Apollo Systems Engineering Manual Service Module and Adapter Structure

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_|NASA-CR- 126236) APOLLO SYSTEMSENGINEERING NgNUAL: SE}IVICE I_ODULE AND

ADAPT_R ST_UCTUHE (North AmeEican Aviation,

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APOLLO SYSTEMS ENGINEERINGService Module and

Adapter StructureJ.',

":_,._ CONTRACT NASg-150

19'_,February1964

SID 64-206(DIM-9)

MANUAL

Exhibit I, Paragraph 5.2

NORTH AMERICAN AVIATION, INC.SPACE and INFORMATION SYSTEMS DIVISION

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NORTH AMERICAN AVIATION, INC. V°lume:DEM-9SPACE and INFORMATION SYSTEIV_ DIVISION Section:

Page: ii

Date: 2-19-64

Rev. Date:

FOREWORD

This manual is one in a series of special Apollo Engineering Manuals (Dli4'si through 18) which furnish a contemporary source of desigm and system in[orm,j-

tion_ and descriptions for the Apollo spacecraft. This manual_ DIM-9, contains

basic information, by use of text and i!lustrations_ on the components of the

service module and adapter structures.

Illustrations include: a. over-all configuration control drawings of' both

service module (S/M) and adapter; b. detail drawings of component parts;

c. installation drawings; d. interface control drawings_ when available.

The structural components of the service module and the adapter are designedto operate within desio_n limftations while subjected to environmental restric-

tions imposed by the NASA Exhibit "B" Technical Specification, Part I, dated3 January 1963.

A final manual can not be consummated at this time. Expanding, dynamic, and

involved technology of the subject matter permits the issuance only of pertinent

information on an as-known basis. When relevant data appear_ revisions will bein order.

The service module and adapter structures Manual Review Board is composed

of, but not limited to_ the following personnel:

Chairman: J.R. Cole, Chief 696-420

Service Module Design

Alternate: To be determined

Recorder: To be determined

Members: (Or their representatives)

H.S. Oder, Chief

Spacecraft Structural Analysis

696-230

J.W. Gibb, Chief

Propellant Systems

696-320

D.I. Champaign_ ChiefElectrical Power

697-810

R.E. Field, Chief

Propulsion Engines

696-310

M.E. Stelzriede, Chief

Environmental Control System

696-510

SID 64-206

I

NORTI-I AlVlERICAN AV'IATION, INC. Volume: DIM-9__

SPACE and INFORMATION SY_STEMS DIVISION S e cti on. --_

Page: iii

Date: ___

Rev. Date:

The following lead engineers can give more definite information on_ andanswers to_ technical questions in their areas of specialization:

H. W. Myers - Spacecraft LI_M Adapter

D. M. Robison - S/M Structure

E. G. Stecki - S-I Adapter; Mounting Provisions for S/M and Adapter

T. Bucuvalas - Service Propulsion System_ Main Tanks

K. C. Dullea - Mounting Provisions for Environmental Control and

Electrical Power Systems

B. F. Glienke - Mounting Provisions for Reaction Control System, Service

Propulsion and Pressurization Systems

Cole,Chie Apollo Service Module Design

SID 64-206

/NORTH AMERICAN AVIATION, INC.SPACE and INFORMATION SYSTEMS DIVISION

Volume= DIM- 9

Section:

Page: iv

Date: _-19-64

Rev. Date:

CONTENTS

Section

1.0

2.0

3.0

4.0

5.0

6.0

7.0

8.0

I_YfRODUCTION

i.i General

1.2 Reliability

SERVICE MODULE STRUCTURE

2.1 General and Configuration

2.2 Component Description and Function

2.3 Operating Conditions

2.4 Characteristics and Criteria - Component Design2.5 Test Requirements

ADAPTER STRUCTURE ......

3.1 General and Configuration

3.2 Component Description


3.4 Design Characteristics and Criteria - ComponentDesig_

3.5 Test Requirements

SERVICE PROPULSION SYSTEM - TANK STRUCTURES4.1 General

4.2 Configuration and Function


4.4 Design Characteristics and Criteria .


SYST_HS MOUNTING PROVISIONS

5.1 General

5.2 ECS Mounting Provisions Configuration

5.3 RCS Mounting Provisions Configuration

5.4 SPS Mounting Provisions Configuration

5.5 EPS Mounting Provisions Configuration

5.6 T.S. Hounting Provisions Configuration

THERMAL CONTROL STRUCTURES

6.1 Aft Heat Shield

6.2 Service Module Insulation

SIGNIFICANT INTERFACES

7.1 General

7.2 External Interfaces

7.3 Internal Interfaces


REFERENCES

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S!D 64-206

NORTH AM.FRICAN AVIATION, INC.SPACE and INFORMATION SYSTEMS DIVISION

Volume: DIM-9

Section:

Page: v

Date: 2-!9-64

Rev. Date:

Figure

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ILLUSTRATIONS

Servlce Module Nomenclature (V17-933200)

Servmce Module: General Assembly (V17-000002) .

Service Module: Structural Assembly (V17-320001-I)

Servmce Module: Structural Assembly (V17-320001-2)

Servlce Module: Structural Assembly (V17-320001-3)

Service Module: Structural Assembly (V17-320001-4)



Complete Interior Arrangement of Service Module (V17-935561-I)

Complete Interior Arrangement of Service Module (V17-935561-2)

Installation of Forward Bulkhead (V17-320101) • •

Assembly of Aft Bulkhead, Station X S 200 (V17-320201-I)

Assembly of Aft Bulkhead, Station X S 200 (V17-320201-2)

Assembly of Aft Bulkhead, Station X S 200 (V17-320201-3)

Assembly of Aft Bulkhead, Station X S 200 (V17-320201-4)Assembly of Radial Beam 2 (V17-322001)

Adapter - GeneralAssembly (VI$-000002).Design Study - Configuration - S-IV B Adapter (V2¼-932002)

Manufacturing Assembly Breakdown of S-I Adapter (SK-015129)

Skin Panel Splice for Adapter Plate (1718-300011) .

Installation of Main Propellant Tank, Service Module

(VI7- 340001 )

Tank Assembly Complete: Main Propellant, Oxidizer

(V17-342001)

Tank Assembly Complete: Main Propellant, Fuel (V17-34;001)

Tank Assembly: Main Propellant, Oxidizer (V17-342002)

Tank Assembly: Main Propellant, Fuel (V17-343002)

Tank Assembly: Main Propellant, Helium (V17-347002) 4.02 _Assembly of Upper Skirt Support, Oxidizer Tank _V17-3 2 P)i

Mounting Provisions, Environmental Control System

Installations (V17-331717-I)


Installations (V17-331717-2)


Installations(V!7-3317!7-3) . • .Assembly of Oxyoen Tank Shelf Support (V17-331667) • •

Module Installation of Reaction Control System (V17-332000).

