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ASEN5116Spacecraft Life Support Systems

FINAL TRADE STUDY REPORT

ECLSS System for theNASA Mars Design Reference Mission

December 16, 2002

ByEarth Replications, Inc.

ContributingEngineers:

Vanessa AponteSteve Chappell

Markus CzupallaNancy Kungsakawin

Nicholee PageJesse Riggert

Tommy Romano

ERI

ASEN5116 Final ReportSpacecraft Life Support Systems

TABLE OF CONTENTS1.0 INTRODUCTION.......................................................................................12.0 SYSTEM & MISSION REQUIREMENTS................................................1

2.1 Mission Overview....................................................................................12.2 System Overview & Requirements Summary.........................................12.3 Metabolic Load Basis..............................................................................22.4 Baseline System Architecture..................................................................3

3.0 SYSTEM & MISSION ASSUMPTIONS...................................................64.0 TRADE STUDY PROCESS & PHILOSOPHY.........................................6

4.1 Identification of Requirements................................................................74.2 Selection of Trade Variables...................................................................74.3 Determination of Weighting Factors.......................................................84.4 Specification Sheets.................................................................................84.5 Data Analysis...........................................................................................84.6 Results......................................................................................................9

5.0 ATMOSPHERE MANAGEMENT...........................................................105.1 Baseline Functional Requirements........................................................105.2 Baseline Architecture.............................................................................105.3 Subsystem Assumptions........................................................................115.4 Candidate Technologies.........................................................................115.5 Subsystem Technology Trade Studies & Design Decisions..................13

5.5.1 C02 Reduction & Removal, O2 Provision, N2 Provision....................145.5.2 Trace Contaminant Control...............................................................155.5.3 Temperature & Humidity Control.....................................................155.5.4 Ventilation..........................................................................................165.5.5 Monitoring & Control........................................................................165.5.6 Fire Detection & Suppression............................................................165.5.7 Results................................................................................................175.5.8 Conclusions and Recommendations..................................................19

5.6 Atmosphere Management Subsystem References.................................196.0 WATER MANAGEMENT.......................................................................21

6.1 Water Management................................................................................216.2 Water Monitoring..................................................................................22

6.2.1 Flow Chart for Water Monitoring.........................................................256.3 Water Generation...................................................................................266.4 Water Processing...................................................................................27

6.4.1 Fire Detection & Suppression............................................................276.4.2 Baseline Architecture.........................................................................286.4.3 Potable and Hygiene Water Processing.............................................29

6.4.3.1 Candidate Technologies..............................................................296.4.3.2 Infeasible Technologies..............................................................296.4.3.3 Technology Trade Study.............................................................29

6.4.4 Urine Processing................................................................................306.4.4.1 Candidate Technologies..............................................................306.4.4.2 Infeasible Technologies..............................................................306.4.4.3 Technology Trade Study.............................................................30

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6.4.5 Closed Loop Architecture..................................................................316.5 Conclusions and Recommendations......................................................336.6 Water Management Subsystem References...........................................33

7.0 WASTE MANAGEMENT........................................................................347.1 Baseline Functional Requirements........................................................347.2 Baseline Architecture.............................................................................347.3 Subsystem Assumptions........................................................................357.4 Subsystem Technology Trade Studies...................................................35

7.4.1 Candidate Technologies.....................................................................367.5 Results....................................................................................................39

7.5.1 Batch and Continuous Incineration (BI, CI)......................................407.5.2 Electrochemical Oxidation (EO).......................................................417.5.3 Gasification (GAS)............................................................................417.5.4 Supercritical Water Oxidation (SCWO)............................................417.5.5 Pyrolysis (PYRO)..............................................................................417.5.6 Plasma Arc Oxidation (PAO)............................................................417.5.7 Trade Study Process..........................................................................42

7.6 The Integrated System...........................................................................437.7 Failure Analysis.....................................................................................457.8 Conclusions and Recommendations......................................................457.9 Waste Management Subsystem References..........................................46

8.0 FOOD SUPPLY.........................................................................................488.1 Baseline Functional Requirements........................................................488.2 Baseline Architecture.............................................................................508.3 Subsystem Assumptions........................................................................528.4 Candidate Technologies.........................................................................528.5 Subsystem Technology Trade Study.....................................................53

8.5.1 Results................................................................................................548.6 Food Supply Subsystem References......................................................55

9.0 SYSTEM INTEGRATE DESIGN RESULTS..........................................579.1 System Architecture...............................................................................579.2 Mass Balance Results............................................................................609.3 Equivalent System Mass Results...........................................................60

10.0 SYSTEM CONCLUSIONS & RECOMMENDATIONS.........................6311.0 APPENDIX A: REQUIREMENTS..........................................................64

11.1 Atmosphere Management......................................................................6911.2 Water Management................................................................................7411.3 Waste Management...............................................................................7511.4 Food Supply...........................................................................................76

12.0 SUBSYSTEM PHYSICAL/CHEMICAL PROCESS FLOW SCHEMATICS..........................................................................................77

12.1 Atmosphere Management......................................................................7712.2 Water Management..............................................................................10912.3 Waste Processing.................................................................................123

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TABLE OF FIGURESFigure 2-1 Human Input / Output Diagram (NASA Tech 109927, 1994)..........................3Figure 2-2 Open Loop Subsystem Mass, Volume and Power Totals..................................4Figure 2-3 Open Loop System Diagram..............................................................................5Figure 4-1 Trade Study Process...........................................................................................7Figure 5-1 Open Loop AM Subsystem..............................................................................11Figure 5-2 AM Subsystem Diagram Transit.....................................................................17Figure 5-3 AM Subsystem Parameters..............................................................................18Figure 5-4 AM Subsystem Diagram - Mars Surface.........................................................18Figure 6-1 The Order of Monitoring Devices....................................................................26Figure 6-2 Open Loop Diagram w/ Flow Rates in kg/day for 6 Crewmembers...............28Figure 6-3 Closed Loop Water Management Flow Diagram............................................31Figure 7-1 WP Open Loop Diagram.................................................................................35Figure 8-1 Food Subsystem Baseline Open Loop Design.................................................50Figure 8-2 Food Supply Comparison Graph.....................................................................53Figure 8-3 Closed Loop Design for Food Supply Subsystem...........................................54Figure 9-1 System Block Diagram – Transit.....................................................................57Figure 9-2 System Block Diagram - Surface.....................................................................58Figure 9-3. Final Design Subsystem Mass, Power and Volume.......................................60

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1.0 INTRODUCTIONThis trade study report was written for the Fall 2002 semester Spacecraft Life Support Design course at the University of Colorado Department of Aerospace Engineering Sciences. It is a preliminary analysis of current life support system technologies and the design of an integrated system. It was based on the NASA Design Reference Mission (DRM) for Mars, Addendum 3.0. This report is intended to summarize the results of the analysis and design activities. The responsibilities and personnel involved in this study are shown in Table 1-1

Table 1-1 Personnel and Responsbilities

Responsibility PersonnelProgram Manager Tommy RomanoSystems Engineer Steve ChappellAtmosphere Management (AM) Steve Chappell & Markus CzupallaFood Supply (FS) Tommy RomanoWaste Processing (WP) Vanessa Aponte & Nicholee PageWater Management (WM) Nancy Kungsakawin & Jesse Riggert

2.0 SYSTEM & MISSION REQUIREMENTS2.1 Mission Overview

The mission for which the ECLSS is designed is based on the NASA Design Reference Mission (DRM) for Mars. The mission is a multistage mission that will send 6 astronauts to live on the surface of Mars for an extended period. The overall mission requires the use of several vehicles that must contain an ECLSS: an Earth Return Vehicle, a Crew Transit/Surface Habitat, and a Crew Ascent Vehicle. The Crew Transit/Surface Habitat will be used to transport the crew of 6 from Earth to the Mars surface. After the Mars surface stay, the Crew Ascent Vehicle will be used to leave the surface of Mars and rendezvous with the Earth Return Vehicle already in orbit about Mars. Once the crew is on-board the Earth Return Vehicle, it will perform the transfer and bring the crew back to Earth. The DRM also identifies overall mission parameters and constraints, such as the need for the systems to be able to operate without re-supply for the duration of the mission. For further details, a full listing of mission requirements is given in Appendix A.

2.2 System Overview & Requirements SummaryThe ECLSS system design encompasses the life support system on board the Crew Transit/Surface Habitat. As specified by the DRM, the life support system onboard the Earth Return Vehicle will be a duplicate of the Crew Transit/Surface Habitat that arrives in orbit around Mars prior to the departure of the Crew Transit/Surface Habitat with the crew onboard.

The ECLSS is broken down into four subsystems:

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Atmosphere Management (AM), Food Supply (FS), Waste Processing (WP), and Water Management (WM).

These four subsystems work together in an integrated system that provides all of the necessary functions of the ECLSS. Specific functional and derived requirements for each subsystem are provided in the subsystem sections as well as in Appendix A.The main system-level driving requirements are:

Provide life support functions for a crew of 6; 180 worst-case transit time between Earth and Mars, 600 day worst-case surface stay on Mars, Perform the entire mission assuming no resupply from Earth, Take advantage of ISRU when possible, Target life support system mass of 4661 kg + consumable weight, Target life support system power usage of 12.1 kW, Operate during launch, transit, descent, and surface g-loads, Provide 2 levels of backup redundancy, Do not rely on biological systems for life support functions, Provide as much loop closure as possible, Reliability, maintainability, and safety.

These driving requirements were primary considerations in the overall design. Other derived requirements were placed on the system and subsystems to define the system further. These details can be found in the subsystem sections and in Appendix A.

2.3 Metabolic Load BasisFigure 2-1 shows the metabolic input and output of each crew member. These numbers were based on chemical compositions of the input and output constituents. Values used in the following sections are based on these baseline values in calculations requiring consumables and processables.



Inputs Outputs

Dry Food kg/per-daySafety Factor

Total kg/per-

day

Total For Six

People (kg)

Total For Six

People (kg)

Total kg/per-

daySafety Factor kg/per-day Solid Wastes

Protein C4H5ON C2H6O2N2 UrineCarbon 0.0770 1.1 0.0847 0.5082 0.1056 0.0176 1.1 0.0160 CarbonHydrogen 0.0081 1.1 0.0089 0.0535 0.0264 0.0044 1.1 0.0040 HydrogenOxygen 0.0257 1.1 0.0283 0.1696 0.1406 0.02343 1.1 0.0213 OxygenNitrogen 0.0225 1.1 0.0248 0.1485 0.1234 0.02057 1.1 0.0187 Nitrogen

Carbohydrates C6H12O6 C42H69O13N5 Feces

Carbon 0.1489 1.1 0.1638 0.9827 0.1168 0.01947 1.1 0.0177 CarbonHydrogen 0.0250 1.1 0.0275 0.1650 0.0158 0.00264 1.1 0.0024 HydrogenOxygen 0.1984 1.1 0.2182 1.3094 0.0482 0.00803 1.1 0.0073 Oxygen

HUMAN 0.0158 0.00264 1.1 0.0024 Nirogen

Fat C16H32O2 Carbon 0.0858 1.1 0.0944 0.5663 C13H28O13N2 SweatHydrogen 0.0144 1.1 0.0158 0.0950 0.0488 0.00814 1.1 0.0074 CarbonOxygen 0.0143 1.1 0.0157 0.0944 0.0092 0.00154 1.1 0.0014 Hydrogen

0.0653 0.01089 1.1 0.0099 OxygenLiquids (H2O) 0.0086 0.00143 1.1 0.0013 Nitrogen

Potable Hydrogen 0.1802 1.1 0.1982 1.1893 Liquid (H20)Oxygen 1.4298 1.1 1.5728 9.4367

UrineFood Prep 1.1174 0.18623 1.1 0.1693 Hydgrogen

Hydrogen 0.0884 1.1 0.0972 0.5834 8.8704 1.4784 1.1 1.3440 OxygenOxygen 0.7016 1.1 0.7718 4.6306

Food Content Feces

Hydrogen 0.1287 1.1 0.1416 0.8494 0.0673 0.01122 1.1 0.0102 HydrogenOxygen 1.0213 1.1 1.1234 6.7406 0.5320 0.08866 1.1 0.0806 Oxygen

Gases

Air Sweat & PerspirationOxygen 0.8359 1.1 0.9195 5.5169 1.6988 0.28314 1.1 0.2574 Hydrogen

13.4831 2.24719 1.1 2.0429 OxygenHygiene H2O 9 1.1 9.9000 59.4000 Laundry H2O 12.5 1.1 13.7500 82.5000 Gases

11846 kJ/per-day CO2 Carbon DioxideTotal weight per day 174.9396 kg Heat Load 71076 kJ/6per-day 1.7860 0.29766 1.1 0.2706 CarbonTotal weight per year 63852.95 kg 25942740 kJ/6per-year 4.7579 0.79299 1.1 0.7209 Oxygen

59.4000 9.9 1.1 9 Hygiene H2O

82.5000 13.75 1.1 12.5 Laundry H2O

Mass Balance 0.0020 174.9376 kg Total weight per day63852.23 kg Total weight per year

Figure 2-1 Human Input / Output Diagram (NASA Tech 109927, 1994)

2.4 Baseline System ArchitectureThe baseline open loop ESM was calculated with the information provided in

Figure 2-2. This figure show the breakdown of each subsystem and its’ components and the values that were obtain or estimated for Mass, Power and Volume. The additional weight column provides inclusion of consumables, such as LiOH canisters, piping and storage tank components.



OPEN LOOP ESMAtmosphere

Component # Weight (kg)

Add. Weight

(kg)

Total Weight

(kg)Power (kW)

Total Power (kw)

Volume (m3)

Total Volume

(m3)

Crew Time

(hrs/day)Oxygen Consumable 1 4303.21 0.00 4303.21 0.00 0.00 0.00 0.00 0.00Oxygen Buffer Tank 1 1463.09 0.00 1463.09 0.60 0.60 0.00 0.00 0.00CO2 Removal 1 5104.24 0.00 5104.24 0.00 0.00 0.00 0.00 0.67LiOH 1 5548.09 1109.62 6657.71 0.00 0.00 0.00 0.00 0.00Nitrogren Consumable 1 1288.00 0.00 1288.00 0.00 0.00 0.00 0.00 0.00Nitrogen Buffer Tank 1 695.52 0.00 695.52 0.60 0.60 0.00 0.00 0.00

Totals 19511.77 1.20 0.00 0.67

Water


Add. Weight

(kg)

Total Weight

(kg)Power (kW)

Total Power (kw)

Volume (m3)

Total Volume

(m3)

Crew Time

(hrs/day)Potable Water 1 128957.40 0.00 128957.40 0.00 0.00 0.00 0.00 0.50Water Tank 1 43845.52 0.00 43845.52 0.00 0.00 0.00 0.00 0.00

Totals 172802.92 0.00 0.00 0.50

Waste


Add. Weight

(kg)

Total Weight

(kg)Power (kW)

Total Power (kw)

Volume (m3)

Total Volume

(m3)

Crew Time

(hrs/day)Toilet assembly 1 16.00 19.20 35.20 0.22 0.22 0.08 0.08 0.08Septic tank 1 14.50 2.90 17.40 0.00 0.00 0.10 0.10 0.00Compactor 1 15.10 10.84 25.94 0.11 0.11 0.36 0.36 0.00Non-processables Storage 1 50.00 0.00 50.00 0.00 0.00 2.00 2.00 0.08

Totals 128.54 0.33 2.53 0.17

Food


Add. Weight

(kg)

Total Weight

(kg)Power (kW)

Total Power (kw)

Volume (m3)

Total Volume

(m3)

Crew Time

(hrs/day)Dehydrated Food 1 3192.27 420.00 3612.27 0.00 0.00 37.00 37.00 3.50Microwave 2 70.00 14.00 154.00 1.80 3.60 0.15 0.30 0.00

Totals 3766.27 3.60 37.30 3.50

Grand Totals 196209.51 5.13 39.83 4.83

Figure 2-2 Open Loop Subsystem Mass, Volume and Power Totals

By using the Equations (1), the total system ESM was calculated to be 196,663 kg.

(1)

This mass was used as the baseline of comparison for the developed system to see the improvements made as more loop closure is obtained. A diagram depicting the baseline open-loop system is shown in Figure 2-3.



HumanHuman

FoodFood

WaterWater

WasteWasteStorageStorage

PreparationPreparation

ProcessingProcessing

PotablePotable

Laundry Laundry

HygieneHygiene

Monitoring

Monitoring

BiologicalBiological

NonNon--BiologicalBiological

ChemicalChemicalStabilizationStabilization

DumpDump

AtmosphereAtmosphereCOCO22 ReductionReduction

OO22 StorageStorage

NN22 StorageStorage

VentilationVentilation

MonitoringMonitoring

FDSFDS THCTHC TCCTCC

StorageStorage

6.5446.544

5.5175.517

PressurePressureControlControl

16.89716.8975.2145.214

0.6140.614

10.62610.626

59.459.4

82.582.5

167.669167.669Waste WaterWaste Water

Solid Solid WasteWaste

0.7240.724

13.67813.678 StorageStorage

All values are in kg/day for 6 All values are in kg/day for 6 crew memberscrew members

Spent LiOH Spent LiOH

HumanHuman

FoodFood

WaterWater

WasteWasteStorageStorage

PreparationPreparation

ProcessingProcessing

PotablePotable

Laundry Laundry

HygieneHygiene

Monitoring

Monitoring




DumpDump

AtmosphereAtmosphereCOCO22 ReductionReduction

OO22 StorageStorage

NN22 StorageStorage

VentilationVentilation


FDSFDS THCTHC TCCTCC

StorageStorage

6.5446.544

5.5175.517

PressurePressureControlControl

16.89716.8975.2145.214

0.6140.614

10.62610.626

59.459.4

82.582.5

167.669167.669Waste WaterWaste Water

Solid Solid WasteWaste

0.7240.724

13.67813.678 StorageStorage

All values are in kg/day for 6 All values are in kg/day for 6 crew memberscrew members

Spent LiOH Spent LiOH

Figure 2-3 Open Loop System Diagram



3.0 SYSTEM & MISSION ASSUMPTIONSSeveral assumptions were made at the system level that affected the overall design. The main assumptions were:

Mission Duration: The DRM listed several different values for the length of the transit phase, ranging from 120 days to 180 days. Additionally, the surface stay was listed as from 500-600 days. For this design, worst case was assumed for the transit and the surface stay, 120 days and 600 days, respectively.

Safety Buffer: Since a detailed analysis on appropriate safety buffers for each technology was not performed, a 10% safety buffer was assumed for all subsystems.

In-Situ Resource Utilization (ISRU): The DRM details the contents of an ISRU plant that will be taken to Mars on board the Cargo Lander. The ISRU plant contains equipment to produce resources from the Martian atmosphere. It was assumed that this plant is in place and that it will be interfaced with the Crew Transit/Surface Habitat upon landing.

Duplicate Systems: It was assumed that the Crew Transit/Surface Habitat and the Earth Return Vehicle have duplicate life support systems and that each system only has to handle a one-way transfer of 180 days.

4.0 TRADE STUDY PROCESS & PHILOSOPHYThe trade study process used in the selection of the technologies for the ECLSS consists of several steps. The steps of the process are depicted in Figure 4-4 and explained in the remainder of this section.



Requirements

TechnologyResearch

TradeMatrix

SpecSheets

SpecSheets

TradeMatrix

Integrate System

Assess System

Final System

••MassMass••PowerPower••VolumeVolume••TRLTRL••Op. Temp.Op. Temp.••Op. PressureOp. Pressure••HeatHeat

Requirements

TechnologyResearch

TradeMatrix

SpecSheets

SpecSheets

TradeMatrix

Integrate System

Assess System

Final System

••MassMass••PowerPower••VolumeVolume••TRLTRL••Op. Temp.Op. Temp.••Op. PressureOp. Pressure••HeatHeat

Figure 4-4 Trade Study Process

4.1Identification of RequirementsThe requirements for the subsystems were first identified. The high level mission and system requirements were derived mainly from the NASA DRM for Mars. The high-level mission and system requirements were flowed down and allocated to the subsystems where applicable. Additional requirements for the subsystems have been derived from analysis of existing systems and systems undergoing research and development.

4.2Selection of Trade VariablesThe trade variables used in the subsystem’s trade studies are based on the subsystem’s requirements and typical assessment criteria for manned space systems. Qualitative and quantitative criteria were taken into account via the identified trade variables. The trade variables are a subset of the overall specification data collected for each candidate technology. Table 4-2 shows a general table of trade variables that are later modified based upon the subsystem and specific trade.



Table 4-2 General Trade Study Variables

Trade VariablesComponent Weight (kg)Additional Weight (kg)Power (kW)Volume (m3)Heat Generated (kW)Operating Temperature (K)Operating Pressure (kPa)Designed Efficiency (%)TRL (1-9)ReliabilityMaintainabilityGravity DependenceCrew Time - OperationsSafetyLifetime CostProspective Improvements

4.3Determination of Weighting FactorsWeighting factors were applied to the trade variables to be used in the technology candidate selection process. These served to set the relative importance of a particular trade variable in relation to the others. Assignment of weighting factors allowed for comparison of all necessary trade variables without less important trade variables overpowering more important trade variables. The weighting criteria for trade variables were assigned by each subsystem for its trade studies.

4.4Specification SheetsSpecification sheets were developed for each candidate technology containing all parameters and trade variables where data is available. The specification sheets served as the repository for the raw trade study data from which data was extracted for input to the trade matrices. See Appendix B for all of the specifications sheets for candidate technologies considered in the design.

4.5Data AnalysisTrade study variables from the specification sheet for each candidate technology were extracted and input into a trade matrix for each required function. The trade matrices assessed how well each candidate technology will meet the optimal trade variables. Weighting factors were applied to adjust the overall importance of particular trade variables. Additionally, an uncertainty percentage was applied to each input value for the trade variables so that the sensitivity to each variable could be more readily assessed. The uncertainty percentage allowed maximum, nominal, and minimum values to be computed to assess the impact of the uncertainty on the trade matrix outcome. Additionally, the trade variable input values were scored based upon a linear normalization; i.e. the scores for each value ranged from 0.0-1.0. The highest score



achieved was intended to be the winner. Scoring and normalization for each trade variable is shown in Table 4-3.

Table 4-3 Scoring & Normalization Scheme

Trade Variables Scoring/NormalizationComponent Weight (kg) 1 for lowest & 0 for highestAdditional Weight (kg) 1 for lowest & 0 for highestPower (kW) 1 for lowest & 0 for highestVolume (m3) 1 for lowest & 0 for highestHeat Generated (kW) 1 for lowest & 0 for highestOperating Temperature (K) 1 for lowest & 0 for highestOperating Pressure (kPa) 1 for lowest & 0 for highestDesigned Efficiency (%) 1 for highest & 0 for lowestTRL (1-9) 1 for highest & 0 for lowestReliability 1 for highest & 0 for lowestMaintainability 1 for highest & 0 for lowestGravity Dependence 1 for ‘no’ & 0 for ‘yes’Crew Time - Operations 1 for lowest & 0 for highestSafety 1 for highest & 0 for lowestLifetime Cost 1 for lowest & 0 for highestProspective Improvements 1 for highest & 0 for lowest

4.6ResultsThe results of the trade studies took into account the data analysis of the trade variables using the trade matrices. Additionally, other program and mission level considerations affected the overall decision. A description of the selected technologies is supplied as well as rationale for the selections in the subsystem sections of this document.



5.0 ATMOSPHERE MANAGEMENTThe Atmosphere Management (AM) subsystem is designed to continuously control and regenerate the module atmosphere. It monitors the status of the atmosphere for gas composition as well as any contaminants deemed harmful. Additionally, it serves as a warning mechanism through the detection and suppression of on-board fires. The following sections will go over the requirements, process, and results of the design of the AM subsystem.

5.1 Baseline Functional RequirementsThe atmosphere management functions of the ECLSS are provided by the AM subsystem and include the following:

CO2 Removal

CO2 Reduction

O2 Provision

N2 Provision

Atmosphere Monitoring and Control

Gas Storage

Ventilation

Trace Contaminant Control

Temperature and Humidity Control

Fire Detection and Suppression

The AM subsystem interfaces with the other subsystems of the ECLSS as necessary to provide the overall functions required for life support. For additional details on the requirements of the AM subsystem see Appendix A.

5.2 Baseline ArchitectureThe baseline architecture of the AM subsystem is based upon a completely open loop design. Figure 5-5 shows the architecture. It includes processing of CO2 by LiOH only. This produces 13.6 kg/day of spent LiOH for 6 people. N2 and O2 provision is covered completely by cryogenic storage. The remainder of the functions of the AM subsystem is supplied by existing systems in use on ISS or STS (e.g. trace contaminant control system, condensing heat exchanger, etc.). This system was used as the basis of comparison as the system was modified to a closed-loop configuration.



S p e n t L iO H= 1 3 .6 k g /d a y

6 .5 k g /d a y C O 2

5 .5 k g /d a y O 2

H u m a nH u m a n

F o o dF o o d

W a te rW a te r

W a s teW a s teS to ra g eS to ra g e

P r e p a ra t io nP r e p a ra t io n

P r o c e s s in gP r o c e s s in g

P o ta b leP o ta b le

L a u n d ry L a u n d ry

H y g ie n eH y g ie n e

Mo

nito

ring

Mo

nito

ring

B io lo g ic a lB io lo g ic a l

N o nN o n --B io lo g ic a lB io lo g ic a l

C h e m ic a lC h e m ic a lS ta b il iz a t io nS ta b il iz a t io n

D u m pD u m p

A tm o s p h e r eA tm o s p h e r eC OC O 22 R e d u c t io nR e d u c t io n

OO 22 S to ra g eS to ra g e

NN 22 S to ra g eS to ra g e

V e n t i la t io nV e n t ila t io n

M o n ito r in gM o n i to r in g

F D SF D S T H CT H C T C CT C C

S to ra g eS to ra g e

6 .5 4 46 .5 4 4

5 .5 1 75 .5 1 7

P r e s s u reP r e s s u reC o n t ro lC o n t ro l

1 6 .8 9 71 6 .8 9 75 .2 1 45 .2 1 4

0 .6 1 40 .6 1 4

1 0 .6 2 61 0 .6 2 6

5 9 .45 9 .4

8 2 .58 2 .5

1 6 7 .6 6 91 6 7 .6 6 9W a s te W a te rW a s te W a te r

S o l id S o l id W a s teW a s te

0 .7 2 40 .7 2 4

1 3 .6 7 81 3 .6 7 8 S to ra g eS to ra g e

A ll v a lu e s a r e in k g /d a y fo r 6 A l l v a lu e s a r e in k g /d a y fo r 6 c re w m e m b e rsc re w m e m b e rs

S p e n t L iO H S p e n t L iO H

S p e n t L iO H= 1 3 .6 k g /d a y

6 .5 k g /d a y C O 2

5 .5 k g /d a y O 2

H u m a nH u m a n

F o o dF o o d

W a te rW a te r

W a s teW a s teS to ra g eS to ra g e

P r e p a ra t io nP r e p a ra t io n

P r o c e s s in gP r o c e s s in g

P o ta b leP o ta b le

L a u n d ry L a u n d ry

H y g ie n eH y g ie n e

Mo

nito

ring

Mo

nito

ring

B io lo g ic a lB io lo g ic a l

N o nN o n --B io lo g ic a lB io lo g ic a l

C h e m ic a lC h e m ic a lS ta b il iz a t io nS ta b il iz a t io n

D u m pD u m p

A tm o s p h e r eA tm o s p h e r eC OC O 22 R e d u c t io nR e d u c t io n

OO 22 S to ra g eS to ra g e

NN 22 S to ra g eS to ra g e

V e n t i la t io nV e n t ila t io n

M o n ito r in gM o n i to r in g

F D SF D S T H CT H C T C CT C C

S to ra g eS to ra g e

6 .5 4 46 .5 4 4

5 .5 1 75 .5 1 7

P r e s s u reP r e s s u reC o n t ro lC o n t ro l

1 6 .8 9 71 6 .8 9 75 .2 1 45 .2 1 4

0 .6 1 40 .6 1 4

1 0 .6 2 61 0 .6 2 6

5 9 .45 9 .4

8 2 .58 2 .5

1 6 7 .6 6 91 6 7 .6 6 9W a s te W a te rW a s te W a te r

S o l id S o l id W a s teW a s te

0 .7 2 40 .7 2 4

1 3 .6 7 81 3 .6 7 8 S to ra g eS to ra g e

A ll v a lu e s a r e in k g /d a y fo r 6 A l l v a lu e s a r e in k g /d a y fo r 6 c re w m e m b e rsc re w m e m b e rs

S p e n t L iO H S p e n t L iO H

Figure 5-5 Open Loop AM Subsystem

5.3 Subsystem AssumptionsThe following assumptions were significant in the design of the AM subsystem:

ISRU via extra life support equipment on the precursor cargo mission is available. This assumption significantly reduced the size and weight of the AM subsystem by designing them for the 180-day transfer (with safety buffer).

