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lZ65 • 12266 gl, "1_ CL_ssIFIC_TIOI_ C_G_ ClaSSl-L_' j.,,.] TeohniCa_ _ scientific _'_ Accession No. Copy No. D_H-_ APOLLO SYST_4 ENGINEERING I_NUAL Environmental Control System [u] 26 March 1963 Rev I February 1964 9_ Y, hgZ3 i_' " _-._, - _'___-"- .................... ',_,).., o_,',t_-" / / This document contains infox_ation aJ/Ipl_ing the national defense of the United States within the me'31_¢ o_fhe Espionage Laws. Title 18 U,S.C. Section 793 and 794. Its trans-I111_ or revelation of its contents in any manner to an unauthorized pers_law. Pub No. 543-G-2_ NORTH AMERICAN AVIATION, INC. SPACE and INFORMATION SYSTEMS DIVISION
Transcript
Page 1: Apollo System Engineering Manual. Environmental Control System

lZ65 • 12266

gl, "1_

CL_ssIFIC_TIOI_ C_G_

ClaSSl-L_' j.,,.] TeohniCa_ _scientific _'_ Accession No.

Copy No. D_H-_

APOLLO SYST_4 ENGINEERING I_NUAL

Environmental Control System [u]26 March 1963

Rev I February 1964

9_ Y, hgZ3 i_' "_-._, -

_'___-"- .................... ',_,).., o_,',t_-"/

/This document contains infox_ation aJ/Ipl_ing the national defense of theUnited States within the me'31_¢ o_fhe Espionage Laws. Title 18 U,S.C.Section 793 and 794. Its trans-I111_ or revelation of its contents in any

manner to an unauthorized pers_law.

Pub No. 543-G-2_

NORTH AMERICAN AVIATION, INC.SPACE and INFORMATION SYSTEMS DIVISION

Page 2: Apollo System Engineering Manual. Environmental Control System

NORTH AMERICAN AVIATION, INC.

SPACE and INFORMATION SYSTEMS DIVISION

_OLUME: DI_--5

SECTION:

PAGE:

DATE:

REV. 'DATE: 2-1-.6%

The Environmental System DIN-5 _presents the information being utilized to

design the Apollo Envirovmental Control Systems. The purpose of this document

is to provide information to all interested groups to ensure consistency with

all program objectives.

Comments shall be brought to the attention of the Am_ - DIM Board, who will

publish the comments and bring the matter up for action at the next scheduled

board meeting.

MANUAL REVIEW BOARD

Chairman:

Recorder:

Members:

N.E. Stelzriede 696-510

H. Tenenbamm 696-510

J.H. Wheatley 696-510J. Furrow 697-820

W.W. Jobson 696-410

R.S. Hirsch 697-410

O.W. Kilham 699-210

O.T. Stoll 696-520

D.D. Waller 698-310

M. E. Stelzriede

Chief

Apollo EnTironmental Systems

Page 3: Apollo System Engineering Manual. Environmental Control System

NORTH AMERICAN AVIATION, INC.

SPACE and INFORMATION SYSTEMS DIVISION

VOLUME: D_5

SECTION:

PAGE : ii

DATE:

REV, DATE" 2-1. -64

Section

1.O

2.0

3.0

4.0

5.0

CON_MTS

FOREWORD

CONTENTS

DISTRIBUTION LIST

ENVIRONMENTAL CONTROL SYSTEM (ECS)

1.1 ECS Functions

1.2 Cabin Suit Circuit System

1.3 Oxygen Supply System

1.4 Water Supply System

1.5 Coolant System

ECS DESIGN AND PERFORMANCE CRITERIA

WASTE MANAGEMENT SYSTEM

RELIABILITY

APPENDIXES

A. List of Current References

B. List of Abbreviations

Pa_zm

i

ii

V

l-1

I-5i-ii

1-141-21

i-3h

2-1

3-1

4-1

5-1

5-4

Page 4: Apollo System Engineering Manual. Environmental Control System

NO,:TH AMERICAN AVIATION, INC.

..... SPACE andINFORMATION SYSTEMS DIVISION

" mili

Volume:

Section:

Page:

Date:

Rev. Date:

DIM-5

iii

2-I-64

Figure

I.i

1.2

1.3

1.4

1.5

1.6

1.7

1.7.1

1.7.2

1.7.3

1.7.3.1

1.7.3.2

1.7.3.3

1.7.4

1.7,5

1.7.6

1.7.7

1.7.8

1.7.9

1.8

1.9

1.9.1

1.9.2

1.9.3

1.9.4

1.9.5

I.I0

i.Ii

1.12

1.13

1.13.1

1.13.2

1.13.3

1.13.4

1.13.5

1.13.6

1.14

1.15

1.16

1.17

i. 18

1.19

1.20

1.21

1.22

1.25

1.24

ILLUSTRAT IONS

Page

Environmental Control System Schematic 1-3

Environmental Control System 1-4

Pressure Suit Circuit and Cabin Atmosphere Control System 1-6

Cabin Temperature Control - Crew Access 1-7

Pressure Suit Supply Umbilical Connectors 1"8

Suit Oxygen Return Valve Item 1.3 1-9

Debris Trap Item 1.8 l-lO

Suit Compressor Item I.i0 l-lO.1

Check Valve and Screen Assy Item 1.11 1-10.2

CO, and Odor Absorber (Operational Schematic) Item 1.15 1-10.3

CO_ and Odor Absorber (Diverter Valve Schematic) Item 1.15 1-10.4

CO_ and Odor Absorber (Flow Schematic) Item 1.15 I-IO,5

CO_ Absorber Filter Assembly Item 1.15 1-10,,6Pr_s_"_e Relief Va!vc Item 1.16 I-IO.7

Cyclic Accumulator Selector and Solenoid Valve Item 1.36 1-I0.8

Water Accumulator Timer Cycle Item 1.36, 1.38 and Dart of 1.29 1-I0.9

Cabin Outflow Valve (Pressure Regulator and Ne_atlve Relief)

Item 3.1 l'lO.lO

Cabin Recirculating Blower Item 3.18 1-10.11

Cabin Absolute Pressure Regulator Item 3.28 1-10.12

Oxygen Supply System Schematic 1-12

ECS Valve Panel - Crew Access 1-13

Back Pack Oxygen Supply Valve Item 4.13 1-13.1

Suit Demand Pressure Re,later Item 4.16 1-13.2

Metering Sbntoff Valve Item 4,_7 !-!_=3

Emergency Inflow Control Valve Item 4.22 1-13,4

Pressure Regulator (Oxygen) Item 4.24 1-13.5

Water Supply System 1-15

Water Management System 1-16

Suit Evaporator (H_O Inflow Control Valve) Item 5,5 1-19

Waste/Potable Wate_ Tank Item 5.10 & 5.15 1-20

Water Chiller Item 5.14 1-20.1

Relief and Shutoff Valve Item 5.19 1-20.2

Potable Water Supply Assy. Item 5.22 1-20.3

Pressure Relief and Shutoff Valve Item 5.23 1-20_4

Fluid Pressure Regulator Item 5.24 1-20.5

Glycol Evaporator (Water Control Valve) Item 5.29 1-20.6

Water Glycol Circuit 1-22

Thermal Load Coolant Flow 1-23

Command Module Coldplate Provisions 1-24

Non-structural Coldplate 1-25

Coldplate .415 inch Counterflow, Counterpass Machined Type 1-26

Sandwich Coldplate - Typical Installation 1-27

Coldplate Bracket and Component Clamp 1-28

Radiators - 60 Sq. Ft. Lunar Mission 1-29

ECS Radiator Sub-Assembly Detail 1-30

Check Valve (Glycol) Item 2.1 & 2,5 1-31

Relief Valve (Glycol Pressure) Item 2.2 1-32

Page 5: Apollo System Engineering Manual. Environmental Control System

NORTH AMERICAN AVIATION, INC.

