,+6. 3.'+ '''2.a 70.ASSUME SAME AS PTe
8S.S PIT'H AND YAw colHROL 706 .. 1. ...5 ,38,3 70.
90.0 f'ITc'H AND YAW CONTROL 70637. ... s ,33,8 70.
9S.S PS2 IMU ALIGN 70633. 3." '30 ... 119.
• 95.S REORIENT 70632. I.S '2S'6 6'.
95.5 REORIENT 70630. I .8 '26.8 .,.
•'7.0 aRiENTATION ~.NEUVERS 70627. 2.5 ,21f.3 .,.
12·
•TABLE 2-III.- SM RCS PROPELLANT BUDGET - Continued
T p1E EVEiIIT SIC ttT SM ReS 5/1 RCS SI'! •(HR, (L8SI USED LEFT ResfLBS' ILBS' LEFT
III
,B.O ORIE~T TO UNnUeKIN<i ATT 7062't. J.lt '20.' .,.98.5 UNOOCK 'taSe8. 't.9 91S.9 68.
9B.S STATION KEEP fn~ LM PHOTOCiIUI"Hy 'tOS7B. 10.0 905.9 67.
98.8 REORIENT FOR 1'1 ... ~ N ACQUISITION '+0576. 1 .1 90'+.3 .7.
98.9 OHIENT fOR SEP BURN "0575. • 8 903.S 67 •
99.2 IotCS SEPARATION 'IU~N I fPS '+0570. 't.' 898., 67. •99.2 REORIENT 'tOS10. • !; 898. I 67 •
99." REORIENT 't0569. •s 897.1> 07 •
99.6 REORIENT '+OS69. .~ 8'7.1 67.
99.8 REURIENT 'tOS68. • 5 8'6'6 67 •
99.8 .'\ I NI MUM IMPU,S[ CONTROL. 'tOS65. J." 893.1 67.
102.0 P!:>l IMU ALIGN 'tOS6J. 1 • 7 891 • ~ 66.
•102.5 MANEUVERS ACQUISITION ATT 't056U. 8el.8 .6.il. TO 2.7
102.9 MNV R TO 8URN A'r T 't0559. I .7 887. I 66.
102.9 ATTITUDE HOLn i1fITH MI "O§58. • 3 I'•.• 66 • •
•13
------ - - ---
TABLE 2-III.- SM RCS PROPELLANT BUDGET - Continued
• T1'''£ EYE t. T SIC ",r SI1 RCS SI'! RCS 51'1(HR I (LBSI uc;ED LEFT RCS
( L. 8 5 I (LBSI LEn( SI
103.2 t'S2 IMU ALIGN 'lOS'; 7e 1.7 885'1 66.
103.A l'lNyli TO 8URN ATT '10555. 1 .7 883.~ "6.
103.8 An HOLD 'tOS5J. 1 .7 881.7 66.
10lf.0 HEORIENT SPACF:CHAFT If TII'IES ,+05lf8. s.o &76.7 65.
IQ'f.l.l I"IINI",UM I I1PUI SE CONTROL 'IOS .. s. 3.0 173.7 65.
• lo~.'t MA~EU\lER TO TPt ATTITUDE ltoSIf't. I .7 872.0 65.
105 ... ATT HOL.D '10SlfJ. .9 871.2 65.
106.0 FoUR MANEUYE~S 1 u ATTITuoE 'foS38. s.o 866.1 6S.
106.0 i'1INlIolUM I MPUI SE CONTROL 'foS36. I .3 8o'f.A 6'1.
106.S REURIENT FOR MsF~ ltoS3S. I .7 863.2 ''I.10&.' Ty ALL.OWANCE '10~)I. '1.0 IS9·2 ''1.
106.9 ORIENT TO OOCKI",(, ATT I TUDE lfoS29. I .7 857.51 "If •
• 107.0 "AIIiTAIN 80RESIGHT '10527. I .7 8!;S'8 "'4.
107.0 DOCKING '1,da9. 2.S aSJ.) ''1.
•108.5 :o1NV~ TO JETT 150,. ATT '1'111. I .2 852'1 63.
-- --~--~----
•
•15
TABLE 2-111.- 8M RCS PROPELLANT BUDGET - Continued
• T 11'1 E(HR)
511 RCS SM RCS
USED LEFT(LaS) ILlS)
126.S ~EoHt~-~ ~AijD"A~S
3 TIMES PER REV"0.,'1. 3.8 11'.S 61.
126.5 ROLL TO ACQUIRE MSFN 'IOIf,I.
"0 ...0. ... lie.. 61.
