(NASA- 52773} W^IGHI AKC £sol leSEGEl (Massachusetts Inst. of T=ch25 p

N73-7W621

Unclas•0/99 20790

E-1142

(UNCLASSIFIED TITLE)WEIGHT AND

REPORT' -

March. 15, 1963

CAMiilP@E 39, MASSACHUSifl

U

DOWNGRADE

GUIDANCE AND NAVIGATION

Approved Date 3/2^/<>3MILTON B. TRAGESB&, DIRECTOR^APOLLO GUIDANCE ^.ND NAVIGATION PROGRAM

fOODBURY,INSTRUMENTATION LABOkATORY

OR

E-1142

(UNCLASSIFIED TITLE)WEIGHT AND BALANC

REPORT^

March 15, 1963COPY

THIS DOCUMENT CONTAINS_2~S^PAGLS

CAMBRIDGE 39, MASSACHUSETTS

ACKNOWLEDGMENT

This report was prepared under DSR Project 55-191, sponsored

by the Manned Spacecraft Center of the National Aeronautics and

Space Administration through contract NAS9-153y

This docume|rf, contains infor/iation affecting

the national demnse of the IMited States within

the meaning of trakEspion&ge Laws, Title 18,

U.S .C. , Sections 7m(an<3794, the transmission

or the revelation of Vl!l|eh in any manner to an^r vl&sw

unauthorized person is plsahibited by law.

The publication of this report does not constitute

approval by the National Aeronautics and Space

Administration of the findings or the conclusions

contained therein. It is published only for the

exchange and stimulation of ideas.

APOLLO G & N WEIGHT & BALANCE REPORT E-1142

ABSTRACT

Report E-1142 (Rev. 6) presents weight, center of gravity.

and moment of inertia values for all components of the guidance and

navigation equipment.

Power requirements of the guidance and navigation equipment

upon the Primary ^28 VDC Power Supply have also been included.

Only data pertaining to the command and service modules is,

at present , included in this report,

Also included in this month's report , at the specific request

of NASA, is an estimate of weights which might result from a

weight reduction program.

E-l 142 is prepared monthly and distributed on the 15th of

each month,

Page

Date 15 Mar. 1963

APOLLO G & N WEIGHT & BALANCE REPORT E-1142

Introduction

E-1142 (Rev- 6) is submitted in compliance with the documentation

requirement of weight, center of gravity, and moment of inertia data for

Apollo guidance and navigation equipment. At present, however, E-1142

pertains to only, the command and service module. ; , .

Power requirements, for Apollo guidance and navigation equipment,

have been included to aid in the determination of spacecraft primary power,/

Weights . ' • '

All weight items are grouped according to their specific location with-

in the spacecraft modules. Subsystem weights are reported to the com-

ponent level and to the nearest tenth of a pound*

Given component weights are identified as calculated, measured, or

estimated. These terms are defined by North American Aviation as follows

Calculated weights (C) are weights based on detailed calculations

made from final production drawings that will be used to build flyable

equipment.

Measured weights (M) are the actual weights of equipment built to the

production drawings.

Estimated weights (E) are rough calculations,

North American Aviation will provide and be responsible for coldplate

weights which are not integral with guidance and navigation equipment.

Page

Date 15 Mar. 1963

APOLLO G & N WEIGHT & BALANCE REPORT E-1142

Weight Status Reporting

Table 1 offers a comparison of present weight values with those

listed in the previous Weight and Balance Report, E-1142 (Rev. 5),

February 15, 1963. All weight changes are explained.

The "Spec, Weight" column contains "proposed MSC" weights, that

is, goals set forth by MSC in a memo to MIT/IL dated December 5, 1962.

Centers of Gravity

The centers of gravity of each weight component or packaged assem-

bly are determined with respect to the basic X, Y, Z axes of the command

module which are shown in figure 1. Center of gravity values are given

to the nearest tenth of an inch and are shown in table 2,

Moments of Inertia

Table,2 presents the moments of inertia, of each weight component

or packaged assembly, determined about each of the components axes which

(1) run through the components center of gravity and (2) are parallel to the

basic X, Y, Z axes of the command module.

Accuracy

The accuracy of numerical values reported in this revision should not

be considered to be within the tolerances implied by the significant figures

quoted. Numerical values will approach the established tolerances as

design and development phases approach completion,

Power Requirements

The electrical load of the guidance and navigation equipment, on the

Primary + 28 VDC Power Supply, is shown in figure 2,

Page 4

Date..15 Mar. 1963

APOLLO G & N WEIGHT & BALANCE REPORT E-1142

Explanation of Weight Listings, Table 1

During this reporting period there has been high activity in design releases

leading to better weight estimates but unfortunately showing unanticipated weight

growth. At the specific request of NASA this month's report includes estimates

of weights which might result from a weight reduction program.

