c E-1142 (REV. 12) (UNC USSlFIED TITI.3 ) SYSTEMS STATUS RE PORT September 15, 1963 I Y ;.I COPY# 94 OF /!,-8COPlES THIS DOCUMENT CONTAINS 2) PAGES
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c
E-1142 (REV. 12)
(UNC USSlFIED TITI.3 )
SYSTEMS STATUS RE PORT
September 15, 1963 I
Y ;.I
COPY# 94 OF /!,-8COPlES THIS DOCUMENT CONTAINS 2) PAGES
ACKNOWLEDGMENT
This repor t was prepared under the auspices of DSR
Pro jec t 55-191, sponsored b y the Manned Spacecraft Center of
the National Aeronautics and Space Administration through con-
t r a c t NAS9-153
$f-
p" d
This document
the national defens
the meaning of t he Laws, Ti t le 18,
U S C , Sections 793a , the1 ,cansmission
or the revelation of wh y manner t o a n
unauthorized person
Th(1 pUbllcatlon of t h i s rc1)or-t d w s not constitute
approvai by the National Aerc:iiautics and Space Administration of
the findings or t he conc:usions contained the re in It i s published
only f o r the exchange and stimulation of ideas
LIST OF EFFECTIVE PAGES
Page Numbers
Title Page through v
1-1
2-1 through 2-10
3-1 through 3-4
4-1 through 4-3
DieWbbion List
CONTENTS
See t ion
1
1-2 I 1- 1
2 2-1 2-1.1 2-1.2 2-1.3 2 -2 2-3 2 -4 2-5 2 -6
3 3-1 3-2 3-3 3-3.1 3-3.2 3-3.3 3-3.4 3-3.5 3-3.6 3-3.7 3-3.8 3 -4
4
INT RODUCTIOPJ INTRODUCTION ACCURACY
COMMAND MODULE DATA WEIGHTS WEIGHT STATUS REPORTING SPEC. WEIGHT DESIGN LOAD WEIGHT REPORTED WEIGHT CHANGES CENTERS OF GRAVITY MOMENTS OF INERTIA COMMAND MODULE POWER REQUIREMENTS CURRENT STATUS OF COMMAND MODULE AGC PROGRAMS
LUNAR EXCURSION MODULE DATA POWER REQUIREMENTS FOR LEM WEIGHTS FOR LEM REPORTED WEIGHT CHANGES FOR LEM C DU ' S TELESCOPE AND ALL EYEPIECES NAVIGATION BASE IMU INTERCONNECT HARNESS ASSEMBLY DISPLAYS AND CONTROLS AGC, JBX PSA GENERAL COMMENT
GLOSSARY
DISTRIBUTION LIST
Page
1-1 1-1 1-1
2-1 2-1 2-1 2-1 2-1 2 -4 2 -4 2 -4 2 -4
2 -4
3-1 3-1 3-1 3 -3 3-3 3 -3 3 -4 3 -4 3 -4 3 -4 3 -4 3 -4 3 -4
4-1
5-1
9/ 15 /63 DATE -
ILLUSTRATIONS
Figure
2 - 1
2 -2
Table
X, Y, Z axes cf Command Module
Eleetrxal load on Primary + 28 VDC
Page
2-9
2-10
TABLES
Page
2 -I Current weight status of Command Module 2 -2
2-11
2-111
2 -HV
3 -1
3 -11
Command Module center of gravity and moment of
inertia data 2-5
Nominal power dissipation (watts) v s
G & N activity
Current Memory Estimates and Statuses of Command
Module AGC Programs
LEM Power Requirements
Estimated weights of LEM G&N components
2 -7
2-8
3-1
3 -2
. PA61 -
I I .
ABSTRACT
The System Stgtus report is distributed monthly on the 15th. This month's
revision (E-1142, Rev. 123 contains weight and balance data and power requirement
information for the gddance and navigation eqEipment in the Lunar Excursion and
Command Modules. In addition, the first monthly report on the status of Command
Module computer programs has been included.
