MSC INTERNAL NOTE NO. 69.FM - NASA · msc internal note no. 69-fm-137 project apollo apollo mission...

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MSC INTERNAL NOTE NO. 69.FM.137

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00/99Unclas16270

MSC INTERNAL NOTE NO. 69-FM-137

PROJECT APOLLO

APOLLO MISSION F (AS-505jCSM-I06jLM-4)SPACEC RAFT OPERATIONAL TRAJECTORY, REVI SION 1

VOLUME II - TRAJECTORY DATAPART 3 - FLIGHT CREW SIMULATOR DATA

By Ron D. Davis and Larry D. DavisFlight Analysis Branch

May 12,1969

MISSION PLANNING AND ANALYSIS DIVISION

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION

MANNED SPACECRAFT CENTER

HOUSTON, TEXAS

Approved:~~. (l~_Charlie C. Allen,hiefFlight Analysis Branch

Approved:~~j.J~~~~~-¥:'=~ __JohnMiss

TABLES

Table Page

-I MISSION-DEPENDENT CONSTANTS

computed from weight

(a)(b)(c)(d)(e)

Launch data .Thruster data . .Center of gravityAerodynamicsCross-section area . ... .. ..

557

1011

II CSM RESET VECTORS

(a) Evasive maneuver(b) MCC-l maneuver(c) LOI-l maneuver(d) LOI-2 maneuver(e) Separation maneuver(f) DOl maneuver(g) Phasing maneuver(h) Insertion maneuver(i) CSI maneuver(j) CDH maneuver(k) TPI maneuver(1) TEl maneuver(m) Entry. • . .

III 1M RESET VECTORS

(a) DOl maneuver(b) Phasing maneuver(c) Insertion maneuver(d) CSI maneuver(e) CDH maneuver(f) TPI maneuver

IV CSM .REFSMMAT

. .

12131415161718192021222324

252627282930

(a) Launch through MCC-3maneuver. . .(b) Mcc-4. maneuver .through Mcc-6 maneuver(c) MCC-7 maneuver through entry .

V CSM NAVIGATION UPDATES

(a) Evasive maneuver(b) MCC-l maneuver

iii

313233

3435

Table Page

(c) LOI-l maneuver · . 36(d) LOI-2 maneuver 37(e) Separation from 1M 38( f) TEl maneuver . 39

VI LM NAVIGATION UPDATES

(a) DOl maneuver 40(b) Phasing 41(c ) Insertion 42(d) CSI maneuver 43(e) CDH maneuver 44(f) TPI maneuver 45

VII DETAILED MANEUVER TABLES

(a) Evasive maneuver 46(b) MCC-l maneuver 47(c) LOI-l maneuver · 48(d) LOI-2 maneuver · 49(e) Separation from 1M 50(f) DOl maneuver . 51(g) Phasing . 52(h) Insertion maneuver 53(i) CSI maneuver 54(j ) CDH maneuver 55(k) TPI maneuver 56(1) TEl maneuver 57

VIII FDAI ANGLES FOR 1M MANEUVERS 58

IX CSM EXTERNAL ~V UPDATES

(a) Evasive maneuver 59(b) MCC-l maneuver 60( c ) LOI-l maneuver · 61(d) LOI-2 maneuver 62(e) Separation from 1M 63(r) TEl maneuver · 64

..,X 1M EXTERNAL ~V UPDATES

(a) DOl maneuver · 65(b) Phasing maneuver 66

iv

Table Page

(c) Insertion maneuver 67(d) CSI maneuver 68(e) CDR maneuver 69(f) TPI maneuver 70

XI MANEUVER PADS

,.. (a) Evasive maneuver 71(b) MCC-l 72(c) LOI-l 73(d) LOI-2 . . . 74(e) Separation from 1M 75(f) DOl 76(g) Phasing TT(h) Insertion 78(i) CSI 79(j) CDR 80(k) TPI 81(1) TEl 82(m) Lunar entry 83

v

.....

"

'w

APOLLO MISSION F (AS-505/CSM-106/LM-4)

SPACECRAFT OPERATIONAL TRAJECTORY, REVSION 1

VOLUME II - TRAJECTORY DATA

PART 3 - FLIGHT CREW SIMULATOR DATA

By Ron D. Davis and Larry D. Davis

SUMMARY

The data in this document are compiled to satisfy flight crew andflight controller training and simulation requirements for the F mission.This data pack is based on a F mission operational trajectory, revision 1(ref. 1). This document contains reset vectors, REFSMMAT updates,navigation updates, navigation checks, detailed maneuver tables,entry data, and associated flight crew data.

INTRODUCTION

The nominal Mission F plan involves the following mission phases

1. Launch, which ends with insertion into earth parking orbit.

2. Earth orbit coast, which ends with TLI.

3. Translunar coast, which ends with LOI.

4. Lunar orbit operations, which ends with TEl.

The prime objective of this phase will be to demonstrate allphases of Mission G except those which directly involve LM powered descentand powered ascent. These operations will include a LM-active rendezvous.

5. Transearth coast, which ends with entry into the mid-Pacificrecovery area.

The total mission duration will be approximately 8 days. Thedata presented in this document were computed by the use of the RTACFprocessors.

AGS

ALPHA

APS

CD

CDH

CL

CM

CSI

CSM

cg

DOl

DPS

DSKY

EECOM

EL

EOI

ER

FDAI

GET GEN

g.e.t.

G.m.t.

GMT ID

I sp

2

ABBREVIATIONS

abort guidance system

angle of attack

ascent propulsion system

coefficient of drag

constant differential height

coefficient of lift

command module

coelliptic sequence initiation

command and service modules

center of gravity

descent orbit insertion

descent propulsion system

display keyboard

electrical, environmental, and communications

earth launch

earth orbital insertion

earth radii

flight director attitude indicator

time of data generation

ground elapsed time

Greenwich mean time

identification of time

specific impulse

"

LES

LGC

LM

LOl-l

LOI-2

PAD

RCS

REF

REFSMMAT

RTACF

8 and S

8LA

8M

8PS

STA lD

t

TEl

TEC

TlGN

TLC

TLl

TPF

TPl

WT

w

3

launch escape system

lunar module guidance computer

lunar module

lunar orbit insertion

circularization maneuver after LOl-l

pre-advisory data

reaction control system

reference body

reference to stable member matrix

Real-Time Auxiliary Computing Facility

start and stop

spacecraft/LM adapter

service module

service propulsion system

station identification

time

transearth injection

transearth coast

time of main engine ignition

trans lunar coast

translunar injection

terminal phase finalization

terminal phase initiation

weight

flow rate

4

RESULTS

A set of data that consists of the following is provided foreach of the Mission F maneuvers (or entry); reset vectors, REFSMMATupdates, navigation updates, navigation checks, detailed maneuvertables, and other required flight crew data. This data pack supersedesall earlier F mission data packs.

A brief summary of mission-dependent constants used in thegeneration of this document are presented in table I. A more detajledtabulation of mass properties data can be found in references 2 and 3.

The CSM and LM reset vectors for each maneuver and entry are containedin tables II and III. These vectors are in the mean Besselian coordinatesystem. This system can be defined as follows: an inertial Cartesiansystem with origin at the center of the reference body (earth or moon)with the X- and Y-axes in the mean equatorial plane and the Z-axiscoincident with the mean polar axis (positive to the north). TheX-axis is alined at the intersection of the earth's equatorial planewith the ecliptic at the nearest beginning of a Besselian year.

The CSM and LM REFSMMAT update quantities for the various phasesof the F mission are contained in table IV. The required navigationupdates for the various maneuver sequences are presented in tables Vand VI.

The "detailed maneuver table" quantities for each of the plannedmaneuvers are presented in table VII. A tabulation of LM gimbal anglesconverted to LM FDAI angles is given in table VIII. The external ~V

updates for each of the maneuvers are presented in tables IX and X.Additional information in the form of pre-advisory data (PAD) isprovided in table XI.

ff

I

5

TABLE 1.- MISSION-DEPENDENT CONSTANTS

(a) Launch data

Date of launch. May 18, 19h9

G.m.t. of launch 16:49:00

(b) Thruster data

SPS steady state

..