SPACE and INFORMATION SYSTEMS DIVISION

Volume: DIM-5

Section:

Page: iv

Date:

Rev. Date: 2-1-64

_" %_Ire

1.24.1

1.24.2

] .24.3

1.24.4

1.24.5

1.24.6

1.24.7

1.24.8

1.25

1 26

1.27

._..28

1.29

3.IA

9./

3.3

3.4

3.5

3.6

ILLUSTRATIONS - continued

Glycol Evaporator (Backpressure Control System)

Glycol Evaporator Item 2.6

Control Valve (Cabin Temperature) Item 2.13

Manual Shutoff Valve Item 2.28 & 5.18

Water Glycol Reservoir Item 2.29

Glycol Pump Assembly Item 2.30

Back Pressure Valve Item 2.39

Glycol GSE Shutoff Valve Item 2.46

ECS - GSE Servicing Locations

S/M RCS Temperature Control System Block I

Temperature Control System

RCS/Temperature Control System

RCS Engines

Waste Management System - Schematic

Waste Management System - ECS

Waste Management System Blower (Centrifugal)

Vacuum Cleaner Assembly - Waste Management System

Waste Management System Backup Valve

Storage Compartment Ventilation System, Check Valve

Item 2.6

Page

1-32.1

1-32.2

1-32.3

1-32.4

1-32.5

1-32.6

1-32.7

1-32.8

1-33

1-351-36

1-37

1-38

3-5

3-4

3-5

3-6

3-7

3-8

Table

2.1

2.2

2.5

2.*+

2.5_..6

2.7

2.8

2.9

2.10

2.11

2.12

2.13

2.14

4.1

4.2

TABLES

Environmental System's Power Requirements

Suit Circuit Subsystem

Cabin Pressure & Temperature

Cabin Heat Exchanger BTU/Hr.ktabolic Loads - Pressurized Cabin

Metabolic Loads - Depressurized Cabin

Environmental Loads - BTU/Hr.

Electronic Loads used for Coldplate Design

Electrical & Miscellaneous Loads

Oxygen Supply System

Heat Loads in BTU/Hr. for Water Glycol Loop

Temperature Control System- Component TemperatureParameters

Noise Level Data Cabin Fan Suit Compressor

Waste Management System Design Criteria

Environmental Control Subsystem Mission Reliability

Environmental Control Subsystem Failure Effects Analysis

Page

2-32-42-52-6

2-72-8

2-92-10

2-12

2-13

2-1_

2-15

2-16

2-17

4-44-5

Page 6: Apollo System Engineering Manual. Environmental Control System

NORTH AMERICAN AVIATION, INC.

. SPACE. and INFORMATION SYSTEMS DIVISION

VOLUME: D_¢-5SECTION-"

PAGE: V

DATE:

REV. DATE" _

123

4

56

7

8

9iO

II

12

].3

14

1516

17

18

1920

21

22

23

24

2526

2728

29

3O

31

32

33

34

35

36

37

38

39

4O

4-I

42

434445

46

DESIGN INFORMATION MANUAL NO. 5

DISTRIBUTION LIST

Stephenson, C. J.

Herschkowitz, B. H.

Brewer, H. M.

Tarr, J. S.Dudek E. F.

Templeton, R. R.

Walkover, L. J.

Cole, J. R.

Nelson, N. H.

Stelzriede, M. E.

Levine, D. S.

Pyle, R. W.

Lassen, R. H.

Copeland, E. J.

Bouman, C. P.

Sheere, R. W.

Ross, J. M.Alpert, R. A.

Fox, D. J.

Pollard, H. F.

Gibby, G. L.

Clary, W. T.

Kinsler, M. R.

Nicholas, R. F.

Wells, J. G.

Ackerman, C. R.

Liebergot, S. A.

Frank, D. E.

Miller, R. J.

Edziak, T. F.

Ackers, J. O.

Rubalcaba, J. R.Anthonisen, N. C.

Armstrong, W. T.

Milliken, R. J.Laubach, G. E.

Barnett, B.

Reithmaier, L. W.Stoll, O. T.

Smith, G. F.

Cho, A.

Neff, R. W.

Malsby, M. W.

Fitzwater, R. J° (Link Co.)

Brockman, C. L.Kilmer, H. A.

695-200

043-O50

697-210

697-210

697-400

698-300

696-410

696-420

697-800

696-510

697-500

695-100

191-O15

696-510

697-810696-510

696-510

699-210

671-OO0672-000

677-000

695-1OO

696-500

696-200

697-200

642-004

642-004

189-141

189-240

693-210

041-675677-000

Dept. 018- Pico Facil. Bldg. 81642-005

O91-O68

696-520

697-810

696-520

696-520

697-110

191-015

697-440

698-320

096-704

697-210O96-700

Page 7: Apollo System Engineering Manual. Environmental Control System

NORTH AMERICAN AVIATION, INC.

SPACE and INFORMATION SYSTEMS DIVISION

CONFIDENTIAL

VOLUME: DIll.5

SECTION:

PAGE: vi

DATE:

REV. DATE: 2_

DESIGN INFORMATION MANUAL NO. 5

DISTRIBUTION LIST (Continued)

47 Amderson, G. E.

48 Gerry, M. E.

49 Johnson, R. W.50 Grycel, F. J.

51 Perkins, W. A.

52 Myers, H. L.

53 Puterbauch, H. J.

54 Funke, F. E.

55 Hereld, G.

56 Jones, T. C.

57 Frankos, D. T.

58 Slemmer, F. C.

59 Meldahl, A. D.60 Alexander, E. J.

61 Cook, P. P.

62 to 82 - NASA via Data Requirements

595-331

693-210042-O70699-220

698-310

697-620

697-530

697-710

699-240677-000

693-220

O41-811696-510

696-510

NAA/S&ID Apollo Representative

Bldg. A, Room iO6OO1 Gulf Freeway

Houston 23, Texas

CONFIDENTIAL

Page 8: Apollo System Engineering Manual. Environmental Control System

NORTH AMERICAN AVIATION, INC.SPACE and INFORMATION SYSTEMS DIVISION

Volume: DIM-5

Section: I

Page: I-I_

Date:

Rev. Date: 2-I-64

Page No.

l-I

i-I.I

i-2

1-3

I-4

1-5

1-6

1-7

I-8

I-9

I-i0

i-I0. I

I-i0.2

1-10.3

1-10.4

1-10.5

1-10.6

1-10.7

1-10.8

i-i0.9

I-I0. I0

I-I0. ii

I-i0.12

I-II

1-12

1-13

1-15.1

1-15.2

1-15.31-13.4

1-13.5

1-14

1-151-16

1-17

1-18

1-19

1-20

1-20.1

1-20.2

1-20.3

1-20.4

1-20.5

1-20.6

1-21

1-22

1-23

1-24

LIST OF CURRENT PAGES

Date Revision

2-1-64

2-1-64

2-1-64

2-1-64

2-1-64

2-1-64

2-1-64

2-1-64

2-1-64

2-1-64

2-1-64

2-1-64

2-i-64

2-1-64

2-1-64

2-I-64

2-1-64

2-I-64

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2-1-64

2-1-642-1-642-1-64

2-1-642-1-64

2-1-642-1-64

2-1-64

2-1-64

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Page 9: Apollo System Engineering Manual. Environmental Control System

NORTH AMERICAN AVIATION, INC.SPACE and INFORMATION SYSTEMS DIVISION

Volume:

Section:

Page:

Date:

Rev. Date:

DIN-5

1

I-I.I

2-I-64

LIST OF CURRENT PAGES -

Page No. Date

.i

.2

.3

.4

.5

.6

.7

.8

1-25

1-26

1-27

_--C.t2

i-29i-3oi-3i1-32

1-32

1-52

1-32

1-32

1-32

1-32

1-52

1-32

1-33

1-34

1-35

1-36

1-37

1-38

continued

Revision

2-I-64

2-1-64

2-1-64

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2-1-64

2-1-64

2-1-64

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..... kfi__ _

Page 10: Apollo System Engineering Manual. Environmental Control System

NORTH AMERICAN AVIATION, INC.

SPACE and INFORMATION SYSTEMS DIVISION

VOLUME: DIM-5

SECTION_ 1

PAGE: i-2

_ATE:

REV. DATE: 2-1-64

1.0

1.1

I.i.I

1.1.2

1.i.3

1.1.4

1.1.5

i.i.6

1.1.7

i.i.8

EI_IRO_ENTAL CONTROL SYSTEM

The Environmental Control System (ECS) is designed to provide controlled

environments for three crew members in a spacecraft for a 14-day mission.

These controlled environments are necessary for crew comfort and safety and

for optimum operation of equipment within the vehicle.

