..

N74-70733

Unclas00/99 16451

JUN 2 1969

May 9, 1969

,#

MANNED SPACECRAFT CENTERHOUSTON.TEXAS

j echnicaf library, Belicomm, Trrc..

Guidance and Performance Branch

MSC INTERNAL NOTE NO. 69-FM-126

REVISION 1 TO THECONSUMABLES ANALYSIS FOR TH E

APOLLO 10 (MISSION F)

SPACECRAFT OPERATIONAL

TRAJECTORY

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION

~8(NASA-TM-X-69660) REVISION 1 TO THE::::::CONSUMABLES ANALYSIS FOB THE APOLLO 10~~(MISSION F) SPACECRAFT OPERATIONAL:}~TBAJECTORY (NASA) 79 p

:.:.:.:":":":":.:":":":

~:~:~:~:~:~:~:~:~:~:~:~::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::.......................:":.:":.:":":":.:":.:"::::::::::::;::::::::::::::::::::::::::::::::::

~~???I~I:::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::.~":":":":":":.:":":":::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::.:.:.:.:.:.:.:.:.:.:.:::::::::::::::::::::::::.:.:.:.:.:.:.:.:.:.:.::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::.:.:.:.:.:.:.:.:.:.:.:.:::::::::::::::::::::::::::::::::::::::::::::::.:.:.:.:.:.:.:.:.:.:.:::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::.:.:.:.:.:.:.:.:.:.:.:.

~~~~If~I~~I:.:.:.:.:.:.:.:.:.:.:.::::::::::::::::::::::::.:.:.:.:.:.:.:.:.:.:.:........ .:.:.:.:.:.:.:.:.:.:.:.:

J·:·······r····.........

...

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MSC INTERNAL NOTE NO. 69-FM-126

PROJECT APOLLO

REVISION 1 TO THE 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,Walter Scott, Jr., and Richard M. Swalin

Guidance and Performance Branch

May9,1969

MISSION PLANNING AND ANALYSIS DIVISION

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION

MANNED SPACECRAFT CENTER

HOUSTON, TEXAS

A .._A. hA-~~dJ~-:;:f'~.M~~IVV"U. /,. , --

Marlowe D. Cassetti, ChiefGuid and P.erf nce Branch

•

•

•

••

FOREWORD

The following table summarizes the consumables requirements forthe Apollo 10 mission, May 18 launch. Percentages refer to nominalusage only and do not include dispersions and contingencies.

Consumable Percentage of available consumableused for mission planning

CM RCS 15

SM RCS 73

SPS 92

LM RCS 59

DPS 6

APS through rendezvous a 8

CSM 02 62

CSM H2 73

1M descent battery 27

1M ascent battery 71

1M ascent H2O 59

1M descent H2O 21

1M ascent 02 31

1M descent 02 8

~rom rendezvous through the depletion burn, the remaining 92%propellant is used.

The results were obtained from detailed consumables analyses per~

formed on the Apollo 10 systems and include Apollo 8 and 9 postflight

iii

data as well as Apollo 10 simulation data. A time history of totalconsumables weight loss is also presented. Consumables for all systemsanlayzed have adequate margins to complete the nominal mission.

The principal sources of data were the data books (refs. 1, 2,and 3). The analyses were based on the Apollo 10 draft final flightplan (ref. 4). The operational procedures described in this study arenot intended to define mission rules or crew procedures but are merelyan attempt to establish an estimate of the 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 System Division.

iv

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••

•

•

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AGS

APS

CDR

CM

COAS

CSI

CSM

DB

DAP

DOl

DPS

ECS

EECOM

EPS

F.T.P.

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

v

LPO

MCC

Ml

MPAD

MSFN

NR

ORDEAL

O2

PGNCS

PTC

RCS

REV

RR

SCS

SEP

SLA

SM

SPS

SPS-n

T, D, and E

TEC

TEl

TLC

T1MC

lunar parking orbit

midcourse correction

minimum impulse

Mission Planning and Analysis Division

Manned Spaceflight Network

North American Rockwell

orbital rate display, earth and luna.r

oxygen

primary guidance and navigation control subsystem

passive thermal control

reaction 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 injection

trans lunar coast

translunar midcourse correction

vi

••

•

,

••

•TPI

TPFI. t

WT..

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terminal phase initiation (of rendezvous)

terminal phase finalization (of rendezvous)

time

weight

vii

•CONTENTS

Section Page •1.0 THE CM RCS ANALYSIS. 1

2.0 THE SM ReS ANALYSIS. 2,

3.0 CSM - ACTIVE RESCUE OF LM. 23

4.0 THE SPS ANALYSIS . . . . . 27

5.0 THE 1M RCS PROPELLANT ANALYSIS 30

6.0 THE DPS ANALYSIS 37

7.0 THE APS ANALYSIS 38

8.0 THE CSM EPS ANALYSIS 39

9·0 THE GSM EGS ANALYSIS 47 •10.0 THE LM EPS ANALYSIS. 54

11.0 THE 1M EGS ANALYSIS. 58

12.0 TIME HISTORY OF CONSUMABLES WEIGHT LOSS. 64

13.0 REFERENCES . . . . . . 67

,

•viii •

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-J,

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Table

I-I

2-1

2-11

2-111

3-1

3-11

3-111

4-1

4-11

5-1

5-11

5-111

5-IV

6-1

6-11

7-I

7-II

8-1

8-II

9-1

TABLES

CM RCS PROPELLANT SUMMARY .. ... ..

GROUND RULES AND ASSUMPTIONS FOR THE SM RCSANALYSIS . . . . .. .

SM RCS PROPELLANT LOADING AND USAGE SUMMARY

SM RCS PROPELLANT BUDGET . . . . .

CSM-ACTIVE RESCUE OF NONPROPULSIVE 1M, SM ReS USAGEABOVE NOMINAL CSM SUPPORT OF 1M-ACTIVE RENDEZVOUS

MINIMUM SM RCS PROPELLANT REQUIRED FOR RESCUE ANDRETURN . . . . . . . . . . . . . .. . ..

SM RCS MARGIN AT UNDOCKING WITH CSM-ACTIVE RESCUE .

SPS PROPELLANT SUMMARY ....

ASSUMPTIONS FOR THE SPS ANALYSIS

GROUND RULES AND ASSUMPTIONS

1M RCS PROPELLANT SUMMARY .

ONABOARD READING OF RCS PROPELLANT REMAINING

1M RCS PROPELLANT BUDGET

ASSUMPTIONS FOR THE DPS ANALYSIS

DPS PROPELLANT SUMMARY . . . . .

ASSUMPTIONS FOR THE APS ANALYSIS

APS PROPELLANT SUMMARY . . . . .

ASSUMPTIONS FOR THE CSM EPS ANALYSIS

CRYOGENIC SUMMARY . . . . . . . . . .

ASSUMPTIONS USED FOR THE ECS ANALYSIS

ix

Page

1

2

2

4

25

26

26

28

29

30

30

31

32

37

37

38

38

40

41

47

•Table Page

9-II ECS OXYGEN REQUIREMENTS . . . . 48 •5410-1 ASSUMPTIONS FOR THE LM EPS ANALYSIS

58 "ll-I ASSUMPTIONS FOR THE LM ECS ANALYSIS

ll-II LM ECS CONSUMABLES SUMMARY . 59•

12-1 TIME HISTORY OF CONSUMABLES WEIGHT LOSS 64

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,

••x

••"',

FIGURES

Figure

2-1 SM RCS propellant profile

(a) Total.(b) Quads A and C(c) Quads Band D

Page

202122

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5-1

8-1

8-2

8-3

8-4

8-5

9-1

9-2

9-3

9-4

9-5

10-1

10-2

10-3

11-1

11-2

1M RCS propellant profile

Total CSM spacecraft current profile

Hydrogen remaining per tank, CSM

Oxygen remaining per tank, CSM

Total DC energy

CM bus voltage .

Potable water tank quantities as a function of missiontime . . . .. . .

Waste water tank quantities as a function of missiontime. . . . . . ...

