DOD

AP GUIDANCE A N D NAVIGATION

Approved: & 4, * Date : ”#@ 7 MILTON B. TRAGESER, DIRECTOR APOLLO GUIDANCE AND NAVIGATION PROGRAM

Approved : Date: 16/. / 6 ? DIR;ECT R

INSTRUMENTATION LABORATORY

E-1142 (REV. 14)

(UNCLASSIFIED TITLE)

SYSTEMS STATUS

REPORT

November 15, 1963

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I N S T R U M E N TAT I 0 N LA6ORATORV

CAMBRIDGE 39, MASSACHUSETTS

COPY# 47 OF 15.5 COPIES THIS DOCUMENT CONTAINS b PAGES

I r* I .

ACKNOWLEDGMENT

T h i s r e p o r t was p r e p a r e d under the ausp ices of DSR P r o j e c t 55-191, sponsored b y the Manned Spacecraf t Cen te r of t he National Aeronaut ics and Space Adminis t ra t ion through

contract NAS9-153.

T h i s document

t h e nat ional defe United S ta tes within

the meaning of t h e a g e Laws , T i t l e 18, U. S. C. , Sect ions 793 a t h e t r a n s m i s s i o n

o r t h e reve la t io m a n n e r to an

unauthorized pe

T h e publ icat ions of t h i s r e p o r t d o e s not const i tute approval

by the National Aeronaut ics and Space Adminis t ra t ion of t h e

findings o r t h e conclusions contained the re in .

only for the exchange and s t imula t ion of i deas .

I t is published

LIST OF EFFECTIVE PAGES

Page Numbers

Title Page through vi

1-1

2-1 through 2-12

3-1 through 3-3

4-1 through 4-3

5-1 through 5-2

CONTENTS

1 INTRODUCTION 1-1 INTRODUCTION

I 1-2 ACCURACY

Page

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

COMMAND MODULE DATA WEIGHTS WEIGHTS STATUS REPORTING S PE C . WEIGHT DESIGN LOAD WEIGHT REPORTED WEIGHT CHANGES IMU G&NIND. CONT. PANEL PSA LOOSE SPARES CENTERS OF GRAVITY MOMENTS OF INERTIA COMMAND MODULE POWER REQUIREMENTS CURRENT STATUS OF COMMAND MODULE AGC PROGRAMS

3 LUNAR EXCURSION MODULE DATA 3-1 POWER REQUIREMENTS FOR LEM 3 -2 WEIGHTS FOR LEM 3-3 REPORTED IXM WEIGHT CHANGES 3-3.1 IMU 3-3.2 PSA

4 GLOSSARY

DISTRIBUTION LIST

P A G E -

1-1 1-1 1-1

2 -1 2-1 2 - 1 2 -1 2 -1 2 -5 2 -5 2 -5 2 -5 2-5 2 -5 2 -5

2-12

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

4 -1

5-1

D A T E 6 3

ILLUSTRATIONS

Figure

2-1

2 -2

2-3 \

Chronological weight status of G&N equipment

X, Y, Z axes of Command Module

Electrical load on primary +28-VDC power supply

TABLES

Table I

I 2 -I

2-11

I

I 2 - I11

~ 2-IV ~

2 - v

3-1

I 3-11

Page

2 -4

2 -8

2 -9

Page

Current Weight Status of Command Module (lbs) 2 -2

Command Module Center of Gravity and Moment of Inertia Data 2-6

Nominal Power Dissipation (watts) vs G&N Activity 2-10

Block I Command Module Power Profile for 14-Day Lunar Orbit Mission 2-11

Current Memory Estimates and the Status of Command Module AGC Programs 2-12

LEM Power Requirements 3-1

Estimated Weights of LEM G&N Components (lbs at 1 g) 3-3

P A G U

ABSTRACT

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

month's revision, Rev. 14, contains weight and balance data and power requirement

information for the 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 .

-~

D A T E Q

Section 1

INT RODUCT ION

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 require- ments of G&N equipment in the Command and Lunar Excursion Modules, and (3) the status of Command Module computer programs.

Weights in this report for the Command Module are based upon the current "Block I" design releases. Purely weight-saving design changes have been held, in general, for the "Block 11" release scheduled for early 1964. The Lunar Excursion Module weights are based on the best estimate of those expected for the LEM design release which will also occur early in 1964.

1-2 ACCURACY

The accuracy of numerical values reported in this revision should not be con- sidered 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.

P A G U

Y

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

Section 2

COMMAND MODULE DATA

2 - 1 WEIGHTS

Table 2-1 presents the weights of all Block I equipment? grouped according to its specific location within the Command Module. Weights are reported to the com- 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 te rms are defined by North American Aviation as follows.

Estimated weights (E) are 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) are 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 . , (El), to denote values which MIT, for various reasons, feels to be more accurate than estimated values, yet which cannot be defined as either calculated o r measured weights.

North American Aviation will provide and be responsible for coldplate weights which are not integral with guidance and navigation equipment.

2-1.1 present component weight values with those listed in System Status Report, E-1142 (Rev. 131, October 15, 1963. All weight changes are explained in paragraph 2-2. Figure 2-1 presents the chronological weight development of the Command Module G&N system.

