NASA/CR-2006-213694 

Advanced Life Support Research and Technology 

Development Metric – Fiscal Year 2005

Anthony J. Hanford, Ph.D.

Jacobs Sverdrup 

Houston, Texas 

February 2006 
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NASA/CR-2006-213694 

Advanced Life Support Research and Technology 

Development Metric – Fiscal Year 2005

Anthony J. Hanford, Ph.D.

Jacobs Sverdrup 

Houston, Texas 

National Aeronautics and 

Space Administration 

Johnson Space Center 

Houston, Texas 77058 

February 2006 
Available from: 

NASA Center for AeroSpace Information National Technical Information Service 

7121 Standard Drive 5285 Port Royal Road 

Hanover, MD 21076-1320 Springfield, VA 22161 

This report is also available in electronic form at http://ston.jsc.nasa.gov/collections/TRS 
Contents 

Section Page 

1 INTRODUCTION ...............................................................................................................................................1

1.1 EXECUTIVE SYNOPSIS ...............................................................................................................................1

1.2 BASIC METRIC FORMAT............................................................................................................................1

1.3 DESCRIPTION OF EQUIVALENT SYSTEM MASS ..........................................................................................2

1.4 PREVIOUS ADVANCED LIFE SUPPORT METRIC COMPUTATIONS................................................................2

1.5 NOTES ON THE METRIC FOR FISCAL YEAR 2005.......................................................................................3

1.6 CONTROL AND CONTACT INFORMATION...................................................................................................5

2 BACKGROUND.................................................................................................................................................5

2.1 SUPPORTING DOCUMENTATION ................................................................................................................5

2.2 REFERENCE MISSIONS...............................................................................................................................6

2.2.1 ORBITING RESEARCH FACILITY: INTERNATIONAL SPACE STATION UPGRADE MISSION ...........................6

2.2.2 NEAR-TERM EXPLORATION MISSION: A LUNAR REFERENCE MISSION ...................................................7

2.2.3 INDEPENDENT EXPLORATION MISSION: MARS DUAL LANDER ARCHITECTURE ......................................7

2.3 METRIC ASSUMPTIONS .............................................................................................................................7

2.4 TECHNOLOGY ASSUMPTIONS....................................................................................................................8

2.4.1 ORBITING RESEARCH FACILITY: INTERNATIONAL SPACE STATION UPGRADE MISSION ...........................8

2.4.2 NEAR-TERM EXPLORATION MISSION: CREW EXPLORATION VEHICLE..................................................13

2.4.3 NEAR-TERM EXPLORATION MISSION: LUNAR SURFACE ACCESS MODULE ...........................................17

2.4.4 NEAR-TERM EXPLORATION MISSION: DESTINATION SURFACE SYSTEM................................................22

2.4.5 INDEPENDENT EXPLORATION MISSION: MARS TRANSIT VEHICLE........................................................27

2.4.6 INDEPENDENT EXPLORATION MISSION: MARS DESCENT / ASCENT LANDER ........................................32

2.4.7 INDEPENDENT EXPLORATION MISSION: SURFACE HABITAT LANDER...................................................37

2.4.8 MISSION PARAMETERS.......................................................................................................................42

2.4.9 INFRASTRUCTURE COSTS/EQUIVALENCIES .........................................................................................49

3 ADVANCED LIFE SUPPORT RESEARCH AND TECHNOLOGY DEVELOPMENT METRIC ..............................50

3.1 SUBSYSTEM TECHNOLOGY DATA ...........................................................................................................50

3.2 ADVANCED LIFE SUPPORT RESEARCH AND TECHNOLOGY DEVELOPMENT METRIC ..............................57

3.2.1 METRIC VALUES ...............................................................................................................................57

3.2.2 DISCUSSION......................................................................................................................................57

3.3 METRIC REPORTING RECOMMENDATIONS ..............................................................................................58

3.3.1 METRIC RECOMMENDATION FOR FISCAL YEAR 2005..........................................................................58

3.3.2 COMPARISON WITH PAST ASSESSMENTS .............................................................................................58

4 CAUTIONS AND DISCLAIMERS......................................................................................................................63

5 SPECIAL RECOGNITION OF WORK...............................................................................................................63

6 SUBSYSTEM COMPONENTS IN FISCAL YEAR 2005 ALS R&TD METRIC...................................................64

7 REFERENCES.................................................................................................................................................93

8 ABBREVIATIONS AND ACRONYMS................................................................................................................94

i
Tables 

Table Page 

Table 1.2.1 Technology Readiness Levels...........................................................................................................1

Table 2.4.1 Advanced Mission Parameters........................................................................................................42

Table 2.4.2 Specific Input Values for Metric Mission Parameters in the Advanced Life Support Sizing 

Analysis Tool (ALSSAT) ...............................................................................................................43

Table 2.4.3 Advanced Mission Cost Equivalencies...........................................................................................49

Table 3.1.1 Orbiting Research Facility: International Space Station Upgrade Mission 

using Baseline Technologies...........................................................................................................50

Table 3.1.2 Orbiting Research Facility: International Space Station Upgrade Mission 

using Advanced Technologies ........................................................................................................50

Table 3.1.3 Near-Term Exploration Mission: Crew Exploration Vehicle using Baseline Technologies...........51

Table 3.1.4 Near-Term Exploration Mission: Crew Exploration Vehicle using Advanced Technologies ........51

Table 3.1.5 Near-Term Exploration Mission: Lunar Surface Access Module using Baseline Technologies ....52

Table 3.1.6 Near-Term Exploration Mission: Lunar Surface Access Module 

using Advanced Technologies ........................................................................................................52

Table 3.1.7 Near-Term Exploration Mission: Destination Surface System using Baseline Technologies ........53

Table 3.1.8 Near-Term Exploration Mission: Destination Surface System using Advanced Technologies ......53

Table 3.1.9 Independent Exploration Mission: Mars Transit Vehicle using Baseline Technologies.................54

Table 3.1.10 Independent Exploration Mission: Mars Transit Vehicle using Advanced Technologies ..............54

Table 3.1.11 Independent Exploration Mission: Mars Descent / Ascent Lander 

using Baseline Technologies...........................................................................................................55

Table 3.1.12 Independent Exploration Mission: Mars Descent / Ascent Lander 

using Advanced Technologies ........................................................................................................55

Table 3.1.13 Independent Exploration Mission: Surface Habitat Lander using Baseline Technologies..............56

Table 3.1.14 Independent Exploration Mission: Surface Habitat Lander using Advanced Technologies ...........56

Table 3.2.1 Equivalent System Mass and Metric Values for a Range of Missions and Technologies...............57

Table 3.3.1 Previous Advanced Life Support Research and Technology Development Metric Values ............58

Table 6.1 Subsystem Breakdown for Orbiting Research Facility: 

International Space Station Upgrade Mission using Baseline Technologies ..................................65

Table 6.2 Subsystem Breakdown for Orbiting Research Facility: 

International Space Station Upgrade Mission using Advanced Technologies................................67

Table 6.3 Subsystem Breakdown for Near-Term Exploration Mission: 

Crew Exploration Vehicle using Baseline Technologies ................................................................69

Table 6.4 Subsystem Breakdown for Near-Term Exploration Mission: 

Crew Exploration Vehicle using Advanced Technologies..............................................................71

Table 6.5 Subsystem Breakdown for Near-Term Exploration Mission: 

Lunar Surface Access Module using Baseline Technologies..........................................................73

Table 6.6 Subsystem Breakdown for Near-Term Exploration Mission: 

Lunar Surface Access Module using Advanced Technologies .......................................................75

Table 6.7 Subsystem Breakdown for Near-Term Exploration Mission: 

Destination Surface System using Baseline Technologies..............................................................77

Table 6.8 Subsystem Breakdown for Near-Term Exploration Mission: 

Destination Surface System using Advanced Technologies ...........................................................79

Table 6.9 Subsystem Breakdown for Independent Exploration Mission: 

Mars Transit Vehicle using Baseline Technologies ........................................................................81

Table 6.10 Subsystem Breakdown for Independent Exploration Mission: 

Mars Transit Vehicle using Advanced Technologies......................................................................83

Table 6.11 Subsystem Breakdown for Independent Exploration Mission: 

Mars Descent / Ascent Lander using Baseline Technologies..........................................................85

Table 6.12 Subsystem Breakdown for Independent Exploration Mission: 

Mars Descent / Ascent Lander using Advanced Technologies .......................................................87

Table 6.13 Subsystem Breakdown for Independent Exploration Mission: 

Surface Habitat Lander using Baseline Technologies.....................................................................89

Table 6.14 Subsystem Breakdown for Independent Exploration Mission: 

Surface Habitat Lander using Advanced Technologies ..................................................................91

ii
Figures 

Figure Page 

Figure 2.4.1 International Space Station Upgrade Mission using Baseline Technologies. .................................11

Figure 2.4.2 International Space Station Upgrade Mission using Advanced Technologies................................12

Figure 2.4.3 Crew Exploration Vehicle using Baseline Technologies. ...............................................................15

Figure 2.4.4 Crew Exploration Vehicle using Advanced Technologies..............................................................16

Figure 2.4.5 Lunar Surface Access Module using Baseline Technologies..........................................................20

Figure 2.4.6 Lunar Surface Access Module using Advanced Technologies. ......................................................21

Figure 2.4.7 Destination Surface System using Baseline Technologies..............................................................25

Figure 2.4.8 Destination Surface System using Advanced Technologies. ..........................................................26

Figure 2.4.9 Mars Transit Vehicle using Baseline Technologies. .......................................................................30

Figure 2.4.10 Mars Transit Vehicle using Advanced Technologies......................................................................31

Figure 2.4.11 Mars Descent / Ascent Lander using Baseline Technologies..........................................................35

Figure 2.4.12 Mars Descent / Ascent Lander using Advanced Technologies. ......................................................36

Figure 2.4.13 Surface Habitat Lander using Baseline Technologies.....................................................................40

Figure 2.4.14 Surface Habitat Lander using Advanced Technologies. .................................................................41

Figure 3.3.1 Equivalent system mass summary for the Fiscal Year 2005 ALS Research and Technology 

Development Metric missions and technology suites. ....................................................................59

Figure 3.3.2 Equivalent system mass summary for the components of the Near-Term Exploration Mission.....60

Figure 3.3.3 Equivalent system mass summary for the components of the 

Independent Exploration Mission. ..................................................................................................61

Figure 3.3.4 Historical progression of Advanced Life Support Research and Technology Development 

Metric values as a function of fiscal year........................................................................................62

iii
iv
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 February 2006 

1 

1 INTRODUCTION

This document provides the official calculation of the Advanced Life Support (ALS) Research and 

Technology Development Metric (the Metric) for Fiscal Year 2005. As such, the values herein are primarily based 

on Systems Integration, Modeling, and Analysis (SIMA) Element approved software tools or reviewed and 

approved reference documents. 

1.1 EXECUTIVE SYNOPSIS

For Fiscal Year 2005, the Advanced Life Support Research and Technology Development Metric value is 

2.12 for an Orbiting Research Facility, 1.30 for a Near-Term Exploration Mission, and 1.76 for an Independent 

Exploration Mission. 

1.2 BASIC METRIC FORMAT

The Metric is one of several measures employed by the National Aeronautics and Space Administration 

(NASA) to assess the Agency’s progress as mandated by the United States Congress and the Office of Management 

and Budget. Because any measure must have a reference point, whether explicitly defined or implied, the Metric is 

a comparison between a selected life support system using the “best” available technologies, including those under 

development within the ALS Project, and an equivalently detailed baseline life support system using technology and 

approaches from current programs such as the Space Transportation System (STS) or the Environmental Control and 

Life Support System (ECLSS) from the International Space Station (ISS). More specifically, the Metric is the ratio 

defined by the equivalent system mass (ESM) of a life support system for a specific mission using current 

technologies, signified by the baseline technologies, divided by the ESM for an equivalent life support system using 

the “best” technologies, often called the advanced technologies here. 

As defined, the Metric should increase in value as the advanced technologies become lighter, less power 

intensive, and require less volume. Here “best” is defined as the advanced configuration that, at the time of the 

Metric evaluation, provides the Metric with the highest value. This process theoretically encourages the ALS 

Project to research more than a single technology for each life support function and then select the most appropriate 

for a particular mission, which is similar to an actual process used by mission planners. Only technologies of a 

certain maturity level, generally of technology readiness level of 5 or higher, are selected for inclusion in the Metric 

to avoid assuming too much with too little data. Some promising advanced technologies at a lower technology 

readiness level might appear here, but those selections should be uncommon. See Table 1.2.1 for a summary of the 

technology readiness levels used by NASA (Henninger, et al., 2002). This implies that the Metric will improve as 

promising technologies mature within the ALS Project and become eligible for inclusion in this calculation. 