Thrust, IbW, Ib/secI ,sec.sp

SPS tailoff ~

Burn time, sec .Thrust, Ib~, Ib/secI ,sec.sp

SM RCS (per quad)


CM RCS (per quad)


1M RCS (per quad)


APS steady-state

Thrust, IbW, Ib/secI ,sec.

sp

20 50065.162314.60

0.5920 847.5

66.590313.07

102.80.371

277.09

96.00.353

271.95

100.00.367

272.48

3 500.011.427306.29

APS tailoff

Burn time, secThrust, lbW, lb/secI , sec .sp

DPS onboard (92.5%)

Thrust, lbW, lb/secI , sec .sp

DPS (40% level)

Thrust, lbW, lb/secI , sec .

sp

DPS (10% level)

Thrust, lbW, lb/secI , sec .

sp

DPS tailoff

Burn time, secThrust, lbW, lb/secI , sec .

sp

6

0.12990.0

9.65309.84

9712.532.270300.98

4200.013.952301.03

1050.03.488

301.03

0.386503.020.080301. 44

7

TABLE I.- MISSION-DEPENDENT CONSTANTS - Continued

(c) Center of gravity computed from weighta

[CSM propellant on bottom of tanks]

WEIGHT X Y Z PITCH TRIM b YAW TRI MbLB INCHES I NCHE S I NCHE S DEG DEG

23200.00 983.59 -2.82 8. ('1 -3.05 -1.0125400.00 9"71 .9R -1.61 1.45 -3.01 -0.6621600.00 962.~17 -C.59 6.98 -3.08 -0.2629800.00 956.14 0.28 6.58 -3.06 0.1332000.00 951.;>7 1.02 6.23 -3.02 0.5034200.00 <;47.83 1.67 5.93 -2.96 0.81t36400.00 945.61 2.25 5.66 -2.88 1.1538600.00 944. B 2.75 5.42 -2.79 1.4240800.00 943.91 3.21 5.21 -2.10 1.6643000.00 944.15 3.61 5.03 -2.59 1.8145200.00 C;44.g8 3.98 4.85 -2.49 2.0447400.00 942.R6 4.15 4.90 -2.56 2.1149600.00 939.03 4.12 5.17 -2.80 2.2351800.00 936.22 4.09 5.42 -3.01 2.2754000.00 934.30 4.G6 5.65 -3.20 2.3056200.c(\ 933.17 4.03 5.86 -3.35 2.3158400.00 932.72 4.01 6.05 -3.48 2.3160600.00 <;32.90 3.99 6.24 -3.58 2.2962800.00 933.62 3.97 6.40 -3.65 2.2665000.00 <;34.89 3.95 6.56 -3.69 2.23

[CSM propellant on top of tanks]

23200.00 982.28 -2.58 8.25 -3.17 -0.9925400.00 981.18 -1.40 7.61 -2.91 -0.5427600.00 979.27 -C.40 7.18 -2.81 -0.1629800. CO 976.62 0.46 6.76 -2.70 0.1832000.00 973.41 1.19 6.40 -2.61 0.4934200.00 969.77 1.83 6.09 -2.55 0.7736400.00 965.84 2.39 5.81 -2.51 1.0338600.00 961.63 2.89 5.51 -2.48 1.294('800.00 957.15 3.34 5035 -2.47 1.5443000.00 9'32.52 3.74 5015 -2.47 1.7945200.00 947.72 4.10 4.98 -2.49 2.0547400.00 947.64 4.18 5011 -2.56 2.0949600.CO <;48.14 4.15 5.38 -2.68 2.075180:). nl) 947.91 4.12 5.62 -2.80 2.0654000.00 947.04 4.09 5.84 -2.94 2.065620(\.00 '145.5'1 4.06 6.04 -3.08 2.075P400.no 943.66 4.04 6.23 -3.23 2.0960600.00 '141.28 4.02 6.40 -3.39 2.1362800.00 938.50 4.00 6.56 -3.57 2.1165000.00 935.70 3.98 6.72 -3.75 2.22

aThese values are based on reference 2.

bThese angles are measured from longitudinal axis and do not include electronicnull bias.

8

TABLE 1.- MISSION-DEPENDENT CONSTANTS - Continued

(c) Center of gravity computed from weighta

- Continued

[1M with APS and DPS propellant on bottom of tanks]

WEIGHTLA

1400,1. or145('n.n('\1500J."0155GG.rn16()(,C.00165C'D.rn

17(':O".no115~O. 00180)"'."1'1 fl 5')1:. rr19000. (.10IG50U.C"21'!)'ln. 'r20 '51)0. '10210 n ').,,071 5n". "0?200 ').nn2251),~.~C

2~C)('.('O

2'3511. rn241'1'):'.002450(1. ''''7<;000.rr2551('.002t10:t r .• \~~,

265Q'). rn21('00.""2750". f'n

2 80')n .l"'''i'8 ')1):"'. ('\02'}()no.')02'}50(, .~C31(':0(1."CV)5:)o.('(\

~l('''().''C

~15,)0.(,O

32000.('0~ 2 500. ,,0

)(

INCHES

20A.60206.04to ~. 732C1.td1q9. 121q7.971S6.3R194.92193.59192.351'H.231ql).21le9. Z718R.411tn.62lR6.92186.24185.661q5.14184.67184.21183.'l5183.52183.22182.'15182. n1e2.56182.41182.2A182.191E2.15182.1111'2.111A2.16182.20181.88Ult.52181.18

VI NCHE S

-0.67-0.65-C. 6 2-a.60-0.5<;-0.57-:.55-0.54-0.52-8.'51- C. 49- C.48-C.47-0.46-0.45-0.44-0.43-0.42-0.41-1).40-C.3<;- (). 38-C.37-C.37-0.36-0.35-C.35-C.34-0.'3"1-:).33- 'J. 32-0.32- ~. 31-0.31-0.30-0.30-0.29-0.29

ZI NCHf: S

0.580.560.54').520.500.490.470.46·1.45').440.420.410.401.3Q:).380.370.37').360.350.340.340. ,130.320.32').310.30':\.300.290.290.28·1.28').27C.270.260.21,0.260.250.25

PITCH TRIM b

DEG

-0.60-0.b1-0.62-0.b3-0.63-0.64-0.b4-0.64-0.65-0.65-0.65-0.65-0.65-0.65-0.65-0.65-0.65-0.65-0.64-0.64-0.64-0.63-0.63-0.62-0.61-0.61-0.60-0.59-0.58-0.57-0.57-0.56-0.55-0.54-0.53-0.53-0.52-0.52

YAW TRIM b

OEG

-0.70-0.71-0.72-0.73-0.73-0.74-0.74-0.75-0.75-0.76-0.76-0.76-0.76-C.76-0.76-0.16-0.76-0.7<;-0.75-0.74-0.74-0.73-0.73-0.72-C.71-0.70-0.70-0.69-0.68-0.67-0.66-0.65-0.64-0.62-0.61-0.6L-0.61-0.61

#

[LM with APS and DPS propellant on top of tanks]

14"(':,). C(\

1451',(\."('1500:1. ,"If'15<;1'1.0(116 n ')('.rC'1650". roc.1 7 rc 1. ,~r,

115()0."t'1 fl r:: ('\ '). 'l(.

1"50C ••~('\

1'}0(1').00

213.14212.13211.12?Ir.132(9.13?C~.15

2C7.1Q2%.2.i2,)~.29

204.362C3.43

-0.(-4-0.62-").6e-').58-J.56-C.54-C.53-0.51-C.50-C.4 9-C.47

- r, • 9(1

-0.R7-0.q4-f).A1-J.7R-0.76-0.74-0.72-0.70-). Ail-').66

0.R70.850.840.830.820.30J.RO0.79').780.770.77

-0.62-0.61-0.60-0.59-J.58-C.58-0.57-0.56-0.56-1).55-0.55


bThese angles are measured from longitUdinal axis and do not include electronicnull bias.

