guidance and navigation - ibiblio · guidance and navigation approved: c date:

GUIDANCE AND NAVIGATION

Approved: c Date: /<A763 MILTON B . T R A G E m R . DIRECTOR ~ - ~ .

APOLLO GUIDANCE A N b NAVIGATION PROGRAM

E-1142 (REV. 15)

(UNCLASSIFIED TITLE)

SYSTEMS STATUS

REPORT

D e c e m b e r 15, 1963

I N ST R LJ IM E N TAT I Q N L A 6 0 RAT 0 RV

CAMBRIDGE 39, MASSACHUSETTS

C O P Y # % \ OF ! 5 < COPIES THIS D O C U M E N T C O N T A I N S '50 PAGES

ACKNOWLEDGMENT

This r e p o r t was p r e p a r e d under DSR P r o j e c t 55-191,

sponsored by the Manned Spacecraf t Cen te r of t h e National A e r o -

naut ics and Space Adminis t ra t ion through Cont rac t NAS 9- 153.

The publ icat ion of t h i s r e p o r t does not cons t i tu te approval

by the National Aeronaut ics and Space Admin i s t r a t ion of t he find-

i ngs o r the conclusions contained there in .

f o r the exchange and s t imula t ion of ideas .

It is publ ished only

c

LIST OF EFFECTIVE PAGES

Page Numbers

Title Page through vi

1-1

2-1 through 2-10

3-1 through 3-3

4-1 through 4-8

5-1 through 5-2

L I

I O DATE 12/15/63

CONTENTS

Section

a

Page

1 1-1 1-2

2 2 -1 2-1 .1 2-1.2 2-1.3 2 -2 2-2.1 2-2.2 2-2.3 2-3 2 -4 2 -5 2 -6

3 3-1 3-2 3-3

INTROD --C T OY INTR,OD. 'C? ON A c C'IT RAC Y

COMMAND MODULE DATA WEIGHTS WEIGHTS STATUS REPORTING SPEC . WETGHT DESIGN LOAD WEIGHT REPORTED WEIGHT CHANGES CONTROL ELECTRONICS D&C/.4GC QLEB) D&C/A4GC (MP) CENTERS OF GRAVITY MOMENTS OF INERTIA COMW4ND MODULE POWER REQUImMENTS CURRENT STATUS OF COMMAND MODULE AGC PROGRAMS

LUNAR EXCURSION MODULE DATA POWER REQUIREMENTS FOR LEM WEIGHTS FOR LEM REPORTED LEM WEIGHTS CHANGES

4 GLOSSARY

DISTRIBUTION LIST

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 2 -4 2 -8

2-10

3-1 3 - 1 3 -2 3-2

4-1

5-1

D A T E 6 3

ILLUSTRATIONS

n

Figure 2-1

Table

2-1

2-11

2 -111

2 -1v

2 - v

3 -I

3 -11

DATE 12/15/63

Page Electrical load on primary +28-VDC power supply 2 -5

TABLES

Current Weight Status of Command Module

Command Module Center of Gravity and Moment of Inertia Data

Nominal Power Dissipation (watts) v s G&N Activity

Block I Command Module Power Profile for 14-Day Lunar Orbit Mission

Current Memory Estimates and the Status of Command Module AGC Programs

LEM Power Requirements

Estimated Weights of LEM G&N Components (lbs at 1 g)

Page

2 -2

2-6

2-8

2 -9

2-10

3-1

3-3

P A G L

ABSTRACT

The System Status Report, E-1142, is distributed monthly on the 15th. This

month's revision, Rev. 15, contains weight and balance data. and power requirement

information f o r t h e guidance and navigation equipment in the Lunar Excursion and

Command Modules. In addition, the status of the Command Module computer pro-

grams is included.

P A G E ! -.

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 Mod- ule 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) the status of Command Module computer programs.

System status reports and revisions to this date have applied to the so-called Block I G&N configuration. The definition of what constitutes Block 71 has now reached the stage (see Glossary) where monthly reporting on Block I7 a s well as Block I and LEM G&N will be added starting with the January edition of this document.