The new format of Table 1 for this month is as follows:

column (a) - Specification weight proposed by MSC in December, 1962in an informal memo.

column (b-c) - The change from spec weight to last reported weight(by request of S&ID).

column (b) - Reported weight last report.

column (c-b) - Change from last reported weight to this report.

column (c) - Weight report this month.

columns (d), (e), ( f ) , (g) - Estimates of results of possible weightreduction program listed in order of decreasing desirability.Many reductions listed are emphatically not recommendeddue to the resulting losses in system performance orreliability not to mention schedule and cost impact. Totalsat bottom are based upon the particular pattern of reductionin the column. Various other combinations would be possible,of course.

column (h) - Estimates of worst possible weights which should be assumedin supporting structure design. These values should be listedin mechanical interface documents and ICDs, and were trans-mitted to S&ID on 13 March by letter AG 155-63-.

The following short descriptions are of weight changes by rows with letters

identifying the column in which the weight change occurs.

Page_

Date 15 Mar. 1963

APOUO-6 & N WEIGHT & BALANCE REPORT _ E-1142

CDU & Frame Assembly

(c-b) Increase due to identification of frame assembly which was not included

in earlier weight reports. This frame was identified in the mechanical

interface with secondary structure on ICD 01-00004 negotiated in

February with S&ID.

(g) Reduction resulting from non-interchangeable design of optics and IMU

CDUst. Affects mission success by removing in-flight repair or backup

capability.

Optical Subsystem

SXT

(f) Engineering redesign and more expensive machining,

SCT

(f) Engineering redesign and more expensive machining.

OPT Base & Gearing

(f) Engineering redesign and more expensive machining.

Optical Eyepieces

Incomplete design and corresponding lack of accurate weight estimate.

Consideration of weight reduction possibilities premature.

Page

Date 15 Mar. 1963

APOLLO 6 & N WEIGHT ft BALANCE REPORT E-1142

IMU

The IMU has 88$ of its reported weight measured, No significant weight

reductions seem possible that would preserve the IMU operation margins

deemed necessary to justify the existence of the IMU. The IMU takes its

design from the Polaris missile where weights reductions have been ac-

complished. Weight of coolant lines beyond the quick disconnects have not

been included, MIT will negotiate with S&ID to determine weight reporting

on these flexible lines.

Navigation Base and Shock Mounts

(e) Reduction in thickness of shock mounts corresponding to reduction in

landing shock specification. Specification is now unofficial; 100 g's.

(g) Serious reduction in (1) alignment performance requirement and (2)

highly qualified ability to hold together in current shock requirement.

Bellows Assembly

(c-b) Change to convoluted bellows instead of welded,

(d) Change seals to beryllium. Cost increase of about $6000 would appear

worth the weight saved,

(g) Reduction from dual to single convoluted bellows. Very risky in terms

of maintaining adequate seal.

Cabling

(c-b) Cable weight was reduced after weighing mockup cable identified after

mechanical interface negotiations with S&ID in February. Weight

Page 7

Date 15 Mar. 1963

APOLLO G & N WEIGHT & BALANCE REPORT E-1142

Cabling (Continued)

reductions cannot be anticipated at this time,

D&C Nav Station

IMU Control Panel

(d) Modification of support hardware

(e) Reduction in skin of honeycomb panel

(f) Removal of attitude error meter - operational significance not

fully evaluated.

(g) Removal of total IMU control panel hardware to G&N Ind Cont Panel

Left Hand Turret

(d) Reduction by new identification of equipment.

(f) Removal of attitude error meter electronics.

Optical Shroud

(d) Skin thickness reduction.

(e) Replace shroud by dust cover. Extreme damage danger to optical

alignment without protection.

G&N Ind. Cont. Panel

(c-b) Better identification of equipment.

(d) Elimination and reduction of miscellaneous hardware and skin thicknes s

reduction.

(g) Additions due to moving IMU control panel hardware to this area.

Page

Date 15

APOLLO G & N WEIGHT ft BALANCE REPORT E-1142

D&C/AGC JLEB & Main Panel

The 15 pounds estimated on each of these displays is an optimistic

minimum estimate. No weight reductions can be anticipated until design

is further along.

Map and Data Viewer, M&DV

(c-b) Reduction in weight and addition of film in viewer resulted in a net

change of zero. No weight reductions of any significance can be

anticipated. Removal of M&DV and substituting printed pages for re-

quired data would probably result in weight penalty.

AGC

No Spare Storage

(c-b) Increase resulting from: Design release possible from ICD negotiations

(ICD 01-0002). Support for spare tray. AGC cable to front panel for

spacecraft electrical interface. Spare logic in four trays. Addition of

power supply.

(e) Optimistic reduction resulting from possible favorable thermal and

structure strength loads allowing removal of metal in frames.

(f) Removal of 5th tray group to modified "H" frame structure leaving four

sliding trays.

(g) Reduction to a mechanical configuration of four non-sliding trays.

Not including coldplate.