Conversely, early assumptions for some technologies may be overly optimistic, so the Metric value using those 

technologies may decrease in the future as additional research uncovers higher than expected costs and outdated 

assumptions are revised. 

Table 1.2.1 Technology Readiness Levels 

Technology 

Readiness 

Level Description 

1 Basic principles observed and reported. 

2 Technology Concept and/or application formulated. 

3 Analytical and experimental critical function and/or characteristic proof-of-concept. 

4 Component and/or breadboard validation in laboratory environment. 

5 Component and/or breadboard validation in relevant environment. 

6 System/subsystem model or prototype demonstration in relevant environment (ground or space). 

7 System prototype demonstration in a space environment. 

8 Actual system completed and “flight qualified” through test and demonstration. 

9 Actual system “flight proven” through successful mission operations. 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 February 2006 

2 

1.3 DESCRIPTION OF EQUIVALENT SYSTEM MASS

Equivalent system mass (ESM) is the sum of the masses of life support equipment and supplied 

commodities, plus the mass penalties for infrastructure support, notably power, volume, and cooling, corrected for 

the crewtime required to operate and maintain the life support system. See Levri, et al., 2003. 

ESM reduces the physical quantities describing a system or subsystem to use a single physical parameter: 

mass. This allows comparison of two systems with different physical parameters using a single scalar, and avoids 

the necessity of arbitrary weightings that reflect the prejudices of the analyst to compare, for example, a lighter 

subsystem to one using less power. 

Conversion factors, or equivalencies, are determined for the environment and infrastructure technologies 

that are likely to be used for a mission. For systems requiring power, for example, examination of the power system 

can yield an appropriate power-mass penalty by dividing the average power-plant output for user loads by the total 

mass of the generating power system. Thus, for a nuclear power system on an independent lander that, on average, 

delivers 100 kW of electrical user power and has an overall mass of 8,708 kg, the power-mass penalty is 87 kg/kWe

(0.0115 kWe/kg) (Hanford, 2004a). This power-mass penalty effectively assigns a fraction of the power system 

mass to a power-using subsystem in place of that subsystem’s power requirement. In like manner, mass penalties to 

account for heat rejection, called cooling here, and volume within a pressurized shell are defined. 

1.4 PREVIOUS ADVANCED LIFE SUPPORT METRIC COMPUTATIONS

Previously released Metric computations, in reverse chronological order, may be found in the documents 

listed below. 1

Hanford, A. J. (2004) “Advanced Life Support Research and Technology Development Metric – 

Fiscal Year 2004,” NASA/CR-2004-208944, National Aeronautics and Space Administration, 

Lyndon B. Johnson Space Center, Houston, Texas, October 2004. 

Hanford, A. J. (2004) “Subsystem Details for the Fiscal Year 2004 Advanced Life Support 

Research and Technology Development Metric,” MSAD-04-0306A, Lockheed Martin Space 

Operations, Houston, Texas, September 2004. 

Hanford, A. J. (2003) “Advanced Life Support Research and Technology Development Metric –

 Fiscal Year 2003,” NASA/CR-2004-208939 (JSC 60455, CTSD-ADV-524), National 

Aeronautics and Space Administration, Lyndon B. Johnson Space Center, Houston, Texas, 

30 September 2003. 

Hanford, A. J. (2003) “Advanced Life Support Research and Technology Development Metric –

 Fiscal Year 2002,” JSC 60313 (CTSD-ADV-510), Revision A, National Aeronautics and Space 

Administration, Lyndon B. Johnson Space Center, Houston, Texas, 24 July 2003. 

Hanford, A. J. (2003) “Advanced Life Support Research and Technology Development Metric –

 Fiscal Year 2002,” JSC 60313 (CTSD-ADV-510), National Aeronautics and Space 

Administration, Lyndon B. Johnson Space Center, Houston, Texas, 15 January 2003. 

Drysdale, A. E., and Hanford, A. J. (2002) “Advanced Life Support Research and Technology 

Development Metric – Fiscal Year 2001,” JSC 47787 (CTSD-ADV-482), National Aeronautics 

and Space Administration, Lyndon B. Johnson Space Center, Houston, Texas, 17 January 2002. 

Drysdale, A. E. (2001) “Update to the Advanced Life Support Research and Technology 

Development Metric,” National Aeronautics and Space Administration, Lyndon B. Johnson Space 

Center, Houston, Texas, 19 February 2001. 

Drysdale, A. E., and Hanford, A. J. (1999) “Advanced Life Support Research and Technology 

Development Metric – Baseline” JSC 39503 (CTSD-ADV-384), National Aeronautics and Space 

Administration, Lyndon B. Johnson Space Center, Houston, Texas, 19 November 1999. 

Hanford, A. J., and Drysdale, A. E. (1999) “Advanced Life Support Technology Research and 

Development Metric – Initial Draft,” LMSMSS 33045, Lockheed Martin Space Mission Systems 

and Services, Houston, Texas, 13 January 1999. 

 

1 For electronic copies of recent documents, please see http://advlifesupport.jsc.nasa.gov/.
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 February 2006 

3 

1.5 NOTES ON THE METRIC FOR FISCAL YEAR 2005 

The ALS Project continues to evolve and change both in structure and focus, and these changes affect the 

Metric, some more strongly than others. For the current calculation, the differences in approach and organization 

from Fiscal Year 2004, Hanford (2004c), are minimal. Most importantly, the current calculation uses a revised 

version of a generalized life support spreadsheet tool, the Advanced Life Support Sizing Analysis Tool (ALSSAT) 

(Yeh, et al., 2002, Yeh, et al., 2003, Yeh, et al., 2004a, Yeh, et al., 2005a, and Yeh, et al., 2005b). ALSSAT 

provided values to the current Metric calculation for all subsystems and applicable external interfaces. 

Previous Metric calculations (See, for example, Drysdale and Hanford, 2002) and SIMA’s official 

definition (See, Levri, et al., 2003) include crewtime as part of equivalent mass assessments. This year, ALSSAT 

includes crewtime in assessments, when data is available. However, crewtime for some systems remains 

unavailable. 

ALSSAT underwent a number of changes internally that impact the Metric, as detailed in Yeh, et al.

(2005a) and Yeh, et al. (2005b). These updates affect many technologies within ALSSAT in some manner, but 

numerical impacts of those changes on the Metric are not individually apparent at this time. Of note, efforts over the 

past year, as detailed in Yeh, et al. (2005a) and Yeh, et al. (2005b), include: 

1. The gas mass balances for the salad machine and crew metabolic loads are now explicitly 

computed instead of represented with averaged values. 

2. The water mass balance for the biomass within the salad machine is now explicitly computed 

instead of represented with averaged values. 

3. Five additional water management options were added. The new options include an International 

Space Station Water Recovery System without Vapor Compression Distillation with urine treated 

by a waste system processor, an International Space Station Water Recovery System without 

Vapor Compression Distillation with urine dumping, a Biological Water Recovery Subsystem 

without the Air Evaporation Subsystem so brine is treated by a waste system processor, a Vapor 

Phase Catalytic Ammonia Removal subsystem without the Air Evaporation Subsystem so brine is 

treated by a waste system processor, and a Vapor Phase Catalytic Ammonia Removal subsystem 

with Lyophilization for brine dewatering in place of an Air Evaporation Subsystem. 

4. Wipes were added to the Human Accommodations External Interface. Specifically, when water is 

not allocated for body or hand/face cleansing, wipes are automatically assumed by ALSSAT. 

Moisture from the wipes may be reclaimed within the waste system if a moisture recovery 

technology is available. To recover moisture from wipes is optional. 

5. Cryogenic oxygen storage algorithms were revised based on data from International Space Station 

hardware. Lacking corresponding information for cryogenic nitrogen storage, relationships based 

on researching cryogenic oxygen storage were substituted. 

6. The power estimate for the ullage gas save pump associated with Solid Vacuum Desorption was 

revised. 

7. Sizing routines for lithium hydroxide usage during long-duration missions were revised to correct 

an error. (This error did not impact the Fiscal Year 2004 Metric calculation.) 

8. An initial model of the Functionalized Carbon Molecular Sieve was integrated into ALSSAT. 

Some data entries for this technology were missing from the available reference materials, so 

some quantities were estimated until more accurate information is discovered. 

9. A more accurate carbon dioxide reduction subsystem based on the Sabatier was researched and 

implemented. 

10. An Advanced Trace Contaminant Control Subsystem was researched and integrated into 

ALSSAT. This technology was not considered in the current calculation. 2

 

2 Because work on ALSSAT is ongoing, some options scheduled for Fiscal Year 2005 were not completed at the time 

ALSSAT was made available to compute the Fiscal Year 2005 Metric. Thus, exclusion of this option and others similarly 

designated was not an oversight. 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 February 2006 

4 

11. The waste stream from the food system was divided into non-biodegradable and biodegradable 

fractions to support waste system computations. 

12. The bulk-packaged menu option within the food system was revised. As part of the new bulkpackaged food system, a bulk drink option with a dispenser and a bread machine were added. 

Bulk-packaged food was not considered in the current calculation. 

13. The individual waste system technologies, Warm-Air Drying, Lyophilization, and Storage, were 

revised. 

14. A second combination of waste system technologies, including lyophilization, waste compaction 

with a Plastic Melt Waste Compactor, and storage, was added. 

15. A third combination of waste system technologies, including Sequential Batch Anaerobic 

Composting, Warm-Air Drying, and Storage, was added. This combination of technologies was 

not considered in the current calculation. 

While ALSSAT continues to evolve and improve, it is believed that the current computations are 

sufficiently accurate to provide credible Metric values for Fiscal Year 2005. 

To be consistent with last year and to reflect advances in thermal rejection technologies, the current Metric 

calculations apply different cooling-mass penalties to the different life support system configuration assessments for 

Independent Exploration Mission vehicles. Cooling-mass penalties, assuming aluminum, flow-through radiators, 

apply this year to life support system assessments using hardware from the baseline technology suite. Cooling-mass 

penalties for life support system assessments based on the advanced technology suite assume advanced hardware 

using composite heat-rejection technologies. This is consistent with two previous calculations (Hanford, 2003b and 

Hanford, 2004c). This current Metric calculation, then, showcases advantages associated with advanced thermal 

rejection technologies developed with ALS Project funding, providing appropriate reduced cooling-mass penalties 

for advanced configurations. 

Finally, the Metric workshop near the end of Fiscal Year 2003 brought together analysts and management 

at all levels of NASA to consider the future of the Metric. Several recommendations from the discussions in that 

forum are included, to varying degrees, in this year’s calculation. The status of the most significant are listed here. 

1. Changes to the Metric will be listed or referenced in this document. Specifically, changes to the 

approach, methodology, or life support architecture are listed in this document, while changes to 

the calculation tool, ALSSAT, are recorded in software specific documentation. See Yeh, et al., 

(2004a). However, while subjective, factors of “great influence” to the Metric related to ALSSAT 

are listed here. Compared to the computation from Fiscal Year 2004 (Hanford, 2004c), there are 

no new changes in the methodology for the Metric. 

2. The Metric computation added a new Near-Term Exploration Mission whose target is Luna based 

upon Hanford (2005). 

3. Dry food mass is excluded from the life support system for both current and advanced 

architectures. 

4. Infrastructure equivalencies may vary over time. The infrastructure values used for this 

calculation appear in Hanford (2004a) or Hanford (2005). The infrastructure values for volume, 

power, and cooling are unchanged from the Fiscal Year 2004 Metric calculation (Hanford, 2004c) 

for the Orbiting Research Laboratory and the Independent Exploration Mission. 

5. ALSSAT does not include stowage factors 3 for all technologies, and this is a deviation from 

Levri, et al. (2003). But, ALSSAT provides all technologies on a common basis. To date, 

secondary structures, or stowage factors, exist for a few technologies, but research in this area is 

ongoing. 

6. Data for all technologies selected in this year’s assessments are thought to correspond to a 

technology readiness level (TRL) of 5 or greater. 

 

3 Stowage factors account for necessary secondary structure to mount hardware inside the vehicle. This secondary structure 

differs from the primary vehicle structure, or hull, which is represented by the volume-mass penalty. See Hanford (2004a) 

for details. 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 February 2006 

5 

7. ALSSAT now tracks crewtime for individual technologies. These values are included in the 

assessments below and are included in the overall equivalent system mass values. Crewtime data 

for all ALSSAT technologies may be incomplete at this time. 

8. ALSSAT now computes the crew metabolic waste stream as feces, urine, respiration, and 

perspiration based on metabolic intake, compared with using average values. 