Weights in this report for the Command Module are based upon the current "Block 1" design releases. The Lunar Excursion Module weights are based on the best estimate of those expected for the LEM design release which will occur early in 1964.

1-2 ACCURACY

The accuracy o l numerical values reported in this revision should not be considered to be within the tolerances implied by the significant figures quoted. The reported values, although based upon the most current information, are subject to normal changes as design and development phases approach completion.

COMMAND M O D U L E

c

Section 2

COMMAND MODULE DATA

2 - 1 WEIGHT S

Table 2-1 presents the weights of all Block I equipment$ grouped according to specific location within the Command Module. Weights are reported to the @om- ponent level and to the nearest tenth of a pound.

Given component weights are identified as estimated, calculated, and measured in the order of increasing accuracy. These t e rms are defined by North American Aviation as follows.

Estimated weights (E) a r e based on rough calculations. Calculated weights (C) are based on detailed calculations made from final production drawings that will be used to build flyable equipment. Measured weights (M) a re the actual weights of equipment built to the production drawings.

Since most weight values now reported can be classified as only estimated weights, MIT herein affixes a prime to the (E) symbol, i .e. , (E'), to denote values which MIT, for various reasons, feels to be more accurate than estimated values, yet which cannot be defined as either calculated or measured weights.

North American Aviation will. provide and be responsible for coldplate weights which are not integral with guidance an.d navigation equ.ipnient

2 - 1 , l WEIGHTS STATUS REPORTING. Table 2-1 also offers a comparison of present component weight values with those listed in System Status Report, E-1142 (Rev. 14), November 15,1963. A l l weight changes are explained in paragraph 2-2,

2-1.2 SPEC. WEIGHT, The I5Spec. Weight" column in table 2-1 contains "proposed MSC weights, I ' that is, goals set forth by MSC in a memo to MHT dated December 5, 1962

2-1.3 DESIGN LOAD WEIGHT. The "Design Load Weight'? column contains worst- estimate design weights assigned to G&N subassemblies attached to the spacecraft structure. These values are included in this report as the result of an S&PD request, at NASA Coordination Meeting No. 8, that one total weight figure for supported G&N

ii; 3

h

T e

c)( COMMAND M O D U L E

4

0 0 0 0 0 0 0 0 0 0 0 4 l - c v ~ c v w o o o o o . . . . . . . . . . si 0 0 0 0 0 0 0 0 0 0 d n ; i A d G d d $ d d I I l I + + I +

* K l c . l w c v 0 O Q C - 0 4 * &

. . . In 0 0 0

rl e l 4 rl

. . . + + + + + + + I + + + +

0 0 0 0 0 0 0 0 0

d * 4 m . . . .

(d s i & j c; o w 0 3 0 m 0 0 0 0 0

0 m u 3 0 In0 m d

. . . . .

DATE12/15/6 3

e

c

. Y . -

" M 8 Gl PI

- COMMAND M O D U L E

h h h h

2 u ) I Y E u)o (om e. I . * * * . . 6 F i m m o rl

o o m o o q 4 o Y ; . . . * d d r - ' d m o o 4 I I I

+

n

0 1 . I

u) 4

tJ h

555 e. e. v 3 o m 0 0 0 m . . . . . . r ; m b o m * o

"LJ

+ I + + + + +

0 0

Gad

a3

hl " * - 0

Q) m I

Q)

" In *

m

GI C I3 0 B

o o o m 0 0 0 0 . . . .

I

h h h h

Y Y Y Y w w w w O C D b O

m * C D m h l m 4 . . . .

COMMAND M O D U L E

load be assigned for structural design use. MIT herein assigns a total G&N design load weight, in table 2-1, which does not include items termed ftloose stored ir.ems. The breakdown of this total weight into the individual items of columna "d" is typical only.