CSM water generated as a function of mission time

CSM water evaporated for cooling as a function ofmission time . . . . . . . .

CSM water dumped as a function of mission time .

Apollo 10 descent stage electrical power profile

Apollo 10 ascent stage electrical power profile

1M-4 total spacecraft current

Descent stage water tank quantities as a function ofmission time . . . . . . . • . . .

Ascent stage water tank quantities as a function ofmission time . . . . . . . . . . . . . . . . .

xi

36

42

43

44

45

46

50

51

52

53

55

56

57

60

61

•Figure Page

11-3 Descent stage oxygen tank quantities as a function •of mission time . . . . 62

11-4 Ascent stage oxygen tank quantities as a functionof mission time 63

... . . . . . . . . .12-1 Spacecraft weight versus ground elapsed time 65

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REVISION 1 TO THECONSUMABLES 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~

Walter Scott~ Jr., and Richard M. Swalin

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 1-1.

TABLE I-I. - CM RCS PROPELLANT SUMMARY

ItemRCS propellant RCS propellant

used~ 1b remaining~ 1b

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 the SM RCSbudget.

1. The first and third MCC's (translunar) are executed asSPS burns with the third MCC trimmed with the RCS.

2. Passive thermal control is assumed to be in the PGNCSwide deadband control mode and to require 1 lb/hr, compared with1.1 to 1.7 lb/hr requirement on Apollo 8 in the SCS control mode.

3. The sixth MeC (transearth) is executed as an RCS burnof 5 fps.

----------- -----

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• 3

TABLE 2-11.- SM RCS PROPELLANT LOADING AND USAGE SUMMARY

•lJ,

Item

Expected loadinga

Initial outage caused by loading

mixture ratioa

aTotal trapped

Gaging inaccuracya

Deliverablea

Propellantrequired, Ib

15.6

26.4

80.4

Propellantremaining, Ib

1342.4

1220.0

~ata provided by Auxiliary Propulsion and Pyrotechnics Branch ofPropulsion and Power· Division.

•

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Nominal UsageLift-off through SPS burn to evade

S-IVB

Remainder of translunar period

LOI-l to undocking

Undocking through two REVS beyonddocking

Remainder of lunar stay to TEl

TEl through CM/SM separation

Outage caused by mission dutycycle mixture ratio shift

Nominal remaining

114.0 1106.0

199.5 906.5

116.3 190.2

224.2 566.0

66.3 499.1141.4 358.3

36.8 321.5

321.5

4·

TABLE 2-111.- SM Res PROPELLANT BUDGET •EVENT

.0

------- _.MISSION F 63529.

SM-HCS SM-RCS SM­us~o LEfT ~~

(LBS) (LBS) LEfT'- - ~-_.- ._-- -t-.-r--.0 .1220.0 lo.a... •

• 0 S~-RCS CHlCKouTNOfL.PROPULSI VE

63529. .0 1220.0 100 •........~_... -f--- -- ... 1------1--... -

"

3.1 TNANSPOSITIUN AND DOCKING

+X .arps, NULL TO 0.3 FPS63511.

3.1 ~ITCH TO ACQUIRE sIva• • d __ .ell CI:L.U.G-..O£G ..1-a~EG ISEC-----.-·

6351'+ • 2.3 1205.5....--- .--- I----....,~· __·-

3.1 ~ULL CSM AT 0.5 DtG/SEC 6J51~.

3.1 PHOTUGRAPHY ANO SYSTEMS fAMILIARIZAT 6J~5~.

lUNINCREASED PER APOLLO 9 HESULTS

3.1 NULL DELTA V 6350'+. 9.5 1195.6 98... --.----r-'-- -

•3.2 I r~DEX AND DOCKLANliLO SrUUy

26.0 1120.3

't.1 LM EJECTION PLUS R'S BURN'i JlT5. 5 SEC

't.!) SPS BURN TO EVADE SIVB- 3 A.X I S oRJ EN l p.G1iCS

7.9 1112.'+ 91.

,

91 •1108.3'I • 1

9'+267.

9 .. 263.

ATTITUDE HOL.O... s

I--- _ .._ .., +----- I-----+-- .._ .

• 1 1-1-07...a .. .9-1.

.81107.1 91. •91 •.0 1107.9

9 .. 18,+.

9~260.

1 1

TAIlOFF

STEADY STATE BURN

51'S BURN

BUU..D .Ue...-._...

... s

".s-+--- .--- ---_..-+---_._- .._--

DAMP SHUTDOWN TRANSIENT 9~la2. ..l...1 I 1Dit • 0 9 1 •

•

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•

••

5

TABLE 2-III.- 8M Res PROPELLANT BUDGET - Continued

TIME EVENT SIC lilT SM-RCS SM-RCS SM-( H'" ) (LaS) US EO LEFT Res

(L.BS) (LBS) LEFT.....--, - .

... 7 U~lENT TO MON ITOR SL I NGSHOT 'lfI78. .. ,. lJ 01_. 8 __'0.0.2 DE(;/SEC PGNCS

!:l.a P!)2 IMU ALIGN ''f17S. 2.8 1099.0 90...- ~ _._- ---._- -_. ---- ...__..- ~ ----_.

5.5 ORIENT FOR' NAV SIGHTINGS ,lfI71. 'f.l J..Q''f., _'0,SET 1-_._-_.-_.~---'- -------~----- - _. -- -- ---_.-

5.6 ORIENT FOR NAV SIGHTINGS 9'f167. 1f.1 1090.8 89,SET Z- '

~--- -------.._.__._~-_.__ .

5.7 ORIENT FOR NAV SIGliTINGS 9'f163, If,J J 0.8..6. ..6.. 8.9.S~T 3

-- .- ._---- ._--- --

~.8 ORIENT FOR NAV SIGHTINGS ''flS9, 1f.1 1082.5 89.coEr .. - --_. ----._. ---_._-------

!).9 URIENT FOR NAV SIGHTINGS 9'flS!:l, Ifa.l 10ZL.~1 U.SET 5

_._- ___'0_- -. _. .--- ----- -----

!).9 ALLOW FOR MIN DB HOLD DURING SIGtiTIN 9'f153. 1.8 1076.5 88.-c. ~ - --_.- ---- -- -- ----_._- --- ._- --_ .. - -

5.9 Sf-'ACECRAFT IN ~ANOOM DR I FT 9'flS3. & lOl.iu S .8a.

-_. - - ..- -- .._-'1.2 P!)2 IMU ALIGN 9'flS0. 2.8 1073.7 88.

f----.---- .. -- ----- .- 1---- .. -'1.2 MCC 1 , NO ULLAGE. NO TRIM 9lfl"'. ".L lO.il ... 1L 8L-_

-~-----.- ---- --- '-- --------- - -

9.2 ATTITUDE HOLD 5 OEG DB 9 .. 1.. 6. ... 1069,2 88.

n _

~ft I I r"\ ... 9ttltt3. .0 10~•• 2 IIA_..,.~ ~u_~ rt___ .___________

BUILD UP..

-~-------.._- -

9.2 STEADY STATE BURN I 1 ' .. 108. • I 1069.1 88.

9.2 U lI...llF'f '''067..1. I- _----.Jl 106A • .1 8A..- ,----- ---- --- ----

6

•TABLE 2-III. - SM RCS PROPELLANT BUDGET - Continued

-+----- - .. -- ..... --.-..----..-------+----- +----+----w.i-t-,-t

EliE r-IT

DAMP SHuT.DOWN TRANSltNT

SIC ttT

CLeS)

9li06&.

SM-RCS SM-RCS SM­\t5-[-o- ,t;t.f' I"CS

CLBS) CLeS) LEFT

•9'tOb3.12.0 ~S2 IMU ALIGN

._-~ ---_ ..._-2.8 106 ... 't 87.

- --- .. -...----- --- ·f------4-·---·-4---·-f--· - ..---

•

12.0 U~IENT FOR PTe3AXIS 0.2 nEG/SEC

9'tDS9. 4,f.O 1000.If 8-1-.

- ._- .- _. -9'tOS8. .li 1060.0 87.

.. _..-

9 Ii O-lio.. 12....1. WU---.l--~....._~ .- _. ----~ ..

9't0 .. 3. 2.8 10't ... S 86._.._. -- - I--

9 .. 0JCl. _......1 1.0 ...0.. ...~ •25.3 O~lE~T FOH NAil SIGHTINbSSET 1

21f.7 ~~l IMu ALIGN

12.0 ESTABLISH ROLL-- - 1---..._- .-..----------------~I----

I----_._~--_.__._------------

2S.'t ORIENT FOR NAil SIGHTINGS__ - - _....5.E T l-- __ . -_.... ...- _

9't03't... f--- - ---

._.-

't.l 1036.3 8S.- ..-.-f----- ..

••

83.

8~.'t ...1 1021.9

't.l 1028.0 81f.

3." 1020... e...----jf- --.----

9 .. 019.

9 .. 026.

_. ----- - -..- -- ---

9't012. ".1 101 ... 0

.-~------+-- ..-_t_---_t_--

. - -- ......-- -------------------+----+----+----+---f

26.5

26 ... SXT STAR CMEeK

26.S M1DCOURSE CORRECTION NO 2_ ..- f---M.H.ll..iL-l 0 BUR N AT I

2!:1.s O~lENT FOR NAil 51GHTINGSSET 3

25.6 OI<IENT fOR NAil SIGHTINGS_.--- <:;FT .'l - --_ ..

2S.7 OHIENT FOR .NAV .slGHTlNGSSET s

.

2S.7 ALLOW fOR MIN DB DUNING SIGHT1N(,S

•7