ECS FUNCTIONS

The ECS shall perform the following functions for the Apollo spacecraft:

Remove carbon dioxide and odors by the use of lithium hydroxide and

activated charcoal.

Store oxygen and hydrogen required for the environmental control system

and electrical power system in a single phase condition for the entire

mission.

Reject equipment and crew heat loads to space through a radiator.

Provide supplemental and emergency cooling by evaporating water.

Maintain a cabin internal pressure of 5.0 psia during normal system

operation and 14.7 psia (ambient) during ground operation.

Maintain a cabin nominal temperature of 75 degrees F with a relative

humidity between 40 and 70 percent during normal system operation.

Maintain a suit pressure of 3.5 psia minimum during emergency system

operation.

Provide thermally controlled water for crew consumption.

_=n_m_rl_lTI A U

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Page 11: Apollo System Engineering Manual. Environmental Control System

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NORTH AMERICAN AVIATION, INC.SPACE and I NFOR_IATION SYSTEMS DIVISION

VOLUME: DIM-5

SECTION; l

PAGE: i--5

DATE:

REV. DATE: 2-1-64

1.2 Cabin-Suit Circuit System

The purpose of the pressure suit circuit is to control automatically the flow,

pressure, temperature, and composition of the pressure suit gas. This system,

in conjunction with the Command Module pressure and temperature control systems,

shall also control these environmental conditions in the Command Module when

any or all the crew are out of their pressure suits.

These functions are provided by a water separator, a regenerative heat ex-

changer, oxygen demand regulators, a debris trap, air compressors, CO2 and

odor absorbers, and an air cooler. Component redundancies are provided as

required to obtain the reliability required for the Apollo missions.

The purpose of the Command Module pressure and temperature control system is

to maintain automatically the pressure and temperature of the command module

interior within prescribed limits. This function is accomplished in conjunc-

tion with the pressure suit circuit system by means of regulated oxygen in-

flow, recirculation blowers, a heat exchanger, a temperature control and

sensor, Command Module pressure relief valve, and various other valves and

controls.

Page 15: Apollo System Engineering Manual. Environmental Control System

NORTH AMERICAN AVIATION, INC.

•SPACE and INFORMATION SYSTEMS DIVISION

VOLUME: DIM- 5

SECTION: "1.

PAGE : 1-6

DATE:

REV. DATE: 2-1-_________64

CABIN OUTFLO___PRESS.REG & NEGIRELIEF VALVE

SUIT

CONNECTOR -___MANUAL 0 2 VALVE

P_ESSURESU. LL_" - _;-_J

AP

iIMU !

NOT PARTllIOF ECS__--- L I

IIII I J .''_DEMAND PRESS. / _ _ I

_ REG & RELIEF i'_ _ 'l---- COLDPLATEI o _ I_.,,wo,,L /I .9 CHARCOAL --- ::::-: _]

, ,, ÷÷_

- {L_//_ Cl_) BLOWERS

/'-SUIT COMPRESSOR CAB'--I IN HEAT EXCHANGER

Figure 1.3 Pressure Suit Circuit and CabinAtmosphere Control System

Page 16: Apollo System Engineering Manual. Environmental Control System

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Page 17: Apollo System Engineering Manual. Environmental Control System

--_ NORTH AMERICAN AVIATION, INC. VOLUME: :D_-5

S]"_-_kC_O _EI.n.d "[Z_Ol::_Mx_kt_][O_'_ S_ILXSr_lq]MS _)1[_'1[S1"O_'%_ SECTION: 1

PAGE: 1--8

"""I'IC .... ",-_.#1 i LI! I Irll[.. DATE:

REV. DATE: 2-1-64

-Z

// RIGHT HAND COUCH

MIDDLE COUCH

\\

/-Y

F±gv.re 1.5 Pressure Suit Supply Umbilical Connectors

.--_#_/111- lULl1 I I/'_L

Page 18: Apollo System Engineering Manual. Environmental Control System

NORTH AMERICAN AVIATION, INC.SPACE and INFORMATION SYSTEMS DIVISION

Volume: DIM-5

Section: 1

Page: I-9

Date:

Rev. Date: 2-1-6A

LJAL SHUTOFF VALVE

OPEN

TEST PORT

FLAPPER CHECK VALVE

(CLOSED)

VALVE SEAL PLAT.__E70

{__ . VALVE (oPEE/NC)K

Figure 1.6 Suit Oxygen Return Valve Item 1.5

Page 19: Apollo System Engineering Manual. Environmental Control System

NORTH AMERICAN AVIATION, INC.SPACE and INFORMATION SYSTEMS DIVISION

Volume: _j)_

Section: 1

Page: 1-10

Date:

Rev. Date:2_1 _64

0 2 FROM RETURN CHECK VALVE

SUIT 0 2 CIRCUIT

BY-PASS VALVE -_

-.-= " ".7.;.

_FILTER ELEMENT

_.//----HOUSIN G

0 2 TO COMPRESSOR

I |

Figure 1.7 Debris Trap Item 1.8

Page 20: Apollo System Engineering Manual. Environmental Control System

NORTH AMERICAN AVIATION, INC.SPACE and INFORMATION SYSTEMS DIVISION

Volume: DIM-5

Section: 1

Page: 1-1_),1

Date:

Rev. Date: 2-1-64

MOTOR ROTORASSEMBI

VANES

HOUSING STATOR Wl NDING

Figure 1.7.1 Suit Compressor Item 1.10

r&]F._

Page 21: Apollo System Engineering Manual. Environmental Control System

/I

NORTH AMERICAN AVIATION, INC.

SPACE and INFORMATION SYSTEMS DIVISION

Volume:_Section: 1

Page: 1-10,2Date:

Rev. Date: 2-1-64

CHECK VALVE SCREEN ASSEMBLY

,SUIT CIRCUIT CHECK VALVE

FiEurel.7.2 Check Valve and Screen Ass), (Suit Circuit) Item I.11

v"Vi.J_i.,le wur uuul.,ul.m v I I/II--

Page 22: Apollo System Engineering Manual. Environmental Control System

NORTH AMERICAN AVIATION, INC.

SPACE and INFORMATION SYSTEMS DIVISION

_l_lmf m ..._al i i II ILL----

Volume: DMI-5

Section: 1

Page: i-i0.3

Date:

Rev. Date: 2-1-64

PRESSURE INTERLOCK PIN

WITHDRAWN INDICATING

EQUALIZED PRESSU RE

THIS COVER

READY TO

BLEED VAL%

HINGE

DETENT FOR DIVERTER,VALVE HANDLE

INTERLOCK PLUNGER LOCKOUT

PREVENTS VALVE REVERSAL

UNTIL COVER IS FULLY CLOSED

(SEE DIVERTER VALVE SCHEMATIC)

VALVE HANDLE-

TO DIVERT FLOW

JGH R.H. CANNISTER

THIS COVER

C LOS ED

SUIT CIGAS FROM

COMPRESSOR

RICH IN CO 2

SUIT CIRCUIT GASTO SUIT HEAT EXCHANGER

EXCESS CO 2 REMOVED

PRESSURE INTERIOR PIN ENGAGED

INDICATING UNBALANCED PRESSURE

CO 2 and Odor Absorber (Operational Schematic)

Figure 1.7.3 Item 1.15

Page 23: Apollo System Engineering Manual. Environmental Control System

NORTH AMERICAN AVIATION, INC.

SPACE and INFORMATION SYSTEMS DIVISION

Volume:Section: 1

Page: 1-10,4Date:

Rev. Date: 2-1-_64

DIVERTER VALVE HANDLE-_

!_ __- _NREi! iOi VPiLUENcGiRSEi SDOfJONUTT'L

!

