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AP Approved 0 *, ~ Date// 3
MILTON B. TRAGESER: DIRECTOR APOLLO GUIDANCE AND NAVIGATION PROGRAM
i , i '
ROC* G". INSTRUMENTATION LABORATORY
iL;* E-1142 (Rev. 7 ) I I -
4 " 1
(UNCLASSIFIED TITLE)
AS?C Jlsrl?,~$[' r i p t i $&;"I WEIGHT AND BALANCE REPORT Dest roy when no lonper in us0
Da n o t . r e t u r n t o ASP0 file P
Apri l 1 5 , 1 9 6 3
cc- -
HUSETTS
c O p y # a b F / I < & CO IES THIS DOCUMENT CONTAINS /Lg PAGES
i 6 I
APOLLO 6 & N WEIGHT S BALANCE REPORT 1-1142
ABSTRACT
Report E-1142 (Rev. 7) presents weight, center of gravity,
and moment of iner t ia values for all components of the guidance and
navigation equipment
Power requirements of the guidance and navigation equipment
upon the P r i m a r y t 2 8 VDC Power Supply have a l so been included.
Only data pertaining to the command and serv ice modules i s ,
a t present , included in this report .
E-1142 is prepared monthly and distributed on the 15th of
each month.
Page 2
Date15 Apr. 1963
APOLLO 6 & W W E I 6 H T & BALANCE REPORT E-1142
Introduction
E-1142 (Rev. 7) is submitted in compliance with the documentation r e -
quirement of weight, center of gravity, and moment of iner t ia data fo r Apollo
guidanc.e and navigation equipment. At present, however, E-1 142 per ta ins
t:, only the command and serv ice module:;.
Power requirements , for Apollo guidance and navigation equipment, have
been included to aid in the determination of spacecraf t p r imary power.
W e i g h t s
All weight i t ems a r e grouped according to their specific location with-
in the spacecraf t modules. Subsystem weights a re reported to the component
level and to the nea res t tenth of a pound.
Given component weights a r e identified as calculated, measured, or
estimated. These t e r m s a r e defined by North Amer ican Aviation as follows:
Calculated weights (C) a r e weights based on detailed calculations made
f r o m final production drawings that will be used to build flyable equipment.
Measured weights (M) a r e the actual weights of equipment built to the
production drawings.
Est imated weights (E) a r e rough calculations.
North American Aviation will provide and be responsible for coldplate
weights which a r e not integral with guidance and navigation equipment.
Weight Status Reporting
Table 1 offers a comparison of present weight values with those l is ted
APOLLO 6 & N WEIGHT & BALANCE REPORT E91142
in the prev ious Weight and Balance Report, E-1142 (Rev. 6 ) , March 15, 1963.
All wei ght changes a r e expl ai ned.
The "Spec. Weight' ' column contains "proposed MSC" weights, that i s ,
goal s s e t for th by MSC in a memo to MIT/IL dated December 5, 1962.
Centers of Gravity
The cen te r s of gravity of each weight component o r packaged assem-
bly a r e determined with respec t to the b a s i c X , Y , Z axes of the command
module which a r e shown in figure 1.
the n e a r e s t tenth of an inch and a r e shown in table 2.
Moments of Iner t ia
Center of g rav i ty va lues a r e given to
Table 2 presents the moments of inertia, of each weight component o r
packaged a s s e m b l y , determined about each of the component's axes which (1)
run through the component's center of gravity and (2) a r e para l le l to the b a s i c
X, Y , Z axes of the command module.
Accuracy
The accuracy of numer i ca l V a l ues reported in this revision should not be
cons idered t o be within the to1 e rance implied by the significant f igures quoted.
Numerical values will approach the established tolerances as design and
development phases approach compl etion.
Power Requirements
The e l ec t r i ca l load of the guidance and navigation equipment, on the
P r i m a r y t 28 VDG Power Supply, is shown in figure 2.
Page 4
Date 15 Apr. 1963
APOLLO 6 & N WEIGHT & BALANCE REPORT E - 1 142
Explanation of Reported Weight Chacges
IMU - Weight increase due to redesign of the 15x connector mount to
provide a c c e s s to the precision resolver alignment module.