The ISRU equipment on the precursor cargo mission will provide EVA gas makeup. This allows for much smaller N2 and O2 stores on the transfer vehicle.

Thermal control equipment to support the cabin air temperature and humidity control system is available as part of the other vehicle systems and is not included in the life support system

5.4 Candidate TechnologiesA list of candidate technologies was established to satisfy the requirements for the AM subsystem. The candidate technologies are identified in Table 5-4 and are mapped to the function for which they were investigated to provide; in bold are the technologies that were analyzed more in depth for this design. Many technologies were eliminated from the study based on the lack of information, low technology readiness level, and other design factors. The following sections go over further trade studies and design decisions that were used to narrow the technology options.



Table 5-4 Candidate Technologies for Atmosphere Management

Atmosphere Management Function Candidate Technologies

CO2 Removal 2-Bed Molecular Sieve20

4-Bed Molecular Sieve20

Electrochemical Depolarization Concentration (EDC) 20

Air Polarized Concentration (APC) 20

Solid Amine Water Desorption (SAWD) 20

LiOH20

Temperature Swing Adsorption6,5,21,22

Osmotic Membranes20

Electroactive Carriers20

Metal Oxides20

Carbonate20

Ion-Exchange Electrodialysis20

Sodasorb20

Superoxides20

Solid Oxide Fuel Cells8,15,3

Pressure Swing Adsorption1

CO2 Reduction Bosch20

Sabatier20

Advanced Carbon Formation Reactor20

Solid Oxide Electrolysis23

CO2 Electrolysis20

Superoxides20

Iron Direct Reduction1

Reverse Water Gas Shift Reaction with Microreactors25

O2 Provision High Pressure Storage Tanks20

Cryogenic Storage Tanks20

Solid Polymer Water Electrolysis (SPWE) 20

Solid Oxide Electrolysis23

H20 Electrolysis20

Static Feed Water Electrolysis (SFWE) 20

Water Vapor Electolysis20

CO2 Electrolysis20

O2 from Chemical Compounds20

Superoxides20

Artificial Gill20

Water Splitting by Visible Light9

N2 Provision High Pressure Tanks20

Cryogenic Tanks20

Thermal Catalytic Dissociation of Hydrazine20

Dissociation of Ammonia20

Modular Pressure Swing Adsorption10

Vacuum Pressure Swing Adsorption11

Atmosphere Monitoring & Control

Mass Spectrometer/Gas Chromatograph20

Ion Trap Mass Spectroscopy/ Mass Spectroscopy20

Fourier Transform IR Spectroscopy20

CFU Analyzer20

Ventilation Air Diffusers and Intakes20

Trace Contaminant Control Particulate Filters20

Activated Charcoal20

Chemiabsorbant Beds20



Atmosphere Management Function Candidate Technologies

Catalytic Burners20

Reactive Bed Plasma (RBP) 20

Super Critical Water Oxidation20

Temperature & Humidity Control

Condensing Heat Exchange (CHX) 20

Fire Detection & Suppression Obscuration Smoke Detector20

Scattering Smoke Detector20

UV/Visible/IR Flame Detector20

CO2 Fire Suppression System20

N2 Fire Suppression System20

Halon Fire Suppression System20

Condensation Nuclei Counter20

Ionization Smoke Detector20

5.5 Subsystem Technology Trade Studies & Design DecisionsThe following sections go over the trade studies and design decisions that led to the selection of the technologies that make up the AM subsystem. The general trade study process described in earlier sections. For weighting criteria within the trade studies, different values were used for each function, but in general the following guidelines were followed by the AM subsystem:

Mass was given a high weighting factor mainly due to its importance in launch costs;

Reliability was given a high weighting factor due to the long-term, isolation aspects of the mission;

TRL was given a high weighting factor due to its relevancy in tested systems; Power was given a mid-range weighting factor due to the general abundance

of power from solar and nuclear sources during the mission; Volume was given a mid-range weighting factor due to the limited volume of

the transfer vehicle; Medium to low weighting factors were generally assigned to operating

temperature, operating pressure, prospective improvements, and maintainability.

Additionally, certainty factors were applied to each value in the trade matrices with the following general guidelines:

100% Number confirmed through multiple references 75% Number from reference or based on reasonable assumptions 50% Number based on reference with questionable assumptions 25% Number based only on assumptions 0% Slightly educated guess

These values were used to look at the sensitivity of our results based on the certainty of the input data. For further information regarding each technology and to see associated trade matrices, see Appendix B.



5.5.1 C02 Reduction & Removal, O2 Provision, N2 ProvisionThe design of the C02 reduction, C02 removal, O2 provision, and N2 provision systems were addressed together and were iterated upon independent from the remaining systems in the AM subsystem. Initially, the winners from the trade matrices were chosen and integrated together, adding buffer tanks, piping, etc., to achieve a baseline for the AM subsystem. Although this system was fully functional, the initial weight was estimated at 4227 kg for these functions of the AM subsystem. It was decided to investigate other options to attempt to reduce the overall mass. The options considered and implemented were:

The solid oxide electrolysis system was chosen even though it did not win in the trade matrix comparison for CO2 reduction or O2 provision. However, the solid oxide electrolysis system can perform both functions. Therefore, the scores from both trade matrices were added together, showing solid oxide electrolysis to win. It is a low mass system compared with the alternatives and it eliminates the need for a CH4 storage tank (as is necessary with the Sabatier reactor). Additionally, it reduces the necessary size of the H2 tank due to the decrease in losses of H2 in CH4. The disadvantage of solid oxide electrolysis is that its power requirements are about 3 times as much as the other two candidates combined, but the benefits are still worth the change.

A main assumption was to use ISRU for the provision of buffer gases. This is the reason why the storage tanks for the buffer gases are only designed for the transfer of 180 days and not for 780 days, as in the first system. The two buffer gases needed are O2 and N2. While the N2 buffer is the main source to allow for pressure maintenance, the O2 buffer takes care of the reaction inefficiencies.

The N2 buffer is sized as follows: The N2 needed to account for the whole transfer leakage of 26 kg (transfer both ways) (BVAD 1999 [page. 21]). The tank weight is 0.524 kg tank/kg gas. Therefore, 13.7 kg was arrived at for the tank weight. The volume was computed using the density of liquid Nitrogen, thus the total N2 buffer tank weight is 39.7 kg. Without being able to close the N2 loop with, for example, ammonia dissociation, ISRU is the only way to stay within reasonable mass limits. The reason is that on the surface multiple EVA´s will be performed. This accounts for a large gas loss (1280 kg due to BVAD 1999 page. 21). This gas loss is too large to be able to bring all the necessary gas from Earth.

The O2 buffer is sized as follows: A 10% loss of O2 due to reaction inefficiencies with the crew needing 5.5 kg O2 per day was assumed. With a transit of 180 days, this means 100 kg of O2 is needed. Using pressurized tanks, 0.364 kg tank/kg gas has to be added. Therefore, we arrived at 36.4 kg of additional weight for the tank. The volume is computed using the density of gaseous O2.

Both N2 and O2 will be provided for the transfer only. On the surface of Mars, those buffer gases will be provided directly by utilizing the Martian Atmosphere. From this atmosphere, CO2 and an N2/Ar mixture can be obtained by using the Temperature Swing Adsorbtion technique (K.R. Sridhar



“Utilization of Martian Atmosphere Constituents by Temperature-Swing Adsorbtion”). The CO2 will then be taken apart by the Sabatier reactor which already is in place (DRM Addendum). The H2 for the Sabatier reaction will be brought from Earth in the Cargo vehicle (DRM Addendum) until H2O sources have been located on Mars.

The penalty of ISRU is that the facilities to extract gas from the Martian atmosphere needs to be added. In particular, this is the Temperature-Swing Adsorbtion plant. The weight is 72 kg, which is a small price to pay for reducing the system mass by the factor of 10. In addition, this TSA system is able to act as a backup for CO2 concentration during transit. The only thing to consider when choosing that option is that the cooling system has to be designed such that it can simulate the Martian temperature change during night and day. This task remains to be solved when designing the transfer vehicle. Even if this should turn out to be too difficult to achieve, the 72 kg is a price which one clearly would be willing to pay.

5.5.2 Trace Contaminant ControlThe trade study to pick the technology to be used for trace contaminant control considered a few options: Super-Critical Water Oxidation (SCWO), Reactive Bed Plasma (RBP), and a conventional Trace Contaminant Control Subsystem (TCCS). The conventional TCCS consists of activated charcoal beds, a catalytic oxidizer, a lithium hydroxide bed, a fan system, flow meters, and an electronic control interface. This type of system is in use on the ISS and is well understood, reliable, and lightweight. SCWO and RBP technologies are both universal waste-processing systems that use air as part of their processing. Since the air is subject to the same processing as the waste, the trace contaminants in the air can be destroyed and the air returned to the cabin. Therefore, they do not meet the requirement to provide continuous trace contaminant control.

The conventional TCCS was chosen to provide trace contaminant control for the life support system mainly due to its light weight, high TRL, and overall effectiveness. Additionally, HEPA filters are used in conjunction with the TCCS to provide high-efficiency particulate control as air is drawn into the ventilation system within the cabin. See Appendix B for more details on the technologies.

5.5.3 Temperature & Humidity ControlTechnologies to perform temperature and humidity control are limited. The most utilized and effective technology for temperature and humidity control consists mainly of a Condensing Heat eXchanger (CHX). The CHX works in conjunction with fan systems, temperature controls, check valves, water separators, and damper valves. The CHX system was chosen for temperature and humidity control for the life support system. See Appendix B for more details on the technology.

5.5.4 VentilationVentilation within the crew cabin is generally performed with various fan, ducting, and valve systems. It is necessary to move air with a portion of the cabin as well as between different floors or modules of the overall cabin. Additionally, it is necessary to be able to



control ventilation within specific areas for the purposes of fine-tuning the ventilation speed as well as to be able to stop the circulation of smoke in the case of fire. A system similar to the ISS was selected that uses intercabin fans, intracabin fans, and a valve control system to achieve the necessary ventilation. See Appendix B for more details on the chosen technologies.

5.5.5 Monitoring & ControlThe monitoring technologies involved in the trade study were: conventional ISS Major Constituent Analyzer (MCA), Gas Chromatograph/ Mass Spectrometer (GC/MS), and Fourier-Transform Infrared Spectrometer. The conventional MCA is based on ISS technologies that include a mass spectrometer for constituent analysis. Recent research and development of GC/MS technology has produced a miniature, space-rated version that performs well and is very lightweight. Mass was the major driver that caused the mini-GC/MS to be chosen for the monitoring technology.

Pressure control technology consists of pressure monitoring sensors and valve systems that can adjust the overall cabin pressure and partial pressures of major constituents. This technology is quite developed and there is little variation in methods from one system to another. A system similar to the ISS pressure control system was chosen for this life support system. See Appendix B for details on the technology.

5.5.6 Fire Detection & SuppressionTechnologies for smoke and fire detection include: scattering smoke detectors, ionization smoke detectors, condensation nuclei counters, obscuration smoke detectors, and UV/IR flame detectors. Scattering and obscuration smoke detectors are quite simple technologies that work well. Condensation nuclei counters and ionization smoke detectors are somewhat more complex and bit heavier than their counterparts. UV/IR flame detectors function to supplement the smoke detectors in warning the crew of an on-board fire. A system of scattering smoke detectors in UV/IR flame detectors was chosen for the life support system based on heritage use in the ISS.

Fire suppression will be handled in the life support system via the use of Portable Fire Extinguishers (PFEs). PFEs are small, pressurized tanks that can be operated by the crew to put out a cabin fire. They can be filled with CO2, N2, or Halon. Since Halon is toxic in large concentrations, it was not chosen as the fire suppressant. CO2 was chosen over N2 for fire suppression since there is an effective way to remove the excess CO2 from the environment via the CO2 removal system after the fire is put out. For more details on the technologies, see Appendix B.

5.5.7 ResultsThe AM subsystem trade process led to the selection of several interacting technologies to fulfill the necessary functions of atmosphere management. The chosen technologies and their interactions are depicted in Figure 5-6 and Figure 5-8. The figures represent two different configurations and operating schemes: one for the Earth-Mars transit phase, and one for the Mars surface stay.



COCO22

Gas Separator

Gas Separator

NN22

2 2 BMSBMS

SOESOE

HUMANHUMAN OO22

PressurePressure ControlControl

COCO22

Low COLow CO22 AirAir

OO22

HEPA Filter TCCS

GC/MS Humidity Control

FDS

CO

2 rich Air

COCO22

AirAir

NH

3 , NO

x , SOx

HH22, NH, NH33, , CHCH44, NO, NOxx, ,

SOSOxx

To WPTo WP

CO

CO

22 , H, H22 , N

H, N

H33 , C

H, C

H44 , N

O, N

Oxx , SO, SO

xx

From WPFrom WPVentVent

ATMOSPHERE MANAGEMENTATMOSPHERE MANAGEMENT

To WPTo WP

CC

COCO22

Gas Separator

Gas Separator

NN22

2 2 BMSBMS

SOESOE

HUMANHUMAN OO22


COCO22


OO22

HEPA Filter TCCS


FDS

CO

2 rich Air

COCO22

AirAir

NH

3 , NO

x , SOx

HH22, NH, NH33, , CHCH44, NO, NOxx, ,

SOSOxx

To WPTo WP

CO

CO

22 , H, H22 , N

H, N

H33 , C

H, C

H44 , N

O, N

Oxx , SO, SO

xx

From WPFrom WPVentVent


To WPTo WP

CC

Figure 5-6 AM Subsystem Diagram Transit

Figure 5-6 shows the configuration of the AM subsystem for the Earth-Mars transit phase. During this phase, the AM subsystem utilizes a 2-bed molecular sieve system for removal of CO2 from the cabin air. The removed CO2 is processed by the solid-oxide electrolysis system, which separates the CO2 into C and O2, sending the C to the WP subsystem and the O2 into use in the cabin air. Additionally, the cabin air is circulated via the ventilation system through HEPA filters and is processed by the Trace Contaminant Control System (TCCS). The gas chromatograph/mass spectrometer sensors insure that the major and minor constituents of the atmosphere are within acceptable limits. Additionally, the temperature and humidity of the cabin air is kept within requirements by the condensing heat exchanger and associated equipment. Overall pressure control is monitored and adjusted by valve systems to the storage containers for N2, O2, etc. The entire crew cabin area is monitored by scattering smoke detectors for early detection of fires. In case of a fire, throughout the cabin are CO2 portable fire extinguishers and portable breathing apparatus. Finally, exhaust gasses from the WP subsystem are routed to the AM subsystem where they are separated into those substances usable by the AM subsystem (i.e.CO2) and those that are currently not (e.g. NH3, CH4, etc.). Those that are not usable by AM may be temporarily stored or vented immediately. Care is taken in the AM subsystem to insure that there is no danger of the unusable gases from the WP subsystem contaminating the crew cabin. Figure 5-7 shows the mass, power, volume, etc. of the chosen components for the AM subsystem in the transit configuration.



Component #Weight

(kg)

Add. Weight

(kg)

Total Weight

(kg)Power (kW)

Total Power (kw)

Volume (m3)

Total Volume

(m3)

Crew Time

(hrs/day)Portable Fire Extinguisher (PFE) 3 15.10 0.00 45.30 0.00 0.00 0.04 0.12 0.00Scattering Smoke Detector 8 1.50 0.00 12.00 0.00 0.02 0.04 0.32 0.00Portable Breathing Apparatus 12 2.80 0.00 33.60 0.00 0.00 0.31 3.72 0.00UV/IR Flame Detector 3 3.70 0.00 11.10 0.10 0.30 0.00 0.01 0.00Pressure Control 1 74.00 0.00 74.00 0.10 0.10 0.41 0.41 0.00Pressure Control Sensors 2 2.00 0.00 4.00 0.01 0.01 0.00 0.03 0.00Gas Chromatograph/Mass Spectrometer (mini) 3 1.80 0.00 5.40 0.02 0.05 0.03 0.09 0.00Trace Contaminant Control Subassembly (TCCS) 1 78.20 163.00 241.20 0.18 0.18 0.50 0.50 0.01HEPA Filters 15 2.00 260.00 290.00 0.00 0.00 0.10 1.50 0.01Common Cabin Air Assembly 2 112.00 0.00 224.00 0.47 0.94 0.40 0.80 0.00Intermodule Ventilation Fan 2 4.76 0.00 9.52 0.55 1.10 0.01 0.02 0.00Intermodule Ventilation Valve 12 5.10 0.00 61.20 0.01 0.07 0.01 0.12 0.00Cabin Fan Assembly 1 26.90 0.00 26.90 0.41 0.41 0.15 0.15 0.002 Bed Molecular Sieve 2 96.00 28.80 220.80 0.50 0.50 0.60 1.20 0.00Solide Oxide Electrolysis 2 220.00 44.00 484.00 6.50 6.50 0.80 1.60 0.00Oxygen Buffer Tank 1 100.00 34.00 134.00 0.00 0.00 0.45 0.45 0.00Nitrogen Buffer Tank 1 26.00 18.90 44.90 0.00 0.00 0.25 0.25 0.00

Totals 1921.92 10.16 11.28 0.02

Figure 5-7 AM Subsystem Parameters


COCO22

Gas Separator

Gas Separator

NN22

TSATSA

SabatierSabatier

HUMANHUMAN SPWESPWEOO22


HH22

COCO22


HH22OO

OO22

HEPA Filter TCCS


FDS

CO

2 rich AirCOCO2 2 , H, H22

AirAir

CHCH44

CHCH44

NH

3 , NO

x , SOx

NH3, NOxSO,

To PyrolysisTo Pyrolysis

CO

CO

22 , H, H22 , N

H, N

H33 , C

H, C

H44 , N

O, N

Oxx , SO, SO

xx

From PyrolysisFrom Pyrolysis

MarsMarsAtmosphereAtmosphere

NN22

VentVent

ISRU PlantISRU Plant


COCO22

Gas Separator

Gas Separator

NN22

TSATSA

SabatierSabatier



HH22

COCO22


HH22OO

OO22

HEPA Filter TCCS


FDS

CO

2 rich AirCOCO2 2 , H, H22

AirAir

CHCH44

CHCH44

NH

3 , NO

x , SOx

NH3, NOxSO,

To PyrolysisTo Pyrolysis

CO

CO

22 , H, H22 , N

H, N

H33 , C

H, C

H44 , N

O, N

Oxx , SO, SO

xx

From PyrolysisFrom Pyrolysis

MarsMarsAtmosphereAtmosphere

NN22

VentVent

ISRU PlantISRU Plant

Figure 5-8 AM Subsystem Diagram - Mars Surface

Figure 5-8 shows the AM subsystem as it is configured for use on the Mars surface. The major difference is the use of equipment from the ISRU plant that has been pre-landed on the surface via the cargolander. The equipment used from the ISRU plant consists of a Sabatier reactor and a solid polymer water electrolysis system. These in conjunction with a temperature swing absorption system perform the O2 and CO2 revitalization while on the surface. The temperature swing absorption system functions through utilization of the changes in temperature on the surface of Mars during day-night cycle. It removes the CO2 from the cabin air and outputs it to the Sabatier reactor. The Sabatier reactor produces CH4 for use as a propellant and H2O, which is sent to the solid polymer water electrolysis system. This system produces H2 and O2, the former being fed back to the



Sabatier reactor and the later being used in the crew cabin air. The remainder of the AM subsystem performs the same on the Mars surface as it does in Earth-Mars transit.

5.5.8 Conclusions and RecommendationsThe result of the design and trade study process for the AM subsystem is a result of both the internal trade study process as well as system integration synergies with other subsystems and the ISRU plant on the Mars surface. The technologies chosen are those that best fit within the mission parameters of the Mars Design Reference Mission. The AM subsystem could benefit from further research into a few technologies: Advanced Carbon Formation Reactor (ACFR), Water Vapor Electrolysis (WVE), and Ammonia Dissociation. Specifically, Ammonia Dissociation would allow more loop-closure for N2 and H2, thus assuring less need to take replacement supplies on-board.

5.6 Atmosphere Management Subsystem References1. Benkmann, C., Hoellriegelskreuth, "CO2 Removal by Pressure Swing Adsorption for

Iron Direct Reduction Plants", Linde AG Reports on Science and Technology, ACHEMA 2000 Special Issue No. 62 2000 ISSN 0942-5268.

2. Chutjian, A., et al, "A Miniature Quadrupole Mass Spectrometer Array and GC For Space Flight: Astronaut EVA and Cabin-Air Monitoring", Warrendale, PA: Society for Automotive Engineers, 2000. International Conference on Environmental Systems, Paper No. 2000-01-2300.

3. Clemens, T., Haines, M., Heidug, W., "Optimized CO2 Avoidance Through Integration of Enhanced Oil and Gas Recovery with Solid Oxide Fuel Cells", F3-3 (2002) SPE 77348, Annual SPE Conference.

4. Common Cabin Air Assembly Description, http://www.hsssi.com/Applications/SpaceHabitat/CCAA.html.

5. Finn, J.E., “Solid State Compressor for Space Station Oxygen Recovery”, Overview in 2000 Annual Report, Astrobiology Technology Branch, Space Sciences Division.

6. Finn, J.E., Sridhar, K.R., McKay, C.P., “Utilization of Martian Atmosphere Constituents by Temperature-Swing Adsorption”.

7. Hanford, A. J. and Drysdale, A. E. (1999) “Advanced Life Support Technology Research and Development Metric – Initial Draft,” LMSMSS33045, Lockheed Martin Space Mission Systems and Services, Houston, Texas, 13 January 1999.

8. Horneck, G., DLR, "Advanced Life Support Systems and Human Exploratory Missions", 2nd Workshop on Advanced Life Support, ESTEC, 17-18 April 2002.

9. http://www.aist.go.jp/aist_e/new_research/20011206_1/20011206_1.html , "Water Split into Hydrogen and Oxygen Using Visible Light".

10. http://www.carbotech.de/AN/e/technologie3.htm , Modular Pressure Swing Adsorption (MPSA).

11. http://www.carbotech.de/AN/e/technologie3.htm , Vacuum Pressure Swing Adsorption (VPSA).

12. Human Spaceflight: Mission Analysis and Design, Larson & Pranke, 2000.13. In-House Life Support Technology Review Databook, FY 91, Volume 5, NASA

Ames Research Center, Advanced Life Support Division, Doc. No. 90-SAS-R-003, Rev.2, 1991 (http://joni.arc.nasa.gov/Database/index.shtml).


http://joni.arc.nasa.gov/Database/index.shtml

http://www.carbotech.de/AN/e/technologie3.htm

http://www.carbotech.de/AN/e/technologie3.htm

http://www.aist.go.jp/aist_e/new_research/20011206_1/20011206_1.html


14. International Space Station Cabin Fan Assembly Description, http://www.hsssi.com/Applications/SpaceHabitat/CFA.html.

15. Lygre, A., Matteo Cé, Vik, A., Byrknes, J., "Solid Oxide Fuel Cell Power Plants with Integrated CO2 Capture", 2nd Nordic Minisymposium on Carbon Dioxide Capture and Storage, Göteborg, October 26, 2001.

16. Marthe, P., et al, Crew Transfer/Return Vehicle Study Phase 3 Report, University of Alabama, April 2000 (http://www.eb.uah.edu/ipt/files/2000/IPT2000_Phase3_Final_Report_Team1.pdf)

17. Section 2.2.3.3, 2.3.3.1, 3.2.3.3, 3.3, 3.3.3.1, & 3.4, International Space Station Environmental Control & Life Support System Training Manual, TD9706.

18. Section 3, Shuttle Environmental Control & Life Support System Training Manual, TD415B.

19. Solid Waste Processing and Resource Recovery Workshop Report – Volume I, NASA Johnson Space Center, Crew & Thermal Systems Division, Doc. No. CTSD-ADV-474, Rev. A, 2002.

20. Spacecraft Life Support and Biospherics, Eckart, 1996.21. Sridhar, K.R., Gottman, M., Baird, R.S., “AIAA 99-2413 2001 Mars In-Situ Oxygen

Production Flight Demonstration”, 35th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Los Angeles, CA, June 1999.

22. Sridhar, K.R., Gottman, M., Baird, R.S., “AIAA 2000-1068 “Update on the Oxygen Generator System for the 2001 Mars Surveyor Mission”, 38th Aerospace Sciences Meeting and Exhibit, Reno, NV, January 1999.

23. Sridhar, K.R, Vaniman, B.T., "Oxygen Production on Mars Using Solid Oxide Electrolysis", SAE Technical Paper Series 951737, 25th International Conference on Environmental Systems, San Diego, California, USAJuly 10-13, 1995.

24. STS Humidity Control Heat Exchanger Assembly Description, http://www.hsssi.com/Applications/SpaceVehicles/multipurphx.html.