DIVERTER VALVE AND COVER INTERLOCKS IN POSITION TO DIVERT

ALL FLOW THROUGH LEFT SIDE WHILE RIGHT SIDE DOOR IS OPENEDTO REPLACE LiOH CONTAINER

!| I=

H

I

DIVERTER VALVE AND COVER INTERLOCKS IN NORMAL FLOW POSITION

Fis_z'e 1.7.3.1 CO 2 and Odor Absorber (Diverter Valve Schematic) Item 1.15

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UPSTREAMCANNISTER FAC

FI LTERFELT

SUIT CIRCUITGAS FROM

COMPRESSOR

RICH IN CO 2

SUIT CIRCUIT GASTO SUIT HEAT

EXCHANGER EXCESS CO 2 REMOVEDCHECK VALVE PLATE

ECK VALVE FLAPPER

NORMAL OPERATION. SCHEMATIC FLOW THROUGH BOTH LiOH CANNISTERSAND OUT THROUGH CHECK VALVES INTO DISCHARGE DUCT

CO 2 and Odor Absorber (Flow Schematic)

Figure 1.7.3.2 Item 1.15

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_,IrlP_ ......---- .Wl I li_ iiii ! i ii ill=

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HANDLi

GAS FLOW IN HOUSING COVER

FILTER

HYDROXIDE

ACTIVATED CHARCOAL

I LTER

HOUSING

GAS FLOW OUT

Figure I.7.3.3

CO2 Absorber Filter Assembly

Item I.15

_

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POPPET

MANUALOVER-RIDE TO

IBRATION ADJUSTMENT

Fi_el.7.4 Pressure Relief Valve Item I .16

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2-1-54

SOLENOID BY-PASS

SHUTOFF VALVE

Figure i.?. 5

Cyclic AccumulatorSelector & Solenoid Valve Item I.36

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I

1-10,9

2-I -64

I:]I11

LW W

IIII IIII IIII II

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>-

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.pH

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o>_

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Rev. Date: 2-1-54

(

DIFFERENTIAL DIAPHRAGM--_

\DIFFERENTIAL

METERINGVALVE_OUTFLOWVALVE

II

AMBIENT SENSE PORT

IN SENSE PORT

CABIN PRESSUREIN LET PORT

CABLE j

VALVE

MANUALOVERRIDE - CLOSE

OVERBOARDDISCHARGE

MANUAL OVERRIDE -

BOTH OPEN & CLOSE

Figure 1.7.7 Cabin Outflow Valve (Pressure Regulator & Negative Relief) Item 3.1

A m m-'=I_ _I m_= I =_A m

VVlll IVkI! i i-iqi.--

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1-10.11

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• , . ':

HOUSING

IMPELLER_

MOTOR ROTOR

ASSEMBLY

STATOR WINDING

"DESWIRL VANES

Figure 1.7.8 Cabin Recirculating Blower Item 3.18

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t

ANEROID

REPRESSURIZATION

CONTROL

_11 SUPPLY PRESSURE INLET

FLOW LIMITER

Figure I.7.9 Cabin Absolute Pressure Regulator Item 3.28

(2 req' d)

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1.3 Oxygen Sun oly System

The oxygen supply system consists of the normal oxygen supply system and

the surge tank oxygen supply system.

The normal oxygen supply system is capable of supolying all of the required

oxygen for the entire mission up to the re-entry phase. The system functions

by reducing the pressure of the space vehicle oxygen supply system as required

to the nominal working pressure of the various suit circuit and potable water

tank pressure controls. This function is accomplished by suitable oressure

regulators, demand regulators, and shutoff and check valves. This system

also provides for the recharging of the Portable Life Support System (PLSS)

in the command module.

The Surge Tank oxygen supply system supplies the oxygen required for inflight

emergencies and mission completion after separation of the service module

from the command module. This system stores gaseous oxygen at a high pressure.

During system operation, the high pressure is reduced to the nominal working

pressure of the various suit circuit pressure controls. This function is

accomplished by pressure regulators, and valves as required.

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2-1-6/+

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Date:

Rev. Date:2-1-6_

SHAFT

RETAINER

MO LDED

Figure 1.9.1 Back Pack Oxygen Supply Valve Item 4.13

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I-I 3.3

2-I -64

BELLOWS

3 POPPET

Figure 1.9.3 Metering Shutoff Valve Item 4.17

L_

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Page: 1-13.4Date:

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REFERENCE CHAMBER RELIEF VALVE

REFERENCEPRESSURECHAMBER

PRESS-TO-TESTBUTTON

_F BLEED

ICE

DEMAND

SUPP LYVALVE

SUPPLY PRESSURE INLET =,_'T4'

VALVE

Figure 1.9.4 Emergency Inflow Control Valve Item 4.22

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Page: 1-15-5Date:

Rev. Date: 2-1-64

• •

• "o O

SELECTOR

o

I

SURE REGULATOR

IEF VALVE

CHECK VALVE

¢

F±_re 1.9.5 Pressure Regulator (Oxygen) Item 4.24

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1.4 Water Supply Syste_

The water supply system provides water for emergency heat transfer operation

in the event of malfunction of the water-glycol heat transfer loop, supple-

menta_y heat transfer during orbital mission modes, and potable hot and cold

water for consumption by the crew members.

Potable and waste water is stored in separate tanks prior to take off and is

replenished from the fuel cells and the water separators. These functions

are accomplished utilizing water tanks, pressure controls, and valves as

required. This system also provides Freon for launch and boost cooling.

Water Supply Critical Characteristics.

Supply Temp. from Fuel Cell (OF)

Supply Pressure from Fuel Cell (psia)

Water Separator (ibs/hr recovered)

Water from Fuel Cell (ibs/hr)

195 + 5 195 ± 5(Notei)

? to 63 7 to 63

O.hto 1.5 O.hto 1.5

i.i to 2.3 0.56 to 1.0

(electrical

emergency)

Note: Water Temp. in Storage Tank h0 to 80

O::'7!C".':T:.=

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VOLUME" DIM-5

SECTIOn" 1

PAGE : 1-15

DATE:

REVo DATE "_

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0°° °°

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PAGE: "!--17

DATE:

REV. DATE: 2-1-64

A.

Crew Support Equipment Requirements

Hot Water Reservoir And Water Supply Valve Package

Requirements: To provide and maintain hot water for food reconstitution.Data:

(i) Hot Water Supply Temperature

(2) Inlet Water Temperature

(3) Reservoir Capacity at 158°F

(A) Maximum Heating Time for 2.5 ibs

Water from 60OF to 15h°F

(5) Draw-off Requirements:

(a)

(b)

(c)

(6) Pressure Drop at Design Delivery

Through Hot Water Reservoir and Valve

(7) Power Consmaption at 28 V

(8) Electrical Power (Heater)

15&°F + &°F

60°F

2.5 ibs

2.0 hours

First draw-off period shall supply 20 fluid ounces of 15h + h°F

water in an elapsed time not to exceed 25 seconds.

Second draw-off period shall commence 20 minutes after the start

of the first draw-off period and shall supply 8 fluid ounces at

15A°F in an elapsed time not to exceed i0 seconds.

The unit shall then be capable of re-supply to the requirements

of paragraphs (a) and (b), one and one-half (11) hours after

the start of the draw-off period of paragraph (a).

20 l:_ig _gximum

_5 watts maximum

28 V - dc

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DATE:

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Be

C.

Water Supply Valve

Requirements:

Data:

To supply hot or cold water for drinking or foodreconstitution.

(I) Delivery rate to be 1 _ .2 fluid ounces per second.

(2) Unit to have capability of distributing chilled water from

Item 5.1A through the supply valve with the valve in cold water

position.

(3) Valve handle to automatically and positively return to off position

following each actuation.

(h) Valve handle operating torques for 1½ inch minimum lever arm on

handle, h.5 in-lbmax.imum- 1.5 in-lbminimum.

Structural Requirements :

(i) Proof Pressure 53 psig

(2) Burst Pressure 88 psig

Water Chiller

Requirements:

Data:

To provide cold water for crew consumption.