WEIGHTS STATUS REPORTING. Table 2-1 also offers a comparison of

2-1.2 MSC weights, 1962.

SPEC. WEIGHT. The "Spec. Weight" column in table 2-1 contains "proposed that is, goals set forth by MSC in a memo to MIT dated December 5 ,

2-1.3 DESIGN LOAD WEIGHT. T-he "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&ID

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request, at NASA Coordination Meeting No. 8 , that one total weight figure for sup- ported G&N load be assigned fo r structural design use. MIT herein assigns a total G&N design load weight, in table 2-1, which does not include items termed ttloose stored items." The breakdown of this total weight into the individual items of column "d" is typical only.

2-2 REPORTED WEIGHT CHANGES

The weight changes since last month's report , E-1142 (Rev. 13), October 15, 1963, shown in table 2-1 a re explained below.

2-2.1 This increase is attributed to: (1) the PIP suspension capacitors, w i r e s , and con- nectors which weigh 0.66 pound more than estimated, (2) the blower speed control modules, not previously considered, weighing 0.170 pounds, (3) a heavier stub shaft design resulting in a 0.10-pound increase , and (4) the wire covers which weigh 0.34 pound more than previously estimated.

IMU. The 1.2-pound increase in the IMU weight is a result of weighing IMU 5.

2-2.2 G&N IND. CONT. PANEL, The weight decrease is due to the deletion of Block I1 i tems, namely, the NVE-Vernier, the NVE-level gain, and the resis tor module.

2-2.3 requirements can be met without sparing any PSA modules.

PSA LOOSE SPARES. Reliability studies at MIT/IL have indicated reliability

2-3 CENTERS OF GRAVITY

Table 2-11 presents the centers of gravity of each weight component o r pack- aged assembly, determined with respect to the basic X, Y , Z axes of the Command Module shown in figure 2-2. Center of gravity values a r e given to the nearest tenth of an inch.

2-4 MOMENTS OF INERTIA

Table 2-11 also presents the moments of 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) a r e parallel to the basic X , Y, Z axes of the Command Module.

2-5 COMMAND MODULE POWER REQUIREMENTS

The power requirements of the Command Module G&N equipment on the prima- r y + 28-VDC power supply are shown in figure 2-3, which presents the magnitude and

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DATE 11/15/63

COMMAND M O D U L E

location of dissipated power values on a subassembly level. This chart assumes a 14- day lunar orbit mission as defined by S&ID for power profile computation (Ref: S&ID letter 63 MA 7332).

Table 2-111 shows the magnitude and location of power dissipaf:ion for the es - tablished G&N activities , each of which consists of various power levels of operation.

Table 2-IV shows the energy requirements for each G&N :ictivit;y on d power level basis. The table is based upon MIT letter AG 679-6, "G&N P0wc.r Profile Status," dated August 14, 1963. The vertical column to the left indicates the various G&N activi- ties (phases of operation) for the model 14-day mission submitted by S&ID i n S&ID letter 63 MA 7332. This column also indicates the power consumptiori arid onerating 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.

+XC

-z c -zc

+YC

+ Z C +zc SIDE VIEW VIEW LOOKING FORWARD

Figure 2-2. X, Y , Z axes of Camman-d Module

COMMAND MODULE

IO W STANDBY 6LI W MISSION L k i

Figure 2-3. Electrical load on primary + 28-VDC power supply

PAGE.%

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

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~ DATE 11/15/63

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P A G E L

COMMAND M O D U L E

Program

2-6 CURRENT STATUS OF COMMAND MODULE AGC PROGRAMS

Status

Table 2-V list,s current Command Module memory es t imaks and the status of AGC programs. The status of LEM AGC programs is not reported tat, this time.

A high and low word estimate is given with each program. Each status is defined a s 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 Sbtus of Command Module AGC Programs

I List Processing Interpreter AGC Executive AGC Waitlister AGC System Exerciser, Checkout,

G&N System Exerciser & Checkout Display, Keyboard, and Telemetry hput/Output Control Midcourse and Orbital Navigation Midcourse and Orbital Guidance Prelaunch Platform Alignment In- Flight Platform Alignment Reentry Control Injection and De-Boost

and Error Handler

Totals

Memory Estimate l(wcrds)

High

1600 2 50 150

1000 1000 1500 850

2000 500 400 * 9 80 1290 1000

12520* -

Low

1600 250 150

750" 750 1500" 350 1500 500 400 * 900

10074*

:k

15, 1963. These items have changed since the last report , E-1142 (Rev. 13), dated October

P A G E 2

LUNAR

Power (watts)

EXCURSION

Time Energy (hrs) @wh)

MODULE

IMU Standby IMU Operate

AGC Operate Radar CDU Optics Display and Controls Rendezvoue Radar Landing Radar

TOTALS

AGC Standby

Section 3

84.7 348.0

10.0 115.0

18.4 Negligible

12.2 * *

493.6 (peak)

; LUNAR EXCURSION MODULE DATA /

3-1 POWER REQUIREMENTS FOR LEM

The cumen$ estimate of LEM G&N power and energy (see table 3-1) is based upon the fixed-teleecope 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, ocuuring at higher power levels during turn-on and slewing operations, are considered to consume negligible energy. When they become available dah on these peaks will be included.

