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NASA TECHNICAL
MEMORANDUM
A P R E L I M I N A R Y INVESTIGATION OF THE ENV I RONMENTAL CONTROL AND LIFE SUPPORT SUBSYSTEM (ECILSS) FOR THE SPACE CONSTRUCTION BASE MANUFACTURING MODULES
By Hubert 3. Wells Preliminary Design Office
April 1977
NASA
George C. Marshall Space Flight Center
Nar~hall Space F/@t Center, Alabama (~asa-ra-7e123) A P R E L I I I I N A B Y INVES'PIGATICN ~ 7 7 - 2 9 7 8 8 OF THE E N V I B O B M E l Z A L C C l f B C L A I D L I F E SUPPOOT SUBSYSTER (EC/LSS) FOB THE SPACE C O N S P B U C T I C N EASE IANUPACTUBIIG HODULES U nc l a s (NASA) 56 p BC I O U / W F A01 CSCL O 6 K G 3 / 5 U UOBUY
MSFC - F o r m 3190 (Rev June 1971)
https://ntrs.nasa.gov/search.jsp?R=19770022844 2019-12-28T04:55:58+00:00Z
TABLE OF CONTENTS
Page
SUhlMARY ...m.*.m.....e...e..e.e........m..... " * a 1
111. EC/LSS GUIDELINES .ND REQUIREMENTS . . . . . . . . . . . . , 1 7
IV. ATMOSPHERIC S U P P L Y AND PRESSURIZATION ASSEMBLY (ASPA) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 7
V. C 0 2 COLLECTION ASSERIBLI' . . . . . . . . . . . . . . . . . . . . 25
VI. CONTAMINANT CCNTROL ASSERIBLY . . . . . . . . . . . . 30
VII. HUMIDITY AND TEMPERATITRE C O F T R O L ASSEIIBLY . . . . 41
VIII. VENTILATION AND IIODULE FAN ASSEMBLIES . , . . . . . . . 4 1
JX. WATER I lANACEhlENT AND SEPARATOR ASSEMRLY . . . . . 45
X, CONDENSATE STORAGE ASSERTBLY . . . . . . . . . . . . . . 47
XI. MODULE SENSORS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 7
XII. F I R E AND SMOKF DETECTION r lSSEMBLY . . . . . . r . . . . 47
XIII. WEIGHT, VOLUhIE, AND POWER SUMMARY. . . . . . . . . . . . 47
REFERENCES.....*...m....*.*m..**m**..** 48
iii
Figure
L I ST OF ILLUSTRATIONS
Title Page
MSFC six-man initial baseline space construction base. . . . . 2
MSFC space construction base manufacturing modules . . . . . 3
MOSC four-man baseline inboard profile . . . . . . . . . . . . . . 5
HM/SM EC/I,SS overall schematic . . . . . . . . . . . . . . . . . . 6
Space processing prototype biological facility module . . . . . . 7
Space processing directional solidification facility module. . . 8
Space processing crystal ribbon facility manufacturing m o d u l e . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
Prototype crystal ribbon facility . . . . . . . . . . . . . . . . . . . . 10
Biologicals commercial production unit concept. . . . . . . . . . 11
Space processing pmduction biological facility module . . . . . 14
Space processing module (biological EC/LSS) . . . . . . . . . . . 15
Noise criteria curves . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 2
Atmospheric Pressure and Composition Control schematic . . 23
RLSE three-man intermittent metabolic profile cabin P co2 response (closed hatch) . . . . . . . . . . . . . . . . . . . . . . . . . 26
Hamilton atandard contractor (solid amine) concept. . . . . . . 2 8
Molesieve diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29
Trace contaminant control assembly . . . . . . . . . . . . . . . . . 3 1
Orbiter tank envelope and moilnting provisions . . . . . . . . . . 4 5
LI ST OF TABLES
Table Title
a j ' , '..I$-, ,..- 1 -.*. -<%*- * .W?. k', a,, , . . .. . - . .
....................... 1. Biological SPM Expendables.
.................. 2. Manufacturing Mcdule Requirements
..................... 3. Tentative Wash Water Standards
........... 4. Typical Composition of Water to be Reclaimed
5. Atmospheric Pressure and Composition Control ....................... Weights, Volume, and Power
6. Maximum Concentration and Production Rate of Trace ................... ............ Contaminants. .. ......... 7. Contaminant Control Weight, Volume, and Power
8. Contaminant Control Assembly Expendables/Spares ........ 9. Biological Facility EC /LSS Weight, Volume, and Power
summarization.,.........^^....^..^..^.........
19. Water Management Weight Summary ..................
Page
LI ST OF SYMBOLS
APCC 1
I i ASPA
I i BFM
a . . GPL
Hz
HCL
HDC
HF
H z 0
IOC
JSC
Atmospheric Pressure and Composition Control
Atmospheric Supply and Pressurization Assembly
Beam Fabrication Module
Methane
Carbon Monoxide
Carbon Dioxide
Copper Sulphate
Docking Module
Environmental Control and Life Support Subsystem
General Purpose Laboratory
Hydrogen
Hydrochloric Acid
Hydrogen Depolarized Cell
Hydrogen Fluoride
Mercury
Habitability ~odule/Subsystems Module
Water
Initial Operational Capability
Johnson Space Center
Low Earth Orbit
LiOH
LM
MAC
MM
MOSC
MSFC
N2
NASA
NC
0 2
PSM
PSP
RLSE
SC B
SI L
SPM
SPS
SSP
TBD
TDS
TOC
LI ST OF SYMBOLS (Concluded)
Lithium Hydroxide
Logistics Module
Maximum Allowable Concentration
Manufacturing Module
Manned Orbital Space Concepts
Marshall Space Flight Center
Nitrogen
National Aeronautics and Space Administration
Noise Curve
Oxygen
Power Supply Module
Public Service Platform
Regenerative Life Support Evaluation
Space Construction Base
Speech Interference ~ e v e l
Space Processing BIodule
Solar Power Satellite
Space Station Prototype
To Ek Detenxined
Total Dissolved Solids
Total Organic Carbon
vii
TECHNICAL MEMORANDUM 78123
A PRELIMINARY INVESTIGATION OF THE ENVI RONMENTAL CONTROL AND LIFE SUPPORT SUBSYSTEM (ECILSS)
FOR THE SPACE CONSTRUCTION BASE MANUFACTURING MODULES
SUMMARY
This report presents the results of a preliminary study definition of the Environmental Control and Life Support Subsystem ( EC/LSS) for the Space Construction Base (sCB) manufacturing modules. The leading module contenders identifiable a t present a r e the production biological, prototype biological, crystal ribbon, directional solidification, and beam fabrication. These modules a r e 1
subsidiaries of the early, low-Earth orbit (LEO) SCB being studied by the $3
Marshall Space Flight Center ( MSFC) . The basic six-man SCB will consist of a combined Habitability Module/
Subsystems Module (HM/sM), a Logistics Module (LM) , a Docking Module (DM), a Power Supply Module (PSM), a General Purpose Laboratory (GPL), and several Manufacturing Modules (MM's) . Logistics and crew rotation for the SCB and attached modules will be accomplished every 90 days with the Space Shuttle vehicles. The basic envelopes selected initially for the MSFC study a r e illustrated in Figures 1 and 2.
A group of assemblies was selected that was suitable for fulfilling the EC/LSS requirements of a typical manufacturing module. The primary assemblies a r e a s follows: humidity and temperature contml, ventilation and cabin fan, water management and separator, and condensate storage. The use of existing EC/LSS assemblies (such a s Spacelab, Orbiter, and Regenerative Life Support Evaluation (RLSE) ) to perform the manufacturing module EC/LSS functions might prove economical. *)
y This report gives brief descriptions of these assemblies including design
criteiqa; schematics; preliminary weights, volume, and power summaries; and other pertinent information. The overall dry weight of the selected EC/LSS 4 (three-man capacity) is 166.40 kg (366.8 lb) ; it occupies 1.048 m3 (37.0 ft3), , . - and requires 803 W (average) of power.