(I) Chiller water supply temperature = 50 _ 5°F

(2) Enteringwater design temperature = 80°F

(3) Must be capable of delivering 8 fluid ounces of cold water, drawn

off at 5 minute intervals.

w

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MANUAL OVERRIDE KNOB

PUSH TO DIS-ENGAGE FROMi_LECTRICAL ACI

ELECTRICAL ACTUATOR ASSEMBLY

MANUAL OVERRIDE CLUTCH

POPPET CONTROL CAM

VALVE POPPET

I

Figure 1.12 Suit Evaporator ('H20 Inflow Control Valve) Item 5.5

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DATE:

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MOUNTING

PROVISION

(6 REQD

EACH END)

0 2 BLADDER SUPPORTRODS (3 REQD)

0 2 BLADDER IN DEFLATEDPOSITION (FULL WATER TANK)

WELD BEAD

(2 REQD)

\

OXYGEN

INLET WATER PORT

Figure 1.13 Waste / Potable Water Tank

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Date:

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_,_I

N

WARMWATER

I N LET

I l I

_co_<] T I ,OUTLETql-

CHILLEDWATER

OUTLET

t n , _"m

I I II __

I I l I

G LYE O LINLET

Figure 1.13.1 Water Chiller Item 5.14

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Date:

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l

®

D

STATIC SEAL

SHUTOFF VALVE

RELIEF VALVE POPPET

Figure 1.13.2 Relief & Shutoff Valve Item 5.19

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Page: 1-26.3

Date:

Rev. Date: 2-1-64

ELECTRICAL CONN ECTOR

& RADIO NOISE FILTER_ .._J,_f'_

\

POTABLE WATER IN /)

(TO BE HEATED IN RESERVOIR) !

COLDW_TERINj /(FROM WATER CHILLER)

INSULATION DELETED FROM

THIS VIEW FOR CLARITY

INSULATI

T

WIRING

HOT WATER

RESERVOIR

COLD WATERDISTRIBOTION LINL

INTERNAL ELECTRICAL HEA

H ERMOSTATS

I

-PAN EL ASSEMBLY

J

7--

HOTOR_

COLD WATER OUT

,,-SELECTORHANDLE

--SELECTOR VALVE

ASSEMBLY

--WATER SUPPLY

NOZZLE

Figure 1.13.3 Potable Water Supply Assy. Item 5.22

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wm__

_1, Ii1_ I ! i llilW il]! ! 11 |k

Volume:_

Section: 1

Page: 1-20.4

Date:

Rev Date: 2-1-64

SELECTOR

_DIE SELECTOR HANDLE

(SHOWN WITH NO. 2 VALVE SELECTED)

ADJUSTER ASSEMBLY

¢ ¢

Figure 1.13.4 Pressure Relief & Shutoff Valve Item 5.23

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"a'rM-51

1.-,20,, 5

2-1-64

0 2 PRESSURE REGULATORS

0 0 0 0

0 000'

0 0 0 0

O0 O0

0 0 O0

0 0 0 0

O00C

0 0 0 0

oooo0000

)000

000 0

_._

O0 0 0

000

000

0 O0 0

0 2 PRESSURE RELIEF VALVES

Figure 1.13.5 Fluid Pressure Regulator Item 5.24

-- vv. ....... rwn_

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Glycol Evaporator (Water Control Valve)

Figure 1.13.6 Item 5.29

XXi|_l_ai_m m_

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i. 5 Coolant System

The water-glycol coolant system is basically a closed intermediate heat-

transfer loop which permits heat to be transferred from the space vehicle

interior to the space radiators. A primary purpose of this system is to

provide cooling for the crew and electronic equipment. This function is

accomplished by pumps, coldplates, heat exchangers, valves, and controls

as required.

- .nw_

ILWJL!

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DATE:

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;UIT HEATEXCHANGER

GLYCOL FILL & VENT

BACK PRESSURECONTROL

L Ej 0i i

GLYCOL DL

EVAPORATOR- RESERVOIR

GLYCOL TEMPCONTROL

• L_J___. TEMPCONTROL

NOT PART

OF

O

GLYCOL

ACCUMULATCL

__rCOLDPLATE

NETWORK

Ir .... iI H

,, 11CABIN BLOWERS

CABIN HEAT EXCHANGER

CONTROL SPACE

Figure 1.14 Water Glycol Circuit

_ ^ I l IPI I_ i-ll'-rl ii

Ivv.ii .w _| i i |111..

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Page: 1-31'

Date:

Rev. Date: 2-1-64

UMBRELLA VALVE

TH IMBLE

FLOWING

CHECKED

Figure 1.23 Check Valve (Glycol) Item 2,1 & 2.5

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FI VALVE POPPET

CALIBRATION ADJUSTMENT

Figure 1.24 Relief Valve (Glycol Pressure) Item 2.2

-32::7:_'2"::T1.:-

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Rev. Date: 2-1-64

iii

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DISTRIBUTION

STEAM TO

OVERBOARD DUCT _}

STEAM FROM

_ SUIT CIRCUITEVAPORATOR

WATER I N LETGLYCOL INLET

GLYCOL OUTLET

Figure 1.24.2 Glycol Evaporator Item 2.6

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F MANUAL OVER-RIDE KNOBPUSH TO DIS-ENGAGE FROM

RICA L ACTUATOR.

j_ _ _ _ ELECTRICAL ACTUATOR

_ ASSEMBLY

MANUAL OVER-RIDE CLUTCH

PORT C

PORT

PORT A

PORT BPORT R

FULL FLOW

\

FLOW

- PORT_

J/

- PORT Bjr

/iZERO FLOW /

MAX. COOLING

PORT I

TYPICAL VALVE SECTION

AT MID-POSITION

f_

/\

;.\¢ /

\\ \\\ / \

\/ \VALVE POSITION MAX. HEATING

Figure 1.24.3 Control Valve (Cabin Temperature) Item 2.13

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BELLOWS

POPPET

n

m

Figure 1.24.4 Manual Shutoff Valve Item 2.28 & 5.18

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GAS IN

¢DISTRIBUTION CHANNELS

EXPULSION BLADDER WATER-GLYCOL OUT

FIGURE I.24.5 Water Glycol Reservoir ITEM 2.29

_,|l r113 r I_ITn J

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Volume: DIM-5

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Page: 1-32.6

Date:

Rev Date: 2-1-64

PLASTIC

INNER

MAGNET (DRIVEN'

JOURNALBEARI

BEAR I N G

IMI

CHECK VALVE

RETAINER

MAGNET (D

WATER-G LYCO LOUTLET

FILl

PRESSURESENSING PORT

WATER-GLYCOlINLET

RESERVOIRISOLATION

HOUSING ASSEMBLY

FLU ID ACCUMULATOR

METAL-BELLOW ASSEMBLY

CABIN PRESSUREREFERENCE

Figure 1.24.6 Glycol Pump Assembly Item 2.30

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Page: 1-52.7

Date:

Rev. Date: 2-1-64

ACI" LEXIBLE LINER

GLYCOL INLET

DAMPER

• :...-._!!: _: ..

-GLYCOL OUTLET

Back Pressure Valve Item 2.39Figure 1.24.7

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t

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Page: 1-32.8

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Rev. Date: 2-1-64

Figure 1.24o8 Glycol GSE Shutoff Valve Item 2.46

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1.6 Service Module Temperature Control System

The Temperature Control System (TCS) is a water glycol circulating system,

which will provide required heating or cooling to the service module

Reaction Control System (RCS) fuel and ocidizer tanks, fuel and oxidizer

valves, and the Reaction Control Engines.

The following components are required for the Temperature Control System:

(a) Pump assembly - Consists of two pumps, two check valves,

accumulator, and filter.

(b) Reservoir - Water glycol

(c) Heat sink -

(d) Heat Exchanger - Used during ground operation.

(e) Electric Heater- Will provide make-up heat to the system.

(f) By-pass valves, solenoid (4) - Used for the purpose of

isolating any of the RCS quads from the system in the event

of a failure.

(g) Shut-off valve -

Page 76: Apollo System Engineering Manual. Environmental Control System

3 h W W

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DATE:

REV. DATE: 2-1-64

TWO-WAY

SOLENOID ,_VALVE

AFT PUMP

ENGINE

T.C.

I

PLATES

TANK TEMP /CONTROL LINES -'J

II

///

ELECTRICALHEATER

RESERVOIR

_"_"_-- HEAT SINK

_3CH_ _ VALVEVALVE

t

PLAN VIEW TOP

LOOKING AFT

im,_aL- - "Figure 1.27 Temperature Control System

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OXIDIZER TANK

VOLUME:

SECTION:

PAGE:

DATE:

REVo DATE:

1

1-57

2-I-64

HEAT EXCHANGE

PLATES

SOLENOIDCONTROL

VALVES

QUICKDISCONNECTS

HELIUM TANK

FUEL

\HEAT

EXCHANGE

PLATES

Figure 1.28 RCS/Temperature Control System

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PAGE: 1--38

DATE:

REV. DATE: 2--1--64

DISCONNECTS

AND/ORFLEX-[

_./__ HEAT EXCHANGE PLATES

I

n_u_, 1.29 RCS ENGINES

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LIST OF CURP_NT PAGES

Pa_e No. Dat____e

2-1

2-2

2-32-42-52-6

2-7

2-8

2-9

2-10

2-11

2-12

2-13

2-142-152-16

2-17

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Revision

2-1-642-1-642-1-6z_2-1-64

2-1-642-1-6z,2-i-64

2-1-64

2-1-64

2-i-642-i-6_2-1-64

2-i-6z,2-1-642-1-642-i-642-1-6/+

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PAGE i 2-2

DATE:

REV. DATE: 2--1--6 4,

2.0 ECS DESIGN AND PERFORMANCE CRITERIA

The Environmental Control Systems Design and Performance

Criteria section portrays the parameters that must be designed

into the subsystems of the ECS.