2-2 REPORTED WEIGHT CHANGES

The Block I weight status summarized in table 2-1 this mon*h separgtes the weight of possible spares from the main body of the table. the Development Test Plan activities now under way at S&ID which are defining Block I G&N usage. manned o r of only limited duration, the need for carr ied spares is doubtful. (Block I1 G&N will ca r ry no spares in any event; a detailed report on weight hopefully wi l l be published here next month. ) Because Block I was originally designed for use of spares for inflight repair, the weight of possible spares is listed separately for information in table 2-1.

This was done in recognition of

Since any spacecraft flights involving Block 1 G&N hardflare will be un-

Other changes since last month's report, E-1142 (Rev. 14j9 Ncwember 15,1963, shown in table 2-1 are explained. below. Al l weight changes shown in column (c - b) of the table a r e the result of weighing of the components except fo r the following.

2 -2 .1 CONTROL ELECTRONICS. The previous weight represented only the t rans- former weight. The weight increase reflects the additional weights of the components which make up the Control Electronics. These a r e identified in the Glossary.

2-2.2 D&C/AGC (LEB). The weight increase is due to the addition of spare relays and to the weighing of 50% of the parts.

2-2.3 D&C/AGC (MP). Same a s 2-2 .2 .

2-3 CENTERS O F GRAVITY

Table 2-11 presents the centers of gravity of each weight component o r packaged assembly, determined with respect to the basic X , Y, Z axes of the Command Module. Center of gravity values are given to the nearest tenth of an inch.

2-4 MOMENTS O F INERTIA

Table 2-11 also presents the moments of the inertia of each weight component o r packaged assembly, determined about each of the component axes which (1) run through the center of gravity of the component and (2) are parallel to the basic X , Y , Z axes of the Command Module.

x

P A G E 4

COMMAND M O O U L E BLOCK I

b+.lW ON 91 7W In" OFF

c

L W 000- 4 A C I SV"

22w 2 5 6 KC CNCODER _I w R FICl

TOTALS: Gq+Zl V UOURS BAYD UPMi 336 MWRS NOTi5: (0 TO 5 (C (I4MY)tUNaR CUBIT MISSION (ZlINTERMITLNT OPER. 188.7 h' AVG 1

607.3 W A U SYSTEtlS WERATIW.

CODE lcl CALCULATED W E R (el ESTIWTED FQWfR (RfF S l I D LETTER 63 M A 7332) W M u L n E D W W f R 641.9 W WORST POSSIBLE

(LESS TYlH 1 % ON TIM€)

Figure 2-1. Electrical load on primary +28-VDC power supply'

. DATE 12/15/63 PAGE-

- C O M M A N D M O D U L E

c

.

U

M u 0 I4 a

* 0 rl d

* m o a 3 0

4 m rl * C J r l m

* 0 rl d

* 0 0 0 0 r l r l m m

* o 4 *

* * * * * C J C J m m o 0 0 C J C J A O C J a a

rlrl a m m r l

* u) d

* * * * *

* * a c - 0 4 m m c - . . . . . . . . . * a m 0 m m o rl . . . 2 m m o y * o 7 m m 0 0 0 G A L

I r l I rl I I I I

* I I * * * * * u) 0 0 0 m m C J C J a C J 0 * m a C J m a m 0 0

4

P A G E

-a ti E E 0 u H U

I c;)

a, Q 3

C O M M A N D M O D U L E

E a, U w

(I)

COMMAND M O D U L E 2-5 COMMAND MODULE POWER REQUIREMENTS

a

The power requirements of the Command Module G & N equipment on the pr imary + 28-VDC power supply are shown in figure 2-1 , which presents the magnitude and location of dissipated power values on a subassembly level. This chart assumes a 14-day lunar orbit mission as defined by S&ID fo r power profile computation (Ref: S&ID) letter 63 MA 7332).

Table 2-111 shows the magnitude and location of power dissipation for the estab- lished G&N activities, each of which consists of various power levels of operation.