Panel Assembly Complete, Reaction Control System (V17-332001-I)

Panel Assembly Complete, Reaction Control System (V17-332001-2)

Panel Assembly, Reaction Control System (V17-332002-I)

Panel Assembly, Reaction Control System (V17-332002-2)

Housing Assembly, Reaction Control System (V17-332010)

Longitudinal Heat Shield Installation, Reaction Control

System (V17-331525)

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SID 64-206

e NORTH AMERICAN AVIATION, INC,SPACE and INFORMATION SYSTEMS DIVISION

Volume: DIH- 9

Section:

Page: vi

Date: 2-19-64

Rev. Date:

Figure

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Lateral Heat Shield Installation, Reaction Control System

(v17-3316N)

Insulation Installation for Reaction Control System

(V17-332046)

End Mounting Assembly of Propellant Tanks_ Reaction Control

System (V17-332041)

Mounting Assembly, Propellant and Pressure Tanks_ ReactionControl System (V17-332042)

Installation of Engine Mount_ Service Propulsion System

(V!7-327!01-I) .

Installation of Engine Mount, Service Propulsion System(V17-327101-2) .

Mounting Provisions Installation, Service Propulsion System

(V17-331000)

Mounting Provisions Installation, Service Propulsion

Pressurization System (V17-331100).

Mounting Provisions, Electrical Power System (V17-331552-!)

Mounting Provisions, Electrical Power System (V!7-331552-2)

Installation of Fuel-Cell Mounting, Stabilized Shear Web

(V17-331524) .Assembly of Support Shelf_ Upper Hydrogen Tank "(V17-331566)

Control Layout - Electrical Power System Radiators_ SectorsOne and Four (V17-933074)

Installation Provisions_ Fluid Lines Suppoz_t, Electrical

Power System (V17-331553-i)

Installation Provisions_ Fluid Lines Support_ Electrical

Power System (V17-331553-2)

Installation Provisions_ Fluid Lines Support, Electrical

Power System (V!7-331553-3)

Outer Shell Assemb!y_ Aft Heat Shield_ Sectors Three_ Four_

and Five (V17-331944) •

Inner Shell Assembly, Aft Heat Shield, Sectors Three_ Four,

and Five (V17-331700)

Installation of Aft Heat Shield_ Station X S 200

(V17-331689-I)

Installation of Aft Heat Shie!d_ Station XS 200

(vr(-331689-2) .

Insulation Installation Provisions_ Service Module

(V17-331562-I)

Insulation Installation Provisions_ Service Module

(V17-331562-2) • •

Complete Assembly of Thermal Simulator for Specimen Test

(DTT-6600) - -

Installation of Fairing V17-310001-I)

Installation of Fairing V17-310001-2)

Fairing Panel Assembly_ Service Module to Command Module

(WT-311ool).

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SiD 64-206

NORTH 'AMERICAN AVIATION, INC.SPACE and INFOR_ATION SYSTEMS DIVISION

Volume:_

Section:

Page: vii

Date: 2-19-64

Rev. Date:

Figure

7-4

7-5

7-6

7-7

Fairing Assembly Complete_ Command Module to Service Module

Umbilical (V17-331771)

Assembly of Support - Command Module to Service Module and

Fly Away Umbilical (V17-331913)

Strap-Tension Tie_ Service Module to Adapter (V18-300005)

Control Layout for Servicing and Umbilical Locations

(V17-933401)

Page

7-5

7-6

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SID 64-206


Volume: DIM-9

Section: _2L__

Page: i

Date: 2-19-64

Rev. Date:

1.0

i.i

i.i.i

I.i.2

1.1.3

1.2

1.2.1

INTRODUCTION

General

The Apollo service module is pictured in the layout V17-933200,

"Service Module Nomenclature 'f (Figure i-i). This layout provides

names and basic details of the S/M_ the fairing_ and the adapter.

Drawing V17-000002 (Figure 1-2) is a perspective of the S/M

general assembly.

This design information manual (D_) presents the structure of

the S/M, the adapters, the tanks of the service propulsion system

(SPS), the mounting provisions of the S/M systems, the signifi-cant interfaces.

The systems of the S/M for which mounting provisions must be

designed are: the SPS, including the S/M aft heat shield; the

reaction control system (RCS) plus its heat shields; the environ-

mental control system (ECS); the electrical power system (EPS);the telecommunication system (T.S.); and the internal insulation

system (I!S).

Reliability

Information furnished by the Reliability Engineering Group for

this manual is classified, but DIM-9 is unclassified. Hence,

reliability information_ advice, or completed studies may be

obtained by contacting Department 643-50.

SID 64-206


Volume: DIM-9

Section: 2

Page: ]

Date: 2-19-64

Rev. Date:

2.0

2.1

2.1.!

2.1.2

2.1.3

2.1.4

2.1.5

2.2

2.2.1

2.2.2

SERVICE MODULE STRUCTURE

General and Configuration

The service module structure consists of the outer shell_ radial

beams_ forward and aft bulkheads, and inner web. (See 7.2.1 for

analysis of the fairing.) Drawing V17-320001 (Figures 2-1

through 2-6) depicts the structural assembly of the S/M.

The definition of the present S/M configuration required studies

in space allotment for its systems and equipment. Design

criteria were the factors of access_ removal_ and servicing.

Both structural design and choice of materials were based on the

exigencies of space environment.

The S,/M is 155 inches long and 154 inches in diameter. The outer

shell is made of one-inch aluminum honeycomb sandwich; the radial

beams of aluminum plate are made by numerically controlled

machining_ followed by chem-milling; forward and aft bulkheads

are fabricated from aluminum honeycomb; and the inner web ismade of aluminum sheet.

The six radial beams divide the interior of the S/M into three

pairs of diametrically opposed sectors which are unevenly sized.

Desigm layout V17-93556! (Figures 2-7 through 2-8) illustrates

the complete interior arrangement of the S/M. A center section

which is 44 inches in diameter extends the length of the S/M.

The function of the S/M is threefold: a) support of the main

engine of the SPS; b) housing of the SPS propellant tanks;

c) housing of all other systems not contained in the command

module (C/M) but required for the spacecraft (S/C) mission.

Component Description and Function

The outer shell of the S/M is formed by bonded one-inch aluminum

honeycomb sandwich panels. This material was chosen for fabri-

cation of the outer shell because it provides the greatest amotunt

of strength and rigidity for the least amount of weight. In

addition_ its simplified structure reduces the number of parts

needed_ handling_ and inspection. Also_ reliability is increased..

The outer shell of the S/M contains the space radiators (ECS

and EPS) which form an integral part of the outer face sheets of

the aluminum honeycomb sandwich panels. It also supports the four

RCS modmles. It distributes the C/H and S/M equipment loadings

from the radial beams into the S/C booster. In addition_ it resists

aerodynamic pressures_ provides a clean aerodynamic shape_ and

protects the S/M interior from external environment.