TABLE I.- MISSION-DEPENDENT CONSTANTS - Continued

(c) Center of gravity computed from weighta - Concluded

[1M with APS and DPS propellant on top of tanks]

WEIGHT X Y Z PITCH TRIM b YAW TRIM bL8 INCHES INCHE S INCHES DEG DEG

19500.00 202.53 -0.46 -0.64 0.76 -0.5420000.00 201.63 -0.45 -0.63 0.75 -0.5420500.00 200.73 -0.44 -0.61 0.75 -0.5421000.00 199.84 -0.43 -0.60 0.75 -0.5321500.00 1'18.99 -0.42 -0.58 0.74 -0.5322000.00 198.12 -0.41 -0.57 0.74 -0.5322500.00 1 'H. 25 -0.40 -0.56 0.74 -0.5323000.00 196.38 -0.39 -0.55 0.74 -0.5323500.00 195.56 -0.38 -0.53 0.74 -0.5324000.00 194.69 -0.37 -0.52 0.74 -0.5324500.00 193.85 -0.37 -0.51 0.74 -0.5325000.00 193.02 -0.36 -0.50 0.74 -0.5325500.00 192.20 -0.35 -0.49 0.74 -0.5326000.00 191.37 -0.35 -0.48 0.74 -0.5)26500.CO 190.53 -0.34 -0.41 0.74 -0.5321000.00 189.72 -0.33 -0.46 0.75 -0.5321500.00 1e8."91 -C.33 -0.46 0.75 -0.5428000.00 188.09 -0.32 -0.45 0.15 -0.5428500.00 181.26 -0.32 -0.44 0.76 -0.5429000.00 186.41 -C.31 -0.43 0.76 -0.5529500.00 185.64 -0.30 -0.43 0.77 -0.5530000.00 184.81 -0.30 -0.42 0.78 -0.5630500.00 183.99 -0.29 -0.41 0.79 -0.5631000.00 183.58 -0.29 -0.40 0.18 -0.5631500.00 183.23 -0.29 -0.40 0.78 -0.5632000.00 182.88 -0.28 -0.39 0.78 -0.5632500.00 182.55 -0.28 -0.39 0.77 -0.55

[Ascent stage with propellant on bottom of tanks]

5001."0 267. 62 '),13 5.94 "~ c.55("0."(\ 262.72 ".11 5.4r r.60"()."C' 25'l.15 j. U: 4.95 ". r.65('0.0r 254.53 1.0 0 4.57

~ c.7"N).Cr, 251.79 ).e8 4.24 I" c.750".,,( 249.65 0.07 3.q~ J. 0.8000.0C 247.99 ').07 3.71 !") O.8500.0C 246.71 ).06 3.49 ", C.901'0.CO 245.74 ) • :: 5 3.3C ,; c.95C".00 245.04 ;.05 3.13 " C.

10n OO.Cr 244.57 ').°5 2.97 ". r.[Ascent stage with propellant on top of tanks]

5"" 1;. er 26" • 51 0.20 1.'12 r.5<;')0.(r 259.37 'j. 18 1.'>5 " 0.6~OO.U 2 5f!. 18 ').16 1.51 \,,'.65U'.QI" 2 56.79 ') • 15 1.4" c.7C00.0" 255.33 'J' .11 1.3" t: •75";. "r 2 53.85 ,~. 12 1.21 r..8"0).,":" 252.35 J. 11 1.14 ".8500.0 r 25,'.35 ) .1 C 1. '17 C· •9C'O"."r 24g.34 '). "g 1 • ) 1 ') . r'

95GC.~" 247.82 1. ': 9 0.96 l.101)()'1.r,- 24~.27 .j .'- e ).91 !. r.


bThese angles are measured from longitudinal axis and do not include electronicnull bias.

10

TABLE 1.- MISSION-DEPENDENT CONSTANTS - Continued

( ) d. ad Aero ynarnlcs

= 1040.90; Ycg = -0.20; Z = 5.80; Weight = 12 121.50 Ib;cg

~x = -100.35 inches; Bank angle bias = -1.97°]

.,14 r H ~.' 4l t) '--l,\ L C) CLIC )I, • \. .

",,), ..., 1 '7" ':45 ? ~ 1F' ) .R.? ':JP' J. 2 R )57• • ~ ·~ .-t

" I, ," 1 t, 7 (, ~ ; l 41., ,..,

;\':) .',. 7 3 ') 2 73 )'"• , · " • ,~ t. • I •

7"', 1 t, .:, .-1

, ) c;~ 1 '=I " 9 'l '")1 2 :I 2 "i '1 n• ·, · ·

........ t"'\ 1-, " '~ 1"

3 ,1 p.-; ,

,; 7 ,<~ • ? gl 3')· · . ~ · "

, 1 " 1 h 7? 4 ; ':'5 ,0 1 1 1 r 74 '. 4( 7 29· • • . • ..,J •

1 ,,~ 1 r; " ) 7 ~

It to, 6 c .. ,1 ~, " " J '"'I. / ,....

)7 /+· · • . · "t' ,

, - C; 1 '. ! '::l,.

~4 cc; ... , ) 'J 7 .:.4 'I. It.'':) '~4· · · - - ·~• C; 1 ~.; 'l ') , t5 Yo

,..(1 /+ 1 'J 7L. -'ol ") 4 ,2,+'3~, · , · • • "- •

? 1. .::: 1 '. f<,

5:2 a::; 72 1 ) .) <', 1, ') It ... 37,.,· • .' -. " • - • "

I. ," 1 ~.;. 4 ")~CJ c q6 1 2 ;;6 1 2- ') c;7~4· . · • • J. · .,

, ·. 1 c; !.. I~ 7 , 7 1 74 ~') ..., ') 7 J .., '~ ') '32- · ·... • - •

4 ! 0; '., -, 7 ,'" 4 341 4 1 .., '·1 2 ) 353':37• · • ·~ ,- r: •, - 1 , .,

If,

!~ 2 1 c:: '5 1 ,~ \ i j ~ 1 ') '), 4 no.. ! · · · •? "'1 c 1 f, \ 7 ,..

1 3 79' .,1 3 ; 1 3 S ) ?Q 124· · , · · •


•

JI

11

TABLE 1.- MISSION-DEPENDENT CONSTANTS - Concluded

(e) Cross-section area

CSM, ft 2 129.4

CM, ft2 129.4

LM, ft 2 200.6

APS, ft 2 200.6

(f) Mass properties, spacecraft weight - See reference 3

12

TABLE 11.- CSM RESET VECTORS

(a) Evasive maneuver

(~EAN 6_;S_§J LI AN)EARTH REFERF-NCED

GET ;; <4 HR 16 MIN 47,56 SEC

X c: 1840~~Z3.?S FT

V :II 9J966 810,r:l0 FT

Z 1I 568811:56,50 FT

XcOT c: .~~~J7, ~5 FT/SEC

YDOT II 127 13. A8 FT/SEC

lOOT II 7;'20.02 FT/SEC

X II I ~]9~70'2J)~ ElL.