Spares Tray & Stored Spares

(d) Removal of the spares tray completely.Page

Datel5 Mar. 1963

APOLLO 6 & N WEIGHT & BALANCE REPORT E-1U2

PSA

(c-b) Increase resulted from: Electronic circuit design releases which

identified larger modules than anticipated. Addition of electronics for

pulse torquing and backup electronics required an extra tray* Addition

of temperature controller electronics, Actual packaging releases of

first two trays showed a higher density than original estimate. Ad-

dition of toe cap for tray holddown, Estimate does not include power

diodes in interface with 28 V power now in negotiation.

(d) Optimistic reduction resulting from possible favorable thermal and

structural loads allowing removal of metal in fra.rn.es,

(e) Removal of tray 9 and capability for storing spares.

(g) Reduction in electronics identified in G&N allowing removal of one tray.

Stored Spares

(c) Item added to recognize room in PSA for spares storage,

(e) Removal of stored PSA spares corresponding to removal in frame to

hold spares.

Signal Conditioning Tray

(c) New item identified in PSA to condition signals for telemetry and in-

flight test equipment. Conditioning previously was performed in right

hand turret.

(g) Removal of signal conditioning and interface with telemetry and in-

flight test. Operational significance not evaluated.

Page 10

DatelB Mar. 1963

APOLLO 6 & N WEIGHT & BALANCE REPORT E-1142

PSAJunction Box

(c-b) Added weight due to better estimates and recognition of increased width

in PSA resulting from shift in walls desired by S&tlD. This allows more

PSA capacity , . . . up to 10 trays,

(e) Reduction due to removal of plug wire and structure due to corresponding

removal of one tray in PSA.

(g) Reduction due to removal of plug, wire and structure due to correspond-

ing removal of second tray in PSA*

D&C/Nav Main Panel

(c-b) Items previously anticipated for G&N main panel have been removed, MIT

is supplying S&ID with relay closures to operate main panel status and

condition lights. All G&N main panel items are incorporated in the

D&C/AGC on main panel.

Eye Relief Eyepiece

(c) Item added as a result of MSC request of 1 February 1963 to provide eye

relief of at least 1.6 inches for closed visor operation.

(e) Recuction in weight of eye relief eyepieces with corresponding reduction

in magnification and/or field of view restricting severely performance of

sighting functions.

(g) Elimination of eye relief eyepieces preventing any possibility of naviga-

tion measurements or IMU alignment sightings in depressurized cabin.

Page 11

Date 15 Mar. 1963

APOLLO G & N WEIGHT & BALANCE REPORT E-1142

Film Cartridges

(c) New item identified: storage of four additional film cartridges to

operate in M&DV and increase data storage capacity. No significant

weight reductions can be anticipated, especially since other weight

reductions may put burden on M&DV to display more backup mode

procedures. Each cartridge handles 1800 frames of high resolution

data.

Loose Stored Items

(c-b) Increase in spares due to a better estimate of module weight. Figure

includes sparing every unique module with no use of modules from LEM.

Spares required to meet reliability allocation.

AGC Loose Spares

(d) Increase due to removal of stored spares and renaming them loose.

(e) Removal of memory from spares.

(f) Reduction of AGC spares. Reliability is adversely affected unless

support from LEM computer sticks.

(g) No AGC spares. Serious reliability effect.

PSA Loose Spares

(e) Increase due to removal of stored spares from PSA and renaming them loose.

(f) Reduction in PSA spares to include only partial spare capability.

Reliability is affected unless LEM modules can be used.

Page 12

Date 15 Mar.196 3

APOLLO 8 & H WEIGHT & BALANCE REPORT E-1142

PSA Loose Spares (Continued)

(g) No PSA spares. Serious reliability effect.

CDU Spare Gearbox

(d) Removal of CDU Spare Gearbox would decrease operational flexibility

and reliability.

Computer Self-Check Plug

(c) Additional item to provide capability of connecting computer outputs

back onto inputs for checkout and diagnosis of failure,

(g) Removal of self-check plug recognizing corresponding removal of

computer spares.

Horizon Photometer

(c) Weight reported for first time. Interchanges with sextant eyepiece

to provide capability for use of earth's illuminated limb as navigation

reference. May be very important for earth orbital operations under

possible conditions of cloud cover hiding landmarks. Design not firm

enough to anticipate weight reduction,

(g) Removal of horizon photometer; advisable only if actual earth orbital

navigation using landmarks provides an experience with cloud cover

consistent with high probability of consistent on-board navigation.

Page 13

Date 15 Mar. 1963

APOLLO G & N WEIGHT & BALANCE REPORT E1142

Radar Transponder

(c-b) Reduction in estimated weight. No further weight reductions can be

anticipated at this time.

Rendezvous Radar k

(c) Item added to recognize LEM rendezvous backup mode. Impact on G&N

in command module weight report is anticipated to be trivial but does not

recognize power switching or interface cabling between service and com-

mond modules,

(f) Removal of rendezvous radar. Corresponding reduction in LJCM rendezvous

probability not evaluated.

