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lZ65 • 12266
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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
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
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
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
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
NORTH AMERICAN AVIATION, INC.
. SPACE. and INFORMATION SYSTEMS DIVISION
VOLUME: D_¢-5SECTION-"
PAGE: V
DATE:
REV. DATE" _
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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
NORTH AMERICAN AVIATION, INC.
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CONFIDENTIAL
VOLUME: DIll.5
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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
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
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1-10.7
1-10.8
i-i0.9
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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
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1-20.6
1-21
1-22
1-23
1-24
LIST OF CURRENT PAGES
Date Revision
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NORTH AMERICAN AVIATION, INC.SPACE and INFORMATION SYSTEMS DIVISION
Volume:
Section:
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1
I-I.I
2-I-64
LIST OF CURRENT PAGES -
Page No. Date
.i
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.4
.5
.6
.7
.8
1-25
1-26
1-27
_--C.t2
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1-32
1-32
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1-36
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continued
Revision
2-I-64
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..... kfi__ _
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.
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NORTH AMERICAN AVIATION, INC.SPACE and I NFOR_IATION SYSTEMS DIVISION
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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.
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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
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PAGE: 1--8
"""I'IC .... ",-_.#1 i LI! I Irll[.. DATE:
REV. DATE: 2-1-64
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// RIGHT HAND COUCH
MIDDLE COUCH
\\
/-Y
F±gv.re 1.5 Pressure Suit Supply Umbilical Connectors
.--_#_/111- lULl1 I I/'_L
NORTH AMERICAN AVIATION, INC.SPACE and INFORMATION SYSTEMS DIVISION
Volume: DIM-5
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Page: I-9
Date:
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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
NORTH AMERICAN AVIATION, INC.SPACE and INFORMATION SYSTEMS DIVISION
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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
NORTH AMERICAN AVIATION, INC.SPACE and INFORMATION SYSTEMS DIVISION
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MOTOR ROTORASSEMBI
VANES
HOUSING STATOR Wl NDING
Figure 1.7.1 Suit Compressor Item 1.10
r&]F._
/I
NORTH AMERICAN AVIATION, INC.
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Volume:_Section: 1
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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--
NORTH AMERICAN AVIATION, INC.
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_l_lmf m ..._al i i II ILL----
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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
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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
NORTH AMERICAN AVIATION, INC Volume: DIM-5
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Date:
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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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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
NORTH AMERICAN AVIATION, INC.SPACE and INFORMATION SYSTEMS DIVISION
Volume:
Section:
Page:Date:
Rev. Date:
DIM-5
11-10.8
2-1-54
SOLENOID BY-PASS
SHUTOFF VALVE
Figure i.?. 5
Cyclic AccumulatorSelector & Solenoid Valve Item I.36
NORTH AMERICAN AVIATION, INC.SPACE and INFORMATION SYSTEMS DIVISION
Volume:
Section:
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Date:
Rev. Date:
DIM-5
I
1-10,9
2-I -64
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NORTH AMERICAN AVIATION, INC.SPACE and INFORMATION SYSTEMS DIVISION
Volume: DIM-5
Section: 1
Page: 1-10.10Date:
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.--
NORTH AMERICAN AVIATION, INC.SPACE andINFORMATION SYSTEMS DIVISION
Volume:
Section:
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Rev. Date:
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1-10.11
2-1-64
• , . ':
HOUSING
IMPELLER_
MOTOR ROTOR
ASSEMBLY
STATOR WINDING
"DESWIRL VANES
Figure 1.7.8 Cabin Recirculating Blower Item 3.18
NORTH AMERICAN AVIATION, INC.SPACE and INFORMATION SYSTEMS DIVISION
Volume:
Section:
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Rev. Date:
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I
1-10.12
2-I -64
t
ANEROID
REPRESSURIZATION
CONTROL
_11 SUPPLY PRESSURE INLET
FLOW LIMITER
Figure I.7.9 Cabin Absolute Pressure Regulator Item 3.28
(2 req' d)
NORTH AMERICAN AVIATION, INC.SPACE and INFORMATION SYSTEMS DIVISION
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PAGE : 1--11
DATE:
REV. DATE: 2--1--6_A4 W
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.