V I: 4,4904~96617 ER

Z :II 2,81 38 1410:56 ER

XCOT c: -,?~O~77~D68_ER!HR_

VoOr I: 2,18 72'6 A4?9 ER/HR

ZOOT :II 1,259~141049 ER/HR

Wl = 94~75J60 l.s

13

TABLE 11.- CSM RESET VECTORS - Continued

(b) MCC-1 maneuver

t·l"tf AN.S.E5.S.1I.-1ANJEARTH REFERENeEn

GET = 9 HR ~6 MIN 46,38 SEC

-- x. -A._--._._.l'I.,.4~l5-tJ1O .. ET-

Y z 2~~S8~'2e,OO FT

Z z 14 9940 9 78,00 FT

XoQT·.!- .~ 4~3A.t 7.5. Frl SEc

Yoor = 67~~.25 FT/SEC

ZOOT = J680.61 FT/SEC

.. _. X. -..-. i.. e .3..t12481625.4 8 f R

Y = ~2.261'665197 ER

l ; 7.~65J854647 ER

.......... ~pOl. =. .. ...?4~~.~-'-::57'3ER/HR

YOOT = 1.1'J~1.866.~4 ER/HR

~OOT =. ~J~,Q05560 ERI HR

---. ----. WT .-. ~-- ... - .. ----~U.2! , 6O. I..-B .-

14


(c) LOI-1 maneuver

(~~AN 6E.S~lLIA.N)

L,UN'R REFERtNeED ,

GET = 14 HR 4~ MIN ,00 SEC

X ;: .. 15309~7'-.12 f'T

Y : "'1 369 4786,15 FT

Z I: p. 8 513J;56,87 FT

XcOT :I 1~7'JA~ FT/SEC

YeOl I: 44 39,36 FrlSEC

ZeOT I: 2379,54 FT/SEC

X I: ·,7)16096649 E~

Y l: "'t6544~70191 ER

Z ;: .,4068356864 ER

XCOT I: 12~6~'t~6~.6 ER/HR

Year I: ,7637346163 ER/HR

ZOOT I: ,409J660419 ER/HR

WT II 9Z~2A,no l..s

15


(d) 101-2 maneuver

(~EAN BESSILIAN)l.lJNAR REFERENCED

''-

GE: T :: 79 HR 11 ~1 I " ,00 St:C

X :: 1122'74.~6 FT

Y .. ,,6121 706,00 Flf..Z :: ..2526~69.66 FT

XOOT :: -~884.16 FT/SEC

Vo°'T :: "683,48 FrlSEC

ZOOT .. -J73,33 FrlsEC..X :: ,053b456527 ER

V :: -,292~~4:5J14 ER

Z :: -,1207206966 ER

XoOT :: -,8402~62216 ER/HR

"'OOT :: -,11 7SH424 7 1 ER/HR

ZOOT :: -,06 4 2265659 ER/HR

WT :: 68"67.15 l.a

16


(e) Separation maneuver

(~t;A.N BE~ lLlAN)~UNAR REFERENCED

GET • 97 HR 3' Mr t\! .00 SEC

X = ..~_O 5~ ~ 71 •62 FT

V • 109~6'.14 FT

Z = .6403'.54 FT

XOOT = 66. 93 FTlsEC

VeOT =: 4~37,:?3 FT/SEC

ZOOT • 2056,68 FT/SEC

X = "',28 92214209 ER

V • ,00 52)12201 ER

Z c "',00 3 0602286 ER

XeO T • ,°t1~_~ ~'7~_? ER/HR

VeOT ;: .84 9JtSS6415 ER/HR

ZeOT • ,3538256884 ER/HR

WT = 6I~8'5,Q6 LoS

17


(f) DOl maneuver

O~E4N BE6S1Lt AN)~UNAR REFEREN~ED

'Ii

GET : 99 HR 14 MIN .00 SEC

X = .'160406,16 FT

V : .,47'12651,00 FT

Z = .2031801,4' FT

XoOT = "'4'62,92 FT/SEC

VOOT = 2609,11 FT/SEC

ZOOT = 100:5,69 FT/SEC

X = "',151C~96166 ER

V = "',22664 19958 ER

'l II -.0970 9 60967 ER

XDOT = ·,784991:5910 ER/HR

YOOT = .44e8 640055 ER/HR

ZDOj = .1726 716720 ER/HR

VlT = 36414,12 LB

18


(g) Phasing maneuver

(~EAN BESSILIAN)L.l.. NAR REFERENr.ED

GE:.T = 100 HR 26 Mhl ,00 nEe

)( = 569266~,C;O F'f'

V = 1866233,95 F"T

Z = 880054,66 FT

XeOT = 161',43 FT/SEC

YeOT = "'4654,1J4 FT/SEC

ZeOT = -1904,93 FT/SEC

X = ,2720'013836 ER

Y = ,0891 8 36630 ER

Z = ,0420'60814 ER

XCOT = ,31266S63 R7 ER/HR

YeOT = ",6006676137 ER/H~

ZDOT = .. ,32 77175674 ER/HR

WT = 36 4 74.12 LB

19


(h) Insertion maneuver

(MEAN BESSiLIAN)~~NAR REFERENeED

",.

GET : 10~ HR a3 MI~, .00 SEC

X II 55°8380.)7 FT

y ;I 226'2.13.134 FT

Z = 1051145.53 FT

XoOT II 2216.93 FT/SEC

, YOOl ;; -4'05.88 FT/SEC

ZeOT ;I ·~~36.19 FT/SEC

X II .263Z347010 ER

Y II ,lQ9Z011128 ER

Z II ,0502321846 ER

XOOT ;II ,381'9385:56 ER/HR

YOOT • ",17'178'548 ER/HR

ZOOT • -,'1"9.2e268 ERIHR

WT ;I 36474,12 ~B

20


(i) CSI maneuver

(ME.AN BESSILUN)I..UNAR REFEReNcED

GET II 100l HR 1~ MIN .00 siC

X • -,926831 ,00 FT

V II .. 4224122 69 FT-- .z ;: .. 183D011.25 FT

)(OOT II .. 4e11.13 ,"'SECVCOT II J231.20 ","SIC

ZOOT II 1211.93 FT/SiC

X • -,181"55569 ER

V • "',2011625451 ER

Z II -,0814'26510 ER

XOOT a ~,100;JaJ9681 E~'Io4R

VOOT II ,'5"152'117 ER/HR

ZoOT ;; ,a18819'612 ER/Io4R

WT • J.~14.12 loB

..

21


(j) CDR maneuver

(MEAN 8E&SJ~IAN)~UNAR REFERENeEO

GET • S.04 HR 12 MhJ .00 SEC

X • 3601290.09 Fif

V • 4467148.94 F'Z • 192"2. •• 1' ,IfXOOT I: 4291,1. ~T/SEC

VOOT • "2~69.01 ~'/5EC

ZOOT ill -1158.86 F1'/SEC

)( • ,2.124331118 IER

V • ,Z134162928 ER

Z • ,0920S,6!U19 ER

)(OOT • ,138;)38 •• 81 ER/IoIR

VeOT I: -.'101fJ992'. ER/HR

ZOOT I: -,199J67!288 ER/HR .

WT • 364'4.12 Le

22


(k) TP1 maneuver

(MEAN BESSILIAN)~U~AR REFERENCED

GET = 104 HR 49 '1 I N 36.00 SEC

X = 2954:51 8 '16 F'T'

Y = ... 489;5702 44 FT•Z = "1964 615.17 FT

XOOT = "'4670.21 FT/SEC

YeOT = -2'80.14 Fi/SeC

ZeOT = "1075.~8 FT/Sec

X = ,14111:110141 ER

Y = -.2;5386044RQ ER

Z : -,09 4 8408972 ER

XOOT = .. ,80344922~4 ER/HR

Yt;OT = -.40 95758647 E~/HR

ZeOT ;: -,3.85091~8CJO ER/HR

WT = 36 4 74.12 Los

23


(1) TEl maneuver

ib'.f.AN-aES.5 ~- tAN,) --._~UNAR REFeRENeED

GET II 136 HR 2D MI~ .00 SEC

)(-- ...L ··----~... ii96_:!_t -'-5''£.T

Y c e3807~8~.09 FT .

Z = -150V2S1,'O FT

X-S0T ~... - -- _- ~J_~U.79 ~!ISiC

YeOT • -Jtl1.56 FT/SEC

ZoOT • -1"1,00 FT/SEC

X II _.__ - ....~VQ!;,'tJ92 ER

Y II

z •. XCQT.II

veQT •

ZOOT •

- --'---_. WT-- =

·.1819~259?O ER

~.07207.66699 ER

.~ ...~Z2~~2..54'1 ERlHR

·,~21J2243A1 ER/HR

• ...270,70.3401 ER/HR

.____._J.O 6 63.. Z9-LB- ..