9. ALSSAT tracks thermal loads separately from power consumption, thus removing the simplifying 

assumption that thermal load is equivalent to power consumption. Thermal data for all ALSSAT 

technologies may be incomplete at this time. When unknown, the thermal load is still assumed 

equal to the power consumption. 

1.6 CONTROL AND CONTACT INFORMATION

The ALS Project controls the Metric, and SIMA provides the Metric calculation. Subsequent releases will 

be made as required. Please forward comments to: 

Mr. Michael K. Ewert 

Manager, Systems Integration, Modeling, and Analysis Element 

Advanced Life Support Project 

National Aeronautics and Space Administration 

Lyndon B. Johnson Space Center 

Mail Code EC2 

2101 NASA Parkway 

Houston, Texas 77058 

E-mail: michael.k.ewert@nasa.gov 

2 BACKGROUND

2.1 SUPPORTING DOCUMENTATION

The listed SIMA reference documents provided inputs for the Fiscal Year 2005 Advanced Life Support 

Research and Technology Development Metric calculation. 4

Hanford, A. J., Editor (2004) “Advanced Life Support Baseline Values and Assumptions 

Document,” NASA/CR-2004-208941, National Aeronautics and Space Administration, Lyndon B. 

Johnson Space Center, Houston, Texas. 

Hanford, A. J. (2005) “A Lunar Reference Mission for Advanced Life Support,” ESCG-4007-05-

TEAN-DO-0082, Engineering and Science Contract Group, Jacobs Sverdrup, Houston, Texas, 

08 July 2005. 

Levri, J. A., Drysdale, A. E., Ewert, M. K., Fisher, J. W., Hanford, A. J., Hogan, J. A., 

Jones, H. W., Joshi, J. A., and Vaccari, D. A. (2003) “Advanced Life Support Equivalent System 

Mass Guidelines Document,” NASA/TM-2003-212278, National Aeronautics and Space 

Administration, Ames Research Center, Moffett Field, California. 

Stafford, K. W., Jerng, L. T., Drysdale, A. E., Maxwell, S., Levri, J. A., Ewert, M. K., and 

Hanford, A. J. (2001) “Advanced Life Support Systems Integration, Modeling, and Analysis 

Reference Missions Document,” JSC 39502, Revision A, National Aeronautics and Space 

Administration, Lyndon B. Johnson Space Center, Houston, Texas. 

Yeh, J., Brown, C., and Jeng, F. (2002) “Advanced Life Support Sizing Analysis Tool (ALSSAT) 

v.2.0 User’s Guide,” LMSEAT 34082, Lockheed Martin Space Operations, Houston, Texas. 

Yeh, J., Brown, C., and Jeng, F. (2003) “Advanced Life Support Sizing Analysis Tool (ALSSAT) 

v.3.0,” MSAD-03-0279, Lockheed Martin Space Operations, Houston, Texas. 

 

4 For electronic copies of the NASA reference documents, please see http://advlifesupport.jsc.nasa.gov/.
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 February 2006 

6 

Yeh, J., Brown, C., and Jeng, F. (2004) “FY04 ALSSAT Upgrade,” MSAD-04-0261, Lockheed 

Martin Space Operations, Houston, Texas. 

Yeh, J., Brown, C., and Jeng, F. (2004) “Reference Manual for the Advanced Life Support Sizing 

Analysis Tool (ALSSAT),” MSAD-04-0303, Lockheed Martin Space Operations, Houston, Texas. 

Yeh, J., Brown, C., and Jeng, F. (2004) “Water Recovery Subsystem (WRS) Options Trade 

Studies Using ALSSAT,” MSAD-04-0353, Lockheed Martin Space Operations, Houston, Texas. 

Yeh, J., Brown, C., and Jeng, F. (2005) “FY05 ALSSAT Upgrade,” MSAD-05-0098, Lockheed 

Martin Space Operations, Houston, Texas. 

Yeh, J., Brown, C., and Jeng, F. (2005) “Advanced Life Support Sizing Analysis Tool (ALSSAT) 

Upgrade for FY05,” ESCG-4470-05-TEAN-DOC-0141, Engineering and Science Contract Group, 

Jacobs Sverdrup, Houston, Texas. 

These reference documents provide the primary resources for the values contained below, and, unless noted 

otherwise, all values are listed in or derived from these documents. 

2.2 REFERENCE MISSIONS

The following missions are addressed for Fiscal Year 2005: 

• Orbiting Research Laboratory: International Space Station Upgrade Mission (Stafford, 

et al., 2001), 

• Near-Term Exploration Mission: Lunar Reference Mission (Hanford, 2005), and 

• Independent Exploration Mission: Mars Dual Lander Architecture (Stafford, et al., 2001). 

These missions are described briefly below. For additional details, please see the cited reference. 

The data given applies to nominal operations. Contingency planning, though extremely important, is not 

sufficiently well advanced at this time for these missions, so contingencies are excluded from these calculations. 

2.2.1 ORBITING RESEARCH FACILITY: INTERNATIONAL SPACE STATION UPGRADE MISSION

The International Space Station (ISS) mission is a ten-year, six-crewmember 5 mission in low-Earth orbit. 

For this assessment, the specifics of Earth-to-orbit transfers are not considered, nor are ISS construction operations. 

Rather, this assessment considers just the ESM for nominal, on-orbit operation of the life support system in the 

United States On-Orbit Segment (USOS) following Phase 3. 6 Extravehicular activities are assumed to be a small 

mission component during the day-to-day operation of the ISS after buildup is complete and are, therefore, omitted 

in the assessments here. 7

The ISS Upgrade Mission follows the initial utilization phase for the complete vehicle and assumes that to 

use ISS for an additional ten-year mission the entire USOS life support system must be replaced with new 

equipment of the same or comparable technologies. This mission scenario, as addressed in the assessments below, 

assumes the cooling hardware will have identical properties to current ISS cooling hardware regardless of the life 

support system technologies used. The rationale for extending ISS beyond its initial design life is not addressed here 

 

5 A crew of six is defined here not as a policy statement or a forward projection for NASA, but rather to make the ISS 

scenario comparable to the Independent Exploration Missions that also proposes six crewmembers. 

6 Phase 3 is also known as “assembly complete.” 

7 While extravehicular activities, and the commodities they may use from the life support system, are a concern, the scenario 

for extravehicular activities beyond assembly complete depends heavily on many factors beyond the scope of this current 

assessment, so rather than add questionable assumptions, “extravehicular activities are assumed to have a small but 

consistent impact on all life support system architectures, and may, therefore, be omitted.” 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 February 2006 

7 

but, rather, significant justification is implicitly assumed. Alternately, this mission might apply to a new space 

station of comparable size and capability that follows ISS in the timeframe indicated. 8

The baseline equipment suite assumes an appropriate life support system for the USOS Phase 3 segment 

using baseline technologies alone. This system includes newly fabricated equipment and it replaces the original 

equipment just prior to the beginning of the utilization phase of the ISS Upgrade Mission. The corresponding 

upgraded USOS life support system using advanced technologies provides the same capabilities as the baseline 

USOS Phase 3 life support system but it employs the most economical, in terms of equivalent system mass, life 

support technologies regardless of origin. 

2.2.2 NEAR-TERM EXPLORATION MISSION: A LUNAR REFERENCE MISSION

This exploration mission consists of a single trip to one site on Luna. The analysis here assumes a standard 

mission profile with an overall duration of no more than 118 days (Hanford, 2005). 

A Crew Exploration Vehicle carries the crew during both Earth-Luna transit segments, remaining dormant 

in low-Lunar orbit while the crew descends to Luna for the surface phase. The crew will transfer to a second 

vehicle, the Lunar Surface Access Module, to transfer from low-Lunar orbit to the surface and, ultimately, back to 

low-Lunar orbit at the conclusion of the surface mission. Finally, a third vehicle, the Destination Surface System, 

will fly to Luna and land robotically on the surface. This last vehicle provides a long-duration habitat during the 

surface segment. An equatorial site is assumed for this assessment. During the surface segment, extravehicular 

activities will be frequent, if not daily, events. Here the extravehicular activities are assumed to occupy two 

crewmembers for up to 8 hours per sortie, with 56 sorties scheduled during surface operations. Each vehicle is 

assessed for either weightless or partial gravity, according to the primary operational environment with the crew. 

Thus, the Crew Exploration Vehicle is studied while weightless, and the Lunar Surface Access Module and 

Destination Surface System are assessed assuming partial gravity. 

2.2.3 INDEPENDENT EXPLORATION MISSION: MARS DUAL LANDER ARCHITECTURE

This Mars exploration mission consists of a single trip to one site on Mars. The analysis assumes a 

standard mission profile with outbound and return transit segments of 180 days and a surface phase of 600 days 

(Stafford, et al., 2001). Actual missions will vary in duration according to the year or transportation opportunity, 

propulsion capabilities, and mission development decisions. 

A Mars Transit Vehicle carries the crew during both interplanetary segments, remaining dormant in 

Martian orbit while the crew descends to Mars for the surface phase. A second vehicle, the Mars Descent / Ascent 

Lander, will fly to Mars orbit robotically. The crew will transfer to, and land in, this second vehicle. A third 

vehicle, the Surface Habitat Lander, will fly to Mars and land robotically on the surface. This last vehicle will house 

the crew during the surface segment. During the surface segment, extravehicular activities will be frequent, if not 

daily, events. Here the extravehicular activities are assumed to occupy two crewmembers for up to 4 hours per 

sortie, with 700 sorties scheduled during surface operations from the Surface Habitat Lander. After completion of 

the surface phase, the crew will ascend to Martian orbit in the Mars Descent / Ascent Lander and rendezvous with 

the waiting Mars Transit Vehicle. Each vehicle is assessed for either weightless or partial gravity, according to the 

primary operational environment with a crew. Thus, the Mars Transit Vehicle is studied while weightless, and the 

Surface Habitat Lander and the Mars Descent / Ascent Lander are assessed assuming partial gravity. 

2.3 METRIC ASSUMPTIONS

Except as may be noted here, all assumptions for the Metric are derived from the reference documentation 

above. The infrastructure, mission parameters, computational algorithms, and most of the overall assumptions are 

identical to the Fiscal Year 2004 Metric values (Hanford, 2004c), where applicable. Any changes in assumptions 

most often arise directly or indirectly from changes and improvements in ALSSAT. See, in particular, Yeh, et al.

(2005a) for a summary of changes to ALSSAT for Fiscal Year 2005. 

 

8 While the ALS Project supports current NASA missions as requested, most ALS technologies under development will 

provide technological solutions for missions that are not yet defined because the technology-development cycle duration 

can be considerably longer than the mission-planning cycle duration. Thus, SIMA analyzes missions deemed probable 

even if the specific rationale for a mission is not currently apparent. 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 February 2006 

8 

The vehicles here assume a cabin volume, for purposes of computing cabin atmospheric parameters, based 

on the estimated structure for each vehicle. Based on Hanford (2004a), all cabin volumes assure at least the minimal 

free volume for the crew. See Table 2.4.1. 

To minimize the effect of infrastructure assumptions on the Metric value, similar infrastructures are 

assumed for each technology option. The International Space Station Upgrade Mission employs infrastructure 

values characteristic of International Space Station throughout, while the exploration missions assume both current 

and advanced technologies with some inflatable modules. With respect to these latter vehicles, the structure 

penalties merely account for a pressurized volume and include no additional mass for environmental radiation 

protection, implying instead that life support equipment is naturally resistant to radiation hazards and crew 

interaction with life support equipment is minimal. The volume penalties for the vehicles within the exploration 

missions do provide pressurized volume. See Table 2.4.3. Where applicable, specifically for the Orbiting Research 

Facility and the Independent Exploration Mission, these infrastructure values are identical to values assumed for the 

Fiscal Year 2004 Metric (Hanford, 2004c). The Near-Term Exploration Mission was evaluated during this 

assessment for the first time. 

Support to extravehicular activities from the life support system, plus associated airlock operation costs, are 

included. Extravehicular mobility units and other extravehicular activity equipment are not included here. As noted 

above, commodity losses for extravehicular activities are carried by the subsystem primarily concerned with that 

commodity and are not specifically identified as extravehicular activity support costs. Any costs associated with 

extravehicular activity support reflect equipment unique to that function. 

Some life support system designs naturally recover more water than the crew uses to support their basic 

metabolic and hygiene requirements. Thus, such a surplus might be a resource for other vehicle systems just as fuel 

cell water is a resource from Shuttle to International Space Station. Any surplus water, however, has not been 

included in the official Fiscal Year 2005 calculations as an additional credit except as it may offset water usage 

elsewhere within the life support system. 