IMU Control Panel - Due to recent design changes in the mounting
facil i t ies of the various displays and controls, the weight of the support hard-
ware has been reduced.
Left Hand T u r r e t - Addftional definition of the modules and configuration
changes have resulted in a re-evaluation of the Left Hand Tur re t weight.
Optical Shraud - Reduction in the inner skin thickness has resul ted in
a weight reduction of the Optical Shroud.
Spare Lamps (Three) - Spare i tem for Display and Control/Navigation
not previously identified.
Spare Relay and Diode Module - Spare i tem for Display and Control/
Navigation not previously identified.
Bellows Assy - Weight decrease due to shor te r transit ion pieces and bet-
t e r weight evaluation.
Page 5
Date 15 Apr. 1963
APOLLO 6 & R WEl6HT L BALANCE REPORT E4142
t4 I
U rw I
9 A +
0. hl +
a,
2 a C id E E i3 w 0 v1 a, x rd
N
* x 6
Q, k
Page 6
Date 1 5 A p r , 1963
__.II____
APOLLO 6 & W WEIGHT & BALANCE REPORT E - 1 1 1 2
Table 1.
Item
COMMAND MODULE
Lower EauiDment Bav
GDU & Frame Assy
3pt ics l Subsys tem SX T SCT Opt Base & Gearing
Optical Eyepieces SX T SCT
[MU NVB & Shock Mounts Bellows Assy Cabling
D & C Nav Station IMU Control Panel Left Hand Tur re t Optical Shroud G&N Ind Cont Panel
D & G/AGC M & DV ( k c . 1 film) AGC (no s p a r e s )
Spares Tray Stored Spares
PSA Stored Spares Signal Conditioning Tra?
;ur rent. Weight St, Spec. 2/62 (a)
6 . 0
12.0 9.0
14.0
2.0
50. 0 16.0
8 . 0 22.0
30. 0
15.0 5.0
80. 0 - - - 0
25.0 - 0
0 -
[b-a)
t10.5
0.0 0.0
t 5.0
t 3.0
t 8. 2 t 8. 0 t 3.0 t 3.0
- 2.5
0.0 t 3.5 t13 .0
t40 0 $11.0
t24 . 7 s2 5 +5.0
1s
itatus 3 /63 (b)
16.5
12.0 9.0
19. 0
1 .0 4.0
58.2 24.0 11.0 25. 0
6.3 7.0 4. 0
10.2
15.0 8.5
93.0 4.0
11.0
49.7 2.5 5.0
(c-b)
0.0
0.0 0 .0 0.0
0.0 0.0
t o . 3 0.0
-3.0 0.0
-0.3 -3. 8 -0.2
0.0
0.0 0.0 0.0 0.0 0 - 0
0 .0 0.0 0.0
-- Statu
4 / 4 3 C ' -- r -
16. 5,El
12. O(E)
19. O[E] 9.0:E1
1. OlEi 4. O r E '
58. 5QE\ 24, OQEP
8. O{E] 25. O[E'
h.O!E) 3. 2(EQ 3, 8[EI
10. 2jEl
15. O(E' 8. 5(E'
93. OgE: 4. O(E'
11, O(E'
49* 7BE: 2.5&E: 5. O$E'
( Go ntinue d)
Page 7
Date 15 Apr. 1963
- APOLLO 6 & W WEIGHT & BALANCE REPORT 1-1142
Table 1. Cur rec t Weight Status (Cont'd)
I tem
Iunction Box
Main Panel A r e a D&C/NAV D&C/AGC
Loose Stored I tems Eye Relief Eyepieces Film Car t r idges (4) AGC Loose Spares PSA Loose Spares CDU Spare Gearbox Computer Self-Check Plug Horizon Photometer Spare Lamps (3) Spare Relay & Diode Module
SERVICE MODU 'LE
Radar (Transponder) (Rendezvous Radar)
TOTAL 350.0
t 4 . 2
-8. 0 t l O . . O
t3.0. t 3 .0
t18.0
t 1 . 0 t 4 . 0 - - - - - -
-5.0
Status 3 /63 (b)
12.2
0.0 15. 0
3 .0 3.0 ; 1.0 4.0 - - - - - -
10.0
0 . 0
- - - 0 . 0
0 . 0 0 . 0 0 .0 0 .0 0 .0 0 . 0 0 . 0