25. VanderWiel, D.P., Zilka-Marco, J.L., Wang Y., Tonkovich, A.Y., Wegeng, R.S., "Carbon Dioxide Conversions in Microreactors", Pacific Northwest National Laboratory, P.O. Box 999, MSIN K8-93, Richland, WA 99352.

26. Whitiker, Alana; Overview of ISS US Fire Detection and Suppression Subsystem; June, 2001.


http://www.hsssi.com/Applications/SpaceHabitat/CFA.html


6.0 WATER MANAGEMENT6.1 Water Management

The requirements for water management are defined in Table 6-5.

Table 6-5. Water Quality Requirement: Maximum Contaminant Levels

Quality Parameters Potable HygienePhysical ParameterTotal Solids (mg/l) 100 500Color, True (Pt/Co units) 15 15Taste (TTN) 3 N/AOdor (TON) 3 3Particulates (max size - microns) 40 40pH 6.0-8.5 5.0-8.5Turbidity (NTU) 1 1Dissolved Gas (free @ 37 C No Detectable Gas N/AFree Gas (@ STP) No Detectable Gas No Detectable GasInorganic Constituents (mg/l)Ammonia 0.5 0.5Arsenic 0.01 0.01Barium 1.0 1.0Cadmium 0.005 0.005Calcium 30 30Chlorine (total - include chloride) 200 200Chromium 0.05 0.05Copper 1.0 1.0Iodine (total - include organic iodine) 15 15Iron 0.3 0.3Lead 0.05 0.05Magnesium 50 50Manganese 0.05 0.05Mercury 0.002 0.002Nickel 0.05 0.05Nitrate (NO3-N) 10 10Potassium 340 340Selenium 0.01 0.01Silver 0.05 0.05Sulfate 250 250Sulfide 0.05 0.05Zinc 5.0 5.0Bactericide (mg/l)Residual Iodine (minimum) 0.5 0.5Residual Iodine (maximum) 4.0 6.0Aesthetics (mg/l)Cations 30 N/AAnions 30 N/ACO2 15 N/AMicobialBacteria (CFU/100ml)Total Count 1 1Anaerobes 1 1



Quality Parameters Potable HygieneColiform 1 1Virus (PFU/100 ml) 1 1Yeast & Mold (CFU/ 100ml) 1 1Organic Parameters (ug/l)Total Acids 500 500Cyanide 200 200Halogenated Hydrocarbons 10 10Total Phenols 1 1Total Alcohols 500 500Total Organic Carbon (TOC) 500 10,000Uncharacterized TOC (UTOC) 100 1,000

6.2 Water MonitoringWater Monitoring is a major subsystem within the water management. Therefore, any technology that has the Technology Readiness Level (TRL) of less than 7 is assumed to be unacceptable for the Life Support System (LSS) and not studied in this section. The TRL of 7 means that the system prototype has been demonstrated in space environment. However, if the technology is not gravity dependent, the acceptable TRL is said to be 5. At this TRL level, the component and/or the breadboard have been validated in relevant environment and shows promising evidences that it would also work in space. With this in mind, the first tread study would be to do the simple pass/fail elimination due to the TRL level.

Table 6-6. List of Technologies & Associated TRLsTechnologies TRL

Fiber Optic Sensor for Water11 (for turbidity, color, pH, iodine, metals, ions, NOC, VOC, semi-volatiles and hardness level)

4

Electronic Nose11 (for taste, metals, NOC and odor) 6Ion Mobility Spectrometry (IMS)11 (monitor iodine level) 2-4Ion Specific Electrodes (ISE)11 (for conductivity level) 2-8Capillary Electrophoresis (CE)11 (for metals level) 3-4Liquid Chromatography (LC)11 (for metals, ions level) 2-3Ion Coupled Plasma (ICP)11 (for metals, ions and silver) 3Solid Phase Extraction-Mass Spectrometry (SPE-MS)11 (for NOC, VOC and semi-volatiles) 2-4Supercritical Fluid Chromatography (SFC)11 (for NOC, VOC and semi-volatiles) 1-2Liquid Chromatography-Mass Spectrometry (LC-MS)11 (for NOC, VOC and semi-volatiles) 3Fourier Transform Infrared (FTIR)11 (for NOC, VOC and semi-volatiles) 4Total Organic Carbon-Infrared (TOC-IR)11 (for TOC/COD) 4Total Organic Carbon (TOC) - conductivity11 6Total Organic Carbon (TOC) - reagentless11 2Total Organic Carbon Analyzer14 3Gas Chromatography (GC)11 (for NOC and semi-colatiles) 4Voltametry11 (for metals and silver) 3UV-visible Spectrophotometer (laser)11 (for turbidity, color, pH, iodine, metals, ions, NOC, VOC, semi-volatiles and hardness level)

2

Surface Acoustic Wave (SAW) Detector11 4Test Kits11 (for pH, chem-strips for specific compounds) 9Conductivity11 8-9Test Kits11 (for pH, chem-strips for specific compounds) 5-9



Therefore the technologies that will be studied are the following:

1. Electronic Nose11 (for taste, metals, NOC and odor) [TRL 6]11

Figure 6-1. Electronic Nose Equipment

2. Ion Specific Electrodes (ISE)11 (for conductivity level) [TRL 2-8]11

3. Total Organic Carbon (TOC) - conductivity11 [TRL 6]11

Earth Replications, Inc.

Figure 6-2. Ion Specific Electrode

Page 23


Figure 6-3. Total Organic Carbon - Conductivity Diagram

Figure 6-4. Actual Total Organic Carbon device

4. Conductivity11 [TRL 8-9]11

Figure 6-5. Sample of Conductivity device

5. Test Kits11 (for pH, chem-strips for specific compounds) [TRL 5-9]11

Table 6-7.Water Sample

Requirement for Off-Line Monitoring (initial On-Orbit

Operations)

Location Sample Volume FrequencyECLSS Storage Tank 500 ml/day Every dayRandom (Tank or Use Port) 500 ml/day Every 2 days


Figure 6-6. Sample Test Kits devices

Page 24


Avg. Total Volume 5,250 ml/weekAvg. No. Sample 10.5 times/week

Table 6-8.Water Sample Requirement for Off-Line Monitoring (Mature Operations)6

Location Sample Volume FrequencyECLSS Storage Tank 110 ml/day 6 days/week

500 ml/day 1 days/weekRandom (Tank or Use Port) 110 ml/day 3 days/week

500 ml/days 1 days/weekAvg. Total Volume 1,990 ml/weekAvg. No. Sample 11.0 times/week

6.2.1 Flow Chart for Water MonitoringSince each technology can detect different contaminates in water, the trade study cannot be conducted to compare them to one another. The combination of all the technologies is considered to be the best arrangement. The repetition of the monitoring follows for the redundancy of the subsystem.

ISE Conductivity pH, Iodine, TOC/COD,

hardness

TOC TOC/COD

Conductivity Gross quality indicator

Electronic Nose Odor, taste

Test Kits Conductivity, pH, Iodine,

TOC/COD, Hardness

Figure 6-9The Order of Monitoring Devices

6.3 Water GenerationWater Generation unit is an excellent system to enclose on Mars LSS since not 100% of water can be reclaimed in the total system even on the high efficiency technology. This indicates that the crews are constantly losing water on the LSS. All the technologies in water generation are in the conceptual level. Even though the crews should not depend on the water generation using in-situ resources, the possibility of the technologies to be



fully developed by the time human exploration on Mars exists is highly achievable. The water generation until is a back up subsystem, which is included mainly for the purpose of experimentation. This is an excellent time to test the technology that is necessary in the future. It was not meant to be a main subsystem and will not have a major effect on the optimum design of the LSS. Please note that the buffer size of water on the LSS is sufficient for the crews without this water generation unit. The list of water generation subsystem is as follow.

Zirconia Electrolysis Cell Unit6 [TRL 1-2] Water Vapor electrolysis11 [TRL 4] Cyanobacteria11 [TRL 6] Sabatier Reaction7,8,9 [TRL 6]

Not all of the technologies have TRL associated with them. Therefore, there is not much information on each technology other than the formula that has CO2 as one of the input and H2O as one of the output. There is no reason to omit any technology until future study has been done and more data is available. Therefore a trade study is not done in this situation. The formulae for all the technologies are as shown.

1. Zirconia Electrolysis Cell Unit: Operate at 800 to 1000 C

2 CO2 2 CO + O2

O2 +2H2 2 H2O

2. Water Vapor Electrolysis: has TRL up to 4 Also use Zirconia Electrolysis Cell Unit

3. Cyanobacteria: has TRL up to 6Depends on biological and might be gravity dependent

4. Sabatier Reaction: TRL up to 6

4 H2 + CO2 CH4 + 2 H2O

Since Sabatier reaction is already being used in the Atmosphere Management Subsystem on the surface of Mars, this technology made the most sense to be used for water generation subsystem as well. This selection is proven to reduce the mass of the whole system.

6.4 Water Processing6.4.1 Fire Detection & Suppression

The baseline water management requirements are to provide potable and hygiene water to the crew for the duration of the mission. As outlined in the human mass balance section, 3.905 kg/CM/day of potable water and 23.65 kg/CM/day of hygiene water must be



provided and meet the water quality requirements outlined in section 1.0. Detailed requirements for the LSS can be found in Appendix A.

6.4.2 Baseline Architecture

Human

Potable

Laundry

Hygiene Storage

18.216

9.4

2.5

Food Management

0.214

.

Waste Management

Figure 6-10 Open Loop Diagram w/ Flow Rates in kg/day for 6 Crewmembers

Table 6-9 WM Parameters

Mass(kg)

Power(kW)

Volume(m3)

180 Days 29759.4 29.8500 Days 82665.0 82.7Total Water

112424.4 112.4

Storage 22484.9 0.02 5.62Total 134909.3 0.02 118.02

Figure 6-10 shows the open loop block diagram for the water management subsystem. The only components needed to operate the system include storage and delivery. A 10% increase in the stored water quantity is included to provide a safety buffer. The storage mass was assumed to be 20% of the stored mass. Table 6-9 includes a summary of the total subsystem mass for 180 day transit and 500 day Martian stay. This mass does not



include any dependence on ISRU because it is unknown if the water production rates would match the 165.33 kg required per day.

6.4.3 Potable and Hygiene Water Processing

Water processing technologies were broken down into two main categories, Potable and Hygiene processing and urine processing. This section discusses potable and hygiene water processing.

6.4.3.1 Candidate Technologies

Table 6-10 Hygiene & Potable Water Treatment Candidate Technologies

WM Function Candidate TechnologiesHygiene & Potable Water Treatment

MIR Technology (Condensate)10

Reverse Osmosis (RO)1,13

Multifiltration (MF)1,13

Electrodialysis1

Oil and Water Seperation2

Rock/Plant/Microbial Filtering System3,4 Thermoelectric Integrated Membrane

Evaporation (TIMES)1

Granular Activated Carbon (GAC)5

Aqueous Phase Catalytic Oxidation Subsystem (APCOS)

Ultrafiltrtion10

MilliQ Absorbtion Beds Pasteurization Ionic Silver1

Regenerable Microbial Check Valve (Iodine)12,15

UV-visible Spectrophotometer (laser)11

6.4.3.2 Infeasible Technologies Due to the significant list of candidate technologies, a series of selection criteria needed to be used to rule out undeveloped technologies. TRL levels less than 6 and complete lack of information were the primary criteria used to reduce the number of candidate technologies. Further elimination of technologies was performed during the formation of the spec sheets due to key information (such as mass or power) missing.

6.4.3.3 Technology Trade Study The potable and hygiene water processing consisted of numerous technologies, each consisting of unique pre and post treatment processes. This required the development of systems of different technologies to be traded between. Hygiene and potable water will be processed with the same system. Consumable data is primarily described for complete



processing to potable quality water, therefore the data is not available for a unique hygiene water processing trade. The following systems were traded:

o UltraFiltration/Reverse Osmosis + APCOSo UltraFiltration/Reverse Osmosis + MilliQ Absorbtion Bedso Multifiltration

The UF/RO and MilliQ Absorption Beds won the trade. Multifiltrations downside was its large consumable mass while the APCOS was significantly pentalized due to the unknown oxygen consumption for the oxidation process.

Microbial control was separated from this trade study due to its need in any system chosen. Due to lack of information, the Iodine Microbial Check Valve was chosen. Iodine removal beds are also required before potable use to eliminate long-term effects of Iodine consumption. Detailed trade sheets can be found in Appendix B.

6.4.4 Urine Processing

6.4.4.1 Candidate Technologies

Table 1-7. Urine Treatment Candidate Technologies.

Water Management Function Candidate TechnologiesUrine Treatment MIR Technology (evaporation, steam condensation, sorption,

electrolysis)10

Vapor Compression Distillation (VCD)1,13

Vapor Phase CatalyticAmmonia Removal (VAPCAR)1

Air Evaporation (AES)1

Aqueous Phase Catalytic Oxidation Post-Treatment System (APCOS)10,13

Super Critical Water or Wet Oxidation (SCWO)1

Incineration (oxidation)11

Pyrolysis11

Aerobic Slurry11

Aerobic Solid Processing (composting)11 Anerobic Solid Processing11

Aquaculture (fish)11 Electrochemical Oxidation11

6.4.4.2 Infeasible Technologies Again this large list of technologies was reduced through a few selection criteria. The primary selection factor in urine treatment was the elimination of biological systems following the DRM requirements. TRL levels below 6 and lack of information rules out many of the other candidates.



6.4.4.3 Technology Trade Study Due to the severe elimination of technologies by initial selection criteria, only two were left. The urine distillation trade was performed between the following technologies:

-Air Evaporation System (AES)-Vapor Compression Distillation (VCD)

Vapor Compression Distillation won the trade study with the Air Evaporation System in second. The primary reason the AES places second was due to the high power consumption of 1 kW. This is approximately 10% of the allotted power for the spacecraft dedicated to one system. A simple trade between carrying makeup water in the VCD only system versus using an AES to process the brine water on a low duty cycle resulted in a significant mass savings of approximately 175 kg as well as providing a very simple redundant system in the case of a VCD failure.

6.4.5 Closed Loop Architecture

Water ManagementWater Management

HUMANHUMAN UrineUrinePretreatmentPretreatment

OzoneOzoneSulfuric AcidSulfuric Acid

VCDVCD

Brine Brine HH22OO

RORO

Milli QMilli QMCVMCVIodineIodine


Hygiene HHygiene H22OOStorage TankStorage Tank

Iodine RemovalIodine RemovalBedBed

PotablePotableHH22OO

PretreatedPretreatedUrineUrine

AESAES

Ultra FiltrationUltra Filtration

Brine H

Brine H

22 OO

ISE MonitoringISE MonitoringIodine testingIodine testing Waste WaterWaste Water

(Hygiene, AM, WP)(Hygiene, AM, WP)

InputInput

Water ManagementWater Management

HUMANHUMAN UrineUrinePretreatmentPretreatment

OzoneOzoneSulfuric AcidSulfuric Acid

VCDVCD

Brine Brine HH22OO

RORO

Milli QMilli QMCVMCVIodineIodine


Hygiene HHygiene H22OOStorage TankStorage Tank

Iodine RemovalIodine RemovalBedBed

PotablePotableHH22OO

PretreatedPretreatedUrineUrine

AESAES

Ultra FiltrationUltra Filtration

Brine H

Brine H

22 OO

ISE MonitoringISE MonitoringIodine testingIodine testing Waste WaterWaste Water

(Hygiene, AM, WP)(Hygiene, AM, WP)

InputInput

Figure 6-11 Closed Loop Water Management Flow Diagram

Figure 6-11 shows the integration of the water management subsystem components. The urine treated by the VCD must be pretreated with Ozone (a commercial oxidizer) and sulfuric acid to prevent the release of ammonia during the distillation process. Brine water from the reverse osmosis filter is also passed through the VCD to reclaim more water. The water flow through the VCD can be arranged in numerous forms and is not completely shown on this diagram. Brine water from the VCD can be passed back through itself to maximize the solid concentration of the brine. The remaining brine water



is stored and periodically processed by the AES. Current AES testing shows a slightly reduced quality of water from the AES, so this water is reprocessed through the VCD to ensure complete processing of the urine.

Product water from the VCD is combined with the remaining wastewater from the craft including that from hygiene, condensate and Pyrolysis recovery. The water stream then flows through an Ultra filtration unit which consists of mechanical filtration media. This increases the lifetime and efficiency of the following reverse osmosis filter. As stated earlier, the brine water produced in processed through the VCD. The product water then flows through the Milli-Q absorption bed which consists of activated carbon and a proprietary organic carbon scavenger media to reduce the TOC to acceptable potable water quality standards. At this time, Iodine is then added to the water stream for microbial control. Monitoring then checks the PH, conductivity, TOC and Iodine levels before the water is stored. Hygiene water is used directly from this source. Potable water must first be passed through the iodine removal bed to reduce the iodine level to acceptable amounts. Online iodine monitoring then ensures this level.

The water buffer capacity of this system is 324.28 kg. This was calculated for the transit trip only due to the ISRU having the capacity to provide the small amounts of makeup water required. The Earth Return Vehicle would require a larger storage capacity to provide for the potential on orbit stay in addition to the return trip. The only water loss within the closed water system takes place in the Pyrolysis waste processing unit used to process feces. This 90% efficient system creates a loss of 10.8 kg of water during transit. With the near 100% design efficiency of the system, and no additional information on losses or buffer size, a value of 1% of the total processed water for transit was used in addition to the expected loss of 10.8 kg from Pyrolysis. Adding in our 10% safety factor of consumables results in 324.28 kg. In an event of total water system failure, this allows for 14 days under normal potable water use without any hygiene use. This should be plenty of time to allow for repairs of the system.

Table 6-11 Water Management Subsystem Mass Breakdown

Mass (kg)Hardware 588.212Water Buffer 324.28180 Day Consumables 54.5500 Day Consumables 142.2Total 1109.192

Table 6-11 shows the breakdown of mass between consumables, buffer and hardware. The total mass includes all consumables for the transit/habitation module, while depending on ISRU for water makeup on the surface. If the cargo lander brought the consumables for the surface stay, the mass would be reduced to 966.99 kg. The Earth Return vehicle water subsystem mass would be larger due to the increased buffer size for the potentially long, on orbit stay.



6.5 Conclusions and Recommendations Current technology provides a substantial choice of operational subsystems within water management. Detailed testing has been performed on several occasions and provides excellent information on physical/chemical and biological systems. Many promising technologies in development or in use have been developed in the private sector and almost all information is proprietary. While these technologies could provide the optimum solution to our design requirements, they had to be eliminated or severely penalized within the trade study due to the lack of detailed information.

Buffer size is one subject that is not discussed within literature. Only one reference was found which mentioned buffer size. This is a very critical design feature that will significantly affect the mass and safety of the system. Further research or testing is needed on this subject.

6.6 Water Management Subsystem References1. Spacecraft Life Support and Biospherics, Eckart, 1996.2. http://techlink.msu.montana.edu/articles/spacedwellers.html, "Water for Space

Dwellers"3. http://techtran.msfc.nasa.gov/Patents/(21).html, "Combined Air and Water Pollution

Control System"4. http://science.nasa.gov/headlines/y2001/ast09apr_1.htm, "Leafy Green Astronauts"5. http://www.admin.mtu.edu/urel/breaking/2000/water.html, "MTU Engineering Earn

Landmark Award for Water Treatment Design Approach"6. http://www.lpi.usra.edu/meetings/isru97/PDF/MINH.PDF, " Production of Oxygen

Carbon Dioxide Using Zirconia Electrolysis Cells"7. http://www.sff.net/people/Geoffrey.Landis/propellant.html, "Making Rocket

Propellant on Mars"8. http://www.isso.uh.edu/publications/A9900/html/mini/mini-richardson.htm,

"Improving Sabatier Reactions for In-Situ Resource Utilization on Mars Missions"9. http://perso.wanadoo.fr/salotti/Zubrincarburant.doc, "Report on the Construction and

Operation of a Mars In-Situ Propellant Production Unit"10. http://www.colorado.edu/ASEN/asen5116/Lect-16.htm, "Lecture 16"11. http://research.hq.nasa.gov/code_u/matrix/index, "Technology Readiness Level (TRL) and

Equivalent System Mass (ESM)"12. http://lsda.jsc.nasa.gov/readingroom/4.2WaterChem.pdf, “Water Chemistry

Monitoring”13. http://advlifesupport.jsc.nasa.gov/ehti2/bkgrd.html, “Lunar-Mars Life Support Test

Project Phase II”14. http://lsda.jsc.nasa.gov/scripts/cf/hardw.cfm?hardware_id=827&string=TOC, “Total

Organic Carbon (TOC) Analyzer”15. http://www.urc.cc/rmcv.htm, “URC: Regenerable Microbial Check Valve”16. Advanced Life Support Program: Requirements Definition and Design

Considerations JSC 38571, National Aeronautics and Space Administration 1998



7.0 WASTE MANAGEMENT7.1 Baseline Functional RequirementsThe waste model for the WP Subsystem is based on the data found in the Baseline Values and Assumptions Document (Hanford et al. 2002) for a six-person crew. The functions of the subsystem include collecting, processing, storing and/or dumping waste, when necessary. Table 7-12 presents a summary of all the different sources of waste within the life support system. Packaging material constitutes the largest waste mass. Even though this life support system does not depend on any bioregenerative sources, inedible plant biomass is taken into account in the mass budget to account for this future possibility.

Table 7-12. Waste Model for a Six-Person Crew (Verostko et al. 2002, Handford et al. 2002)

Subsystem or Interface Waste Component Weight (kg/day)

WP, WM Dry Human Waste: feces, urine, shower/hand wash and sweat.

0.720

FS Inedible Plant Biomass 1.691AM, WM Filters 0.326

In General

Trash: clothes/towels, pads/tampons, menstrual solids and paper.

0.556

Packaging Material: snack packaging, food containers, plastic bags, food remains, frozen, refrigerated, ambient, beverage and straws.

7.908

Paper: wipes, tissues and general waste. 1.164Tape: masking, conduit and duct. 0.246Miscellaneous: Teflon and PVC. 0.069

Total 12.680

7.2 Baseline ArchitectureThe WP open-loop mass flow diagram is shown as Figure 7-12. This diagram illustrates the baseline architecture for the system at its fundamental level with no waste processing. In this mode of operation, the only processes taking place are chemical stabilization of decomposable matter such as biological waste, and storage of materials. This mass will drastically decrease as the waste product output is incorporated as consumables into the input streams for the WM and AM subsystems.



All values are in kg/day All values are in kg/day for 6 crew membersfor 6 crew members

14.29214.292

168.393168.393

WasteWaste




DumpDump

StorageStorageAll values are in kg/day All values are in kg/day for 6 crew membersfor 6 crew members

14.29214.292

168.393168.393

WasteWaste




DumpDump

StorageStorage

WasteWaste




DumpDump

StorageStorage

Figure 7-12 WP Open Loop Diagram

7.3 Subsystem AssumptionsThe following assumptions have been made when designing the WP Subsystem:

A collection system for human wastes such as urine and feces has already been designed (urinal and commode); therefore, no further development will be explored within this document.

Urine and feces are assumed to be collected individually; therefore, there is no need for separation within the WP Subsystem.

The Water Management Subsystem will treat urine effluent. The WP Subsystem will not rely on any biological treatment. No metals will be processed. The budget for developing and building technologies is not constrained.

7.4 Subsystem Technology Trade StudiesThe trade variables used to compare the technologies in the WP Subsystem is shown in Table 7-13. Out of all these variables, mass, TRLs, and the inherent process variables such as pressure, temperature and volume were given a higher weight in the trade matrix. Numerical values were assigned to qualities such as reliability and safety (1=low, 2=med, 3=high) to be able to account for those variables in the selection process.

Table 7-13. Waste Processing Trade Variables

Selection Criteria Unit/ValueComponent Mass KgAdditional Mass KgPower kWVolume m3

Operating Temperature KOperating Pressure kPaTRL 1-9Reliability 1-3*Maintainability 1-3*



Selection Criteria Unit/ValueGravity Dependence yes, noSafety 1-3*Prospective Improvements 1-3**(low, med, high)

7.4.1 Candidate TechnologiesA wide variety of technologies were considered to establish the infrastructure of the WP Subsystem. Given the assumptions for the WP design, biological treatments were mentioned but not compared against physicochemical technologies, due to the increased challenges involved in maintaining plants and bacterial cultures alive. Physicochemical processes have the advantage of rapidly converting waste to products, most of which can be used to complete other functions within the system. The candidate technologies are characterized in – Table 7-16, mapped to the function that they help provide.



Table 7-14. Preprocessing Technologies for Waste Management

Waste Management Function Candidate Technologies (Refs. 2,6,7)

Collection and stabilization of waste

Vacuum Waste Collection and Transport Bulk Compaction Dry Size Reduction and Particle Size Control Drying (Forced Air Thermal Convection, Forced Air,

Thermal Vacuum, and Freeze Vacuum) Pneumatic Transport of Dry Material Screw Conveyor Slurry Pumping Solid/Liquid Blending; Slurrying (50-95% H2O) Solid/Solid Blending Storage Wet Size Reduction and Particle Size Control

Table 7-15. Biological Processing Technologies for Waste Management

Waste Management Function Candidate Technologies (Refs. 2,5,6,7)

Biological treatment of waste

Aerobic/Anaerobic Waste Processing Activated Sludge Composting Aerobic Completely Mixed (Slurry) Biological

Reactor Plant Nutrient Extraction Variant – 7 Day Residence

Time (No Curing Stage/Biofilter) Plant Nutrient Extraction Variant – 21 Day

Residence Time Fixed-Film Bioreactor High-Solids Leach Bed Anaerobic Digestion using

SBAC (Sequential Batch Anaerobic Composting) Paper and Biomass to Products Single Cell Protein Production and Crop Nutrient

Recovery



Table 7-16. Physicochemical Technologies for Waste Management

Waste Management Function Candidate Technologies (Refs. 1,2,3,6,7)

Biologically decomposable solids (feces, waste with bound water, solids from urine, sweat and hygiene water, clothes)

Super Critical Wet Oxidation Wet Oxidation Batch Incineration Continuous Incineration Pyrolysis Gasification Electrochemical Oxidation Molten Carbonate Oxidation Starved Air Combustion Proteolysis Acid Hydrolysis Plasma Arc Oxidation Peroxide Oxidation Space Shuttle Waste Management System Waste Management – Water Systems

Non decomposable solids (spare parts, plastic, metal, filters)

Batch Incineration Continuous Incineration Electrochemical Oxidation Molten Carbonate Oxidation Super Critical Wet Oxidation Dumping Storage

Non decomposable solids (products from experiments, medicine)

Batch Incineration Continuous Incineration Plasma Arc Oxidation Pyrolysis Molten Carbonate Oxidation Dumping Storage

7.5 ResultsA total of seven (7) technologies were selected from all the initial candidates, using TRL, versatility and prospective potential as cut-offs. Versatility was determined by the number of functions and the capability of the technologies to process a variety of wastes. Prospective potential was determined by the number of years and cost for the technology to achieve a TRL of 5 (Verostko et al. 2002). The chosen technologies were: Electrochemical Oxidation, Gasification, Supercritical Water Oxidation, Incineration (Batch and Continuous), Plasma Arc Oxidation and Pyrolysis. All of these have a TRL of 3 or above, with the exception of Gasification (TRL 2), which was deemed worthy of consideration because of all of its advantages and potential for future development.