5
I. INTRODUCTION
The National Aeronautics and Space Adnlinistration (NASA) is performing preliminary studies a t the Johnson Space Center (JSC) , Houston, Texas, and MSFC , IIuntsville, Alabama, on an early SCB. Present SCB planning has scheduled initial operational capability (IOC) for 1934, The SCB will be modular in design to accommodate anticipated growth in capabilities and crew size during its lifetime. Two previous studies, the "Manned Orbital Space Systems Concept (MOSC) Study" [ I ] and the "Space Station Prototype (SSP) ; Environmental/ Thermal Control and Life Support System" [ 2 ] have been utilized a s points of departure. One MOSC configuration is included in Figure 3 for informationd purposes.
The reference SCB configuration i s depicted in Figure 1. Individrlal station modules defined for MOSC were analyzed, modified, and adapted to the reference design. Figure 4 portrays a simplified schematic 9f the HM/SM six- man EC/LSS, which shows the major interfaces among the assemblies, Addi- tional modules (Fig. 2) a r e being added to the reference design base to per- form various functions. Examples a r e the Space Processing Module (sPM) , the Beam Fabrication Module (BFM) , and the Public Service Platform (PSP) . Biologicals and crystal ribbon manufacture occur in the Satellite Power System (SPS) , and extruded beams a r e fabricated in the BFM for the SPS. The purpose of the PSP is to handle personal cornrnunications, ship-to-ship communications, burglar alarm systems, etc, Figures 5, 6, and 7 a r e representative illustrations of the biological, directional solidification, and crystal ribbor SPM's.
Figures 8 and 9 [ 3 ) present schematics of the ribbon growth and biological processes. Ribbon growth is a process in which power is delivered from photo- voltaic cells to an RF heating system o r solar collectors to melt and possibly shape the ribbon. Biological processes such a s tissue culturing by electro- phoresis could drastically reduc8 the cost of drugs.
To standardize the EC/LSS, it was decided to assume a three-man maximum capacity per MM. This would allow the usage of existing EC/LSS assemblies such a s Spacelab o r Orbiter, which might prove economical.
Atmospheric stores ( 0 2 and N2) and drinking water for the MM will be piped in from the aft end of the LM. A crew of two (which is part of the HM/SM crew) will occupy the biological SPM 12 h/day. Table 1 reflects the only SPM consumables [134.7 kg (297 lb) ] necessary for leakage and pressurization. Carbon dioxide removal and atmospheric pressure control will be handled
ORIGINAL PAGE !S OF POOR QUALITY
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TABLE 1. BIOLOGICAL SPM EXPENDABLES
RIodulc 1 aakage Reserve ( 10 pe :;cent)
Requirement -- Initisl R3;dule Pressurization
124.63 m3 ( 4411 ft?)
Ovctmll Requirements 1 66.2 (146) Less Ir ~it ial Pressurization Gases 1 -34-9177)
4
Weight kg (lb)
Total C ryogen Storage
Total 0, and N2
0 2
34.9 ( 77)
a. 1,3E kg ( 3 lb)/module/day
b. C mversion Factor: 2.205 lb/kg and 0.0283 m3/ft?
N2
114.3 (252)
through the HIlVSM EE/LSS. Catalytic oxidizers, presorbent, post-sorbent, and other sorbent beds control contaminants; condensing heat exchanger are employed for humidity control. hlodule temperature control is affected by individual cabin heat exchangerbn units. A thermal control assembly of some type is needed for the HM/SM and each manufacturing module; however, no attempt was made to include the subsystem in the EC/LSS. The overall weight, power, and volume of t'le ECjLSIq a r e given in Section XIII.
I I. ECILSS DESCRIPTION
The EC/LSS provides cabin atmosphere control and purification, water man?.,,,nent, and thermal control for all the MM's. The MM's presently con- sid2red for attachment !o the Space Station a r e space processing and beam fabrication. .Additional modules a r e attached to facilitate the manufacturing such a s GPT., construction, control, and pallets. The production biological SPM was stlicted a s a baseline configuration for all the MM's and associated
modules; Figure 10 presents an illustration which consists of a pressurized enclosure containing biological racks and equipment, and two docking posts. The module provides utilities and an environment conducive to developmental pilot plant and commercial production activities. It is designed to assure ade- quate pi 3tection for proprietary interests, personnel safety, aad quality of space processed !~roducts. At launch, it will be equipped with a full complement of space processing equipment and sufficient supplies to support 90 days of operation.
The SPM EC/LSS is based on a three-man crew with provisions fo r variations in crew size from zero to three men. An economic advantage can be obtained through the use of existing assemblies and components with an IOC of 1984. Existing assemblies and hardware considered for use in this time frame a r e Spacelab, Orbiter, and RLSE. S9acelab assemblies were utilized as much a s possible.
The schematic of the biological SPM EC/LSS is displayed in Figure 11. The EC/LSS provides for SPM ventilation flow, a i r revitalization, module temperature control, and thermal control activities. (This item is not covered in this report.) The a i r revitalization encompasses carbon dioxide, trace con- taminant, humidity, and odor control.
Air from the module is drawn into a filter/debris trap/unit upstream of redundant cabin fans. Check valves shall be provided to prevent recirculation through the inactive fans. One fan shall be normally operating. A differential pressure sensor shall measure and indicate the fan performance. A temperature sensor shall provide a signal to a cabin temperature controller. The catalytic oxidizer unit uses its own fan to draw a certain portion of the a i r from the module for contaminant control and discharges it upstream of the bacteria and prime sorbent beds.
The a i r is then ducted from the cabin fans through the humidity control condensing heat exchanger, which interfaces with the avionics and condensate water loop. The cabin temperature control valve directs a portion of the warm a i r amund the heat exchanger, thereby controlling the temperature of the mixed gas that is returned to the module. The position of the temperature control valve and, subsequently, the amount of a i r bypassed around the heat exchanger is controlled by a sigma1 received fmm duct mounted temperature sensors. This signal is sent to the temperature controller which, in turn, pmvides a positioning signal to the valve actuator. The signal i s based upon a desired cabin tempera- ture dialed into a cabin temperature selector, which is mounted in the cabin. Air bvpass, nl.ther than coolant bypass, is utilized because greater control over
Fig
ure
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CONDENSING Hx
TEMPERATURE CWTROLLER
VENTILATION
f
MANUFACNR ING CLEAN ROOMS AREAS AND
LABORATORY
1 CABIN
- - -- I HX'S
VENTILATION r-- DISTRIBUTION SYSTEM---
-- -- FAN ASSY. r-- DISTRIBUTION SYSTEM-'; - - -- : INLETS, WCTINGS, I I : INLETS, DUCTINGS. I I I DIFFUSERS I I DIFFUSERS I
~--------------------a PARTICULATE L,,,---,,,,,,,,,,- ---I FILTER
r CONTAMINANT MONITORING1 PRIME r---. CONTAMINANT----"-# I A m . I SORBENT MONITORINGASSY. I I------------.--------' L-,,,,,,,,,-,-,,,,,,,
r---- CABIN SENSORS ------ t ----. CABIN SENSORS ------ 4,-----..------------- J L,,,---,,,,,---------J
BACTER l A PARTICbLATE p----FIRE AND m K E w - - - v FILTER ----.FIRE AND SMOKE ----r FILTER I MTECT;ON I ' DETECTION
I L-----,--,---------.-- : --------------------: DEBR 19
DEBRIS FlLTE TRAP
- TO CONDENSATE STORAGE
L \ AVIONICS n20 f INTERFACES
CLEAN ROOMS
i--0lSTRIBUTlON SYSTEM --9
8 INLETS, MICTINGS.
p---. mNfAMINANT------# i--- CONTAlMlNANT -----.r I MONITORINGASY. I ' MONITORING ASSY. L--,,,,,,,,,,-,-,,,,, &I-------------------.