Page 82: Apollo System Engineering Manual. Environmental Control System

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| | i

VOLUME: DIM-5

SECTION: 2

PAGE: 2-A

DATE:

REV. DATE: _

Table 2.2. Suit Circuit Subsystem

Temperature (°F)Normal

Max.

Min.

Pressure (psia)

Normal

Max.

Min.

Flow (ib/hr)Normal

Max.

Min.

Composition (psia)

5 psia 02Cabin CO 2 (max.)Pressurized

H2 0 (max.)

Composition (psia)

O2

3.5 psia C02 (max.)Suit Loop H20 (max.)

Cabin

Depressurized

Compressor

Discharge

103.0i12.0

i03.0

5.32

15.5o4.04

50.6152.538.6

Hx

Inlet

12o.8

140.5120.8

5.2115.4

3.98

50.5152.4

38.5

Hx

Outlet

50.0

50.045.o

5.17

15.34

3.96

50.0

152.o37.2

Suit

Inlet

55.058.O47.0

5.12

15.23.94

16.7

5o.712.4

4.327

.165

.508

2.718

.170

.612

4.253

.147

.6oo

2.638

.iN

._5

4.675 4.675

•147 .147

•178 .178

3.175 3.175

•147 .147

•178 .178

CompressorSuction

79.0

87.o7o.o

4.9314.63

3.75

50.6152.538.6

4.327.165

.5o8

2.718.170.612

33: '2Z[;7;.q

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VOLUME: DIM-5

SECTION: 2

PAGE: 2--5DATE:

REV. DATE" 2__'1 __6],

Table 2.3 Cabin Pressure & Temperature

Temperature

Normal

Max.

Min.

(°F)

Pressure (psia)

Normal

Max.

_n.

Flow Rate (ib/hr)Normal

Max.

Min.

Composition (psia)

O2

c% (Max.)H20 (Nomo)

Cabin

758o

70

5154.8

312

720

3OO

4.638

•147

•215

Fan

Suction

758o

70

312

72O

3OO

5154.8

4.638

.147

.215

Fan

Dis charge

76.481.4

71.4

5.01

15.o24.81

312

72O

3OO

4.638

•147

.215

Hx

Outlet

6O

856o

5154.8

312

72O

3OO

4.638

.147

•215

Page 85: Apollo System Engineering Manual. Environmental Control System

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VOLUME: Dlq_-5

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PA_E: 2-7DATE:

REV, DATE: _

Table 2.5 Metabolic Loads

Per Man Day (90% Man)

Pressurized Cabin

Parameters

Time (hr)

Total Metabolic

Load (btu/day)

Water Production

(ib/day)

Carbon Dioxide

Production (ib/day)

Oxygen

Consumption (ib/day)

Water Consumption

(lb/day)

Urine

Production (ib/day)

Nominal

Design

24

11;200

Work

8

4;200

Rest

7

2,850

Sleep

8

2, 570

5.0

2.12

1.84

7.6

2.6

3.20

.8

.69

4.87

1.67

.73

.54

.47

i. ii

.38

.66

.48

.42

i. Ol

.35

Exercise

i

i,580

.41

.3O

.26

.62

.21

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DATE:

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Table 2,6 Metabolic Loads

Per Man Day (90% Man)

Depressurized Cabin

Parameters

Time (hr)

Total Metabolic

Load (btu/day)

Water Production

(lb/day)

Carbon Dioxide

Production (ib/day)

Oxygen Consumption

(iblday)

Water Consumption

(ib/d y)

Urine

Production (ib/day)

Nominal

Design

24

12;000

9.8

2.27

1.97

12.4

2.6

6_270

Work

8 8

3,180

5.47

1.2

1.03

6.93

1.44

Rest

2.47

.6

.52

3 •ii

.64

Sleep

8

2,550

1.86

•47

.42

2.36

.52

""'lrlP'- ......

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Table 2.7 ENVIRONMENTAL LOADS

BTU/HR

D

Mission Phase

Prelaunch

As cent

Earth Orbit

Nominal

Design

-15o

1000

-15o

Maximum

0

i000

160

Trans-Lunar Injection

Trans-Lunar Coast

Lunar Orbit Injection

Lunar Orbit

Trans-Earth Injection

Trans-Earth Coast

-15o

-375

-375

-25o

-25o

-3o0

200

2O0

2OO

-350

io6o

lO6O

Minimum

-2OO

i000

-475

-258o

-258o

-258o

-270

-2580

-2580

A III. l I llll i Ipll. IIII_ i l _ I lu

v_.-...II,.II I I#-IIL

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VOLUME: DIM- 5

SECTION: ;_

PAGE: 2 __] [_j

DATE:

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Table 2.8 Electronic Loads Used For Coldplate Design

MAX

COMPONENT BTU/HR

CDU 150.

Rop 6o.

_AP 135.

EDIA 17.

PSA 1014.

AGC 410.

DISP/AGAP ECA 213.

YAW ECA 44.

INV 1109.

BATT CHBGR 64.

S-BAND PA' s 234.

C-BAND XPNDR 230.

VKF/AM XCVR i03.

EEC. BEACON 34.

WF/FM X_R 145.HF XCVR - .

PCM #2 12.

VHF MWLT 13.

AWD CENTER 20.

CENT TIMING 85.

PEEMOD PROC 29.

SIGNAL C0ND 171.

DATA STORAGE 113.

SEQ 171.

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PAGE: 2--].]..

DATE:

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Table 2.8 Electronic Loads Used For Coldplate Design (Cont)

MAX

COIV_ONENT BTU/HR

FG TELM

S-B XPNDR

W-P-DATA

76.

12.

47.

51.

AWX ECA 92.

PITCH ECA 44.

POLL ECA 42.

RADEQ 38.

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PAGE: 2--]2

DATE:

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Table 2.9 Electrical & Miscellaneous Loads

BTU/HR

Glycol Pump Motor

Suit Compressor Motor

Cabin Fan Motor

Non Coldplate Cooled Equip.

LiOH Canister. Heat

Nominal

Design

120.0

278.0

45.o

715.0

287.0

Page 92: Apollo System Engineering Manual. Environmental Control System

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REV. OATE:2--1--64

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DATE:

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LIST OF CURRENT PAGES

Page No. Dat____e

3-I

3-2

3-3

3-4

3-53-6

3-7

3-8

Revision

2 -1-64

2 -1-64

2-1-64

2-1-64

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2-I-64

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3.0 WASTE MANAGEMENT SYSTEM

The Waste Management System (WMS) is designed to remove the gaseous, solid,

and liquid wastes from within the command module of the Apollo. The system

removes objectionable odors from the food, refuse, and personal equipment

storage compartments. Wastes, in the form of fecal odors, urine, particulate

matter, food and water spillage, and results of unanticipated bodily functions

are removed by a vacuum cleaner, urine disposal system and fecal odor lines.

The resultant gaseous wastes are transferred to the ECS for further processing.

These functions are accomplished by a blower, switch, flexible lines, urine

separator, chemical tank, and valves.