128.0 REV 27 IMU ALIGN 'IOIf90. .& 111.0 'it
•IZI.!> 'UO~ I tNT "-OR" ~.IItD"ARI(S
3 TIMES PER REV
128.S kOLL TO ACQUIRE MSFN IfOIfAS.
J.I 11".2 6it
.3 113.9 'I.
128.~ ... 8l3.S 6 ••
12R.S PS2 IMU ALIGN
3.8 808.0 60.
128.S AuTO OR8 RATE 1t7 80'.3 60.
12'.U PS2 IMU ALIGN
.If 8UIf.2 60 •
1.7 loa., 60.
sXT STAR CHEC"129.0
12'.8 TRA~-tA~ tN~[~TtO~
MNVR TO BURN ATT••
12'.8 - ATTITUDE HOLn
12'.R U~t~
2 JET BAND tJ
.'1 102.2 60.
Ilt.D 7BI.2 s...
16
•TABLE 2-111.- SM RCS PROPELLANT BUDGET - Continued
TIME E'JEr. T SiC oIIT SM RCS SM ReS sM •(HR) (LBS) Ut:;ED LoEn RC.S(LRS) (L.BS) L.EFT
(i I
129.8 SPS 8URN '+0,+s7. .0 768.2 59.BUIL.D UP
129.R STEADY SUTE IiURN 136 SEC PbNCS 31293. .2 788.0 59.
129.8 TA I LOFF' 31252. .U 788.0 !il9.
129.8 OAf1P SHUTDOWlr.. TkANSIENT 3\ Zs I. I • 1 786.9 5'19.
130.0 MANEUV-ER FOR MSFN ACQUISITION 3\250. 1 .5'1 785.,+ 5 ••
131 .7 P52 l"lU ALIGN 3\2148. I .5 783.9 Sb. •132.0 ORIENT FOR PTe 3\2148. .7 783.2 S8.
3AXIS 0.2 Ole./Sle
132.0 ATTITUDE MOLD U·2 oEr:a DB Sc.c; 312'17. .tt 782." !tR.
132.0 t.ST. 0.3 oEr-ISEC ROLL 3IZ'I7. .2 782.2 Sa.
13Z.U PITCH ANt> YA .. CONTROL 31216. \ I • a 771 .2 S7.
1'I3.u P!t2 IMU ALIGN 3\23'+. \ .5 76'.7 !t7.
1.. 3.5 C1SL.UNAR NA\lIc.ATiulII 31228. b.2 763.10 !:I7.STAR/L.UNAR HDWIZO~ ORIE.NT •1143.S MIN. IMPUL.SE ~, ARI( I NG 31226. 2.2 761. " S7.
114'1.8 MIOCOURSE CORREcTION NO S 3122", I.S 759.9 57.1'l,:VR TO BURN ATT
1,,'+.8 ATTITUDE HOLn "tTM MJ 3\22'1. • 3 759.7 S7 • •
•17'
TABLE 2-III. - SM RCS PROPELLANT BUDGET - Continued
• TIME EVE~T SIC ttT 5"" RC S SM RCS 5"( HR ) 1t BS I USED L. EF' T RCS
(LBSI CL8S) LEFTIII
1..... 6 DEL- vEL • NO", ZERO Jr 22". .0 759.7 17.
1.. 6.0 pTe TEST W/O A1 T CONTROL 1\2\5. 9.0 750.7 !i ••
llf8.0 pTe TEST ""0 ATT CONTROL 31206. 9.0 7 .. 1.7 f:lS.
150.0 pTe TEST Wi/O An CONTROL 31197. 9.0 732.7 55.
ls0.0 Tv ALLOWANCE 31193. ... 0 728.7 SIf •
• lS6.0 P52 I"U ALIGN 311,2. I • S 727.2 5 ...
156.5 ORIENT FOR PTe 31191. .7 726.5 Sif.
3AX IS 0.2 DEr.ISEe
156.5 ATTITUDE. HOln 0.2 DE, 08 SCS 3\ 190. • 8 725.7 S...
156.5 EST. 0.3 DECo/SEe ROLL 31190. • 2 72S.S 5 ...
IS6.~ PITCH AND VA.,. CONTROL J 117'. 1... 0 71 Ie S 53.