.
9/15/63 DATE ,-, V
PME
Section 1
INTRODUCTION
1-1 INTRODUCTION
The following information is included in this month's report: (1) weights, centers of gravity, and moments of inertia of G&N equipment in the Command Module and weights of G&N equipment in the Lunar Excursion Module, (2) power requirements of G&N equipment in the Command and Lunar Excursion Modules, and (3) status of Command Module computer programs.
Al l weights in this report, including those for both the command module and LEM, are based upon the current "block I" design releases. saving design changes have been held, in general, for the "block 11" release scheduled for early 1964,
Purely weight-
1-2 ACCURACY
The accuracy of numerical values reported in this revision should not be considered to be within the tolerance implied by the significant figures quoted. Numeri- cal values will approach the established tolerance as design and development phases approach completion.
9/15/63 DAVE PA61 .A8
CM
--: . . i
. L
Sc,:,;cn 2
COMMAND MQDULE DATA
2-1, h WEIGHT STATUS REPORTING, Tabhe 2-1 alsc o f f ~ r s d nomparlscn of present :smpcne?t we'ight; values w:kh :k:~se. llsred in Syszean Siabs Rep-A, E-1142 (Rev. 111, Aug' ls t 15, 1963. AI1 weight ~har:ges aye explained (see 2-2).
2-1.2 SPEC. WEXGHT. The Wpec, Weight" adumn in table 2-1 contains "proposed MSC'" wefghts, that Is, goals set fcr th kJy MSC in a memc $0 M.T dated December 5 , 1962
2-1.3 DESIGN LOAD WE'LHT. The Wesign Load Weight.'? cchmn cen?ains assigned WCPS; es?:rnate design we:@-e l o G&N su5assemsl;es &:ached $?J ?he spacecraft
e imluded in this repnrt 2s h e result of 8" S & ID re- ra Meering Nc. 8, that crx total we'ght figme for supported
MIT herein assigns a tctal G&N C&N load be ass:g.:ed for structural design use. d e ~ i g x load we,gh4 , jr, fasle 2-1, whkh d L c s T C ~ include :';ems )termed 'sloose stored ikrns. The treakdown czf this total weight into the IndivZd~al items of column 'kl" is typical cnlyo
9/15/63 D111.E 2 -1 PAGE -
E-1142
A P O L L O G U I D A N C E A N D N A V I G A T I O N S Y S T E M S T A T U S R E P O R T
9/15/63 D A T E .-.
CM
C G C C 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0
c' C O O C " 0 " d " o " ~ o " 0 0 o " o " O " o " o " o " o " o " 0 ' D O 0 0 0
C G O O
2 -2 P A G E -
E4142
A P O L L O G U I D A N C E A N D N A V I G A T I O N S Y S T E M STATUS R E P O R T
cv P- m
0
0
0 m c c m 0 c c N 5,
m f
-. ,..~ . ... . . _... -.
9/15/63 D A T E ._. 2-3 P A G E <-
CM
A P O L L O G U I D A N C E A N D N A V I G A T I O N
E-1142
S Y S T E M S T A T U S R E P O R T
2-2 REPORTED WEIGHT CHANGES
No weigh: ehatages weye reported TOP khSs month. The PSA and AGC have reached a stcge of developmenk zhdt erda"ces a muzh bette? weight ea1c"Ilatkcn than was possible be- fore, These data, whi. h w'ill inclx?e 8 lar-gs proportion 3f be availa ale ;n %he ne*{ K epcrs L,
a! weighted ;terns, should
2-3 CENTERS OF GRAVHTP
Table 2-1ai presmLs the centers of grav3.y of each w-eight. compone,nt or packaged assemtly, whkh are determined w9h respect to the basic X, Y, Z axes of the Command ModLls shown in figwe 2-1, Center of gravity values ape given to the nearest tenth of an i n ~ h .