----a CABIN SENSORS ------ L-,,,,,-,,,,,--,,-,-,1
FILTERIOEBRIS TRAI181LENCER
L U o R I A FILTER
AVIONICS H20 A INTERFACES \d
.----------------.--------------------------------- I I HYMOOEN DEPOLARIZED CELL (LOCATED I N HSM) W S M
I 1
O O O W T COOLANT
HUMIDIFIER
TOCABIN = 3
WATER SWARAtOR AQ)V. COWDENSATE STORAOE A m .
TO
CHECK D(8CONNECT CABIN
ILTERIOE%RIS VALVES VALVE
RAWSILENCER
n
ION ICS n20 QlECK VALVIS TANK
AERFACES OVERBOARD W M I I N O
ROTARY W A R ATOR
Figure 11. Space processing module (biological EC/LSS).
~ L D o U T FR A ~r.3
relative humidity can be achieved with varying heat loads. The a i r that passes through the condensing heat exchanger is cooled below the dewpoint to condense excess moisture and remove excessive cabin heat. The condensed moisture shall then pass through the water separator assembly and be delivered into a condensate storage tank.
The hydrogen depolarized cell (HDC) located in the HM/SM receives a i r from the humidity control heat exchanger and removes C02 by an electmchemical process. Upon leaving the HDC, the processed a i r i s returned to the module compartment. Two ventilation fans a r e pro~ided in each module compartme.;lt a s part of the a i r distribution system to improve module a i r velocity to satisfy crew comfort requirements. Adjustable a i r diffusers provide sufficient a i r velocity for crew comfort only in localized areas.
The EC/LSS for the SPM i s composed primarily of Spacelab assemblies with SSP contaminant control derivatives. Since the biological experiments o r requirements a re unknown a t this time, modifications may be required in the EC/LSS. Details a r e included on all the necessary assemblies in the following sections.
Ill. ECILSSGUIDELINES AND REQUIREMENTS
A preliminary listing of the EC/LSS requirements and assumptions necessary to perform a prephase type study for a typical Manufacturing Module i s given in Table 2.
IV, ATMOSPHERIC SUPPLY AND PRESSURIZATION ASSEMBLY (AS PA)
To be compatible with the SCB atmosphere, the biological MM atmosphere will be composed of 21 percent O2 and 79 percent N2 (by volume) a t a total pressure of 101 353 N/m2 (14.7 psia) . The partial pressures for the modules a r e 21 305 N/m2 (3.09 psia) for O2 and 80 048 ~ / r n ~ ( 11.61 psia) for Nn.
"? , /:
Atmospheric stores (02 and N2) will be piped in from the aft end of the LM. Atmospheric leakage i s assumed to be the same a s Skylab, which amounts to 1.35 kg (2 .977 lb) /day/module. This amounts to a lealcige rate of approximately 1.36 kg ( 3 lb) /day, which amounts to 1.043 kg (2.30 lb) /day of O2 and 0.31 kg (0.70 lb) /day of Nz.
TABLE 2. MANUFACTURING MODULE REQUIREMENTS
A. Crew/Passenger Data [in kg (o r lb) / man-day unless otherwise designated]
Number of Crew ( 12 h/day) O2 Consumption, kg (Ib)
Range, kg (lb) C02 Produced, kg (lb)
Range, kg (lb)
B. Manufacturing Module Data
Station Total Pressure, x/m2 (psia) Atmospheric Mixture, (7, volume)
0 2 Partial Presscre, ~ / r n ~ (psia) N2 Partial Pressure, ~ / m ~ (psia) C02 Partial Pressure, Nominal Maxi-
mum, mm Hg (psia) [4] ~0~~ Emergency, Maximum, mm Hg
(psis) 141 Leakage, kg (lb) /day/module Manuhcturing Module Free Volurnc,
m3 (ft3) (Typical) Operational Temperature, "C (OF) Relative Humidity
Resupply Period (days)
C. Trace Contaminants [ 4 ]
L t i; i
4 Requirement
2
0-3 Men 0.839 (1.85j 0.766-0.998 (1.69-2.20) 0.989 (2.18) 0.871-1.215 (I. 92-2.68)
101 353 (14.70) 21 O2 79 N2 21 305 (3.09) 80 048 (11.61)
3.0 (0.058) o r below
15.0 (0.29) 1.36 (3.0)
124.83 (4411.0) 18 to 26 (65 to SO) 6°C (43°F) to 70T> Humidity 90
a. Carbon dioxide partial pressure during emergency operations shall
1. Normal atmosphere leakage shall not be considered as a method of controlling the level of airborne trace contaminants.
2. Expected airborne trace contaminants, initial and nominal production rates and their maximum allowable concentmtions during nominal operational levels a r e TBD.
be maintained below 2000 ~ / r n ~ ( 15.0 mm Hg) (allowable exposure time i s 2 h) [4]
I f I
TABLE 2. (Concluded)
-
3, The riaximum allowable concentration (MAC) of total organics, excliuive of fluorocarbons, is 100 ppm n-pentane equivalents.
4. The MAC of total E'luorocarbons is 100 ppm. 5, The airbarne trace contaminants not permitted in the pa]!s:'d
atmosphere are: Chlorocorbons Cartan Tetrachloride Chloroform Methyl Chloroform Trichloroethylene
Miscellaneous Mercury
The ahove cleaning agents, solvents, o r chemicals should not be used in o r around the payload o r during ma~iilfacture of itt corn ponents.
6, Airborne Particles Contaminant Control [4 ]
The Manufacturing Module life support shall adhere to the Spacelab airborne particle control requirement a s follows:
Airborne particle filtering - 300 p nominal
D. Potable Water (41
Reclaimed water used a s potable water shall meet the requirements of the water quality specification NAS-MSC Specification SD-W-0020,
E. Hygiene Water [ 4 ]
The hygiene water quality specification will be the same a s the wash water specification established by the N a t i o d Academy of Science and shown in Table 3. Typical composition of hygiene waters to be reclaimed a r e shown in Tnble 4,
F. Acoustical Criteria [ 4 1
Continuous noise levels shall not exceed 50 dB in speech i n k - ference level (SIL) range (600 to 4800 Hz) , 70 dB at frequencies below SIL, nor 60 dB at frequencies above SIL. The noise criteria (NC) curves a r e shown in Figure 12.
TABLE 3. TENTATIVE WASH WATER STANDARUS [ 4 ]
Total Organic Carbon (TOC) , mg/l 200
Specific Conductivity, m!J -cm-1 2000
PH 5 t o 7 . 5
Ammonia, mg/l 5
Turbidity, ppnl SiOz 10
Color, Pt-Co Units 15
Foaming Nonpe rsi stant more than 15 s
Odor Nonobj ectionable
Total Dissolved Solids ( TDS) , mg/l 1500
Urea, mg/'l 50
Lactic Acid, mg/l 60
NaC1, mg/l 1000
Microorganisms, Number per ml 10 L
TABLE 4. TYPICAL COMPOSITION OF WATER TO BE RECLAIMED
Note: Conversion factor: 2.205 ; kg.