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Volume: DIM-9_

Section: 2

Page: 9 ,_Date: 2-!9-64

Rev. Date:

SID 64-206

e NORTH AMERICAN AVIATION, INC.SPACE and INFORMATION SYSTEMS DIVISION

Volume: DIM-9

Section: 2

Page: !0

Date: 2-19-64

Rev. Date:

2.2.3

2.2.4

2.2.5

2.2.6

2.2.7

2.2.8

Panels which form the center shell or web are made of aluminum

sheet 0.016 inch in thickness. The web structures are found only

along the center lengths of Sectors 0ne_ Four_ Six and Three.(See dra_ngs ..... F, -_'Ii-_3;;om, Figures 2-7 through x-o, and Vi7-320001,

Figures 2-1 through 2-6. )

The function of the center webs is twofold: a) to aid as stabili-

zers for the six radial beams; b) to distribute the weight of the

helium bottles and the engine mou_ts which are located in Sectors

One_ Four, Six and Three.

The aft bulkhead is made of bonded aluminum honeycomb sandwich

three inches thick and 154 inches in diameter. The center open-

ing coincides with the inner caps of the vertical beams and is44 inches in diameter. The forward bulkhead is made of the same

type of material_ has the same size of center opening_ but is only

one inch thick. See drawing V17-320101 (Figure 2-9) for the for-

ward bulkhead_ and drawing V!7-320201 (Figures 2-10 through 2-13)

for the aft buli_head.

Both bulkheads distribute the radial beams' loading into the outer

shell. The aft bulkhead per se acts as support structure for the

SPS main tanks_ the SPS engine and gimbal mount_ the radial beams_

the EPS fuel cel!s_ the cryogenic hydrogen tank_ the aft heat

shield_ the high-gain antenna_ hard lines_ electrical wiring_ etc.The aft bulkhead also serves as a heat barrier between the SPS

engine and the S/M interior. The forward bulkhead provides

lateral support for the upper ends of the SPS main tanks.

All radial beams have similar configurations. Each beam is a

rectangular structure machined and chem-milled from 2.5-inch

aluminum-plate stock. Each has a minimum web .0iS-inch thick

and stiffeners .06-inch thick. The vertical distances between

stiffeners vary between 6 and 19 inches. For a typical beam con-

figuration_ see drawing V17-320001_ "Assembly of Radial Beam 2"

(Figure 2-14).

Criteria which governed the choice of radial besom configuration

were: a) the length of the main SPS tanks in their final con-

figuration; b) accessibility to these tanks; c) weight and fabri-

cation savings through the use of numerically controlled machining

and chem-milling instead of the use of more conventional methods

including welding of structures.

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Figure 2-9. Installation of Forward Bulkhead (V17-320101)

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Volume: DIM-9

Section: 2

Page: 16

Date: 2-19-64

Rev. Date:

®

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Fig-4re _-_. Assembly of Radial Bes_ 2 t v±7-jssOu±)

SID 64-206


Volume: D]2vb 9

Section: 2

Page: 17 _

Date: 2-19-64

Rev. Date:

2.2.9

2.3.2

2.4.2

2.5

2.5.1

Functions of the radial beams are five: a) supporting structures

for the C/M; b) transfer fraznes for propellant loads from the aft

bu]_khead to the S/M shell; c) transfer framework for SPS loads

to the S/M and C/M; d) support structhres for aumi!iary equipment

pertaining to S/M systems; e) adjuncts to the outer shell for the

distribution of pressure loads.

O_eratin_ Conditions

In normal launch mission> the S/M with all its systems_ including

the SPS and RCS engines_ will successfully perform all of the

maneuvers required of the spacecraft (S/C) between lift-off and

reentry. Among these maneuvers are the following: earth orbit

with in-flight and ground-directed checks; injection into lunar

trajectory; transpositional docking with LEM; mid-course correc-

tion; translunar flight; f'free-turn _'trajectory; lunar orbit;

transpositional docking; and earth trajectory.

In a normal launch abort mission the S/H will use either or both

of its propulsion systems in operations designed to successfully

keep the S/C within orbit_ or return it to the earth.

Characteristics and Criteria - Component Design

The S/H outer shell_ fairing_ and radial beam structures will

withstand the aerodynamic heating during boost. The internal

structure of the S/M is designed for a temperature range between

-200 and +300 F_ although temperature and load conditions are

not always concurrent. The S/M structure is designed to withstand

hazards imposed by the environment as described by the environ-

mental requirements listed in the NASA Exhibit B. Technical

Specification_ Part !> dated 3 January 1963. These requirements

include resistance to the following: a) acoustics_ vibration_

and flight loads; b) extremes of humidity and temperature;

c) high a!titudes_ ground handling, and transportation; d) salt-

in-air_ ground winds> storm conditions_ meteoritic storms_ andradiation.

Other and more technical criteria which have been used to fix the

design of the S/H components are found in the.Apollo Requirements

Manual (ARM) -6_ "Structural Loads and Criteria."

Test Requirements

Test requirements for the S,/M outer shell_ fairing_ radial beams_

and other internal sti_uctural components including mounting-

provisions structures are specifically called out in SID 62-109-2,

"General Test Plan_ Research and Development for Project Apollo

Spacecraft - Individual System Test."

SID 64-206


Volume: DIM-9

Section: 2

Page: 18

Date: 2-!9-64

Rev. Date:

2.5.2

2.5.3

2.5.4

2.5.5

Tests which have been completed and for which Apollo Test Reports

(ATR's) have been released are listed here:

ATR NO. NAME OF TEST

301-7

301-9

301-IO

301-12

301-14

301-17

303(213)

3o4

3o4-t

Joint - S/M to Adapter

Circumferential Edge Member

Longitudinal Edge Member

Structural Component Test - S/M

Outer Shell Pane!_ Blind RivetJoint Tests

Structural Component Test -

Aluminum Honeycomb Sandwich

S/M Honeycomb Attac_hment Test

S/MMeteroid Shielding

S/M Aft Bulkhead Structural

Components Test

S/M Aft Bulkhead Structural

Components Test_ Bulkhead Spliceand Shear Panel Tie

Tests which have been completed but for which no reports have

been written are these:


301-i

301-3

301-5

S/M - Outer Shell Panel Test

S/M Simulated Aft Bulkhead Test

S/M Radial Shear Web Test

Scheduled tests as yet uncompleted are these:


3OO

301-6

304-2

S/M with Adapter Static Test

Fittings - C/H Support

Aft Bu_head Component Test - S/M

ATR 600_ Combined Module Static Structural Test_ has not been

l%_q.

S!D 64-206


Volume: DZM-9

Section: 3

Page: ]

Date: 2-1q-64

Rev Date:

3.0

3-i

3.1.1

3.1.2

3.1.3

3.1.4

3.2

3.2.1

3.2.2

3.2.3

ADAPTER STRUCTURE

General and Configuration

Two S_ adapter structures are in preparation: the S-1 adapter

and the S-5 or S/C L_ adapter. Drawing V18-000002, "Adapter

General Assembly" (Figure 3-i) shows the S-I configuration.

Drawing V24-932002 (Figure 3-2) pictures a design proposed for

the S-5 adapter.