2-4 MOMENTS OF INERTIA
Table 2-11 alsc, presents the momenss of inertia of each weight component o r packaged assembly, determened about each of the compone5t axes which (1) run through the center of gravitj of "she component and (2) are parallel to the basic X, Y, Z axes of the Command Module.
2-5 COMMAND MODTJLE POWER REQUIREMENTS
The power requirements of the Command Module G & N equipment on the p r i m a q .d- 28 VDC Power S~pp1-y are shown in figure 2-2, which paesents the magni- tude and l o e a t % o ~ ~ of dissipated power values on a suhassembkj level. This chart asswnes a 14-day l ~ n a r orbit mission.
various mode ope1 ation tmmbinations. Table 2-111 shows the magnitude and location of pswm dissipation fo r
2-6 CURRENT STATUS OF COMMAND MODULE AGC PROGRAMS
Table 2-IBr lists zument memory est%m%tes and the s t a h of Ccjrnrnand Module
A high and Bow word estimate is given with each program. The following AGC programs. LEM AGC programs are not reported at this time.
Ststuses a r e defined:
9/15/63 D A T E .-, 2 -4 P A G E -
E4142
A P O L L O G U I D A N C E A N D N A V I G A T I O N S Y S T E M S T A T U S R E P O R T
C M
E f: a
9/15/63 D A T E ,-, 2-5 P A G E ,-,
.
E-1142
A P O l l O GUIDANCE A N D NAVIGATION SYSTEM STATUS REPORT
C M
n
2 -6 P A C E -
E4142
APOLLO GUIDAIICE AND WAVIGATIOW SYSTEM STATUS REPORT
00
Ln U 0'
m
9. In
od h I
s N
N A'
m
m
0 9 b.
h
m & 0 N m - N
N m m-
9 ui In
h s N
d
0' 3
0 N 4
0 2
0 2
9
\o m'
00 0 0
In
m N m*
In
m N
m- N A' d
6
N 4
N
U d
0
00
r\' r; 0 e m
Ln
U m-
Ln
w m'
v,
D I a 0 m
L
9/15/63 BATE 2-7 M E .-. L
E-1142
Program -.
List Proe e s s Zng Pnte rpreter AGC Executive AGC Waitlister AGC System Exerciser, Checkout,
G&N System Exerciser & Checkout Display, Keybcard, and Telemetry lrnput/Obtprzt Control. Midcsmse and Orbital Navigation Midcourse arid Orbital GLidanee Pre -launch Plat form Alignment
& Error Handler
A P O L L B G U I D A N C E A N D N A V I G A T I O N S Y S T E M S T A T U S R E P O R T
Status
Coded Coded Coded Planning
Planning Programming Programming Programming Planning Planning
1; Planning stage. 2) Programming stage.
2aj Pr c gram coded. 3) 4) 5) Check oct on AGC.
Check 0r.t on AGC simulatfon. Chezk oux en G & N simda-ion.
Table 2-TV0 Current Memt;T Estimates and Statuses of Command Modde AGC Programs
Totals
__ - .
Msmory Estimate (words)
H; gh
1600 250 15 0
1000
1000 1500 850
2000 50C 120 9 80
1290 1000
12240
Low ---
1600 250 15 0 400
750 1024 350
1500 500 12 0 900
1024 400
8968
' This is a temporary status. Normally check-out on the AGC simulator would immediately follow coding and the statement that a program is coded would not be of much interest,. Accordingly, this category will be dropped when sim- ulation commences.