Materials
Solubles Calcium Chloride Chr mium (hexavalent)
COPP' Magnesium Manganese Nickel Potassium Silver Sodium Zinc Amino Acids Creatinine Glucose Lactic Acid Urea Uric Acid Detergent Germicide
Subtotal
Insolubles Sebum Body Hair, Skin, etc. Clothing lint, etc. Food wastes Particulates
Subtotal
Total Solids b
Shower kg/kg water x 10- (lb/lb water x 10%)
0.19 (0.42) 15.12 (33.34) 0.023 (0.05) 0.454 (1.00) 0.19 (0.42) 0.023 (0.05) 0.023 (0.05) 5.66 (12.47) 3.023 (0.05)
15.12 (33.34) 2.27 (5.00) 0.64 . (1.41) 0.376 (0.83) 0.943 (2.08) 4.72 (10.41) 6.61 (14.58) 0.132 (0.39)
453.51 (1000.00) - 506.027 (1115.79)
13.293 (29.31) 61.247 ( 135.05) - - - 74.54 (164.36)
580.567 (1280.15)
Wash Water kg/kg water x 10'~ (lb/lb water x lod)
0.127 (0.28) 10.08 (22.22) 0.023 (0.05) 0.454 (1.00) 0.127 (0.28) 0.023 (0.05) 0.023 (0.05) 3.77 (8.31) 0.023 (0.05)
10.08 (22.22) 2.27 (5.00) 0.426 (0.94) 0.25 (0.55) 0.626 (1.38) 3.15 (6.94) 4.41 (9.72) 0.086 (0.19)
453.51 (1000.00) - - 489.458 (1079.23)
8.853 (19.52) 40.80 (89.96) -
- -
49.653 ( 109.48)
539.111 (1188.71)
Requency (Hertz)
Figure 12. Noise criteria curves.
C02 r e m o ~ x l and atmospheric pressure control will be handled by the Hhl/SRI and pressure control assembly, respectively. If a sepamte pressure
I control assembly i s required in the MM, the Splcelab assembly can be modified and added. Figure 13 and Table 5 represent a mc dified schematic and weights
i of the Spacelab assembly and a r e included in this report f ~ r information purposes only.
; r The total amount of O2 and N2 requiring storage in the LM cryogenic
bottles (AAP type) is 27.21 kg (60 lb) of O2 and 103.4 kg (228 Ib) of N2 for leakage purposes. The 02[27.21 kg (69 1b)I can be stored in the two O2 bottles provided; however, the 103.4 kg (228 Ib) of N2 will require the addition of another N2 cryogenic bottle for cont~inrnent. The initial 21 percent O2 and 79 percent N2 pressurization gases 184.9 1ig (177 Ib) of O2 and 114.3 kg ( 252 lb) of N2jwill be loaded into the MM on t h e ground. Thus, thc1.e will be no need to contain the initial atmosphere supply in the supply tanks.
The only weight penalty involving the ASPA i s an assumed weight of 24.49 kg (54 lb) for plumbing the various compartments for the SPM.
TABLE 5. ATMOSPHERIC PRESSURE AND COMPOSITION CONTROL WEIGHTS, VOLUME, AND POWER
24
h v r r \W)
2
1
30 1
6
6
1
7 3
1 2
6 0
Total Welght k (lb)
2.934 (6.47)
2.326 ( 5.13)
4.10 (9.04)
1.497 ( 3.3)
5.502 (12.13)
2.500 (5.51)
l.nO0 (3.97) '
0.700 (1.54)
5.08 (11.20)
0.200 (0.4)
ii.ies (24.68)
?
6.:67 (14.02)
44.189 (87.49)
Nomenclature
supply Unit ElrctrIcd Valve (0,) Valve Pomltlon Indcator (01) Presmure Senmot (4) Check Valve Qulck DlrcoMect 0, Supply L l m s
Na Supply U d t Electrical Valve (N*) Valve Pomltlon Indicator (N2) Flow Re8tr lcbr Quick Disconnect N, supply Linea
N, High Pressure Regulator Unlt
ElectrIesl Valve (N2) Valve Posltlon lnd la to r (N2) P m m r e Regulator (N2) Relief Valve (N2) P ressu re Senwr (N2) Check Valve (NI) Hmunl 'jbut4ff Valve (N2) P.ek.glW
Abnorphere P r r s ~ r e C o d m l Ualt
Solenoid Valve (N,) Valve Pos~tlon Indicator (N2) s h ~ t e t l V P ~ = IN,) F lo r hdlcator (N2) Check Valve 1%) Flow Indicator (q) Module Pressure Regulator Mo&le Pressure S e ~ 0 r M a d Shut- N a n d Oxygen Control Valve P.CL.%%
Atmosphere Supply Control Assy.
Partial Pressure Control ler(q) Partlal Pressure Sensor ( q ) Misctllrneous (Elect. IInea.
eoamxlona. ttc. ) -cl=dw
Csbln Pressu re Relief
P ressu re Relief Valve (Pos.) Valve Poaltlon Indicator (Pos. ) Pressure Rellef Valve (Nw.) D e p r e r ~ r l a t t o n Valve Valve Posltlon lnd la to r (Dcprrrn.) P a c k a m
C o m p m e d Supply Unlt ,
h l r d Shut 011 ~ r e a l u r e Regulator Rellef Valre RckUgllIg
Experiment Vent Asmy.
Mamd Bhut4Xl Valve R e r t r l c b r Qulck D l s c o ~ c c t Cabln Bleed Vdve Adrpbr
r a ( M l )
Qunnttty
( 1)
; ) 1 2 1 7
( 1)
! ) 1 ?
(1)
: ] 2 2 1 2 2
(1)
> 1 2 1 2 2 2 2
(1)
1 1
(1 )
2 2 2 1 1
(4)
4 4 4
(4)
4 4 4 4
Dlmrns~ons m (ln.)/ma (R')
0 . 7 9 r 0 . 9 7 ~ 1 . 3 0 (31 x 38 x 51) 0.991 (45)
l . 5 5 ~ 0 . 9 7 ~ 1 . 3 0 (61 \ 38 x 51) 1.955 (69)
0.79 ' 0.19 0.33 (31 x 31 X 13) n.ms (7.2)
0.63 x 1.30 x 0.84 \ 25 x 51 x 33)
.698 (24.34)
0 . 6 3 ~ 0.:8 x 1.30 (25 x 15 * 51) 0.311 (11)
0.63 x 0 . 3 8 ~ 1.30 (25 x 15 x 51) 0.311 (11)
Unlt W e l ~ h t k (lb)
0.635 (1.40)
0.245 (0.54) 0.680 ( 1.50) 0.272 (0.60) 1.102 (2.43)
0.635 (1.40)
0.218 (0.4H) 0.272 10.60) 1.202 (2.65)
0.635 (1.40)
0.726 11.60) 0.901 (2.00) 0.245 (0.54) 0. b8O (1.50) 0.907 (2.0)
0.635 (1.40)
0.635 (1.40) 0.136 10.30) 0.680 (1.50) 0.136 (0.30) 1.882 (4.15) 0.490 (1.0M) 0.454 (1.00) 0.454 (1.00)
1.134 (2.50) 0.490 (1.08) 0.177 10.39)
1.860 (4.1) 0.11" (0.24 1.860 (4.1) 1.134 (2.5) 0.113 (0.25)
1.905 (4.2) 0.870 (1.92) 1.088 (2.40) 2.494 (6.5)
V. C02 COLLECTION ASSEMBLY
The C q collection assembly is employed to remove C02 from the MM and b iw Y
deliver high purity C02 to either a Sabatier o r Bosch reactor (if used) for O2 generation, To assure continuous, long duration controls of this assembly, redundancy will have to be provided through interconnected dud components, maintainability, repair, replacenlent, safety equipment, and spares, C02 i
removal and collection for the MM's will t e accamplished by piping the a i r thrcugh the HM/SM C02 collection assembly, which could be an HDC (six-man Y '
cn~xicity) , a moleseive, o r a Hamilton Standard concentrator,
The CQ collection assembly must maintain all MM's at o r below 3.0 mm IIg (0.058 psiaj even under conditions of maximum C02 generation. Because of mixing and variations in crew activity, the average inlet C02 partial pressure will be approximately 2 mm Hg (0.039 psia) . During emergencies, the C 4 partial pressure (emergency maximum) must not exceed 15 mrn Hg (0.29 psia) (allowable exposure time is 2 h) [3 ] .
Figure 14 is a plot of the RLSE [ 51 three-man intermittent C02 generation and partial pressure responses uneer closed hatch conditions. Tine values m g e d around 2 mm Hg (0.039 psia) o r below for C02 partial pressure and appr ~ximately 0.136 kg (0.3 lb) /h for CQ generation.