TABLE 2-111.- SM RCS PROPELLANT BUDGET - Continued

---- -._.

• 't 100S.2 82.

,p- 1013.8 83.

't.l 1009.0 83.--- ._--

't,l 100S.6 82.

SI1-RCS SH-RCSUSED _ - ~E.f T

(LBS) (LBSI

9 .. 00't.

914003.

914012.

9 .. 008.

SIC wT(LBS)

EVENT

DELTA VEL. NOMINALLY lERO

27.1 ORIENT FOR PTC3AXlS 0.2 OEG/SEC

27.1 lSTABLISH ROLL

2b.S

27.0 U~IENT FOR S-BAND REFL~CTIVITY TEST

SH­RCSLEFT• cr •.---+--.----- -------------.---------+-----If----+---........,H-a.+--;

TIME, HF< I

•'.- ---._- -_..- ----+-----4

32.0 PITCH AND YAW CONTROL 8..1 99'. S 82...

- . -

38.0 PITCH AND YAW CONTROL 93986. 8.7 987.8 81 •~. . --- -- --_._---- .. -----,--~ --_.- ---" - .- _.. - -- -_ ..- 1-----

• "S.U f'~2 IMU ALIGN 9398't. 2.3 98S.S 81.

--'45.0 O~ 1Ern Fo..~ PTe 93980. 't.l 98le't 80.

----- ._- .------_ . _.- -- - -~--

't!:l.O ESTABLISH ~OLL 93979. ... 981.U 80.

'tY.U PIT CH AND YAW CONTROL 93971. 8.0 973.0 80.- - - -------_. --- -.- - -_. -------.- -_. ..- _.~. - - --.._- r------. ._-

513.0 PS2 IHU ALIGN 93969. 2.3 970.7 80.

79..0 966.0

".1 96,.6 79.

__.... CI....lis. Ii Lz.9.

.- - f- _.-

93961.

939651.

--+-----+----+----t---.___.. 1L _9 .If.lt.t..

ATT I TUOF. HOL,D __

STE·ADY STATE BURN513.7

513.,

513., MIDCOURSE CORRECTION NO 3_ MNV_IL TO BURN All -+ • + -+- _

513.7 SPS BURN_-_ CII1 " UP

••

8

•TABLE 2-111.- SM RCS PROPELLANT BUDGET - Continued

---._-f- ----

5't.~ PITCH ANU YA~ CONTROL

5'1.1 [STABLISH ROLL

62.U PITCH AND YAW CONTHOL

'I

•

•SIC WT SM-HCS SH-RCS SI'I-

CLRS) USto-- - L~fT ReS(LBS) CLBS) LEfT

- --- --- t---- -.9389'h • i- Us.l _19.

-- -- -

93893. 1 • 1 96'f.0 7'1.-- --- . -- ----- -- -- -- -- -

93077. 16.2 9'f7.B 78.

- ----

93873. 'f.0 9'f3.8 77.._.- -- - ----

93869. 't.l -9-39.7 77.

-- - - -

93869. ... 939e3 77.- - -_.- --~ --'-- f-- -- ---

93861. 7.8 9 J 1. S lA.

9385J. 7.8 923.7 76.-- - --- . __. -_._-

938&1. 2 • ..1 _9.21. 't 76.

----- -- ..-- - --------

EVENT

-- ------- -------------4-

--- ----------

TAILOFf

-----

DAMP S~UT.DOW~ TRANSIENT

~.- - --

-- -.

S't.l OHIENT FOR PTe3AXIS 0.2 DEG/SEC

53.}

69.~ P~l IMU ALIGN

53.7 TV ALLOWANCE

53.7 ~cs TRIM TO O.S FP~

ALLUW 1.5 FPS TRIM

-- ------_._-------------._----------

72.1 TV ALLOWANCE

72tl ORIENT FOR C.Q.MM

,

•".0 908.8 7,+.

At • 1 917.3 75.- .-

_.'1 916.9 25.

--

.0 916.9 75.- --

_!....L --'-1-,.A 7~_

93838.

938,+6.

938 .. 7.--- ---- -------

PuNCS 938'+6.ATT HOLD a.s DEG DB

DEL VEL • NOM ZlRO7 I • 7

71 .7

71.7 MIDCOUHSE CORRECTION NO 'f

MN V~ l-O aURN.-411 -.

- -- 1-------. ---- .-._-------------- ---- ------- - ----It---- --- -- ---

72.1 SlXTANT STAR CHtCK1N~ 9383" 2.~ 'OluS. _1't.

•

•9

TABLE 2-111.- SM Res PROPELLANT BUDGET - Continued

ATTITUDE HOLD

7~.~ LUNAR ORelT INSERTIONJ-AXIs ORIENT

BURN 1 93832.

PGNCS

SM-HCS SJ04-RCS SM-USEO LEFT RCS

(LBS) (LBS) LEFT--- H&t

".1 902." 7 ...

... 902.0 7 ...

---- 1----- -

1 .3 900.7 7 ...9383U.

SIC WT(L&S)

EVENT

STAHT TRANSIE~T CONTHOL7~.7

T I ME.(HIO

.,•76.~ LOll, NO ULLAGE, NO TRIM 93627. .0 900.1 7 ...

STEADY STATE BURN 1 1 702lf J. .6 900d 7 ...

76.~ DAMP SHUT uor~ TRANSiENT•76.5 TAILOFF 70203.

70202.

.0 '00.1 7...---1------- -1--- --- .

1.1 899.0 1 ...

76.~ ~EV 1 ATTITUO[ HOLD 70200. I.!:» 8Yl.S 7 ...

7b.5 ~OLL lriO nEG FOR COMMUNICATIONS 70200. .s 897.0 7 ...

7b.7 MANEUVER TO LUNAR OBSERVATION ATTITU 7019b. 3." 893.6 73.[> l _ _. _ _ __ _

7b.3 ~lV 2 ATTITUDE HOLD 70193. 3.0 890.6 73.

-- -- -------- -

7ij.S HOLL TO IMPROVE LUNAR OBSERVATL~N

7/.2 MANEUVER TO SLEEP ATT fOR COHM TEST

883.3 72.

-,-" 882,9:12.

3." 887.Z 13.- ---- ---l~-.- I--- -

70190.

1019 U, __ .I Of

70186. 3 ...

70186.

- I-------~------+----+------------A TT nUOE HOLD

-79.Z LUI 2 LPO CIRC

_ .l1..Ci.YJL -r OBI/ H N A II••

10

TABLE 2-111.- 8M RCS PROPELLANT BUDGET - Continued ••

SM-~CS

\t5EO(L as)

7017 U

SIC tnCLaS)

SH-RCS SM­l~fT ~.,

(LBS) LEFT-- ------------- - . - -- --t------+- ---4-4-1"uH----t

8U.2 ULLAGEZ JUS A ANO C

--+-----t--

8U.2 Sf'S BUI-<N...8lJ.l L.D up.

70168.-- ------- --- --.._--. _. -- .._--f-------.--.

.0 867.7 71.

8U.2 STEADY STATE bU~N 1~.5 SEC PGNCS 69190.

80.2 TA[LOH 691S0. .0 867.S 11.------------------t--- ---- ------ ---- --+----"1I---f

DAMP SHUTDOWN TRANSIENT 1 ._1 BAA. /oj_ 71 ..

- -- . ---"-'

8U.2 REV 3 ATT[TUDE HOLDe- --1--- -_.

au.3 ROLL FOR COHM

691~6.

691~6.

------- - -

•8U.3 TV ALLOWANCE 691~2. ~.o 8S9.0 70..- ----...- .._..__ . -_. - -_._--- -- - ---'.--_.- . _._.- . _.- -..- --._-- -

8U.3 f'52 H1U Al.I GN - 69138. J.J:a ASS.S 10.

-.

81 .0 MI~V R TO L(lMK TRKG ATT 6913't. J.S 8S2.0 10.----_.~---

.- --_.__ .. - -'..- ----_.,,- '.-1----- - ----- -82.S REV 't ATTITUDE HOLD 691Jl. J.u 8~9.0 70. ...

--- I-- •.. -.-------- -- ----------- -._- ---+------1-----;----;

•69122.

69128.

80.~ REV 6 ATTITUDE HOLD

82.S R~OR1ENT TO SLEEP ATTITUDE

8't.~ H£V S ATTITUDE HO~O

----------------- ._.----------t------t-._. -----+----r- - --

88.3 REV 7 ATTITUOE~OLD

•

•II

TABLE 2-111.- SM Res PROPELLANT BUDGET - Continued

•..

•

•

EVENT

YU.3 Hev 8 ATTITUD~ HOLD

9~.3 ~~v 9 ATTITUO~ HOLD

9'4.3 IH:v 10 ATTITUDE HOLD

9S.S ~~ORIENT FOR LoMK STG

9 ~ • 2 I~ L. VII ATTl TU0 E Hal. l)

96.7 ORIENT TO UNDOCKIN~ ATT, ROl.L£O laoQ.lJi.. . _ _._.__ . _.

97.U YA~ LEFT 1'4 DEG

~--

97.U EXTRA ALLOCATION PRE-S£~ARATION

BASED OM APULLO 9 DATA

98.2 UNL>OCK

9B.2 srATION KEEP FOR l.M PHOTOGRAPHy

SIC ~T SM-RCS sr1-RCS SM-(LBS) USI:.O LEf T Res

(LBS) (LBS) l.EFT.. ._-..--- .-•. -_.-k-s)

69116. 3,0 8J3.S 68 •

69113. 3.D a30.~ 6a._ .. - -- -

69110. 3.0 827,S isa,

69106. 3.5 82,..0 68 •._-- f--.... -... - .. - ..

69103. 3,0 821.0 67.

69100. 3.5 8l7.S 67.. - ..-- '- _. -----

69098. 1.5 816.0 67.

69097. 1 .9 81'4.1 67._..- t-. .--

69073. 23.9 790.2 65.

38222. ".7 7eS.5 6'4... _.- ._-- .-- ---

382ll. 10.0 77S.~ 6'4,

---+---- ---------- ---- .. - -- ----. -4----~.---_+--.--

98.7 RlS SlPA~ATION BURN 2.5 FPS 3'193 •

--- -- --

767.7 63,- -

1.8

5.2 770.J 63.._.._-----+-_.- -_.-

3820't.

38207.

38206.

..- .. _._.-------.- _. _._-_ .

ORIENT FOR SEP BURN

98.2 REV 12 ATT HOLD IN MIN 08.. . -. --+----_._----_._._---

••

•TABLE 2-III.- SM RCS PROPELLANT BUDGET - Continued "-

TIME EVENT SIC WT SM-HCS SM-RCS SM ..(HRI (LaS) USfO- -tV'T ~~---

I L BS) rL as) ~~FT •-- -.._- .- -"- --- -- ---_ .._--- ----_.-- - ~----_.- -- .91;.8 I"lU ORIENTATION .1BI90. --L-L 71:"0.'\,,, -6..2-.

~ -

9Y.~ 1-'20 MANEUVER IPlfCHI J8187. l.1 7S0d 61 •-,-- -- . - . . . - -------- ---- ------ ._-_.

9Y.tJ I-'2Ll ORIENTATION MANEUVE:R I P lTtH I 3818 ... .1 ..1- 1~:]. 2 61.TIol I t1 TRKG A TT POST 001

-- - -- -