A brief description of each candidate technology and a summary of their main traits follows in Table 7-17. Process diagrams as well as specification sheets can be found in Appendix B.

Table 7-17 Summary of Assessed Physicochemical Technologies

Technology Advantages Disadvantages TRLProspective

ImprovementBatch Incineration

-Treats all wastes-High conversion

-Flue gas contaminants-High T 3 High

$ to TRL 5= $1M

Continuous Incineration

-High TRL-High conversion

-Flue gas contaminants-High T 5 Uncertain

Electrochemical Oxidation

-Low T & P-Treats all wastes

-Pretreatment required-Complex waste effluent

4 Medium$ to TRL 5= $5M

Gasification-Minimum NOx, SO2

-Many useful products

-Low TRL-High T 2 High

$ to TRL 5= $600k - $1M

SCWO -Treats all wastes-Clean products

-High T & p-Solids plugging 4 Medium

$ to TRL 5= $1 - 5M

Plasma Arc Oxidation

-Treats combustibles -Fast reaction

-Doesn’t treat metals-High power & T 4 Medium

$ to TRL 5= $8 - $13M

Pyrolysis-Treats many wastes-Many useful products

-Doesn't treat metals-CO production 3 High

$ to TRL 5= $500k

7.5.1 Batch and Continuous Incineration (BI, CI)Incineration is a process that is capable of converting almost all waste into CO2, H2O, and inorganic ash. Pretreatment is necessary to dry and prepare the waste for the feed system. Waste is heated at ambient pressure to 813 K using pure O2 as the oxidizing agent. The incineration process consists of a combustor and a contaminant clean-up system. Produced contaminants (CO, HCl, SOx, NOx, and trace hydrocarbons) are removed by catalytic systems and absorption beds. In the continuous mode the system is fed at a constant feed rate, holds a constant temperature and composition, and produces a continuous constant composition output. Under batch operation, a pack of material is fed at a specified interval of time.

7.5.2 Electrochemical Oxidation (EO)In this process, soluble organic materials can undergo oxidative degradation at a low temperature and pressure. This method does not produce NOx, SOx, or CO and it requires less clean up than thermal systems. The breakdown occurs by the reaction that takes place at the interface between the anode and the electrolyte-waste solution. H2 is



produced as a by-product at the cathode, which can be used to feed a fuel cell to produce electricity. This system can be easily scaled down to fit the waste requirements of a crew of 6 (Verostko et al. 2002). Some of the drawbacks that this process presents are that the feed needs to be pretreated and turned into slurry; some of the gaseous emissions include chlorine; and it consumes high amounts of acid and alkaline solutions.

7.5.3 Gasification (GAS)In the gasification process, any carbon-containing material can be converted into synthesis gas and energy, through the reaction between the feed and steam in the presence of O2 in a high temperature and pressure gasifier. The waste is fed in dry or in slurry form to the gasifier. Once in the gasifier this material reacts with steam and CO2 at a high temperature and temperature in an oxygen starved environment. This produces a synthesis or “syn” gas made up of mostly of CO and H2. The high temperature in the gasifier changes the inorganic material into stable “slag”. Post treatment processing refines the raw gases and collects trace contaminants. This system can convert nearly 100% of all waste into useful end products of gas and energy. Gasification has a current TRL of 2, but shows future potential.

7.5.4 Supercritical Water Oxidation (SCWO)SCWO uses water in its supercritical state to break down toxic organic compounds into harmless oxidation by-products such as carbon dioxide and water. It consumes oxygen and power at a high temperature and pressure and has an aqueous stream output that carries all the inorganic salt residues. It produces water and carbon dioxide that is clean enough to be reused without processing. Safety concerns exist because the system operates at a high temperature and pressure. Precautions such as venting, monitoring, pressure relief must be taken to assure proper reactions.

7.5.5 Pyrolysis (PYRO)From the Greek “puro” (fire, heat) and “lusis” (destruction), Pyrolysis is a process that breaks down waste by heating at high temperature in the absence of O2. It is able to function both in batch and continuous mode, and has the advantage of having a product-rich waste stream that can be used by other subsystems. This technology will produce a char residue that can be gasified, combusted or activated to be used as an adsorbent (Verostko et al. 2002). Other by-products of this process include H2O, CO2, H2, CH4 and NH3.

7.5.6 Plasma Arc Oxidation (PAO)PAO completely decomposes waste materials in an oxygen-starved, extremely high temperature environment. A plasma arc torch provides a plasma gas at 2000-3000 Celsius. This extreme heat and oxygen-starved environment results in Pyrolysis, or heat destruction. The output of this system is combustible gas and an inert slag, whose characteristics will vary, depending on the type of input waste. This process is extremely efficient and creates a volume reduction of almost 250:1. This system has not been tested



in a microgravity environment and concerns exist regarding heat transfer characteristics. Reducing the size of this system for a human spacecraft environment may be a problem.

7.5.7 Trade Study ProcessOnce the technologies made the first cut, they were divided into two groups according to the type of waste they could process: technologies that could break down virtually all waste (EO, GAS, and SCWO), and technologies that could break down everything but metals (BI, CI, PAO, and PYRO). Gasification obtained the highest score in the ‘all waste’ category. This technology was included in the trade matrix for the ‘all waste/no metals’ category as well, since it was comparable to their functionality. Again, Gasification won within this category, leaving Pyrolysis as the runner-up technology.

The final step in the trade study was to contrast the strengths and weaknesses of those two remaining technologies and weight their functionality with respect to the other subsystems’ needs and capabilities. For comparison purposes, includes Plasma Arc Oxidation along with the two top technologies that resulted from the trade study. Even when the three technologies have similar traits, Pyrolysis has a richer product stream and less consumables than the other two processes. Plasma Arc Oxidation has the highest TRL [4], but is nearly 20 times heavier than the other two systems. Even when the prospects for future improvement are high for this technology, scale down is foreseen to be very difficult and the cost to TRL 5 is the highest of all the technologies (see Table 7-17). There is a major contrast in the two top technologies processing capability. Gasification can treat a batch of 50 kg of waste in one hour’s worth of operation, while Pyrolysis can process about 0.5 kg/cycle (cycle = 0.5 – 2 hours), meaning that continuous operation would be required for the latter. While batch operation may seem desirable against continuous operation, this does not necessarily equate to less crew time because aspects such as maintenance come into play. Pyrolysis is has been tested extensively on Earth and has a higher TRL than Gasification, thus providing the advantage of years of troubleshooting. Given that the design for this mission encompasses not only transit to Mars, but an extended stay on the Martian surface as well, gravity dependence becomes a critical issue in deciding which technology is more suitable for all scenarios. The only system out of the entire list of candidate technologies that is not foreseen to have any issues with changing gravity conditions is Pyrolysis, making it the winning technology for this trade study.

Table 7-18. Comparison of Top Three Trade Study Candidate Technologies



Technology Products Weight (kg) Processing

Capability Consumables

Gasification CO2, CO, H2, Ash, Energy 65 kg 10 - 20 kg/hr Heat, Steam

Pyrolysis H2O, CO2, CO, H2, NH3, CH4, Ash 62 kg 1 kg/hr Power

Plasma H2O, N2, Trace gases, Ash 1413 kg 50 kg/hr Power, Air

One of the functions that Pyrolysis fails to provide is the ability to process metals. Even when Pyrolysis does break down small amounts of inorganic compounds, including metals, these types of waste should be avoided because of problematic clean up issues caused by the post-process residues. The approach to handle this type of waste, which will be mainly comprised of filter components, will be taken care of by storing the used filters during transit, and then, once in the surface habitat, these filters can be disassembled to remove the non-processable components. The leftovers are treated with Pyrolysis, thus reducing the amount of space that this type of waste occupied originally.

7.6 The Integrated SystemThe WP Subsystem consists of these major components (See Figure 7-13):

Urinal Commode Bacteria/Odor Filter Compactor Pyrolysis Processable Materials Storage area Non-processable Materials Storage area

A mass, power and volume breakdown for each subsystem component is presented in Table 7-19.

Table 7-19. System Components Mass Summary

System Component Total Mass (kg)(Includes spares) Power (kW) Volume (m3)

Toilet Assembly 16.33 0.224 0.078Biological Waste Tank 17.40 0.000 0.100Compactor 25.94 0.110 0.355Pyrolysis 84.00 0.600 0.002Non-processables Storage Tank 50.00 0.000 2.000Chemicals 41.00 0.000 0.043

The collecting scheme for human waste follows the basic design principles used in the Space Shuttle (NASA-WCS 2102C). Urine and feces are collected separately by means



of a urinal and a commode. Feces and other decomposable matter such as food remains will be stabilized through chemical treatment to prevent/reduce bacterial growth while in storage, in a similar fashion to the products used on portable toilets. Several companies such as Walex Products (Walex 2002) and Toico Industries (Toico 2002) provide formaldehyde-free chemicals that not only disinfect, but help in the decomposition of the waste, thus reducing its volume. The feces’ residence time inside the biological waste tank will be minimum, as the goal will be to treat all processable waste on a continuous basis. Freeze drying (Lyophilization) was the alternate method considered for stabilization, however, chemical treatment is more appealing since it translates to less mass, power and volume penalties, in addition to eliminating the complexity of adding another mechanical component to the system. The AM Subsystem will take an integral part in the WP scheme by integrating a bacteria/odor filter for the re-circulated air around the urinal/commode area.

All other processable waste, such as plastics and trash from the FS Subsystem, will be placed in sealed plastic bags in a storage area. For pretreatment, this system will utilize a compactor to reduce waste volume prior to feeding it into the Pyrolysis unit.

Finally, the Pyrolysis unit will accept all the processable waste (including the feces’ stabilizing chemical agent) and convert it into a gaseous and solid output. The resulting gases from this process (mainly CO2, H2, NH3, CH4, H2O, NOx and SOx) will be accepted by the AM Subsystem, except for H2O vapor, which will be condensed and sent to the WM Subsystem for further treatment. The residual carbon will be stored in the Non-


OtherOtherSubsystemsSubsystems

CommodeCommode(Feces)(Feces)

STORAGESTORAGE

UrinalUrinal

To Water To Water ManagementManagement

PyrolysisPyrolysis

COCO22, H, H22, NH, NH33, CH, CH44, NO, NOxx, SO, SOxxTo Atmosphere To Atmosphere

ManagementManagement

HH22OO

STORAGESTORAGE

NonNon--processable waste processable waste from all subsystemsfrom all subsystems

CarbonCarbon

RecyclingRecycling

All otherAll otherprocessablesprocessables

(plastics, paper, etc)(plastics, paper, etc)

CompactorCompactor

BiologicalBiologicalWasteWasteTankTank

NonNon--processableprocessableMaterialsMaterialsStorageStorage

OtherOtherSubsystemsSubsystems


STORAGESTORAGE

UrinalUrinal


PyrolysisPyrolysis



HH22OO

STORAGESTORAGE


CarbonCarbon

RecyclingRecycling



CompactorCompactor




STORAGESTORAGE

UrinalUrinal


PyrolysisPyrolysis



HH22OO

STORAGESTORAGE


CarbonCarbon

RecyclingRecycling



CompactorCompactor



Figure 7-13.Waste Processing Subsystem Diagram

Page 42


Processable Materials Storage area for possible future use or to be discarded if no further processing is available.

7.7 Failure AnalysisEquipment failure is highly probable on missions of extended duration. While design should provide for preventing malfunctions, no system is infallible. Failures must therefore be dealt with in planning. Table 7-20 summarizes the WP Subsystem approach to failures of the main components of the technologies previously described. Two levels of redundancy are provided for every major step in the WP cycle, most of which includes replacement of the faulty part followed by temporary storage, and/or dumping of waste if necessary.

Table 7-20 Waste Processing Subsystem Contingency Approach

One of the most critical failures of the WP Subsystem revolves around the Pyrolysis unit. Major failure of main combustion shell/reactor in the Pyrolysis unit may result in higher concentration of contaminants in effluent due to incomplete combustion, which in turn might put a heavier load on the AM subsystem. The immediate contingency will be to store waste and replace the defective parts. As a last resource, excess material will be dumped while in transit.

7.8 Conclusions and RecommendationsThe WP Subsystem design complies with all the requirements established by the DRM. It provides storage for non-processable items and treatment for those that can be processed to recover and recycle resources. Pyrolysis is chosen as the technology that best balances functionality with overall system mass and power consumption. Challenges that accompany this technology include separation of the large volume and complex mixture of product gases. Incorporation of a carbon activation step would reduce non-processable


Failure Redundancy (1st level) Redundancy (2nd level)

Urinal vacuum failure Repair with spares.

Diapers (males/females) or urine collection in plastic bags (males).

Commode Repair with spares. Diapers or collection in bags (males/females).

Compactor Repair with spares. Process waste without compaction.

Pyrolysis reactor failure

Repair with spares. Store waste in the meantime. Redundant unit will be in place at Mars base.

Store and dump waste as necessary.

Pipe leakage Repair with sealant. Adjust connections.

Replace. Minimal capability as not many spares will be available.

Page 43


waste and increase the amount of reusable by-products. The WM Subsystem can make use of the activated carbon for trace contaminant control.

There is a great need for more in depth research for the technologies considered in this study. Since most of the technologies have a relatively low TRL (less than 5), there is a lack of experimental data showing how these systems operate under various gravitational conditions.

Although multiple aspects of waste processing have been considered, the issue of soil contamination from the Martian surface to the living headquarters will have to be addressed. Many EVAs will certainly contribute to dust accumulation and possibly hindrance of systems such as atmosphere particle control.

7.9 Waste Management Subsystem References

1. Davidson, William. 2002. Supercritical Water Oxidation: State of the Art Environmental Technology. General Atomics Advanced Technologies Group. Available from the World Wide Web: http://www.ga.com/atg/aps/scwo.html

2. Eckart, Peter. 1996. Spaceflight Life Support and Biospherics. Torrance: Microcosm Press

3. Ferrall, J.F., G.B. Ganapathi, N.K. Rohatgi and P.K. Seshan. 1994. Life Support Systems Analysis and Technical Trades for a Lunar Outpost. NASA Technical Memorandum 109927

4. Horneck, G., DLR, "Advanced Life Support Systems and Human Exploratory Missions", 2nd Workshop on Advanced Life Support, ESTEC, 17-18 April 2002.

5. NASA Research Opportunities Online. 2002. Advanced Life Support Program (ALS) and the Advanced Environmental Monitoring and Control (AEMC) Program Technology Assessment Matrix. Available from the World Wide Web: http://research.hq.nasa.gov/code_u/matrix/index.cfm.

6. Verostko, C., J. Joshi, M. Alazraki and J. Fisher. 2002. Solid Waste Processing and Resource Recovery Workshop Report - Vol I. Engineering Directorate, Crew and Thermal Systems Division. CTSD-ADV-474. Available also from the World Wide Web: http://advlifesupport.jsc.nasa.gov/PubNew.html

7. Verostko, C., J. Joshi, M. Alazraki and J. Fisher. 2002. Solid Waste Processing and Resource Recovery Workshop Report Appendix - Vol II. Engineering Directorate, Crew and Thermal Systems Division. CTSD-ADV-474. Available also from the World Wide Web: http://advlifesupport.jsc.nasa.gov/PubNew.html

8. Hanford, A. J. and M. K. Ewert. 2001. Advanced Life Support Systems Integration, Modeling, and Analysis Reference Missions Document. Engineering Directorate, Crew and Thermal Systems Division. CTSD-ADV-383. Available also from the World Wide Web: http://advlifesupport.jsc.nasa.gov/PubNew.html


http://advlifesupport.jsc.nasa.gov/PubNew.html



http://www.ga.com/atg/aps/scwo.html


9. Hanford, A. J., M. K. Ewert and D. L. Henninger. 2002. Advanced Life Support Baseline Values and Assumptions Document. Engineering Directorate, Crew and Thermal Systems Division. CTSD-ADV-383. Available also from the World Wide Web: http://advlifesupport.jsc.nasa.gov/PubNew.html

10. National Aeronautics and Space Administration. Waste Collection System Workbook WCS 2102C. November 26, 1984. Johnson Space Center. Advanced Training Series. Training Division. Systems Training Branch.

11. Walex Products, Portable Sanitation, <http://www.walex.com/pages/portable.html> (9 December 2002).

12. Toico Industries, Cleaning Supplies, <http://www.toico.com/cleaningsupplies.html> (9 December 2002).


http://www.toico.com/cleaningsupplies.html

http://www.walex.com/pages/portable.html



8.0 FOOD SUPPLY8.1 Baseline Functional Requirements

Food Supply needs to supply the six crew members with the proper amount of protein, carbohydrates and fat daily for the mission duration. Below, Table 8-8-21 shows the input masses of these basic food constituents. These masses correlate with the Metabolic Load Balance shown in section 2.3.

Table 8-8-21. Mass of Food Type (kg/person-day)6

Food Type Chemical Composition

Carbon Hydrogen Oxygen Nitrogen Total

Protein C4H5ON 0.0770 0.0081 0.0257 0.0255 0.1332Carbohydrate C6H12O6 0.1489 0.0250 0.1984 0 0.3723Fat C16H32O2 0.0858 0.0144 0.0143 0 0.1145

The above table shows values before the 10% per person-day safety factor is added. Therefore, the total mass for each food type is now is shown Table 8-22,

Table 8-22. Food Type Mass

Food Type Mass(kg/person-day)

Protein 0.1465 Carbohydrate 0.4095 Fat 0.1260 Total Daily Allowance 0.6820 (dry)Water Content 1.2650Total Daily Allowance 1.9470 (wet)

This will provide each crew member with a low fat, high carbohydrate diet with the following percentages shown in Table 8-23.

Table 8-23. Percent of Food Type Per Daily Meal

Food Type Percentage of Daily Meal

Protein 25%Carbohydrate 70%Fat 5%

US Recommend Daily Allowances (USRDA) show that a minimum of 2000 kcal/day is needed to provide the minimum amount of nutrients and vitamins. Based on the above amounts, Table 8-24 shows the amount of calories that is to be provided.



Table 8-24. Caloric Provision

Food Type Mass in gramsCalories per

gram8 Total CaloriesProtein 146.630 4 586.520Carbohydrate 409.530 4 1638.120Fat 12.595 9 113.355

Total kcals 2337.995

Table 8-25 and Table 8-26 show the recommended amounts of vitamins and minerals for mission duration ranges. This is a requirement to provide nutritional meals to the crew members, but was not included in the trade study.

Table 8-25. Daily Recommended Vitamin Intake for Mission 30 day to 1 year2

Nutrient Recommendation Amount

Vitamin A 1000μg

Vitamin D 10 μg

Vitamin E 20 mg

Vitamin K 65-80 μg

Vitamin C 100 mg

Vitamin B12 2 μg

Vitamin B6 2 mg

Thiamin 1.5 mg

Riboflavin 2 mg

Folate 400 μg

Niacin 20 mg

Biotin 100 μg

Pantothenic Acid 5 mg



Table 8-26 Daily Recommended Mineral Intake for Mission 30 day to 1 year2

Nutrient Recommendation Amount

Calcium 1000-1200 mg

Phosphorus 1000-1200 mg

Magnesium 280-350 mg

Sodium <3500 mg

Potassium 3500 mg

Iron 10 mg

Copper 1.5-3.0 mg

Manganese 2.0-5.0 mg

Fluoride 4.0 mg

Zinc 15 mg

Selenium 70 μg

Iodine 150 μg

Chromium 100-200 μg

8.2 Baseline ArchitectureThe baseline open loop design concept is to bring everything along at launch with no re-supply. Therefore, the Food Supply subsystem will need to bring along the food and preparation water for the entire mission duration of 780-days (transit and surface stay). Figure 8-14 shows the basic open loop food subsystem block diagram. shows the masses for the food subsystem components.



Freezer Oven Microwave

Fresh Food Storage

Food Preparation

Human H2O

Heat

Waste Waste

Figure 8-14 Food Subsystem Baseline Open Loop Design

Table 8-27. Baseline Open Loop Subsystem Component Mass

Component Description Mass (kg) Mass for 6 Crew Members Per Day (kg)

Fresh Food (wet) 1.9470 (person-day) 11.682Packaging 0.5/day N/CFreezer/Refrigerator 400/unit N/CMicrowave 35/unit N/COven 50/unit N/CFood Prep Water 0.8690 (person-day) 5.214Total 488.316 502.396

Using the numbers in , the total mass needed for the Food Supply Subsystem can be calculated for the entire mission duration. Table 8-28 shows the total mass per phase and the total mass.

Table 8-28. Total Subsystem Baseline Mass

Phase Mass (kg/six-CM)Transit (180 days) 3616.20Surface Stay (600 days) 10173.60



Total Subsystem Mass 13789.80

8.3 Subsystem AssumptionsAssumptions made throughout the trade study process are identified. At a high level, assumptions must be stated to allow proper interface between subsystems. In the subsystem level, it is necessary to record all assumptions to ensure accurate comparison between technologies.

The following assumptions have been made when designing the Food Supply Subsystem:

Any Biological Regenerable Plant Growth system will only be a supplement not a back up to the base line food supply scheme.

Food will be allotted by daily allowances. Trading one day’s meals for another will be allowed, but consumption will be limited to one daily allowance per day.

Each daily allowance will met the minimum RDA levels of vitamins and minerals (per Table 8-25 and Table 8-26).

10% for each person/day was added to the baseline daily requirements for Protein, Carbohydrates and Fat. This assumption will provide:

o Additional food for variance in kcal/person intakeo Additional food for contingency (mission duration is longer than

planned)o Additional food for variance in eating habits between crew members

Packaging mass is assumed to be 0.5 kg/day of food.7

Water to prepare or re-hydrate any food will be provided by the water management subsystem.

The choose food technology type will contain the minimum vitamin and mineral content shown in Table 8-5 and 8-6 above.

8.4 Candidate TechnologiesA preliminary list of candidate technologies has been established to satisfy the requirements for the Food Supply Subsystem. The candidate technologies are identified in Table 8-29 and are mapped to the function that they help provide. Biological technologies shown here are for additional information only and were not part of the trade study. The DRM constrained the design to using Physio-Chemical Technologies as the primary system basis, and biological only as an experimental supplement.



Table 8-29. Candidate Technologies for Food Supply

Food Supply Function Candidate Technologies

Supply Food

Rehydratable Food3

Thermostabilized Food3

Intermediate Moisture Food3

Natural Form Food3

Irradiated Meat3

Candidates but not as primary source Algae4

Fungi4

Hydroponics – Vegetable Plant Growth4

o Nutrient Film Technique5

o Gravel Culture System5

o Sand Culture System5

o Sawdust Culture System5

o Rockwool Culture System5

Aeroponics4

Zenoponics4

Animals as food4

Aquaculture4

8.5 Subsystem Technology Trade StudyFor the food supply subsystem trades, the overall mass was the driving trade variable. The goal of the trade study was to minimize overall subsystem mass while still providing all the nutrient and mineral requirements to the crew members. The four main food types used in the trade were; Dehydrated, Fresh/Natural Form, Frozen and Thermo-stabilized. Figure 8-15 shows a comparison of subsystem mass including consumables using all of one type or a mix.



0

2000

4000

6000

8000

10000

12000

Total Weight in Kilograms (kg)

1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21Trade Case Number

Total Food Weight Comparison

Thermal StablizedFrozenDehydratedFresh

Figure 8-15 Food Supply Comparison Graph

8.5.1 ResultsFrom Figure 8-15 it can be seen that a food supply solely of dehydrated food is the lowest overall mass. Figure 8-16 shows the new system. The oven and freezer/refrigerator are no longer needed, because all the food is dehydrated. Also, the water content within the food is no longer an additional mass to the food supply subsystem. In the integrated design, the water content of the food is negligible and the re-hydration water will come from the water management subsystem. This differs from bringing all the re-hydration water along which was the baseline open loop design.



Microwave

Fresh Food Storage

Food Preparation

Human H2O

Heat

Waste Waste

Microwave

Figure 8-16 Closed Loop Design for Food Supply Subsystem

Table 8-10. Closed Loop Mass for Food Supply Subsystem

Component # Weight (kg)Add. Weight

(kg)Total Weight

(kg)Dehydrated Food 1 3612.27 722.45 4334.73Microwave 2 70.00 14.00 154.00

Totals 4488.73

Comparing to the 13789.80 kg subsystem mass for the open loop design, closing the water loop to provide food prep water and removing the water content in the food supply is a large savings. The trade and redesign has provided a mass savings of 32.5% for the food supply subsystem.

8.6 Food Supply Subsystem References1. Hoffman, S.J., Kaplen, D.L., “Human Exploration of Mars: The Reference Mission of the NASA Mars Exploration Study Team”; 19972. NASA FTGSC Space Food Insights http://www.ag.iastate.edu/centers/ftcsc/pages/insig.htm3. ASEN 5116 Class Notes, “Food Supply”; November 12, 2002. University of Colorado – Boulder. http://www.colorado.edu/ASEN/asen5116/Lect-18.htm 4. Spacecraft Life Support and Biospherics, Eckart, 1996.


http://www.colorado.edu/ASEN/asen5116/Lect-18.htm

http://www.ag.iastate.edu/centers/ftcsc/pages/insig.htm


5. Hydroponic Food Production, Horward M. Resh, Ph.D, 20016. Ferral, J.F., Ganapathi, G.B., Rohatgi, N.K., Seshan, P.K., “Life Support Systems Analysis and Technical Trades for a Lunar Outpost” NASA Technical Memorandum 109927, 1994.7. Larson, W.J., Pranke, L.K., Human Spaceflight: Mission Analysis and Design, MacGraw-Hill, New York.8. Guyton, A.C., Hall, J.E., Textbook of Medical Physiology, W.B. Saunders Company, Pennsylvania, 2000.



9.0 SYSTEM INTEGRATE DESIGN RESULTS9.1 System Architecture

The integrated system is comprised of four subsystems: Atmosphere Management (AM), Food Supply (FS), Water Management (WM), and Waste Processing (WP). The details of each subsystem are discussed in earlier sections and the interactions are highlighted here. The main interactions within the system are between AM, WM, and WP. AM takes inputs from WP in the form of output gases from the Pyrolysis system and outputs CO2 to WP as feed gases to the Pyrolysis system. WP takes input of all wastes from AM, FS, and WM. The WM subsystem takes in H2O produced by WP during pyrolysis processing as well as the used water from laundry and hygiene. WP outputs potable and hygiene water to FS. The interactions are shown in Figure 9-17. Figure 9-18 shows the overall system diagram for the surface stay on Mars. The subsystem interactions remain the same except, except that the AM subsystem interfaces with ISRU plant on Mars to take advantage of the Martian resources.