Page 14

DatelS Mar. 1963

P8LIO 6 & N HEIGHT & BALANCE REPORT E-1142

a1£oz

6 KIU O4. O

W•5

os.•d

o;

UVMOn

N

U)s

Page_ 15

DatelS Mar. 1963

APOLLO 6 & N WEIGHT & BALANCE REPORT \-\\tt

GOO

OJ

,

Up

£wj^&o'S

CJJi— i•H

COCO

ftOCO

CO<0

OH

coNO

PO

1

co0•4->

w£60

•H

^^*

cVb

U

bO .••H -l_>w ;>.co !>Q

g800o^ crft xo „

• ?"H V

« s-3 *""PH

CO ^^o

rt *^~55^

3 M•H i

8 N

N

U NO

Ok (M

KH

_-^("1

*—

^_^00

ii_'oT

^

* * *U

3"U

2"

"J?i*r'i—>£

'

s»W ri

OM

MA

ND

MO

DU

Lov/e

r E

quip

men

t B

U A

o,

001— 1

•"fin

.*~t

mNJ3•— *

mNO

*-*

mNO

^^

5LrT,NOi-H

mi-H

O

in1-1

o«

T

oNO

36

DU

&

Fra

me A

sse

U

/•— - r — - —O CO O

--H 06 in•— t i-H

O PO O

-H' 00 ini-H ^H

0 0 0

(M O* ONi-H .— t

O O O

(NJ ON ONi-H p-H

555o" o* o"

• • \CNJ ON ONi-H i-H

O O 0

o d d

1 Jod•*

o«

in>^

i io o o(SJ ON ^-H i-H

• 5

pti

cal

Subsy

stem

SX

TS

CT

Opt

. B

ase &

Gea

r

O

oLOr-"Z

o o-4 ^

o o-^o o

^ ^

0 0

pH Tj3

55o" 5*

« e

-H ^

"o"d

,-P•in

• Pi*c9'' •

'iP"*"

•o•)' '™

C ~*~~\I 1

pti

cal

Eyep

iece

sS

XT

SC

T

O 1

(NJ

00in

(NJ

00m

CNl

00in

ro00in

w"rvT

o

00m

-H

di

co00m

CO*

CO

odin

g

oON.— «

O

PO

oPO(NJ

o•(NJ

5o"

o

•(NJ

0

d

o'tM

09

coj.T

oNO

(0

VB

& S

hock

Mount

Z 1

•N.— Vr^NO

0

00

o*

00

0

00

5o"

0

(— 1i-H

O

0

O9

m"*

o,

t*+

oco

ello

ws

Ass

em

bly

CQ

odco

oin(NJ

oinM

O

in(NJ

oin(M

5o"

t

m(NJ

0

ini-H

I

O

d* •

o%

CO^•4

oNro

.r3U

in in in oB t t •

r- oo Tt< r-^

O CO ON (NJ

O (NJ r-H (Si

"

O CO O Tf

Tt* (M -H ON

00 (NJ CJN rt1

m co —i ON

O (NJ 00 -^

NO CO PO ON

5555CO O O N

o .e l t.vo r~ o

^

o o o oO O O Tf

I

V. Jin

— HCO

in•

^odcoj^

r ^

-H U

<u ^ 5

&C

Nav

. S

tation

IMU

Contr

ol

Pan

Lef

t H

and

Tu

rret

Opti

cal

Shro

ud

G&

N I

nd C

ont.

Pa

o.m(X]

oinr— t

O

in•-H

O

ini-H

O

in^H

5o"

t

in1—1

0

d

oini-H

O

*

O

0

in— i

&C

/AG

C/L

EB

Q16

Date 15 Mar. 1963

IPOLLO G & N WEIGHT & BALANCE REPORT E-1142

U

^f-J

CO

•<->

bO•|HD

^CU

2COCOo

*oCO

4->r-H

CO

oi

COsO

coI

CO

rico£bJO

•|Hcu

^0

CUMFHjjU

don ,CO ^

P

rtJ

GuO^^

n w^j^ *rj

0 a;+3 <uU CO

CDrt

CO3 co

rt --•4-* rf\CO °°

1

co::ro-M -^

*w t 3CO

O xDCO CTP* og

BCU-ut-H

-ir£i*— •?

oo

CT

cu

^a— •

.-,o

«^-«X

^ .

^

-£-ii

1?'

£.

rt '.

.

- •

<

.