luu.2 REOIolIENT PITCH AND ROLL fOR COI1M 38182. 1.9 7445.3 61.- ._.-. - - .- ----- -- -- - -- --- ---_.- ._-- ._- -_. --_.- ._-

10U,2 ~I::.V 1J ATI HDL[) IN MIN UB 38111. S.2 1~~ -4--1.

.- - f--~ - .

IOU.7 MANEUVER TO TRACK PHASING BURN 38173. l.l 736.8 60... ._-._--- ~._----- ._-- ._ .. -_.- ---- _._- _. ._- ..'- - _._ ..•.•.. - ._-- "--.

•10U.~ 11-/11'1 TRKG ATT POSt PHASING l8170. 3..0 71-~.a 6-0-.

10l,2 tn 'J I 'f ATT HOLD IN MII~ DB J816!). 5.2 728.6 60.-- --- _._-~. -- ._._-- - - - ._-- -. --_.- --- - ~---_. .-

I02.~ P'fU ORIENT TO BACK up LM INSERTIUN B 38162.UIolN

,

722."38159. l.1

J81S6.

59.---- _.-- ------. --_.._-. '-'---'- --- - .....-.------ ... f--- --- -- ... --·-------+----t----

103.0 P20 TRIM TO TRKG ATT

lUJ.~ MANEUVER TO BACKUP CSI

IO't.l REV l~ ATT HOLD IN. MIN DB

lO'f,7 TRIM TO THK LM POSI PLA~E CHANGE

10J.b TklM To TRKG ATT PO~T C51. _._--~-

--_._-_. .. _..•._------------

I O~. U I1ANEU VlR TO BACK UP TP 1

--------

381S3.

381't1.

381't44.

-- -_. .-------- -

3.2 716.2 59 •

L.2 -.u~o U-.-- •-. ---" ----- r-- - .. -

3.2 707.8 58.

_~...Ll 7~... ,- t---.s..a.....

•

••-,

•

••

TABLE 2-III.- SM RCS PROPELLANT BUDGEI' - Continued

TIME EVENT 5/, WT SH-RCS SM-Res SM-tHIn (l.BS) Ui-Eo. ~ ~T ~cs-

(L.BS) (LaS) LEFT...I-'-~' -- ..10~.0 TRIM ATT TO TRACK L.M POST TPI 3813tt. 3,L1-1.01,6 _ 5.8.-

-- I- -

lOS." ORIENT TO MCCI ATT 3813!). 3.1 698 ... 57.-_._-- -- -- ---" ..-

10~." 11<11'1 TO TRKG ATT 38132. 3.2 6'5.2 57,

---- ._--~._- ---- -,,"-'._.- ---------""-- ----~-,. ,-

IDS." OHIENT TO Hce2 ATT 38129. 3.1 6'2.1 57.

10!)." TRIM TO TRI<G~ATT 38126..1 J. 1 "u..o.. ' 1:. ...----- -- -

-- -_._._--_.__ ....__ .-. ".'-_._... _- -. .. __ .- .- -, ~. -- - - - - -----106.0 STATIOI~ KEEP FOR Lf'I PHOTOGRAPHY 381 U. 10.0 67,.0 56.~,-,~. ----

106.U HI:.OR 1EIH. FOR poClSlNG-~ - .. 38112. 3,1 ~.6lit~ ss ...

., .-- - -- _. --1-----. .-----

106.1 Rl:.V 16 A1T HOLD IN MIN 08 38107. 5.2 670.7 55.-, --- -- _._. - -._---- - ,--_..- ..---_ .... .--- _.--_._-

1U6. 1 MAINTAIN BORESIGHT 38105. . 1.. 1 1- 6 U...o ss._

- ---_._- , 't--" ,-. f---,-106.1 E~TRA ALLOCATION DURING RENDEZVOUS 380'0. 15.0 65 ... 0 5 ...

--_._, gACrr\ ON APOI.L.O 9 DATA - --

106.3 CSM ACTIVE STATION KEEP AND DOCK "57 .. '. 25. L 6.28.9 --u.....

. -'- - - .. _. - -"--,._-- ------_. .. _. -- ._.-.- ..._-106.3 EXTRA ALL.OCATION POST DOCKING .. 5720. 29.0 5".9 ..,.

RACiF"O ON APOlLO 9 nATA

106.7 MAt!E~YEJL .JJLA PSaT 0 &TT fI!;717. -.3....2 &.... _~ ••0.5 DEli/SEC

-, f----108.1 REV 17 ATT nUDE HOLD .. 571 ... 3.0 593.7 "'.108.6 OHIENT fO~_SEP BURN --- ~.1tl.!..r-- _~.t.1 590.c;. fiAt.-

14

TABLE 2-111.- SM RCS PROPELLANT BUDGET _ Continued •TIME EVENT SIC wr SH-RCS SM-RCS SM."'flU (La SJ IJ5-ED LE-"T RC5

CLas) CL8S J LEfT;"f--- --f- - . _._- --- •. --_ .. --- , . ,

10ij.7 JETTISON LM 2FPS - 38016. _10 .. 9 I--S.7!J .,. _Ita. •108.7 M~VR TO ooSERVE LM 3801", 1.8 577.8 't7.

108.7 TV ALLONANCE 3801U.

108.7 MANEUVER TO SLEEP ATTITUDE 38DOY. 1.8 572.0 't7.-- - '---------- ---- ------ ---- --- - - - - - ---- -f- - ----1-----+----+

11U.O ~~v 18 ATTITUDE HOLD 38006. .1.0 ~9 .o..W7-.-

112.0 HEV 19 ATTITUDE HOLD

11".U H~V 20 ATTITUDE HaLU

- -

3800.1. .1.0 566.0 't6.-- ---. -- ~------- .- _._-.-

38000. 3...0 i ••• O- "6. •llb.U ~EV 21 ATTITUDE HOLD- -- - ---- -- --- -----

.17997. 3.0 560.0 If6.----------- ----- -- ------4-----4----.-

...

•

.1.0 SEt7.0 ....---

2.6 551f ... "S.

3.11 _SSl./i liS.

- --I .7 SAt9.7 AtS.

..B ~-S ....~ -!4i~

-----1---

31988 ..

J799't.

37986.

.l7!8S.

37991.-----~._--

1tY.9 HEV 23 ATTITuDE HOLD

11/.Y ~lV 22 ATTJTUDl HOLD

119.9 MNVR To SUBSOLAR pT

121.9 ~lV 2't ATTITUDE HOLD

- - - -- --- --- ------------- -----------

117.9 MANEUVER FOR PHOTO~RAPHY

.----. - -.--2.- .lUllIEI!VE.RS-_._

37982.-- -- -- -- - - -- -- ---------- ------- --~- --------------4--------lI-----4

122.S REORllNT FOR LANDMARKS3 TIMES PER REV

37979.

•

••"

•

"

••

15

TABLE 2-III.- SM RCS PROPELLANT BUDGET - Continued

T pH. EVENT SIC "'T SM-RCS SM-RCS SM-(HI'<) (LBS) USED LEfT ReS

(LBS) (LBS) LEFTN

f-- - ..122.51 fofOLL TO ACQUIRE HsFN 37979. .3 ._~'f2..ID 'llh

._..

123.9 tH:V ZS ATTITUDE HOLD 37976. 3.0 539.0 'f'f.-- ._.- ~-------~ ..----- -_ ..__ . _. _._._---_ .. 1-- - ._-

lZ'+.O REV 25 IHU ALIGN 37975. .8- -- 538.3 'f 'f...

- --- .- -- - --- - -- ----12't.~ RI:.ORIENT f'OR LANDMARKS 37971. 3.6 53'f.7 'f'f.

3 TIMES _P...E.R REV --_._----- -- '.~ ------

lZ't.!) ROLL TO ACQUIRE MSFN 37971. _,3 SJIt.If. _If.!i-e-

-------"12!).8 REV 26 ATTITUDE HOLD 37968. 3.0 531." "'f.

- f----- - ----'-'-- ._------._- ._ .._- --, --------- '_4·'

126.0 foIEV 26 IHU ~L1GN 37967. 11 8 530.6 '13.

... ---- ------ ..--- -- -126.5 foff-ORIENT FOR LANDMARKS 3796't. 3.6 527.0 'f3.

•.._.. - _. ___ ...3 J I t1£ SJ£B-..B.O -- --- _. -- --- . - - --

120.5 ROLL TO ~CQUIRE MSFN 37963. .3 526.7 'f3.

._- --12/.8 IH.V 27 ATTITUDE HOLD 37960. 3.0 523.7 'f3.

-_...- ~---_._--- ----------_ ..- ----_ ..- -- -

128.0 REV 27 IHU ALIGN 379S9. , • Q. SUI..8 ~t3.

- .. 1----

128.0 O~IENT TO REST ATTITUD£ 379!:tS. 1.7 52110 "3.

12S.0 REV 28 ATT HQLlL-- ...Jll§.§ • 3.n c;. ... n &I"- ----'-------

- - ~- ---- - - - ----- I---- -- -~. __._-- -~-~ ----._, .._--- -

128.0 folEY &9 ATT HOLD 37952. 3.0 515.0 'f2.

131 .9 MNYR FOR .. HOT O_~R ~Plir._ f-...Jll~O • .. LJ c;.''ll 'l &I" •- ------_.-

16

•TABLE 2-111.- SM RCS PROPELLANT BarrG~ - Continued- .. _-. - -

SIC ttT SM-RCS SM-RCS SM.- iLe 5 ) US~o-- -U...-T ~

(LBS) (LBS) LEFT

•_.0- ,.,379'18. 1~1 5-11-- 6 'i2-..13~.O M~¥R FOR PHOTO~RAPHy

~ ---~ .. ---- ------ ._-- - --'-'---

133.9 MNV~ Tu LDMK STG ATT--- ---- --- -- ---

379'16.--------- ----

1.7 S09.9 '12.-

133.9 ~ULL TO 4CQUIRE MSFN 379'16, .• 3 SO.9..S_ '12.

133.9 HEV 3U ATT HOLD 379'13.- 1-­

3.0 !»06.S "2.-- ---.-- ------------------ -----------. -- .._- ------+----1----+----+

13~.9 MNVR TO PHOTO ATTITUDE 319'11 .. 1.1 .---Sn~ ..B at 1 •

136.0 YAN 2X fOR PHOTOS----- --._---------------

136.0 HlY 31 ATT HOLD

13b.3 MNVR TO TEl ATT (HOLLED 180 DEGI1---- - -1----------_. -- ---.----------.--------

13b.3 O~IENT FOR TElROLL 180 DEG

- I-- ..-

37939. 2.1 S02.7 '11 •--- I- -_ ...- 1----- _ .. _-

37936. 3..0- !t 9-9.1 -~l-.. •- -

3793S. 1 .7 '198.0 .. I •._- --- I-- - _.- - - --'-

3793". .S ~91.~ '11..

137.3 SPS ~UR~

___ aU 11.0 lip . _ _

_.- - ----- _.-

136.3 - ATTITUDE HOLD

••

.'1 .. 97.1 'I 1 •'-- ----

lS...2 'Ul.9 39,

- -

.0 '181.9 39.--

.3 -U1 • .6 -.19... -

• 0 '181t6 39 •

281S 1.

28711.

3793'1.

Z8710,

31918.

3791S.

-- 1-------- ~-

.-4-----..... ------+----...--