Power and cooling infrastructure costs are estimated here using nominal power and cooling loads. This 

approach implies that peak loads have little impact on the power and cooling systems, or that these loads can be 

successfully averaged when considering the entire vehicle. 

Finally, the computation for Fiscal Year 2005 assumes a single-string life support system architecture for 

all cases. Because different technologies may require differing levels of additional equipment to assure satisfactory 

redundancy and reliability for an actual flight configuration, this assumption may be a significant simplification in 

this computation. 

2.4 TECHNOLOGY ASSUMPTIONS

2.4.1 ORBITING RESEARCH FACILITY: INTERNATIONAL SPACE STATION UPGRADE MISSION

International Space Station uses aluminum modules and nodes pressurized to 101 kPa. Solar photovoltaic 

power generation with rechargeable batteries for energy storage provide continuous power. The external thermal 

control system uses a single-phase, pumped ammonia loop to transport thermal energy and rejects the thermal loads 

using anti-sun tracking radiators with Z-93 surface coating. The baseline hardware configuration associated with 

completion of Phase 3, or “assembly complete,” is the assumed baseline along with an additional mission duration 

of ten years. For this computation, extravehicular activities are not considered. Further, the baseline provides 

1.27 kg/d of potable water to payloads that is not recovered. 9 Table 2.4.2 details specific inputs for the ISS 

Upgrade Mission. 

2.4.1.1 BASELINE LIFE SUPPORT SYSTEM TECHNOLOGY

The baseline, for the purposes of this document, is defined based on the USOS ECLSS scaled for a crew of 

six. See Stafford, et al. (2001), for details of the life support system architecture. This suite uses physicochemical 

technologies to regenerate air and water, while food is supplied as individual prepackaged entrees, including frozen 

food selections. Waste is stored without reclaiming any commodities. Thermal management employs coldplates 

 

9 While this may seem wasteful, especially over a mission duration of ten years, payload wastewater may contain many 

constituents that the life support system’s water subsystem is not designed to handle adequately. Thus, rather than limit 

research on International Space Station only to experiments that generate compatible wastewater, and possibly jeopardize 

its overall research mission and/or the crew’s health through contaminating the water subsystem, it is prudent to simply 

dump this wastewater stream. 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 February 2006 

9 

and condensing heat exchangers to collect sensible and latent heat loads, a single-phase fluid to transport heat, and 

radiators to reject heat. Clothing is supplied from Earth clean and discarded to the waste subsystem once it is 

deemed too dirty to wear. See Figure 2.4.1. See Section 8 for a list of acronyms used in this figure. 

2.4.1.1.1 Air 

The baseline air suite uses regenerable carbon dioxide removal equipment based on molecular sieve 

technology. The absorbed carbon dioxide is dumped overboard without recovering any commodities. The trace 

contaminant control system for atmospheric gases uses activated carbon, for non-combustible trace gas removal, and 

bacteria filter assemblies, for particulate removal, neither of which are regenerated. Further, the trace contaminant 

control system also removes trace combustible gases in the crew cabin. Oxygen is supplied both as pressurized gas 

from high-pressure stores, and as a product from electrolysis of water using solid polymer technology. The 

associated product hydrogen is dumped overboard. Electrolysis water is provided by the water subsystem. Nitrogen 

is supplied from high-pressure gas stocks. A major constituent analyzer and a fire detection and suppression system 

provide monitoring for air contaminants and combustion products. 

2.4.1.1.2 Food 

Food is provided as individual entrees from Earth. A mix of fresh, dehydrated, and full-water preserved, 

shelf-stable, or frozen foods are used. This system provides significant quantities of water, but also requires 

significant quantities of packaging. The nominal crew metabolic energy requirement for intravehicular activities 

only is 11.82 MJ/CM-d. Heavier workloads, such as those associated with extravehicular activities, generally 

require greater food intake. For this mission, the crew nominally receives 1.372 kg/CM-d 10 of food. Neglecting 

the dry component, the food mass as-shipped is 0.691 kg/CM-d of moisture with 0.240 kg/CM-d of disposable 

packaging. The corresponding specialized food storage structure adds an additional 0.860 kg/CM-d. Supporting 

technology includes conditioned cold storage and some food preparation equipment. 

2.4.1.1.3 Thermal 

Thermal management is divided into two systems here. The internal thermal control system includes the 

avionic air assemblies, which provide air-cooling for equipment, the common cabin air assemblies, which cool, 

dehumidify, and circulate cabin air, condensate storage, and the water flow loops for heat transport. Coldplates and 

heat exchangers are assumed part of other equipment, while the external thermal control system costs are assessed 

using the cooling-mass penalty. 

2.4.1.1.4 Waste 

Solid waste is stored and returned aboard the crew transfer vehicle or burned upon re-entry in an 

expendable resupply vehicle. This includes trash, fecal material, brine from the urine and water processing, and 

used filters and cartridges. The toilet is also included here under the waste subsystem. 

2.4.1.1.5 Water 

Urine is processed by vapor compression distillation. The brine is either returned to Earth or dumped. All 

grey water, including hygiene water, effluent from the vapor compression distillation, and condensate from 

dehumidification, is processed through a water processor. The water processor employs two multifiltration units, a 

volatile removal assembly, phase separators, and an ion exchange bed. A process control water quality monitor 

provides water quality assurance. Efficiency of recovery is high, but many expendables, mostly filter cartridges, are 

needed. Additional water may enter ISS directly, such as from the Shuttle’s stock of fuel cell water or as moisture 

contained in food, or indirectly, as a human metabolic product from the consumption of supplied food. The first 

mechanism is not included while the second and third mechanisms are a natural part of the overall life support 

commodity mass balance. Lastly, water may also come from stocks, which is the assumed source of any additional 

water not contained either as food moisture or arising as metabolic products from food consumption. Due to water 

losses for payloads, the ISS Upgrade Mission will probably be “water poor” in the nominal case without additional 

water stores. 

 

10 The units here, kilograms per crewmember per day [kg/CM-d], denote a per person basis. 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 February 2006 

10 

2.4.1.1.6 Human Accommodations 

Clothing is delivered with the crew at the beginning of an expedition and returned to Earth with the crew at 

the end of each expedition. A usage rate of 0.486 kg/CM-d, in a volume of 0.00285 m3/CM-d, is assumed. 

2.4.1.2 ADVANCED LIFE SUPPORT TECHNOLOGY

In contrast to the architecture using the baseline hardware, the advanced technology suite reduces 

accumulated atmospheric carbon dioxide with a Sabatier carbon dioxide reduction assembly and extracts water from 

waste, including hygiene wipes, using lyophilization. Melt compaction provides waste volume reduction. 

Additionally, the advanced technology suite stores atmospheric gases as cryogens, feeds the crew with an ambient 

temperature pre-packaged food system, and reclaims water using a vapor phase catalytic ammonia removal water 

recovery system without air evaporation. An aqueous laundry recycles crew clothing. See Figure 2.4.2. See 

Section 8 for a list of acronyms used in this figure. 

2.4.1.2.1 Air 

The advanced suite uses a regenerable carbon dioxide removal assembly based on a four-bed molecular 

sieve technology, a Sabatier carbon dioxide reduction assembly with a gas stream compressor, and a trace 

contaminant control assembly based on baseline technology. Adequate water is assumed available to avoid supply 

penalties for any necessary oxygen and hydrogen. Specifically, Sabatier reduces carbon dioxide according to the 

availability of hydrogen from the oxygen generation assembly. Any carbon dioxide that is not reduced is vented to 

space. High efficiency particulate air filters provide particulate removal. Gases for atmospheric pressurization, 

specifically oxygen and nitrogen, are stored under lower pressure as cryogens compared to the high-pressure storage 

used within the baseline suite. Other aspects of the advanced air suite are identical to the baseline technology suite 

for air listed in Section 2.4.1.1.1. 

2.4.1.2.2 Food 

The advanced suite for food employs ambient storage, prepackaged food with comparable nutritional 

content to the food subsystem outlined in Section 2.4.1.1.2. This food system provides 1.147 kg/CM-d of food, or 

0.466 kg/CM-d of food moisture, as-shipped, if the dry food mass is neglected. 0.264 kg/CM-d of disposable 

packaging is required. The corresponding specialized food storage structure adds an additional 0.860 kg/CM-d. 

Dedicated cold storage is unnecessary. 

2.4.1.2.3 Thermal 

The advanced suite for the thermal subsystem uses the same technologies as the baseline suite for the 

thermal subsystem described in Section 2.4.1.1.3. 

2.4.1.2.4 Waste 

The advanced suite for waste uses lyophilization to recover water from solid wastes and hygiene wipes. 

Reclaimed water passes to the water subsystem to remove impurities. Dry, solid waste is volume reduced using a 

plastic melt compactor, stored, and finally returned to Earth for ultimate disposal. 

2.4.1.2.5 Water 

The advanced suite for water recovery uses the vapor phase catalytic ammonia removal technology for 

primary water processing of both urine and grey water. Vapor phase catalytic ammonia removal uses distillation as 

its basic physicochemical mechanism, with additional integrated reactors for oxidation and reduction. Brine is sent 

to the waste subsystem for dewatering. Product water from the vapor phase catalytic ammonia removal assembly 

requires no further polishing, though a process control water quality monitor provides water quality assurance. 

Recovery efficiency with this system is high with reduced expendables compared to the baseline suite. 

2.4.1.2.6 Human Accommodations 

The advanced approach assumes an aqueous laundry. This will significantly increase the daily grey water 

load, but reduce the required mass of clothing compared to the baseline approach. While the apparent clothing 

usage rate to the crew remains unchanged, the laundry system cleans soiled clothing for reuse, prolonging clothing 

life and reducing associated waste loads. 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 

11 

Figure 2.4.1 International Space Station Upgrade Mission using Baseline Technologies. 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 

12 

Figure 2.4.2 International Space Station Upgrade Mission using Advanced Technologies. 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 February 2006 

13 

2.4.2 NEAR-TERM EXPLORATION MISSION: CREW EXPLORATION VEHICLE

The Crew Exploration Vehicle uses a capsule to transport the crew in Earth-Luna space. With the 

infrastructure values assumed, per Table 2.4.3, some cabin radiation shielding covers the entire cabin. The power 

infrastructure assumes fuel cells, although water from the fuel cells is not assumed. 11 The external thermal control 

system uses a single-phase, pumped-loop to transport thermal energy and rejects the loads using body-fitted, flowthrough radiators. Extravehicular activities from the Crew Exploration Vehicle are contingency events only, so 

support for extravehicular activities is not included here. Table 2.4.2 details specific inputs. 

2.4.2.1 BASELINE LIFE SUPPORT SYSTEM TECHNOLOGY

The baseline technology suite, for the purposes of this document, uses current storage technology to 

support a crew of four. See Hanford (2005) for details. The Crew Exploration Vehicle life support system, using 

current technologies, maintains the cabin atmosphere with high-pressure gas stores and consumable carbon dioxide 

removal hardware. Clean water is provided from stores, while wastes are all stored. Food is pre-packaged, 

requiring only minor operations before consumption. Cooling employs coldplates and condensing heat exchangers 

to collect heat loads, a single-phase fluid to transport heat, and radiators to reject heat. For this assessment, the 

applied cooling-mass penalty represents radiators constructed solely from aluminum and other metallic materials. 

Clothing is supplied from Earth clean and discarded to the waste subsystem once it is deemed too dirty to wear. See 

Figure 2.4.3. See Section 8 for a list of acronyms used in this figure. 

2.4.2.1.1 Air 

The baseline air suite uses non-regenerable carbon dioxide removal equipment based on lithium hydroxide. 

The trace contaminant control system for atmospheric gases uses activated carbon for non-combustible trace gas 

removal, and high efficiency particulate air filters for bacteria and particulate removal, neither of which are 

regenerated. Further, the trace contaminant control system also removes trace combustible gases from the crew 

cabin. Oxygen and nitrogen are supplied as pressurized gases from high-pressure stores. A major constituent 

analyzer and a fire detection and suppression system monitor for air contaminants and combustion products. 

2.4.2.1.2 Biomass 

The Crew Exploration Vehicle does not produce any biomass. 

2.4.2.1.3 Food 

The baseline suite for food uses ambient storage, prepackaged food. The nominal crew metabolic energy 

requirement for intravehicular activities only is 11.82 MJ/CM-d. Heavier workloads, such as those associated with 

extravehicular activities, generally require greater food intake. For this mission, the crew nominally receives 

1.147 kg/CM-d of food, or 0.466 kg/CM-d of food moisture, as-shipped, if the dry food mass is neglected. 