24

TABLE 11.- CSM RESET VECTORS - Concluded

(m) Entry

( f' EAN 8ESSI LIt:.. N )EARTH REFERFNCED

H:T = 191 HR 31 '1 I 'I '00 SEC

X : -223~1t19S.75 FT

y ;: -2 7 107 131).'5 FT

l. : -1399917'i.P.7 FT

>- COl : cl1J~.43 FT/SEC

YL,;CT : "36"),07 FT/SEC

ZCOT : 1U74.46 FT/SEC

X : -1. i)6 9 :.,tl69:S27 ER

y : -1,2953 9 062 6 0 CoR

! : -,66 891J 2(n66 EP

Xl;OT : 4.6b2J917l:i~b ~R/HR

YCCn : .4J6C19Ci2 n O ER/HR

ZeOT : .184b 4 75356 ~R/HR

WT : 24581.0 L.R

25

TABLE 111.- LM RESET VECTORS

(a) DOl maneuver

(MEAN SEI'ILIAN)~UNAR RE'IRENeED

GET • 99 HR ~_ MIN ,00 SEe

)( III

Y ;;

z •)(OOT I

YOOT

lOOT •)( .Y II

z •XOOT 11

YeOT I:

ZOOT II

WT •

.31"65,,61 .T••7.8~5',12

".aO:)4202,'7"·.'64,25 '1151t:

a~0,.20 'Tille2,001.20 FT/SIC

-,1'0".'144 E-",a26'a88264 ER

"'.0912tO!442 ER

'"'.7152"883'9 iR/""R

, 441'4'61666 ER/IolR

It12~~4021" ER/""R

36484,00 loB

26

TABLE 111.- 1M RESET VECTORS - Continued

(b) Phasing maneuver

(MiAN BESSILI'N)~UNAA RE'ERENeEO

GET , 100 \l4R a6 MIN ,DO ~Ee

X • ~164995.a7,,.

V ;; 'Z94554,19 ,,.Z , 6J9~28.96 ,t

XPOT : 1350.'7 'T/SEC

VcOT • ....984.~1 'T/S£C

ZeOT -= -2051.16 ,,./8£C

)( :; ,2659'0241J2 E~

V I; ,061'6420'10 E~

Z 11 .030l57'1,932 ER

XOOT • .2l2J'2d9!6 ER/IolR

VcOT • ·,8~1'88805l ER/~-

ZeOT • ·."28148788 (R/MR

\tiT :; )1069,90 LB

27

TABLE 111.- LM RESET VECTORS - Continued

(c) Insertion maneuver

(MEAN BISSILIAN)~UNAR RE'IRENeEO

G~T • 1o~ HR 23 MIN ,DO SEe)( • -'ZI12i. ~H "v • 3940"1.06· ,'"Z • 111"06,14 FT

)(eOT • J~8',22 F'r/IIC

veo' • ·~~48.'9 'T/SEC

ZOOT , -l'J9,'2 ,t/SEC

)( • ,206'1"426 E~

y I ,188J112118 (fit

Z ;; ,082i5211'1 iR

)(eOT • .'99"12997 ER/\oI~

VDOT • ... 6620~6D424 ER/\oIR

ZOOT • ·.2641:S6!U60 ER/\oIR

WT • 30618.'0 LB

28

TABLE 111.- LM RESET VECTORS - Continued

(d) CS1 maneuver

GET • 10~ ~R 2,' MiN ,00 SEe

x • ·'Oz,~o•• e1 ItT

y • .4660~'S.9, FT

Z • -199"69.!2 FT

)(DOT II .'67ZaS.D "/SEC

YeOT I 2'11. " "/IIC

ZeOT :I 9. ,. ""/SEC. 1.

X II ·,1'477'1'" E~

'1 II "12221a'!l100 IR

Z • .. ,O'5~'956t9 ER

)(eOT II -I eO:H 144686; ER/HR

YOOT " 1',ZQe6!2" E~/~Pt

ZeOT ;: .16'J9 14154 illt/~_

WT • 82'2. 80 L.B

29

TABLE 111.- 1M RESET VECTORS - Continued

(e ) CDR maneuver

(MIAN BE&'ILIAN)~UN'~ RE'IRENCID

GET " ~O. ~R 12 MIN ,DO sre)( It '0'7671.19 "Y It 410'019.00 FT

Z ;: 201'!:H .12 'TXCQ' " .626.05 'T/81e

YCOT iii "'2'82.'1 FT/SEC

200T • .991.81 FT/SEC

)( II ,146~20i6n8 E~

y I .ia4,.).,62 lilt

z !II ,Q962704942 ER

)(OOT • •"'1'12'06 IR/~'"

YoOT • "',444a011070 ER/~R

ZOOT • ,,,,,, 10••'iI16 e:llt/~.

WT • "9,.90 L.B

30

TABLE 111.- LM RESET VECTORS - Concluded

(r) TP1 maneuver

(MEAN 8ES5ILI4N)L.UNAR Re'ERENCED

GET • ~O4 IoIR 49 MiN ".00 SEe

)( • )1820'.,47 ,,.Y = ~4671600t~O FT

Z , -1887 936,"J ,,.XOOT I "4'~9 •• 9 '''/I,C

YOOT • -262'. !U "/SIC

ZeOT :; ·"~".~8 FT/SEC

)( .. .2.~206J66'8 ER

Y • -.2232 11 '6321 ER

Z ;: -,O90220~OO6 EFt

)(COT III -.'84.002168 ER/IoIIlt

VpOT II: -,4520a96119 ER/~~

ZpOT • -.Z024".'492 ER/~~

WT • '"9~,10 L.B

31

TABLE IV.- CSM REFSMMAT

(a) Launch through MCC-3 maneuver

[Earth orbit insertion]

Fe T OSKV DECIMAL.

XIX~ 6:3113 ",80333900XIXE 41400

XIVE 10J66 ,5301 3910XJVE J4142

XI~E 04256 ,2 712 899 0XJZE 15012

VIXE 011 7:5 ,07758620'fIXE 22604

VIV~ 1Q!)5? ,544837 60VJVE 11721

YIZE 62'10 .. ,A3494450VIZE .42:55

ZlXE ~!> 43~ .. ,5 9044620ZIXE 42044

ZIVE 65465 ",,6496 9520ZIVE 662J~

ZIZE 70255 .. ,4788 2 090ZIZE 57'61

32

TABLE IV.- CSM REFSMMAT - Continued

(b) Mcc-4 maneuver through Mcc-6 maneuver

[Lunar landing site]

FeT DsKV DFCtMAL

XPE 17152 ,9505 474 0XIX!: :54231

XIVE 73244 .. ,2924 6010XlvE 45255

XIZE 76247 ... 10 45'0 90XIZE 6566:5

VIXE 77566 ""n1675490YIXE 67632

VIVE 7166:3 .. ,:584:5 648 0YIVE 51045

YIlE 16011 .92302920'''I ZE 16442

ZIXt. '13023 -,3101 2720llXE 56007

ZIYE 61 77 2 .. ,8756 3160ZP'E 72333

ZIlE 720 4 6 ",,37025720lIlE 73221

33

TABLE IV.- CSM REFSMMAT - Concluded

(c) MCC-7 maneuver through entry

FCT D5KY DECIMAL

XIXE 15153 .825:>9312XIXE 10221

XIYE 10021 .5U2085~.3

XIYE 02553

XIZE 04075 .2574997SXIZE 16010

YIXE 77733 -.OU4S019~

YIXE 43662

YIYE 07312 .4021912L1YIYE 10516

YIZE 61637 -.8t)b-'688dYIZE 62667

ZIXE 66701 -.5042~79't

ZIXE 65622

ZIYE 135~.3 .7.3095103ZIYE 36333

ZIZE 06110 .3d3d422~

ZIZE 157~0

34

TABLE V.- CSM NAVIGATION UPDATES


)( OO,~, 1.8403574.0'X 05741

V 01'5, 9,3?666tC·07V 0163t

Z 0104:! 5.8ro11~6"'07Z 2625~

X"'~CT 7442~ p.4,537R463+03X"'r'lC T 6261C

V"OCT 11:>4C 1.2113619·04V"'f)C'T 0762~

Z-nc T 0544' 7,320021 4*0 3Z"DCT 3346~

,.00136 A 16 47,56

T 0122~

35

TABLE V.- CSM NAVIGATION UPDATES - Continued

(b) MCC-l maneuver

36

TAB1E V.- CSM NAVIGATION UPDATES - Continued

(c) 101-1 maneuver

)( 77J1C ~8,31141035"O~

X 71;'71

V 00007 2,0 739391"'0 5V 2673:!