NORTH AMERICAN AVIATION, INC. DIM-5
SPACE and INFORMATION SYSTEMS DIVISION
VOLUME:
SECTION:
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DATE:
REV, DATE:
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2-1-6/+
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NORTH AMERICAN AVIATION, INC.SPACE and INFORMATION SYSTEMS DIVISION
Volume: ,,DIM-5
Section: 1
Page: 1-13_.1
Date:
Rev. Date:2-1-6_
SHAFT
RETAINER
MO LDED
Figure 1.9.1 Back Pack Oxygen Supply Valve Item 4.13
NORTH AMERICAN AVIATION, INC. Volume:_
SPACE and INFORMATION SYSTEMS DIVISION Section: 1
Page: 1-15.P
Date:
Rev. Date: 2-1..64
/__ NORTH AMERICAN AVIATION, INC.
SPACE and INFORMATION SYSTEMS DIVISION
Volume:
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Page:
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Rev. Dete:
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I
I-I 3.3
2-I -64
BELLOWS
3 POPPET
Figure 1.9.3 Metering Shutoff Valve Item 4.17
L_
NORTH AMERICAN AVIATION, INC.SPACE and INFORMATION SYSTEMS DIVISION
Volume: DIM-_Section: 1
Page: 1-13.4Date:
Rev. Date: 2-1-64
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
/
//_-_---_ NORTH AMERICAN AVIATION, INC.
I(_) _. _,_o_,o___ o,v_io_Volume: DIM-5Section: 1
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
NORTH AMERICAN AVIATION, INC.
SPACE and INFOR_IATION SYSTE_IS DIVISION
VOLUME:
SECTION: 1
PAGE: 1-14
DATE:
REV, DATE: 2--1--64
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:.=
II
NORTH AMERICAN AVIATION, INC.SPACE and INFORMATION SYSTEMS DIVISION
VOLUME" DIM-5
SECTIOn" 1
PAGE : 1-15
DATE:
REVo DATE "_
¢_ ,,_ IZ M,II
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NORTH AMERICAN AVIATION, INC.SPACE and INFORMATION SYSTEI_IS DIVISION
VOLUME: DIM-5SECTION: ].
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
NORTH AMERICAN AVIATION, INC.SPACE and INFORI_IATION SYSTE_IS DIVISION
VOLUME: DIM-5
SECTION; 1
PAGE: 1-18
DATE:
REV. DATE: 2--1--64
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
NORTH AMERICAN AVIATION, INC.
SPACE and INFORMATION SYSTEMS DIVISION
Volume: DIM-5
Section: 1
Page: 1-19
Date:
Rev Date: 2-1-64
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
NORTH AMERICAN AVIATION, INC.SPACE and INFORMATION SYSTEMS DIVISION
VOLUME: DIM-5
SECTION: 1
PAGE: 1--20
DATE:
REV. DATE:
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
NORTH AMERICAN AVIATION, INC.
SPACE and INFORMATION SYSTEMS DIVISION
Volume: T_T_4-5
Section: 1
Page: 1-20.1
Date:
Rev. Date: 2-1-64
_,_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
NORTH AMERICAN AVIATION, INC. 7
SPACE and INFORMATION SYSTEMS DIVISION
Volume: DIM-_
Section: 1
Page: 1-20.2
Date:
Rev Date: 2-1-6_
l
®
D
STATIC SEAL
SHUTOFF VALVE
RELIEF VALVE POPPET
Figure 1.13.2 Relief & Shutoff Valve Item 5.19
NORTH AMERICAN AVIATION, INC. Volume: DIM-5
SPACE and INFORMATION SYSTEMS DIVISION Section: 1
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
NORTH AMERICAN AVIATION, INC.
SPACE and INFORMATION SYSTEMS DIVISION
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
NORTH AMERICAN AVIATION, INC.SPACE and INFORMATION SYSTEMS DIVISION
Volume:
Section:
Page:Date:
Rev. Date:
"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_
NORTH AMERICAN AVIATION, INC.
SPACE and INFORMATION SYSTEMS DIVISION
Volume: _TM- 5
Section: i
Page: 1-20.5
Date:
Rev Date: 2-1-54
Glycol Evaporator (Water Control Valve)
Figure 1.13.6 Item 5.29
XXi|_l_ai_m m_
NORTH AMERICAN AVIATION, INC.
SPACE and INFORMATION SYSTEMS DIVISION
VOLUME: DIM-5
SECTION: "1
PAGE: "!--2],
DATE:
REV. DATE: 2-1-64
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.
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ILWJL!