,

W d

OM

MA

ND

MO

DU

Lo

wer

Eq

uip

men

t B

(Co

nti

nu

ed)

U ^

: o.0

' CMi— i

' in00

mCO

1 m00

inCO

Bm• CO

': O

O

mco

in

co+

o. in

1•r-(

•— |

U

£•H

Q

S

o0

Om

f — — "i

0 O O

d d o

o o oco d dr-

o o o06 d doo

o o oco d do

W W WcT 5" o"co ^ •— 'o ^

O 11 . 1 #m ico~\~

O I

00 1in

O 1

CM ICM

1

O I0 1 <|f

O 100

-— , W0) ^ V

s z «ri £ P<OH H CO« CO

o « «s 5 K— rt o. - PH -UU co co0<

oo

0

inf^

r ^

o o odo d•*

CO O O

in d in^CO O O

in o in^

o m or^ CM m•"*"

W W WP^ in" o"a-- CM m•

r~ i. * i

O 1CM~i~

0 1

O1* • ICM

O

T^<

+

O 1„ * Im iCM

ofi^ d

SA

(ex

cep

t as

n

ote

bel

ow

)S

tore

d

Sp

are

sS

ign

al C

on

dit

ion

iT

ray

PV

oa

O00

1— (t— 1

CT-

1 — fJ—i

0s

, — 11 — '

CM

CM°• — i

BCM"CM^

CM

t~t+

O

r— 1i-H

O

co-t-

o0

00

on

ctio

n B

ox

t-n

[ain

Pan

el

Are

a

S

od

od.

od

o -d

Boo

o0

o1— 1

" .

odH

O

CM+

O„

00

&C

/NA

V

P

oe

OCM

O

ini-H

O

inf— 4

O

in•"

omi-H

Boini — i

o„o

oin•— i

O

dr— 1

+

O0

in

&C

/AG

C

P

0 0

O CO

m oCM 00

in o

CM CO

o oco co

to S"o oro co

1 0! fl0 D

D 0G DD 0

D tt fS 0

e D9 1B 0

Ifl

oo

se S

tore

d I

tem

sy

e R

eli

ef

Ey

ep

iece

ilm

Ca

rtri

dg

es

(4)

J W W

O 0 O

o o o

O Tp O

•^ CO O1 — i

o r- oCO r-H O

CM -<

o o or~- o oco

w" 3" w"o o oso cr- co-- — '

*m,(-H

^-f"

*O

d•

odCM+

%O

„oCM

GC

Lo

ose

Sp

are

sS

A L

oo

se

Sp

are

sD

U S

pare

Gearb

ox

< PH O

Page_ 17

Date 15 Mar. 1963

POLIO 6 & N WEIGHT ft BALANCE REPORT E-1142

4J 00U .H3 toh 0) • *-?+J r\ ?~ HHCO W ^ —,£

OJO•r; — .<U QjQ

• k> ^rt

(U IH

'™ J^ *-^ *+*

w Pk "^* " "

S § sVH Tj D — ~° 0 S ^J.

05 rH ^rH QJ

M fi^CQ HH ^_^

4) -0fyj »-'

COvO•^^co

1

COwp

4-*CO

•H0)

^C(Ufnw3(J

« m' _5^24-> COCO

3"o

CO CO ,_0 xO rt

•*•* *•*• ^_-*5 tvjCO

1?'

£,

O fn *~-cu ** ^ rtft ro *~"

aCD

i— i

^7° s.U n

CO

MM

AN

D M

OD

UL

E(

Lo

ose

Sto

red I

tem

's (

c<

0 0

d d

o o

^ ^5

o oC 0

1—4 ^*

o oi— I rf

BEo" o"

-i -

I 1t 11 1

g iI 0I D

g .1g gg o

0 0g ii i

i— iCL

Co

mp

ute

r S

elf

Ch

eck

]H

ori

zo

n P

ho

tom

ete

r

o od dt— i

0 0

d d

o o0 »

O O--< co

o od d

w"wcT 5"d dr— 1 pTJ

O I. g

m ig

0 ,* 0

""> g1—1

0 J

d '

0 Iiin ir— i

SE

RV

ICE

MO

DU

LE

Rad

ar

(Tra

nsp

on

der)

(Ren

dezv

ou

s R

ad

ar

BEE•^ o ooo m oo <-* •*&^4

^H O0 »

fvj OCO U">+ +

CO

a

TO

TA

LS

Wei

gh

t In

cre

ase

of

Ite

pre

vio

usl

y

rep

ort

ed

.

Wei

gh

t o

f It

em

s n

ot

pre

vio

usl

y

rep

ort

ed

Lo

wer

Eq

uip

men

t B

ay

Mai

n P

anel

Lo

ose

Sto

red I

tem

s

— i oco d^ i— iooN3 O

•<4< O0 ^co0s ^5

e eTj< O

co ""f^ren oTt* dm Tt<

E STf< O

j\J C3[*• ^<*44

co o0 0

m ini—4 i— 1

"*

CO O

d doo+

o oe D

in mPO •-*co

CO

MM

AN

D M

OD

UL

E

SE

RV

ICE

MO

DU

LE

^H

comco04

•o.•*o

0

^4f-™

CO

T^

?