O~MP SHUTOO~N TMAN51tNT

TAILOFF

STEADY STATE BURN 136 SEC PGNCS

--- .-137.3

136.3 ULl.AGE2 JlTS B ANL) 0

137.3

137.3

• 17

TABLE 2-III.- SM Res PROPELLANT BUDGET - Continued

• TIMI:: EVENT SIC ilT SM-~CS sr1-RC 5 SM-( H 10( ) (LBS) USEe L.EFT Res

(LBS) (Las) L.EfT- - - - _. -_._- -_.. ----"- ---- ------- f--------~--

131.3 TV ALLO~ANCE 28706. 'f.0 't16.!) 39.

138.,+ P!',)l. IMU ALIGN 2870'" 1 • S "'75.0 39.- - .--- .. _.. ---

_138.5 l) f.l I t:: NT FOR PTe 2870'" .6 '+7,+.J 39.3AXlS 0.2 Dt.G/StC

13M.S E~fAULISH ROLL 28703. .2 '+7".2 39 •..- .. - --

138.!) PITCH AND YAt/ CONTROL 28692. 1 1 • U '+63.2 3a.

• ISU.U P~2 HIU ALIGN 28691. 1.5 '+61.7 38.-- - - . _•. ---._- -- --- -- f- ._.-

~.. - .-

150.U CISLUNAr. NAVIGATION !> STAR ~ETS 286S!;), !).9 't!;)S.8 37.

I 5 U • II CISLUNAR NAV SIGHTI~GS TorAL OF 9 5 28681. '+.2 '+51.S 37.EIS --- -- _. ---.._- --..

150.0 ATT CONTROL 28679, 2.2 '+'f9.,+ 37.

152.3 MIDCOU~SE CORRECTION NO 5 28677. 1.5 '+'+7.9 37._.!'1N\I.ij TO-BURN AtL__ -- ---- ---- - -

152.3 ATTITU:l1:: HOLD 28677, .3 ..... 7.b 37.

• 15l.3 OI::L VEL • NOli lI:. R0 28677. .0 '+ ... 7.6 37.- -- --- _.. --_. -".._.. --- -- ----.-- --- . - - ._-- ----- - . ---- -- '-- --

15.2.3 TV ALLO\'l ANtE 28673. 't .. D 'HU. b 36,

.

ISJ.u lIRIENT FOR PTe 28672. .6 ... .. 3.0 36.

• ---- lAXl S U,2 DEli'SEC ---- - -

ISJ.U EST, 0.3 DEG/SEC ROI.1. ZB612. .-L2 1l'l..2-e a. -3...-_.

18

TABLE 2-III.- SM RCS PROPELLANT BUDGET - Continued

TIME EVEt\JT SiC. NT SM.fo(CS SM.RCS 51'1 ..eHI< J (L8S) ust:.o LEn IH:S

(LBS) (LBS) LEfT- ~~

1~3.u fo> ITCH ~ND YA·~ cunTROL 2866U. 12.0 '+Jo.t:1 3S.

1':I6.U /-,!;)2 IMU AL I GtJ 28659. I .!) '+29.3 3~.

16!;).U CiSLUNAR I~AVIGATION 2a6!;»). S,9 '+23 ... 35.5 T AR/Ll!NAR HO~llON ORIENT

16!;).~ ORIENT FOR PTe 28652. .6 '+22.R 35.:1"".1 S 0.2 D~'/St:.C

16!;).5 ESTAHLISH ~OLL 28b!;),l. .2 '+22.6 3:..

165.5 PITCH AND YA'II CU"JT~OL 286'+6. b.O '+16.6 3 ...

171 • U PSZ !MU AL I GN 286'+'+. 1 • S '+IS.1 31i.

III • U IJ A V SII:,HTIN~S 2861.1-'. .7 '+11i.5 3,+._.- - -- I-- -.-

17 Z. U (l ~ I t:: r.. T rOR PTe 2861i3. .6 '+13.1:1 3,+.3AXlS '.1.2 OlG/Sl:.t

172.0 EST. 11.3 nEG/SEC ROLL 28b1i3. .2 '+13.b 31i.,..--

I 72. U PITCH AND YAiN CUNTlo/OL 28639. Ii.O '+09.6 3,+.

17~.U fo>~l IMU ALIGN 28b37. I.!;) lioe.l 33._. -

176.2 tl I UC0 lJ RS E (ORRE.CTIlJN NO 6 28036. 1.S li06.6 33.~'NV R TO BURJ~ ATf

176.2 ATT HOLD .5 DEG DB P~NCS 26636. .'+ "Ob.2 33._.. --- - -- -- - - -

176.2 ~c~ -x TRANS 5 fP~ 28b19. 16.e 389.5 32.

••

•

••

••

•

••

19

TABLE 2-III.- SM RCS PROPELLANT BUDGET _ Concluded

TI Ml EVlNT SIC it r SM-RCS SP1-RCS S/l1-( t~ H ) (LaS) USEO UF1 ~5

(LBS) (LBS) LEFT~-- - ~-- ---- - ~ ----- - - I. ,.

176.7 () k I E.t~ T FOR PTc 28b18. •• _J8B., u.3AXl5 0.2 nEG/S!:.C

176.7 L5TAt:lLISH ~OLL 2ett18. .2 381.7 32.- - ~

17t).7 PIT eli AND Y Ail CL)IJTROL 2860<1. 9.0 ~JL9L7 31..

-187.0 PSl IMIJ ALIGN 28007, 1 • !:I 378,2 31 •

- - - -

IA/.Ll TV ALLOwANCE 28603. '+.0 _31'i.L ~

18 H. J 11 I i) C[) Uf~ SE COR ~ ECTI U~1 NO 7 28602. 1.S 372.6 3 I ,t.lNVW TO a.uWN ATT ~- __ w_ -

18 H • :\ All HOLD .s OE.~ l>B PGNCS 28602. ,3 312, .. 31 ,

- ---18ti.3 [)C.L VEL .. NOM ZI;.RO 28002. • 0 372 ... 31 •

-- _._---~-

189.0 I"!l2 IMU ALIGN 28600. 1,6 3ZD, a Jo.

189.0 t"ANEUVER TO ~EENTRY ATTITUDE 28599. I • ~ 3'9.3 30.

189.0 ATTITUDE HOLD o.z OEG DB ScS 28598. .8 3Ila.!;, 30.

- --18Y.U PITCH TO AC(./UIRE HOKIZON 28597. .7 367,8 30.I-- - -- - ---- I----

189.U YA~ "IS DEb 28596, .7 361... 2 30.

189.0 ATT HOLD .s DEu DB PGNCS 28596. ... 3••• 8 30.- ~----t------- -- - -- -------- - ------- --

1<11.6 CHISM SEPARATION 1611J, ~..J.s ls..a. '\ '1'1_DlLTA VEL-3 FPS

~xcept for mission duty cycle mixture ratio shift, (table 2-11),this propellant is usable.

20rI

ISP

Sev

asiv

em

aneu

ver

MC

C-3

II

I0

020

4060

1220

1200

-e10

000

'> C c"E

n;Q

J~OO

uE

....Q

J

QJ

....C

-"E

0'>

~

CQ

J60

0.0

,~

C-

O'>

0 ....-0

C-

....V

I~ 0

U.c

a:::

c 0~ V

IQ

J

.c ~20

0V

'l::::

>

o

100 80 60 40

II

ILO

I-l

Und

ockI

TEl

II

Dock

II

II

~O

100

120

140

11)0

Gro

und

elap

sed

time,

hr

(al

Tota

l.

Figu

ret..

~.SM

RCS

prop

ella

ntpr

ofile

.

180

200

[ota

ll

220

1\) o

240

••

••

•

••

••

•

c C1>

U ~60

0,

c: ""tV "" -=40

~ tV a .0 c: 0

21H

,1I

II

IU

ndoc

kI

SPS

evas

ive

man

euve

rM

CC

-3LO

I-lI

Dock

TEl

II

II

II

0

C16

0..!

!! ~ a ... 0.

120

V'> u 0::: :E

eoV

'> '" :c tV '"«I

=>

0

I~5[

100

~:~h

_~.

c: c: ~20

0~

••

••

•

"["o

re--_

.-_

.-

II\

)

'::

~.

,I\

)

eo""c: c:

C;;

200

EC1

>u

C1>

......

8.60

C tV16

00

,c:

8-'0

.a

tV...

""0

."C

«l

~V

I12

0...

ItV

Ua

0::

.0

ic:

:E0

-,V

I80

~.-

.0

20tV '" =>

«I oL

o0

20«I

60SO

100

120

1«1

160

ISO20

022

02«

1

Gro

und

elap

sed

lime,

hr

Ie)

Qua

dsB

and

D.

Figu

re2.

1.-

Con

clud

ed.

•

The critical consumable for a CSM-active rescue of a disabled 1Mis the SM RCS propellant. The rescue situation analyzed here is onein which the CSM must begin rescue with the insertion burn. The 6V re­quired from the SPS (320.5 fps) is well within the 900 fps missionflexibility 6V available (section 4.0: The SPS Analysis).

••

3.0

23

CSM - ACTIVE RESCUE OF LM

•

••

The minimum quantity of SM ReS propellant remaining at undockingfor initiation of the nominal LM-active rendezvous must be sufficientto provide for a CSM-active rescue of a nonpropulsive 1M and for thetransearth phase of the mission. Two rescue situations are consideredhere.

1. The LM is unable to perform insertion, CSI, CDR, and TPI, butthe malfunction does not preclude use of the LM RCS for the brakingphase.

2. Same as above, but the LM is also unable to perform the braking.

Based on an appraisal of the likelihood of various failure modes,it is felt that case II is unduly conservative, and it has been recom­mended that case I be the redline requirement for the decision ofwhether or not to commit to the rendezvous. Case II is included forreference purposes.

The propellant budget for the CSM support of the nominal 1M-activerendezvous has been increased considerably over the budget of reference 6.This increase reflects Apollo 9 postflight results and Apollo 10simulator data. If a CSM rescue occurs, this propellant would be avail­able for those activities common to the nominal CSM support of the1M-active rendezvous and the CSM-active rescue.

