nasa · 2015. 3. 9. · msc internal note no. 69-fm-137 project apollo apollo mission f...
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MSC INTERNAL NOTE NO. 69.FM.137
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00/99Unclas16270
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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
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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
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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
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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
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'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.
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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
"
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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
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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 ~Vupdates 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
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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)
Thrust, IbW, Ib/secI ,sec.sp
CM RCS (per quad)
Thrust, IbW, Ib/secI ,sec.sp
1M RCS (per quad)
Thrust, IbW, Ib/secI ,sec.sp
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
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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
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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
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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.rn17(':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
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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
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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 ,
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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
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12
TABLE 11.- CSM RESET VECTORS
(a) Evasive maneuver
(~EAN 6_;S_§J LI AN)EARTH REFERF-NCED
GET ;;
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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/SECZOOT = 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 .-
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14
TABLE 11.- CSM RESET VECTORS - Continued
(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 FTZ 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 ERZ ;: .,4068356864 ER
XCOT I: 12~6~'t~6~.6 ER/HR
Year I: ,7637346163 ER/HRZOOT I: ,409J660419 ER/HR
WT II 9Z~2A,no l..s
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15
TABLE 11.- CSM RESET VECTORS - Continued
(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
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16
TABLE 11.- CSM RESET VECTORS - Continued
(e) Separation maneuver
(~t;A.N BE~ lLlAN)~UNAR REFERENCED
GET • 97 HR 3' Mr t\! .00 SECX = ..~_O 5~ ~ 71 •62 FTV • 109~6'.14 FTZ = .6403'.54 FT
XOOT = 66. 93 FTlsECVeOT =: 4~37,:?3 FT/SEC
ZOOT • 2056,68 FT/SECX = "',28 92214209 ERV • ,00 52)12201 ERZ c "',00 3 0602286 ER
XeO T • ,°t1~_~ ~'7~_? ER/HRVeOT ;: .84 9JtSS6415 ER/HR
ZeOT • ,3538256884 ER/HRWT = 6I~8'5,Q6 LoS
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17
TABLE 11.- CSM RESET VECTORS - Continued
(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 ERV = "',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
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18
TABLE 11.- CSM RESET VECTORS - Continued
(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 ERY = ,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
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19
TABLE 11.- CSM RESET VECTORS - Continued
(h) Insertion maneuver
(MEAN BESSiLIAN)~~NAR REFERENeED
",.
GET : 10~ HR a3 MI~, .00 SECX 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/HRZOOT • -,'1"9.2e268 ERIHR
WT ;I 36474,12 ~B
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20
TABLE 11.- CSM RESET VECTORS - Continued
(i) CSI maneuver
(ME.AN BESSILUN)I..UNAR REFEReNcED
GET II 100l HR 1~ MIN .00 siC
X • -,926831 ,00 FTV 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 ERV • "',2011625451 ERZ 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
..
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21
TABLE 11.- CSM RESET VECTORS - Continued
(j) CDR maneuver
(MEAN 8E&SJ~IAN)~UNAR REFERENeEO