Z 777JJ? "8,65 92552"'0 5Z 7100~

X-DCT 14:30~ 4,0638651·03X--reT 37034

v.. rCT 2~~S4 5,2 17646 9+03V-reT o 22

Z-DCT 112614 3.06838n2·0JZ... neT 16061

T OJi 74 7S :n 43'1 7T 11 1~

37


(d) LOI-2 maneuver

X 7747~ "5.1 9 56790+06X 6551?

" 0016( 3.0127.22"0 6

" O:3G:3r.

Z OCU5~ 1.1586&10"'06'l. 0;344('

X-De T . 11121 3,0')52858"'03X-DCT ,nO!

""'DCT 14533 4 .159~H26.03Y-DCT 12 421

Z-D'CT 05341 1.7 A51 8t42+03Z-nCT 35232

T 0333~ 79 '38 45.52i lJ~5C

38


(e) Separation from LM

)( 0027~ 5,OQ3 4 732*06)( 20J2~

y 00151 2.9 A74014"'06If 0410 4

Z 000 61 1.33598 19.0 6Z 2651'

X-nCT 10 634 2.8092:591'*03X"DeT 34044

y-DCT 6~~1? t"4.1'30C 77 +0)Y-OCT 6642~

Z"DCT 7267';. "'1.6 R50430"'03Z-nCT 5345.,

T 042. 61 98 ?-3 15 ,62T 32652

39

TABLE v. -' CSM NAVIGATION UPDATES - Concluded

( f) TEl maneuver

x_ 71H:.Z- -5 .. 9666077·06X 4000~

Y 00044 9.6'63251·05Y 00055

Z- 0001~ . 2.2100952+0 5Z 01501

XO!'DCT 02552 8.8~54185·02X~bC'T ~4'Ot

- y"DCT __ 1664~ - . 4.8640506"'03Y"nCT 27031

Z"'OCT 0616E 2.0446628+0 3C Z"'OCT ~J~02

T. O~PO~ .1'7 8 22J4CT 1220C

40

TABLE VI.- 1M NAVIGATION UPDATES

(a) DOl maneuver

1- 77~UO - .... 997l~b1+lJoX '12110

Y 77613 -3.1 "U'I1 btHUbY 7'1OU1

i. 7771'1 -1.JI;90 ...... ~+UbL !:d ;)~U

X-DOT 66bJJ -J.U11J978+uJX-DOT '1J70~

V-ooT 1'1370 .... U96JbJl+UJY-uOT 267 .. 7

~,. _._. _.- -

Z-uUT 05020 1.bb091.l7+UJZ-UUT 1J 77'"

T O",~U7 99 .l1 ~8.I;U

T 12J!)O

41

TABLE VI.- LM NAVIGATION UPDATES - Continued

(b) Phasing

x.- ------ +----------

y

y

U0320 S.~90~28b+Uo

Ii 0 g 6!i ------ --_.._-.. ----- ----- --_.--.

--17 7-2-1--- -----} .. -2 b 3-0 3-'H ... (J 653310

i 77700 -~.2082S2~+O~

.-..-.-- -. --2 ..- -----------------~.~-- -.-------- --------- --- --.. -._--

X-LJorX-DOT,

V-DOT.. ------- --¥.~------

I-I)-OT·Z-DOT

-J ~lJ~oSS6!)

b001S

'617~

--1-1"'~1--

'i7023

-}.252J07'i+U3

-Lt.99&+S052+U",._------------_.

T--_ ..,---,.+----

O~2'il lOU 3&+ 20.89·-----,f-,IJ~Otf_i_l,2----_.-.. -.---- ---....---.----- ..- ..-------

42

TABLE VI.- 1M NAVIGATION UPDATES - Continued

(c) Insertion

X 00317 !:J. ~876j2b+lib3~6i5

.. --...

X

V 00077 1.7U80111+UbV 21464

Z 00036 8.122836,++U5Z 0·7100 ..

X-')JT 04355 1.46464-6:)+03X-JUT 2611~

V-JOT ~0623 -4-.9909998+03Y-)JT 45225-

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

Z-I')JT 71575 -2.u518125+037-)OT 77S47

T O~314 1u2 31 17.30T 254-b~

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


(d) CSI maneuver

- it • 8 7 1 2. 'f 'I 2 + U6x..._-_._-_ .... ~-_.- -_._.

77512.---~7.u.C+l-i.-;l-=!:)~------..--..--...--.-.---

yY

X... DOT>'-110T

7771'f.-bl-o-2~.--·..

. 6~.377 .SJ03'i

-,j.!09001'++l/6

-1.J8263a9+U6

-:;. 1-1 } 2. 173 +{j 3

Y-DOT- ¥-I)..Q..l- .---.--.

1~2'f'f ~.O'f2.b8'+2+0J

J §it ~.J..1--_._. __..... -.- ... -.----.-...

Z... OOTL-I)OT

T.• _ •. o· ._I--,,-- ......

"--_._._.. -- ... _....._-_ ...._--

O~337

----ll!i 7 S 11

}ee270"+9'i+1I3

lOJ 21 L16.lIO

44


(e) CDH maneuver

A 0026~ 't • 13 7 1 7!;) 7 b + 1I b

.~ 1..Q..l.,}-J- ._--_ ... - -----

y UfJlb'i J.l'i026S3 ... n6y 32102

l UOiJ6J i.J957127+U6L 35012·

X-JOT 1 1J~b J.IUSllU9+(J3;~ - ) Ot- 31251

Y-lid T 63"126 - '•• 0 8 6 6 7 18 + UJV-dOl ~6~Gl--·-- -- --- ._--- .- -"-"-----'

l-·)OT 721b7 -1.6'1S07"11+U3L-'}IJl 71"173

'T UIt J 6 '1 10'. 19 Lj 2 • '10T L17 J+U

45

TABLE VI.- 1M NAVIGATION UPDATES - Concluded

(r) TPI maneuver

X OOU'fJ 9,61StH29+11SX ~070'f

Y 77lt65 -S,'tJ .. 7SJ2+0c,y 7 1175

l 77bS'f -2,2'f58622+U6Z S60 II

X-lJOT S1617 -S,J21lf6S2+0JX-DOl 5»627S

y-OOT 7S~ZO -7, ~&"'O~d7+02Y-OOT 730Jl

Z.OOT 76~66 -",161'+191+U2Z-OOT 02'11"

T 0"1102 10 ... S6 S9,"0.T 0066 ..

TABL

EV

II.-

DET

AIL

EDM

JV1E

UVER

TABL

ES

(al

Ev

asi

ve

man

euv

er

CST

AI"

LsT

A10

STA

Ir'

'viT

94

575.

6[')

....C

gET

V0

C.0

GE:T

V0

0.f

)GF

TV0

0•n

wL---

.-.

CD~

RH

EART~

G[T

RCl

0.0

'WF

•on

GEt

I4

28

47

.6~t

Ba

2.2

DTtg

0.59

REFs

"'IM

AT

DEL

P,9

1FE

r21

174

7,6

I",0

0;0,

V4.

13I'l

lRE

FDE

LV

~,23

DVM

19

,7ve

x"4

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18

C.7

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v!-I

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.0Ve

V-.