Above the nominal rendezvous usage, the propellant quantitieslisted in table 3-1 for case I must be reserved for the rescue situation.Because the total allocation for the nominal CSM support of the 1M-activerendezvous is 161.3 pounds (table 2-111, undock through dock) with anextra allocation for the rescue of 190.2 pounds (table 3-1, case I),the total propellant available for the rescue rende~vuus is 351.5 pounds(of ~Thich 161.3 Ib are included in the nominal bUdget) with the LM doingthe braking.

The minimum SM RCS propellant requirements for rescue and safe re­turn are summarized in tables 3-11 and 3-111. Case I is recommended toestablish a mission redline. It is based on a rescue that includes1M-active braking followed by an immediate return to earth (deleting sub­sequent lunar orbit activities and nonessential transearth TV allocations).

24

Case II shows the margin for the 1M-active braking followed by comple­tion of the nominal mission. Case III is based on the CSM braking withimmediate return. Case IV shows the CSM braking completion of thenominal mission. As shown in table 3-111, all but case IV show a posi­tive margin at undock.

••

•

••

•

•

••

25

TABLE 3-1.- CSM ACTIVE RESCUE OF NONPROPULSIVE 1M,SM RCS USAGE ABOVE NOMINAL CSM SUPPORT OF

LM-ACTIVE RENDEZVOUS

Propellant used Propellant usedfor Case I for Case II

(LM braking) , (CSM braking) ,lb lb

RCS usage for SPS insertion burn

Ullage, four jets, 10 sec plusSame as2 sec overlap 17.3case I

lVJ.oment control 2.0

RCS usage for SPS CSI

Ullage 17.3Moment control 2.0 Same asTrima

10.4 case I

RCS usage for SPS CDR

Ullage 17·3 Same asMoment control 2.0case I

Trima13.0

RCS usage for SPS TPI

Ullage 17.3Same asMoment control 2.0case I

Trima10.4

Subtotal 111.0 111.0

Braking -- 150

MCC's and LOS b69.2 69.2control

Mixture ratio allowance 10.0 10.0-

Total 190.2 340.2

~eference 7.

bReference 8.

26

TABLE 3-11.- MINIMUM SM RCS PROPELLANT

REQUIRED FOR RESCUE AND RETURN

[Case I, LM braking]

••

Mission phase

Undock

Postinsertion

Post-CSI

Post-CDH

Post-TPI

Postdocking

TEl

Minimum propellantrequired, lb

581.2

497 .2

461.4

429.1

384.6

229.7

166.8 •CM/SM separation O·

TABLE 3-111.- SM RCS MARGIN AT UNDOCKING

WITH CSM-ACTIVE RESCUE

Case Active vehicle Mission activities Propellant marginno. for braking post-rendezvous at undock, lb

I 1M Immediate return 209.0

II 1M Nominal mission 130.7

III CSM Immediate return 59.0

IV CSM Nominal mission -19.3 ••

The budget presented in table 4-1 is for a May 18 launch, 72°launch aximuth, first opportunity injection, and fast earth return. Theassumptions used to prepare this budget are presented in table 4-11.Engine performance characteristics are taken from reference 1, and thebV requirements are taken from reference 9.

••

4.0

27

THE SPS ANALYSIS

•

••

Note that the mission flexibility bV of 900 fps has been used inaddition to the fast return. In real time, however, it is highly likelythat a slower return would be performed if the 900 fps had been usedprior to TEl (e.g., for 1M rescue). Hence, the margin of 762 poundsshown in table 4-1 assumes both a fast return and use of the 900 fpscontingency bY .

28

TABLE 4-1.- SPS PROPELLANT SUMMARY

,

Item Propellant Propellantrequired, Ib remaining, Ib

a 40 808.7Loaded --Trapped and unavailable

a 441.4 40 367.3Outage 78.5 40 288.8

Un-oalance meter bias 100.0 40 188.8

A-raila-Dle for !:::.V -- 40 188.8

Required for !:::.Vb 39 049.1TLMC (120 fps) 1139·7

1,01-1 (2978.35 fps) 23650.8 15 398.3JJH-2 (138.5 fps) 952·9 14 4!+~~.4

TEI C(3622.5 fps) 11101.4 3 )44.0

r~ominal remaining 3 544 .cMission flexibility !:::.V (900 fps) 2234.1 1 10S'·9

Dispersions (- 5J) 348.4 761.5Propellant margin 761.5

~eference 3.

bIncludes 19.7 fps for evasive burn and 57.0 fps for nominal MCC-l.

cApproximately 9100 Ib are required for I-day later return.

••

•

••

••

29

TABLE 4-11.- ASSUMPTIONS FOR THE SPS ANALYSIS

1. Launch was on May 18, 1969 at a 72° launch azimuth with afirst opportunity injection and a fast earth return.

2. Each SPS engine start used 14.4 lb of propellant in non­propulsive losses.

3. Spacecraft weight:

5. CM equipment jettisoned with the ascent stage in lunar orbitwas 193.4 lb.

•

..

••

CM, Ib .

SM, Ib

SLA ring, Ib

Tanked SPS, Ib

LM (unmanned), lb.

Spacecraft at TLC, lb ..

4. SM RCS, EPS, and ECS weight losses

Mission Period

Lift-off to evasive maneuver.

Evasive maneuver to MCC-l

MCC-l to LOI-l.

L01-1 to LOI-2.

LOI-2 to TEL .

12 276.8

10 641.8

98.0

40 606.4

30 848.8

94 471. 8

97.9

53.4

404.8

26.3

231.8

30

5.0 THE 1M RCS PROPELLANT ANALYSIS

TABLE 5-1.- GROUND RULES AND ASSUMPTIONS

1. Data for the 1M RCS propellant re~uirements wereobtained from reference 2.

2. All orientation maneuvers were assumed to be made at2.0 deg/sec.

3. All orientation maneuvers were assumed to be three-axismaneuvers.

4. Line of sight with the CSM was assumed to be maintainedin the AGS minimum impulse mode.

TABLE 5-11.- 1M Res PROPELLANT SUMMARY

DescriptionPropellant, Ib

Re~uired Remaining

Loaded 633.0

Trapped 40.6

Gaging inaccuracy and loading tolerance 39.5

Mixture ratio uncertainty 17.0

Usable 535.9

Nominal mission requirement 318.2

Nominal remaining 217.7

••

•

••

••

•

••

31

TABLE 5-111.- ONBOARD READING OF RCS PROPELLANT REMAINING

Event Percentage of propellant Percentage of propellantremaining in system A remaining in system B

Post-DOl 96 94

Postphasing 93 89

Postinsertion 85 82

Post-CSI 79 75

Post-CDR 75 71

Post-TPI 69 65

Postbraking 54 51

Postdocking 51 47

• ;;

TABLE 5-IV.- LM RCS PROPELLANT BUDGET - Continued

TIME EVENT TI HE SIC WT UI lV l,..

•HRS r~ (lBSI RCS ReS Res

USED lEFT lEFT(lBSI (lOS) ( & )

lC~O 46 ATT nUDE HOLD 30314. .5 56~ .6 89.

1CO 46 YA,~ 30313. 1.5 560.1 88.

100 4,., PITCH 30311. 1.8 558.3 83.

lCO 50 RR LOCK ON 30307. 3.9 55',.5 58.

1 cr: 50 MAINTt.rr~ RR TRACKING 30306. .7 553.8 87.

lei 0 INU REALIGN STAR 1 30302. 3.9 549.9 87.

1G1 0 H1U REALIGN ST tlR 2 302119. 3.9 546.1 86.

lOl- a CGAS (t.L i BR IH ION 30295. 3.8 542.2 86.

•J0' 1:) RR LOCK ON 30291. 3.8 538.4 85.

1n 10 MAINTAIN RR T~ACK INC 30289. 2.0 536.3 85.

102 10 RR LOCK ON 30285. 3.8 532.5 84.

102 10 MAINTAIN RR TRACKING 30784. 1 • It 53l.1 84.

102 33 ORIENT FOR STAGING 30280. 3.9 527.3 83.

102 "33 STAGING 8378. .e 527.3 83.

10L 33 START STAGING 8377. 1.9 525.4 '33.

102 33 C01~PLETE STAG I NG 8375. 1.9 523.6 8'2-' .1C2 '37 j,\NVR TO BURN ATT I TUDE 8374. .9 522.7 '33.

lei 37 ATTITUDE HOLD 8372. 2.2 520.5 82.

102 43 2 JET ULLAGf 8369. 2.8 517.7 82.

• .,.. ... , ..r·~ctl [NT CONTR.OL T ~l C t: D T T nI.l BURN 8197. .9 516.8 8Z";'.I.vt.: .. = ... I'" """ r-" , & ... ~ I 'I

1.02 43 NULL CVEL lFP S XA XI S 8196. .9 515.9 82.