0.264 kg/CM-d of disposable packaging is required. The corresponding specialized food storage structure adds an 

additional 0.860 kg/CM-d. Dedicated cold storage is unnecessary. Supporting technology includes some food 

preparation equipment. 

2.4.2.1.4 Thermal 

Thermal management for the baseline configuration is divided between two systems, the Thermal 

Subsystem and the Cooling External Interface. The internal thermal control system includes the avionics air 

assembly, which provides air-cooling for equipment, the common cabin air assembly, which dehumidifies cabin air 

and controls air temperature, condensate storage, and thermal transport fluid loops. Coldplates and heat exchangers 

are physically integrated into the hardware they cool. The external thermal control system is nominally represented 

by the cooling-mass penalty. 

 

11 Author’s note: The Metric assessments for the Crew Exploration Vehicle before the release of an official Lunar 

architecture. Thus, assuming no water from fuel cells is conservative for this mission element. 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 February 2006 

14 

2.4.2.1.5 Waste 

Solid waste is stored aboard the Crew Exploration Vehicle. This includes trash, fecal material, and used 

filters and cartridges. The toilet is also included in the waste subsystem. 

2.4.2.1.6 Water 

For this assessment, the baseline water subsystem provides water solely from stores. Wastewater is also 

stored. A process control water quality monitor samples discharged water to assure overall water safety. 

2.4.2.1.7 Human Accommodations 

Clothing is launched with the crew at the beginning of this mission and returns to Earth with the crew at the 

end of this mission. A usage rate of 0.486 kg/CM-d, in a volume of 0.00285 m3/CM-d, is assumed. 

2.4.2.2 ADVANCED LIFE SUPPORT TECHNOLOGY

Though similar to the baseline approach above, the advanced technology suite for the Crew Exploration 

Vehicle stores pressurization gases as cryogens and recycles non-urine wastewater. A low-moisture content diet is 

also assumed. See Figure 2.4.4. See Section 8 for a list of acronyms used in this figure. 

2.4.2.2.1 Air 

The advanced life support suite, compared to the baseline suite in Section 2.4.2.1.1, stores gases for 

pressurization as cryogens instead of under high pressure. Other technologies within the advanced air suite are 

identical to those within the baseline technology suite for air as listed in Section 2.4.2.1.1. 

2.4.2.2.2 Biomass 

The biomass subsystem here is identical to the baseline suite in Section 2.4.2.1.2. 

2.4.2.2.3 Food 

The advanced suite for food employs ambient storage, low-moisture content, prepackaged food with 

comparable nutritional to the diet described in Section 2.4.2.1.3. This food system provides 0.918 kg/CM-d of food, 

or 0.248 kg/CM-d of food moisture, as-shipped, if the dry food mass is neglected. 0.267 kg/CM-d of disposable 

packaging is required. The corresponding specialized food storage structure adds an additional 0.860 kg/CM-d. 

Again, dedicated cold storage is unnecessary and supporting technology includes some food preparation equipment. 

2.4.2.2.4 Thermal 

The advanced life support suite for the thermal subsystem uses the same technologies as the baseline suite 

for the thermal subsystem described in Section 2.4.2.1.4. 

2.4.2.2.5 Waste 

The advanced life support suite for waste management uses the same technologies as the baseline suite for 

waste management described in Section 2.4.2.1.5. 

2.4.2.2.6 Water 

The advanced water system dumps urine but reclaims grey water using Water Recovery System 

technologies from the ISS ECLSS. The water processor employs two multifiltration units, a volatile removal 

assembly, phase separators, and an ion exchange bed. A process control water quality monitor provides water 

quality assurance. Efficiency of recovery is high, but many expendables, mostly filter cartridges, are needed. 

2.4.2.2.7 Human Accommodations 

The advanced life support approach for human accommodations uses the same approaches as the baseline 

human accommodations interface described in Section 2.4.2.1.7. 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 

15 

Figure 2.4.3 Crew Exploration Vehicle using Baseline Technologies. 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 

16 

T

Vent

Air

Air

Air

Grey Water

HO

Urine

LiOH, CO

2, and Food Waste

Hygiene

Consumable 

Clothing

H

2

O

Food & 

Drink

Food 

Preparatio

Food 

Waste

/ Trash

Food Waste

O2 from 

O2 / N2 Cabin

Regulator

Crew Cabin

Cryogenic

O2 / N2

Storage

CO2, Air

FDS

HP O

2 / N2

TCCS HEPA MCA

Air

Urinal

Urine Feces

Commode

Feces

Grey Water

pretreat 

oxone + H2SO4

CCAA Heat

H2O

AAA

Tank

Cond. 

Grey Water

Potable Water

Away from Luna

Human Waste 

Storage

Trash 

Waste 

Storage

Expended Clothes to Trash

Air

AIR . 

 HUMAN ACCOMMODATIONS

WATER . WASTE

LiOH

Urine

LiOH, 

CO2

Potable Water

Potable 

H2O 

Product 

Tank

W W 

Tank

MCV

Vent to 

Cabin

MLS

MF Bed 1MF Bed 2

VRA

Particulate

Filter

IX Bed Clean?

Unclean

H2O

Clean 

H2O

Water 

Storage H2O

Volatiles to Vent

TCS Worki

Used Wipes

Fecal 

Storage

HP O

2

Figure 2.4.4 Crew Exploration Vehicle using Advanced Technologies. 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 February 2006 

17 

2.4.3 NEAR-TERM EXPLORATION MISSION: LUNAR SURFACE ACCESS MODULE

The Lunar Surface Access Module transports the crew between low-Lunar orbit and the surface. With the 

infrastructure values assumed, per Table 2.4.3, some cabin radiation shielding covers the entire cabin. The power 

infrastructure assumes fuel cells, although water from the fuel cells is not assumed. 12 The external thermal control 

system uses a single-phase, pumped-loop to transport thermal energy and rejects the loads using body-fitted, flowthrough radiators. An equatorial landing site is assumed. Table 2.4.2 details specific inputs. 

2.4.3.1 BASELINE LIFE SUPPORT SYSTEM TECHNOLOGY

The baseline technology suite, for the purposes of this document, uses current storage technology to 

support a crew of four. See Hanford (2005) for details. The Lunar Surface Access Module life support system, 

using current technologies, maintains the cabin atmosphere with high-pressure gas stores and consumable carbon 

dioxide removal hardware. Clean water is provided from stores, while wastes are all stored. Food is pre-packaged, 

requiring only minor operations before consumption. Cooling employs coldplates and condensing heat exchangers 

to collect heat loads, a single-phase fluid to transport heat, and radiators to reject heat. For this assessment, the 

applied cooling-mass penalty represents radiators constructed solely from aluminum and other metallic materials. 

Clothing is supplied from Earth clean and discarded to the waste subsystem once it is deemed too dirty to wear. See 

Figure 2.4.5. See Section 8 for a list of acronyms used in this figure. 

2.4.3.1.1 Air 

The baseline air suite uses non-regenerable carbon dioxide removal equipment based on lithium hydroxide. 

The trace contaminant control system for atmospheric gases uses activated carbon for non-combustible trace gas 

removal, and high efficiency particulate air filters for bacteria and particulate removal, neither of which are 

regenerated. Further, the trace contaminant control system also removes trace combustible gases from the crew 

cabin. Oxygen and nitrogen are supplied as pressurized gases from high-pressure stores. A major constituent 

analyzer and a fire detection and suppression system monitor for air contaminants and combustion products. 

2.4.3.1.2 Biomass 

The Lunar Surface Access Module does not produce any biomass. 

2.4.3.1.3 Food 

The baseline suite for food employs ambient storage, prepackaged food. The nominal crew metabolic 

energy requirement for intravehicular activities only is 11.82 MJ/CM-d. Heavier workloads, such as those 

associated with extravehicular activities, generally require greater food intake. For this mission, the crew nominally 

receives 1.198 kg/CM-d of food, or 0.487 kg/CM-d of food moisture, as-shipped, if the dry food mass is neglected. 

0.275 kg/CM-d of disposable packaging is required. The corresponding specialized food storage structure adds an 

additional 0.860 kg/CM-d. Dedicated cold storage is unnecessary. Supporting technology includes some food 

preparation equipment. 

2.4.3.1.4 Thermal 

Thermal management for the baseline configuration is divided between two systems, the Thermal 

Subsystem and the Cooling External Interface. The internal thermal control system includes the avionics air 

assembly, which provides air-cooling for equipment, the common cabin air assembly, which dehumidifies cabin air 

and controls air temperature, condensate storage, and thermal transport fluid loops. Coldplates and heat exchangers 

are physically integrated into the hardware they cool. The external thermal control system is nominally represented 

by the cooling-mass penalty. 

 

12 Author’s note: The Metric assessments for the Lunar Surface Access Module before the release of an official Lunar 

architecture. Thus, assuming no water from fuel cells is conservative for this mission element. 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 February 2006 

18 

2.4.3.1.5 Waste 

Solid waste is stored aboard the Lunar Surface Access Module. This includes trash, fecal material, 

extravehicular activity solid wastes, and used filters and cartridges. The toilet is also included in the waste 

subsystem. 

2.4.3.1.6 Water 

For this assessment, the baseline water subsystem provides water solely from stores. Wastewater is also 

stored. A process control water quality monitor samples discharged water to assure overall water safety. 

2.4.3.1.7 Extravehicular Activity Support 

To support extensive extravehicular activities while operating independently, the Lunar Surface Access 

Module is assumed to carry a standard airlock even though this vehicle will see few extravehicular activities 

according to Hanford (2005). The life support system provides stores of water and oxygen to the extravehicular 

mobility units for cooling and crew consumption, and water to charge the internal liquid cooling loops. Further, 

carbon dioxide is removed from the airlock atmosphere using dedicated lithium hydroxide canisters. An airlock gas 

pump recaptures all but ten percent of the airlock atmosphere during each airlock cycle. 

2.4.3.1.8 Human Accommodations 

Clothing is launched with the crew at the beginning of this mission and returns to Earth with the crew at the 

end of this mission. A usage rate of 0.486 kg/CM-d, in a volume of 0.00285 m3/CM-d, is assumed. 

2.4.3.2 ADVANCED LIFE SUPPORT TECHNOLOGY

Though similar to the baseline approach above, the advanced technology suite for the Lunar Surface 

Access Module stores pressurization gases as cryogens and recycles non-urine wastewater. A low-moisture content 

diet is also assumed. See Figure 2.4.6. See Section 8 for a list of acronyms used in this figure. 

2.4.3.2.1 Air 

The advanced life support suite, compared to the baseline suite in Section 2.4.3.1.1, stores gases for 

pressurization as cryogens instead of under high pressure. Other technologies within the advanced air suite are 

identical to those within the baseline technology suite for air as listed in Section 2.4.3.1.1. 

2.4.3.2.2 Biomass 

The biomass subsystem here is identical to the baseline suite in Section 2.4.3.1.2. 

2.4.3.2.3 Food 

The advanced suite for food employs ambient storage, low-moisture content, prepackaged food with 

comparable nutritional content to the diet described in Section 2.4.3.1.3. This food system provides 0.959 kg/CM-d 

of food, or 0.259 kg/CM-d of food moisture, as-shipped, if the dry food mass is neglected. 0.278 kg/CM-d of 

disposable packaging is required. The corresponding specialized food storage structure adds an additional 

0.860 kg/CM-d. Again, dedicated cold storage is unnecessary and supporting technology includes some food 

preparation equipment. 

2.4.3.2.4 Thermal 

The advanced life support suite for the thermal subsystem uses the same technologies as the baseline suite 

for the thermal subsystem described in Section 2.4.3.1.4. 

2.4.3.2.5 Waste 

The advanced life support suite for waste management uses the same technologies as the baseline suite for 

waste management described in Section 2.4.3.1.5. 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 February 2006 

19 

2.4.3.2.6 Water 

The advanced water system dumps urine but reclaims grey water using Water Recovery System 

technologies from the ISS ECLSS. The water processor employs two multifiltration units, a volatile removal 

assembly, phase separators, and an ion exchange bed. A process control water quality monitor provides water 

quality assurance. Efficiency of recovery is high, but many expendables, mostly filter cartridges, are needed. 

2.4.3.2.7 Extravehicular Activity Support 

The extravehicular activity support for the advanced life support system within the Lunar Surface Access 

Module is identical to the technologies described for the baseline extravehicular activity support suite in 

Section 2.4.3.1.7. 

2.4.3.2.8 Human Accommodations 

The advanced life support approach for human accommodations uses the same approaches as the baseline 

human accommodations interface described in Section 2.4.3.1.8. 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 

20 

Figure 2.4.5 Lunar Surface Access Module using Baseline Technologies. 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 

21 

Fecal 

Storage

AIR .