Table 2-IV shows the energy requirements for each G&N activity on a power level basis, The table is based upon &LIT letter AG 679-6, "G&N Power Profile Status, '' dated August 14,1963. The vertical column to the left indicates the various G&N activities (phases of operation) for the model 14-day mission submitted by S&ID in S&ID let ter 63 MA 7332. This column also indicates the power consumption and operating time for each specific activity. The top row indicates the various power levels along with the power consumption and operating time of each power level.

Table 2-111. Nominal Power Dissioation (watts) v s G&N Activi

G&N Activity ower levels

A IMU & AGC Operate (1,4)

B IMU Alignment (1, 2 , 4 , 6)

C Low-Orbit Navigation (1, 3 , 4 . 6)

D Standby & Computing (1% 5)

F IMU & AGC Standby

G IMU Operate & AGC i Standby (4, 7)

(5. 7)

N

IMU

74.5

-

- 74.5

74.5

4 3 . 5

43 .5

- 43.5

74 .5

The rma l Load on

440 .1

110 I 564.6

110 I 555 .6

I-- 194 .7

319.2

340 .1

1. AGC 2 . Optics, SXT on 3. Optics, SXT off 4 . IMU Operate 5. IMU Standby 6. Display and Control 7 . AGC Standby

120 watts 111.1 watts 1 0 2 . 1 watts 330 .8 watts

84.7 watts 45 .4 watts 10 watts

P A G E 2 k L

I I Ele;c!;aI

450.8

I 42:: 1 607.3

598.3

t- 204.7

361.2

0 .7 340 .8

C O M M A N D M O D U L E

- rl m t-

W m

-

t- 3 00

t-i

N In N W * N * rl

J N

kc t-r

N

rr: N

,- c- c- W 3 N

I I

r Q1

C

r

00 0 0

3

- 3 t- t-

* N

-

t- c-

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m

- m N * 0

I I

m W 0)

W

w

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C

W

Q,

3

m I I

d C lc C

00 0 P-

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m t- N I I

I rl

I

I I

E o a w I 4 1 m n u

c

DATf 12/15/63 PAG-

COMMAND MODULE 2-6 CURRENT STATUS OF COMMAND MODULE AGC PROGRAMS

Table 2-V l is ts current Command Module memory estimates and the status of AGC programs. The status of LEM AGC programs is not reported at this time.

A high and low word estimate is given with each program. Each status is defined as follows:

(1) Planning stage (2) Programming stage (3) Checkout on AGC simulation (4) Checkout on G&N simulation (5) Checkout on AGC

Table 2-V. Current Memory Estimates and the Stztus of Command Module AGC Programs

Program

List Processing Inte rp re te r AGC Executive AGC Wait1 iste r AGC System Exerciser , Checkout,

G&N System Exerciser & Checkout Display, Keyboard, and Telemetry Input/Output Control Midcourse and Orbital Navigation Midcourse and Orbital Guidance Prelaunch Platform Alignment In-Nigkt Hath r m A1 ignment Recentry Wntrol Injection and De-Boost

and E r r o r Handler

I Totals

Status Memory Estimate

(words) TI$-- -

1600 250 150

1000 1000 1500 850

2000 500 4 00- 980

12 90 1000

12520

Low

1600 250 150

750 750

1500 350

15 00 5 00 400 90 0

1024 400

10074

* These items have changed since the last report, E-1142 (Rev. 14), dated November 15,1963.

c

LUNAR EXCURSION MODULE . __-

Section 3

LUNAR EXC'LTRGION MODULE DATA

3-1 POWER REQUIREMEWS FOR LEM

The current estimate of LEM G&N power and energy (see table 3-1) is based upon the fixed-telescope concept and the use of the Command Module IMU and computer.