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TO ECU SYSTEM

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Figure 3.3 Waste Management System Blower (Centrifugal)

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3-6

2-1-6h

MAIN HOUSINGFLEX HOSE

CONNECTION --

BAG INSERT

LATCH

NOZZLE

Figure 3.4 Vacuum Cleaner Assembly Waste Management System

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r v . ,r_m°

CAM GUIDE

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90 ° FITTING

@END

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VALVE BODY

SEAL ELEMENT (NEOPRENE)

Figu._e 3.5 Waste Management System Backup Valve

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ACTUAL SIZE

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Figure 3.6 Storage Compartment Ventilation System, Check Valve

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LIST OF CURRENT PAGES

Page No. Date

4-I

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4-34-44-54-6

4-7

4-8

4-9

4-10

4-11

4-12

4-13

4-14

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4.0

4.1

4.1.1

4.1.2

4.1.3

4.1.4.2

RELIABILITY

Environmental Control Subsystem

The Reliability goals for the ECS have been apportioned as

0.9935 for the probability of mission success and 0.9997 as

the probability for crew safety. These goals were apportioned

from the overall spacecraft reliability goals as specified byNASA.

Safe Abort Criteria

For design purposed it is to be considered that the mission

will be aborted if enough failures occur in the ECS so that one

additional failure would eliminate the capability of a safe abort.

This criteria requires the design to have redundancy for components

that perform critical functions, and/or have high failure rates,

and/or have failure modes that prevent system operation.

Failure Mode and Effect Analysis

The Failure Mode and Effect Analysis included in Table 4,2 depict

the components and their failure modes in the ECS. The failure

modes are evaluated as to their effects on system operation and the

overall spacecraft mission. The main purpose of these analyses is

to indicate the need for design consideration to remove the "Abort"

classification associated with component failure modes. The

Failure Mode and Effect Analysis are updated as firm design changes

are made.

Reliability Assessment

Reliability Assessment is the technique of statistically evaluating

test data on the equipment to obtain a measure of probability ofmission success.

Associated Subsystem Reliability Goals

ECS Radiators

The ECS radiators have apportioned reliability goals of

0.99995 for mission success and 0.999998 for crew safety.

Coldplate Circuit

Mission success and crew safety reliability goals for the

coldplate circuit have been apportioned at 0.99995 and

0.999999, respectively.

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4.1.4.3 Waste Management System

Mission success and crew safety reliability goals for the

waste management system have been apportioned at 0.999965

and 0.999998, respectively.

The Safe Abort Criteria and Reliability Assessment technique

explained previously are applicable to the associated ECS sub-

systems.

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Page 125: Apollo System Engineering Manual. Environmental Control System

NORTH AMERICAN AVIATION, INC.SPACE and INFORMATION SYSTEMS DIVISION

VOLUME: DIM-5

SE_T,O_- 4PAGE: 4-20

DATE:

REV. DATE: 2-1-64

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Page 126: Apollo System Engineering Manual. Environmental Control System

NORTH AMERICAN AVIATION, INC.SPACE and INFORMATION SYSTEMS DIVISION

VOLUME: DIM-5

_ECT,O... 4PAGE: 4-21DATE:

REV. DATE: 2-1-64

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Page 127: Apollo System Engineering Manual. Environmental Control System

NORTH AMERICAN AVIATION, INC.SPACE and INFORMATION SYSTEMS DIVISION

VOLUME: DIM-5

_ECT,O_" 4

PAGE: 4-22

DATE:

REV. DATE: 2--1--64

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Page 128: Apollo System Engineering Manual. Environmental Control System

NORTH AMERICAN AVIATION, INC.SPACE and INFORMATION SYSTEMS DIVISION

VOLUME: DIM-5

_ECT,O_." 4

PAGE: 4-23DATE:

REV. DATE: 2--1--(;4

¢)

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Page 129: Apollo System Engineering Manual. Environmental Control System

/

NORTH AMERICAN AVIATION, INC.SPACE and INFORMATION SYSTEMS DIVISION

VO'UME: DIM-5

SECTION: 5

PAGE : 5--1

DATE:

REV, DATE: 2-1-64

LIST OF CURRENT PAGES

Page No. Date

5-1

5-2

5-3

5-4

5-5

5-6

5-7

5-8

5-9

Revision

2-i-64,

2-i-64

2-i-64

2-i-64

2-i-64

2-I-64

2-I-64

2-I-64

2-1-64

Page 130: Apollo System Engineering Manual. Environmental Control System

NORTH AMERICAN AVIATION, INC.

/_ SPACE and INFORMATION SYSTEMS DIVISION

i

VOLUME: DIM-5

SECTION: 5

PAGE: 5--2

DATE:

REV. DATE: 2-1-64

NAA/SID

MC- 901- 0215

MC-999-0028

MC-999-0008

HC-284-0050

MC-901-0024

MC-901-0025

MC-901-0027

MC-901-0029

HC-901-0030

MC-901-0068

MA-0201-O051

MA-0201-0053

HA-020m-0054

MA-0306-0001

APPENDIX A

CVREENT EEFEEENCES

Procurement Specification

Environmental Control System

General Specification

Environmental Control System/Ground Support

Equipment

Documentation Requirements for Project Apollo

Procurement Specification

Vent Check Valve_ Waste Management System

Procurement Specification

Vacuum Cleaner, Waste Management System

Procurement Specification

Control Valve_ Waste Management System

Procurement Specification

Germicide Tank, Waste Management System

Procurement Specification

Urine Separator, Waste Management System

Procurement Specification

Blower_ Waste Management System

Procurement Specification

Back-up Valve, Waste Management System

Process Specification Checkout Procedure

Waste Management System

Process Specification Checkout Procedure

Environmental Control System

Interface Requirements Specification

Environmental Control System

ECS and Associated Plumbing Installation

Page 131: Apollo System Engineering Manual. Environmental Control System

NORTH AMERICAN AVIATION, INC.SPACE and INFORMATION SYSTEMS DIVISION

VOLUM E: DIM-

SECTION: 5

PAGE: 5-,_DATE:

REV. DATE; 2-i-64

CURRENT EEFEEENCES

MA-0206- 0003

SID 62-i0

SID 62°5O

SID 62-700-i

ARE-62-11 Rev.

MA-0306-0003

Integrated E&D Cooling Systems

Checkout Procedures for B/P's 12 and 13

Statement of Work for

Apollo Environmental Control System

Apollo Ground Support Equipment Specification

Apollo Mission Requirements

Apollo Environmental Criteria

WMS and Associated Plumbing Installation

AIEESEARCH

SS-IO00-R Rev. 4

SS-IO01-R Rev. 3

SS-IOI2-R Rev. 2

SS-1014-R Rev. 2

SS-1020-R Rev. 2

AiResearch System Specification

Environmental Control System

Test Plan

Environmental Control System

End Item Test Plan

Environmental Control System

Design Criteria Specification

Environmental Control System

Program Plan

Environmental Control System

Page 132: Apollo System Engineering Manual. Environmental Control System

NORTH AMERICAN AVIATION, INC. VOLUME:

SPACE and INFORMATION SYSTEMS DIVISION SECTION:

PAGE:

DATE:

REV., DATE:

DIM-5

5

5'-4

2-i-64

ABBKEVIATIONS

The following abbreviations are commonly used in Environmental

Control Systems terminology. Many of the terms have been extracted from

MIL-STD-12B, NAS 9-150, and existing Apollo documentation.

Accumulator ..... ACCUMR

Air Conditioning ..... AC

Airframe ....... AFIRM

AiResearch Mfg. Co ...... A/R

Alternating Current ........ AC

Aluminum ........ AL

Ambient ........ AMB

Apollo Guidance Computer .... AGC

Apollo Requirements Manual ...... ARM

As soon as possible ....... ASAP

Assembly ........ ASSY

Atlantic Missile Range ....... AMR

Atmosphere ......... ATM

Attitude Gyro Accelerometer .... AGAP

Automatic .......... AUTO.

Automatic mixture control ...... AMC

Auxiliary ......... AUX

Average .......... AVG

Avoid Verbal Orders ....... AVO

Back Pressure ......... BP

Back Pressure Control ....... BPC

Breadboard ......... B/B

Boilerplate ......... B

Boiler Plate ......... B/P

Blower ......... BLO

Bulkhead .......... BHD

Bypass .......... BYP

Cabin .......... CAB.

Capacity ......... CAP.

Carbon Dioxide ......... CO Z

Carbon Monoxide, cut off ...... CO

Center of gravity ........ CG

Check Valve ......... CV

Chilled drinking water ..... CDW

Circuit ...... CKT

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NORTH AMERICAN AVIATION, INC.SPACE and INFORMATION SYSTEMS DIVISION

VOLUME: DIM-5

SECTION: 5

PAGE: 5--5

DATE:

REV. DATE: 2--1--64

Clockwise • •

Close . .