T

 HUMAN ACCOMMODATIONS

WATER .

 EVA SUPPORT

 WASTE

Air

Air

Grey Water

Urine

Consumable 

Clothing

HP O2

Food & 

Drink

Food 

Preparatio

Food 

Waste

/ Trash

t

O2 from 

O2 / N2 Cabin

Regulator

Crew Cabin

Cryogenic

O2 / N2

Storage

CO2, Air

FDS

EMU

TCCS HEPA MCA

Air

Urinal

Urine Feces

Commode

Feces

pretreat 

oxone + H2SO4

CCAA

H2O

AAA

Food

Grey Water

Potable Water

Away from Luna

Human Waste 

Storage

Trash 

Waste 

Storage

Spent H2O, O2

Used Wipes to Trash

LiOH

LiOH, 

CO2

Vent

Potable 

H2O 

Product 

Tank

W W 

Tank

MCV

Vent to 

Cabin

MLS

MF Bed 1MF Bed 2

VRA

IX Bed Clean?

Unclean

H2O

Clean 

H2O

Water 

Storage H2O

CO2 Removal

 (LiOH)

A/L Air Save Pump

to Cabin

from A/L

Lost A/L Gases

CO2

Hygiene

TCS Workin

Figure 2.4.6 Lunar Surface Access Module using Advanced Technologies. 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 February 2006 

22 

2.4.4 NEAR-TERM EXPLORATION MISSION: DESTINATION SURFACE SYSTEM

The Destination Surface System assumes a rigid International Space Station common module structure with 

dedicated radiation protection from polyethylene lining the walls. The crew may be housed within a hardened 

domain, but this is not included in the assessed infrastructure values for life support system hardware. A small 

nuclear reactor provides continuous power. The external thermal control system uses a single-phase, pumped loop 

to transport thermal energy and rejects the thermal loads using flow-through radiators. An equatorial site on the 

Lunar surface is assumed. Table 2.4.3 lists assumed infrastructure values while Table 2.4.2 details specific inputs 

for the Destination Surface System of the Near-Term Exploration Mission. 

2.4.4.1 BASELINE LIFE SUPPORT SYSTEM TECHNOLOGY

The baseline technology suite, for the purposes of this document, is defined based on the USOS ECLSS 

scaled for a crew of six. See Hanford (2005), for details. This suite uses physicochemical technologies to 

regenerate air and water, while food is supplied mainly as prepackaged individual, shelf-stable entrees. Breathing 

and pressurization gases are provided from stores. Waste is stored without reclaiming any products from that waste. 

Cooling employs coldplates and condensing heat exchangers to collect heat loads, a single-phase fluid to transport 

heat, and radiators to reject heat. For this assessment, the applied cooling-mass penalty represents radiators 

constructed solely from aluminum and other metallic materials. Clean clothing is launched with the vehicle and left 

on the surface with the vehicle upon the departure of the crew from Luna. See Figure 2.4.7. See Section 8 for a list 

of acronyms used in this figure. 

2.4.4.1.1 Air 

The baseline air suite for the Destination Surface System uses regenerable carbon dioxide removal 

equipment based on molecular sieve technology, which is a four-bed molecular sieve. Absorbed carbon dioxide is 

dissociated from the absorbing media and exhausted from the vehicle without recovering any commodities. The 

trace contaminant control system for atmospheric gases uses activated carbon for non-combustible trace gas 

removal, and high efficiency particulate air filters for bacteria and particulate removal, neither of which are 

regenerated. Further, the trace contaminant control system also removes trace combustible gases from the crew 

cabin. Oxygen and nitrogen are supplied as pressurized gases from high-pressure stores. A major constituent 

analyzer and a fire detection and suppression system monitor for air contaminants and combustion products. 

2.4.4.1.2 Biomass 

The Destination Surface System baseline configuration does not produce any biomass. 

2.4.4.1.3 Food 

The baseline suite for food uses ambient storage, prepackaged food. The nominal crew metabolic energy 

requirement for intravehicular activities only is 11.82 MJ/CM-d. Heavier workloads, such as those associated with 

extravehicular activities, generally require greater food intake. For this mission, the crew nominally receives 

1.150 kg/CM-d of food, or 0.467 kg/CM-d of food moisture, as-shipped, if the dry food mass is neglected. 

0.264 kg/CM-d of disposable packaging is required. The corresponding specialized food storage structure adds an 

additional 0.860 kg/CM-d. Supporting technology includes some food preparation equipment. 

2.4.4.1.4 Thermal 

Thermal management is divided into two systems. The internal thermal control system includes the avionic 

air assemblies, which provide air-cooling for equipment, the common cabin air assemblies, which cool and 

dehumidify cabin air, condensate storage, and the water flow loops for heat transport. Coldplates and heat 

exchangers are assumed part of other equipment while the external thermal control system is included in the 

assessed cooling-mass penalty. 

2.4.4.1.5 Waste 

Solid waste is simply stored, without treatment, aboard the Destination Surface System. This includes 

trash, fecal material, brine from the urine and water processing, and used filters and cartridges. The toilet is also 

included in this calculation under the waste subsystem. 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 February 2006 

23 

2.4.4.1.6 Water 

Urine is processed by vapor compression distillation. The brine is stored and remains with the vehicle after 

the crew departs. All grey water, including hygiene water, effluent from the vapor compression distillation, and 

condensate from dehumidification, is processed through a water processor. The water processor employs two 

multifiltration units, a volatile removal assembly, phase separators, and an ion exchange bed. A process control 

water quality monitor provides water quality assurance. Efficiency of recovery is high, but many expendables, 

mostly filter cartridges, are needed. Water may enter the life support system directly, such as from moisture within 

prepackaged food, or indirectly, as a human metabolic product from the consumption of the prepackaged food. 

Water may also come from water stores. 

2.4.4.1.7 Extravehicular Activity Support 

The extravehicular mobility unit consumables include oxygen, for metabolic consumption and suit 

pressurization, and water, which is rejected to provide thermal management and consumed by the crew as drinks. 

Though not consumed, water also provides the working fluid for the internal cooling garment. This extravehicular 

mobility unit uses lithium hydroxide for carbon dioxide removal. An airlock pump, which is a compressor, reduces 

the airlock internal pressure to about ten percent of the cabin pressure, reducing gas losses during airlock operations. 

The Destination Surface System airlock also accommodates removal of carbon dioxide from the extravehicular 

mobility unit following extravehicular activities, and a carbon dioxide removal assembly specifically dedicated to 

the airlock. Atmospheric gas and water losses are actually included as part of the air and water subsystems in this 

calculation, and not as part of the values presented for extravehicular activity support. 

2.4.4.1.8 Human Accommodations 

Clothing is launched from Earth with the Destination Surface System and stays with the vehicle at the end 

of the surface phase. When clothing is deemed too dirty to wear, it is sent to waste storage and replaced with a clean 

garment from stores. A usage rate of 0.486 kg/CM-d, in a volume of 0.00285 m3/CM-d, is assumed. 

2.4.4.2 ADVANCED LIFE SUPPORT TECHNOLOGY

The advanced life support suite is similar to the baseline approach above. Cryogenic gas storage, vapor 

phase catalytic ammonia removal, and a low-moisture content, ambient food system are less massive than similar 

baseline technologies. See Figure 2.4.8. See Section 8 for a list of acronyms used in this figure. 

2.4.4.2.1 Air 

The advanced air suite for the Destination Surface System stores oxygen and nitrogen cryogenically. Other 

aspects of the advanced air suite are identical to the baseline technology suite for air listed in Section 2.4.4.1.1. 

2.4.4.2.2 Biomass 

The biomass subsystem here is identical to the baseline suite in Section 2.4.4.1.2. 

2.4.4.2.3 Food 

The advanced suite for food employs ambient storage, low-moisture content, prepackaged food with 

comparable nutritional to the diet described in Section 2.4.4.1.3. This food system provides 0.921 kg/CM-d of food, 

or 0.249 kg/CM-d of food moisture, as-shipped, if the dry food mass is neglected. 0.267 kg/CM-d of disposable 

packaging is required. The corresponding specialized food storage structure adds an additional 0.860 kg/CM-d. 

Again, the supporting hardware includes some food preparation equipment. 

2.4.4.2.4 Thermal 

The advanced suite for the thermal subsystem uses the same technologies as the baseline suite for the 

thermal subsystem described in Section 2.4.4.1.4. 

2.4.4.2.5 Waste 

The advanced suite for waste is identical to the baseline approach given in Section 2.4.4.1.5. 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 February 2006 

24 

2.4.4.2.6 Water 

The advanced water system is built around a vapor phase catalytic ammonia removal assembly to provide 

primary water processing of both urine and grey water. Brine is sent directly to waste storage without recovering 

any moisture. Product water from the vapor phase catalytic ammonia removal assembly requires no further 

polishing, though a process control water quality monitor provides water quality assurance. 

2.4.4.2.7 Extravehicular Activity Support 

The advanced suite for extravehicular activity support is identical to the baseline suite for extravehicular 

activity support. See Section 2.4.4.1.7. 

2.4.4.2.8 Human Accommodations 

The advanced life support system for human accommodations is identical to the corresponding baseline 

suite. See Section 2.4.4.1.8. 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 

25 

AIR .

T

 HUMAN ACCOMMODATIONS

WATER .

 EVA SUPPORT

 WASTE

Fecal 

Storage

Air

Air

Grey Water

Urine

Hygiene

Consumable 

Clothing

HP O2

Potable 

H2O 

Product 

Tank

W W 

Tank

MCV

Urine 

Tank

VCD

G/L Separator

Vent to 

Cabin

MLS

MF Bed 1MF Bed 2

VRA

IX Bed Clean?

Unclean

H2O

Clean 

H2O

HP O2

Food & 

Drink

Food 

Preparatio

Food 

Waste

/ Trash

t

O2 from 

Cabin

CO2 to

Vent

O2 / N2

Regulator

Crew Cabin

High 

Pressure 

O2 / N2

Storage

CO2, Air

FDS

EMU

TCCS HEPA MCA

Air

Urinal

Urine Feces

Commode

Feces

pretreat 

oxone + H2SO4

CCAA

H2O

AAA

Food

Grey Water

Potable Water

4BMS

Water 

Storage H2O

Brine Away from Luna

Human Waste 

Storage

Trash 

Waste 

Storage

Volatiles to Vent

Spent H2O, O2

Wipes to Trash

TCS Workin

A/L Air Save Pump

from A/L

Lost A/L Gases

A/L CO2

Removal CO2

to Cabin

CO2

CO2 Removal

 (LiOH) CO2

Figure 2.4.7 Destination Surface System using Baseline Technologies. 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 

26 

Fecal 

Storage

AIR .

T

 HUMAN ACCOMMODATIONS

WATER .

 EVA SUPPORT

 WASTE

Air

Air

Air

Grey Water

HO

2

Potable Water

Consumable Food Waste Clothing

HP O2

H

2

O

Food & 

Drink

Food 

Preparatio

Food 

Waste

/ Trash

Food Waste

t

O2 from 

Cabin

CO2 to

Vent

O2 / N2

Regulator

Crew Cabin

Cryogenic 

O2 / N2

Storage

CO2, Air

FDS

HP O

2 / N2

Drink H

2

O

EMU Cooling H

2

O

EMU

TCCS HEPA MCA

Air

Urinal

Urine Feces

Commode

Feces

Grey Water

pretreat 

oxone + H2SO4

CCAA Heat

H2O

AAA

Tank

Cond. 

EMU Solid Waste

Food

Grey Water

Potable Water

4BMS

Away from Luna

Human Waste 

Storage

Trash 

Waste 

Storage

Expended Clothes to Trash

Spent H2O, O2

Air

Wipes to Trash

Potable 

H2O 

Product 

Tank

W W 

VPCAR

Tank Grey Water

H

2

O

H

2

O

MCV

Clean? No

Yes

Brine

Urine

TCS Workin

CO2 Removal

 (LiOH)

A/L Air Save Pump

from A/L

Lost A/L Gases

A/L CO2

Removal CO2

to Cabin

CO2

Hygiene

CO2

Figure 2.4.8 Destination Surface System using Advanced Technologies. 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 February 2006 

27 

2.4.5 INDEPENDENT EXPLORATION MISSION: MARS TRANSIT VEHICLE

The Mars Transit Vehicle uses inflatable modules with radiation shielding for interplanetary travel. 