The values shown in table 3-1 are center value estimates and do not include any safety factor for bad estimating. .,

Transient power peaks, occuring at higher power levels during turn-on and slewing operations, are considered to consume negligible energy. When they become available data on these peaks will be included. *

Table 3-1. LEM Power Requirements *

Display and Controls

Note that the total eneqgy drawn, 21.70 Irvvh, is considerably higher than for a '"normal" mission since the estimate provides for full operate power for the 18 hours of "orbit contingency" mode. Without this contingency the G&N takes about 13 kwh based upon the GAEC profile.

l U N A R E X C U R S I O N MODULE .-

s p a p a t e power turn-on switches are assumed fo r “IMU operate, It %omputer standby, I t ‘komputer operate, It and “radar CDU. The LEM G&N uses only the spacecraft + 28-VDC power supply except fo r operation of condition lights. The condition

I lights operate from the spacecraft 400-cps power supply.

3-2 WEIGHTS FOR LEM

Lunar Excursion Module weights are presented in table 3-11. In general the data conform to the information contained in paragraph 2-1 and 2-1.1.

Column (a), Target Weight, was taken from GAEC LMD 490-39, Enclosure 1 , submitted to MIT at a weights review meeting on September 10, 1963. GAEC reported that G&N weights associated with D&C will be reported by them as part of the total spacecraft D&C. Therefore, target weights were not given by GAEC to supply the five items denoted by aster isks in column (a).

The row labeled Bare Guidance System is inserted to provide for comparisons with .I --> * . . ”... ..” similarly ~- specified systems. * -.

3-3 REPORTED LEM WEIGHT CHANGES e _. I_

All weight changes shown in column (c - b) are the result of CM BLOCK I1 G&N design changes which reflect directly on LEM hardware status. (see Glossary).

P A G E - 2

. .. , . . .,.

Y

e

- LUNAR EXCURSION MODULE

* *

m o 0 o m o m m o d *

_ _ 0 0 N O o w c o o n;,.

d @ i u i dddui + I + I I l l

m m 0 N

co' m I

m 0 d d

GLOSSARY AND SYSTEM DEFINITION

CM BLOCK I A single complete flight cornpv-tex" wctniring -ill loeiri, memory, associated power supplies, and all interface CII'C nits except thc,se ider,?,Lfied with the CDU's. Does not contain the associated displays znd controls.

Consists of two t rays containing rc=pltccea*:le eler,tv.onir modules, the AGC end connector, and toe plate. Does not iccllude the necessiry cold plate OF the G&N to CM interface assembly which is located in &e adj.;lcera& n r e i . Spnce exists for carrying an extra spare pair of AGC f-rays. These wozld not f v r r : t km h this spares location but could interchange with f m l t y cra:ys 1 " ~ the d ~ t i v e position. The spare trays are not included in this acco1iriting.

CM BLOCK I1 Two complete and active cornp?iteys tach havinq she same functions as the BLOCK I AGC.

Consists of two wiring matrix headers mor.2",ed on each side at the cold plate.

The modules ~f the ['X" compile.. mount on one of This cold plate is not included in this accomting wrd m ~ s t be moved up from the BLOCK I configuration location. these headers, the ltYrr computer on the other.

BLOCK I and BLOCK I1 AGCss are not intexbangeable.

- LEM A single complete flight computer having the same Suncki.ons as one of the BLOCK I1 computers. Unless installation c::onst::aints yet to he determined. prevent it, the LEM computer will be physically i.deril;ical with one of the BLOCK 11 m m - puters.

ACC S p a r s

CM BLOCK I Spare AGC modules or trdjs as indlaatedo

CM BLOCK I1 No spares for AGC in BLOCK IT

LEM No spares for AGC in LEM

CM BLOCK I and CM BLOCK I1 Flexible pressure seal hetween CM structure and optical subsystem on NAV EASE fo r penetration of press3jy.e h7.nll with ~ p l i c s .

LEM ___ Not identified separately in L,EM. Is included in L,EM as r~art of the AOT.

CM BLOCK I and CM BLOCK I1 Consists of (1) three aluminum ilex coolant hoses between IMU and spacecraft, optics and spacecraft, and optics and IMU, (2) bracket assembly screws and clamp, and (3) entrapped coolant,

LEM Not identified as part of LEM

CDU and Frame _I Assemhly

The CDU provides the necessary sigxal interfaces among the llMU gimbal angles, optics gimbal angles, radar gimbal angles, angle registers in the AGC, the spacecraft autopilot attitude e r r o r signals, and the tracking radar command e r r o r signals.