9/15/63 D A T E - 2-8 P A G E - -
1-1142
1 . A P O U O GUIDANCE AND NAVIGATION SYSTEW STATUS REPORT m 1 . 8 ' . ' "
9 / 15 I63 DATE
V w I
t
I s Y
t 5
s *) 0
2 -9 PAU - c
E4142
APOLLO G U I D A N C E A N D N A V I G A T I O N S Y S T E M S T A T U S R E P O R T
IZO"'
4 9-
-- 2,30+ V HOURS 111.l W OPR ( 5 x 1 ON) I62.IW OPR ( X T OFF] caw nissim AW
- +Le PRIMARY GUIDANCE C NAVIGATION LOAD ON PRlUflRY +28VDC
CODE (Cl CALCULATED W E R (el ESTIWTED mwm (REF S t I D LETTER 63 M A 7332) (LE54 THAN 1% ON T l H d W MEASURED W f R 641.9 W WORST POSSIBLE
60L3 W ALL STSTCHS W E R A T I W
u 3 n
+ c E 3 cd
.r(
a cd 0 d
hl I
9/15/63 D A T E .-, 2-10 P A G E ,-,
L E M
,.
Se&ia!I 3
LUNAR EXCURSIOSU' MODULE DATA
Power Time (watts) @rs)
PMU Standby 70 . 100 HMU Operate. 330 6 . 2 AGC 100 30 Optics NegligMe Display and Controls 18 3 Radar Interface CDUqs 26 2
2 Randezvous Radar * 1 Landing Radar
Totals do not include radar loads
* * 474 (peak)*
watts L
3-1 POWER REQUIREMENTS FOR LEM 4
The current estimate of LEM G&N power and energy [see table 3-1 is based upon the flxed-tebmope (sowept and the use of the Command Module IMU
I! and romputer, Earlier e a t h a t e s ~.tsed 8 shorter PMU standby power time than is in-
dicated in table 3-1, The values shown in table 3-1 a re normal avesage power and energy estimates and do n ~ t Endude any factor for bad estimating,
Energy ( h h )
9.0 2.05 3.0
0.05 0.05 * *
12.15 (total)* KWH
The data include checkorut time as required. The computer is turned on and t ime z e r w d at the s b r t of LEM operations and runs at full power for 24 hours an the moon's susfaoe. Separate power turn-on switches are assumed for I M U operate, computer, and radar CDU's. The LEM G&N uses spacecraft + 28 VDC
\
-- supply only. other voltages are generated internally.
3-2 WEIGHTS FOR LEM
Lunar Excwsion Module weights a r e presented in table 3-II. The data, in general, esnfsrm to the information contained in paragraphs 2-1 and 2-1.1.
E-1142
APOLLO GUIDANCE AND NAVIGATION SYSTEM STATUS REPORT
. . . . . . . . . -~ .- - .. .- . . . . . . . . . . . . . . . . .
. . -. ...... -.-_- ...
o m o o o o o o o o o m o
+ r c I 4 - 1 a t$ &4 0" 0" 4 Goo d d &$+
+ 0
!f
0
h
';J a t o o I P O 0 E 10000
cd k . ... -. . . . . . .
'Y
i 1 ....... .....
9/15/63 DATE .-,
c
x
L EM
APOLLO GUIDANCE AND NAVIGATION
E4142
The PQW laheled vgB8re GU%&.me System" is inserted to provide for comparisons with similarly spet:S2ed systems.
3-3 REPORTED WEIGHT' CHANGES FOR LEM
3-3.1 CDUPe. The increase of 3 pollands in the CDU weights refleeus the addition of a sixth CDU i& provide the landing engine thrust magnitude control with an analog carrier interface, Preslz~~mly this interface was assumed to be the direct digital increment asmmand from the AGC outpwt.