Since O2 generation is a likelihood in the larger SCB crews, the MOSC study [ 11 recommended usage of either the molecular sieve o r the HDC with retrofits for closed oxygen loops. The molecular sieve emerged a s the favorite candidate for the McDonnell Douglas Astronautics Company 60 and 90 day manned simulator tests (1971) and Slqlab (1974). The HDC is the MOSC favored candi- date because of the lower power costs and a well developed SSP. The RLSE program singled out three prime candidates for C02 collection, namely the molecular sieve, the Hamilton Standard concentrator (solid amine) , and the HDC. RLSE gave preference to the HDC concept.
The baseline Orbiter iemoves C02 from the cabin by filtering the atmos- phere through lithium hydroxide (LiOH) filters. Rockwell International has completed a preliminary study [ 6 ] to extend the 30 day capability of the Shuttle. The Hamilton Standard solid amine C02 removal concept (referred to as HS-C
5
i
in Reference 6) was designed to adapt to the Orbiter's LiOH C02 removal A'
assembly installation.
-. . A schematic showing the Hamilton Standard concentrator plumbing i s
configured in Figure 15 [ 7 ] . Air drawn fimm the module by a f;n enters the amine sorbent bed, where C02 and H20 a r e removed. The a i r then returns to the module through a valve. A timer operates motor driven valves, which select the absorbing and desorbing canisters. Cold thermal fluid is directed to the t absorbing canisters bj- a solenoid operated valve. This fluid is heated by a heat exchanger before entering the desorbing canister. C02 delivery is difficult because the gas contains considerable water vapor, and a pressure of 40 mm Hg (0.774 psia) is needed for desorption. A condenser-separator and a water- * cooled two-stage vacuum pump-compressor a r e required to deliver C02 from 40 mm Hg (0.774 psia) to 275 790 N/m2 I40 psia) . Condensing will occur in the delivery pump. A bypass line to the absorbing bed inlet i s used during initial desorption to recycle abmrbed and void-volume air, preventing collection of impure C02.
The detailed schematic of C02 removal by molecular sieve i s shown in Figure 16. It consists of two regenerative adiabatic sorbent modules for normal operation and a third module for standby. The condensing heat exchanger is upstream of each molecular sieve module. The moisture from cabin a i r i s removed considerably in the condensing heat exchanger and i s stored in the condensate tank for reuse, Each molecular sieve module comprises (1) an adiabatic sorbent canister with bakeout heater and associated temperature sensor and control, (2) a gas selector valve which directs the process a i r into the bed and back to the cabin o r exposes the bed to vacuum for desorption, (3) a switchover valve which positions the gas selector valve in the l'absorb" o r "desorb" position, and (4) isolation valves to shut off the system in the event of failure. The concept also incorporates three compressors I two a r e redundant units) to reduce bed pressure to 6894.76 N/m2 ( 1.0 psia) before opening the beds to vacuum which reduces the overboard gas loss considerably. Isclation valves a r e provided to isolate any o!le of the compressors and in addition a bypass valve permits operation without the compressor. Much of the equipment in this concept is existing designs from the Skylab.
Under NASA sponsored programs, HDC technology has been developed and evaluated for application to a Space Station EC/LSS. Life Systems, Icc., Cleveland, Ohio, successfully developed and tested a four-man capacity HDC with a four-man cagacity Bosch C02 Reduction Subsystem [ a ] . Existing KDC -. and Bosch reduction subsystem prototypes were refurbished and modified to /'
allow for the integrated operation. A one-man [ 91 and two six-man [ 10,111 self- conklined HDC1s have been developed and experimentally characterized for NASA. Integration of an HDC with Sabatier C02 reduction hardware has been investigated 4 previously.
EL
EC
TR
IC
HE
AT
I
T
I U
SIN
G H
EA
TIN
G F
LU
ID
f FO
R D
ES
IGN
S 2
AN
D 3
Fig
ure
15.
H
amil
ton
sta
nd
ard
con
trac
tor
( sol
id a
min
e) c
once
pt.
The four-man HDC is the C02 removal assembly utilized by the RLSE program. RLSE is a JSC planned payload scheduled for an early 30 day Spacelab mission and is basically the old SSP activities with Hamilton Standard. Figure 4 (overall EC/LSS schematic) relates the associated plumbing for the HDC concept.
Input power for the HDC is not required because the electmchemical concentration process is superimposed on a fuel cell type reaction between O2 and Hz, which generates electricity. Inlet a i r is passed through a humidifier before entering the cell. Within the cell, C02 is tlansferred from the process a i r to an Hz atmosphere through an electrolyte maintained in a porous matrix. Outlet process gas returns to the cabin thmugh the other sidl? of the humidifier where water i s transferred to the inlet stream through a membrane. H2 and O2 a r e continuously supplied to the concentration cell by the electrolysis cell, and a pump delivers the C02 and the excess H2 to an accumulator through a condenser- separator. Electrical power generated continuously by system can be con- ditioned for use o r dissipated.
CONTAM I NANT CONTROL ASSEMBLY
The contaminant control assembly for the MM removes atmospheric con- taminants and maintains contaminant concentrations of less than 0.1 of the industrial threshold limit values. The assembly contains debris and bacterial filters, sorbent beds for ammonia acid and peak contamination production, and a catalytic oxidizer (with a pre- and post-sorbent) for removal of other trace
. contaminants. The RLSE contaminant control assembly is illustrated in Figure 17 [5].
The Lockheed Missiles and Speno Company identified a list of contaminants which was accepted by the JSC under the SSP program 121 a s potential trace con- taminants. These contaminants a l ~ listed in Table 6 together with their maxi- mum allowable concentration and estimates of their generation rates. The SSP ccntaminant model i s based on a crew of six men.
The debris filters prevent particle debris, aerosols, and moisture from entering the MM process a i r ducting and equipment. They consists of a Teflon coated screen (100 mesh) which lies across the outlet a i r duct of the MM. The particulate contaminants include wet and dry debris consisting of water droplets and other liquids, fabric particles, nail clippings, skin flakes, hair, etc.
L I
950
MM
Max
O
B Mou
ntin
g su
rface
'Ais
le
View
(Acc
ess
Face
)
\
All
Line
s Ar
e 1
112"
0
i 4 W
i w
F
igu
re 17.
Tra
ce c
onta
min
ant
con
tml
asse
mb
ly [
5].