6IP

25

4.4

pB,n

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83

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15

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359

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177

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VP.0

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pH

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131

114

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L-AN

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P~OO

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13

1.6

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68

16

96

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LLL

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428

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OPT

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TABL

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EDM

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TABL

ES-

Con

tinu

ed

(b)

MC

C-l

man

euve

r

CS

TAID

l.sT

A10

STA

IDW

T9

45

75

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weGE

TV0

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GEoT

Va

°to

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WLCO

DpRE

FEA

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GE'T

R0

a,0

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,00

GET

!9

384

6,4

Dr

80

,.5

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REFs

MM

Ar

DEL

p,9

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t26

274\

6,4

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4.14

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EF

DEL

V_

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57

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X-,6

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.0YH

16

7,2

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eVRE

tv'.0

VcY

11

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92

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31

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.JD

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53.9

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80

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90

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10

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2924

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16e

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fLTA

P0

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-51

15

7:

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15

1,9

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,91

82

26

48

PLL

s0

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PHAS

E,0

00

I3

1,7

00

0L

Ll..S

al'

lE

P~AS

DCT

'00

00

wp

318

,46

88

RLL

S,n

coW

EDGE

A"'G

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58

TABLE VIII.- FDAI ANGLES FOR LM MANEUVERS

Maneuver Roll Pitch Yaw

DOI 0.600 286.100 -0.

Phasing 0.600 264.400 -0.

Insertion 180.000 242.100 360.000

eSI o. 105.800 -0.

eDH 180.000 2.300 360.000

TPI 0.240 196.689 0.120

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71

TABLE XI. - MANEUVER PADS


P30 MANEUVER-

PURPOSE

SET STARS S p s /C & N PROP/GUID

9 4 5 7 5 .6 WT N47

R ALIGN + 0 0 0 9 1 PTR1M N48

- - -P ALlGN_ + 0 0 0 2 3 Y

TR1M- -Y AlIGN_ + 0 0 0 0 4 HRS GETI--

+ 0 0 0 2 8 MIN N33+ 0 4 7 5 6 SEC

ULLAGE No ullage + 0 0 0 5 1 I'NX N81

+ 0 0 0 0 0 I'Ny+ 0 0 1 9 0 "N Z

8-

X X X 1 1 R

X X X 2 5 4 P--- --

X X X 3 5 9 YHA

-+ N44

+ 1 1 9 4 Hp (DMT)

+ 0 0 1 9 7 6VT

HORIZONjWlNDOW _ X X X 0 0 3 BT

X 0 0 1 5 5 6VC-

X X X X 2 4 SXTS

+ 2 7 3 3 0 SFT

+ 0 8 2 0 0 TRN

X X X BSS

X X SPA

X X X SXP

OTHER 0 LAT N61

LONG-t RTGO EMS

+ V10

I GET O.OSG

72

TABLE XI.- MANEUVER PADS - Continued

(b) MCC-l

P30 MANEUVER

PURPOSE

SET STARS C' p s VG & N PROP/GUID,j

9 4 5 7 5 .6 WT N47

RAl.IGN + 0 0 0 9 1 PTR1M N48

- - -

P ALlGN_ + 0 0 0 2 3 YTR1M

- -y ALlGN_ + 0 0 0 0 9 HRS' GETI- -

+ 0 0 0 3 8 MIN N33+ 0 4 6 3 8 SEC

ULLAGE No ullage - 0 0 4 2 9f:N

X N81

+ 0 0 1 0 ,- f',.Vy---------- )

- 0 0 3 6 0f',.V z

X X X 0 0 7 R

X X X 0 9 2 P

X X X 0 1 1 Y

+ HA N44

- 0 0 0 5 J Hp (m1T)

+ 0 0 5 7 0 L\VT

HOI IZONj'NINDOW _ X X X 0 0 8 BT

X 0 0 5 3 9 f',.VC

X X X X 1 6 SXTS

+ 0 9 9 5 0 SFT

+ 2 4 6 0 0 TRN

X X X BSS

X X SPA

X X X SXP

OTHER 0 LAT N61. ~- f--

LONG+ RTGO EMS

+ VIO

I GET O.OSG

73


(c) LOI-l

P30 MANEUVER

PURPOSE

SET STARS S P S /G & N PROP/GUID

+ 9 2 4 2 8 WT N47

R ALIGN + 0 0 0 9 6 PTR1M N48- - - YTR1MP ALlGN_ - 0 0 0 2 5- -

Y ALlGN_ + 0 0 0 7 5 HRS GETI--+ 0 0 0 4 5 MIN N33+ 0 4 3 1 7 SEC

ULLAGE No ullage - 2 9 1 2 9 tNX N81

- 0 5 8 7 4 6Vy

- 0 2 0 1 0 6V ZX X X 3 5 6 R

X X X 2 2 8 P

X X X 3 4 2 Y

+ 0 1 7 1 3 HA N44

+ 0 0 5 2 1 Hp (DMT)

+ 2 9 7 7 9 6VT

HORIZON/'NINDOW _ X X X 6 0 2 BT

X 2 9 7 2 2 6VC

X X X X 2 1 SXTS

+ 2 6 7 5 0 SFT

+ 1 6 0 0 0 TRN

X X X BSS

X X SPA

X X X SXP

OTHER 0 LAT N61

LONG+ RTGO EMS

+ Vl0

I GET O.05G


(d) L01-2

P30 MANEUVER

PURPOSE

SET STARS S P S/G & N PROP/GUID

+ 6 8 8 6 7 WT N47

R ALIGN + 0 0 1 4 4 PTR1M N48

- - - ---- YTR1Mp. ALlGN_ - 0 0 0 6 6

- -Y ALIGN_ + 0 0 0 8 0 HRS GET!-- -

+ 0 0 0 1 0 MIN N33+ 0 4 5 5 2 SEC

ULLAGE 2 quad - 0 1 3 8 5 6VX N81

20 second + 0 0 0 0 0 6Vy

+ 0 0 0 0 06V

ZX X X 0 0 0 R

X X X 2 1 9 P

X X X 0 0 0 y

+ 0 0 5 8 6 HA N44

+ 0 0 5 7 9 Hp (DMT)+ 0 1 3 8 5 6VT

HORIZON/\VINDOW _ X X X 0 1 4 BT

X 0 1 3 2 3 6VC

X X X X 2 2 SXTS

+ 0 1 9 1 0 SFT

+ 0 5 8 0 0 TRN

X X X BSS

X X SPA

X X X SXP

OTHER 0 LAT N61-- -

LONG+ RTGO EMS

+ V1Q

f GET O.OSG

75


(e) Separation from LM

P30 MANEUVER

PURPOSE

SET STARS R C sVG & N PROP/GUID

+ 6 7 8 8 6 WT N47RALIGN + 0 0 0 0 0 P

TRIM N48- - - YTR1MP ALlGN_ + 0 0 0 0 0

- -Y AlIGN_ + 0 0 0 9 8 HRS GETI--

+ 0 0 0 3 5 MIN N33+ 0 1 5 6 2 SEC

ULLAGE RCS only + 0 0 0 0 0 tNX N81

+ 0 0 0 0 0 t:Ny

+ 0 0 0 2 5 t::.VZ

X X X 3 5 9 R

X X X 1 9 4 P

X X X 0 0 0 y

+ 0 0 6 0 0 HA N44

+ 0 0 5 9 5 Hp (DMT)

+ 0 0 0 2 5 ~NT

HORIZONj'NINDOW _ X X X 0 0 6 BT

X 0 0 0 2 5 6.VC

X X X X 1 6 SXTS

+ 2 5 8 6 0 SFT+ 1 5 8 0 0 TRN

X X X BSS

X X SPA

X X X SXP

OTHER 0 LAT Nol

LONG+ RTGO EMS

+ Vl0

I GET O.OSG

76


(r) DOr

~~'-r-

+ 0 0-- ----- -~. ~

-t 0 0- f---- ~--- -

+ 0 ._-

~ f--.