3-3.2 TELESCOPE AND ALL E"Y'EPBEGES, The increase in afig'irnent telescope weight is a ceonsequenee of the telescope insbPPation being worked out with GAEC. The earlier figure assumed a 12-imh t&e lookkg directly through the side of the spacecraft. Installation aonstrahta for the spacewaft and radar provided by Grumman have led to the use of a 37-inch long perfscope looking through the top of the spacecraft. The characteristics of this telescope have been changed from a fixed 'IO-degree field of view to a three-position 55-degree field sf view having a fourth storage position. These changes were made fop the following reasons:
a. dish if it gets s t w k in an unfortunate position. b. transfer of a wide field sf viewo Q.
of freedom IMTJ alignment. This depends upon preventing sunlight from striking the objective and assumes that the sunlit earth, moon, or spacecraft does not appear in the field sf view. d. To provide for prote:%lon of the objective elements against deposits arising from cperat:m of the Jets and engines and to prevent abrasion by lunar materials dinring the landing. The fourth storage position can provide
the glass might p r c ~ $ e me~essary and heavy. The weight for the tePesc2pe provides for a separate 2 pound eyepiece for long
To avoid poselble optical line of sight interference with the radar
To prevent the large weight penalty associated with the long optical
To enhance the possibility of finding two acceptable stars for three degrees
this at ~i . lmn~~& rm addit ~al penaltygr. Otherwise some type of door protecting
eye relief emergency operatiion with spaces& helmet faceplate down. This eyepiece would be designed fm 112 pcwer t o save the severe pena le of large glass size. If a helmet transfer teleseape w w x ? used, this weight could be eliminated. The normal eyepiece operates at uni ty power.
* DATE
SYSTEM STATUS REPORT
9/15/63 - 3-3 PA6E -
h
i
I'
APOLLO 6UIDAWCE AND WAVl6ATlOW
E4142
SYSTEM STATUS REPQRT
3-3.3 NAVIGATION BASE, The ourrent installation concept considers the navimion base as four reference buttons in the spacecraft secondary structure opposite the mounting feet of the HMU on one side and opposite the optics attachment points on the other. .M is expected that this positioning can be done for the l-pound saving shown over earlier estimates.
3-3.4 IMU. The change of 1 pound in the IMU brings the IMU up to the weight _I quoted -. . for the command module. This estimate includes a very high proportion of actual weighed items.
3-3.5 INTERCONNECT HARNESS ASSEMBLY . The Interconnect Harness Assembly weight linear densities have been estimated for the various interconnections of G&N ha'rdware. Unlike the command module installation, the G&N in LEM will probably consist of widely separated elements. This means a high usqge of spacecraft cable runs, and only a small amount of cable harness will be furnishgd by the qnufac tu re r with the G&N. T'b new weight figure estimates this effect.
3-3.6 neither This simpUf€cation results in the new estimate tabullated.
S AND CONTROLS, The displays and controls for the LEM will have oud nor the optics aesochted items included in the command module.
3-3.7 AGC, JBX. The previous estimates for the LEM AGC assumed a 12,000- word fixed memory and arrangement to provide partial sparing. The latest concept uses two trays identical with those in the command module, which provides twice the memory capacity, 24,000 words. The weight figure, unchanged from last report, includes the interooansctions between all AGC and PSA trays and assumes, as indicated, that the coldplate is provided as part of the ove ra l l G&N electronics.
3-3.8 PSA, The modules of the PSA for the LEM have been identified and all are identical with modules existing in the command module system. The new figure in- corporates a 50 percent actual weight knowledge of LEM PSA modules.
3-4 GENERAL COMMENT. The common usage of LEM and CM G&N hardware will be based upon block II CM G&N design for those common parts in the LEM. Accordingly, any weight saving changes incorporated into CM block II design that have common usage with the LEM will reflect in a reduction of the LEM weight. The figures do not show this as yet since final MI[T and NASA review of the block II proposals has not been completed.
\
9/15/63 DATE -,
* I3 E LL 0-W S ASS EMB LY :
1NTERCONNECT WIRING HARNESS:
COOLANT HOSES:
CDU & FRAME ASSEMBLY:
D & C/AGC:
*
Enterconnect wiring h a . r n . 3 ~ ~ which electrically ties together the aAssernhlf~.s whish constitute a completely integrated system.