Human AccommodationsHuman Accommodations

LaundryLaundry

HygieneHygiene

WasteWaste WaterWater

FoodFoodAtmosphereAtmosphere

ProcessableProcessableMaterialsMaterialsStorageStorage


Dehydrated Dehydrated FoodFood

Food Food PreparationPreparation

MicrowaveMicrowave

HUMANHUMAN

HUMANHUMAN

HUMAN

HUMAN

UrinalUrinal CommodeCommode(Feces)(Feces)

PyrolysisPyrolysis

COCO22

Gas Separator

Gas Separator

CO

CO

22 , H, H22 , N

H, N

H33 , C

H, C

H44 , , N

ON

Oxx , , SOSO

xx

HH22OO

NN22

2BMS2BMS

SOESOE

HUMANHUMAN OO22

Pressure ControlPressure Control

COCO22

OO22


HEPA Filter

TCCS


FDS

CO

2 rich Air

COCO2 2 , H, H22

AirAir

CHCH44

Urine PretreatmentOxoneSulfuricacid

VCD

Brine H2O

ROMilli Q

MCVIodine

Monitoring

Hygiene H2O

Iodine Removal Bed

Potable H2O

NH

3 ,NO

x ,SOx

NH3, NoxSOx

COCO22

OO22

Pretreated Urine AES

Ultra Filtration

Brine H

2 O

ISE Monitoring

Feces

CompactorOther waste


LaundryLaundry

HygieneHygiene








MicrowaveMicrowave

HUMANHUMANHUMANHUMAN

HUMANHUMAN

HUMAN

HUMANHUMAN


PyrolysisPyrolysis

COCO22

Gas Separator

Gas Separator

CO

CO

22 , H, H22 , N

H, N

H33 , C

H, C

H44 , , N

ON

Oxx , , SOSO

xx

HH22OO

NN22NN22

2BMS2BMS

SOESOE

HUMANHUMAN OO22


COCO22

OO22


HEPA Filter

TCCS


FDS

CO

2 rich Air

COCO2 2 , H, H22

AirAir

CHCH44


PretreatmentOxoneSulfuricacid

VCD

Brine H2O

ROMilli Q

MCVIodine

Monitoring

Hygiene H2O

Iodine Removal Bed

Potable H2O

NH

3 ,NO

x ,SOx

NH3, NoxSOx

COCO22

OO22


Ultra Filtration

Brine H

2 O

ISE Monitoring

Feces



LaundryLaundry

HygieneHygiene







MicrowaveMicrowave

HUMANHUMAN

HUMANHUMAN

HUMAN

HUMAN


PyrolysisPyrolysis

COCO22

Gas Separator

Gas Separator

CO

CO

22 , H, H22 , N

H, N

H33 , C

H, C

H44 , , N

ON

Oxx , , SOSO

xx

HH22OO

NN22

2BMS2BMS

SOESOE

HUMANHUMAN OO22


COCO22

OO22


HEPA Filter

TCCS


FDS

CO

2 rich Air

COCO2 2 , H, H22

AirAir

CHCH44


VCD

Brine H2O

ROMilli Q

MCVIodine

Monitoring

Hygiene H2O

Iodine Removal Bed

Potable H2O

NH

3 ,NO

x ,SOx

NH3, NoxSOx

COCO22

OO22


Ultra Filtration

Brine H

2 O

ISE Monitoring

Feces



LaundryLaundry

HygieneHygiene








MicrowaveMicrowave


HUMANHUMAN

HUMAN

HUMANHUMAN


PyrolysisPyrolysis

COCO22

Gas Separator

Gas Separator

CO

CO

22 , H, H22 , N

H, N

H33 , C

H, C

H44 , , N

ON

Oxx , , SOSO

xx

HH22OO

NN22NN22

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SOESOE

HUMANHUMAN OO22


COCO22

OO22


HEPA Filter

TCCS


FDS

CO

2 rich Air

COCO2 2 , H, H22

AirAir

CHCH44



VCD

Brine H2O

ROMilli Q

MCVIodine

Monitoring

Hygiene H2O

Iodine Removal Bed

Potable H2O

NH

3 ,NO

x ,SOx

NH3, NoxSOx

COCO22

OO22


Ultra Filtration

Brine H

2 O

ISE Monitoring

Feces


C

Vent


LaundryLaundry

HygieneHygiene







MicrowaveMicrowave

HUMANHUMAN

HUMANHUMAN

HUMAN

HUMAN


PyrolysisPyrolysis

COCO22

Gas Separator

Gas Separator

CO

CO

22 , H, H22 , N

H, N

H33 , C

H, C

H44 , , N

ON

Oxx , , SOSO

xx

HH22OO

NN22

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SOESOE

HUMANHUMAN OO22


COCO22

OO22


HEPA Filter

TCCS


FDS

CO

2 rich Air

COCO2 2 , H, H22

AirAir

CHCH44


VCD

Brine H2O

ROMilli Q

MCVIodine

Monitoring

Hygiene H2O

Iodine Removal Bed

Potable H2O

NH

3 ,NO

x ,SOx

NH3, NoxSOx

COCO22

OO22


Ultra Filtration

Brine H

2 O

ISE Monitoring

Feces



LaundryLaundry

HygieneHygiene








MicrowaveMicrowave


HUMANHUMAN

HUMAN

HUMANHUMAN


PyrolysisPyrolysis

COCO22

Gas Separator

Gas Separator

CO

CO

22 , H, H22 , N

H, N

H33 , C

H, C

H44 , , N

ON

Oxx , , SOSO

xx

HH22OO

NN22NN22

2BMS2BMS

SOESOE

HUMANHUMAN OO22


COCO22

OO22


HEPA Filter

TCCS


FDS

CO

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COCO2 2 , H, H22

AirAir

CHCH44



VCD

Brine H2O

ROMilli Q

MCVIodine

Monitoring

Hygiene H2O

Iodine Removal Bed

Potable H2O

NH

3 ,NO

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COCO22

OO22


Ultra Filtration

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MicrowaveMicrowave

HUMANHUMAN

HUMANHUMAN

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HUMAN


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COCO22

Gas Separator

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CO

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H, N

H33 , C

H, C

H44 , , N

ON

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xx

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NN22

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SOESOE

HUMANHUMAN OO22


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OO22


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TCCS


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ROMilli Q

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HUMAN

HUMANHUMAN


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CO

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H, N

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ON

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xx

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COCO2 2 , H, H22

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Iodine Removal Bed

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NH

3 ,NO

x ,SOx

NH3, NoxSOx

COCO22

OO22


Ultra Filtration

Brine H

2 O

ISE Monitoring

Feces


C

Vent

Figure 9-17 System Block Diagram – Transit




LaundryLaundry

HygieneHygiene

WasteWaste


NonNon --processableprocessableMaterialsMaterialsStorageStorage



MicrowaveMicrowave

HUMANHUMAN

HUMANHUMAN

HUMANHUMANPyrolysisPyrolysis

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H, N

H33 , C

H, C

H44 , , N

ON

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xx

HH22OO

NN22

TSATSASabatierSabatier



HH22

COCO 22

Low COLow CO 22 AirAir

HH22OO

OO22

HEPA Filter

TCCS


FDS

CO

2 rich Air

COCO 2 2 , H, H 22

AirAir

CHCH 44

CHCH 44

NH

3 , NO

x , SOx

NH3, Nox

SOx

WaterWater

HUMAN Urine PretreatmentOxoneSulfuricacid

VCD

Brine H2O

ROMilli QMCV

IodineMonitoring

Hygiene H 2O

Iodine Removal Bed

Potable H 2O


Ultra Filtration

Brine H2 O

ISE Monitoring

ProcessableProcessableMaterialsMaterialsStorageStorageUrinalUrinal CommodeCommode

(Feces)(Feces) Feces


Mars

Mars

Atmosphere

Atmosphere

ISRUISRU


LaundryLaundry

HygieneHygiene

WasteWaste






MicrowaveMicrowave


HUMANHUMAN

HUMANHUMANHUMANHUMANPyrolysisPyrolysis

COCO 22

Gas Separator

Gas Separator

CO

CO

22 , H, H22 , N

H, N

H33 , C

H, C

H44 , , N

ON

Oxx , , SOSO

xx

HH22OO

NN22NN22

TSATSATSASabatierSabatier



HH22HH22

COCO 22


HH22OO

OO22

HEPA Filter

TCCS


FDS

CO

2 rich Air

COCO 2 2 , H, H 22

AirAir

CHCH 44

CHCH 44

NH

3 , NO

x , SOx

NH3, Nox

SOx

WaterWater



VCD

Brine H2O

ROMilli QMCV

IodineMonitoring

Hygiene H 2O

Iodine Removal Bed

Potable H 2O


Ultra Filtration

Brine H2 O

ISE Monitoring




Mars

Mars

Mars

Atmosphere

Atmosphere

Atmosphere

ISRUISRU


LaundryLaundry

HygieneHygiene

WasteWaste






MicrowaveMicrowave


HUMANHUMAN


COCO 22

Gas Separator

Gas Separator

CO

CO

22 , H, H22 , N

H, N

H33 , C

H, C

H44 , , N

ON

Oxx , , SOSO

xx

HH22OO

NN22NN22

TSATSASabatierSabatier



HH22HH22

COCO 22


HH22OO

OO22

HEPA Filter

TCCS


FDS

CO

2 rich Air

COCO 2 2 , H, H 22

AirAir

CHCH 44

CHCH 44

NH

3 , NO

x , SOx

NH3, Nox

SOx

WaterWater



VCD

Brine H2O

ROMilli QMCV

IodineMonitoring

Hygiene H 2O

Iodine Removal Bed

Potable H 2O


Ultra Filtration

Brine H2 O

ISE Monitoring




Mars

Mars

Atmosphere

Atmosphere

ISRUISRU


LaundryLaundry

HygieneHygiene

WasteWaste






MicrowaveMicrowave


HUMANHUMAN


COCO 22

Gas Separator

Gas Separator

CO

CO

22 , H, H22 , N

H, N

H33 , C

H, C

H44 , , N

ON

Oxx , , SOSO

xx

HH22OO

NN22NN22

TSATSATSASabatierSabatier



HH22HH22

COCO 22


HH22OO

OO22

HEPA Filter

TCCS


FDS

CO

2 rich Air

COCO 2 2 , H, H 22

AirAir

CHCH 44

CHCH 44

NH

3 , NO

x , SOx

NH3, Nox

SOx

WaterWater



VCD

Brine H2O

ROMilli QMCV

IodineMonitoring

Hygiene H 2O

Iodine Removal Bed

Potable H 2O


Ultra Filtration

Brine H2 O

ISE Monitoring




Mars

Mars

Mars

Atmosphere

Atmosphere

Atmosphere

ISRUISRU

Mars

Mars

Mars

Atmosphere

Atmosphere

Atmosphere

ISRUISRU

Figure 9-18 System Block Diagram - Surface



9.2 Mass Balance Results9.3 Equivalent System Mass Results

The integrated system design ESM was calculated with the information provided in Figure 9-19. This figure show the breakdown of each subsystem and its’ components and the values that were obtain or estimated for Mass, Power and Volume. The additional weight column provides inclusion of consumables, such as LiOH canisters, piping and storage tank components.



CLOSED LOOP ESMAtmosphere

Component #Weight

(kg)

Add. Weight

(kg)

Total Weight

(kg)Power (kW)

Total Power (kw)

Volume (m3)

Total Volume

(m3)

Crew Time

(hrs/day)Portable Fire Extinguisher (PFE) 3 15.10 0.00 45.30 0.00 0.00 0.04 0.12 0.00Scattering Smoke Detector 8 1.50 0.00 12.00 0.00 0.02 0.04 0.32 0.00Portable Breathing Apparatus 12 2.80 0.00 33.60 0.00 0.00 0.31 3.72 0.00UV/IR Flame Detector 3 3.70 0.00 11.10 0.10 0.30 0.00 0.01 0.00Pressure Control 1 74.00 0.00 74.00 0.10 0.10 0.41 0.41 0.00Pressure Control Sensors 2 2.00 0.00 4.00 0.01 0.01 0.00 0.03 0.00Gas Chromatograph/Mass Spectrometer (mini) 3 1.80 0.00 5.40 0.02 0.05 0.03 0.09 0.00Trace Contaminant Control Subassembly (TCCS) 1 78.20 163.00 241.20 0.18 0.18 0.50 0.50 0.01HEPA Filters 15 2.00 260.00 290.00 0.00 0.00 0.10 1.50 0.01Common Cabin Air Assembly 2 112.00 0.00 224.00 0.47 0.94 0.40 0.80 0.00Intermodule Ventilation Fan 2 4.76 0.00 9.52 0.55 1.10 0.01 0.02 0.00Intermodule Ventilation Valve 12 5.10 0.00 61.20 0.01 0.07 0.01 0.12 0.00Cabin Fan Assembly 1 26.90 0.00 26.90 0.41 0.41 0.15 0.15 0.002 Bed Molecular Sieve 2 96.00 28.80 220.80 0.50 0.50 0.60 1.20 0.00Solide Oxide Electrolysis 2 220.00 44.00 484.00 6.50 6.50 0.80 1.60 0.00Oxygen Buffer Tank 1 100.00 34.00 134.00 0.00 0.00 0.45 0.45 0.00Nitrogen Buffer Tank 1 26.00 18.90 44.90 0.00 0.00 0.25 0.25 0.00

Totals 1921.92 10.16 11.28 0.02

Water

Component #Weight

(kg)

Add. Weight

(kg)

Total Weight

(kg)Power (kW)

Total Power (kw)

Volume (m3)

Total Volume

(m3)

Crew Time

(hrs/day)VCD 1 101.00 43.80 144.80 0.12 0.12 0.49 0.49 0.00AES 1 45.00 30.00 75.00 1.00 1.00 0.30 0.30 0.01UF/RO 2 90.00 34.00 214.00 0.60 0.60 0.35 0.70 0.01MiilQ 2 11.00 85.68 107.68 0.00 0.00 0.06 0.12 0.01MCV 4 10.00 3.80 43.80 0.01 0.01 0.06 0.24 0.00Iodine removal bed 2 5.00 10.00 20.00 0.00 0.00 0.06 0.12 0.01Quality Monitor 2 39.00 12.00 90.00 0.08 0.08 0.08 0.16 0.08Urine/RO Brine Storage Tank 1 3.60 0.00 3.60 0.00 0.00 0.06 0.06 0.00VCD Brine Storage Tank 1 5.00 0.00 5.00 0.00 0.00 0.08 0.08 0.00Water Storage 1 32.43 0.00 32.43 0.20 0.20 0.61 0.61 0.00Plumbing 20% Hardware 1 101.40 0.00 101.40 0.00 0.00 0.06 0.06 0.00Buffer Water 1 324.28 0.00 324.28 0.00 0.00 0.00 0.00 0.00

Totals 1161.99 2.01 2.94 0.12

Waste

Component #Weight

(kg)

Add. Weight

(kg)

Total Weight

(kg)Power (kW)

Total Power (kw)

Volume (m3)

Total Volume

(m3)

Crew Time

(hrs/day)Toilet assembly 1 16.00 19.20 35.20 0.22 0.22 0.08 0.08 0.08Septic tank 1 14.50 2.90 17.40 0.00 0.00 0.10 0.10 0.00Compactor 1 15.10 10.84 25.94 0.11 0.11 0.36 0.36 0.00Pyrolysis 1 60.00 24.00 84.00 0.60 0.60 0.00 0.00 0.08Non-processables Storage 1 50.00 0.00 50.00 0.00 0.00 2.00 2.00 0.08

Totals 212.54 0.93 2.54 0.25

Food

Component #Weight

(kg)

Add. Weight

(kg)

Total Weight

(kg)Power (kW)

Total Power (kw)

Volume (m3)

Total Volume

(m3)

Crew Time

(hrs/day)Dehydrated Food 1 3612.27 722.45 4334.73 0.00 0.00 37.00 37.00 3.50Microwave 2 70.00 14.00 154.00 1.80 3.60 0.15 0.30 0.00

Totals 4488.73 3.60 37.30 3.50

Grand Totals 7785.18 16.71 54.06 3.89

Figure 9-19. Final Design Subsystem Mass, Power and Volume



By using the Equations (1), the total system ESM was calculated to be 7,791 kg.

(1)

This is approximately a 102 order of magnitude savings over the Open Loop Design. Even though there are more components to the final design, the mass savings comes mostly from closing the water loop. Instead of bringing all the water that the six crew members will need, the system recycles and reclaims most of the water needed daily.



10.0 SYSTEM CONCLUSIONS & RECOMMENDATIONSThis report represents a 2nd iteration design of a life support system. The final system design shows a significant improvement over the open loop design, as seen in the final equivalent system mass results. Further improvements can be made with more iterations of the design process. With further iteration of the design, more loop closure can certainly be obtained. Also, detailed mass flows of all inter-subsystem products should be computed in more detail to insure proper interaction of the technologies.

Further development and testing of promising technologies needs to be done to improve TRLs. Particularly, further research on Advanced Carbon Formation Reactors (ACFR), Water Vapor Electrolysis (WVE), and Ammonia Dissociation would help to gain further loop closure of the overall system. Particularly, Ammonia Dissociation systems would allow for further closure of the N2 loop. Additionally, in the waste processing technologies, further development of charcoal reactivation methods would decrease the overall resupply mass of the system. Charcoal reactivation would eliminate the need to take resupply charcoal for such systems as trace contaminant control. Also, soil removal (from EVAs) was not addressed in this study, but is recognized to be a potential problem that needs to be solved.



11.0 APPENDIX A: REQUIREMENTS



Rqmt #

Rqmt Type (C,F,P,D) I/Fs Requirement Source

S010 C AM,WM,WP,FS

Limit length of time that the crew is continuously exposed to the interplanetary space environment (6 months - 8 months max). DRM Page 1-7 DRM Page 1-8

S020C AM,WM,

WP,FSThe system shall support surface operations for during of 600 days (plus safety buffer). DRM Page 1-7

S030 C AM,WM,WP,FS

The system shall use in-situ resources to the extent possible to support surface duration. DRM Page 1-7

S040 F AM,WM,WP,FS The system shall support a crew of 6 during entire mission. DRM Page 1-13

S050 D AM,WM,WP,FS Deployment of Bioregenerative life support system is to augment the LSS only. DRM Page 1-14

S060 D AM, WM The system shall use in-situ resources to produce (water, O2, N2 and Argon). DRM Page 1-16

S070 C AM,WM,WP,FS The entire mission must be completed without resupply from Earth. DRM Page 1-16

S080 F AM,WM,WP,FS

Transit Habitat must operate in 1-G Micro-G, Martian-G (3/8-G) and Launch/Decent. DRM Page 1-21

S090 D AM,WM,WP,FS During Transit power source is Solar Arrays ( 30 KW). DRM Page 1-22 DRM Page 3-98

S100 D AM,WM,WP,FS

During Surface power source is 2 Nuclear reactors (Primary and Backup each capable of 160 KW) (50 kW) and solar arrays used during flight. DRM Page 1-22 (Appendix A.3.2.2 page 2)

S110 F AM The system must provide contamination and particle control. DRM Page 1-35

S120 C AM,WM,WP,FS The system must have as much loop closure as possible. DRM Page 1-35

S130 F AM,WM,WP,FS The system shall promote introduction of locally produced consumables. DRM Page 1-35

S140 F FS The system must be able to produce food. DRM Page 1-35S150 F WP The system must collection and process trash and waste. DRM Page 1-35

S160 P AMThe system must have a high efficiency and lighter weight active thermal control system. DRM Page 1-35

S170 F AM The system must provide fire detection, prevention and suppression. DRM Page 1-35

S180 D AM,WM,WP,FS Total system mass should not exceed 10.7 tons. DRM Page 3-82 (Appendix A.3.2.2 page 2)

S190 D AM,WM,WP,FS Life Support mass should not exceed 4661 kg. (Appendix page 3 of 8, Table A4-2)

S200 D AM,WM,WP,FS Total system power should not exceed 12.7 KW. DRM Page 3-93



System Requirements

Rqmt #


S210 F AM,WM,WP,FS The system should have two backup levels functional redundancy. DRM Page 3-99

S220 F AM,WM,WP,FS

Crews will have the capability to explore in the vicinity of the surface outpost out to 500 kilometers. DRM, page 1-8

S230 F AM,WM,WP,FS

Long-range surface rovers will have the capability to operate at a remote site for up to 10 days with total trip time of less than 14 days. DRM, page 1-23

S240 F AM,WM,WP,FS

During remote site operations, up to 16-hours will be available for EVA operations. DRM, page 1-23 & 3-50

S250 F AM,WM,WP,FS

Long-range surface rovers will have the capability to carry 2 persons, or 4 persons in the event of an emergency. DRM, page 1-23

S260 P AM,WM,WP,FS

Systems must be highly reliable and highly autonomous to improve the effectiveness of surface operations. DRM, page 1-8

S270 F AM,WM,WP,FS

The system should allow for 2 emergency EVAs during transit by 2 crew members with an 8-hour duration. DRM Addendum, page 15

S280 F AM,WM,WP,FS

The system should allow for 1 8-hour EVA per week during surface operations. DRM Addendum, page 15-16

S290C AM,WM,

WP,FSMars must be protected from biological contamination from Earth that would interfere with or confound the search for natural Martian organisms. DRM, page 1-37

S300 D AM,WM,WP,FS The first level of life support redundancy should be fully automated. DRM, page 3-15

S310 C AM,WM,WP,FS

The Earth-Mars and Mars-Earth transit times will not exceed 180 days and will not be less than 120 days. DRM, page 3-42

S320 D AM,WM,WP,FS

All life support systems should use common hardware and software whenever possible. DRM, page 3-61

S330 F AM,WM,WP,FS Life critical systems will require automatic fault detection. DRM, page 3-62

S340 C AM,WM,WP,FS

The earth return vehicle life support system will be able to operate autonomously for up to 4 years. DRM, page 3-86

S350D AM,WM,

WP,FS

The earth return and crew transit/surface habitat vehicles will have an internal volume defined by a 7.5 meter diameter cylinder that is 4.6 meters long with elliptical end-caps. DRM, page 3-90



System Requirements

Rqmt #


S360D AM,WM,

WP,FS

The earth return and crew transit/surface habitat vehicles will have an internal habitable space defined by the 7.5 meter diameter cylinder, separated into 2 floors of 3 meters each. DRM, page 3-90

S370D AM,WM,

WP,FS

The crew transit/surface habitat vehicle will have an inflatable Trans/Hab with an internal volume defined by a 7.5 meter diameter cylinder that is 4.6 meters long with elliptical end-caps. DRM, page 3-90; assumption for size

S380 D AM, WMThe earth return vehicle and crew transit/surface habitat vehicle will have no more than 0.5 kg/day of gas leakage. Larson & Prank, 2000, page 568

S390D AM

The earth return vehicle and crew transit/surface habitat vehicle will have airlocks with an internal volume of 2 m3. Larson & Prank, 2000, page 568

S400 D AMLife support systems shall provide a sufficient total pressure to prevent the vaporization of body fluids NASA MSIS, section 5.1.2.1

S410 D AMLife support systems shall provide free oxygen at sufficient partial pressure for adequate respiration. NASA MSIS, section 5.1.2.1

S415 D AMLife support systems shall provide oxygen at a partial pressure not so great as to induce oxygen toxicity. NASA MSIS, section 5.1.2.1

S420 D AMLife support systems shall, for long durations (in excess of two weeks), provide some physiologically inert gas to prevent atelactasis. NASA MSIS, section 5.1.2.1

S430D AM All other atmospheric constituents provide by the life support system must be

physiologically inert or of low enough concentration to preclude toxic effects. NASA MSIS, section 5.1.2.1

S435 D AMLife support systems shall provide a breathing atmosphere composition that will minimize flame/explosive hazard. NASA MSIS, section 5.1.2.1

S440 D AM Life support systems shall provide an ambient temperature 18.3-26.7 deg C. NASA MSIS, section 5.8.3.1; Eckart (1996), page 92S450 D AM, WM Life support systems shall provide a relative humidity of 25-70%. NASA MSIS, section 5.8.3.1; Eckart (1996), page 92S460 D AM Life support systems shall provide cabin ventilation of 0.076-0.203 m/s. NASA MSIS, section 5.8.3.1; Eckart (1996), page 92

S470D AM

Life support systems shall provide the capability to limit trace contaminants to the Space Maximum Allowable Concentration (SMAC) for the duration of the mission. Eckart (1996), page 94



System Requirements

Rqmt #


S480

D AM,WM,WP,FS

Each crew member will have a nominal daily schedule for the duration of the mission of:- 8 hours sleep- 5 hours light work (e.g. leisure activities)- 9 hours medium work (e.g. standard work duties)- 2 hours heavy work (e.g. exercise) Eckart (1996), page 93

S490

D AM,WM,WP,FS

During crew work periods, the summation of the individual sound pressure levels from all operating systems and subsystems should not exceed exposure limits that will cause hearing loss or interfere with voice communication. NASA MSIS, section 5.4.2.1

S500

D AM,WM,WP,FS

During crew sleep and rest periods, noise levels should not exceed noise levels that interfere with sleep or comfort and the hearing of wanted sounds.