Seg^H

m

•-H«

OJ00+

co0

oCO

"*CO

doo+

o„

oinro

TO

TA

L

CO£

81

•o Sll

» „

U fe93 *~ Zco po ^ h

(H •"? fl!n) <? ft

J-l0

CO0

Page 18

Date 15 Mar. 1963

APOLLO G ft N WEIGHT & BALANCE REPORT E-1142

-"

"o -S^, 1

B ~~'o

.1-1

M

to

° r£

« -S

U

^

"So« :

§4->H- 1

tQNi— i

t— l

SI—I

,

AHw"

0

0

00

in

i

in

rovO

win

vOi — i

CO

MM

AN

D

MO

DU

LE

Lo

wer

Eq

uip

. B

ay

CD

U

& A

ssem

bly

1 1 1 1 i i 1 1 ! ! ^ i : ) • ]1 1 ! ! i i 1 1 1 1 [— ) ! ) 1 !1 1 1 ) 1 1 1 1 ) 1 (Nl 1 1 1 1 i

1 1 1 1 1 1 1 1 1 1 | }< . 1 l i ! J1 1 I 1 1 1 1 1 1 1 IsD 1 > 1 ! 11 1 1 ! 1 1 1 1 1 i sO ! J 1 « !

°"

i

I 1 1 1 ! I 1 1 1 1 M I I ' ' !t 1 i i I I 1 I I I ( J x 1 1 i i !1 1 1 I 1 1 1 1 1 1 ^ 1 ! 1 * 1

ro ' ' 1 i <M (\J Is- O rO ^D ro f— O CT^ (M

f\J .1 i 1 l >^O \O r"-( ^* sO OO rO ' — ' N^ ^0 ^^r o M t s l ^ ^ f O c O r o p O r o f M r o

c ^ i i i i m m o o r O j O o o - - H O O i nr - i i i i i c O ^ i o O O ! O f M i n o O O T J

1 . 1 r-H 0)r sc

1O ' ' ' f ' — i • — H O x D u O . c O O O O x O O O r - ^ ^i i t i . . , . . ; . . U

O^ i i i i uO U"l vO O •— i (M I-H fO r-H sX) LO ^*^sO ^o sO i/ xO r**~ >^& ^o r*" *^o ^o 10

W W W H W H W W W W ' W H W W W W W W W W W W W H W WO O O O O O O f M O O f M O t ^ - c O t v J O M O i n o O O t ^ - m O f M

•^r-i •— i i n c M ' - ' i o o r O r o i— i -H o .— i ^ j < —<il— I

nlt-l

— HS3 ^5 £ M.5 <n ^ c ^j c^J d -H <" ^? ^ 'Sg 2 « § >-J c | £ -d - _ M m §

• ^ w c o O ' ^ c o w p C Q ^ ! | 2 ( j ^ i J O ' O U Q U c / 3 . w < ( j c o w ^

O O § £ p Q U Q Q 2 < ; 0< £

Page 19

Date 15 Mar. 1963

POLIO 6 & N WEIGHT & BALANCE REPORT E-1142

n)r-l

4)

M ^

o .'T

"H' i.

sos.

-u

n)MO '«

^0 -2h •£C(UU

•4-1

bO•iH

£

N

i— (

i— (

J

N

>•<

X

CO

-H•M*

w w w w w w w w w wo o o o o o o o ooU1 c O c O N O O ^ r O ^ ^ ^ J * r-H^ji

00

U

OM

MA

ND

MO

DU

LI

U

[ain

Pan

el

Are

a

S

U

L>

P

CO

oo

se S

tore

d I

tem

s

!-}

(U0

• H

H

^-i(UPi(U

W

ilm

Ca

rtri

dg

es

(4)

GC

Lo

ose

S

par

es

k •<

CO

n)CO

COOO

OH

DU

Sp

are

Gea

rbo

x

U

_^

om

pu

ter

Sel

f C

hec

l

U

ori

zon

P

ho

tom

eter

£

ER

VIC

E M

OD

UL

E

w

-— - «i

ad

ar

(Tra

nsp

on

der

(Ren

dez

vo

us

Rad

c

rt

v i .2v< OO U

c! O

«» & 23 O C

> S S

^ 2 1<u J; S

« « -g'S <u rt

U'J ^a s >§ 8 ^O u h

u rt M

6 ti °O O co** 4J ^W cd ®

P 3 ^Q ."S <u

<uM

CO CO-H -M

•^ oc &

w o C

W J3 C)

O 'SCH bo 4) Q

C g co

8 . 4 5 . S

Page 20

Date 15 Mar. 1963

IPOLLO G & N WEIGHT & BALANCE REPORT E-1142

0£

*?O0-

uJ£t* J)°" *£w P0 a< 0

1]

CO

MP

UT

ER

C

LO

CK

O

J_

.«

CO

MP

UT

ER

P

WR

. S

UP

PL1

3

§

SfO

^

1 1

_Ja

otfUl

o

D.o

X

\\Z

QV

J M

3Z

W

o

£5

W

SE

RV

O M

OT

OR

E

)

, ,

j) O

* o

e s"

5

(M

eo

ocp

s2

8V

S

%SU

PPLY

oin

<

,

auvUJ

zo

•4

3

.