CM BLOCK I Five interchangeable gear boxes each with nec~essarp motor, tach, resolver synchros, and encoder with mounting framework. Does not include associated electronics which are located in the PSA.

CM BLOCK I1 Functionally identical to BLOCK I except the instmmentation is all electronic Includes all support electronics including special power supply and is located in some volume as BLOCK I CDU?s.

Changes in resolver synchro characteristics and mode controls make BLOCK I and I1 CDUPs noninterchangeable.

LEM Interchangeable with CM BLOCK I1 CDUPs.

Display and Cont rol/Apol io Gu idarice __ - Comzute - I

CM BLOCK I & BLOCK I1 Number displays and keybosrd control associated with the operation of the AGC. Two functionally identical and parallel operation units: one in lower equipment bay and one on main panel between left and center couches.

P A G E L

LEM Identical to CM except only a single unit is required. _I_

' *

G&N IND. CONT. PANEL

@&N 'Indicator Control Panel y_I_-

- CM BLOCK I & BLOCK 1% Consists primarily of controls and displays fo r the operation of the optics, and the PMU cemperzture control. Includes display and control elements , panel, panel airing, and supporting hardware.

LEM Not defined at this time for LEM.

IMU Control Panel

CM BLOCK I Consists of panel, wiring, attitude error meter , CDU transfer switch, manual alignment switch. CDU mode control switches, connector, and supp o 1-t ing ha rdw a re.

.- CM BLOCK I1 Does not exist in BLOCK 11. Moding is done by AGC program and AGC push buttons.

L

LEM Not defined at this time for LEM.

Control Electronics Assembly

CM BLOCK I Consists of one power transformer, one re1a.y and diode module, and a bracket end connector. Used to support display and control functions.

CM BLOCK II May be relocated with other similar functions.

- LEM Not defined in LEM

D&C Electronics Assembly

CM BLOCK I Consists of a chassis, a relay and diode module, a Demod. Elect. inodule, a saturable reactor, a time delay module, a ccnmector, and wiring. Used t o support displays and controls functions.

GM BLOCK 11 Similar and probably ideretical to BLOCK I .

LEM Not defined in LEM at this time.

CM BLOCK r AND BLOCK WX Ccnsis's of a SXT and B SC'T eyepiece t o provide eye relief of a t least 1.6 inches fo; pueceb of SXT and SCT.

- _ I _ _ ~ -. - losed-visor opei'dOion. b'sed in place of normal eye-

-I_ LEM Lag-eye-relief eyepicze for the A 0 T is induded as part of the AOT in this am uonring.

@tical Shroud & Cover Assemblv

CM BLOCK I AND BLOCK _-_. IX Consists of the Opt.icz1 Shroud and protective cover. --I_

LEM Does not exist in LEM,

Film Cartridges -__*I- I

CM BLOCK I AND BLOCK I_ El Consists of film cartrid.ges and film for the Map and Datz. Vieher.

LEM Does not exist in LEM. I-

G& N Inte rconne'i: tim A s sembly

.I_-___ CM BLOCK 9 Consists of PSA End Connector Assembly and intercxmnect wiring harness R hich electrically t ies together the assembles that constitute a completely integrated system. This t e r m dces not include the G&N to CM Interface Assembly \&eight o r the weights of harness stippart brdekets which are a NAA responsibility.

V

CM BLOCK PI Similar to Block I but not interchangeable with Block I .

-111 LEM Not clearly defined at present, w a s called in earlier reports the AGC/PSA In',ercnnneetion Assy. Because of the wide separaticn 0f G&N components, most intercennection will be accomplished BS part of spacecraft wiring.

G&N to CM Interface Assembly

CM BLOCK I Tnterconnecticms between the spacecrzf?, wiring c ha.nnel, the computer end connector, and the PSA end connector. Contains no active electronics.