_._ NORTH AMERICAN AVIATION, INC
SPACE and INFORMATION SYSTEMS DIVISION
VOLUME: D_--5
SECTION: 1
PAGE [, 1--22
DATE:
REV DATE: 2-1-64
;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
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NORTH AMERICAN AVIATION, INC.SPACE and INFORMATION SYSTEMS DIVISION
Volume: DIM-5
Section: 1
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
NORTH AMERICAN AVIATION, INC.SPACE and INFORMATION SYSTEMS DIVISION
_-- I I I_lil_ IPil'l'l I I .
_I/Vlll I1._ I- • ..... --
Vo Iu me: _ZE]__
Section: 1
Page: 1-_2Date:
Rev. Date: 2-1-64
FI VALVE POPPET
CALIBRATION ADJUSTMENT
Figure 1.24 Relief Valve (Glycol Pressure) Item 2.2
-32::7:_'2"::T1.:-
NORTH AMERICAN AVIATION, INC.SPACE and INFORMATION SYSTEMS DIVISION
Volume: DIM-5
Section: 1
Page: 1-32.1
Date:
Rev. Date: 2-1-64
iii
NORTH AMERICAN AVIATION, INC.
SPACE and INFORMATION SYSTEMS DIVISION
Vo I u me: __DIN=5_
Section: 1
Page: 1-32.2
Date:
Rev Date: 2-1-64
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
NORTH AMERICAN AVIATION, INC.SPACE and INFORMATION SYSTEMS DIVISION
Volume: D._=5Section: 1
Page: 1-3;_. 3Date:
Rev Date: 2-1-64
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
/
NORTH AMERICAN AVIATION, INC.SPACE and INFORMATION SYSTEMS DIVISION
Volume:
Section:
Page:
Date:
Rev. Date:
DIM-5I
1-32_4
2-I-64
BELLOWS
POPPET
n
m
Figure 1.24.4 Manual Shutoff Valve Item 2.28 & 5.18
NORTH AMERICAN AVIATION, INC.SPACE andINFORMATION SYSTEMS DIVISION
Volume:
Section:
Page:Date:
Rev. Date:
DIM-5
I
1-32.5
2-I -64
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
NORTH AMERICAN AVIATION, INC.SPACE and INFORMATION SYSTEMS DIVISION
Volume: DIM-5
Section: 1
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
NORTH AMERICAN AVIATION, INC.
SPACE and INFORMATION SYSTEMS DIVISION
Volume:
Section: 1
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
t
NORTH AMERICAN AVIATION, INC.SPACE and INFORMATION SYSTEMS DIVISION
Volume: DIM-_
Section: 1
Page: 1-32.8
Date:
Rev. Date: 2-1-64
Figure 1.24o8 Glycol GSE Shutoff Valve Item 2.46
__ NORTH AMERICAN AVIATION, INC.
SPACE and INFORMATION SYSTEMS DIVISION
i
vOLUME: DIM- 5
SECTION-" 1
PAGE; 1--3/' ,,DATE:
REV. OATE: 2--1--64
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 -
3 h W W
i
vu0
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oc-o
u
2
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, I
/
/
NORTH AMERICAN AVIATION, INC.SPACE and INFORMATION SYSTEMS DIVISION
VOLUME: 'D I'_--5
SECTION: 1
PAGE: 1--_6
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
Dl'_-5NORTH AMERICAN AVIATION, INC.SPACE and INFORMATION SYSTEMS DIVISION
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
NORTH AMERICAN AVIATION, INC.
SPACE and INFORMATION SYSTEMS DIVISION
VOLUME: DIM-5
SECTION; '_
PAGE: 1--38
DATE:
REV. DATE: 2--1--64
DISCONNECTS
AND/ORFLEX-[
_./__ HEAT EXCHANGE PLATES
I
n_u_, 1.29 RCS ENGINES
N'ORTH AMERICAN AVIATION, INC.SPACE and INFORMATION SYSTEMS DIVISION
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
VOLUME: . DIM- 5
SECTION;
"AGE: 2-1
DATE"
REV. DATE: 2-i-64
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/+
NORTH AMERICAN AVIATION, INC
SPACE and INFORMATION SYSTEMS DIVISION
VOLUME- DIM-5
SECTION: 2
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.
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SPACE and INFORMATION SYSTEMS DIVISION
| | 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
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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
NORTH AMERICAN AVIATION, INC.SPACE and INFORMATION SYSTEMS DIVISION
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
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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
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6O
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312
72O
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4.638
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NORTH AMERICAN AVIATION, INC.SPACE and INFORMATION SYSTEMS DIVISION
VOLUME: Dlq_-5
SECTION: 2
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
NORTH AMERICAN: AVIATION, INC.SPACE and INFORMATION SYSTEMS DIVISION
VO'UME: DIM-5_I....