17 I • (1 PS2 IMU ALIGN 3\17'+. 1.5 710.0 53.
173.5 ORIE.~H FOR PTC J I 17 If • .7 70'.3 53.
• 3AXIS 0.2 Dlto/SEC
173.5 ATT I TUDE HaLl) 0.2 OEG 08 SCS 31173. .& 708.i 53.
173.5 EST. 0.3 DEli/SEC ROLL 3\171. .2 70t.3 53.
173.S PIT'" •-no Y.,,; CONT"OL 3 I I ,~. ... 0 70".1 52 •
•
18
•TABLE 2-111.- SM RCS PROPELLANT BUDGET - Continued
TIME lVEr-.T SIC NT 51'1 RCS SI'I HCS SI'I •(104Ft) ILSS) Uc;Eo LEFT RCSIL"SI CLBS) LEFT
III
175.0 P~2 lI'IlJ ALIGN 3,1117. I • ~ 702.8 52.
176.2 MIOCOURSE CORREc.TION NO • 311,,6. I • ~ 701.3 ~2.
I'INVR TO BURN ATT
176.2 ATT ~OL [) .~ DE" 1')8 PGNCS 311,,5. ... 70 I .0 ~2.
17t-.2 ReS -x TRANS 5 FI-'5 311 .. 7. \ 8. I 682.8 5 I •
17 b • 7 ORIENT rOR PiC 311&+6. .7 682. I 5 I •JAXIS 0.2 DE(,/sEe
176.7 ATTITUDE HOLe. U.2 OEG 01:1 SCs 3\1 .. 6. .8 681.3 ~ 1 • •176.7 EST. 0.3 OEc;/SEC ROLL 3\1&+'. .2 68\ • I !J , •
176.7 PITCH AND YA" CONTROL 31137. 9.0 612. 1 ~a.
187.U P52 II'IU ALlCaN 31IJ~. I • ~ 61U'6 ~O.
1S8.3 ~11 OCOURSE CORRECTION NO 7 31133. 1 .5 669.1 ~o.
MNVR To BURN ATT
18 B• J ATT HOLD .~ DECi DB PCiI~CS 31133. .3 "68.9 50 •
188.3 UEL vEL • NO", zERO 31133. .0 668.9 ~o.
189.& PS2 IMU ALIGN 3113l. I.~ 667.3 So. •191 .0 MANEuvER To REENTRY ATTITUDE 31130. 1 • S 665.8 SO.
19 I .0 ATTITUDe: ,",Olo 0.2 OEC'i os SCs J I 12' • .8 ••S.O So.
•
•19
TABLE 2-III. - 8M RCS PROPELLANT BUDGET _ Concluded
• T P"E EvENT SiC .. T s" ReS S"RCS 5"
CHR) CL8!) U
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23
3.0 THE SPS ANALYSIS
Weight assumptions for the SPS analysis are shown in table 3-1(ref. 3, amendment 41); SPS performance parameters were taken fromreference 1.
The SPS propellant budget for a May 17 launch, 72° launch aZimuth,first opportunity injection is presented in table 3-II(a). Thepropellant budget for a May 18 launch with a 72° launch azimuth,first opportunity injection, 61-hour lunar orbit time, and 2-dayreturn is shown in table 3-II(b). Both budgets include a contingency~v of 900 fps to provide the capability to perform a worst case 1Mrescue, to return by use of the SCS, or to return from any lunarorbit.
The May 18 launch has two other sets of ~V associated with it,one which assumes a 51-hour lunar stay (TEl of 3198.8 fps), andthe other which assumes a 61-hour lunar stay and 3-day return(TEl of 2818.8 fps). The propellant margins associated with thesetrajectories are shown in table 3-II(b). The contingency ~v of900 fps would be used for a quick earth return or for a 1M rescue inthe last case. Propellant margin for the May 17 launch [table 3-II(a)]is 1837 pounds, and for the May 18 launch, fast return [table 3-II(b)]is 818 pounds .