GET • S.04 HR 12 MhJ .00 SECX • 3601290.09 FifV • 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 IERV • ,Z134162928 ERZ • ,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
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22
TABLE 11.- CSM RESET VECTORS - Continued
(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
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23
TABLE 11.- CSM RESET VECTORS - Continued
(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 FTX-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
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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
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26
TABLE 111.- 1M RESET VECTORS - Continued
(b) Phasing maneuver
(MiAN BESSILI'N)~UNAA RE'ERENeEO
GET , 100 \l4R a6 MIN ,DO ~EeX • ~164995.a7 ,,.V ;; 'Z94554,19 ,,.Z , 6J9~28.96 ,tXPOT : 1350.'7 'T/SEC
VcOT • ....984.~1 'T/S£CZeOT -= -2051.16 ,,./8£C
)( :; ,2659'0241J2 E~
V I; ,061'6420'10 E~
Z 11 .030l57'1,932 ER
XOOT • .2l2J'2d9!6 ER/IolRVcOT • ·,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/IICveo' • ·~~48.'9 'T/SECZOOT , -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/\oIRZOOT • ·.2641:S6!U60 ER/\oIRWT • 30618.'0 LB
-
28
TABLE 111.- LM RESET VECTORS - Continued
(d) CS1 maneuver
GET • 10~ ~R 2,' MiN ,00 SEex • ·'Oz,~o•• e1 ItTy • .4660~'S.9, FTZ • -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~/~PtZeOT ;: .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 FTZ ;: 201'!:H .12 'TXCQ' " .626.05 'T/81eYCOT iii "'2'82.'1 FT/SEC
200T • .991.81 FT/SEC)( II ,146~20i6n8 E~
y I .ia4,.).,62 liltz !II ,Q962704942 ER)(OOT • •"'1'12'06 IR/~'"YoOT • "',444a011070 ER/~RZOOT • ,,,,,, 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 FTZ , -1887 936,"J ,,.XOOT I "4'~9 •• 9 '''/I,C
YOOT • -262'. !U "/SIC
ZeOT :; ·"~".~8 FT/SEC
)( .. .2.~206J66'8 ERY • -.2232 11 '6321 ERZ ;: -,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~.3XIYE 02553
XIZE 04075 .2574997SXIZE 16010
YIXE 77733 -.OU4S019~YIXE 43662
YIYE 07312 .4021912L1YIYE 10516
YIZE 61637 -.8t)b-'688dYIZE 62667
ZIXE 66701 -.5042~79'tZIXE 65622
ZIYE 135~.3 .7.3095103ZIYE 36333
ZIZE 06110 .3d3d422~ZIZE 157~0
-
34
TABLE V.- CSM NAVIGATION UPDATES
(a) Evasive maneuver
)( 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
TABLE V.- CSM NAVIGATION UPDATES - Continued
(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
TABLE V.- CSM NAVIGATION UPDATES - Continued
(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;UT 12J!)O
-
41
TABLE VI.- LM NAVIGATION UPDATES - Continued
(b) Phasing
x.- ------ +----------
y
y
U0320 S.~90~28b+UoIi 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~
. -- ~. ----- _... ._--
-
TABLE VI.- LM NAVIGATION UPDATES - Continued
(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
TABLE VI.- LM NAVIGATION UPDATES - Continued
(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.-
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tinu
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(b)
MC
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TAID
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(c)
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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.
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TPI 0.240 196.689 0.120
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00
00
11T
IGN
03
34
180
104
5.5
2
12T
IGN
30
05
0
-
TABL
EIX
.-CS
MEX
TERN
AL
~V
UPD
ATE
S-
Co
nti
nu
ed
(e)
Sep
arat
ion
from
LM
'01
0FC
TD
SKY
V71
DE
CIM
AL
1IN
DE
X
2AD
D
3V
GX
00
00
0O
.
4V
GX
00
00
00
\W
5V
GY
00
00
0o.
6V
GY
00
00
0
7V
GZ
00
00
00
.25
00
00
00
E0
1
10
VG
Z3
71
54
11
TIG
N0
41
66
98
35
15
.60
12
TIG
N0
73
50
-
TABL
EIX
.-CS
MEX
TERN
AL
6VU
PDA
TES
-C
oncl
uded
(1')
TE
lm
an
eu
ver
01
0Fe
rD
SK
YV
71D
EC
IMA
L
1IN
DE
X
2A
DD
3V
GX
02
60
30
.36
18
06
62
E0
40
\
4V
GX
22
10
7+:
-
5V
GY
77
76
2-0
.34
75
24
18
E0
2
6V
GY
56
10
1
7V
Gl
00
10
40
.17
64
49
70
E0
3
10
VG
l3
27
20
11T
IGN
05
71
11
37
20
22
.41
12
TIG
N2
67
00
-
TAB
LEX
.-LM
EXTE
RN
AL
t:::.V
UPD
AT
ES
(a)
DO
rm
aneu
ver
OlD
FCT
DSK
YV
71D
EC
IMA
L
1IN
DE
X
2A
DD
3VG
X7
77
44
-0.7
10
99
99
7E
02
~
4VG
X5
02
57
V1
5VG
Y0
00
00
O.
6V
lJY0
00
00
7V
GZ
77
77
7-0
.27
00
00
00
E0
0
10
VG
Z7
45
01
11T
IGN
04
21
39
93
35
8.8
0
12
TIG
N2
74
50
-
TABL
EX
.-LM
EXTE
RNA
L~v
UPD
ATE
S-
Co
nti
nu
ed
(b)
Ph
asi
ng
man
euv
er
01
0F
Cr
DSK
YV
71D
EC
IMA
L
1IN
DEX
2A
DD
3V
GX
00
10
20
.17
04
00
00
E0
30
'\
4V
GX
17
30
10
'\
5V
GY
00
00
0O
.
6V
GY
00
00
0
7V
GZ
77
73
2-0
.95
59
99
96
E0
2
10
VG
L6
63
60
11T
IGN
04
24
61
00
46
20
.89
12
TIG
N0
75
10
-
TA
BL
EX
.-LM
EXTE
RN
AL
/',.V
UPD
AT
ES
-C
on
tin
ued
(c)
Inse
rtio
nm
aneu
ver
OlD
FeT
DSK
YV
71D
EC
IMA
L
1IN
DEX
2A
DD
3V
GX
77
66
6-0
.18
91
99
99
E0
3
0'\
4V
GX
45
72
2--.