t o . 2 t o . 3
0.0 0 .0
-6.5
Status 4 /63
gcg
12. 2gE)
15. O I E )
3.O(E& 3.O(E)
26. OiE) 9. O(E1 3 . O(Ej 1. O(E) 4. O(E) O . Z ( E ) 0 .3(E]
10. O(E) 30. O ( E ]
505.6
8 Page Date 15 Apr. 63
c4. a a, 5 Li
m m o o m 4 9 0 0 m w
u * " I ' I O . . . . . . . + 4 P 1 1 4 4 0 0 0 L n o \ o 4 4 4 I I 4 1
Y I I l l I
APOLLO G & N WEIGHT & BALANCE REPORT E - 1 1 4 2
m r? 4
4
oc) P U P
$ D I I
D I I
0
4 m
.d + Id
r; --u 0 k a, c,
$ u h h h h h n h n - A n n - - h h h h h
Y Y U Y ~ d Y Y Y Y Y - Y Y Y e Y w w w w w w w w w w w w w w w w w w w w w
u , o o o o 0 0 I n 0 0 0 O m N o O N O L n O O O Y Y Y Y Y N
a,
P z
;1
m a, V a, E
a, w H
" M a 3 F : 4 rd
\ u a n
u .d c, a 0
i\ .rl
Page 9
Date15 Apr. 1963
APOLLO 6 & N WEIGHT & BALANCE REPORT E - 1 1 4 2
a d cd h
> cd
* .rl
6 +I 0 k a, .G a, e,
c,
N
a, a
E a; c, w
a, M 3 a
4
3 a, a 0
;;;6 rn
Page 10
Date15 Apr. 1963
A P O L t O 6 & W WEIGHT & BALANCE REPORT E - 1 112
1"
3 v -
N
I *
I
APOLLO 6 & N WEIGHT k BALANCE REPORT E - 1 1 4 2
AG6:
BELLOWS ASSEMBLY:
CA B LING:
CDU & FRAME ASSEMBLY:
D&C/AGC:
D &C / NA V:
G&N Ind Cont Panel:
Apollo Guidance Computer: complete com- puter, except display and keyboard. In- cludes: - all s t ruc tura l mounting rails, support for spa re tray, AG6 cable to front panel for spacecraf t e lec t r ica l in te r face , spare logic in four t r ays , and power supply.
Bellows Assembly: connection between Command Module and Optical Subsystem.
Cabling: intr asubassembly cabling in lower e quipmen t bay I) f rom lower equipment bay to other as- semblies is assumed a spacecraf t respon- sibility. )
(Int e re quipme nt cab ling
Coupling Display Units and f r ame as- sembly: five gea r boxes and f r ame ass- sembly, used as an angle data interface among the optics, IMU, AGC, and space- craf t autopilot.
Display and Control, Computer: l e t te r and number readout, keyboard, contr 01, re lays , and support s t ructure .
Display and Control, Navigation: consists of G & N Indicator Control Panel, IMU Control Panel, Left Hand Tur re t , and Optical Shroud. switches, l ights, etc. except as reported elsewhere. clock group which is supplied by NAA.
The above includes m e t e r s ,
The weight does not include the
G&N Indicator Control Panel: consists of the necessary switches, indicators, and controls for the navigation task not repor t - ed elsewhere. ler, altitude impulse control? panel wiring, and supporting hardwar e.
Includes optics hand control-
Page 12
Date15 Apr.1963
APOLLO 6 & N WEIGHT & BALANCE REPORT E - 1 1 4 2
HMU Cont Panel:
Left Hand Turret :
IMU Control Panel: m e t e r s , switches, panel wiring and supporting hardware.
Left Hand Turre t : contains electronic modul-es.