24
TABLE 3-1.- ASSUMPTIONS FOR THE SPS ANALYSIS
1. Each SPS engine start used 14.4 lb of propellantin nonpropulsive losses.
••2. Spacecraft weights
CM, lb •
SM, lb
SLA ring, lb
Tanked SPS, lb
LM (unmanned), lb
Spacecraft at TLC, lb
12 276.8
10 641.8
98.0
40 633.7
30 848.8
94 499.1
3. SM RCS, EPS, and ECS weight losses
Lift-off to MCC-l 89.4
MCC-l to LOI-l . . . . . . 185.5
LOI-l to L01-2 30.5
LOI-2 to TEl 234.8
Mission Period Incremental weightloss, lb
•
••
••
•
••
25
TABLE 3-11.- SPS PROPELLANT SUMMARY
(a) May 17 launch, 72° launch azimuth,first opportunity injection
Item Propellant Propellantrequired, Ib remaining, Ib
Loaded -- 40 836.0
Trapped and unavailable 441.4 40 394.6
Outage 78.5 40 316.1
Unbalanced meter bias 100.0 40 216.1
Available for /::"V -- 40 216.1
Required for /::"V
TLMC (120 fps) 1 128.4 39 087.7
LOI-l (2866.3 fps) 23 004.0 16 083.7
LOI-2 (137.7 fps) 962.9 15 120.8
TEl (3252.2 fps) 10 507.8 4 613.0
Nominal remaining -- 4 613.0
Contingency /::"V (900 fps) 2 238.7 2 374.3
Dispersions (-30) 537.6 1 836.7
Propellant margin 1 836.7
26
TABLE 3-11.- SPS PROPELLANT SUMMARY - Concluded
(b) May 18 launch, 72° launch azimuth,first opportunity injection
••Item
Loaded
Trapped and unavailable
Outage
Unbalanced meter bias
Available for [).V
Required for [).V
TLMC (120 fps)
LOI-l (2856 fps)
LOI-2 (137.4 fps)
TEl (3693.5 fps)
Nominal remaining
Contingency ~V (900 fps)
Dispersions (-30)
Propellant margina
Propellantrequired, Ib
441.4
78.5
100.0
1 128.4
22 932.5
961.8
11 711.6
2 123.4
540.0
Propellantremaining, Ib
40 836.0
40 394.6
40 316.1
40 216.1
40 216.1
39 087.7
16 155.2
15 193.4
3 481.8
3 481.8
1 358.4
818.4
818.4
•
•~or a 51-hour lunar orbit time and a TEl [).V of 3199 fps,
propellant margin is 1884.3 lb. For a 61-hour lunar orbit timeand a TEl [).V of 2819 fps (3-day return), the propellant marginis 2852.9 lb. •
TABLE 4-1.- GROUND RULES AND ASSUMPTIONS
••
4.0
27
THE 1M RCS PROPELLANT ANALYSIS
1. Data for the LM RCS engine performance andpropellant requirements were obtained from reference 2.
2. All orientation maneuvers were assumed to bemade at 2.0 deg/sec.
3. All orientation maneuvers were assumed to be3-axis maneuvers.
4. Line-of-sight with the CSM was assumed to bemaintained in the minimum impulse mode.
TABLE 4-11.- LM RCS PROPELLANT SUMMARY
•
••
Description
Loaded ..
Trapped
Nominal deliverable
Gaging inaccuracy and loadingtolerance . • • . . . .
Mixture ratio uncertainty
Usable . . . . . . . . . .
Nominal mission requirement
Nominal remaining
Propellantweight, lb
633.0
40.6
592.4
39.5
17.0
535.9
359.7
176.2
28 •TABLE 4-111.- 1M Res PROPELLANT BUDGET
TIMt. t.VENI TITL.E SIC lilT L.H L.M L.MHR M - lL.IISI RCS HCS RCs
USED ~HT ~EfT
•IL.BSI IL.BSt 4II
U 0 OUTPUT PROPEL.L.IINT L.OAUINGs 9'19!t9. .0 633.0 100.
96 !>8 RCS HOT FIRI:: 9'19!t'l. !t.O 628.0 99.
98 l!i AGS ACCEL.t.RATIUN AND bYHO CAL.I 9'19!t2. 2.0 62,.0 99.- BRATIONS
'II 33 UNOOCKING 31J01. • 0 6;l6.0 99 •
911 '17 MNV H FOR INSP liND FOR FL.Y 31297. 10.0 616.0 97.
99 20 P20 RR L.OCI( ON 31293. '1.1 611.9 97.