However, with the infrastructure values assumed, per Table 2.4.3, the cabin radiation shielding does not protect the 

life support equipment. 13 Thus, the volume infrastructure value reflects a pressurized, inflatable structure without 

radiation shielding. Power is provided by solar photovoltaic generation with minimal energy storage. The external 

thermal control system uses a single-phase, pumped-loop to transport thermal energy and rejects the loads using 

body-fitted, flow-through radiators. Extravehicular activities from the Mars Transit Vehicle are contingency events 

only, so support for extravehicular activities is not included here. Table 2.4.2 details specific inputs for the Mars 

Transit Vehicle segment of the Independent Exploration Mission. 

2.4.5.1 BASELINE LIFE SUPPORT SYSTEM TECHNOLOGY

The baseline technology suite, for the purposes of this document, is defined based on the USOS ECLSS 

scaled for a crew of six. See Stafford, et al. (2001), for details. This suite uses physicochemical technologies to 

regenerate air and water, while food is supplied mainly as prepackaged individual entrees, including frozen food 

selections. Because of the long mission duration, a biomass production chamber provides salad to supplement the 

prepackaged food system. 14 Waste is generally stored without reclaiming any products from that waste. Cooling 

employs coldplates and condensing heat exchangers to collect heat loads, a single-phase fluid to transport heat, and 

radiators to reject heat. For this assessment, the applied cooling-mass penalty represents radiators constructed solely 

from aluminum and other metallic materials. Clothing is supplied from Earth clean and discarded to the waste 

subsystem once it is deemed too dirty to wear. See Figure 2.4.9. See Section 8 for a list of acronyms used in this 

figure. 

2.4.5.1.1 Air 

The life support system for the Mars Transit Vehicle using baseline technologies employs regenerable 

carbon dioxide removal equipment based on molecular sieve technology. The absorbed carbon dioxide is dumped 

overboard and not recovered. The trace gas contaminant system uses activated carbon, for non-combustible trace 

gas removal, and bacteria filter assemblies, for particulate removal. These filters are not regenerated. Further, the 

trace contaminant control system also removes trace combustible gases in the crew cabin. Oxygen is supplied both 

as pressurized gas from high-pressure stores, and as a product from electrolysis of water using solid polymer 

technology. The associated product hydrogen is dumped overboard. Water for electrolysis is provided by the water 

subsystem. Because the Mars Transit Vehicle will be “water rich” from moisture stored in food and the relatively 

high rate of water reclamation from grey water, most oxygen will be generated by electrolysis. Nitrogen is supplied 

from high-pressure gas stocks. A major constituent analyzer and a fire detection and suppression system provide 

monitoring for air contaminants and combustion products. 

2.4.5.1.2 Biomass 

The baseline suite contains a small biomass production chamber, providing salad crops as a supplement to 

an otherwise prepackaged food system. Though the dietary nutrients gained from salad crops are relatively minor, 

salads, snacks, and steamed entrees provide a psychological advantage unavailable in a completely prepackaged 

food system and support anticipated requirements for long-duration space missions. 15 Supporting equipment for 

the biomass production chamber includes a nutrient solution supply, condensate storage, and a supplemental 

common cabin air assembly to handle the greater humidity loading and air circulation requirements. 

 

13 In fact, efficient design may use the mass of the life support hardware as partial radiation protection from the crew cabin, 

but any “radiation credit” may be difficult to forecast and, therefore, none is assumed here. 

14 While International Space Station Upgrade Mission is longer than the combined mission durations for all vehicles within 

the Mars Independent Exploration architecture, individual ISS crewmembers usually spend significantly less than a year 

per deployment to ISS. Thus, while fresh salad is assumed here as essential for crew physical and psychological health on 

extended missions, distinctions between International Space Station and this mission should be noted. 

15 Biomass production is not part of the current ISS ECLSS technology suite, so a salad machine may seem “odd” here. 

However, the significant rationale for a small biomass production facility like a salad machine is related to requirements for 

dietary diversity. Thus, a salad machine is included in both life support system configurations here to meet a requirement 

that is beyond those associated with historical and current vehicles. 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 February 2006 

28 

2.4.5.1.3 Food 

Food is provided as individual entrees from Earth. The baseline Mars Transit Vehicle relies on a variety of 

fresh, dehydrated, and full-water preserved, shelf-stable, or frozen foods. The diet is supplemented with fresh salad, 

snacks, and steamed entrees from a biomass production chamber. The nominal crew metabolic energy requirement 

for intravehicular activities only is 11.82 MJ/CM-d. Heavier workloads, such as those associated with 

extravehicular activities, generally require greater food intake. For this mission, the crew nominally receives 

1.362 kg/CM-d. Neglecting the dry component, the food mass as-shipped is 0.685 kg/CM-d of food. In either case, 

0.238 kg/CM-d of disposable packaging is required. The corresponding specialized food storage structure adds an 

additional 0.860 kg/CM-d. Supporting technology includes a dedicated cold storage and some food preparation 

equipment. 

2.4.5.1.4 Thermal 

Thermal management is divided into two systems. The internal thermal control system includes the avionic 

air assemblies, which provide air-cooling for equipment, the common cabin air assemblies, which cool, dehumidify, 

and circulate cabin air, condensate storage, and the water flow loops for heat transport. Coldplates and heat 

exchangers are assumed part of other equipment while the external thermal control system is included in the 

assessed cooling-mass penalty. 

2.4.5.1.5 Waste 

Solid waste is stored aboard the Mars Transit Vehicle. This includes trash, fecal material, brine from the 

urine and water processing, and used filters and cartridges. The toilet is also included in the waste subsystem. 

2.4.5.1.6 Water 

Urine is processed by vapor compression distillation. The brine is sent to waste storage. All grey water, 

including hygiene water, effluent from the vapor compression distillation, and condensate from dehumidification, is 

processed through a water processor. The water processor employs two multifiltration units, a volatile removal 

assembly, phase separators, and an ion exchange bed. A process control water quality monitor provides water 

quality assurance. Efficiency of recovery is high, but many expendables, mostly filter cartridges, are needed. 

Additional water may enter the life support system directly, such as from moisture within prepackaged food, or 

indirectly, as a human metabolic product from the metabolism of food. A third source of water is stores, but in the 

nominal case the Mars Transit Vehicle will probably be “water rich.” 

2.4.5.1.7 Human Accommodations 

Clothing is launched with the crew at the beginning of this mission and returns to Earth with the crew at the 

end of this mission. A usage rate of 0.486 kg/CM-d, in a volume of 0.00285 m3/CM-d, is assumed. 

2.4.5.2 ADVANCED LIFE SUPPORT TECHNOLOGY

Though similar to the baseline approach above, the advanced technology suite for the Mars Transit Vehicle 

employs a vapor phase catalytic ammonia removal water recovery system with a dedicated lyophilization for brine 

dewatering, a Sabatier to reduce carbon dioxide, stores pressurization gases as cryogens, and substitutes a 

completely ambient food subsystem. The salad machine is retained. Additionally, an aqueous laundry recycles 

crew clothing. The applied cooling-mass penalty reflects lightweight radiators constructed from composite 

materials. See Figure 2.4.10. See Section 8 for a list of acronyms used in this figure. 

2.4.5.2.1 Air 

The advanced life support suite, compared to the baseline suite in Section 2.4.5.1.1, adds a Sabatier carbon 

dioxide reduction assembly and stores gases for pressurization as cryogens instead of under high pressure. Adequate 

water is assumed available to avoid a supply penalty for any necessary oxygen and hydrogen. Sabatier reduces 

carbon dioxide according to the availability of hydrogen from the oxygen generation assembly. Carbon dioxide that 

is not reduced is vented to space. Other technologies within the advanced air suite are identical to those within the 

baseline technology suite for air as listed in Section 2.4.5.1.1. 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 February 2006 

29 

2.4.5.2.2 Biomass 

The biomass subsystem here is identical to the baseline suite in Section 2.4.5.1.2. 

2.4.5.2.3 Food 

Food is provided as individual entrees with some bulk packaged items. This diet relies on a variety of 

ambient temperature foods and is supplemented with fresh salad, snacks, and steamed entrees from a biomass 

production chamber. The nominal crew metabolic energy requirement for intravehicular activities only is 

11.82 MJ/CM-d. Heavier workloads, such as those associated with extravehicular activities, generally require 

greater food intake. For this mission, the crew nominally receives 1.138 kg/CM-d of food. Neglecting the dry 

component, the food mass as-shipped is 0.463 kg/CM-d with 0.262 kg/CM-d of disposable packaging. The 

corresponding specialized food storage structure adds an additional 0.860 kg/CM-d. Supporting technology includes 

some food preparation equipment. 

2.4.5.2.4 Thermal 

The advanced life support suite for the thermal subsystem uses the same technologies as the baseline suite 

for the thermal subsystem described in Section 2.4.5.1.4. 

2.4.5.2.5 Waste 

The advanced life support suite for waste management uses the same technologies as the baseline suite for 

waste management described in Section 2.4.5.1.5. 

2.4.5.2.6 Water 

The advanced water system is built around a vapor phase catalytic ammonia removal assembly to provide 

primary water processing of both urine and grey water. Lyophilization reclaims water from the primary processor 

brine, allowing almost complete water recovery. Product water from the lyophilization process passes to the 

primary processor. Product water from the vapor phase catalytic ammonia removal assembly requires no further 

polishing, though a process control water quality monitor provides water quality assurance. Overall recovery 

efficiency with this system is also high, with reduced expendables, compared to the baseline suite. 

2.4.5.2.7 Human Accommodations 

The advanced life support approach assumes an aqueous laundry. This will significantly increase the daily 

grey water load, but reduce the required mass of clothing compared to the baseline approach. While the apparent 

clothing usage rate remains unchanged for the crew, the laundry system cleans soiled clothing for reuse, prolonging 

clothing life and reducing associated waste loads. 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 

30 

Figure 2.4.9 Mars Transit Vehicle using Baseline Technologies. 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 

31 

Air

Grey Water

Food Waste

Heat

Tank

Cond. 

H

2

O

H

2

O CH4 to Vent

Tank

Cond. H2

O

Solution

Nutrient 

H

2

O

Food Waste

Urine

CO

2

H

2

O

VPCARH2O

H

2

O

Expended Clothing to Trash

Figure 2.4.10 Mars Transit Vehicle using Advanced Technologies. 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 February 2006 

32 

2.4.6 INDEPENDENT EXPLORATION MISSION: MARS DESCENT / ASCENT LANDER

The infrastructure penalties for the Mars Descent / Ascent Lander are associated with surface operations. 

This vehicle uses rigid aluminum modules per International Space Station architecture. Solar photovoltaic panels 

with regenerable fuel cell storage, assuming an equatorial surface site, provide power. The external thermal control 

system uses a single-phase, pumped loop to transport thermal energy and rejects the thermal loads using body-fitted, 

flow-through radiators. Again, an equatorial site on the Martian surface is assumed. While this vehicle will spend 

sufficient time operating in Martian orbit and, as a result, infrastructure for that phase must be considered for any 

viable vehicle, past experience dictates that the most severe sizing constraints are placed upon solar photovoltaic 

power generation and radiant cooling systems by the Martian surface environment when considering an equatorial 

landing site. Table 2.4.3 lists assumed infrastructure values while Table 2.4.2 details specific inputs for the Mars 

Descent / Ascent Lander segment of the Independent Exploration Mission. 

2.4.6.1 BASELINE LIFE SUPPORT SYSTEM TECHNOLOGY

The baseline technology suite, for the purposes of this document, is defined based on current technology 

scaled for a crew of six. See Stafford, et al. (2001), for details. This suite uses physicochemical technologies to 

regenerate air and water, while food is supplied as individual prepackaged entrees, including frozen food selections. 

Waste is stored without reclaiming any commodities. Thermal management employs coldplates and condensing 

heat exchangers to collect heat loads, a single-phase fluid to transport heat, and radiators to reject heat. Clothing is 

supplied from Earth clean and discarded to the waste subsystem once it is deemed too dirty to wear. See 

Figure 2.4.11. See Section 8 for a list of acronyms used in this figure. 

2.4.6.1.1 Air 

The baseline air suite for the Mars Descent / Ascent Lander uses regenerable carbon dioxide removal 

equipment based on molecular sieve technology. The absorbed carbon dioxide is dumped overboard without 

recovering any commodities. The trace contaminant control system for atmospheric gases uses activated carbon, for 

non-combustible trace gas removal, and bacteria filter assemblies, for particulate removal, neither of which are 

regenerated. Further, the trace contaminant control system also removes trace combustible gases in the crew cabin. 

Oxygen is supplied both as pressurized gas from high-pressure stores, and as a product from electrolysis of water 

using solid polymer technology. The associated product hydrogen is dumped overboard. Electrolysis water is 

provided by the water subsystem. Nitrogen is supplied from high-pressure gas stocks. A major constituent analyzer 

and a fire detection and suppression system provide monitoring for air contaminants and combustion products. 