~t~--I

-x~H---

x ~t;.(-x x xI

-- I--- -

--- -- --- -

'---- '----

x X X- _ . . - P--- .-X X~-xtxf--~__L ___

REMARKS:

-

--_.__._------_._._-------....,...-.--,P30 LM tAANEUVER

N81LOCAL

VERT..-

Ullage: 2 quad, 8 sec

77


(g) Phasing'-

P30 LM MANEUVER

T P H A S I N G1. PURPOSE+ 0 0 + 0 0 1 0 0 HR N33

f--

+ 0 0 0 + 0 0 0 4 6 MIN TIG+ 0 + 0 2 0 9 0 SEC

+ ° 1 7 0 4 t:,.VX N81r----+ ° 0 0 0 0 t:,.VY LOCAL•- ° 0 9 5 6 t:,.VZ VERT

+ + °1 1 9 5 4 t:,.VR--X X X X X X 0 4 2 BT

X X X I X X X 0 0 1 R FOAl.--L-

X X XI

X X X 2 6 4 INERI P1 + 01 1 7 2 0 f::,VX AGS N86

~--- -)--t l + °1 00 0 0 tNY AGS

-- --I--~---, - .-t7 AGSi ~ - °I 0 9 2 t>VZ1"--- --

X X X I I X xi X N A COP-.S--+--+2-- --e-X X -I· -1· ·X:EI AZ

--e-

X X : X X 1 EL~~.-_I-_-

REMARKS:Ullage: 2 quad, 8 sec

78


(h) Insertion~- -----------.------

P30 LM ~IIANEUVER

N81LOCAL

VERT

REMARKS:

Ullage: 2 quad, 4 sec

79


(i) CSI

P32 C51 UPDATE

•

HRTIGMIN

5EC C51

+ 0 0- _._. ,---- .__._- -_.-+ 0 0 0...__ . -,._-- .. -. -..-. ._- '.

+ 0

+ 0 0_." -- --_. - _.+ 0 0 0

... .,.. ,+ 0

+ 0 0 1 0 3+ .. ·0 1 0.0' 3- j-3

.. .1 __

+ 04;6.0 i O

+ 00 1 0 5• ~ - - ~ --- t --.-

+ 0 0 0 0 8+ 6' 5 9 "4'0•

HR

mNSEC

TIGTPI

Nll

N37

N86l1VX AGS

11 VY AGS

l1VZ AGS

!J. VX LOCAL N8111 VY VERT

PLM FOAl

•

- -,o 0

Io 0-

ntil~

o I 0f----_

• 11 VX

AVY

6.VZ

AVX

11 VY

l1VZ

N81PGNCS 1----1

LOCALVERT

CHARTS N81LOCALVERT

REMARKS:4 quad, +X


(k) TPI

P34 TPI UPDATE

HR TIG N37MINSEC TPI

t,VX N81t,VY LOCALt, VZ VERTt,VRRLM FOAl N42PLM INER

R TPI N54TIG-5

R TPIF/A{+/-} N59R/L{+/-} t,VD/U{+/-} LOSBT

F/A PGNCS N59R/L t,V

DIU LOS

F/A CHARTS N59R/L t,V .....

LOS 0-

D/U t-

~

•

•

•

- ~ .

o 0

o 0•

••

•

ONBOARD LOG

+ 0 0 2 4 8..- .....- I-- .. - i -_.

+ 0 0 0 0 1_.'--I--"-~' _....

• - 000 0.1

+ 0 33 ,14• .-.. I-- . ..L ...• •.. _

- 0'1'0 97• •

••

o 0

o 0....... --- t--

o 0

X XX 0' 0 ' 0. . . __.....:..._._.t _

X X X 197

xxxxxxxxxo 0

o 0 .. - ...... . t--

o ,0

o 0

x X Xo 0

+'Oio' +'O:0!1 1 0 5- -- ~ -- : _. i -1-- ... :-_._; --;- t---- j--'

+10,00 +,000 Oi8- '-- .. ----'.-- .. ---- .-----\- ;---1--·_·'·+ 0 i.! + 05'9. 4i O

x X X.- - .. -- .-X X X

. + 0 0

+ 0r--

o

+ 0!o,212;1.- -. +-_. I-- -., ..:..-

+ 0:0 010:1~ .. - ,-'" -: -.~ 0 i'o:1--' i--: 3

,~

!x X

o 0

o 0

I 0 0

..

r.-----i REMARKS:

4 quad, +X

-82

TABLE Xl.- MANEUVER PADS - Continued

(1) TEl

P30 MANEUVER

PURPOSE

SET STARS S P S I7G & N PROP/GUID

+ 3 6 6 6 6 WT N47RALIGN - 0 0 0 7 2 PTRIM N48- - -P ALlGN_ + 0 0 0 2 3 YTR1M- -y ALlGN_ + 0 0 1 3 7 HRS GElI--

+ 0 0 0 2 0 MIN N33+ 0 2 2 4 1 SEC

ULLAGE 2 quads + 0 3 6 1 B.l ~VX N81

20 second - 0 0 3 4 8 ~VY

+ 0 1 7 6 4 ~Vz

X X X 1 8 0 R

X X X 0 5 1 P

X X X 0 0 1 Y

+ N A HA N44

+ 0 0 5 9 1 Hp (DMT)

+ 3 6 2 2 7 ~VT

HORIZOt"-l/WINDOW _ X X X 2 4 9 BT

X 3 6 0 4 8 ~VC

X X X X 1 1 SXTS+ 0 1 4 9 0 SFT

+ 2 1 8 0 0 TRN

X X X BSS

X X SPA

X X X SXP

OTHER 0 LAT N61

LONG+ RTGO EMS

+ VIO

I GET O.OSG

..

83

TABLE XI.- MANEUVER PADS - Concluded

(m) Lunar entry

LUNAR ENTRY

M I D P A c AREAI-- -

X X X X X X 0 0 0 R .OSG

X X X X X X 1 5 3 P .OSGX X X

.~X X X 0 0 1 Y .OSG

~I--

1 9 1 3 3 3 2 GET HOR

X N ACK

X X X X X P EI-17--,- I -0 - 0 1 5 1 1 LAT N61- --- +-t--f-

I - 1 6 5 0 0 LONG-JX X Xl --f- X X X 0 6 8 MAX G

+

*+~3 1 0 V400K N60i-

!f-- -- 0 0 - 0 10 6 5 2 Y 400K

+ + 1 2 2 2 0 RTGO EMS

+ + 3 6 I 3 9 0 VIOI-- -- '---- -- -1 ---r--

! , n 1· 5 i 0+ 3: 2 RRT-++ I.L 7

xix Oi#2:8X X I • RET .05G' .~-

+ o '~~--L+ +100 Ni A DL MAX1-- N69

+ 01 0: • I +~NIA DL MINI--t--rJ------T-

>-:;:-~ ! lirAV

LMAX+

I-- -- 1-""""1--1-- ~ VL MIN+ + I NI A--J--t-jX~xm

---X X X I DO

-- f-3_+.2<+0 2 0 B REl VCIRCX X

'-- --X xi X i X 0, ~gi 8 RUBBO

It---

X X,

X I X 0 3. 2 0 RETEBOI I-

X X I X X 0 8: 1 6 RETDROI- r- ,

X X X X I X X X Xl N A SXTS

+ 0 +! N' A' 0 SFT EI - 2

0 0---t--

N A 0 0 TRN+ +-- --- ~-f- --- ---

X X X I X X X N A BSSr--- t-----X X I X X N A SPA EI-2

1--

X X X X X X N A SXP

X X X X X X X X u P LIFT VECTOR

84

REFERENCES

1. Apollo Mission F (AS-505/CSM-I06/LM-4) Spacecraft OperationalTrajectory, Revision 1. April 28, 1969.

2. CSM/LM Spacecraft Operational Data Book, Volume III - Mass Properties.Amendment 34, November 1968.

3. CSM/LM Spacecraft Operational Data Book, Volume III - Mass Properties.Amendment 50, November 1968.

•

MSC INTERNAL NOTE NO. 69.FM - NASA · msc internal note no. 69-fm-137 project apollo apollo mission...

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Transcript of MSC INTERNAL NOTE NO. 69.FM - NASA · msc internal note no. 69-fm-137 project apollo apollo mission...