99 28 MAINTAIN HR TWIICKINb II MIN 31292. • 8 61 I • I 91 •
99 29 IHU REAL.lbN sINGL.t. STIIH J12811. '1.1 607.1 '6.
99 29 If'1U REAL.lbN SINGL.E STAH 3128'1. '1.1 6U3.0 9!u
9'# 19 I HU REAL.lbN sINGL.t. STAH J1280. '1.1 ~98.9 9!t.
9'1 !>'1 HNyH TO lIlJRN AITlTUUE 31216. '1.1 ~'I'I.8 9'1. •,'# !>'f ATTITUDE HOL.U 31276. .0 lo9'1.8 ''I.99 !>'I ATTITUDE HOL.O 31276. .2 5'1'1.6 9'1.
99 S'I 2 JET UL.L.AGE 31270. !t.9 lollB.7 93.
9'1 S'I DESCENT OWIIIT INSI::RT. lIUHN 31036. .0 ~1I8.7 93.
99 !>'I HOMENT CONTRUL. 31029. 7.0 ~111.7 92.
9'1 li'l ATTITUDE HOL.D 310211. .!t ~111.2 92.
IUU 20 RR L.OCK ON 3102'1. '1.1 lo77.2 91.
IUU so MAINTAIN WH THACKING 2S MIN 31022. 2.S 57'1.7 91.
IUU lOO PITCH DOIIIN 9U UEG. 3102U. I .7 lo/3.0 91.
IUU SO YIIW L.EFT 18U ut.G. 31019. I.!t 57105 90.
IUU lOU YAlii RIGHT 18U LJEG. 31U17. I.S !i70.0 90.
IOU !>U PITCH UP '1O Dt.b. 31017. • I &70.0 90. •IOU !>9 MNyR TO BURN AlTITUDE 31013. '1.0 56S.9 89.
•
29
• TABLE 4-III.- LM RCS PROPELLANT BUDGET - Continued
TIME EVENT TI TLE SIC WT LM LM LHHft M IL8s) ReS Ncs ItCS
USED L.EFT LEFTIL8S) ILSSi III
• lUU !il9 ATTITUDE HOLD 310U. • 0 ilUt • , 8' •
IOU 59 ATTITUDE HOLD 31013. • 2 !il6S.7 89 •
100 il9 2 JET ULLAGE 31007. 5.9 !;il,.1 18.
101 6 DPS PHASING BUNN 303'''. .0 i59.8 18.
101 6 MOHENT CONTRUL 30392. l.i !ilS8.3 88.
101 6 AlT ITUDE HOLD 30392. .5 557.1 88.
10 I 6 YAW 30391. 1 ... !;b6 ... 88.
101 6 PITCH 30389. I .7 !ilS ... 7 88.
lUI 10 RR LOCI( ON 30385. ... 0 bSO.7 87.
1UI l8 MAINTAIN HR TI( ACI( I fiG 30383. 1.8 !iI't8.9 87.
101 28 IHU REALlliN SINGLE STAI( 30379. ".0 il ..... ' 86.
101 l8 II1U REALIGN SINGLE STAI( 30375. ... 0 !iI't0.9 85.
• 101 28 COAS CALI8RA!IUN 30371. ...0 i36.9 8S.
101 3'f RR LOCI( ON 30367 • 't.o bl2.9 8",
102 ilJ MAINTAIN TRACKING 303i9. 7.6 il2S.3 83.
1112 53 ORIENT FOR STAlolNli 30355. '1.0 b21 .3 82.
102 ilJ STAGING 8J6'1. • 0 b21.3 12 •
102 bJ START STAIoINCo 8362. 1.9 l»1,.5 82.
102 53 COMPLETE STAc.lNCii 8361. 1., !il17.6 82.
102 53 MNyR TO BUNN ATTITUDE 8360. .8 516.8 82.
102 5J ATTITUDE HOLD 8360. .2 516.6 82.
102 il3 ATTITUDE HOLD 8359. .9 !":tlS.7 81.
IUZ 53 'I JET ULLA(;E 8353. 5.7 !ill0.0 81.- -103 .. MOHENT CONTHOL INSE;KTION BURN 8116. 1.3 bD8.8 80.
• 103 .. NULL DYEL lFPS ,(AXIS 8115. ., !aU7.' BO.