800
MM
M
ax
Show
n)
v ,'
I : . I
* L
TABLE % a
6. MAXIMUM CONCENTRATION AND PRODUCTION RATE OF TRACE CONTAMINANTS [ 21
Contaminant
A cetoiie
Acetaldehyde
Acetic Acid
Acetylene
Acetonitrile
Acrolein
Ally1 Alcohol
Ammonia
Amy1 Acetate
Amy1 Alcohol
Benzene
n-Butane
iso-Butane
Butene-1
cis-Butene-2
tmns-Rutene-2
1, 3 Butadicne
iso-Butylene
n-Butyl Alcohol
iso Butyl Alcohol
SCC-BU~Y~ Alcohol
tert-Butyl Alcohol
Maximum Allowable
Concentration ( mg/m3)
240
36
2.5
180
7
0.25
0.5
3.5
53
36
8
180
180
180
180
180
2 20
180
30
30
30
30
Total (gm/day)
10.20
2.50
0.25
2.50 , 0.25
0.25
0.25
14.50
0.25
0.25
2.50
2.50
0.25
2.50
0.25
2.50
2.50
0.25
2.54
0.25
0.25
0.25
Non- Biological ( gm/day)
10.20
2.50
0.25
2.50
0.25
C. 25
0.25
2.50
0.25
0.25
2.50
2.50
0.25
2.50
0.25
2.50
k., 50
0.25
2.30
0.45
0.2ii
0.25
Production Rates
Biological ( gm/da~)
0.0059
0.0023
I
12.0
0.036
TABLE 6. (Continued)
Contaminant
Butyl Acetate
Butraldehydes
Butyric Acid
Carbon Disulfide
Ca rbon Monoxide
Carbon Tetrachloride
Carbonyl Sulfide
Chlorine
Chloroacetone
Chlorobenzene
Chlorofliloromethane
Chlomform
Chloropropane
Caprylic Acid
Cumene
Cyclohexane
Cyclohexene
C yclohexanol
C yclopentane
C yclopmpane
Cyanamide
Decalin
1, 1 Dimethyl cyclohexane
i
J
Maximum Allowable
Concentration 'mg/m3)
I
7 1
70
14
G
29
6.5
25
1.5
100
'. :)
24
24
84
155
2 5
100
100
20
100
100
45
5.0
120
d
Production Rates
Non- Biological ( g m / h ~ )
0,25
0.25
0.25
0.25
Eiolagical ( gm/day)
Total (gm/day)
0.25
0.25
0.25
0.25
2.50 ( 0.4
0.25
0.25
0.25
0.25
0.25
0.25
2.50
0.25
0.25
2.50
0.25
0.25
0.25
0.25
0.25
0.25
0.25
2.9
0.25
0.25
0.25
0.25
0.25
0.25
2.50
0.25
0,25
0.25
2.50
0.25
0.25
0.25
0.25
0.25
0.25
0.25
TABLE 6. (Continued)
Contamimint
t rans 1, 2, Dimethyl C yclohexane
2, 2 Dimethyl Butane '
Dimethyl Sulfide
1, 1 Dichlomethane
Di iso Buwl Ketone
1, 4 Dioxane
Dimethyl Furan
Dimethyl Hydrazine
Ethane
Ethyl Alcohol
Ethyl Acetate
Ethyl Acetylene
Ethyl Benzene
Ethylene Dichloride
Zthyl Mher
Ethyl Butyl Ether
Ethyl Formate
Ethylene
Ethylene Glycol
t n n s 1, Methyl ,' Ethyl Cyclohexane
Ethyl Sulfide
E thy1 Me rcaptan -
. nilcximum
Allowable Concentration
( mg/m3)
120
93
15
40
29
36
3.0
0.1
180
190
140
180
44
40
120
200
30
180
114
117
97
2.5
Non- Biological ( g m / d a ~ )
0.25
0.25
0.25
2.50
0.25
2.50
0.25
0.25
2.50
2.50
2.50
0.25
0.25
0.25
2.50
0.25
2.50
2.50
0.25
0.25
0.25
0.25
Production Rates
Biological ( g m / d a ~ )
0.12
Total (gm/day)
0.25
0.25
0.25
2.50
0.25
2.50
0.25
0.25
2.50
2.62
2.50
0.25
0.25
0.25
2.50
C. 25
2.50
2.50
0.25
0.25
0.25
0.25
TABLE 6. (Continued)
Contaminant
Freon 11
Freon 12
Freon 21
Freon 22
Freon 23
Freor 113
Freon 114
Freon 114 unsyin
Freon 125
Formaldehyfle
Fumn
Furfural
Hydrogen
Hydrogen Chloride
Hydmgen Fluoride
Hydrogen Sulfide
Heptane
Hexene-1
n-IJ exane
Hexamethylcyclotri- sihemne
Indole
Isoprene
Methylene Chloride
Maximum Allowable
Concentration (mg/m3)
560
500
420
3 50
12
700
700
700
25
0.6
3
2
2 15
0.15
0.08
1.5
200
180
180
240
126
140
2 1 A
Non- Biological [ W I / ~ ~ Y )
2.50
2.50
0.25
0.25
0.25
0.25
2.50
0.25
0.25
0.25
0.25
0.25
2.50
0.25
0.25
0.25
0.25
2.50
0.25
0.25
0.25
2.50
Production Rates
Biological (gm/&y)
0. G
0.0007
1.2
Total f gm/dny)
2.50
2.50
0.25
0.25
0.25
0.25
2.50
0.25
0.25
0.25
0.25
0.25
3.10
0.25
0.25
0.0009
0.25
0.25
2.50
0.25
1.45
0.25
2.50
TABLE G. (Continued)
Contaminant
Methyl Acetate
Rlethyl Butyrate
Methyl Chloride
2-Methyl-1 Butene
hlethyl Chlorofolln
hIethyl Fumn
Methyl Ethyl Ketone
Methyl Isobutyl Ketone
RIethyl Isopropyl Ketone
Methyl Cyclohe=ne
Methyl Acetylene
Methyl Alcohol
3-hlethyl Penhne
RIethy 1 Rlcthacrylate
Methane
hlesitylene
mono hlethyl Hydr~zine
Methyl Mrrcnptan
Naphthalene
Nitric Oxide
Nitrogen Tetroxide
Nitrogen Dioxide
Maximum Allowable
Concentration ( mg/mg)
6 1
30
21
1430
190
3
59
4 1
70
200
165
2 (i
295
4 1
1720
2.5
0.035
2
5.0
32
1.8
0.9
Non- Biological ( gm/day)
2.50
0.25
0.25
0.25
2.50
0.25
2.50
0.25
2.50
0.25
0.25
2.50
0.25
0.25
29.5
0.25
0.25
0.25
0.25
0.25
0.25
Production Rates
Biological ( gm/day)
0.12
7.2
Total ( gm/day)
2.50
0.25
0.25
0.25
2.50
0.25
2.50
0.25
2.50
0.25
0.25
2.62
0.25
0.25
36.7
0.25
0.25
0 . 2,s
0.25
0.25
0.25
0.25
TABLE 6. ( Continued)
Contaminant
Nitrous Oxide
Octane
Propylene
iso-Pentane
n-Pentane
Pentene-1
Pentene-2
Propane
n-Propyl Acetate
n-Propyl Alcohol
iso-Propyl Alcohol
n-Propyl Benzene
iso-Propyl Chloride
iso-Propyl Ether
Proprionaldehyde
Propionic Acid
Propyl Mercaptan
Propylene Aldehyde
Pyruvic Acid
Phenol
Sliatol
Sulfur Diorj de
Styrene
Tetnchloroethylene !
?
Maximum Allowable
Concentration (mg/m3)
47
235
180
29
295
180
180
180
84
75
98
44
260
120
30
15
82
10
0.9
1.9
14 1
0.8
42
67
Non- Biological ( gm/day)
0.25
0.25
2.50
2.50
2.50
0.25
0.25
2.50
0.25
2.50
2.50
0.25
0.25
0.25
0.25
0.25
0.25
0.25
0.26
0.25
0.25
Production Rates
Biological ( gm/day)
4.53
4.53
Total ( gm/day)
0.25
0.25
2.50
2.50
2.50
0.25
0.25
2.50
0.25
2.50
2.50
0.25
0.25
0.25
0.25
0.25
0.25
0.25
4.53
4.78
0.25
0.25
0.25 I
0.25
TABLE 6. ( Continued)
Note: The following a r e pertinent chemical synonyms for Table 6:
.