Coaxial •

Command module

Compartment . •

Compressor •

Constant . •

Contaminated . .

Contract Change Notice

Contractor . . .

Control . . .

Coolant . . .

Copper . . .

Corrosion resistant .

Corrosion resistant steel

Counterclockwise

Coupling and Display Unit

Cryogenic Storage System

Cubic feet per minute

Cycle ....

Cycles per second

• •

e • •

• • •

Decrease . . . . . .

Deep Space Instrumentation Facilities

Density ......

De sign ......

Design Data Manual ....

Design Information Manual . .

Dew Point .....

Diaphragm .....

Dimension .....

Direct Current . .

Disconnect .....

Display ....

Earth Landing System

Electronic Control Assy.

Electrical Pqwer System . .

Enginee ring . . .

Engineering Change Proposal

Engineering Design Change . .

Englneering Order ....

Englneering Order Purchase Request

Englneering Program Authorization

Englneering Work Order . .

Envlronmental Control System

Equl )ment ......

• o •

• • o

• i

• • •

e o •

• • •

• •

CW

CL

COAX•

C/M

COMPT

COMPR

CONST

CONTAM

CCN

CONTR

CONT

COOL.

COP. or CU

CRE

CRS

CCW

CDU

CSS

CFM

CY

CPS

DECR

DSIF

D

DSGN

DDM

DIM

DP

DIAPH

DIM.

DC

DISC

DIS

ELS

ECA

EPS

ENGRG

ECP

EDC

EO

EOPR

EPA

EWO

ECS

EQUIP•

Page 134: Apollo System Engineering Manual. Environmental Control System

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VOLUME: DIM-5

SECTION: 5

PAGE: 5-6

DATE:

REV. DATE: 2-1-64

Estimate .........

Evaporator ........

Exhaust .........

Exterior .........

Fabricate .........

Fairing ..........

Fastener • . . • . . . • .

Figure .........

Filter .........

Fitting ........

Flexible .........

Flight ..........

Flight Director Attitude Indicator . . .

Fluid ..........

Forward .........

Freezing Point ........

Frequency .........

Gage ..........

Gaseous Nitrogen .......

Government Furnished Equipment . .

Government Furnished Property ....

Gravity .......

Ground Operational Support System • . •

Ground Support Equipment ....

Grumman Aircraft Engineering Corp . . .

Guidance and Navigation ......

Hardware .........

Hardware Utilization List .....

Heat ........

Heat Resisting ......

Heat Exchanger ......

Heater .......

Housing .........

Hydrogen ......

Impact ........

Inboard ......

Increase ....... •

Indicator .........

Inertial Measurement Unit .....

Inertial Rate Integrating Gyroscope . . .

Inertial Reference Package .....

Inflight Test System ......

Information .......

Instrument .........

Insulation .........

o

o

o

EST

EVAP

EXH

EXT

FAB

FAIR•

FASTNR

FIG

FIL

FTG

FLEX•

FLT

FDAI

FL

FWD

FP

FREQ

GA

GN Z

GFE

GFP

G

GOSS

GSE

GAEC

G&N

HDW

HUL

HT

HR

HX

HTR

HSG

H 2

IMP,

INBD

INCR

IND

IMU

IRIG

IRP

IFTS

INFO

INST

INS

-_vuln u_ll U It'lL

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/

/_ NORTH AMERICAN AVIATION, INC.VOLUME: DIM-5

SECTION: 5

PAGE: ___7

DATE:

REV. DATE: 2-1-64

Integral ......

Item Change Analysis . . .

Inter- Office Letter ....

Interchangeable ....

Interface Coordination Document .

Interior ......

Inte rmittent .....

Launch Escape System . . .

Liquid Oxygen .....

Liquid Hydrogen ....

Liquid Nitrogen ....

Lithium Hydroxide . . .

Little Joe ......

Low Pressure .....

Lunar Excursion Module

Lunar Orbital Rendezvous

Maintenance ....

Man Months .....

Manned Spacecraft Center . .

Manual ......

Manufacture .....

Manufactur_ d ....

Manufacturing .....

Map and Data Viewer

Massachusetts Institute of Technology

Master Change Record ....

Material .......

Material Schedule Authorization .

Maximum .......

Mean Time Between Failures .

Minimum .......

Miscellaneous ......

Mockup .......

Modification, Modify ....

Mount ........

Mounted .......

National Aeronautics and Space.Administration .

Navigational Base Assy e

Negative .....

Nitrogen ......

Normally Closed . . .

Normally Open ....

Not applicable .....

Not in contract ....

Not to scale .....

o

• •

INT

ICA

IOL

INT C HG

ICD

INT

INTMT

LES

LO z

LH Z

LN Z.LiOH

LJ

LP

LEM

LOR

MAINT

MM

MSC

MAN.

MFR

MFD

MFG

MDV

MIT

MCR

MTL

MSA

MAX.

MTBF

MIN

MISC

M

MOD

MT

MTD

NASA

NBA

NEG

N 2NC

NO

NA

NIC

NTS

- ri,_11 al=Ji=.ll i IrIL

Page 136: Apollo System Engineering Manual. Environmental Control System

NORTH AMERICAN AVIATION, INC.SPACE and INFOR_IATION SYSTEMS DIVISION

VOLUME: DIM-5

SECTION: 5

'='AGE: 5"8DATE:

REV. DATE-" 2-1-64

Numb e r ....

Obsolete ....

Opposite ....

Optical Base Assy. . .

Optimum ....

Outboard ....

Overboard ....

Override ....

Oxygen . . .

Pacific Missile Range

Package . . . •

Panel ......

Paragraph ....

Parallel . . .

Part ....

Part Number ....

Parts per million . .

Phase ......

Portable Life Support System

Position . .

Potable Water ....

Pounds per square inch . .

Pounds per square inch absolute

Pounds per square inch gage

Power and Servo Assy . .

Premodulation . . .

Pressure ......

Program Evaluation Review Technique

Pulse Code Modulation . .

Quantity ......

Radiation absorbed dose . . .

Radiator ......

Reaction Control System • .

Relocated ......

Research and Development . .

Reservoir ......

Restraint System . . .

Revolutions per minute . . .

Revolutions per second . . .

Revise, revision, reverse . .

Saturn Apollo .....

Select, Selector ....

Self closing ....

Sequence ......

Service Module ....

• • • • •

• • • • •

• • • • •

• • • • •

• o

• Q •

• • •

• • • •

• • • •

NO.

OBS

OPP

OBA

OPT

OUTBD

OVBD

OVRD

O 2 or OXYPMR

PKG

PNL

PAPA

PAR.

PT

PN

PPM

PH

PLSS

POS

POT W

PSI

PSIA

PSIG

PSA

PREMOD

PRESS•

PERT

PCM

QTY

PAD

PAD

RCS

RELOC

R&D

RES

RES

RPM

RPS

REV

SA

SEL

SELF CL

SEQ

S/M

Page 137: Apollo System Engineering Manual. Environmental Control System

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VOLUME:

SECTION;

PAGE:

DATE:

REV. DATE:

DIM-5

5

5-9

2-1-64

Sextant ....

Sink .....

Spacecraft ....

Spare ......

Specification . . .

Specification Control Drawing

Stabilization and Control System

Station ......

Structural .....

Structure ....

Subcontractor Engineering Memo

Superseded .....

Switch ......

Tank ......

Telemeter .....

Telephone Conversation . .

Teletypewriter exchange . .

Temperature

Terminal

Thermal

Through

Time .

T ole r ant e

Torque

Transceiver

Transducer

Transmitter

Transponder

Transfer

Tubing • •

Typical

Value, Valve

Vacuum • •

Variable

Vehicle ....

Waste Management System

Water Glycol . •

White Sands Missile Range

Without ....

Working Pressure . •

m • •

SXT

SK

S/C

SP

SPEC

SCD

SCS

STA

STR

STRUCT

SEM

SUPSD

SW

TK

T/M

TELECON

TWX

TEMP

TERM.

T HRM

THRU

T

TOL

TOR

XCVR

XDCR

XMTR

XPDR

TRANS

TUB.

TYP

v

VAC

VAR

VEH

WMS

W-G

WSMR

W/OWp


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