•
30
TABLE 4-III.- •1M RCS PROPELLANT BUDGET - Continued
THIL EYENT TITLE SiC IT LM LM LMHR H (LaS) RCS RCS RCS
USED LEFT L.EFT(LBS) (L.aSt (15'
IUJ If NULL DYEL IFf'S lUIS 117". 1 • I 506.7 80. •10J If NULL. DYEL IFf'S UXIS 1173. 1.0 ~OS.7 .0.
10J If ATTITUDE HOLL> '170. 2.3 503." .0.
103 If IHU REALIIIN SINGLE STAR 1170. •• ~U2.S 7"
103 If IMU REALIIIN SINGLt:: STAR 116'. .1 bOI.7 7'.
103 If IHU REALlliN SINGLE STAM '161. • 8 bOO.' 7' •
10J l2 RR LOCI( ON 8167. .8 1000.0 7"
103 22 MAINTAIN KR TKACKING l~ MIN 8163. ".2 "'5., 78.
IUJ l2 MNyR TO BURN A!TJTUDE 81.l. • 8 "'5.0 78 •
IUJ l2 UTI TUO!:: HOLD 81.Z. .2 ..,..., 78.
IUJ 22 ATTITUDE HOLD 81.1. ., .. , ... 0 78 •
103 10 .. CSI RCS B~RN II U. 1... 2 "7'.8 7"
103 51f ATTITUDE HOLD 'IIJ. 2 ... .. 77 ... H.. •IUJ 10 .. RR LOCK ON 8112. • 1 "'6.6 75 •
10J 10'1 MAINTAIN KR TRACKING 1108. ... 1 .. 71.7 75.
10'1 23 PLANE CHANGE 810•• 2.0 '1.,.7 7'"
IU't b3 MAINTAIN KR TKACKINl'i 8101. ".2 ".5 •• 7...
10'1 !o3 MNyR TO BVRI'l ATTITUDE 8101. • 8 '1 .... 7 73 •- .
IU't 53 ATTITUDE HOLD 8100. • 2 ....... 73 •..
10'1 53 ATTITUDE HOLD 810U. ., .. 63.7 73 •
10" 53 CDH .z BURN 80'''. 5.7 .. 58.0 72.
10'1 103 ATTITUDE HOLD 80'1. 2 ... .. 55 •• 72.
10'1 !o3 UPDATE AGS wiTH RK DURING ATTI 107'. 12.3 .... 3.3 70.TUDE HOLD
IUS 23 MNyR TO BURN ATTITUDE 8078. .8 .... 2.5 70.-
I o lit 23 ATTITUDE HOLD 8071. • 2 ""2.3 70 • ••
31
• TABLE 4-111.- 1M RCS PROPELLANT BUDGET - Concluded
TI"'l t.YI::NI TITLE SIC IT L'" I." L'"HR '" eLBS ) RCS RCS RCS
USLD ~E'T ~EneLas) eI.BS, (1)-
•IDS 23 ATTITUDE HaLL! 8077 • ., ~"l ... 70 •
IDS 2' TPI I'CS BURN 8055. 1".2 'U7.2 .7.-105 2, ATT nUDE 1'101.0 8053. 2 ... "l ... 8 .7 •
IDS SI Ol'IENT To ATTITUOl IOSl. .a .. l ... O .7.-lOS St ATT ITUDE 1'101.0 803... 17.8 "0•• 2 ....10. 12 "'NyR TO BURN A!TI!UDE 8033. .8 ..US ... ....106 lZ ATT nUDE 1'101.0 8033. .Z '105.2 ....10' 12 ATTITUDE HOL.D 1032. ., .. 0 ... 3 ....-106 lZ TPF +Z BURN 7982. "'.7 JS ... 7 5••
10. 12 ATTITUDE HOLD 7'80. 2.'1 3SZ.3 5••
10' 12 ATT nUDE "'NYHlt AND LOS CONTHoL 7,5'1. 26.0 326.3 !il.
106 38 FOR". FLYINCi 7, .. Z. 12.0 311103 SO.
•106 S5 DOCKIN' 715 .. 6. "1.0 l73 • .l .. 3 •
NOTE: The APS propellant used through the RCS for moment controlduring the APS burn to depletion (assumes Z = 2.1 in. atc.g.burnout) is 139 lb •
••
10
0
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••
•
~ 33
5.0 THE DPS ANALYSIS
~
~
~
~
The assumptions for the DPS analysis are presented in table 5-1,and the DPS propellant requirements are shown in table 5-11. The loadingnumbers are from amendment 41 of reference 3. Burn requirements reflectthe following thrust profiles: DOl performed at 10 percent for15 seconds and at 40 percent for 11.7 seconds, phasing performed at10 percent for 26 seconds and F.T.P. at 10 percent for 15 seconds. Apropellant margin of 16 767 pounds exists.