Note that the total energy drawn, 21.70 kwh, is considerably higher than for a "normal" mission since the estimate provides fo r full operate power for the 18 hours of "orbit contingency" mode. Without this contingency the G&N takes about 13 kwh using the GAE C profile.

103.8 26.4 21 .3 26.4 23.8

8.78 9.19 0 .21 3.04 0.44

I 21.70

. .. P U

LUNAR EXCURSION MODULE

Separate power turn-on switches are assumed for IIIMU opemte, 'bomputer stand- by, 'komputer operate, and "radar CDU. The LEM G&N uses only the spacecraft + 28-VDC power supply except fo r operation of condition lights. The condition lights operate from the spacecraft 400-cps power supply.

3-2 WEIGHTS FOR LEM

Lunar Excursion Module weights are presented in table 3-II. In general the data conform to the information contained in paragraphs 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 space- . craft D&C. Therefore, target weights were not given by GAEC to supply the five items denoted by asterisks in column (a).

The row labeled Bare Guidance System is inserted to provide for comparisons with similarly specified systems.

3-3 REPORTED LEM WEIGHT CHANGES

The weight changes since last month's report, E-1142 (Rev. 13), October 15, 1963, are explained below.

3-3.1 IMU. For explanation of the weight increase see section 2 -2.1.

3-3.2 down of the PSA in Appendix B, System Status Report, E-1142 (Rev. 13), dated October 15, 1963.

PSA. The 0.2-pound weight decrease is a result of the itemized weight break-

DATF 11/15/63

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Section 4

GLOSSARY*

AGC: APOLLO Guidance Computer--complete computer except display and keyboard. Includes all structural mounting details,> one logic and one memory t ray, the AGC end connector assembly, and a beryllium toe plate.

AGC SPARES: Consists of a complete spare logic tray to be stored in the computer spares a rea and one spare module for each module not already spared, i . e . , a spare for each unique module to be stored as a loose spare.

BELLOWS ASSEMBLY: consisting of SXT and SCT bellows plus bellows seals.

Connection between Command Module and Optical Subsystem

COOLANT HOSES: and spacecraft, optics and spacecraft, and optics and IMU, (2) bracket assembly screws and clamp, and (3) entrapped coolant.

Consists of (1) three aluminum flex coolant hoses between IMU

CDU AND FRAME ASSEMBLY: Command Module (Block I), five interchangeable gear boxes and frame assembly used as a data interface among the optics, IMU, AGC, and spacecraft autopilot. In LEM, five electronic CDU's including mounting frame, screws, interwiring, and connectors.

Coupling Display Units and Frame Assembly--In

D & C/AGC: keyboard, control panel, relays, and support structure. One is located in lower equip- ment bay and one is located in main panel.

Display and Control, Computer--consists of letter and number readout,

D & C/NAV: Panel, IMU Control Panel, D&C Electronics, and Optical Shroud. The above includes meters , switches, lights e t c . , except as reported elsewhere. The weight does not include the clock group which i s supplied by NAA.

Display and Control Navigation--consists of G&N Indicator Control

G&N IND. CONT. PANEL: switches, indicators, and controls for navigation that a re not reported elsewhere. Includes optics hand controller, altitude impulse control, panel wiring, panel, and supporting hardware.

G&N Indicator Control Panel--consists of the necessary

* the interpretation of LEM items. As unique LEM details become better identified, descriptions will be included.

This applies specifically to Command Module, though it can provide a guide to

DATF 11/15/63 PAGEAIL

A l o ~ s ~ , , R. AprlFi.. Library (15) Bc.rttin, R. Bein, W. Bowditch, P. Boyce , A. .1- Ryizn! , L P

Copps, 5.

Dwgan, E. Dahlen, J.

Flanders, J. Felix, S. HA1, E. C. H d z c l , I. H2r!ey, D. Hickey, E.

H ~ ~ u s ~ w I , F. HlIPsh, J.

H0i.g. D.

DISTRIBUTION LIST E-1142, Rev. 14

Apollo Limited Internal

External

Deldney, Capt. W. (AFSC/MIT) Ciregorek, S. (NAA S & ID/MIT) Hcuermann , T . (GAE C/MIT) %me, W. (NASA/RASPO/MIT) Smal I . J . [GAE C/RASPO) AC Spark Plug Knl1 smdn RJy!h,F.i’n

Koso, A4. Kramer, M. Kupfes, W. Ladd, D. L,awrence, J . Lawton, T o Mayo, G. M i l l e r . J. MIT/IL Library (68 Albany St. ) Nevins, J. Nugent, J e

Olsson, E . A. Sciegienny , J. Sears, N. Trageser, M. Wilk, L. 32) Woodbury, R.

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

HDQ:

CA4E C :

NAA:

MSC:

WESCo:

AMR:

P A G U .

NASA Headquarters 1520 H Street Washington, D. C. Attn: Mr. G. M. Low, MD(P)

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