102 43 NULL DVEL lFP S YA XI S 8195. 1.1 514.8 81.

le 2 43 NULL eVEl lFPS lA XI S 9193. 1.0 513.7 8).•

• Ifl2 43 YAW 81Q3. • 3 513.t. 81 •

1C' 2 43 PITCH 8193. • 2 513.2 ''1 •

34~ •TABLE 5-IV.- LM RCS PROPELLANT BUDGET - ContinuedTIt-lE EVENT TITLE SiC WT LM LtJ L/ll

HRS M ( LBS) ReS RCS RCSUSED LEFT LEFT

(LBS) (L BS) ( f. ) •1~2 43 ATTITUDE HOLD 8191. 2.3 510.9 81.

l02 50 IMU REi'LIGN STAR 1 8190. • a SiO.O n,(J.I..

Ie? 50 Ito'lJ REALIGN STAR 2 8189. .8 509.2 80.

1 C2 50 I/o1U REALIGN STAR 3 8188. • 8 508.3 80.

103 0 RR LOCK ON 8187. .8 507.5 80.

103 a MAINTAIN RR TRACKING 8180. 6.8 500.7 79.

103 27 I.1NVR TO BURN ATT lTUDE 8180. .8 499.~ 19.

lC327 ATT lTUDE HOLD 8179. .Q 499.0 19.

)03 33 CSI RCS BURN 81. 33. 14.2 484.7 77.

103 33 ATT nUDE HOLD 8131. 2.3 482.4 76.

•!03 37 RR LOCK ON 8130. .8 481.5 76.

1(\3 37 MAINTAIN RR TRACKING 8125. 4.6 417 .0 15.

104 ! PLANE CHANGE 8123. 2.0 415.0 75.

104 5 MAINTAIN RR TRACKING 811t. 11.4 463.6 73.

104 25 ~'NVR TO BURN ATTITUDE 8111. .8 462.7 13.

104 25 ATTITUDE HOLD 8109. 2.2 460.5 73.

104 31 C()H +Z BURN 8105. 3.4 457.1 12.

1C4 31 ATT nUDE HrJlD 8103. 2.4 4S4.7 72.

104 35 MAINTAIN LCJS 8095. 8.0 446.7 71-0.-

105 <; TPI Res BURN 8070. 24.7 422..0 67. •lC~ 9 ATT (TUDE HIJLD 8068. 2.4 41S.7 66.

IO!:> 12 OR lENT TO ATTl TUDE 8067. .8 418.8 66.

105 12 MAINTAIN LOS S063. 4.6 414.3 05.

le5 I.e Mec AND BRAKING 8013. 49.1 365.1 58.

105 40 ATTITUI)E HGLD 8011. 2.4 3.2.8 57. •

• 35'

TABLE 5-IV.- LM RCS PROPELLANT BUDGET - Concluded

• T It4E EVENT TITLE SIC WT LM Lr-' LMHS M (LBS) RCS RCS ReS

USED LEFT LEFT(LBS) (LBS) u:.)

1C5 40 HTITUDE MNVRS AND lCS CONTROL 7985. 26.0 336.8 53.

lC5 55 FOR FLYING 7913 • 12.0 324.8 51.•

106 70 U' CO" TROL DURING CSI-l ACTIVE 0 79 ~3. 10.0 314.8 50.OCK.

lC7 C TRANSFER EQP TO U1 8243. .0 314.8 50.

107 <J UNDOCKING 7778. .0 314.8 50.

lea 39 APS BURN TO DEPLE. ')47'5. .0 314.8 50.

•

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The assumptions for the DPS analysis are presented in table 6-r,and the DPS propellant requirements are shown in table 6-11. Propellantloads are taken from reference 3. Burn requirements reflect the followingthrust profiles: DOl performed at 10 percent thrust for 15 seconds andat 40 percent thrust for 14.9 seconds; phasing performed at 10 percentthrust for 26 seconds and at F.T.P. for 19.3 seconds. There isa propellant margin of 16 865 pounds.

••

6.0

37

THE DPS ANALYSIS

•

TABLE 6-1.- ASSUMPTIONS FOR THE DPS ANALYSIS

1. Mixture ratio = 1.597 ± 0.0141 (ref. 10).

2. Propellant cost for engine and valve operation is 8.6 Ibper engine start.

3. Buildup and tailoff cost is 19.15 Ib of propellant per burn.

4. Propellant flow rates for various throttle settings weretaken from reference 2.

TABLE 6-11.- DPS PROPELLANT SUMMARY

Propellant Propellantrequired, Ib remaining, Ib

Loadeda 18 264.2

a 198.2 18 066.0Trapped

30 outage 125.2 17 940.8

Available for b,V 17 940.8

Required for b,Vb

29.9c 308.2 17 632.6DOl, 71.1 fps, sec

Phasing, 195.6 45.3d

767.8 16 864.8fps, sec

Propellant margin 16 864.8

• ~eference 3.

b 1 . and buildup/tailoff usage.Includes nonpropu Slve usage

c15 seconds at 10% thrust and 14.9 seconds at 40% thrust.

d26 seconds at 10% thrust and 19.3 seconds at F.T.P.

•

38

7.0 THE APS ANALYSIS

The assumptions for the APS analysis are presented in table 7-I.The APS propellant budget is presented in table 7-II. The data forusable propellant were taken from reference 3 and assume a 50 percentAPS propellant loading. The CSI was performed with RCS/APS inter­connect for 22 seconds. Because of the APS burn to depletion, thereis a zero APS propellant margin.

TABLE 7-I.- ASSUMPTIONS FOR THE APS ANALYSIS

1. I = 308.5 ± 3.6 seconds (ref. 2).sp

2. APS propellant tanks are 50% loaded.

3. Ascent stage at earth lift-off weighs 7959 Ib (unmanned).

4. LM RCS and ascent stage EECOM weight loss is 122.6 Ibprior to insertion.

5. Mixture ratio = 1.587 ± 0.018 (ref. 2).

6. Engine and valve operation uses 3.6 Ib of propellant perAPS burn.

TABLE 7-II.- APS PROPELLANT SUMMARY

Item Propellant Propellantrequired, Ib remaining, Ib

Loadeda 2631. 7

b 48.9 2582.8Trapped

Available for tJ.V 2582.8

Required for tJ.V

Insertion, 206.9 fps, 15.4 sec 174.8 2408.0

CSI, 50.3 fps, 22 sec throughinterconnect 32.3 2375.7

Burn to depletion 2375.7 0

Propellant margin 0

~eference 3.

bDoes not include trapped in feed lines and heat exchanger, whichis considered usable for depletion burn.

••

•

••

~ 39

8.0 THE CSM EPS ANALYSIS

~

~

~

~

The power levels of each component were obtained from reference 1;the cryogenic loading data were obtained from reference 3. Cislunarheater cyclic rates were used for TLC and TEC.

The EPS profile presented in figure 8-1 indicates that no seriousproblems exist. Because the May 18 mission is only 192 hours, thereare ample cryogenics (figs. 8-2 and 8-3) for mission completion.However, a worst case tank failure could occur at TEl minus 18 hours(REV 24) which would increase the time on one tank. REV 24 was deter­mined to be the worst case point because at this point there is notenough SPS ~V available to return to earth earlier than the nominal192 hours and still land in the primary landing area. Therefore, anominal power-down of the spacecraft to 55 amperes for TEC insures asafe return to earth. The total DC energy accumulated throughout themission is presented in figure 8-4. The CM bus voltage profile ispresented in figure 8-5 and indicates that no voltage limits are vio­lated.

The metabolic O2 requirements were altered to 0.197 It/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 onpostflight testing of the entry and postlanding batteries.

40

8-I.- ASSUMPTIONS FOR' THE CSM EPS ANALYSIS

----------------]. The system was assumed to opei'atE~ witb three fuel celli> and t'y/o

j nv c:J:ters .

2. '1'1Ic fuel cells were pU)'L~e(l ev(;]'y 900 A-h.

3. 'J'hree entry and postlanding batteries were com;idcrcrl nvailaiJleto Bupply the total spacecraft power required for entry, parachut.e descentaHa postlHildinc; time. Bach battery was assumed to have a 40 A-h capacityuntil splashdown, at which time the caj,acity was uprated to 45 A-h.

4. 'J\ro batteries were considered to be in parallel with the fuelcells during ascent and for each SPS rr,aneuver.

5. No cryoGenic venting ....IRS assumed.

G. 'I'he Ii:PS hJ'drogen consumption rate (lb/11r) ::: 0.00257 x I rc '

'r. 'l'he EPS oxygen consumption rate (lb/hr) = 7.936 x fIr")'L.

8. An SPS evasive m::l.lleuver find h;o S1'S midcourse correctiO!1S wereassumed.