Each adapter is a connecting structure between the S/M and the

instrument package. Each serves as an enclosure for the lower

portion of the main SPS engine and its attached cone_ the aft

heat shield below Station X S 200_ and the high-gain antenna in

stowed position. Each adapter is made of aluminum honeycomb

panels spliced together with pairs of longitudinal splice plates

of aluminum. Each adapter structure is equipped with shaped-

charge explosives for separation.

The S-I adapter is a cylindrical structure formed of four equally

sized rectangular panels which have a uniform thickness of two

inches. Location of the S-I adapter is between Stations X D 200and XD 084. Drawing SK-015129 (Figure 3-3) is the manufacturing

assembly breakdown for this adapter.

The S-5 adapter is a truncated conic structure with a conic angle

of approximately nine degrees. Its panels vary in thickness.

In addition to enclosing the same kinds of items mentioned in

3.1.2_ the S-5 houses and supports the lunar excursion module

(L_).

Component Description

The panels of both S-I and S-5 adapters are made of bonded alu-

minum honeycomb. This material was chosen for the same reasons

as those given in 2.2.1.

Four pairs of longitudinal splice plates made of sheet aluminum

O.06-inch thick are used to bind the panels of the S-I adapter

together. Drawing V18-300011, "Skin Panel Splice for Adapter

Plate" (Figure 3-4)_ displays details of the splice-plate config-uration.

The function of the shell structure as formed by the use of the

splice plates in both the S-I and S-5 adapters is as follows:

SID 64-206

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Rev. Date:

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sip 64-2o6


Volume: DIM- 9___

Section: 3

Page: 6 ,,.

Date: 9_19_64

Rev. Date:

3.2.4

3.3

3.3.1

3.3.2

3.3.3

D

3.4.2

3.5.2

a) to protect the equipment noted in 3.1.2 and 3.1.4 from the

effects of environmental forces; b) to distribute the body loads

in both C/M and S/H; c) to distribute the S/C loading to thebooster.

The support structure for the LEM is also one component of the

S-5 adapter, but the present configuration is still in the

design stage.

Operating Conditions

In normal launch and abort missions_ the S-! adapter structure

will function until the adapter panels are separated from the

S/C by explosive charges %o allow SPS-engine operation.

In normal launch and abort of the spacecraft LEM adapter_ only

the portion above the LEM attach points is separated by

explosive charges into four hinged panels. The latter open

out to permit the removal of the LEMwhich withdraws from thebooster and leaves it behind.

No detrimental dynamic pressures nor structural shrapnel will

be permitted to strike the aft face at Station XS 200 or any

equipment within the confines of the adapters.

Design Characteristics and Criteria - Component Design

Criteria used to complete the design of the adapter componentsare found in the ARM-6.

Environmental requirements for the adapters are identical to

those for the S/M structure. Details are given in 2.4.1.

Test Requirements

Test requirements for the S-I adapter components are specifically

stated in SiD 62-I09-2_ "General Test P!an_ Research and

Dpv_Tnpm_ f_ Project Apollo _....... _ _....................... y__ _ - _n_zvz_ua± SystemTest."

Tests completed and covered by released ATR's are these:

ATR NO. N_ME OF TEST

301-7401-i

401-2

Joint - S/H to Adapter

Circumferential Shear and

Tension Splice

Longitudinal Panel Splice

SID 64-206

NORTH AMERICAN AVIATION, INC.SPACE and INFOR_IATION SYSTEMS DIVISION

Volume: DIM-9

Section: 3

Page: 7 ..

Date: 2-19-64

Rev. Date:

3.5.3

3.5.4

The following tests have been scheduled but have not beem

complet ed :


400

401

Spacecraft Adapter Static Test

Adapter Structural Test

Those who are not on the ATR distribution list and who have need

to know the content of the reports listed above are asked to

contact the responsible coordinator.

SID 64-206


Volume: D!M-9

Section: 4

P_g e: i

Date: ___4

Rev. Date:

D

J

4.0

4.1

4.1.1

4.1.2

4.1.3

4.1.4

4.2.2

4.2.3

4.2.4

SERVICE PROPULSION SYSTEM - TANK STRUCTURES

General

There are six SPS tanks (two each of three types). They are

designed for storage of fuel_ oxidizer_ and pressurant. The

fuel and oxidizer tanks are domed cylinders; the pressurant tanks

are spheres. An over-all view of these tanks is found in drawing

V!7-340001 (Figure 4-1).

The SPS tamks are the only major subcontracted items. Allison_

!nd is_apo!is_ Indiana is fabricating the fuel and oxidizer tanks.

Airite_ Los Amgeles_ California is m_king the pressurant tanks.

All three pairs of tanks are constructed of titanium, alloy

(6AI-4V). NAA drawings (See 4.2.1 and 2 below) are used to

coordinate and control fabrication processes.

Actual installation of these tamks in the S/M will be governed by

Process Specification MA 0310-0007, dated 4 March 1963_ and

entitled "Fitting and Installation of Apollo SPS Tanks."

Configuration and Function

Drawing V17-342001 (Figure 4-2) describes the main oxidizer tank

assembly, including the door. Drawing V17-343001 (Figure 4-3)

does the same thing for the main fuel tank and its door. Drawings

V17-342002 (Figure 4-4) and V!7-34_002 (Figure 4-5_ depict details

for fabrication of the oxidizer and fuel tanks, respectively.

In the latter two drawings the door is not included.

Dra_ng V17-347002 (Figure 4-6) sets forth fabrication details for

the main pressurant tanks.

These six ta__ks of the SPS f1_ction as the storage and provision

vessels for the fuel and oxidizing agent which under pressuriza-

tion feed the main SPS engine.

The approximate outside diameter of each fuel tank is 45 inches;

of each oxidizer tamk_ 51 inches. The lengths of these two tanks

vary between 166 and 165 inches. The diametric difference between

them_ coupled with their almost equal length_ make for dissimilar-

ity in both weight and volumetric capacity. If one omits the

weight of the tank doors and the internal structures, then the

weight of the fuel tank is 230 pounds and of the oxidizer tank,

290 pounds. The volumetric capacity of the fuel tank is 140

cubic feet and Of the oxidizer tank_ 175 cubic feet.

SiD 64-206

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Figure 4-5. Tank Assembly: Main Propellant_ Fuel (V17-343002)

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s_D 64-2o6


Volume: D]_4- 9

Section: 4

Page:

Date: 2-19-64

Rev. Date:

4.2.5

4.2.6

4.3.2

4.4.2

4.5.2

The weight and volume capacity of each pressurant tank are 390

pounds and 19 cubic feet, respectively. The outside diameterof each is about 41 inches.

Drawing V17-342025, "Assembly of Upper Skirt Support, Oxidizer

Tank"_igure 4-7), presents typical support details of these

large oxidizer and fuel tanks at the forward bulkhead. Support

details for these same tanks at the aft bulkhead are found in

Figures 2-10 through 2-13.

Operatin_ Conditions

In a normal launch mission, the SPS tanks will store (without

loss of contents) and supply under pressure the necessary fuel

and oxidizing agent to the SPS engine for all maneuvers between

transpositional docking and earth trajectory. A temperaturerange of 40-80 F will be maintained.