TABLE 5-1.- ASSUMPTIONS FOR THE DPS ANALYSIS
1. Mixture ratio = 1.6 ± 0.024.
2. Propellant cost for engine and valve operation is 8.6 lb perengine start.
3. Buildup and tailoff cost is 19.15 lb of propellant per burn.
4. Propellant flow rates for various throttle settings were takenfrom reference 2.
34
TABLE 5-11.- DPS PROPELLANT SUMMARY
Item Propellant Propellantrequired, lb remaining, lb
Loaded 18 229.5
Trapped outside tanks a95.5 18 134.0
Tanked 18 134.0
Trapped inside tanksa 272.0 17 862.0
30 outage 214.5 17 647.5
Available for /::,.V 17 647.5
Required for /::,.Vb
DOl, 72.8 fps, 26.7 c 255.7 17 391.8sec
Phasing, 193.5 fps, 41.0 d 625.0 16 766.8sec
Propellant margin 16 766.8
aReference 3, amendment 41.
b .Includes nonpropuls1ve usage and buildup/tailoff usage.
c15 seconds at 10% and 11.7 seconds at 40%.
d26 seconds at 10% and 15 seconds at F.T.P.
••
•
••
••
•
••
35
6.0 THE APS ANALYSIS
The assumptions for the APS analysis are presented in table 6-1 .The APS propellant budget is presented in table 6-11. The data forusable propellant were taken from amendment 41 of reference 3 and assume a 50 percent APS propellant loading. The CSI was performed withRCS propellant for 10 seconds and with APS propellant through theRCS/APS interconnect for 22 seconds. Because of the APS burn todepletion, a zero APS propellant margin exists.
TABLE 6-1. - ASSUMPTIONS FOR THE APS ANALYSIS
1. I = 306.3 ± 1.5 sec.sp
2. APS propellant tanks are 50% loaded.
3. Ascent stage at earth lift-off weighs 8012 Ib (unmanned).
4. LM RCS and EECOM weight loss is 88.6 Ib prior to insertionburn .
5. Mixture ratio = 1.6 ± 0.0183.
6. Engine and valve operation uses 3.6 Ib of propellant per APSburn.
TABLE 6-11.- APS PROPELLANT SUMMARY
Item Propeliant Propellantre'luired, Ib reIllaining, Ib
Loaded 2631.7
Trapped outside tanksa 12.7 2631.7
Tankeda 2619.0
Trapped in tanksa 40.4 2578.6
Available for ~v 2578.6
Required for ~V
Insertion, 213.3 fps, 14.5 sec 182.1 2396.5CSI, 50.3 fps, 22 sec through interconnect 32.3 2364.2Burn to depletion 2364.2 0
Propellant margin 0
aReference 3, amendment 41.
36
7.0 ASSUMPTIONS AND RESULTS OF THE EPS ANALYSIS
The power levels of each component were obtained from reference 1;the cryogenic loading data were obtained from reference 3. However,because the component data for F mission were not available, the D mission component values were used. Cislunar heater cyclic rates wereused for TLC and TEC.
The EPS profile presented in figure 7-1 indicates that no seriousproblems exist. There are ample cryogenics (figs. 7-2 and 7-3) for theMay 17 launch date even with a one-tank failure at TEl. However, aMay 18 launch date will require power~ng the vehicle down during TECwith a tank failure. The cryogenics become marginal because the missionduration is increased by 24 hours. Figure 7-4 presents the total DCenergy that accumulates during the mission.
The metabolic 02 requirements were altered to 0.197 Ib/hr, rather
than 0.23 Ib/hr, based on postflight analyses of Apollo 7 and 8. Thisalteration corresponds to approximately 400 Btu/hr as compared with467 Btu/hr.
The 45 A-h rating mentioned in assumption 3 also was based on,postflight testing of the entry and post landing batteries.