NASA MSIS, section 5.4.2.1

S510

D AM,WM,WP,FS

Vibration generation and penetration shall be controlled to the extent that vibration energy will not cause personnel injury, interfere with task performance, induce fatigue, or contribute to the degradation of overall man/machine effectiveness during manned periods NASA MSIS, section 5.5.3.1



11.1 Atmosphere Management

Rqmt #


AM010 F WPThe Atmosphere Management subsystem will provide the capability to remove excess CO2 from the atmosphere within the vehicle. Eckart (1996), p. 176

AM020 F WM,WPThe Atmosphere Management subsystem will provide the capability to reduce excess CO2 from the atmosphere within the vehicle into usable products such H2O. Eckart (1996), p. 176

AM030 F WMThe Atmosphere Management subsystem will provide the capability to generate O2 within the vehicle. Eckart (1996), p. 176

AM040 FThe Atmosphere Management subsystem will provide the capability to monitor the total vehicle cabin pressure as well as the partial pressures of CO2, N2, and O2. Eckart (1996), p. 176

AM050 FThe Atmosphere Management subsystem will provide thermally conditioned storage for CO2, N2, and O2. Eckart (1996), p. 176

AM060 FThe Atmosphere Management subsystem will provide the capability to distribute thermally conditioned CO2, N2, and O2. Eckart (1996), p. 176

AM070 F WMThe Atmosphere Management subsystem will provide the capability to control the relative humidity within the vehicle cabin. Eckart (1996), p. 176

AM080 P WMThe Atmosphere Management subsystem will provide the capability to maintain the relative humidity between 25% and 70% within the vehicle cabin. Eckart (1996), p. 176

AM090 FThe Atmosphere Management subsystem will provide the capability to control the temperature within the vehicle cabin. Eckart (1996), p. 176; S160

AM100 PThe Atmosphere Management subsystem will provide the capability to maintain the temperature between 18° and 27° C within the vehicle cabin. Eckart (1996), p. 176

AM110 FThe Atmosphere Management subsystem will provide the capability to continuously monitor the amount of particle and microbial trace contaminants within the atmosphere in the vehicle cabin. Eckart (1996), p. 176; S110

AM120 FThe Atmosphere Management subsystem will provide the capability to continuously monitor the amount of organic contaminants (hydrocarbons) within the atmosphere in the vehicle cabin. Eckart (1996), p. 176; S110

AM130 F WPThe Atmosphere Management subsystem will provide the capability to remove partical and microbial trace contaminants from the atmosphere within the vehicle cabin. Eckart (1996), p. 176; S110

AM140 D The Atmosphere Management subsystem will provide the capability to sensors for monitoring contaminants near potential sources for those contaminants. Eckart (1996), p. 176

Atmosphere ManagementEarth Replications, Inc. Page 67


Rqmt #


AM150 FThe Atmosphere Management subsystem will provide the capability to control the speed of ventilation with the vehicle cabin. Eckart (1996), p. 176

AM160 PThe Atmosphere Management subsystem will provide the capability to control the ventilation with the vehicle cabin so that air speeds fall within 0.08-0.2 m/s. Eckart (1996), p. 176

AM170 FThe Atmosphere Management subsystem will provide the capability to detect and suppress fires with the vehicle cabin. Eckart (1996), p. 178; S170

AM180 CThe Atmosphere Management subsystem will operate autonomously with minimal crew time to keep the system functional. Eckart (1996), p. 176

AM190 CThe Atmosphere Management subsystem will continuously be exposed to the interplanetary space environment for a period of 6 - 8 months. S010

AM200 C The Atmosphere Management subsystem will support Mars surface operations for a mission duration of 600 days, with additional margin of TBD. S020

AM210 C WM,WPThe Atmosphere Management subsystem will utilize in situ resources during Mars surface operations whenever possible. S030, S130

AM220 C WM,WPThe Atmosphere Management subsystem will provide the capability to support 6 crew members throughout the life of the mission. S040

AM230 C WM,WP, FS

The Atmosphere Management subsystem may use biogenerative solutions to augment physico-chemical solutions. S050

AM240 C WM,WP, FS

The Atmosphere Management subsystem will operate for the lifetime of the mission without resupply from Earth. S070

AM250 FThe Atmosphere Management subsystem will provide the capability to operate in 1-G, Micro-G, Martian-G (3/8-G), and Launch/Decent G-loads. S080

AM260 DThe Atmosphere Management subsystem will operate with TBD kW of power while in the interplanatary environment. S090

AM270 DThe Atmosphere Management subsystem will operate with TBD kW of power during Mars surface operations. S100

AM280 DThe Atmosphere Management subsystem will operate as a closed-loop system to the extent possible. S120

AM290 D The Atmosphere Management subsystem will not weigh more than TBD kg. S190



Atmosphere Management

Rqmt #


AM300 FThe Atmosphere Management subsystem will have 2 backup levels of redundancy with the first level being automatic. S210, S300

AM310 C The Atmosphere Management subsystem will provide the capability to allow the crew to explore in the vicinity of the Mars outpost to a distance of 500 km. S220

AM320 C WM, WPThe Atmosphere Management subsystem will provide the capability for long-range surface rovers to operate at a remote site for up to 10 days with total trip time of less than 14 days. S230

AM330 CThe Atmosphere Management subsystem will provide the capability during remote site operations for up to 16-hours of EVA operations. S240

AM340 CThe Atmosphere Management subsystem will provide the capability for long-range surface rovers to support 2 persons, or 4 persons in the event of an emergency. S250

AM350 CThe Atmosphere Management subsystem will be highly reliable and highly autonomous to improve the effectiveness of surface operations. S260

AM360 CThe Atmosphere Management subsystem will support 2 emergency EVAs during transit by 2 crew members with an 8-hour duration. S270

AM370 CThe Atmosphere Management subsystem will support 1 8-hour EVA per week during surface operations. S280

AM380 C WPThe Atmosphere Management subsystem will prevent biological contamination from Earth that would interfere with or confound the seach for natural martian organisms. S290

AM390 CThe Atmosphere Management subsystem will support a Earth-Mars and Mars-Earth transit times that will not exceed 180 days and will not be less than 120 days. S310

AM400 FThe Atmosphere Management subsystem will provide automatic fault detection. S330

AM410 CThe Atmosphere Management subsystem on the earth return vehicle will be able to operate autonomously for up to 4 years. S340

AM420 DThe Atmosphere Management subsystem on the earth return and crew transit/surface habitate vehicles will have an internal habitable space defined by the 7.5 meter diameter cylinder, separated into 2 floors of 3 meters each. S360




Rqmt #


AM430 DThe Atmosphere Management subsystem on the crew transit/surface habtate vehicle will have an inflatable Transhab with an internal volume defined by a 7.5 meter diameter cylinder that is 4.6 meters long with elliptical end-caps. S370

AM440D

The Atmosphere Management subsystem for the earth return vehicle and crew transit/surface habitat vehicle will have no more than 0.5 kg/day of gas leakage. S380

AM450D

The Atmosphere Management subsystem for the earth return vehicle and crew transit/surface habitat vehicle will have airlocks with an internal volume of 2 m3. S390

AM460 DThe Atmosphere Management subsystem shall provide a total atmospheric pressure of 99.9-102.7 kPa (TBD). Eckart (1996), page 92; S400; S435

AM470 DThe Atmosphere Management subsystem shall provide a pO2 of 19.5-23.1 kPa (TBD). Eckart (1996), page 92; S410; S415; S435

AM480 DThe Atmosphere Management subsystem shall provide a pN2 of 79 kPa (TBD). Eckart (1996), page 92; S420; S430; S435

AM490 DThe Atmosphere Management subsystem shall provide a pCO2 of 0.4 kPa (TBD). Eckart (1996), page 92; S420; S430; S435

AM500 DThe Atmosphere Management subsystem shall provide an ambient temperature 18.3-26.7 deg C. Eckart (1996), page 92; S440

AM510 D WMThe Atmosphere Management subsystem shall provide a relative humidity of 25-70%. Eckart (1996), page 92; S450

AM520 DThe Atmosphere Management subsystem shall provide cabin ventilation of 0.076-0.203 m/s. Eckart (1996), page 92; S460

AM530D

Life support systems shall provide the capability to limit trace contaminants to the Space Maximum Allowable Concentration (SMAC) for the duration of the mission. S470

AM540

D

The Atmosphere Management subsystem will support each crew members nominal daily schedule for the duration of the mission of:- 8 hours sleep- 5 hours light work (e.g. leisure activities)- 9 hours medium work (e.g. standard work duties)- 2 hours heavy work (e.g. exercise) S480




Rqmt #


AM550

D

During crew work periods, the Atmosphere Management subsystem will not contributute to the sound pressure levels from all operating systems and subsystems such that it exceeds exposure limits that will cause hearing loss or interfere with voice communication. S490

AM560

D

During crew sleep and rest periods, the Atmosphere Management subsystem willnoise levels should not exceed noise levels that interfere with sleep or comfort and the hearing of wanted sounds.

S500

AM570

DThe Atmosphere Management subsystem will vibration generation shall be controlled to the extent that vibration energy will not cause personnel injury, interfere with task performance, induce fatigue, or contribute to the degradation of overall man/machine effectiveness during manned periods S510



11.2 Water Management

Rqmt #


WM010 F AM, WP, FSThe Water Management subsystem will collect all waste water provided created on the vehicle JSC-38571

WM020 F AM, WP, FSThe Water Management subsystem will provide hygiene quality water as outlined in JSC-38571 Eckart (1996)

WM030 F AM, WP, FSThe Water Management subsystem will provide potable quality water as outlined in JSC-38571 Eckart (1996)

WM040 FThe Water Management subsystem will provide the capability for constant monitoring of conductivity, pH and TOC. Sauer (1991)

WM050 FThe Water Management subsystem will provide the capability for regular testing of turbidity and color. Sauer (1991)

WM060 FThe Water Management subsystem will provide the capacity to reprocess water which does not meet JSC-38571

WM070 FThe Water Management subsystem will process water at a sufficient rate to maintain minimum storage requirements JSC-38571

WM080 FThe Water Management subsystem will provide water storage to meet contingency needs JSC-38571

WM090 FThe Water Management subsystem will provide storage for makeup water for losses within the system

WM100 D The Water Management subsystem will be regenerable to the extent possible DRM

WM110 DThe Water Management subsystem will rely on in-situ resource utilization on the surface of mars DRM

WM120 D The Water Management subsystem will meet all system requirements S010-S510



11.3 Waste Management

Rqmt #


WP010 F AM, WM, FSThe Waste Processing Subsystem will provide biological waste collection, treatment/processing and removal. S150, Eckart (1996), page 237

WP020 F AM, FSThe Waste Processing Subsystem will be in charge of non-consumable waste collection, treatment/processing and removal. S150, Eckart (1996), page 238

WP030 F AM, WM, FSThe Waste Processing Subsystem will be responsible for maintaining spacecraft/habitat areas free of non-aerial contaminants. S150

WP040 F AM, WM, FSThe Waste Processing Subsystem will be responsible for preventing waste build-up. S150

WP050 D AM, WM, FSThe Waste Processing Subsystem will only rely on physico-chemical processes for stabilization, treatment/processing and removal of waste. S150

WP060 F AM, WM, FSThe Waste Processing Subsystem will remove all biological waste (vomit, menses and feces), except urine. S150, Eckart (1996), page 238

WP070 F AM, WM, FSThe Waste Processing Subsystem will treat/process biological waste (vomit, menses and feces). S150, Eckart (1996), page 238

WP080 F AM, WM, FS The Waste Processing Subsystem will handle used batteries. S150, Eckart (1996), page 238

WP090 F AM, WM, FSThe Waste Processing Subsystem will handle general waste (cans, trays, wrappers, utensils). S150

WP100 F AM, WM, FS The Waste Processing Subsystem will handle sanitary paper. S150

WP110 F AM, WM, FS The Waste Processing Subsystem will handle soil removal. S150

WP120 F AM, WM, FSThe Waste Processing Subsystem will handle food waste (food scraps, leftovers). S150

WP130 F AM, WM, FSThe Waste Processing Subsystem will handle plant biomass (if biological processes are included in the habitat). S150



11.4 Food Supply

Rqmt #


FS010 F The Food Supply Subsystem will provide daily allowance amount of protein. S140

FS020 F The Food Supply Subsystem will provide the daily allowance amount of fat. S140

FS030 FThe Food Supply Subsystem will provide the daily allowance amount of carbohydrates. S140

FS040 FThe Food Supply Subsystem will provide the daily allowance amount of calories. S140

FS050 F WMThe Food Supply Subsystem will use system recycled water for rehydration of food.

FS060 D WP The Food Supply Subsystem will minimize food packaging waste. DRMFS070 F The Food Supply Subsystem will provide food for 150 + 600 days. DRM

FS080 CThe Food Supply Subsystem will use a regenerable food supply system on Mars as a supplement. DRM

FS090 C Food supply will be managed on a daily basis. FS100 F Mineral content will meet minimum the RDA. NASA FTGSCFS110 F Vitamin content will meet minimum the RDA. NASA FTGSC



12.0 SUBSYSTEM PHYSICAL/CHEMICAL PROCESS FLOW SCHEMATICS

12.1 Atmosphere Management

CO2 Removal Specification Sheets

Subsystem Atmosphere ManagementFunction CO2 ConcentrationTechnology 2 Bed Molecular SieveComponent Weight (kg) 96Additional Weight (kg) NonePower (kW) 0.46Volume (m3) 0.52Operating Temperature (K) 338

Operating Pressure (kPa) 0,395TRL (1-9) 9 (as used on ISS)Reliability High

Gravity Dependence High

Safety Unknown

AdvantagesSimple. No humidity removal sorbent needed; needs half the power of 4 bed

Molecular SieveDisadvantages Low, as System is already well defined


AirAir CMSCMS SorbentSorbent Bed Bed ((AdsorbtionAdsorbtion))

CCOO22

Revitalized AirRevitalized Air

CMSCMS SorbentSorbent Bed Bed ((DesorbtionDesorbtion))

CompressorCompressor COCO22 (compressed)(compressed)

2 BED MOLECULAR SIEVE2 BED MOLECULAR SIEVE

AirAir CMSCMS SorbentSorbent Bed Bed ((AdsorbtionAdsorbtion))

CCOO22


CMSCMS SorbentSorbent Bed Bed ((DesorbtionDesorbtion))

CompressorCompressor COCO22 (compressed)(compressed)


Page 75


Prospective Improvements 338




Subsystem Atmosphere Management

Function CO2 ConcentrationTechnology 4 Bed Molecular SieveComponent Weight (kg) 186Additional Weight (kg) -Power (kW) 1.07Volume (m3) 0.8Operating Temperature (K) 1.07Operating Pressure (kPa) 423TRL (1-9) 10Reliability 8


Safety HighAdvantages Can be used to Control Air Humidity

Disadvantages Needs H20 removing Bed,Needs more Power than the 2BMS

Prospective Improvements Low as System is already known well

AirAir

DesicantDesicant BedBed((AdsorbtionAdsorbtion))

DesicantDesicant Bed Bed ((AdsorbtionAdsorbtion))

DesicantDesicant Bed Bed ((DesorbtionDesorbtion))


COCO22

Low COLow CO22AirAir

Revitalized Air Revitalized Air ((rehydratedrehydrated))

Dry Dry AirAir CompressorCompressor

COCO22(compressed)(compressed)


AirAir

DesicantDesicant BedBed((AdsorbtionAdsorbtion))

DesicantDesicant Bed Bed ((AdsorbtionAdsorbtion))



COCO22



Revitalized Air Revitalized Air ((rehydratedrehydrated))

Dry Dry AirAir CompressorCompressor



Page 77



Subsystem Atmosphere ManagementFunction CO2 Concentration

Technology Air Polarized Concentration (APC)

Component Weight (kg) 67Additional Weight (kg) UnknownPower (kW) 0.222Volume (m3) 0.107Operating Temperature (K) 0.504Operating Pressure (kPa) 297TRL (1-9) NormalReliability 6 (for EDC)

Gravity Dependence Low

Safety Moderate

Advantages Needs no H2, capacity to handle large CO2 overload situations

Disadvantages Heat generated, net power consumer

Prospective Improvements High potential of Improvement.Higher TRL desirable

AIR POLARIZED COAIR POLARIZED CO22 CONCENTRATORCONCENTRATOR

AirAir ECSMECSM

OO2 2


EOSMEOSM

COCO22, O, O22

COCO22

PowerPower

HeatHeat

CompressorCompressor


AIR POLARIZED COAIR POLARIZED CO22 CONCENTRATORCONCENTRATOR

AirAir ECSMECSM

OO2 2


EOSMEOSM

COCO22, O, O22

COCO22

PowerPower

HeatHeat

CompressorCompressor


Page 78



Technology Electrochemical Depolarization Concentration (EDC)

Component Weight (kg) 67Additional Weight (kg) Unknown

Power (kW)

uses 0.062 total(Uses 0.222 AC; provides 0.16

DC)

Volume (m3) 0.107Operating Temperature (K) 0.504Operating Pressure (kPa) 297TRL (1-9) 100Reliability 6

Gravity Dependence Moderate

Safety Moderate

Advantages

CO2 concentration capacity may be regulated by current

adjustments,DC Power generated

DisadvantagesHeat Generated, Requires Supply

of H2, O2 Consumed (due to inefficiency of Reaction)

Prospective Improvements Moderate


ELECTROCHEMICAL DEPOLARIZED COELECTROCHEMICAL DEPOLARIZED CO22CONCENTRATORCONCENTRATOR

EDCEDC

AirAir

HH22

POWERPOWER

HH22OO

COCO22 and Hand H22

HEATHEAT

ELECTROCHEMICAL DEPOLARIZED COELECTROCHEMICAL DEPOLARIZED CO22CONCENTRATORCONCENTRATOR

EDCEDC

AirAir

HH22

POWERPOWER

HH22OO

COCO22 and Hand H22

HEATHEAT

Page 79




Function CO2 Concentration/ReductionTechnology LiOHComponent Weight (kg) 5975Additional Weight (kg) 1195 (20% cartridge Weight)Power (kW) NoneVolume (m3) A lotOperating Temperature (K) NoOperating Pressure (kPa) 295TRL (1-9) Normal pressureReliability 9


Safety High (40 min/day)Advantages No Heat generated,

Disadvantages High Maintainability, High Volume, High Mass,

Prospective Improvements Low

LiOH LiOH CARTRIDGESCARTRIDGES

LiOHLiOHAirAir Revitalized AirRevitalized Air

LiOH LiOH CARTRIDGESCARTRIDGES

LiOHLiOHAirAir Revitalized AirRevitalized Air

Page 80




Technology Solid Amine Water Desorption (SAWD)

Component Weight (kg) 102.6Additional Weight (kg) noPower (kW) 0.908Volume (m3) 0.42Operating Temperature (K) 0.908Operating Pressure (kPa) 373TRL (1-9) 100Reliability 6


Safety ModerateAdvantages No Heat generated,

Disadvantages Amine may be degraded, moisture content of bed must be controlled

Prospective Improvements Moderate

SOLID AMINE WATER DESORPTIONSOLID AMINE WATER DESORPTION

AirAir Revitalized AirRevitalized Air

Amine BedAmine Bed((DesorptionDesorption))

Steam Steam GeneratorGenerator

HH22OO

SteamSteamAmine BedAmine Bed(Adsorption)(Adsorption)

SteamSteam COCO22CompressorCompressor


SOLID AMINE WATER DESORPTIONSOLID AMINE WATER DESORPTION

AirAir Revitalized AirRevitalized Air

Amine BedAmine Bed((DesorptionDesorption))Amine BedAmine Bed((DesorptionDesorption))

Steam Steam GeneratorGenerator

HH22OO

SteamSteamAmine BedAmine Bed(Adsorption)(Adsorption)Amine BedAmine Bed(Adsorption)(Adsorption)

SteamSteam COCO22CompressorCompressor


Page 81


Subsystem Atmosphere ManagementFunction CO2 ConcentrationTechnology Temperature Swing AdsorbtionComponent Weight (kg) 74 Additional Weight (kg) None

Power (kW)No power on mars (better

efficiency when bed is heated with water heat from O2 Generation)

Volume (m3) 0.52Operating Temperature (K) NoneOperating Pressure (kPa) 193 – 306 (using waste heat)TRL (1-9) Mars pressureReliability 4


Safety ModerateAdvantages Operates on mars without power

Disadvantages Need mars temperatures during travel

Prospective Improvements High


TEMPERATURE SWING ADSORBTIONTEMPERATURE SWING ADSORBTION

AirAir SorbentSorbent Bed (Bed (AdsorbtionAdsorbtion) ) Day CycleDay Cycle

POWER (IF SYSTEMPOWER (IF SYSTEMIS USED DURING FLIGHT)IS USED DURING FLIGHT)


SorbentSorbent Bed (Bed (DesorbtionDesorbtion))Night CycleNight Cycle

COCO22 CompressorCompressor


TEMPERATURE SWING ADSORBTIONTEMPERATURE SWING ADSORBTION

AirAir SorbentSorbent Bed (Bed (AdsorbtionAdsorbtion) ) Day CycleDay Cycle




SorbentSorbent Bed (Bed (DesorbtionDesorbtion))Night CycleNight Cycle

COCO22 CompressorCompressor


Page 82


CO2 Reduction Specification Sheets

Subsystem Atmosphere ManagementFunction CO2 Reduction

Technology Advanced Carbon Formation Reactor

Component Weight (kg) 360Additional Weight (kg) NonePower (kW) 0.4Volume (m3) 0.3Operating Temperature (K) -0.30Operating Pressure (kPa) 1600TRL (1-9) VacuumReliability 2


Safety HighAdvantages Utilizes H2 out of CH4

Disadvantages Too high temperatureProspective Improvements Moderate


ADVANCED CARBON FORMATION REACTORADVANCED CARBON FORMATION REACTOR

SABATIERSABATIER

COCO22

HH22

POWERPOWER

HH22OO

CHCH44

HEATHEAT

Carbon Carbon FormationFormation

ReactorReactorHH22

C (solid)C (solid)

HEATHEAT

ADVANCED CARBON FORMATION REACTORADVANCED CARBON FORMATION REACTOR

SABATIERSABATIER

COCO22

HH22

POWERPOWER

HH22OO

CHCH44

HEATHEAT


ReactorReactor


ReactorReactorHH22

C (solid)C (solid)

HEATHEAT

Page 83


Subsystem Atmosphere ManagementFunction CO2 ReductionTechnology BoschComponent Weight (kg) 446Additional Weight (kg) NonePower (kW) 0.411Volume (m3) 2.50Operating Temperature (K) 0.411

Operating Pressure (kPa) 1000TRL (1-9) 130Reliability 6


Safety HighAdvantages Utilizes all O2 (only carbon gets out)

Disadvantages High re-supply of cartridges (needs crew time)



BOSCH REACTORBOSCH REACTOR

BOSCHBOSCH

COCO22

HH22

POWERPOWER

HH22OO

C (Solid)C (Solid)

HEATHEAT

BOSCH REACTORBOSCH REACTOR

BOSCHBOSCH

COCO22

HH22

POWERPOWER

HH22OO

C (Solid)C (Solid)

HEATHEAT

Page 84


Subsystem Atmosphere ManagementFunction CO2 ReductionTechnology SabatierComponent Weight (kg) 182Additional Weight (kg) 10 (Logistics)Power (kW) 0.2Volume (m3) 0.21Operating Temperature (K) 0.2Operating Pressure (kPa) 800TRL (1-9) Normal pressureReliability 6


Safety High (1.7 man hours/year)

AdvantagesSmall Volume, little Power, 99% single pass efficiency, short start up time, low re-supply, Reliable

Disadvantages CH4 needs treatment Prospective Improvements low


SABATIER REACTORSABATIER REACTOR

SABATIERSABATIER

COCO22

HH22

POWERPOWER

HH22OO

CHCH44

HEATHEAT

SABATIER REACTORSABATIER REACTOR

SABATIERSABATIER

COCO22

HH22

POWERPOWER

HH22OO

CHCH44

HEATHEAT

Page 85


Subsystem Atmosphere ManagementFunction CO2 ReductionTechnology Solid Oxide Electrolysis Component Weight (kg) 220 Additional Weight (kg) None Power (kW) 6.5Volume (m3) 0.6 Operating Temperature (K) 6.5

Operating Pressure (kPa) 1023 (good insulation hull temp. 288 K)TRL (1-9) 55Reliability 6


Safety Moderate

Advantages Generates 1 kg O2 directly from 6.8 kg CO2 per day

Disadvantages Needs power to remain hot or time to get up the temperature



SOLID OXIDE ELECTROLYSISSOLID OXIDE ELECTROLYSIS

SOESOE

COCO22

POWERPOWER

OO22

COCO22 + CO+ CO

HEATHEAT

BouduoardBouduoardReactorReactor COCO22

Used C cartridgesUsed C cartridges

SOLID OXIDE ELECTROLYSISSOLID OXIDE ELECTROLYSIS

SOESOE

COCO22

POWERPOWER

OO22

COCO22 + CO+ CO

HEATHEAT

BouduoardBouduoardReactorReactor COCO22

Used C cartridgesUsed C cartridges

Page 86


N2 Provision Specification Sheets

Subsystem Atmosphere ManagementFunction N2 ProvisionTechnology Cryogenic Storage TanksComponent Weight (kg) 26Additional Weight (kg) 15.9Power (kW) NoneVolume (m3) 0.6Operating Temperature (K) NoneOperating Pressure (kPa) UnknownTRL (1-9) 100000Reliability 5


Safety ModerateAdvantages UnknownDisadvantages High loss of gasProspective Improvements Moderate


CRYOGENIC STORAGE TANKSCRYOGENIC STORAGE TANKS

Cryogenic Cryogenic StorageStorageTankTank

NN22



NN22

Page 87


O2 Provision Specification Sheets

Subsystem Atmosphere ManagementFunction O2 ProvisionTechnology Pressurized Storage TanksComponent Weight (kg) 4634Additional Weight (kg) 1686Power (kW) NoneVolume (m3) 10Operating Temperature (K) None



Safety LowAdvantages Unknown

DisadvantagesHigh loss of gas, dangerous if hit by micrometeorites as gas is under high

pressureProspective Improvements Moderate


PRESSURIZED STORAGE TANKSPRESSURIZED STORAGE TANKS

Pressurized Pressurized StorageStorage

TankTank

NN22

PRESSURIZED STORAGE TANKSPRESSURIZED STORAGE TANKS

Pressurized Pressurized StorageStorage

TankTank

NN22

Page 88


Subsystem Atmosphere ManagementFunction O2 ProvisionTechnology Cryogenic Storage TanksComponent Weight (kg) 4634Additional Weight (kg) 1992Power (kW) Power to maintain pressureVolume (m3) 1.57Operating Temperature (K) None



Safety ModerateAdvantages UnknownDisadvantages High loss of gasProspective Improvements Moderate




NN22



NN22

Page 89


Fire Detection & Suppression (FDS) Specification Sheets

Subsystem Atmosphere ManagementFunction Fire DetectionTechnology Scattering Smoke DetectorComponent Weight (kg) 1.5Additional Weight (kg) 0.0Power (kW) 0.002Volume (m3) 0.04Operating Temperature (K) 291 - 299

Operating Pressure (kPa) 101.325TRL (1-9) 9Reliability High

Gravity Dependence None.