In a launch abort mission, the SPS tanks will provide sufficient

fuel and oxidizer under necessary pressure to enable SPS engine

operation for bringing the C/M successfully into earth reentry.

Design Characteristics and Criteria

Criteria useful in design of SPS components of tank structures

may be found in ARM-6.

The environmental requirements listed for the S/M in 2.4.1 are

equally valid for the SPS tank structures.

Test Rezuirements

Test requirements for the SPS tank structures are stated in

SID 62-109-2, "General Test Plan, Research and Development for

Project Apollo Spacecraft - Individual System Test."

Tests already completed and covered by released ATR's are these:


301-4

301-8

301-13

302-1

3o5

Static Test of Tank Skirt

SPS Main Propellant Tank Cover Door

Seal Test - S/M, Main PropellantManhole Door

Pressure Vessel Tests - S/M

Pressurant and Propellant Tanks

S/M Fuel and Oxidizer Tank

Fastener Tests

SID 64-206

41

_cr A-AI_


Volume: DIM-9

Section: 4

Page: 9

Date: 2-19-64

Rev. Date:

_*OPED IKT_/Nf I_r CODIN6_ _asr*c_ r-H._

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SID 64-206


Volume: DIM-9

Section: 4

Page: i0

Date: __79_64

IRev. Date:

4.5.3 Particular fabrication test requirements for the subcontractors

of the SPS tanks are called out in SID 62-1259 (reissued 12

February 1963), "Statement of Work for Testing of Pressurant

and Propellant Tanks_ Project Apollo."

SiD 64.-206


Volume: DIM-9

Section: 5

Page: i

Date: ___Rev. Date:

5.0

5.1

5.1.i

5.1.2

5.1.3

5.2.2

5.2.3

5.2.4

SYSTEMS MOUNTING PROVISIONS

General

Mounting provisions (or support structures) are a requirement for

the following systems:

a. Environmental control system

b. Reaction control system

c. Service propulsion system

d. Electrical power system

e. Telecommunication system

The subject matter of this section of DIM- 9 is confined to con-

figuration details supported by drawings.

The function of systems-support structures is self-explanatory.Any variables in the treatment of the environmental requirements

other than those found in 2.4.1 will be stated. Again, operating

conditions for these mounting provisions differ in no way from

the conditions imposed on the structures supported by them. Like-

wise, design characteristics and criteria for component configura-

tion are also given in ARM-6. Finally_ only one test requirement

exists for the testing of systems-mounting provisions. It is

ATR 301-i1, "Fittings and Equipment Support," and it is yet

unwritten, pending completion o£ test.

ECS Mounting Provisions Configuration

Drawing V17-331717, "Mounting Provisions, Environmental Control

Systems Installations" (Figures 5-i through 5-3) shows configura-

tion details for supporting structures of this system.

Particular details concerning the L02 supercritical storage bot-

tles are found in drawing V!7-33!667, "Assembly of Oxygen Tank

Shelf Support" (Figure 5-4).

which special support structures need design. The drawings forthese are in preparation.

Valving and hard line supports in the ECS are mounted by means of

brackets, often of special design.

RCS Mounting Provisions Configuration

Drawing V!7-332000, "Module Installation of Reaction Control

System" (Figure 5-5), and drawing V17-332001_ "Panel Assembly

S!D 64-206

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Volume: DiM-ip__

Section: 5

Page: 3

Date: 2-19-64

Rev. Date:

_VSK_S

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Date: 2-19-64

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FOR L/M,G/N¢ _ SEESHt

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F_ oU .... Assembly _+_ n...... Tank _=_o

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SID 64-206


Volume: D!M-9 ._

Section: 5

Page: 7

Date: 2-19-64

Rev. Date:

5.3.2

5.3.3

5.3.4

5.3.5

5.3.6

5.3.7

5.4

5.4.1

5.4.3

Complete Reaction Control System" (Figures 5-6 through 5-7) show

the over-all configuration o£ the RCS mounting provisions.

Drawing _±7-332002 (Figures 5-8 through 5-9) gives details of the

panel per se.

The housing assembly of the RCS is shown in drawing V!7-332010

(Figure 5-10). Brackets are used for mounting the assembly.

The engines of the RCS are supported on panels which form part

of the outer shell of the S/H. Hinges, attached by screws to

the shell, allow the RCS panels to be swung out for access or

replacement.

Heat shields which protect the outer shell of the S/H from RCS-

engine-flame impingement are shown, with their mountings, in

two drawings: V17-331525 (Figure 5-11) for the longitudinal

installation, and V17-331611 (Figure 5-12) for the lateral

installation. The insulation for the RCS panels is depicted in

drawing V!7-332046 (Figure 5-13).

The RCS engine installation requires a cluster of three tanks in

each of its four locations. The complete assembly of the fuel,

oxidizer, and pressurant tanks which are mounted as a cluster is

exhibited in drawings V!7-332041 (Figure 5-14) and V17-332042

(Figure 5-15).

Mounting of valves for the RCS is done by brackets and a panel.

Mounting of the RCS control unit has not been designed yet.

SPS Mountin_ Provisions Configuration

Drawing V17-327101, "Installation of Engine Mount, Service

Propulsion System" (Figures 5-16 through 5-17), breaks down the

mounting provisions for the SPS main engine.

A propellant distribution system of valving, hard lines; and

electrical harnesses carry fuel and electricity to the SPS main

engine. Drawing V!7-33!000 (Figure 5-18) depicts mounting pro-

visions for this distribution system.

Support provisions for the pressurization system which assures aconstant flow of fuel and oxidizer to the main engine are shown

in drawing V17-331!00 (Figure 5-19). Included in these pro-

visions are a control panel, line supports, and mounting brackets.

Drawings V!7-33!I01 and V17-331102 which exhibit supports for

the panel assembly of the pressurization-system module are not

available and therefore not included.

SID 64-206

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Date: 2-19 .64

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Volume: D!M-9

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Page: 19

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Figure 5-18. Mounting Provisions installation_

Service Propulsion System (V17-331000)

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Volume: DIM- 91

Section: 5

Page: 22

Date: 2-19-64

Rev. Date:

5.5.2

5.5.3

5.5.4

5.5.5

5.5.6

5.6.2

EPS Mountin_ Provisions Configuration

The over-all view of the EPS mounting provisions for the instal-

lation of the fuel cells and related equipment is the purpose of

drawing V17-331552 (Figures 5-20 through 5-21). Sheet one of

this drawing is a perspective of the installation. The fuel cell

itself is mounted by means of a stabilized shear web as seen in

drawing V17-331524 (Figure 5-22).

Both the LH 2 and L02 bottles in Sector One serve the EPS. The

manner of mounting the L02 bottles is stated in 5.2.2. Hounting

of the upper LH2 tank is shown in drawing V17-331566 (Figure

5-23). See Figures 2-10 through 2-13 for provisions made for

the lower LH 2 tank.