2-Duranone = Methyl ethyl ketone
Chlorodifluoromethane = Freon 22
C rotonaldehyde = Propylene aldehyde
Decahydronapl~thalene = Decalin
1, 2 Dichloroethane = Ethylene chloride = Ethylene dichloride
Dichlorodifluoromethane = Freon 12
>
Maximum Allowable
Concentxation ( mg/m3)
-
205
59
75
52
49 I
140
70
110
130
60
20
44
44
44
Contaminant
Tetrafluomethylene
Tetmhydmfurane
Toluene
Trichloroeth ylene
1, 2, 4 Trimetllyl Bezene
1, 1, 3 Thrimethyl cyclohexane
Valeraldehyde
Valeric Acid
Vinyl Chloride
Vinyl Methyl Ether
Vinyldene Chloride
0-Xylene
m-Xylene
p-Xylene
Production Rates
Non- Biological
(gm/da~)
0.25
0.25
2.50
2.50
0.25
0.25
2.50
0.25
0.25
2.50
2.50
2.50
Biological ( gm/day)
Total ( fZm/da~)
0.25
0.25
2.50
2.50
0.25
0.25
0.25
0.25
2.50
0.25
0.25
2.50
2.50
2.50
Dichlorofluoromethane = Freon 2 1
Dichlorotetrafluorethane = Freon 114
p-Dioxane = 1, 4 Dioxane I-
: 2-Methyl Butanone-3 = 3-Methyl 2 Butanone = Methyl isopropyl ketone
Methoxy Ethane = Vinyl methyl ether
Propene = Propylene
Propyne = Propone + Methyl acetylene
Pentafluoroethane = Freon 125
Perchloroethylene = Tetrachlomethylene
Trichlorofluoromethane = Freon 11
Trichlorotrifluoroethane = Freon 113
Trifluoromethane = Fluoroform = Freon 23
1, 3, 5 Trimethyl Benzene = Mesitylene
The bacteria filters consist of prefabricated depth filters that consist of continuous sheets of binderless fiber mat folded and separated by a corrugated separator made of a ceramic material. Blockage of the filter is caused pri- marily by dust build-up, not the bacteria. Effective bacterial removal efficiency is 95 percent with a 0.3 p particle size. The filters must be designed to operate in a class 100 000 clean room, which approximates the McDonneil Douglas Astronautics Company 60 and 90 day manned chamber tests.
Trace contaminants, combustible gases, odors, hydrocarbons, etc. , a r e removed by a combination of sorbent beds and a catalytic oxidizer. Sorbent beds a r e utilized primarily for ammonia, whereas the catalytic oxidizer controls CO, Hz, CHI, benzene, and other combustible gases.
The catalytic oxidizer has its own blower and operates independently of other elements of the circuit. Module a i r flows through two prefilter beds (con- taining LiOH and CuS04 coated smbeads) , and thence through the catalytic oxidizer, and then thrmugh a post-sorbent bed. The oxidizer contains a regenera- tive heat exchanger, an electric a i r heater, and a catalyst bed.
LiOH is used a s the protective material for the first pre-sorbent and post-sorbent beds. As a pre-sorbent mate rial, LiOH will effectively remove such compounds a s SO2, HP, S, HCI and HF. As a post-sorbent, it will also
& 1.
remove acid gases such a s HC1 and H F , which might be created in the oxidiza- p i
tion process. The second pre-sorbent bed, containing CuS04 coated sorbeads . . 4
is used for ammonia and basic (high pH) compound control. - < * ' 7 '.,
The prime sorbent bed removes ammonia and handles peak odor pmduc- , , f 4 tions. A CuSOa coated silica gel (6-10 mesh size) sorbent type R is used because
of its high ammonia capacitr. Primary odor control is provided by the catalytic oxidizer.
t . Tables 7 and 8 depict the unit parts list, component quantities, spares, g C . ':!
and expendables, a s well as component weights, volumes, and powers. The installation envelope for the assembly is 95.00 x 48.01 x 80.01 cm (37.4 x 18.9 x 31.5 in. ) Ci appmximately 0.365 m3 ( 13 ft3). Sparing the catalytic oxidizer and the sorbent canisters is not considered necessary. These com- ponents a r e considered inherently reliable. Should a failure occur, the HM/SM contaminant control assembly is capable of performing the functioils.
. i
V I I . H U M I D I T Y A N D TEMPERATURE CONTROL ASSEMBLY LT .
Module a i r cooling and humidity control is provided downstream of the - . . . HM/SM HDC (CO* removal assembly) by a condensing heat exchanger which
interfaces with the water loop, Condensed moisture adheres to the surface of the heat exch~nger fins by surface tension. At the outlet of each heat exchanger - a i r passage, a series of holes a r e provided to draw off a secondary flow consist- ing of a mixture of a i r and water. This mixture then passes through the water separator assembly containing redundant motor driven rotary separators.
Module iemperature control is achieved by a bypass around the condensing heat exchanger. Air flow is modulated through the heat exchanger according to I the control signals of the selected module temperature and the temperature
r : sensors upstream of the cabin fans and downstream of the condensing heat $ d exchanger.
The weight, volume, and power for this assembly a re given in Table 9.
V I I I. VENT:LATION AND MODULE FAN ASSEMBLIES
In the cabin a i r loop, a i r is drawn from the module into a filter/debris trap assembly upstream of redundant module fans. Check valves are provided to prevent recirculation through the inactive fans. Normally, one fan shall be operating. A differential pressure sensor measures and indicates fan performance.
< -
i r i
1 f a, Contaminant Control Assembly Envelope = 95.30 x 48.01 x 80.00 cm
d 1 (37.40 x 18.90 x 31.50 in.) = 0.365 m3 (12.88 ft3)
Number Weight Power Component Required kg (Ib) (w)
Debris Trap 1 0.227 (0.5) b
Pre-Sorb Canister 2 6,984 ( 15.4) b
Post-Sorb Canister 1 3.492 (7.7) b
Chemi-Sorb Canister 1 4.535 ( 10.0)
Fan 1 5.896 f 13.0) 83.5
Catalytic Oxidizer 1 4.717 ( 10.4) 97.5 (Est.)
Regenerative Heat Exchanger 1 1.134 (2.5)
b, Expendable part of installed unit i s replaced on day 90
c. Fault detection instrumentation.
Controller, Catalytic Oxidizer b
Bacteria Filter
valve, Solenoid Shut-Off
Valve, Manual Shutaf f
Gas Chromatograph C
Flowmeter C
Temperature Sensor C
Differential Pressure Sensor
Voltage sensorC
Total
1
1
4
7
1
1
1
1
1
1.361 (3.0)
3.855 ( 8.5)
3.265 (7.2)
2.540 (5.6)
3.401 (7.5)
0.136 (0.3)
0.091 (0.2)
0.317 (0.7)
0.136 (0.3)
42.087 ( 92.8)
TBD
- 183
V ) , e cd c4
a 0 )
2 , 8 R
n n
r(
9-g
* h
63 .d -
, A 2
0
n
a m a .i 2~ SrnG
e n W6,s
'S - 3 3
A c, - 9 4 C,
0'
*
h n & N
- ! 00 $ . d S ? c 3 g 0 - 4 a o o
e m 4 - b ; = E , . a o r - d o . ; ; : 0 , . g , m 7 m 0 o m w m . G ' ( O d d 0
n - h O n 0 . m . 0 m . ua - l-l I-, 4
L - - - g y M W O o D 0 m ( O m
o ' d d d
3 d d d
h
3 00 d .
n 4
n 0 4 v
l-l 4 c'a - z -a
. L o d' d
a m CD Q)
CD 0
0 m 0 0
In .
0
n A m .
0 L L 0
L - O O E - R1 OI
N 01 .
0 0
$ 4 0 0
B & E
rl k a,
m s 'i: e
o a c 2 0 U d $ "
TA
BL
E 9
. B
IOL
OG
ICA
L F
AC
ILIT
Y E
C/L
SS
WE
IGH
T,
VO
LU
ME
, A
ND
PO
WE
R S
UM
MA
RIZ
AT
ION
t
Ass
emb
ly
0,
Pip
ing
N2
Pip
ing
Pre
ssu
re C
on
tro
l
CO
z C
oll
ecti
on
Co
nta
min
ant
Co
ntr
ol
Co
nta
min
ant
Mo
nit
ori
ng
Hu
mid
ity
an
d T
emp
erat
ure
C
on
tro
l
Mod
ule
Fan
Ven
tila
tio
n F
an
H20 T
ank
an
d P
lum
bin
g
Co
nd
ensa
te S
tora
ge
Wat
er S
epar
ato
r
Ov
erb
oar
d D
um
pin
g
Mod
ule
Se
nso
rs
Fir
e/S
mo
ke
Det
ecti
on
To
tal
Nu
mb
er
Req
uir
ed
1
1
1
1
2 1
1
1
1 - TBD
Sel
ecte
d
Can
did
ate
1/2
in.