Safety High

Advantages-Simple operation-Well tested and proven-Used on STS and ISS

Disadvantages -NoneProspective Improvements Low


Cabin AirCabin Air

SCATTERING SMOKE DETECTOR

PowerPower HeatHeat

ScatteringScatteringSmoke DetectorSmoke Detector

Low T, PLow T, PCabin AirCabin AirCabin AirCabin Air


PowerPower HeatHeat




PowerPower HeatHeat




PowerPower HeatHeat


Low T, PLow T, PCabin AirCabin Air

Page 90


Subsystem Atmosphere ManagementFunction Fire SuppressionTechnology CO2Portable Fire ExtinguisherComponent Weight (kg) 15.1Additional Weight (kg) 0.0Power (kW) 0.0Volume (m3) 0.04Operating Temperature (K) 255

Operating Pressure (kPa) 5860.5TRL (1-9) 9Reliability High

Gravity Dependence None

Safety Medium

Advantages

-Simple operation-Well tested and proven-Used on STS and ISS-On-board systems can easily remove excess CO2 from enviroment

Disadvantages -High pressure-Potential danger of CO2 ‘cloud’



COCO22

CO2 PORTABLE FIRE EXTINGUISHER (PFE)

PowerPower

COCO22 PFEPFELow T, PLow T, P COCO22COCO22

CO2 PORTABLE FIRE EXTINGUISHER (PFE)

PowerPower

COCO22 PFEPFELow T, PLow T, P COCO22

Page 91


Subsystem Atmosphere ManagementFunction Fire SuppressionTechnology N2Portable Fire ExtinguisherComponent Weight (kg) ~15.1Additional Weight (kg) 0.0Power (kW) 0.0Volume (m3) ~0.04Operating Temperature (K) ~255

Operating Pressure (kPa) ~5860.5TRL (1-9) 9Reliability High


Safety MediumAdvantages - Simple operation

Disadvantages-High pressure-On-board systems can’t efficiently remove excess N2 from environment



NN22

N2 PORTABLE FIRE EXTINGUISHER (PFE)

PowerPower

NN22 PFEPFELow T, PLow T, P NN22NN22

N2 PORTABLE FIRE EXTINGUISHER (PFE)

PowerPower

NN22 PFEPFELow T, PLow T, P NN22

Page 92


Subsystem Atmosphere ManagementFunction Fire SuppressionTechnology Halon Portable Fire ExtinguisherComponent Weight (kg) ~15.1Additional Weight (kg) 0.0Power (kW) 0.0Volume (m3) ~0.0Operating Temperature (K) ~255

Operating Pressure (kPa) ~5860.5TRL (1-9) 9Reliability High


Safety MediumAdvantages - Foam base to stick to fires

Disadvantages

-High pressure-Toxicity-On-board systems can’t efficiently remove Halon from environment



HALON PORTABLE FIRE EXTINGUISHER (PFE)

PowerPower

Halon PFEHalon PFELow T, PLow T, P HalonHalon

HALON PORTABLE FIRE EXTINGUISHER (PFE)

PowerPower

Halon PFEHalon PFELow T, PLow T, P HalonHalon

Page 93


Subsystem Atmosphere ManagementFunction Fire Suppression

Technology Portable Breathing Apparatus (PBA)

Component Weight (kg) 2.8Additional Weight (kg) 0.0Power (kW) 0.0Volume (m3) 0.31Operating Temperature (K) UnknownOperating Pressure (kPa) 20,700TRL (1-9) 9Reliability High


Safety Medium


Disadvantages -Limited breathing time-Hose length may limit movement



PERSONAL BREATHING APPARATUS (PBA)PERSONAL BREATHING APPARATUS (PBA)

PBAPBALow T, PLow T, P

OO22OO22 PBAPBALow T, PLow T, P

OO22OO22

PERSONAL BREATHING APPARATUS (PBA)PERSONAL BREATHING APPARATUS (PBA)

PBAPBALow T, PLow T, P

OO22OO22 PBAPBALow T, PLow T, P

OO22OO22

Page 94


Trace Contaminant Control (TCC) Specification Sheets

Subsystem Atmosphere ManagementFunction Trace Contaminant Control

Technology Supercritical Water Oxidation (SCWO)

Component Weight (kg) 694Additional Weight (kg) 492Power (kW) 0.65 - 1.44 Volume (m3) 0.289Operating Temperature (K) 647 – 1023Operating Pressure (kPa) 2.21 • 104 - 2.53 • 104

TRL (1-9) 4Reliability Moderate

Gravity Dependence Liquid & solid separation issues

Safety High

Advantages

- Can combine oxidation of trace contaminants in air and air organic contaminants in water in a single unit or reactor.

Disadvantages

-High P and T process

-Subsystem Functional Element weight and power-Solids plugging

Prospective Improvements Moderate - High


InsulatedInsulatedReactorReactor

CatalyticCatalyticDecompositionDecomposition

of Nof N22OO

Aqueous Aqueous WasteWaste

SCWO

OO22

Gas/Gas/LiquidLiquid--Solid Solid

SeparatorSeparator

Inorganic Inorganic SaltsSalts

OO22, N, N22

COCO22, H, H22

HH22OO



of Nof N22OO


SCWO

OO22


SeparatorSeparator


OO22, N, N22

COCO22, H, H22

HH22OO

Page 95


Subsystem Atmosphere ManagementFunction Trace Contaminant ControlTechnology Reactive Bed Plasma (RBP)Component Weight (kg) 1150Additional Weight (kg) 5.85Power (kW) 34.8Volume (m3) 3.9Operating Temperature (K) 1298 - 1877Operating Pressure (kPa) 101.0-101.325TRL (1-9) 4Reliability Unknown


Safety Medium

Advantages

- Intense flame- Requires little O2 with low by-products- Short on/off cycle- Potential for high mobility

Disadvantages- Durability of arc due to high temp.- Skilled operators necessary



REACTIVE BED PLASMA (RBP)

PowerPower

Reactive BedReactive BedPlasmaPlasmaLow T, PLow T, P

??

Cabin Cabin AirAir

Organic/Toxic WastesOrganic/Toxic Wastes

Human WastesHuman Wastes(Urine & Feces)(Urine & Feces)

????

REACTIVE BED PLASMA (RBP)

PowerPower

Reactive BedReactive BedPlasmaPlasmaLow T, PLow T, P

??

Cabin Cabin AirAir

Organic/Toxic WastesOrganic/Toxic Wastes

Human WastesHuman Wastes(Urine & Feces)(Urine & Feces)

????

Page 96



Technology Trace Contaminant Control System (TCCS)

Component Weight (kg) 78.2Additional Weight (kg) 163.0Power (kW) 0.175Volume (m3) 0.5Operating Temperature (K) 673.15Operating Pressure (kPa) 101.325TRL (1-9) 9Reliability High


Safety High


Disadvantages - Charcoal bed change-out- LiOH change-out

Prospective Improvements Medium


TRACE CONTAMINANT CONTROL SYSTEM (TCCS)

PowerPower

TCCSTCCSMed T, Low PMed T, Low P

Cleaned Cabin AirCleaned Cabin Air

HeatHeat

Cabin AirCabin Air Deactivated CharcoalDeactivated CharcoalUsed FiltersUsed FiltersUsed Used LiOHLiOH

TRACE CONTAMINANT CONTROL SYSTEM (TCCS)

PowerPower

TCCSTCCSMed T, Low PMed T, Low P

Cleaned Cabin AirCleaned Cabin Air

HeatHeat

Cabin AirCabin Air Deactivated CharcoalDeactivated CharcoalUsed FiltersUsed FiltersUsed Used LiOHLiOH

Page 97



Technology High-Efficiency Particulate Air (HEPA) Filters

Component Weight (kg) 2.0Additional Weight (kg) 260.0Power (kW) 0.0Volume (m3) 0.01Operating Temperature (K) 291 - 299Operating Pressure (kPa) 101.325TRL (1-9) 9Reliability High


Safety High

Advantages- Simple- Lightweight- Easy to change-out

Disadvantages - Frequency of change-out- Storage of extra filters



HIGH-EFFICIENCY PARTICULATE AIR (HEPA) FILTERS

HEPA FiltersHEPA FiltersLow T, PLow T, P

Cabin AirCabin AirCabin AirCabin Air

HIGH-EFFICIENCY PARTICULATE AIR (HEPA) FILTERS

HEPA FiltersHEPA FiltersLow T, PLow T, P

Cabin AirCabin AirCabin AirCabin Air

Page 98


Temperature & Humidity Control (THC) Specification Sheets


Function Temperature & Humidity Control (THC)

Technology Condensing Heat Exchange (CHX)

Component Weight (kg) 96.4Additional Weight (kg) 0.0Power (kW) 0.01Volume (m3) 0.31Operating Temperature (K) 291 - 300Operating Pressure (kPa) 62 - 104.8TRL (1-9) 9Reliability High


Safety High


Disadvantages- Fairly heavy- Depends on vehicle thermal system



CONDENSING HEAT EXCHANGER (CHX)

PowerPower

CHXCHXLow T, PLow T, P

Cabin AirCabin Air

HeatHeat

Cabin AirCabin Air

HH22OO

CONDENSING HEAT EXCHANGER (CHX)

PowerPower

CHXCHXLow T, PLow T, P

Cabin AirCabin Air

HeatHeat

Cabin AirCabin Air

HH22OO

Page 99


Atmosphere Monitoring & Control (THC) Specification Sheets

Subsystem Atmosphere ManagementFunction Air Constituency Analysis

Technology Gas Chromatograph / Mass Spectrometer

Component Weight (kg) 1.8Additional Weight (kg) UnknownPower (kW) 0.015Volume (m3) 0.003Operating Temperature (K) 394.15Operating Pressure (kPa) 101.325TRL (1-9) 9Reliability High


Safety HighAdvantages - Very lightweightDisadvantages - UnknownProspective Improvements Low


GAS CHROMATOGRAPH / MASS SPECTROMETER (GC/MS)

PowerPower

GC / MSGC / MSLow T, PLow T, P

Cabin AirCabin Air

HeatHeat

Cabin AirCabin Air

GAS CHROMATOGRAPH / MASS SPECTROMETER (GC/MS)

PowerPower

GC / MSGC / MSLow T, PLow T, P

Cabin AirCabin Air

HeatHeat

Cabin AirCabin Air

Page 100


Subsystem Atmosphere ManagementFunction Air Constituency Analysis

Technology Major Constituent Analyzer (MCA)

Component Weight (kg) 54.7Additional Weight (kg) 12Power (kW) 0.103Volume (m3) 0.44Operating Temperature (K) 394.15Operating Pressure (kPa) 101.325TRL (1-9) 9)

Reliability High


Safety HighAdvantages - Unknown

Disadvantages - Bulky- Heavy



MAJOR CONSTITUENT ANALYZER (MCA)

PowerPower

MCAMCALow T, PLow T, P

Cabin AirCabin Air

HeatHeat

Cabin AirCabin Air

MAJOR CONSTITUENT ANALYZER (MCA)

PowerPower

MCAMCALow T, PLow T, P

Cabin AirCabin Air

HeatHeat

Cabin AirCabin Air

Page 101


Trace Contaminant Control Trade Matrix

Selection Criteria

Criteria Wghtng Factor

(0.0-1.0)Certainty (0-100%)

Unwtd Score

(0.0-1.0) Min Nom MaxCertainty (0-100%)

Unwtd Score


Unwtd Score

(0.0-1.0) Min Nom MaxComponent Weight (kg) 1.0 90% 1.0 0.90 1.00 1.10 90% 0.5 0.45 0.50 0.55 90% 0.0 0.00 0.00 0.00Additional Weight (kg) 0.8 25% 0.0 0.00 0.00 0.00 25% 1.0 0.20 0.80 1.40 25% 1.0 0.19 0.77 1.35Power (kW) 0.5 90% 1.0 0.45 0.50 0.55 90% 1.0 0.44 0.49 0.54 90% 0.0 0.00 0.00 0.00Volume (m3) 0.5 90% 0.8 0.38 0.42 0.47 90% 1.0 0.45 0.50 0.55 90% 0.0 0.00 0.00 0.00Heat Generated (kW) 0.5 90% 1.0 0.45 0.50 0.55 90% 1.0 0.44 0.49 0.54 90% 0.0 0.00 0.00 0.00Operating Temperature (K) 0.8 50% 1.0 0.40 0.80 1.20 50% 0.8 0.30 0.60 0.90 50% 0.0 0.00 0.00 0.00Operating Pressure (kPa) 0.8 50% 1.0 0.40 0.80 1.20 50% 0.0 0.00 0.00 0.00 50% 1.0 0.40 0.80 1.20Designed Efficiency (%) 0.2 0% 0.0 0.00 0.00 0.00 0% 1.0 0.00 0.20 0.40 0% 1.0 0.00 0.20 0.40TRL (1-9) 0.8 100% 1.0 0.80 0.80 0.80 100% 0.0 0.00 0.00 0.00 100% 0.0 0.00 0.00 0.00Reliability 0.7 25% 1.0 0.18 0.70 1.23 25% 1.0 0.18 0.70 1.23 25% 1.0 0.18 0.70 1.23Maintainability 0.7 25% 1.0 0.18 0.70 1.23 25% 1.0 0.18 0.70 1.23 25% 1.0 0.18 0.70 1.23Gravity Dependence 0.9 90% 1.0 0.81 0.90 0.99 90% 1.0 0.81 0.90 0.99 90% 1.0 0.81 0.90 0.99Crew Time - Operations 0.2 25% 1.0 0.05 0.20 0.35 25% 1.0 0.05 0.20 0.35 25% 1.0 0.05 0.20 0.35Safety 0.8 50% 1.0 0.40 0.80 1.20 50% 0.0 0.00 0.00 0.00 50% 0.0 0.00 0.00 0.00Lifetime Cost 0.1 0% 1.0 0.00 0.10 0.20 0% 1.0 0.00 0.10 0.20 0% 1.0 0.00 0.10 0.20Prospective Improvements 0.1 0% 0.0 0.00 0.00 0.00 0% 1.0 0.00 0.10 0.20 0% 1.0 0.00 0.10 0.20

Totals 12.8 5.39 8.22 11.06 12.2 3.50 6.29 9.08 9.0 1.80 4.47 7.14

Summary: Min Nom MaxTCCS 5.391 8.224 11.056

SCWO 3.499 6.289 9.078RBP 1.803 4.471 7.140

RBPInput Values Input Values Input Values

TCCS SCWOWeighted ScoresWeighted Scores Weighted Scores



Atmosphere Monitoring Trade Matrix

Selection Criteria


(0.0-1.0)Certainty (0-100%)

Unwtd Score


Unwtd Score

(0.0-1.0) Min Nom MaxComponent Weight (kg) 1.0 90% 1.0 0.90 1.00 1.10 90% 0.0 0.00 0.00 0.00Additional Weight (kg) 0.8 25% 1.0 0.20 0.80 1.40 90% 0.0 0.00 0.00 0.00Power (kW) 0.5 90% 1.0 0.45 0.50 0.55 90% 0.0 0.00 0.00 0.00Volume (m3) 0.5 90% 1.0 0.45 0.50 0.55 90% 0.0 0.00 0.00 0.00Heat Generated (kW) 0.5 90% 1.0 0.45 0.50 0.55 90% 0.0 0.00 0.00 0.00Operating Temperature (K) 0.8 50% 0.0 0.00 0.00 0.00 50% 0.0 0.00 0.00 0.00Operating Pressure (kPa) 0.8 50% 0.0 0.00 0.00 0.00 50% 0.0 0.00 0.00 0.00Designed Efficiency (%) 0.2 0% 1.0 0.00 0.20 0.40 0% 1.0 0.00 0.20 0.40TRL (1-9) 0.8 100% 1.0 0.80 0.80 0.80 100% 1.0 0.80 0.80 0.80Reliability 0.7 25% 1.0 0.18 0.70 1.23 25% 1.0 0.18 0.70 1.23Maintainability 0.7 25% 1.0 0.18 0.70 1.23 25% 1.0 0.18 0.70 1.23Gravity Dependence 0.9 90% 1.0 0.81 0.90 0.99 90% 1.0 0.81 0.90 0.99Crew Time - Operations 0.2 25% 0.0 0.00 0.00 0.00 90% 0.0 0.00 0.00 0.00Safety 0.8 50% 1.0 0.40 0.80 1.20 50% 1.0 0.40 0.80 1.20Lifetime Cost 0.1 0% 0.0 0.00 0.00 0.00 0% 0.0 0.00 0.00 0.00Prospective Improvements 0.1 0% 1.0 0.00 0.10 0.20 0% 1.0 0.00 0.10 0.20

Totals 12.0 4.81 7.50 10.19 7.0 2.36 4.20 6.04

Summary: Min Nom MaxMS/GC (mini) 4.810 7.500 10.190

MS (MCA) 2.360 4.200 6.040

Input Values Input ValuesMS/GC (mini) MS (MCA)

Weighted ScoresWeighted Scores



CO2 Removal Trade Matrix

Selection Criteria


(0.0-1.0)Certainty (0-100%)

Unwtd Score


Unwtd Score


Unwtd Score

(0.0-1.0) Min Nom MaxComponent Weight (kg) 1.0 100% 1.0 1.00 1.00 1.00 100% 1.0 0.98 0.98 0.98 75% 1.0 0.75 1.00 1.25Additional Weight (kg) 1.0 100% 1.0 1.00 1.00 1.00 100% 1.0 1.00 1.00 1.00 50% 1.0 0.50 1.00 1.50Power (kW) 0.7 100% 0.6 0.40 0.40 0.40 100% 0.0 0.00 0.00 0.00 25% 0.8 0.14 0.56 0.97Volume (m3) 0.8 100% 0.9 0.69 0.69 0.69 100% 0.8 0.62 0.62 0.62 75% 1.0 0.60 0.80 1.00Heat Generated (kW) 0.7 100% 0.6 0.40 0.40 0.40 100% 0.0 0.00 0.00 0.00 25% 0.5 0.09 0.37 0.65Operating Temperature (K) 0.4 100% 0.7 0.27 0.27 0.27 100% 0.0 0.00 0.00 0.00 25% 1.0 0.10 0.39 0.69Operating Pressure (kPa) 0.2 100% 0.9 0.18 0.18 0.18 100% 1.0 0.20 0.20 0.20 25% 0.0 0.00 0.00 0.00TRL (1-9) 0.9 100% 1.0 0.90 0.90 0.90 100% 1.0 0.90 0.90 0.90 25% 0.0 0.00 0.00 0.00Reliability 1.0 50% 1.0 0.50 1.00 1.50 50% 1.0 0.50 1.00 1.50 25% 0.0 0.00 0.00 0.00Maintainability 0.1 25% 1.0 0.03 0.10 0.18 25% 1.0 0.03 0.10 0.18 25% 0.5 0.01 0.05 0.09Prospective Improvements 0.6 40% 0.0 0.00 0.00 0.00 40% 0.0 0.00 0.00 0.00 100% 1.0 0.60 0.60 0.60

Totals 8.6 5.36 5.93 6.51 6.8 4.23 4.80 5.38 6.8 2.79 4.77 6.75

APCInput Values Input Values Input Values

2 BMS 4 BMSWeighted ScoresWeighted Scores Weighted Scores

Certainty (0-100%)

Unwtd Score


Unwtd Score


Unwtd Score


Unwtd Score

(0.0-1.0) Min Nom Max100% 1.0 1.00 1.00 1.00 100% 0.0 0.00 0.00 0.00 100% 1.0 1.00 1.00 1.00 50% 1.0 0.50 1.00 1.50100% 1.0 1.00 1.00 1.00 100% 0.0 0.00 0.00 0.00 100% 1.0 1.00 1.00 1.00 75% 1.0 0.75 1.00 1.2575% 0.9 0.49 0.66 0.82 100% 1.0 0.70 0.70 0.70 100% 0.2 0.11 0.11 0.11 75% 1.0 0.53 0.70 0.88

100% 1.0 0.80 0.80 0.80 100% 0.0 0.00 0.00 0.00 100% 0.9 0.72 0.72 0.72 50% 0.9 0.35 0.69 1.04100% 0.5 0.37 0.37 0.37 100% 1.0 0.70 0.70 0.70 50% 0.2 0.05 0.11 0.16 75% 1.0 0.53 0.70 0.88100% 1.0 0.39 0.39 0.39 100% 1.0 0.40 0.40 0.40 100% 1.0 0.38 0.38 0.38 75% 0.9 0.27 0.37 0.4615% 0.0 0.00 0.00 0.00 100% 0.0 0.00 0.00 0.00 100% 0.0 0.00 0.00 0.00 75% 1.0 0.15 0.20 0.25

100% 0.4 0.36 0.36 0.36 100% 1.0 0.90 0.90 0.90 100% 0.4 0.36 0.36 0.36 50% 0.0 0.00 0.00 0.0025% 0.5 0.13 0.50 0.88 100% 1.0 1.00 1.00 1.00 25% 0.5 0.13 0.50 0.88 25% 0.0 0.00 0.00 0.0025% 0.5 0.01 0.05 0.09 100% 0.0 0.00 0.00 0.00 25% 0.5 0.01 0.05 0.09 25% 0.5 0.01 0.05 0.0925% 0.5 0.08 0.30 0.53 100% 0.0 0.00 0.00 0.00 50% 0.5 0.15 0.30 0.45 100% 1.0 0.60 0.60 0.60

7.4 4.63 5.43 6.24 5.0 3.70 3.70 3.70 6.1 3.91 4.52 5.14 8.3 3.68 5.31 6.93

EDCInput Values Weighted Scores

LiOHInput Values Weighted Scores

TSAInput Values Weighted Scores

SAWDInput Values Weighted Scores



CO2 Reduction Trade Matrix

Selection Criteria


(0.0-1.0)Certainty (0-100%)

Unwtd Score


Unwtd Score


Unwtd Score


Totals 5.7 2.50 2.93 3.35 6.6 3.26 3.66 4.06 7.9 4.90 5.30 5.70

Input Values Input Values Input ValuesACFR BOSCH

Weighted ScoresWeighted ScoresSABATIER

Weighted Scores

Certainty (0-100%)

Unwtd Score

(0.0-1.0) Min Nom Max75% 0.6 0.46 0.61 0.7675% 1.0 0.04 0.05 0.0650% 0.0 0.00 0.00 0.0050% 0.8 0.33 0.66 0.9975% 0.0 0.00 0.00 0.00

100% 0.7 0.29 0.29 0.29100% 0.6 0.12 0.12 0.1250% 1.0 0.45 0.90 1.3525% 0.5 0.13 0.50 0.8825% 0.5 0.01 0.05 0.0990% 1.0 0.54 0.60 0.66

6.7 2.35 3.77 5.19

SOEInput Values Weighted Scores


Summary: Min Nom MaxACFR 2.504 2.926 3.349

BOSCH 3.256 3.656 4.056SABATIER 4.904 5.304 5.704

SOE 2.355 3.772 5.190

Page 105


N2 Provision Trade Matrix

Selection Criteria


(0.0-1.0)Certainty (0-100%)

Unwtd Score


Unwtd Score

(0.0-1.0) Min Nom MaxComponent Weight (kg) 1.0 75% 0.0 0.00 0.00 0.00 75% 0.0 0.00 0.00 0.00Additional Weight (kg) 0.0 75% 1.0 0.01 0.01 0.01 75% 0.0 0.00 0.00 0.00Power (kW) 0.7 75% 1.0 0.53 0.70 0.88 75% 1.0 0.53 0.70 0.88Volume (m3) 0.8 75% 1.0 0.60 0.80 1.00 75% 0.0 0.00 0.00 0.00Heat Generated (kW) 0.7 75% 1.0 0.53 0.70 0.88 75% 1.0 0.53 0.70 0.88Operating Temperature (K) 0.4 75% 1.0 0.30 0.40 0.50 75% 1.0 0.30 0.40 0.50Operating Pressure (kPa) 0.2 75% 1.0 0.15 0.20 0.25 75% 0.0 0.00 0.00 0.00TRL (1-9) 0.9 75% 0.0 0.00 0.00 0.00 75% 0.0 0.00 0.00 0.00Reliability 1.0 25% 0.0 0.00 0.00 0.00 25% 0.0 0.00 0.00 0.00Maintainability 0.1 25% 0.0 0.00 0.00 0.00 25% 0.0 0.00 0.00 0.00Prospective Improvements 0.6 25% 0.0 0.00 0.00 0.00 25% 0.0 0.00 0.00 0.00

Totals 6.0 2.11 2.81 3.51 3.0 1.35 1.80 2.25

Summary: Min Nom MaxCRYOGENIC STORAGE 2.108 2.810 3.513

PRESSURIZED STORAGE 1.350 1.800 2.250

Input Values Input ValuesCRYOGENIC STORAGE PRESSURIZED STORAGE

Weighted ScoresWeighted Scores



O2 Provision Trade Matrix

Selection Criteria


(0.0-1.0)Certainty (0-100%)

Unwtd Score


Unwtd Score


Unwtd Score


Totals 6.5 2.30 3.92 5.53 9.1 5.50 6.20 6.89 3.6 1.41 2.25 3.09

Input Values Input Values Input ValuesCRYOGENIC STORAGE SPWE

Weighted ScoresWeighted ScoresPRESSURIZED STORAGE

Weighted Scores

Certainty (0-100%)

Unwtd Score

(0.0-1.0) Min Nom Max75% 1.0 0.73 0.97 1.2175% 1.0 0.75 1.00 1.2550% 0.0 0.00 0.00 0.0050% 1.0 0.40 0.80 1.2075% 0.0 0.00 0.00 0.00

100% 0.0 0.00 0.00 0.00100% 1.0 0.20 0.20 0.2050% 0.5 0.23 0.45 0.6825% 0.5 0.13 0.50 0.8825% 0.7 0.02 0.07 0.1290% 1.0 0.54 0.60 0.66

6.6 2.98 4.58 6.19

SOEInput Values Weighted Scores


Summary: Min Nom MaxCRYOGENIC STORAGE 2.304 3.919 5.533

SPWE 5.499 6.195 6.891PRESSURIZED STORAGE 1.407 2.249 3.092

SOE 2.983 4.585 6.187

Page 107


12.2 Water Management

Subsystem Water ManagementFunction Urine ProcessingTechnology Air Evaporation SystemComponent Weight (kg) 451Additional Weight (kg) 680 days 281

Power (kW) 1.01Volume (m3) 0.31Design Efficiency (%) 1002Heat Generated (kW) 1.0Operating Temperature (K) 280-3332

Operating Pressure (kPa) 103.42

TRL (1-9) 6

Reliability High2Maintainability High2Inflow Stream Urine

Outflow ProcessingHygiene/Potable

Processing

AdvantagesSimple, Maintainable,

Reliable, 100% efficient

DisadvantagesLow outflow quality, high

power


AIR EVAPORATION SYSTEM (AES)AIR EVAPORATION SYSTEM (AES)

AESAES

POWERPOWER

HH220 + solids0 + solids

HEATHEAT

HH2200

AIR EVAPORATION SYSTEM (AES)AIR EVAPORATION SYSTEM (AES)

AESAES

POWERPOWER


HEATHEAT

HH2200

Page 108


Subsystem Water ManagementFunction Potable ProcessingTechnology APCOS -Hamilton StandardComponent Weight (kg) 451Additional Weight (kg) 680 days 101+unk O2 ProvisionPower (kW) 1.071Volume (m3) 0.184Design Efficiency (%) UnknownHeat Generated (kW) 1.07Operating Temperature (K) moderateOperating Pressure (kPa) moderateTRL (1-9) 93Reliability UnknownMaintainability UnknownInflow Stream Urine Distillate, Hygiene WaterOutflow Processing Microbial, Particulate, Gas SepeationAdvantages Very Low Media Consumables

DisadvantagesOxygen Consumption Unknown

Sparse Info Availability


AQUEOUS PHASE CATALYTIC OXIDATION AQUEOUS PHASE CATALYTIC OXIDATION SUBSYSTEM (APCOS)SUBSYSTEM (APCOS)

APCOS

POWER

HEAT

H20 + solids

GasO2

H20 + solids

AQUEOUS PHASE CATALYTIC OXIDATION AQUEOUS PHASE CATALYTIC OXIDATION SUBSYSTEM (APCOS)SUBSYSTEM (APCOS)