Proposed mounting of the space radiators of the EPS is depicted

in layout V17-933074 (Figure 5-24).

Hard lines and valves which supply liquid oxygen and liquid

hydrogen to the fuel cells are mounted in Sector Four as illus-

trated by drawing V!7-331553 (Figures 5-25 through 5-27).

Supports for other lines which supply glycol fill to the EPS

radiators include blocks, line mountings, saddle clamps, and

clips.

EPS control is accomplished by an electric power box mounted

by a bracket.

Wire harness for the EPS is supported by channel blocks, clips,

angles, and brackets.

T.S. Hountin_ Provisions Configuration

A drawing of the installation provisions for the telecommunica-

tion system is unobtainable at this time.

Hountings for the wire harness and wave guide of this system_ _l_ to thos_ noted in 5.5.6.

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REVISIONS

Figure _<-on=_. Mounting Provisions_

Electrical Power System (V17-33!552-I)

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Figure 5-24.

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Control Layout - Electrical Power System Hadiator_

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Electrical Power System (V!7-33!553-3)


Volume: DIM-9 _

Section: 6

Page: i

Date: 2-19-64

Rev. Date:

6.0

6.1

6.i.i

6.1.2

6.1.3

6.1.4

6.1.5

6.1.6

6.1.7

THERMAL CONTROL STRUCTURES

Aft Heat Shield

There are two means of thermal control of the S/H structures:

a) the aft heat shield below the aft bulkhead at Station KS

200; and b) the service module insulation. (Note: Insulation

of the RCS heat shields is mentioned in 5.3.4.)

The aft heat shield is fabricated from nickel_ Fiberglas_ quartzfiber_ and aluminized Hylar. Nickel 0.005 to O.!5-inch thickforms the outer shell. Drawing V$,7-331944 (Figure 6-1) depictsthe outer shell assembly [typical) for Sectors Three, Four andFive. Fiberglas which varies in thickness between 0.03 and 0.06

inch makes up the inner shell as illustrated for Sectors Three,Four, and Five in drawing V17-331700 (Figure 6-2). Quartz fiberl.O-inch thick is used as an interlining between the outer andinner shells, while aluminized Mylar about 0.25-inch thick on theinboard side of the inner shell supplies the last layer of theaft heat shield. Differential pressure between the S/M and the

adapter during prelaunch GN2 purge and boost blow-down isrelieved by five valves _laced in the outer shell of the aft heatshield. Drawing V17-331889 (Figures 6-3 through 6-4) showsinstallation details for the heat shield.

The aft heat shield and the flexible boot protect the main SPS

tanks_ propellant distribution systems, and electrical wiring

from SPS engine heating.

Criteria which influenced the configuration of the aft heat

shield were these: a) provision of sufficient clearance space

for fuel lines, valves_ tanks, engine gimbal, and high-gain

antenna below the aft bulkhead; b) provision of an interface

between the engine and the fuel tanks; c) choice of materials

for weight and the best thermal protection.

On either the normal launch mission or the normal launch abort

mission the aft heat shield will fully protect the SPS tanks,

valving, and distribution lines from engine radiation tempera-tures in excess of 2000 F.

Other and more technical criteria which have been used to set

the design of the aft heat shield are found in the ARM-6.

No tests are planned for the aft heat shield, hence there are no

test requirements.

Service Hodule Insulation

Crinkled, aluminized Hylar is the insulation material used in allsectors of the service module and in the space between the

service module and the command module. One-half inch of space

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Figure 6-2.Sectors

inmer Shell Assembly, Aft Heat Shield,

Three, Four, and Five (V!7-33!700)

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Volume: DIM-9

Section: 6

Page: 4

Date. 2-19-64

Rev. Date:

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Station XS 200 (V17-331689-I)

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Station X S 200 (V17-331689-2)

Volume: DIM-9

Section: 6

Page:

Date: 2-19-64

Rev. Date:

smD 54-_o6


Volume: DIM-9

Section: 6

Page:

Date: 2-iO-64

Rev. Date:

6.2.2

6.2.3

6.2.4

6.2.5

has been allotted for insulation, even though the total thick-

ness of the Mylar layers uncompressed will be only 0.25 inch.

Installation accessories are hollow aluminum rods, nylon buttons,

cords, and thread; spring clamps; and reflecting pressure-

sensitive tape. Drawing V17-331562 (Figures 6-5 through 6-6)

shows the perspective of the insulation-installation provisions.

The function of this insulation system is to supplement the aft

heat shield in the dissipation of heat from any source and to

keep the SPS tanks, propellants, and other equipment at an even,

nondestructive, proper, operative temperature. The insulation

system also prevents loss of heat in the cold environment of

space.

Criteria which governed the choice of aluminized Mylar (NRC-2)

as insulation material are these: a) it is the best reported

insulation value per pound; b) it has the ability to withstand

high compression of large g loads while maintaining initial

insulation effectiveness; c) its low bulk density is needed to

achieve thermal equilibrium with a minimum loss of cryogenic

fluids; d) by its use a high vacuum can be obtained; e) it is

easy to apply to complex shapes; f) a minimum effect is obtained

from thermal short circuiting.

During the normal launch mission or the normal launch abort

mission the thermal insulation system will protect the SPS tanks

and internal equipment of the S/M from environmental temperature

extremes generated externally. The insulation will maintain

the temperature range of 80 through 40 F for the propellant dur-

ing the mission.

Test requirements for the thermal insulation system are stated

in SID 62-109-2, "General Test Plan, Research and Development

for Project Apollo Spacecraft, Individual System Test." ATR

306, "Thermodynamic Analysis of the Typically Insulated S/M

Propellant Sextant," has not been completed since the test has

not been run. However, design work has begun on the thermal

simulator - test specimen. Drawing DTT-6600 (Figure 6-7) gives

details ol _ae SPS tank-insulation assembly. If additional

information is desired, contact can be made with Department696-210.

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Volume: D!M-9

Section: 6

Page: 7

Date: 2-19-64-

Rev. Date:

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Volume: DIM-9__

Section: 6

Page: 8

Date: P-39-6_

Rev. Date:

SID 64-206

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% NORTH AMERICAN AVIATION, INC.SPACE and INFORMATION SYSTEMS DIVISION

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Volume: DTM-9

Section: 6

Page: 9

Date: 2-19-64.

Rev. Date:

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Figure 6-7. Complete Assembly o£ Thermal Simulator for Specimen Test(DTT-6600)

SID 64-206


Volume: DIM- 9__

Section: 7

Page: !

Date: 2-19-64

Rev. Date:

7.0

7.1

7.1.1

7.1.2

7.1.3

7.1.4

7.2.2

7.2.3

SIGNIFICANT INTERFACES

General

By the term "interface" is meant the common boundary between

two or more systems or subsystems. At their points of contact_

matching or accommodation must be properly achieved to assure

compatibility and successful functioning.

Significant interfaces are divided into two categories: a)

those which are external, affecting structures; b) those which

are internal, affecting such things as mechanics, hydrau!ics_

pyrotechnics, and things electrical.