L
ine
(E
st. )
112
in.
Lin
e (E
st.)
SS
P (
Lo
cate
d i
n
HM
/SM
)
RL
SE
( L
oca
ted
in
H
M/S
M)
RL
SE
Sp
acel
ab
Sp
acel
ab
Sp
acel
ab
Sp
acel
ab
Orb
ite
r
Sp
acel
ab
Sp
acel
ab
Sp
acel
ab
Sp
acel
ab
Sp
acel
ab
Dry
Wei
ght
kg (
lb)
24.4
9 (5
4)
- -
42.0
9 (9
2.8
)
1.36
0 (3
)
28.5
7 (6
3)
16.3
3 (3
6)
5.44
(1
2)
28.1
7 (6
2)
10.4
3 (2
3)
' 4
.99
(11
)
3.17
(7
)
1.36
(3
)
TB
D
166.
40
(36
6.8
)
Vol
ume
m3
(ft
3)
? - -
0.36
5 (1
2.9
)
0.01
4 (0
.5)
0.02
8 (1
.0)
0.14
2 (5
.0)
(Est
. )
0.00
6 (0
.2)
0.43
9 (1
5.5
)
0.05
1 (1
.8)
0.00
3 (0
.1)
Neg
.
Neg
.
TB
D
1.04
8 (3
7.0
)
Av
erag
e P
ow
er
(w) - - -
18
3
80
19
30
3
75
3 20
11
5
5
TS
D
80
3
Two vmtilation fans are provided a s part of the a i r distribution system to improve a i r velocity according to crew comfort requirements.
Weights, volumes, and power values for these assemblies are shown in Table 9.
IX. WATER MANAGEMENT AND SEPARATOR ASSEMBLY
Potable water for the MM's i s furnished by the SCB water assembly located onboard the MM. It i s piped to the MM and stored in a single Orbiter waste water tank. This tank weighs 15.65 kg (34.5 lb) empty and can contain 74.83 kg ( 165 lb) of water. However, due to prior use residual and error, the tank has an actual mission usable storage capacity of 68.48 kg ( 151 lb). An estimated weight (28.12 kg/62 lb) of this tank ( Fig. 18) and its associated accessories i s given in Table 10.
Figure 18. Orbiter tank envelope and mounting provisions ( side view).
TABLE 10. WATER MANAGEMENT WEIGHT SUMMARY
i a. Each 393.7 mm (15 1/2 in.) diameter by 901.7 mm (35 1/2 in.) long
Water vapor is condensed from the MM atmosphere by the condensing t
heat exchanger. The condensate 1eavir.g the condensing heat exchanger shall be entrained i r the form of water droplets.
Component
H20 Tank (Orbiter) a
H20 Residuals
GM2 Tank, 101.6 mm ( 4 in.) Diameter
Chiller
Silver Ion Generator
Solenoid Valve
shut-Off Valves
Flowmeters (H20)
Flowmeter Couplers
Check Valve
Cap
Quick Disconnect
Pressure and Quantity Instrumentation
Water Outlet
Plumbing
Total
The condensed moisture is then passed through the water separator ! assembly (Skylab extraction) containing redundant motor driven r o t a ~ j separa-
tors. The water i s separated from the a i r by centrifugal effect and delivered t into a condensate storage tank. Then the a i r i s returned to the cabin. At ths a i r inlet and wate;. outlet of each separator, check valves shall be provided to prevent water backflow. Speed sensors shall be p n l d e d to give indication of g separator performance. The weight, volume, and power for the water separator assembly i s included in Table 9.
Number Required
1
1
1
1
1
2
2
2
1
1
1
1
?
Weight
kg (lb)
15.65 (34.5)
6.35 ( 14.0)
0.454 (1.0)
0.907 (2.0)
0.816 (1.8)
0.091 (0.2)
1.088 (2.4)
0.363 (0.8)
0.082 (0.18)
0.150 (0.33)
0.136 (0.30)
0.181 (0.40)
0.771 (I. 7)
0.227 (0.5)
0.907 (2.0)
28.17 (62.11) I
X. CONDENSATE STORAGE ASSEMBLY
Condensate separated in the interfacing water separator assembly will be delivered to the condensate storage tank. The condensate quantity i s measured by a quantity sensor. A manually operated shut-off valve is provided to isolate the condensate tank from the water separator and overboard dumping assemblies ( Tzble 9).
X I . MODl'LE SENSORS
Various sensors a r e required in the module for measuring temperature, prebsurt?, humidity, etc. The weight and power for these sensors a r e given in Table 3.
X I I. FIRE AND SMOKE DETECTION ASSEMBLY
The fire/smoke detection assembly consists of independently operating ionization sensors. These sensors shall give signals to genemte an alarm in response to incipient fire conditiona in the module.
X I I I . WEIGHT, VOLUME, AND POWER SUMMARY
An overall weight, vomme, and power breakdown of the MM EC/LSS constituents is given in Table 9. These values amount to 166.4 kg (377 lb) , 1.048 m3 (37.0 €t3), and an average power of 803 W.
REFERENCES
McDonnell Douglas A stmnautics Company - West: Manned Orbj tal Systems Concepts (MOSC) Study. MDCG 5919, September 30, 1975.
Hamilton Standard: Space Station Prototype (SSP) ; Environmental,/ Thermal Control and Life Support System, August 1971.
Grumman A emspace Corpomtion: Space Station Systems Analysis Study, Mission Requirements Handbook, NSS-SS-TR 009, Contract NAS8-31993, September 1, 1976.
Hamilton Standard: Regenerative Life Support Evaluation (RLsE) Per- formance and Interface Specification, Specification No. SVHS 7216, Revision B, June 1, 1976.
Hamilton Standard: Integration and Design Study for a Regenerative Life Support Evaluation (RLsE) ; Concept Design Review, Octobcr 5, 1976.
Rockwel International: Shuffle Orbiter Capability Extensior-,, Report No. SD75-Sll-0218.
Hamilton Standard: Trade-Off Study and Conceptual Designs of Regenera- tive Advanced Integrated Life Support Systems (AILSS) , Contrast NAS1-7905, July 1969.
Life Systems, Incorporated: Integration of the Electrochemical Depolar- ized C 0 2 Concentrator with the BOSCH C02 Red~lction Subsystem, Final Report No, NAS CR-1-44248, March 1976.
~ i f e Systems, I n ~ o r p ~ r a t e d : One-blain, Self-Contained Carbon Dioxide Concentrator Subsystem, Final Report No. NASA CR-114426, March 1972.
Life Systems, Incorporated: Six-Man, Self-Contained Carbon Dioxide Concentrator Subsystem for Space Stntion Prototype (SSP) Application, Final Report No. NASA CR-114742, May 1973.
Life Systems, Incorporated: Six-Man, Self-Contained Carbon Dioxide Concentrator Subsystem, Final Report No. NASA CR-114743, June 1974.
APPROVAL
A PRELIM I NAR Y INVEST1 GAT1 ON OF THE ENV I RONMENTAL CONTROL AND LIFE SUPPORT SUBSYSTEM (ECILSS)
FOR THE SPACE CONSTRUCTION BASE MANUFACTURING MODULES
By Hubert B. Wells
The information in this report has been reviewed for security classifi- cation. Review of any information concerning Department of Defense o r Atomic Energy Commission programs has been made by the hISFC Security Classifica- tion Officer. This report, in its entirety, has been determined to be unclassified.
This document has also been reviewed and approved for technical accuracy.
CHHRLE~ H. DARWIN Director, Preliminary Design Office
Q U.S. GOVERNMENT PRINTING OFFICE 1977-7400901363 REGION NO. 4