APCOSAPCOS

POWER

HEAT

H20 + solids

GasO2

H20 + solids

Page 109


Subsystem Water ManagementFunction Microbial Control

Technology Iodine Microbial Check

ValveComponent Weight (kg) 101

Additional Weight (kg) 680 days 1.51 + 23.0Power (kW) 0.0121

Volume (m3) ??Design Efficiency (%) N/AHeat Generated (kW) 0.012Operating Temperature (K) ??Operating Pressure (kPa) 310 TRL (1-9) 93

Reliability High2

Maintainability High2

Inflow Stream Processed Hygiene WaterOutflow Processing Iodine Removal

AdvantagesSimple, Maintainable, Reliable

Disadvantages Small Consumable Mass


IODINE MICROBIAL CHECK VALVEIODINE MICROBIAL CHECK VALVE

MCVMCVHH220 0

HEATHEAT

HH220 + Iodine0 + Iodine

IODINE MICROBIAL CHECK VALVEIODINE MICROBIAL CHECK VALVE

MCVMCVHH220 0

HEATHEAT

HH220 + Iodine0 + Iodine

Page 110


Subsystem Water ManagementFunction Hygiene Post ProcessingTechnology Mili-Q AbsorbtionComponent Weight (kg) 111

Additional Weight (kg) 680 days 861

Power (kW) 0.231

Volume (m3) 0.061

Design Efficiency (%) 100Heat Generated (kW) 0.06Operating Temperature (K) 293Operating Pressure (kPa) 310 TRL (1-9) 63

Reliability HighMaintainability High

Inflow StreamPre Processed Hygiene

WaterOutflow Processing Hygiene Water


Reliable

DisadvantagesConsumable Mass,

Proprietary


MILLIMILLI--Q ABSORBTION BEDQ ABSORBTION BED

MILLIMILLI--QQ

POWERPOWER

HH220 0

HEATHEAT

HH2200

MILLIMILLI--Q ABSORBTION BEDQ ABSORBTION BED

MILLIMILLI--QQ

POWERPOWER

HH220 0

HEATHEAT

HH2200

Page 111


Subsystem Water ManagementFunction Potable ProcessingTechnology MultifiltrationComponent Weight (kg) 5101

Additional Weight (kg) 680 days 30921

Power (kW) 0.851

Volume (m3) 1.15Design Efficiency (%) 1001

Heat Generated (kW) 0.85Operating Temperature (K) 289 – 3282

Operating Pressure (kPa) 70 – 2102

TRL (1-9) 93

Reliability High2


Inflow StreamUrine Distillate, Hygiene

WaterOutflow Processing Microbial

AdvantagesSimple, Maintainable, Reliable

Disadvantages Mass


MULTIFILTRATIONMULTIFILTRATION

MFMF

POWERPOWER


HEATHEAT

HH2200

MULTIFILTRATIONMULTIFILTRATION

MFMF

POWERPOWER


HEATHEAT

HH2200

REVERSE OSMOSIS AND ULTRAFILTRATIONREVERSE OSMOSIS AND ULTRAFILTRATION

RO/UFRO/UF

POWERPOWER


HEATHEAT

HH2200

Brine HBrine H2200

REVERSE OSMOSIS AND ULTRAFILTRATIONREVERSE OSMOSIS AND ULTRAFILTRATION

RO/UFRO/UF

POWERPOWER


HEATHEAT

HH2200

Brine HBrine H2200

Page 112


Subsystem Water ManagementFunction Potable Processing

TechnologyReverse

Osmosis/UltraFiltrationComponent Weight (kg) 901

Additional Weight (kg) 680 days 33.51

Power (kW) 0.351

Volume (m3) 0.31

Design Efficiency (%) 911

Heat Generated (kW) 0.35Operating Temperature (K) 280 – 3202

Operating Pressure (kPa) 310 – 31002

TRL (1-9) +63

Reliability High2


Inflow StreamUrine Distillate, Hygiene

WaterOutflow Processing For TOC and Microbial


Reliable

Disadvantages Not 100% efficient


VAPOR COMPRESSION DISTILLATION (VCD)VAPOR COMPRESSION DISTILLATION (VCD)

VCDVCD

POWERPOWER

Pretreated Pretreated UrineUrine

HEATHEAT

HH2200

BrineBrine

VAPOR COMPRESSION DISTILLATION (VCD)VAPOR COMPRESSION DISTILLATION (VCD)

VCDVCD

POWERPOWER

Pretreated Pretreated UrineUrine

HEATHEAT

HH2200

BrineBrine

Page 113


Subsystem Water ManagementFunction Urine Distillation

Technology Vapor Compression

DistillationComponent Weight (kg) 1012

Additional Weight (kg) 680 days 46.61

Power (kW) 0.1152

Volume (m3) 0.492

Design Efficiency (%) 952

Heat Generated (kW) 0.115Operating Temperature (K) 3162

Operating Pressure (kPa) LowTRL (1-9) 6+Reliability HighMaintainability MediumInflow Stream Pre-treated UrineOutflow Processing Hygiene/Potable ProcessingAdvantages Low Power ConsumptionDisadvantages Complexity


CONDUCTIVITYCONDUCTIVITY


POWERPOWER

HH22OO HH22OO



POWERPOWER

HH22OO HH22OO

Page 114


Subsystem Water ManagementFunction Water MonitoringTechnology ConductivityTRL (1-9) 8-9Reliability High

Advantagesgive gross, general quality

indication

Disadvantagesdoes not address TOC

level

Prospective Improvements high


ELECTRONIC NOSEELECTRONIC NOSE

ENEN

POWERPOWER

HH22OO HH22OO

ELECTRONIC NOSEELECTRONIC NOSE

ENEN

POWERPOWER

HH22OO HH22OO

Page 115


Subsystem Water ManagementFunction Water MonitoringTechnology Electronic NoseTRL (1-9) 6

Reliability Moderate

Advantages

monitor taste and metals. For odor (TRL 5) This will eliminate the need for the

crews to do the odor or the tasting test of unsanitized

waterDisadvantages NOC (TRL 1)



ION SPECIFIC ELECTRODESION SPECIFIC ELECTRODES

ISEISE

POWERPOWER

HH22OO HH22OO

ION SPECIFIC ELECTRODESION SPECIFIC ELECTRODES

ISEISE

POWERPOWER

HH22OO HH22OO

Page 116


Subsystem Water ManagementFunction Water Monitoring

TechnologyIon Specific Electrodes

(ISE)TRL (1-9) 2-8Reliability High

Advantages

Mulitfuctions. Monitor conductivity (TRL 8), pH (TRL 6), iodine (TRL 2),

TOC/COD (TRL 3), hardness (TRL 4)

Disadvantages

Low TRL for some parameter such as iodine

monitoring



TEST KITSTEST KITS

HH22OO HH22OOTEST KITTEST KITHH22OO HH22OO

TEST KITSTEST KITS

HH22OO HH22OOTEST KITTEST KITHH22OO HH22OO

Page 117


Subsystem Water ManagementFunction Water MonitoringTechnology Test KitsTRL (1-9) 5-9Reliability HighAdvantages Simple, potable, reliable

Disadvantages

Manual, need separate chem-strip for each

particular parameter of interest


TOTAL ORGANIC CARBON (TOC) TOTAL ORGANIC CARBON (TOC) --CONDUCTIVITYCONDUCTIVITY

TOCTOC

POWERPOWER

HH22OO HH22OO

TOTAL ORGANIC CARBON (TOC) TOTAL ORGANIC CARBON (TOC) --CONDUCTIVITYCONDUCTIVITY

TOCTOC

POWERPOWER

HH22OO HH22OO



Subsystem Water Management

Function Water Monitoring

TechnologyTotal Organic Carbon (TOC) - conductivity

TRL (1-9) 6

Reliability High

Advantagesspecialized in monitoring

TOC/COD only

Disadvantages only monitor TOC/COD




Selection Criteria


(0.0-1.0)Certainty (0-100%)

Unwtd Score


Unwtd Score


Unwtd Score


Unwtd Score

(0.0-1.0) Min NomComponent Weight (kg) 0.7 100% 0.7 0.51 0.51 0.51 100% 0.0 0.00 0.00 0.00 100% 0.8 0.56 0.56 0.56 100% 1.0 0.70 0.70Additional Weight (kg) 0.7 25% 1.0 0.17 0.69 1.21 100% 0.0 0.00 0.00 0.00 100% 1.0 0.67 0.67 0.67 100% 1.0 0.70 0.70Power (kW) 0.7 100% 0.0 0.00 0.00 0.00 100% 0.4 0.28 0.28 0.28 100% 0.6 0.41 0.41 0.41 100% 1.0 0.70 0.70Volume (m3) 0.5 25% 0.7 0.08 0.33 0.58 100% 0.0 0.00 0.00 0.00 100% 0.7 0.33 0.33 0.33 100% 1.0 0.50 0.50Heat Generated (kW) 0.5 100% 0.0 0.00 0.00 0.00 100% 0.4 0.18 0.18 0.18 100% 0.6 0.29 0.29 0.29 100% 1.0 0.50 0.50Operating Temperature (K) 0.5 25% 0.0 0.00 0.00 0.00 100% 0.3 0.14 0.14 0.14 100% 0.3 0.14 0.14 0.14 100% 1.0 0.50 0.50Operating Pressure (kPa) 0.5 25% 0.8 0.10 0.41 0.72 100% 0.9 0.44 0.44 0.44 100% 0.0 0.00 0.00 0.00 100% 1.0 0.50 0.50Designed Efficiency (%) 0.5 25% 1.0 0.13 0.50 0.88 100% 1.0 0.50 0.50 0.50 100% 1.0 0.50 0.50 0.50 100% 0.0 0.00 0.00TRL (1-9) 0.7 100% 1.0 0.70 0.70 0.70 100% 1.0 0.70 0.70 0.70 100% 0.8 0.54 0.54 0.54 100% 0.0 0.00 0.00Maintainability 0.7 25% 0.3 0.06 0.23 0.41 75% 1.0 0.53 0.70 0.88 75% 1.0 0.53 0.70 0.88 100% 0.0 0.00 0.00Crew Time - Operations 0.5 50% 0.5 0.13 0.25 0.38 50% 0.0 0.00 0.00 0.00 50% 0.0 0.00 0.00 0.00 100% 1.0 0.50 0.50Safety 0.5 25% 0.5 0.06 0.25 0.44 75% 1.0 0.38 0.50 0.63 75% 0.0 0.00 0.00 0.00 100% 0.5 0.25 0.25

Totals 6.5 1.94 3.88 5.82 5.9 3.14 3.44 3.74 6.7 3.98 4.16 4.33 8.5 4.85 4.85

Summary: Min Nom MaxUF/R.O +apcos 1.944 3.881 5.818

multifiltration 3.144 3.444 3.744UF/R.O.+milliq 3.982 4.157 4.332

0 4.850 4.850 4.850Alternative #5 4.600 4.600 4.600Alternative #6 5.100 5.100 5.100Alternative #7 5.100 5.100 5.100Alternative #8 5.100 5.100 5.100Alternative #9 4.850 4.850 4.850

Alternative #10 5.100 5.100 5.100

Input Values Weighted ScoresUF/R.O.+milliq

Input Values Input Values Input ValuesUF/R.O +apcos multifiltration

Weighted ScoresWeighted Scores Weighted Scores



Selection Criteria


(0.0-1.0)Certainty (0-100%)

Unwtd Score


Unwtd Score


Unwtd Score


Unwtd Score

(0.0-1.0) Min NomComponent Weight (kg) 1.0 100% 0.0 0.00 0.00 0.00 100% 0.6 0.55 0.55 0.55 100% 1.0 1.00 1.00 1.00 100% 1.0 1.00 1.00Additional Weight (kg) 1.0 100% 0.0 0.00 0.00 0.00 100% 0.6 0.58 0.58 0.58 100% 1.0 1.00 1.00 1.00 100% 1.0 1.00 1.00Power (kW) 1.0 100% 0.9 0.89 0.89 0.89 100% 0.0 0.00 0.00 0.00 100% 1.0 1.00 1.00 1.00 100% 1.0 1.00 1.00Volume (m3) 0.5 100% 0.0 0.00 0.00 0.00 100% 0.4 0.19 0.19 0.19 100% 1.0 0.50 0.50 0.50 100% 1.0 0.50 0.50Heat Generated (kW) 0.5 100% 0.9 0.44 0.44 0.44 100% 0.0 0.00 0.00 0.00 100% 1.0 0.50 0.50 0.50 100% 1.0 0.50 0.50Operating Temperature (K) 0.5 100% 0.0 0.02 0.02 0.02 100% 0.0 0.00 0.00 0.00 100% 1.0 0.50 0.50 0.50 100% 1.0 0.50 0.50Operating Pressure (kPa) 0.5 100% 1.0 0.48 0.48 0.48 100% 0.0 0.00 0.00 0.00 100% 1.0 0.50 0.50 0.50 100% 1.0 0.50 0.50Designed Efficiency (%) 1.0 100% 1.0 0.95 0.95 0.95 100% 1.0 1.00 1.00 1.00 100% 0.0 0.00 0.00 0.00 100% 0.0 0.00 0.00TRL (1-9) 1.0 100% 1.0 1.00 1.00 1.00 100% 1.0 1.00 1.00 1.00 100% 0.0 0.00 0.00 0.00 100% 0.0 0.00 0.00Maintainability 0.5 75% 0.3 0.13 0.17 0.21 100% 1.0 0.50 0.50 0.50 100% 0.0 0.00 0.00 0.00 100% 0.0 0.00 0.00Crew Time - Operations 0.5 50% 1.0 0.25 0.50 0.75 50% 0.0 0.00 0.00 0.00 100% 1.0 0.50 0.50 0.50 100% 1.0 0.50 0.50Safety 0.5 75% 0.7 0.25 0.33 0.42 75% 1.0 0.38 0.50 0.63 100% 0.0 0.00 0.00 0.00 100% 0.0 0.00 0.00

Totals 6.7 4.40 4.78 5.15 5.5 4.20 4.32 4.45 8.0 5.50 5.50 5.50 8.0 5.50 5.50

Summary: Min Nom MaxVCD 4.400 4.775 5.150AES 4.199 4.324 4.449

0 5.500 5.500 5.5000 5.500 5.500 5.500

Alternative #5 5.500 5.500 5.500Alternative #6 5.500 5.500 5.500Alternative #7 5.500 5.500 5.500Alternative #8 5.500 5.500 5.500Alternative #9 5.500 5.500 5.500

Input Values Weighted ScoresInput Values Input Values Input ValuesVCD AES

Weighted ScoresWeighted Scores Weighted Scores



12.3 Waste Processing

Subsystem Waste ProcessingFunction Anaerobic breakdown of wasteTechnology Pyrolysis ProcessingComponent Weight (kg) 60 (4)

Additional Weight (kg) 12Power (kW) 0.6 (4)

Volume (m3) 0.002 (4)

Operating Temperature (K)

900 - 1300 (4)

Operating Pressure (kPa) 500 - 2000 (4)

TRL (1-9) 3 (4)

Reliability High

Gravity DependenceMicrogravity and hypergravity concerns about separation of solid, liquid, and gas

streams. (4)

Safety High

Advantages

- Flexibility and adaptability with regard to feedstock (4)

- Simplicity, low mass, and potentially useful products (4)

- Reduction of waste volume (4)

Disadvantages- Microgravity processing sensitivity (4)

- High temperature operation (4)

- Complex processing scheme (4)


ReactorReactorHigh T, PHigh T, P

““PyroPyro--gasgas””HH2 2 HH22OOCOCO2 2 COCOCHCH4 4 NHNH33

““CharChar””(C, N(C, N22, Ash), Ash)

Char ActivationChar Activationoror

DisposalDisposal

Recycle and further Recycle and further breakdownbreakdown

Gas treatmentGas treatmentoror

separationseparation

Mixed wasteMixed waste(no metals)(no metals)

PYROLYSIS

PowerPower HeatHeat





DisposalDisposal





PYROLYSIS





DisposalDisposal





PYROLYSIS





DisposalDisposal









DisposalDisposal





PYROLYSIS

PowerPower HeatHeat

Page 122


Subsystem Waste ProcessingFunction Converts waste to gaseous

productsTechnology GasificationComponent Weight (kg) 50 (4)

Additional Weight (kg) 15*Power (kW) 1 (4)

Volume (m3) 2 (4)

Operating Temperature (K) 400 - 1000 (4)

Operating Pressure (kPa) 101.13 (4)

TRL (1-9) 2 (4)

Reliability High

Gravity Dependence Gas-solid separation issues. (4)

Safety High

Advantages

- Compact, reliable, safe to operate (4)

-Potential for recovery of waste heat and valuable side products (4)

-Minimum NOx and SO2 (4)

-Little size reduction or preprocessing (4)

Disadvantages-Low TRL (4)

-High T (4)

-Complex process (4)



GasifierGasifierHeat Heat

Recovery Recovery and Purifierand Purifier

Energy Energy Recirculation (2)Recirculation (2)

Ash and Ash and SlagSlag

WasteWaste

GASIFICATION

PowerPower

High THigh TSynSyn GasGas

Low TLow TSynSyn GasGas

Energy Energy ConverterConverter


Energy Recirculation (1)Energy Recirculation (1)

EffluentsEffluents

EnergyEnergyOutputOutput


VerostkoVerostko et. al (2002)et. al (2002)

GasifierGasifierHeat Heat

Recovery Recovery and Purifierand Purifier


Ash and Ash and SlagSlag

WasteWaste

GASIFICATION

PowerPower

High THigh TSynSyn GasGas

Low TLow TSynSyn GasGas

Energy Energy ConverterConverter


Energy Recirculation (1)Energy Recirculation (1)

EffluentsEffluents



VerostkoVerostko et. al (2002)et. al (2002)

Page 124


Subsystem Waste ProcessingFunction Waste OxidationTechnology Supercritical Water Oxidation Component Weight (kg) 694 (1)

Additional Weight (kg) 492Power (kW) 0.65 (5)

- 1.44 (1)

Volume (m3) 0.289 (5)

Operating Temperature (K) 647 – 1023 (1)

Operating Pressure (kPa) 2.21 • 104 - 2.53 • 104 (1)

TRL (1-9) 4 (5)

Reliability Moderate

Gravity Dependence Liquid & solid separation issues (5)

Safety High

Advantages

-Processes all waste. (5 )

- High destruction efficiencies at short residence times (< 5 minutes). (1)(2)

-Minimizes consumables and hazardous solids. (3) Low NOx and SOx (2)

-Totally contained process. (2)

-Clean products (5)

Disadvantages

-High P and T process (1)

-Subsystem Functional Element weight and power (3)

-Solids plugging (5)

Prospective Improvements Moderate - High




of Nof N22OO


SCWO

OO22


SeparatorSeparator


OO22, N, N22

COCO22, H, H22

HH22OO



of Nof N22OO


SCWO

OO22


SeparatorSeparator


OO22, N, N22

COCO22, H, H22

HH22OO

Page 125

INCINERATION (BATCH & CONTINUOUS)

Controlled Controlled Continuous Continuous

Thermal Thermal CombustorCombustor

HH2200Mixed wasteMixed waste(no metals)(no metals)

PowerPower

Fly AshFly Ash

Exhaust GasExhaust GasHH22O COO CO2 2 NN22

INCINERATION (BATCH & CONTINUOUS)

Controlled Controlled Continuous Continuous

Thermal Thermal CombustorCombustor

HH2200Mixed wasteMixed waste(no metals)(no metals)

PowerPower

Fly AshFly Ash



Subsystem Waste Processing

Functionsterilization & mass reduction

of waste (no trace metals) (5)

Technology Incineration (Batch & Continuous)

Component Weight (kg) 303Additional Weight (kg) 1296Power (kW) 6.6 (4)

Volume (m3) 4.54 (4)

Operating Temperature (K) 814 (1) - 1400 (4)

Operating Pressure (kPa) ambient 101 (1)

TRL (1-9) 4 (4)

Reliability High

Gravity Dependence

-Fluidized bed not microgravity capable (4)

-Gas-solid separations occur (4)

Safety Medium

Advantages

- Sterile end product (1) - Mass and volume reduction (1)

- Low operating pressure (3) - Minimizes hazardous solids (3)

-Processes all waste (4)

Disadvantages - Incomplete combustion (1)

-High operating temperature



(1))

-Low water quality (2)

-Flue gas contaminants (4)



Function Sterilization & mass reduction of waste (except metals) (4)

Technology Plasma Thermal Arc Destruction (4)

Component Weight (kg) 1150 (4)

Additional Weight (kg) 263.7(4)

Power (kW) 34.8 (4)

Volume (m3) 3.9 (4)

Operating Temperature (K) 1100 - 1700 (4)

Operating Pressure (kPa) ambient (4)

TRL (1-9) 4 (4)

Reliability High

Gravity Dependence Heat transfer affected (4)

Safety

- All surfaces need to be kept at safe temperatures (4)

- Electrical power can be shut off quickly in case of an emergency (4)

Advantages Processes all waste (4)

Disadvantages - High power and temperature (4)

- Scaledown difficult (4)



ReactorReactor

High THigh T


Trace GasesTrace GasesScrubberScrubberMixed wasteMixed waste

(no metals)(no metals)

PLASMA ARC

PowerPower HeatHeat

Air Air Plasma Plasma TorchTorch

ReactorReactor

High THigh T


Trace GasesTrace GasesScrubberScrubberMixed wasteMixed waste

(no metals)(no metals)

PLASMA ARC

PowerPower HeatHeat

Air Air Plasma Plasma TorchTorch

Page 127



Functionsterilization and mass reduction

of waste (processes all wastes) (5)

Technology Electrochemical OxidationComponent Weight (kg) 3310 (4)

Additional Weight (kg) 660 (4)

Power (kW) 20 (4)

Volume (m3) 4.2 (4) - 5.1(4)

Operating Temperature (K) 320 (4) - 422(1)

Operating Pressure (kPa) ambient (4)

TRL (1-9) 4 (4)

Reliability Low

Gravity Dependence -separation of the gases formed at the anode and cathode (5)

SafetyHazardous - includes

caustic and/or acidic liquids and gases including pure oxygen (5)

Advantages

-Low power requirements. (1)

-Does not consume oxygen. (1)

-Low temperature and pressure.(4)

-Low production of oxides. (4)

Disadvantages

-Gaseous emissions include Cl2.(4)

-Requires consistent and very fine particle waste. (4)



ELECTROCHEMICAL OXIDATION

ReactorReactor HH2200All wasteAll waste

PowerPower

AnolyteAnolyte

OffOff--gassinggassing

ELECTROCHEMICAL OXIDATION


PowerPower

AnolyteAnolyte



PowerPower

AnolyteAnolyte


Page 128



Selection Criteria


(0.0-1.0)Certainty (0-100%)

Unwtd Score


Unwtd Score


Unwtd Score


7.5 4.23 4.23 4.23 8.3 5.49 5.91 6.33 13.7 5.87 6.85 7.83

Summary: Min Nom MaxElectrochemical Ox. 4.233 4.233 4.233

SCWO 5.486 5.909 6.331Gasification 5.873 6.853 7.833

Electrochemical Ox.Input Values Weighted Scores

SCWOInput Values Weighted Scores

GasificationInput Values Weighted Scores

Page 129


Selection Criteria


(0.0-1.0)Certainty (0-100%)

Unwtd Score


Unwtd Score


Unwtd Score


Totals 8.2 5.30 5.39 5.48 12.0 6.32 7.30 8.28 9.4 3.28 5.88 8.48

Batch IncinerationInput Values Input Values Input Values

Plasma GasificationWeighted ScoresWeighted Scores Weighted Scores

Certainty (0-100%)

Unwtd Score


Unwtd Score

(0.0-1.0) Min Nom Max100% 0.8 0.77 0.77 0.77 100% 1.0 0.99 0.99 0.9950% 0.0 0.00 0.00 0.00 0% 1.0 0.00 0.80 1.60100% 0.8 0.42 0.42 0.42 100% 0.9 0.43 0.43 0.43100% 0.0 0.00 0.00 0.00 100% 1.0 0.50 0.50 0.50100% 0.0 0.00 0.00 0.00 100% 0.9 0.00 0.00 0.00100% 0.6 0.46 0.46 0.46 100% 0.6 0.46 0.46 0.46100% 0.0 0.00 0.00 0.00 100% 0.0 0.00 0.00 0.00100% 0.5 0.00 0.00 0.00 100% 1.0 0.00 0.00 0.00100% 1.0 1.00 1.00 1.00 100% 0.3 0.33 0.33 0.3380% 1.0 0.64 0.80 0.96 80% 1.0 0.64 0.80 0.9650% 0.5 0.13 0.25 0.38 30% 1.0 0.15 0.50 0.85100% 1.0 0.80 0.80 0.80 100% 1.0 0.80 0.80 0.80100% 0.0 0.00 0.00 0.00 100% 0.0 0.00 0.00 0.0050% 0.7 0.27 0.53 0.80 50% 0.0 0.00 0.00 0.00100% 0.0 0.00 0.00 0.00 100% 1.0 0.00 0.00 0.00100% 0.0 0.00 0.00 0.00 100% 1.0 0.50 0.50 0.50

6.8 4.48 5.03 5.58 11.7 4.80 6.11 7.42

Continuous IncinerationInput Values Weighted Scores

PyrolysisInput Values Weighted Scores


Summary: Min Nom MaxPlasma 5.297 5.387 5.477

Gasification 6.320 7.300 8.280Batch Incineration 3.276 5.880 8.484

Continuous Incineration 4.478 5.030 5.581Pyrolysis 4.797 6.107 7.417

Page 130


References1. Eckart, Peter. 1996. Spaceflight Life Support and Biospherics. Torrance: Microcosm Press2. Davidson, William. 2002.Supercritical Water Oxidation: State of the Art Environmental Technology. General Atomics, Advanced Technologies Group. Available from the World Wide Web: http://www.ga.com/atg/aps/scwo.html3. Ferrall, J.F., G.B. Ganapathi, N.K. Rohatgi and P.K. Seshan. 1994. Life Support Systems Analysis and Technical Trades for a Lunar Outpost. NASA Technical Memorandum 1099274. Verostko, C., J. Joshi, M. Alazraki and J. Fisher. 2002. Solid Waste Processing and Resource Recovery Workshop Report - Vol I. Engineering Directorate, crew and Thermal Systems Division. CTSD-ADV-474. Available also from the World Wide Web: http://advlifesupport.jsc.nasa.gov/PubNew.html 5. Verostko, C., J. Joshi, M. Alazraki and J. Fisher. 2002. Solid Waste Processing and Resource Recovery Workshop Report Appendix - Vol II. Engineering Directorate, crew and Thermal Systems Division. CTSD-ADV-474. Available also from the World Wide Web: http://advlifesupport.jsc.nasa.gov/PubNew.html


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