Some of the external interfaces are in the study stage. As the

studies crystallize into designs, the resultant drawings willbe added to later editions of this manual.

All of the systems-mounting provisions are really interfaces.

However_ these provisions are separately treated under heading5.0.

External Interfaces

The fairing_ an important part of the S/C is one of the chief

aerodynamic interfaces between the S/M and the C/M. It is made

of six equally sized panels fabricated from bonded aluminum-

honeycomb sandwich one-inch thick. Installation drawing

V!7-3!0001 (Figures 7-1 through 7-2) and panel assembly drawing

V17-3!!001 (Figure 7-3) depict the fairing interface. The

function of the fairing is twofold: a) to shield from atmos-

pheric pressure certain equipment essential to the smooth

functioning of the S/M and C/M; b) to prevent rapid evacuation

of air from the S/M interior.

The C/M to S/Mumbi!ical with its own fairing is the second

vital interface. This fairing is located in Sector One on the

outer shell of the S/M - C/M f_i_g. D_T_ V17-_q1771

(Figure 7-4) shows configuration details of the fairing. Drawing

V17-331913 (Figure 7-5) depicts these details for the fly away

umbilical. One criterion by which an external structure was

added to the otherwise smooth surface of the S/M was the impera-

tive necessity of finding a route for the umbilical - hard lines

and electrical wiring - such that it would not penetrate the

ablative material of the C/M.

A third significant interface exists between the S/M and the S-I

adapter. The chief feature is a strap-tension tie which also

carries the shaped charges used to separate the S-! adapter

panels from the S/C. See drawing T18-300005 (Figure _ £_I-u} •

S!D 64-206

. --

VIEW B-B_

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SECTION A-A []

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_ V1'7-310 OOl

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/ NORTH AMERICAN AVIATION, INC.SPACE and ]ZNFORMATION S¥STI_,MS DIVISIOIN

Volume: DIM-9

Section: 7

Page: 2

Date: 2-19-64

Rev. Date:

-Xs 355,000 (_E=3

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Figure 7-1. Installation of Fairing (VI7-3IO00I-I)

SID 64-206

a4 ] 2_--'-----r------ 22 21

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(_ NAtIoi_'l- _ R[Q'°) NAS 1_34C-7 (*e _E_'O)

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t ! FAIRING ATTACH

Volume: DIM-9

Section: 7

Page: 3

Date: 2-19-64

Rev. Date:

3,ADDED .1_ 01M ('i PLACES)i ,:'_mi (__,L_c_s.).I I I

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+ + + + 4- + + + + + + + + + + + + _-_i _

_ fAIRING ATTAC _

VI7-311101 FLAT PATTERN (a_E ae¢'r,o. A-ASCALE _ IHT _Z_ ZONE IO_

X_ SSs. oo

I?

17t Vl7-31OOOI L F2It II

16

FOR L/M, GENERAL NOTES,

USAGE, SEE SHT I /

Figure 7-2. Installation of Fairing (V17-310001-2)

sip 64-206

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Volume: DIM-9

Section: 7

Page: 4

Date: 2-19-64

Rev. Date:

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Eigure 7-3 Fairing Panel As _=_3_Service Module to Command Module (V17-3!!00!)

SID 64-206

12 10 , I

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Volume: DIM-9

Section: 7

Page: 5

Date: 2-19-64

Rev. Date:

Figure 7-_. Fairing Assembly Complete,

Command Module to Ser__ce Module Umbilical (V!7-33!77!)

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NORTH AMERICAN AVIATION, INC,SPACE and INFORMATION SYSTEMS DIVISION

z 4.

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VIEW LOOKING AFT.

AT FAIRING INSTL.- S/_ TO C./_l

, !

Volume: DIM-9

Section: 7

Page: 6

Date: 2-!9-64

Rev. Date:

Figure 7-5. Assembly of Support - Command Module to Service Module

and, Fly Away Umbilical (V!7-331913)

_ NORTH AMERICAN AVIATION, INC. Volume:D!M-9SPACE and INFORMATION SYSTEMS DIVISION S ecti on: 7

Page: 7Date: 2-19-64

Rev. Date:

Figure 7-6. Strap-Tension Tie,

Service Module to Adapter (V18-300005)

szD 64-2o6


Volume:_

Section: 7

Page: 8

Date: 2-19-64

Rev. Date:

7.2.4

7.2.5

7.3

7.3.1

7.3.2

7.4.2

A fourth external interface concerns the S/M and Adapter-to-

Launch Complex or the GSE umbilicals. Drawing V17-933401

(Figure 7-7) presents the control layout for the servicing and

umbilical locations. The latter are blown away hydraulically

from their respective structures at time of blast-off. (S-I

configuration only; S-5 configuration now in design study. )

Design studies are now in progress for the following external

interfaces:

a. S/M to SLA;

b. SLA to Saturn instrument package;

c. S-IV B adapter to L_;

d. S-I Adapter to S-IV B.

Internal Interfaces

One of the two internal interfaces is between the ECS and the

EPS. Drawing V17-331549 (not included) exhibits a bracket

mounting which binds members of each system.

A second internal interface is between the SPS and the EPS.

Drawing V17-331501 (not included.) likewise shows a bracket

mounting for members of each respective system.

Test Requirements

Tests for interfaces have been scheduled chiefly for separation

systems involving the modules. The test schedule given below is

included in this manual for information purposes. 0nly the

first three tests have been completed.


i00 A

i01

i01-i

i01

I01 A

Separation System: C/M from S/M

Separation System: S,/M to S-!VB

Adapter

S/M Adapter Panel Ejection System

Supplement i - Separation System_

S/M to S-IV B Adapter

Separation System: S/M from

Adapter

SiD 64-206

1;

2

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Volume: DIM-9

Section: 7

Page: 9

Date: 2-19-64

Rev. Date:

Figure 7-7. Control

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Layout for Servicing and Umbilical Locations (V!7-933401)

SlD 64-206

NORTH AMERICAN AVIATION, INC.SPACE and INFOR_IATION SYSTEMS DIVISION

Volume: D!M-9 ,

Section: 8

Page: 1

Date: ____4Rev. Date:

8.4

8.5

8.6

REFERENCES*

IOL AE-I-62-313, dated 5 December 1962, from C.H. Feltz, Department 695-i00_

to Apollo Engineering Management_ on subject of Apollo Engineering Manuals.

NASA Exhibit "B" Technical Specification_ Fart I. 3 January 1963.

Composite Construction £or Flight Vehicles_ Part III_ Design Procedure_

MiL Handbook 23.

Apollo Test Requirements Status and Coordination List. NAA S&ID_ 17 July

1963.

Command Module and Launch Escape System Structures. DIM-8_ Apollo Systems

Engineering Manual. NAA S&ID, 7 August 1963.

General Test P!an_ Research and Development for Project Apollo Spacecraft,

Individual System Test. NAA S&ID_ S!D 62-109-2.