Coolant Hoses: cor.sisLs of (1) molant hose between IMU and spacesrait, optics and spacecraft, and q t i c s a.7d IMU, (2) bracket assembly screws and ~1amps, and (3) entrapped codanto
"Cupling Display Units and frame assembly: all iriter-changeable gear boxes and frame assembly used as a datz. interface among the optics, IMU, AGC, and spacezraft autapilot. (Radar and thrust magnitude in LEM)
Display and Control, Computer: letter and number readout, keyboard, control panel, relags and support structrare.
This applies specifically tcl command m ~ d u l e , though it, can p-ovide a guide to the interpa.etzPon of LEM i';erns. As wique LEM details become better identified, des>rtp'i lms will be ir,sl';dsd.
9/15 /63 M T E
E-1142 c
A P O L L O G U I D A N C E A N D N A V I G A T I O N
D & C/NAV:
G&N Pnd. Cant Panel:
S Y S T E M S T A T U S REPORT
EMU Cmt. Panel:
Optical Shroud & Cover Assy:
D&C Electronics LH
D&C Electronics RH
LONG EYE RELIEF EYE- PIECES
FILM CARTRIDGES:
HORIZON PHOTOMETER:
IT"sp1q,j a d Cmtr*?l , Navigation: cmnsrsts of G&N 11 Panel, ZMU Control Panel, D&C
c h d e s meters, switches, lights, etc. except as re- s, a d Optf:al Shroud. The above ,n-
ed elsewhe-e. The weight does not include the k grcrup w-hkh is supplied by NAA,
G&N Pnd\li38;Lor Control Panel: csnsists of the nec- essary S W " ~ ,hes, indfcators, and controls for the nav;@; AX Task not repcrted elsewhere. Includes
p" _. s hand mntroller, altitude impclse control, p t 1 w5 I" ing , a nd supporting hardware e
IMV Ccn";ol Panel: meter, switches, panel wiring and supporting hardware.
Opb4cal ShPoud & Cover Assembly: optical shroud ar,d prcstel-.?Afre -over.
D&C Electronics: consists of six electronic modules En one space envelope.
One step down power transformer for map and data viewer and indicator and illumination lights,
Long Eye Relief Eyepieces: a SXT and a SCT eye- piece to provide eye relief of at least 1.6 inches for closed-visor operation.
Fllm Cartridges: film cartridges, including film, for Map and Data Viewer,
Horizon Photometer: an automatic, photometric, h r k c m detec,t;or device interchangeable with sextant eysp1e.e to provide capability for use of earth's "hluninated limb as a navigation reference
4-2 P A G E -
E-1142
I - I . A P O L L O G U I D A N C E A N D N A V I G A T I O N S Y S T E M S T A T U S R E P O R T
HMU:
JUNG TZON BOX:
M&DV: Mar a m Da;t V;PWEP film viewer f o ~ display of maps, .ha rLs9 p ~ o edv res , etc ~ Weight includes one film $sc,r?r idge w0,h f".m.
NVB & SHOCK MOUNTS: Base and Shock Mounts: rigid structure IIW and the Opt. dwdre and se-ppo_pted by Fhree shock
1 Subsystem with its
a'. z44a -,h the hVB to the spdee ,raft. Includes k e r s acd three holmo
OPTICAL EYEPZECES. Opth( A. E y s p k e s : optical eyepieces fer SXT and SCT.
OPTICAL SGBSYSTEM: Gp. ; fa l SuPsys*,em: SXT, SCT, O@,ia al Base and gearing, panel h s e , and associated hardware.
SCT :
S X T :
PSA:
Sed onerag 'Ieles: ope: single line -of-s;ght, wide-field, tw G = degree-&'-freedom telescope and its attached gearing.
S6.q ant: two lf ne -of-sight , narrow-f ield, two-degree-of- fzeedom sexta.nt, including attaiched gearing.