SECTION: 2
PAGE: 2"8
DATE:
REV. DATE: 2--1--64
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'- ......
NORTH AMERICAN AVIATION, INC.SPACE and INFOR1VIATION SYSTEMS DIVISION
VOLUME: DIM-5
SECTION'. 2
P._E: 2-9OATE:
REV. DATE: _
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
NORTH AMERICAN AVIATION, INC.SPACE and INFORMATION SYSTEMS DIVISION
VOLUME: DIM- 5
SECTION: ;_
PAGE: 2 __] [_j
DATE:
REV. DATE.* _
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.
NORTH AMERICAN AVIATION, INC.SPACE and INFORMATION SYSTEMS DIVISION
VOLUME: DIM-_
SECTION:
PAGE: 2--].]..
DATE:
REV. DATE: _
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.
NORTH AMERICAN AVIATION, INC.SPACE and INFORMATION SYSTEMS DIVISION
VOLUME: DIM=, 5
SECTION: 2
PAGE: 2--]2
DATE:
REV. DATE: 2_1_64
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
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NORTH AMERICAN AVIATION, INC,SPACE and INFORMATION SYSTEMS DIVISION
VOLUM E: DIM- 5
SECTION: 2
PAGE: 2-15
DATE:
REV. OATE:2--1--64
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NORTH AMERICAN AVIATION, INC.SPACE and INFORMATION SYSTEMS DIVISION
VOLUME: :D_--_
SECTION: 2PAGE: 2-16
DATE:
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NORTH AMERICAN AVIATION, INC.
SPACE and INFORMATION SYSTEMS DIVISION
VOLUME: DIM-5
SECTION: 2
PAGE -' 2--17
DATE:
.EV. DATE:2-1-6/+
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NORTH AMERICAN AVIATION, INC.SPACE and INFORMATION SYSTEMS DIVISION
VOLUME: DIM-5
SECTION: 3
P AGE : 3--1
DATE:
REV. DATE: 2--1 ._
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
2-1-64
2-i-6 2-1-64
2-I-64
/
/f_---_ NORTH AMERICAN AVIATION, INC.DIM-5
VOLUME:
SECTION: 3
PAGE: 3-2
DATE:
_E_. DATE: 2--1--64
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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NORTH AMERICAN AVIATION, INC. DI_I-%
SPACE and INFORMATION SYSTEMS DIVISION
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SECTION:
PAGE:
DATE"
REV. DATE:
33-4
2-].-6_
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T1TM_NORTH AMERICAN AVIATION, INC. ---"SPACE and INFORMATION SYSTEMS DIVISION
VOLUME:
SECTION:
PAGE:
DATE:
REV. DATE:
3
3-5 '"
2-1-64
TO ECU SYSTEM
0
0
Figure 3.3 Waste Management System Blower (Centrifugal)
NORTH AMERICAN AVIATION, INC.SPACE and INFORMATION SYSTEMS DIVISION
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REV. DATE:
3
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2-1-6h
MAIN HOUSINGFLEX HOSE
CONNECTION --
BAG INSERT
LATCH
NOZZLE
Figure 3.4 Vacuum Cleaner Assembly Waste Management System
NORTH AMERICAN AVIATION, INC.SPACE and INFORMATION SYSTEMS DIVISION
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SECTION: ]
PAGE: 311"{
DATE:
REV. DATE: 2--1--6l*
r v . ,r_m°
CAM GUIDE
COVER PLATESPINDLE
TE
90 ° FITTING
@END
PLATE
45 ° FITTING
•CAM PLATE
VALVE BODY
SEAL ELEMENT (NEOPRENE)
Figu._e 3.5 Waste Management System Backup Valve
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ACTUAL SIZE
(ROTATED 90 ° )
EAL
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SEAT
PLATE, IDENT
Figure 3.6 Storage Compartment Ventilation System, Check Valve
/
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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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LIST OF CURRENT PAGES
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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
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
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
/
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•
NORTH AMERICAN AVIATION, INC.SPACE and INFOR_IATION SYSTEI_IS DIVISION
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
/
/_ 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
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
NORTH AMERICAN AVIATION, INC.SPACE and INFORMATION SYSTEMS DIVISION
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