*Add all current control_ perspective_ and nomenclature drawings as called out

in the list of illustrations for this manual.SID 64-206

ILLUSTRATION LOG

PROJECT DESIGN INFORMATION MANUAL DIM-9

SECTION

REQUESTOR REPORT NO. --

I D FIGg

NO.

I-i Service Module Nomenclature (V17-933200)

i-2

7-2-

Service M_ule: General Assembly (Vl?-O00002) /-

Service Module: Structural Assembly (9-17-320001-1) i. Z

F INAL

2-1

2-2 Service Module: Structural Assembly (VI?-320001-2)

2-3 Service Module: Structural Assembly (V17-320001-3)

2-4 Service Module: Structural Assembly (V17-320001-4)

2-5 Service Module: Struc t_-al Assembly_ (V17-320001-5) z .-

C_mplete Interior Arrangement of Service Module (V17-935561-I) ;-

2- t_1,

Complete Interior Arrangement of Service Rodule

Installation of Forward Bulkhead (V17-_20101)

Assembly of Aft Bulkhead, Statiom _. 200 (_17-320201-i)

Assembly of Aft Bulkhead, Station _ 200 (V17-320201-2)

z-._/

l- /.,L

Z-I-_

_2 Assembly of Aft Bulkhead, Station XB 200 (_17-320201-3) _ - /V

_,'/3 Assembly of Aft Bulkhead, Station _ 200 (n7-320201-4) 2_ -',/'b-

2-14 Assembly of Radial Beam 2 (V17-322001) 2 -/_,

Adapter: General Assembly (V18-OOOOO2) _-2..

3-3 Manufacturing Assembly Breakdown of _ Adapter (_E-015129) -;;-,+

3-4>

4-s

_-4

Skin Panel Splice for Adapter Plate (V18-300011)

Installation of Maim Propellant Tank, Service Module (V17-340001) _-z.:_ Assembly Complete: Main Propellant, Oxidizer (VlT-3_l_O01J _ '_¢

Tank Assembly Complete: Main ProPellant _ Fuel (IF17-343001) _/"_¢

Tank Assembly: Main Propellant, Oxidiser (_17-342002) _ 5"

_-5 Tank Assembly, Main Propellant, Fuel (V17-343002)

4,.-6 Tank Assembly: Main Propellam%,. _elium (V17-347002)

A_sembly of Upper Skirt .Suppert, Oxidizer Tank (VlT-342025)

PROJECT

ILLUSTRATION LOG

DZ'!;I_-NI._'_(,=.:'.,;,TI','_'!"2_2._7AL DIM- 9

SECTION

REQUESTOR

I

NO.

P- 7_. t_.a_st 3503, .4 REPORT NO.

FINAL

Mo_mting Provisions, Znvir:m.'_enta! 3ontrc! System Instal]s.ticns (7].7-.55;71 7-"I

_-2 Mounting Provisions, Environmental Control System _nst,_.!]stions (_J!7-3-,J! 7-.2I

5-9 Molmting Provisions, Environmemtal Control System Installations (V3.7-_17 7":_.)

5-4 :-m_,_mb._ of Oxygen Tar_: Shelf Support (V17-331667)

5-5 Nodule InstalPation of Reaction Control System (V17-322000)

"9 ,. ,_4- " (_ . ......5-6 Panel Assembly 3omplete, ,_e_._ _l.m Control System (v17-33.2001-I)

5-7 Panel Asse_b!y Comolete, _*4c.n Control System (I_,-..j2001-_)

5-8 Pa_e]. Assemb2.y_ Peacticn Control System (F17-332002-I)

5-9 Panel Assemb_!y_ Peaction Ccntro! ._yst_m (V17:_.2OO2-2)

_-!O Housin_ Assembly, _....+_ o....... ......_ .n Control. Sys+.,_m (V!7-332010)

5-11 Longitudinal He_t Shield Instal].stion, .qe_ction Control System (7]..7-33:

5-].2 Lateral H_o.t Shield Installation, Reaction Control _vstem (VI7-_°_n]

5-]3 Insulation Imstallation for Reaction Control Systen,. (V17-3_2046)

5-1,/+ End M.ounti.-gAssembTy of Prooellant Tanks, Reaction Cen,<ro! System (7].5

5-].5 Motu_ting Assembly, Pro;._ellant and Pressure Tanks, Re cL_on C_t_o_

2ystem (V!7-332042)

5-16 Installation of _ _" *...._ngxne Mount, Service Propulsion oy_,,e_ ( V!7-3:_7101-I

"" _o,_ulsion Sv_t.__ (U!7-327!01-2)5-17 Installation of Engine No,mr, _er_ce . _. . .....

5-18. Mountin_ Provisions Installation, Service Propu!sJen Svst,_m (,l_-__.100(

5-19 }"..ounting_:'ovisions Installation, Service Pronu_--ion._.,_ _"_ssuriza1:.ion

System (717-331100)

r.,O ,_

)

0f:l)

--]

FORM 930- R-1

__;ou/uti_Provisions, Electrical Power System (V17-351552-I)

Mounting Provisions, Electrical Power System (V17-931552-2)l

/

!;"

PROJECT

SECTION

REQUESTOR

NO.

,o,. ,30 7

ILLUSTRATIONLOG

_IGN INFORMATION MANUAL DIM- 9

P. B. gaist. 3503. 4

| ,

i

REPORT NO,

Insta/lation of Fuel-Cell M_antlq, Stabilised Shear Web (VI?-33152_)

Assembly of Support Shelf, Upper R_rogen Tank (VI?-331566)

Control Layout - Electrical Power System Radiators, Seet_rs 0he and

FINAL

It

Four (V17-933074} _-"

Installation Previsions, Fluid Lines Support, Electrical Power _"

_ystem (_i?-331553-I)

Installation Provisions, Fluid Lines Support, Elee%rioal Power

System (VI?-331553-2)

Installation Provisions, Fluid Lines _ppert, _ee_ieal E_wer

Systen (v'z?-33z553.:.3)

0uter S_ell Assembly, Aft Heat Shleld, Seekers Three F_Ar and Five

Inner ShellAssembly, A_ Heat Shield, Se@ters Three and Fi_

)

Installation. of Aft Heat Shield, Station 200 (T17-331689-I)

InstaAlation of Aft Heat Shield, Statian 200 (V17-331689-2)

Insulation Installa_zon Pr_isions, Servlse Mule _rI?-331562-1)

Insulation _,stalla_Ion Provisions, Ser_Ise M_le (_17-33156_-2)

Complete Assembly of Thermal Simulator for Speoi_en Test _TT-6600)

Installation of Fairing (VI?-310001-1) 7- 2_

Installation of Fairing (_I?-31000_-2) 7-9

Fairing Panel Assembly, Serviee M_ule te Comad _ule (V17-311001)

Fairiag Assembly Complete, C_ma_ M_ule to Series R_4_I_ U_billeal

Strap-Tension Tie, Service _ule to _dapter (V18-300_05) _-7

Apollo Systems Engineering Manual Service Module and Adapter Structure

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Transcript of Apollo Systems Engineering Manual Service Module and Adapter Structure