80

0 C

PS

28V

1%

SU

PP

LY

r1o;K 5

I"1

§ £u 0

11 1O t/i ^t

s i r *g S S 5o o o oo o u> v

310

_--•-

(M

t

EN

CO

DE

R

EX

C

210

zUl

25.6

. K

GE

NC

OD

ER

EX

C

*

5J

I

in ?u in

t «Q- 0.° 0

s? °g 55

1 £ i<

D * Y\ f

a,-^i-

Ul

SSUJI3£

1

DU

CO

SY

N

EX

C

19 1,

1

UJ *

1"5 0

"rt y01 ^

> j

,

HE

AT

ER

S

ef*

a.0

3

E wj 4-£ 0

ii• 33 S

32

OO

CP

S

SU

PP

LY

/

c1i

II

In

ItO

oz

IMU

&

1MB

AL

SE

RV

O ?

tJ*.

AD

A

PR

EA

MP

PW

R

u

r

4X3ot»

" .

3£

PIP

A P

ULS

E T

OB

QU

E E

LE

CT

!

SCJ

l|

in

IR1

0 ^.

PIP

A

ELE

CT

RO

NIC

4

&5N

1

£

JN

-28

VD

C

SU

PP

LY

N

1 1 Z SI \ll0 U « U>5| 111

3:

a1

a

yOf

IRIG

P

ULS

E T

OR

QU

E E

LEC

IMU

P

RE

AW

PS

° o2 > ->

? ° 3 5°^

r*in

5voN

g

? <n

a,O

UJ

DOU

N

GY

RO

WH

EE

LS

»?zH<fi

*JQ

*n

BL

OW

ER

S

*

Xif)

S

CD

U

MO

TO

R E

XC

3

.

artSrf

?to

I B

OO

C

PS

28

V

S%

SU

PP

LY

3

in

^i2 si f => <"tJ W •Z K

§2

^ £ 2 S| °S5i 3 i 3

5 In 3 1".O K i0 m_ y v *(M (M fl

-

o><UJ

oos:

i

^>

in0

fiA

.I ^

AU

TO

PIL

OT

R

EF

?eO

1 ao

o C

PS

28

V

1%

5U

PP

LV

3

3Eg

£

i/)z-ii-e^h- *^

2z

0X

3

TJ3

Q03N

1

3

ENC

OD

ER

EL

EC

TR

ON

ICS

I2S

.4 *C

EW

CO

DE

R|E

XC

~S

i r;

MA

P f

cDA

TA

VIE

WE

R

i/ii\j

2

UJ

UJ

0

b_X

l-

i*+50

in

oX

00in

i

tn

iTO

Rt

ILLU

MIN

AT

ION

Ll

&W

35""

n .

201 S

0 ^ 0or zz S *D 0 0.

O o£^•^.ui/l

< § 2 sa) j on uiin 1-

. in VJ

a o »- jS * 0 "*

S 3 3 i

o •*"! 5— (0 ~- *(^ - o m

^ ^ ta

ifl_ji-o(-

oclUJ

«i£

^y o

R. O

PT

ICS

AR

E

ON

0

o*

OV1I T

^HM

^I3:(D

inc£•=>OI

?

801

r °° >=it- > >• a ^52 3 = S- «" 0. U> .., .

I* ss.?2

|| fl||

' "* o *" *" *3C O 2 Wl

s fil?I O Ul ? u. •

~ i S <n z3 o 3 o- 5 S --«>•* ^ u-^ 0* Of ul« Ul Ul° °- 3 T5°gl0 .., in5 a S S2< H u

*

UpooCM

n)O

o•l-l

4->

O

(UI—(W

0)

OJO-iH

fa

Page 21

Date 15 Mar. 1963

APOLLO G & N WEIGHT & BALANCE REPORT E-1142

Glossary

AGC:

BELLOWS ASSEMBLY:

CABLING:

CDU & FRAME ASSEMBLY:

COMPUTER SELF-CHECK PLUG:

D&C/AGC:

D&C/NAV:

G&N IND CONT PANEL:

Apollo Guidance Computer: complete com-puters except display and keyboard. In-cludes: - all structural mounting rails,support for spare tray, AGC cable to frontpanel for spacecraft electrical interface,spare logic in four trays, and power supply*

Bellows Assembly: connection between Com-mand Module and Optical Subsystem,

Cabling: intrasubassembly cabling in lowerequipment bay* (Interequipment cablingfrom lower equipment bay to other assembliesis assumed a spacecraft responsibility. )

Coupling Display Units and frame assembly:five gear boxes and frame assembly, usedas an angle data interface among the optics,IMU, AGC, and spacecraft autopilot.

Computer Self-Check Plug: an additionalitem to provide capability of connecting com-puter outputs back onto inputs for checkoutand diagnosis of failure.