P ~ e - r Serwc-u Assembly: HMU, SCT, and SXT servos, p-wer slxpplks, CDU electronics, 7MU backup mode F Z F .i;rora:cs, Signal Conditioning electronics, and mis- J eljanecaus electronics. Includes toe cap.
. 9/ 15 /63 D A T E - 4-3 P A G E -
A E c ~ ~ s o , Re APOLLO L i b r s r y ( 15) Battin, R. Bean., W. Bowditch, P. Boyce, A. Bryant,, P. Dahl,?TL, J. Egai?., KO Flar&de r s , J. Hall , E. C. Halzel , I. H a n k y , D. Hickey, E.
Houston, F. Hursh , J.
Hoag, D.
DP ST RIBU T ION LIST E-1142 Rev. 12
Apollo Limited Internal
Delaney, apt. W. (AFSC/MIT) Gregorek , S. (NAA S & ID/MIT) Heuermann, T. (GAEC/MIT) Rhine, w. (NASA/RASPO/MIT) AC S p a r k p l u g Kollsman Raytheon
KOSO, A. K r a m e r , M. Kupfer, W. Ladd, D. Lawrence, J. Mayo, G. Mil ler , J. MIT /IL L ib ra ry (68 Albany St. ) (8) Nevins, J. Nugent, J. Olsson, E. A. Sc ie g ienny , J . Sears, N. T r a g e s e r , M. Wilk, L. (2) Woodbury, R.
External
N A B RASPO: National Aeronautics and Space Administration (1) Resident Apollo Spacecraft P ro jec t Officer North American, Inc. Space and Information Systems Division 122 14 Lakewood Boulevard Downey , California
DATE _9/15/63 5-1 P A H -
CAPE: Na t ioca l Aeronautics and Space Administration
P o r t C a a v e r - ~ h , Flor ida Xttr.: Mr . B. P. Brown
Atl=.-Ltic Missile Range Operations
HDQ : NASA He 3 d2aarte r s 1520 H Street Washizgtor*, D. C. A t t ~ : Mr. G. Me LOW, MD(P)
( 3 )
GAEC: G r u m m a - Aircraf t Engineering Corporation Bethpagz, Loag Island New York Attc: Mr. P. Gardner and Mr . A. Whitaker (1)
Mr. S, C, Salina NAA: North American Aviation, Inc. ( 2 )
4 Space iLGd Information Systems Division 12214 Lakewood Boulevard Downe y , California Attn: Mr. R. B e r r y (1) Attn: Mr. S. Fel ix (1)
Dept. 4-612
. &
GAEC RASPO: National Aeronautics and Space Administration Resident Apollo Spacecraft P ro jec t Officer Grumman Aircraf t Engineering Corporation Bethpage, L . I . , New York Attn: Mr. J a c k Small
WSMR: National Aeronautics and Space Administration P o s t Office Drawer D White Sands Missi le Range White Sands, New Mexico
MSC: National Aeronautics and Space Administration (4 5) Manned Spacecraft Center
Houston 1, Texas , I Apollo Document Control Group (SDG)
CSM: National Aeronautics and Space Administration Manned Spacecraft Center Apollo Command and Service Module Houstor_ 1, Texas Attn: Mr. F. P e t e r s Attn: Mr. P. Ebersole ( 2 )
( 3 )
9 /15 /63 DATE - 5 -2 P M E -
L
'
WESCo:
AMR
Washington Engineering Services Co. , Inc. (1) White Fl int Science P a r k Kensington, Maryland Attn: Mr. J. P. Smith
WESCo 68 Rogers Street Cambridge 3 9 , Massachusetts Attn: Mr. J. Levy (2)
Mr. Kexmeth Dunipace
MIT Guidance T e s t Manager P.O. Box 828 Cocoa Beach, F lor ida
MIT -AMR
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