9. Six battETy eharces were assur.,ed: three on battery A and three0:'1 b3.ttery B.

10. Five perc:ent uncertainty ir, the EPS profile is included in thecryogenic reqnirements.

••

•

••

••

41

TABLE 8-11.- CRYOGENIC SUMMARY

DescriptionRequired Remaining Required Remaining

•

••

Loaded (two tanks)

Residual

Instrumentation error

Available for mission planning

Prelaunch requirements

t minus 28 hr to t minus 12 hr at loadof 10.8 amperes

Vent allowance (H2 = 0.055 lb/hr),(02 = 0.65 lb/hr)

t minus 12 hr to t minus 9 hr at loadof 60 amperes

t minus 9 hr to t minus 2 hr (includes6 hr hold) at load of 45 amperes

Crew ingress at t minus 3 hr (0.196 lb/hr)

t minus 2 hr at 75 amperes

Mission requirements

EPS

ECS (includes CSM LM requirements)

Uncertainties

5% uncertainty in EPS

Launch window 4.5 hr

Margin

2.32

1.53

.45

.88

.46

1.50

.39

36.12

- ",.L.O.L

.87

58.60

56.28

54.75

54.75

53.42

51.46

51.07

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12.27

12.27

13.0

17.5

3.59

10.40

3.67

11.93

.59

3.06

260.86

95.62

, "':) ",v"")..L-J.vt"-

7.80

660.20

647.20

629.70

629.70

626.11

615.71

612.04

600.11

599.52

596.46

335.60

239.98

219.16

219.16

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• 9·0

47

THE CSM ECS ANALYSIS

•TABLE 9-1.- ASSUMPTIONS USED FOR THE ECS ANALYSIS

1. Average metabolic O2 rate was as follows.

a. One man, lb/hr.

b. Two men, lb/hr.

c. Three men, lb/hr.

2. Cabin leakage rate was 0.1 lb/hr.

3. Tunnel leakage rate was 0.05 lb/hr.

4. 1M leakage rate was 0.1 lb/hr.

0.066

0.131

0.197

•5. Waste management vent flows O

2at 0.85 lb/hr.

6. H20 tank bleed rate was 0.032 lb/hr.

7. Waste management was 0.024 lb/hr for the first 96 hours andwas 0.051 lb/hr from 96 hours to end of mission.

8. Cabin temperature control was set at 70°F.

9. Water produced by the LIOH-C02 reaction was 0.108 lb/hr.

10. Crew water usage was 18.96 lb/day.

11. Water lost by crew micturition was 2.64 lb/day per man.

12. Waste tank water was dumped from 85% of full capacity to25% of full capacity when the waste tank quantity reached 85% of fullcapacity.

13. Water tank capacities were the following.

14. Water tank quantities at lift-off were the following.••

Potable, lb.

Waste, lb.

Potable, lb.

Waste, lb. .

40

60

21.2

45.0

48

TABLE 9-1.- ASSUMPTIONS USED FOR THE ECS ANALYSIS - Continued

15. The water evaporator boiling efficiency was 100%.

16. The average glycol flow rate was approximately 225 Ib!hr.

17. The heat loads of the cold-plated equipment were split sothat 88% of the heat load went to the glycol, 9% was lost through thestructure, and 3% went to the cabin.

18. The heat loads of the noncold-plated equipment were splitso that 50% of the heat load went to the cabin and 50% was lostthrough the structure.

TABLE 9-11.- ECS OXYGEN REQUIREMENTS

I--

I Oxygen .6t, OxygenMission time, hr consumption rate, hr requirements,

IIb/hr Ib

o - 3·2 1.203 3·2 3.85

3.2 - 4.5 ·503 1.3 .65

4.5 - 8.0 1·353 3·5 4.738.0 - 95·92 .503 87.92 44.22

95·92 - 106. It .215 10.48 2.25

106.4 - 107·7 ·530 1.3 .69107.( - 192.0 .380 84.3 32.03

IM and tunnel pressurization at 3 hr 25 min 6·9Tunnel pressurization at 106.4 hr ·3

Total ECS 02 requirement, Ib 95.62

••

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10.0 THE 1M EPS ANALYSIS

The 1M descent and ascent stage battery energy used for thenominal mission is 423 A-h and 391 A-h, respectively. Unusables definedin assumptions 2, 3, and 4 of table 10-1 indicate that the descentstage and ascent stage have 10 and 28 percent energy remaining, respec­tively.

TABLE 10-1.- 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 1 A-h,respectively.

3. Energy unusable for the descent stage batteries and the ascentstage batteries because of telemetry inaccuracy is 14 A-h and 11 A-h,respectively.

4. Energy unusable for the descent stage batteries and the ascentstage batteries because of equipment power dispersions is 21 A-h and20 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.

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58

11.0 THE LM ECS ANALYSIS

Because of the late availability of a revised trajectory and updatedEPS data, the ECS analysis shown in this report is based on a previousflight plan and trajectory. A revised ECS analysis will be performedand documented as soon as the above information is available. However,this analysis is presented here because it provides a good estimate ofthe ECS requirements.

TABLE 11-1.- ASSTlMPTIONS FOR THE LM ECS ANALYSIS

1. Cabin 02 leakage rate was 0.1 Ib/hr while pressurized.

2. Metabolic rates were varied according to reference 2.

3. Metabolic O2

consumed was (1.643 xIO- 4 ) x (metaholic rate).

4. H2

0 consumed because of sublimator cooling was (total heat

load, Btu/hr) x (H 20 x 1/1040, Btu/lb).

5. H2

0 lost because of micturition was 0.11 Ib/hr/man.

h. Cabin temperature control was set at 75° F.

7. Average glycol flow rate was 250 Ib/hr.

8. Uncertainty in the water nrofile was calculated using 1 Ih/hr.

9. Uncertainty in the oxygen profile was calculated as 5~ of therequired 02 plus 0.1 Ib/hr for the uncertainty in the cabin leakage rate.

••

•

••

••

•

••

59

TABLE 11-11.- 1M ECS CONSUMABLES SUMMARY,

I (:-J.! L}ctjl~(,ll ,. stage

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••

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•••

•

1. CSM!LM Spacecraft Operational Data Book, Volume I - CSM Data Book,Revision 1. MSC SNA-8-D-027, November 1968.

••

13.0

67

REFERENCES

•

••

2. CSM!1M Spacecraft Operational Data Book, Volume II - 1M 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. Flight Planning Branch. FCSD: Apollo 10 Flight Plan (Draft Final,April 17,1969).

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.

6. Alexander, Martin L.; Kamen, Sam A.; Loyd, Arnold J.;Mayfield, Samuel 0.; Peterson, Dwight G.; and Scott, Walter, Jr.:Consumables Analysis for the Apollo 10 (Mission F) SpacecraftOperational Trajectory. MSC IN 69-FM-76, April 7,1969.

7. Graf, O. F.: The Predicted Accuracy of D Mission Short Burns.MSC memo 69-FM73-46, February 11, 1969.

8. Simpson, R. W.; and Smith, H. E.: Apollo Rendezvous with CommandModule Active. MSC IN 67-EG-23, September 28, 1967.

9. LMAB; LAB; and OMAB: Revision 1 of the Spacecraft Operational Tra­jectory for Apollo 10 (Mission F), Volume I - Operational MissionProfile Launched May 18, 1969. MSC IN 69-FM-96, April 28, 1969.

10. Seto, R. K. M.; Roson, D. F.; Wood, S. C.; and Ware, J. 0.: ApolloMission F!1M-4!DPS Preflight Performance Report. TRW document,February 21, 1969.