~ = - CM BLOCK 11 Similar in flrnction to BLOCK ?[ except the configuration is much different and not interchangeable wish BLOCK 1.

___ LEM Not identifiedyet a s a separate item in LEM.

- CM --. BLOCK 1 Size 14 BMU (14-icch case diameter) gimbal assembly including all parts inside hermetic case a rd 3: lccling Pxcrapped coolant.

_I CM BLOCK YB Size 12.5 YMU fune.t,fenallv interchangeable w%h BLOCK 1 unit, but me, physically interchangeable o:ith BLOCK 1.

LEM SiAe 12 .5 IMU as described above. . _ _ -

PSA End. Connector Assemblv

CM BLOCK I Electrical inf,erccnnect.;cn between the PSA t rays , the G&N Inter- cunnection Assy. and the G&N to CM Interface Assy, ~ _ -

CM BLOCK 11 Not identified as a. semrate item: will be part of the PSA matrix

.-- LEM Not yet defined. Wil l probably not exist in

M&DV

Man and Data Viewer

LE M

-- CM BLOCK I AND BLOCK - 11 Film viewer for display of maps, charts, procedures, etc a Weight includes one film cartridge with film.

--._ LEM Not in LEM; see Book of Procedures.

NVB AND Ssolation Mounts -- ---l_l___ CM BLOCK I Rigid structure srapporting the IMU and the optical subsystem with its associated hardware TSQUTHON MOUNTS to prevent spacecraft strains from distorting the NVB and the alignment between the HMU and Optics. Y; ikr ration ztittenuat ion.

The NVB is attached to the spacecraft using flexible

These mounts also provide shock and

-*-I- CM BLOCK 11 Functionally s imilar t o BLOCK H but will be lighter and provide for momting the size 12.5 IMU.

LEM --_ The need f o r tieing the AOT and 9MU together exists but is aceomplnshed using s t r i c + u r k provided by the spacecrsfr cen?,_?rastor.

Optic;. X Eyepieces --I__.

I CM RLCKK 1 Removable SXT eyepiece and removable SCT 1-and 3- .po~t!r eyeph-x oanbinat,ion.

_I GM BLOCK I1 Same as BLOCK B for SXT but only a. 1-power eyepiece will be L J S ~

PZ-Lth the SCT e

LEM Included as part of the AOT. --

ODtical Subsvstem

CM BLOCK I Consists of SXT, SCT, Potlcal base, and associated hardware defmzd 2.s follows,

SX T:

SCT:

Sextant - - a two-line-of-sight, narrcm -field t~vo-degree- of-freedom sextant and i ts attached gearing, Scanning Telescope -- a single-line-of-sight, .iv;de -field- of-viewV, two-degree-of-freedom articulatetiom opt L c x l instrument and its attached gearing.

a

OPTICAL BASE: Base for SXT and SCT with associated gearing a d internal cooling.

_I--.- CM BLOCK 11 Similar to BLOCK I except for changes in the sextant to pmvide line-of- sight velocity control directly without CDUvs.

LEM Not in LEM, see AOT. .-_I-

AOT

A1 ignment Optical Telescope

CM BLOCK P AND BLOCK I1 Not in CM, see Optical Subsystem _- --

LEM A 3-position periscope with single-degree-of-freedom manual read reticule for alignment of the IMU.

PAGE4 -c;

Horizon Photometer

.

.CM BLOCK I Not all BLOCK I systems wi l l contain this function, but to support expected early unmanned fliphts using BLOCK I this will be incorporated into la ter BLOCK I systems for preflight qualification and flight test. Equipment is defined below. BLOCK I weights assume Horizon Photometer.

- CM BLOCK I1 An earth horizon brightness photometer and automatic star t racker for navigation measurements against the earth 's illuminated limb. The sensors are incorporated into the head of the SXT, the weight of which includes this function. The PSA includes support electronics.