.:l
5VG
Y0
00
00
0.9
99
98
00
0E
-Ol
6V
GY
01
17
7
7V
GZ
77
73
7-0
.83
89
99
94
E0
2
10
VG
Z5
04
24
11T
IGN
04
32
11
02
43
17
.80
12
TIG
N0
21
04
-
TABL
EX
.-LM
EXTE
RNA
L~V
UPD
ATE
S-
Co
nti
nu
ed
(d)
CSI
man
euve
r
DID
FC
rD
SKY
V71
DE
CIM
AL
1IN
DE
X
2A
DD
3V
GX
00
02
30
.50
50
00
00
E0
2
0\
4V
GX
26
36
2co
5V
GY
00
00
0O
.
6V
GY
00
00
0
7V
Gl
77
77
7-0
.60
00
00
00
E0
0
10
VG
l7
04
04
11
TIG
N0
43
43
10
33
34
6.0
0
12
TIG
N2
14
50
-
TABL
EX
.-1M
EXTE
RNA
L~V
UPD
ATE
S-
Co
nti
nu
ed
(e)
CDR
man
euve
r
01
0FC
TD
SKY
V71
DE
CIM
AL
1IN
DE
X
2A
DD
3V
GX
77
77
7-O
.SO
OO
OO
OO
E0
0
4V
GX
-06
00
5(j\
\0
5V
GY
00
00
0o.
6V
GY
00
00
0
7V
GZ
00
00
10
.33
00
00
00
E0
1
10
VG
Z1
11
46
11
TIG
N0
43
70
10
431
42
.40
12
TIG
N3
04
40
-
TABL
EX
.-LM
EXTE
RNA
L~V
UPD
ATE
S-
Con
clud
ed
(r)
TPI
man
euve
r
OlD
FeT
DSK
YV
71D
ECIM
AL
1IN
DEX
2A
DD
3VG
X0
00
10
0.2
20
99
99
9E
02
4V
GX
23
72
2-.
J0
5VG
Y0
00
00
0.0
99
99
99
9E
00
6VG
Y0
11
77
7V
Gl
77
77
3-0
.11
30
00
00
E0
2
10
VG
l6
27
30
11T
IGN
04
40
61
05
85
9.4
0
12T
IGN
15
36
4
-
71
TABLE XI. - MANEUVER PADS
(a) Evasive maneuver
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
YTR1M- -
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 9 f: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 TRNX X X BSS
X X SPA
X X X SXP
OTHER 0 LAT N61. ~- f--
LONG+ RTGO EMS
+ VIO
I GET O.OSG
-
73
TABLE XI.- MANEUVER PADS - Continued
(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 9tN
X 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 02 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
-
TABLE XI.- MANEUVER PADS - Continued
(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 56V
X N81
20 second + 0 0 0 0 0 6Vy
+ 0 0 0 0 0 6V 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 X0 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
TABLE XI.- MANEUVER PADS - Continued
(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 PTRIM N48- - - Y
TR1MP 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::.V ZX 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
TABLE XI.- MANEUVER PADS - Continued
(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
TABLE XI.- MANEUVER PADS - Continued
(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 X
I
X X X 2 6 4 INERI P1 + 01 1 7 2 0 f::,VX AGS N86
~--- -)--t l + °1 0 0 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
TABLE XI.- MANEUVER PADS - Continued
(h) Insertion~- -----------.------
P30 LM ~IIANEUVER
N81LOCAL
VERT
REMARKS:
Ullage: 2 quad, 4 sec
-
79
TABLE XI.- MANEUVER PADS - Continued
(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 VXAVY
6.VZ
AVX
11 VY
l1VZ
N81PGNCS 1----1LOCALVERT
CHARTS N81LOCALVERT
REMARKS:4 quad, +X
-
TABLE XI.- MANEUVER PADS - Continued
(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 0o 0
....... --- t--
o 0
X XX 0' 0 ' 0. . . __.....:..._._.t _
X X X 197
xxxxxxxxxo 0
o 0 .. - ...... . t--o ,0o 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 0o 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 N8120 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 24 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-J
X 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 7xix Oi#2:8X X I • RET .05G' .~-
+ o '~~--L+ +100 NiA DL MAX
1-- N69+ 01 0: • I +~NIA DL MINI--t--rJ------T-
>-:;:-~ ! lirA VL MAX+I-- -- 1-""""1--1-- ~ VL MIN+ + I NI A--J--t-jX~xm
---X X X I DO
-- f-3_+.2
-
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.
•