Optical Shroud: Optical Shroud: includes protective cover,
E Y E RELIEF EYEPIECES: Eye Relief Eyepieces: eyepieces to provide eye relief of a t l ea s t 1.6 inches for closed visor operation.
FILM CARTRIDGES:
HORIZON PHOTOMETER:
IMU : t
JUNCTION BOX:
M&DV:
NVB & SHOCK MOUNTS:
0 P TLCA L E Y EPIEC ES :
Fi.lrn Cartr idges: film car t r idges? iccludis,g film, for Map and Data Viewer.
Horizon Photometer: an automatic, photo- met r ic ~ horizon detector device inter change - able with sexant eyepiece to provide capability fo r use of ea r th ' s illuminated l imb as a navigation reference.
Inertial Measurement Unit: gimbal assembly,, inertial components, data t ransducers , sup- port s t ruc ture , and internal cooling.
Junction Box: e lectr ical interconnection center between subassemblies i n lower equip- ment bay.
Map and Data Viewer: film viewer for display of maps, char t s , procedures , etc. Weight includes one film car t r idge with film.
Navigation Base and Shock Mounts: rigid s t ruc ture supporting the IMU and the Optical Subsystem with i t s associated hardware and supported by three shock mounts that attach the NVB to the spacecraft .
Optical Eyepieces: optical eyepieces for SXT and SCT.
Page 1 3
Date 15 Apr.1963
APOLLO 6 & N WEIGHT & BALANCE REPORT 1-1141
OPTICAL SUBSYSTEM: Optical Subsystem: SXT, SCT, Optical Base and gearing, panel baseg and associat- ed hardware
Optical Base & Gearing: Optical Base and Gearing: base for SCT and SXT with associated gearing.
SCT:
SX T:
PSA :
Scanfling Tele s cope : single l ine - of - s-: ght .. wide - fi el d two -de g r e e - of - f r e e dom t e le - scope and its attached gedring.
Sextart: two line-of-sight, narrow field, two-degree-of -f reedom sextant, including attached gearing and lnternal cooling.
Power Servo Assembly: IMU, SCT, and SXT servos , power supplies, 6DU elec- t ronics , IMU backup mode electronics, and mi s c ellane ous electronic s .
Signal Conditioning Tray: Sigxal CDnditioning Tray: t r ay in PSA to condition signals for te lemetry and iceflight t e s t e qui pm ent e
RADAR (Transponder and Ren- dezvous Radar ) Radar (Transponder and Rendezvous Radar) :
electromagnetic ranging equipment, located in service module, for lunar orb i t rendezvous.
Date 15 Apr. 1963
APOLLO 6 K N WEIGHT K BALANCE REPORT 1-1142
DIS TRIBU TIQN LIST E-1 142 Rev.7
NASA (50 copies)
Participating edontrac tor s (36 copies., 12 each)
Apollo Limited Ixternal
A ~ o ~ s Q , R. APOLLO Library (15) Battin, R. Bean W.
Bowditch, P. Boyce, A. Bryant, P. Dahlen, J.
Duggan, E.
F lande r s , J- Gregorek, S . (S%ID, Cambridge) Hall, E. C. Halzel, I. Hanley. D. Hickey, E. Hoag, D. Houston. F.
"Black, D .6 . - Dept. 695-323
"Day, W, E. - De$, 695-313
>:Felix, S . (Attn, Dept. 4-612)
Hursh, J. Koso, A. Kramer? M. Kupfer, W. Ladd, D. Levy, J. (WESCo) (2) Mayo, G. Miller, J. M I T / I L Library (68 Albany St , ) (8) Nevins, J. Nugent, J. Olsson, E . A .
>:>$Peters, F r e d Redding, F. W. (S&ID, Cambridge) Rhine, W. (NASA) (3) S c ie g i enny , J. Sears , N. T ragese r , M. Wilk, L. (2) Woodbury, R.
:%North Amer ican Aviaticn, Inc. ~ ~ S A p o l l o Command and Service Module Space & Systems Information Div. 12214 Lakewood Boulevard Down ey, California Houston 1, Texas
Office City Manned S p c e c r a f t Center (NASA)
Page 15