••
•
••
••
•
••
TABLE 7-1.- ASSUMPTIONS FOR THE CSM EPS ANALYSIS
1. The system was assumed to operate with three fuel cells andtwo inverters.
2. The fuel cells were purged every 900 A-h.
3. Three entry and postlanding batteries were considered availableto supply the total spacecraft power required for entry, parachute descentand postlanding time. Each battery was assumed to have a 40 A-h capacityuntil splashdown, at which time the capacity was uprated to 45 A~h.
4. Two batteries were considered to be in parallel with the fuelcells during ascent and for each SPS maneuver.
5. No cryogenic venting was assumed.
6. The EPS hydrogen consumption rate (lb!hr) = 0.00257 x I fc .
7. The EPS oxygen consumption rate (lb!hr) = 7.936 x H2 •
8. Two SPS midcourse corrections were assumed.
9. Six battery charges were assumed: three on battery A and threeon battery B.
10. Five percent uncertainty in the EPS profile is included in thecryogenic requirements .
38
TABLE 7-11.- CRYOGENICS SUMMARY
Item H2 , lb O2
, lb
Loaded (two tanks) 58.60 660.2
Less residual 2.32 13.0Less 2.65% instrumentation error 1.53 17.5
Total usable 54.75 629.7
Prelaunch requirements
t minus 28.5 hr to t minus 6 hr at 40A 2.38 18.46-hr built-in hold at 40A .63 4.9t minus 6 hr to t minus 2 hr at 40A .42 3.3ECS requirements (3 hr) -- .7t minus 2 hr to t (hr) at 75A .39 3.1
Total 3.82 30.4
Mission requirements
EPS 35.21 268.5ECS -- 91.5
Total 35.21 360.0
Uncertainties
4.5-hr launch window at 75A .87 7.85% uncertainty 1. 76 13.4
Total 2.63 21.2
Total required 41.66 411.6
Margin 12.09 218.1
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The CSM ECS analysis will be supplied when the detailed operationaltrajectory time line is available .
••
•
••
8.0
43
THE CSM ECS ANALYSIS
4h
9.0 THE 1M EPS ANALYSIS
The 1M descent and ascent stage battery energy used for the nominalmission is 550 A-h and 432 A-h, respectively. Unusables defined in assumptions 2, 3, and 4 of table 9-1 indicate that the descent stage andascent stage have 62 and 21 percent energy remaining, respectively.
This particular analysis was performed by an individual block typeapproach rather than by the integration of crew procedures switch settings through the mission. As Apollo 10 becomes more defined, more detailed data will be published, including total spacecraft current profiles.
TABLE 9-1.- ASSUMPTIONS FOR THE 1M EPS ANALYSIS
1. Energy available for the descent stage batteries is 1600 A-hand for the ascent stage batteries is 592 A-h.
2. Energy unusable for the descent stage batteries and the ascentstage batteries because of lack of MSFN coverage is 21 A-h and 7 A-h,respectively.
3. Energy unusable for the descent stage batteries and the ascentstage batteries because of telemetry inaccuracy is 8 A-h for both vehicles.
4. Energy unusable for the descent stage batteries and the ascentstage batteries because of equipment power dispersions is 28 A-h and22 A-h, respectively.
5. The descent stage batteries would go on the line at lift-offminus 30 minutes with no recycle on the pad. They would go off the lineagain at transposition and docking.
6. All ReS quad heaters were considered to be on continuously for1 hour prior to the first ReS hot fire test.
7. All S-band equipment was considered to be on continuously frominitial activation until the completion of the mission.
••
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•
•••
•
••
•
••
10.0 THE 1M ECS ANALYSIS
The LM ECS analysis will be supplied when the detailed operationaltrajectory time line is available .
TAB
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12.0 REFERENCES
1. CSM!LM Spacecraft Operational Data Book, Volume I - CSM Data Book,Revision 1. MSC SNA-8-D-027, November 1968 •
2. CSM!LM Spacecraft Operational Data Book, Volume II - LM Data Book.MSC SNA-8-D-027, June 1968.
3. CSM!LM Spacecraft Operational Data Book, Volume III - Mass Properties,Revision 1. MSC SNA-8-D-027, November 1968.
4. Anderson, W. M.: Preliminary Flight Plan Apollo 10 AS-505!CSM-I06!LM-4.(Draft copy, February 14, 1969.)
5. Lunar Mission Design Section: Spacecraft Operational Trajectory forApollo Mission F, Volume I - Operational Mission Profile LaunchedMay 17,1969. MSC IN 69-FM-65, March 26,1969 .
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