LEM Not par t of LEM.

PSA

Power Servo Assembly

CM BLOCK I Consists of most of the support electronics: power supplies; IMU? Optics, and CDU servos; IMU temperature control; and accelerometer and gyro pulse torquing.

Connector Assembly. Includes front toe plate but not necessary cold plate. Consists of 10 t rays with replaceable modules which plug into the PSA End

CM BLOCK 11 Similar in function to BLOCK I but does not contain the CDU servos needed in BLOCK I.

modules plugging onto the top. Consists of a single plane matrix header. to mount onto the cold plate with the

Eye Register for Reticule

- CM Not in CM

LEM Device o r equipment not defined yet in detail to position the LEM pilot!s eye to use the window marking reticule pattern for landing point observation and selec- tion during the constsnt flight path phase of landing.

Two-Digit Readout for Reticule

C A Not in CM.

~. LEM A 2-digit readout driven by the AGC from 00 to 99 to indicate range component of landing point using fixed numbered scale on window reticule.

Book of Procedures

CM Not in CM; see M&DV.

-- LEN Book o r other form of maps, charts, plpo~edures, instructions, et?. needed for lunar operations.

Cold Plate - CM BLOCK 1 AND BLOCK 11 Cold plates for the HMU are built into the ZMU. Nesessary cold plates for electronics are part of the equipment supplied by the spa- t,e@mft m h m - facture I.

PAGE_-4 -

DISTRIBUTION LIST E-1142, Rev. 15

Apollo Limited Internal

Alonso, R. ApsElo Library (15) Battin, R. Bean , W. Bowditch, P. Boyce, A. Bryant, P.

Dahlen, J. Duggan, E. Flanders, J. Felix, S. Hall, E. C. Halzel, I. Hanley, D. Hickey, E. Hoag, D. Houston, F. Hu r s h J .

copps, s.

Ddaney] Capt. W. (AFSC/MIT) Gregorek, S. Heuermann, T. (GAEC/MIT) Rhine, W. (NASA/RASPO/MIT) Small, J. (GAEC/RASPO) AC Spark Plug Kollsman Raytheon

(NAA S & ID/MIT)

NAB RASPO:

DATE&,/15/6 3

Koso, A . Kramer, M. Kupfer , W. Ladd, D. Lawrence, J. Lawton, T. Mayo, G. Miller, 3. MIT/IL Library (68 Albany St. )i (8 ) Nevins , J. Nugent, J . Olsson, E.A. Sciegienny , J . Sears , h. Stameris , W. Trageser , M. Wilk, L. (2) Woodbury, R.

External

National Aeronautics and Space Administration Resident Apollo Spacecraft Project Officer North American, Inc. Space and Information Systems Division 122 14 Lakewood Boulevard Downey, California

P A G E 2 - L

H m

GAE (2:

NAA :

MSC:

NASA Headquarters 1520 H Street. Washington, D, C: Attn" M r . G. M. h w , MDCP)

Grumman h i r c ra.ft, Engineering Corporation Bethpage Long 1sle.nd New York Attn" Mr. Po Gardner

North American Aviation, Inc. Space and hformation Systems Division 122 14 Lake wood Boulevard Downey , California Attn: M r . R. Berry (1)

National Aeronautics and Space Administration Manned Spacecraft Center Houston 1, Texas ApOllCJ Document Control Group (SDG) (42) Apollo Command and Service Module (3) Atfn: M r . F. Peters Attn: Mr. P. E b e r s d e (2)

WESCo: Washington Engineering Services Go. , Inc. White Flint Science Park Kens in@ on ~ Maryland A t h : M r . J. P. Smith

WESCo 68 Rogers Street Cambridge 39, Massachusetts Attn: Mr. J. Levy (2)

AMR: Mr. Kennet,h Dunipace MXT -A MR MHT Guidance Test Manager P. 0. Box 828 Cocoa Beach, Florida

Q6 P

(45) ?

a

guidance and navigation - ibiblio · guidance and navigation approved: c date:

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