Display and Control, Computer: letter andnumber readout, keyboard, control, relays,and support structure.

Display and Control, Navigation: consistsof G & N Indicator Control Panel, IMUControl Panel, Left Hand Turret, andOptical Shroud. The above includes meters,switches, lights, etc. except as reportedelsewhere. The weight does not include theclock group which is supplied by NAA.

G&N Indicator Control Panel: consists ofthe necessary switches, indicators, andcontrols for the navigation task not reported

Page

Date 15 Mar, 1963

APOLLO G & N WEIGHT & BALANCE REPORT [•1142

G&N IND CONT PANEL: (cont'd)

IMU CONT PANEL:

LEFT HAND TURRET:

OPTICAL SHROUD:

EYE RELIEF EYEPIECES:

FILM CARTRIDGES:

HORIZON PHOTOMETER:

IMU:

JUNCTION BOX:

M&DV:

NVB & SHOCK MOUNTS:

OPTICAL EYEPIECES:

elsewhere. Includes optics hand controller,altitude impulse control, panel wiring, andsupporting hardware,

IMU Control Panel: meters, switches,panel wiring and supporting hardware.

Left Hand Turret: contains electronic modules.

Optical Shroud: includes protective cover./

Eye Relief Eyepieces: .eyepieces to provideeye relief of at least 1. 6 inches for closedvisor operation.

Film Cartridges: film cartridges, includingfilm, for Map and Data Viewer.

Horizon Photometer: an automatic, photo-metric, horizon detector device interchange-able with sexarit eyepiece to provide capabilityfor use of earth's illuminated limb as anavigation reference. j

Inertial Measurement Unit: gimbal assembly,inertial components, data transducers, sup-port structure, and internal cooling.

Junction Box: electrical interconnectioncenter between subassemblies in lower equip-ment bay.

Map and Data Viewer: film viewer for displayof maps, charts, procedures, etc. Weightincludes one film cartridge with film.

Navigation Base and Shock Mounts: rigidstructure supporting the IMU and the OpticalSubsystem with its associated hardware andsupported by three shock mounts that attachthe NVB to the spacecraft.

Optical Eyepieces: optical eyepieces for SXTand SCT.

Page 23

DatelS Mar. 1963

APOLLO G & N WEIGHT & BALANCE REPORT E-1142

OPTICAL SUBSYSTEM:

OPTICAL BASE AND GEARING:

SCT:

SXT:

PSA:

SIGNAL CONDITIONING TRAY:

RADAR (TRANSPONDER AND REN-DEZVOUS RADAR):

Optical Subsystem: SXT, SCT, OpticalBase and gearing, panel base, and as-sociated hardware.

Optical Base and Gearing: base for SCTand SXT with associated gearing,,

Scanning Telescope: single line - of -sight,wide-field, two-degree-of-freedom tele-scope and its drive mechanism.

Sextant: two line-of-sight, narrow field,two-degree-of-freedom sextant, includingdrive mechanism and internal cooling.

Power Servo Assembly: IMU, SCT, andSXT servos, power supplies, CDU elec-tronics, IMU backup mode electronics,and miscellaneous electronics.

Signal Conditioning Tray: tray in PSA tocondition signals for telemetry and in-flight test equipment.

Radar (Transponder and Rendezvous Radar):electromagnetic ranging equipment, locatedin service module, for lunar orbit rendezvous.

Page_ 24

Date 15 Mar. 1963

APOLLO 6 & N WEIGHT I BALANCE REPORT E-1142

DISTRIBUTION LIST

Er-1142 Rev 6

NASA (50 copies)

Participating Contractors (36 copies, 12 each)

Apollo Limited Internal

Alonso, R.

APOLLO Library (15)

Battin, R.

Bean, W.

*Black, D. C. - Dept. 695-323

Bowditch, P.

Boyce, A.

Bryant, P.

Dahlen, J.

*Day, W. E. - Dept. 695-313

Duggan, E.

*Felix, S. (Attn. Dept. 4-612)

Flanders, J.

Gregorek, S. (S&ID, Cambridge)

Hall, E. C.

Halzel, I.

Hanley, D.

Hickey, E.

Hoag, D.

Houston, F.

Harsh, J.

Koso, A.

Kramer, M.

Kupfer, W.

Ladd, D.

Levy, J. (WESCo) (2)

Mayo, G.

Miller, J.

MIT/IL Library (68 Albany St.). (8)

Nevins, J.

Nugent, J.

Olsson, E. A.

**Peters, Fred

Redding, F. W. (S&ID5 Cambridge)

Rhine, W. (NASA) (3)

Sciegienny, J.

Sears, N.

Trageser, M.

Wilk, L. (2)

Woodbury, R.

.* North American Aviation, Inc.Space & Systems Information Div.12214 Lakewood BoulevardDowney, California

** Apollo Command and Service ModuleOffice CityManned Spacecraft Center (NASA)Houston 1, Texas

Page 25

Date_j5 Mar. 1963