2.4.6.1.2 Food 

Food is provided as individual entrees from Earth. A mix of fresh, dehydrated, and full-water preserved, 

shelf-stable, or frozen foods are used. The nominal crew metabolic energy requirement for intravehicular activities 

only is 11.82 MJ/CM-d. Heavier workloads, such as those associated with extravehicular activities, generally 

require greater food intake. For this mission, the crew nominally receives 1.378 kg/CM-d of food. Neglecting the 

dry component, the food mass as-shipped is 0.694 kg/CM-d. In addition, 0.241 kg/CM-d of disposable packaging is 

required. The corresponding specialized food storage structure adds an additional 0.860 kg/CM-d. Supporting 

technology includes dedicated cold storage and some food preparation equipment. 

2.4.6.1.3 Thermal 

Thermal management for the Mars Descent / Ascent Lander is divided between two systems here. The 

internal thermal control system includes the avionic air assemblies, which provide air-cooling for equipment, the 

common cabin air assemblies, which dehumidify cabin air, condensate storage, and the flow loops. Coldplates and 

heat exchangers are assumed part of other equipment while the external thermal control system is included in the 

assessed cooling-mass penalty. 

2.4.6.1.4 Waste 

The waste system provides only for rudimentary collection and storage of waste products. The waste 

system includes a toilet, pretreatment to stabilize urine, and separate storage for human metabolic wastes and trash. 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 February 2006 

33 

2.4.6.1.5 Water 

Urine is processed by vapor compression distillation. The brine is sent to the waste subsystem. All grey 

water, including hygiene water, effluent from the vapor compression distillation, and condensate from 

dehumidification, is processed through a water processor. The water processor employs two multifiltration units, a 

volatile removal assembly, phase separators, and an ion exchange bed. A process control water quality monitor 

provides water quality assurance. Efficiency of recovery is high, but many expendables, mostly filter cartridges, are 

needed. Additional water comes from stores. 

2.4.6.1.6 Extravehicular Activity Support 

While extravehicular activities from the Mars Descent / Ascent Lander are essential to mission success, 

such activities are expected to be limited in number. Thus, the entire cabin will function as an airlock and no effort 

is made to recover cabin gases before depressurization, preferring instead to simply repressurize the cabin from gas 

stocks when the crew reoccupies the Mars Descent / Ascent Lander en route to rendezvous with the Mars Transit 

Vehicle. The life support system is expected to provide stores of water and oxygen to the extravehicular mobility 

units for cooling and crew consumption, and water to charge the internal liquid cooling loops. A dedicated carbon 

dioxide removal assembly removes carbon dioxide from extravehicular mobility units following an extravehicular 

activity. 

2.4.6.1.7 Human Accommodations 

Clothing is launched with the vehicle before the Mars Descent / Ascent Lander leaves Earth. This clothing 

will remain with the vehicle when the crew departs either for surface operations or upon returning to the Mars 

Transit Vehicle. This clothing is not laundered. A usage rate of 0.486 kg/CM-d, in a volume of 0.00285 m3/CM-d, 

is assumed. 

2.4.6.2 ADVANCED LIFE SUPPORT TECHNOLOGY

The advanced life support suite for the Mars Descent / Ascent Lander uses the same technologies as the 

baseline suite for the waste subsystem, extravehicular activity support, and human accommodations. The advanced 

life support suite uses different technologies within the air subsystem, the food subsystem, and the water subsystem. 

The applied cooling-mass penalty reflects advanced technologies in the form of lightweight radiators constructed 

from composite materials. See Figure 2.4.12. See Section 8 for a list of acronyms used in this figure. 

2.4.6.2.1 Air 

The air subsystem for the advanced life support suite within the Mars Descent / Ascent Lander uses a solid 

amine vacuum desorbed processor to remove cabin carbon dioxide loads. Oxygen is not reclaimed from the carbon 

dioxide. Oxygen is supplied only from stores, and all pressurization gases are supplied from cryogenic sources. 

Other air subsystem hardware is identical to the technologies described for the baseline air subsystem in 

Section 2.4.6.1.1. 

2.4.6.2.2 Food 

Food is provided as individual entrees. This diet relies on a variety of ambient temperature, low-moisturecontent foods. The nominal crew metabolic energy requirement for intravehicular activities only is 11.82 MJ/CM-d. 

Heavier workloads, such as those associated with extravehicular activities, generally require greater food intake. 

For this mission, the crew nominally receives 0.922 kg/CM-d of food. Neglecting the dry component, the food mass 

as-shipped is 0.249 kg/CM-d. 0.268 kg/CM-d of disposable packaging is required. The corresponding specialized 

food storage structure adds an additional 0.860 kg/CM-d. Supporting technology includes some food preparation 

equipment. 

2.4.6.2.3 Thermal 

The thermal subsystem for the advanced life support suite within the Mars Descent / Ascent Lander is 

identical to the technologies listed for the baseline thermal subsystem in Section 2.4.6.1.3. 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 February 2006 

34 

2.4.6.2.4 Waste 

The waste subsystem for the advanced life support suite within the Mars Descent / Ascent Lander is 

identical to the technologies described for the baseline waste subsystem in Section 2.4.6.1.4. 

2.4.6.2.5 Water 

The water subsystem for the advanced life support suite within the Mars Descent / Ascent Lander uses 

vapor compression catalytic ammonia removal as the primary water processor. The brine is sent directly to solid 

waste storage with its moisture. A process control water quality monitor provides water quality assurance. 

2.4.6.2.6 Extravehicular Activity Support 

The extravehicular activity support for the advanced life support system within the Mars Descent / Ascent 

Lander is identical to the technologies described for the baseline extravehicular activity support suite in 

Section 2.4.6.1.6. 

2.4.6.2.7 Human Accommodations 

The human accommodations for the advanced life support system within the Mars Descent / Ascent Lander 

is identical to the technologies described for the baseline human accommodations suite in Section 2.4.6.1.7. 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 

35 

Figure 2.4.11 Mars Descent / Ascent Lander using Baseline Technologies. 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 

36 

Fecal 

Storage

Air

Air

Air

Grey Water

HO

2

Urine

Potable Water

Food Waste

Brine

Consumable 

Clothing

Potable 

H2O 

Product 

Tank

W W 

Tank

MCV

Clean?

No

Yes

Expended Clothes to Waste H2O

AIR .

T

 HUMAN ACCOMMODATIONS

WATER .

Wipes

Food & 

Drink

Food 

Preparatio

Food 

Waste

/ Trash

Food Waste

t

O2 from 

Cabin

CO2 to

Vent

O2 / N2

Regulator

Crew Cabin

Cryogenic

O2 / N2

Storage

CO2

FDS

O

2 / N2

 EVA SUPPORT

Spent H2O

Drink H

2

O

EMU Cooling H

2

O

EMU

TCCS HEPA MCA

Air

 WASTE

Urinal

Urine Feces

Commode

Feces

Solid Waste 

Storage

Grey

 Water

CCAA Heat

H2O

AAA

Tank

Cond. 

EMU Solid Waste

Food

Grey Water

Potable Water

SAVD

CO2 Removal

 (LiOH)

Hygiene

CO2

VPCAR

Grey Water

TCS Workin

Figure 2.4.12 Mars Descent / Ascent Lander using Advanced Technologies. 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 February 2006 

37 

2.4.7 INDEPENDENT EXPLORATION MISSION: SURFACE HABITAT LANDER

The Surface Habitat Lander assumes an inflatable module without radiation protection with the implied 

assumption that life support hardware is hardened versus environmental radiation loads. The crew may be housed 

within a hardened domain, but this is not included in the assessed infrastructure values for life support system 

hardware. A small nuclear reactor provides continuous power. The assumed value corresponds to a 100 kWe

nuclear reactor on an independent lander, but an actual system for this mission will likely be much smaller, both in 

capacity and overall mass, so the infrastructure value assumed is an approximation of the actual system. The 

external thermal control system uses a single-phase, pumped loop to transport thermal energy and rejects the thermal 

loads using body-fitted, flow-through radiators. An equatorial site on the Martian surface is assumed. Table 2.4.3 

lists assumed infrastructure values while Table 2.4.2 details specific inputs for the Surface Habitat Lander segment 

of the Independent Exploration Mission. 

2.4.7.1 BASELINE LIFE SUPPORT SYSTEM TECHNOLOGY

The baseline technology suite, for the purposes of this document, is defined based on the USOS ECLSS 

scaled for a crew of six. See Stafford, et al. (2001), for details. This suite uses physicochemical technologies to 

regenerate air and water, while food is supplied mainly as prepackaged individual entrees, including frozen food 

selections. Because of the long mission duration, biomass production chamber provides salad to supplement the 

prepackaged food system. 16 Waste is generally stored without reclaiming any products from that waste. Cooling 

employs coldplates and condensing heat exchangers to collect heat loads, a single-phase fluid to transport heat, and 

radiators to reject heat. For this assessment, the applied cooling-mass penalty represents radiators constructed solely 

from aluminum and other metallic materials. Clean clothing is launched with the vehicle and left on the surface 

within the vehicle upon the departure of the crew from Mars. See Figure 2.4.13. See Section 8 for a list of 

acronyms used in this figure. 

2.4.7.1.1 Air 

The baseline air suite on the Surface Habitat Lander uses regenerable carbon dioxide removal equipment 

based on molecular sieve technology. The absorbed carbon dioxide is dumped overboard without recovering any 

commodities. The trace contaminant control system for atmospheric gases uses activated carbon, for noncombustible trace gas removal, and bacteria filter assemblies, for particulate removal, neither of which are 

regenerated. Further, the trace contaminant control system also removes trace combustible gases in the crew cabin. 

Oxygen is supplied both as pressurized gas from high-pressure stores, and as a product from electrolysis of water 

using solid polymer technology. The associated product hydrogen is dumped overboard. Electrolysis water is 

provided by the water subsystem. Nitrogen is supplied from high-pressure gas stocks. A major constituent analyzer 

and a fire detection and suppression system provide monitoring for air contaminants and combustion products. 

2.4.7.1.2 Biomass 

The baseline suite contains a small biomass production chamber, providing salad crops as a supplement to 

an otherwise prepackaged food system. Though the dietary nutrients gained from salad crops are relatively minor, 

salads, snacks, and steamed entrees provide a psychological advantage unavailable in a completely prepackaged 

food system and support anticipated requirements for long-duration space missions. 17 Supporting equipment for 

the biomass production chamber includes a nutrient solution supply, condensate storage, and a supplemental 

common cabin air assembly to handle the greater humidity loading and air circulation requirements. 

 

16 While International Space Station Upgrade Mission is longer than the combined mission durations for all vehicles within 

the Mars Independent Exploration architecture, individual ISS crewmembers usually spend significantly less than a year 

per deployment to ISS. Thus, while fresh salad is assumed here as essential for crew physical and psychological health on 

extended missions, distinctions between International Space Station and this mission should be noted. 

17 Biomass production is not part of the current ISS ECLSS technology suite, so a salad machine may seem “odd” here. 

However, the significant rationale for a small biomass production facility like a salad machine is related to requirements for 

dietary diversity. Thus, a salad machine is included in both life support system configurations here to meet a requirement 

that is beyond those associated with historical and current vehicles. 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 February 2006 

38 

2.4.7.1.3 Food 

Food is provided as individual entrees from Earth. This system relies on a variety of fresh, dehydrated, and 

full-water preserved, shelf-stable, or frozen foods. The diet is supplemented with fresh salad, snacks, and steamed 

entrees from a biomass production chamber. The nominal crew metabolic energy requirement for intravehicular 

activities only is 11.82 MJ/CM-d. Heavier workloads, such as those associated with extravehicular activities, 

generally require greater food intake. For this mission, the crew nominally receives 1.362 kg/CM-d of food. 

Neglecting the dry component, the food mass as-shipped is 0.685 kg/CM-d with 0.238 kg/CM-d of disposable 

packaging. The corresponding specialized food storage structure adds an additional 0.860 kg/CM-d. Supporting 

technology includes dedicated cold storage and some food preparation equipment. 

2.4.7.1.4 Thermal 

Thermal management is divided into two systems. The internal thermal control system includes the avionic 

air assemblies, which provide air-cooling for equipment, the common cabin air assemblies, which cool and 

dehumidify cabin air, condensate storage, and the water flow loops for heat transport. Coldplates and heat 

exchangers are assumed part of other equipment while the external thermal control system is included in the 

assessed cooling-mass penalty. 

2.4.7.1.5 Waste 

Solid waste is simply stored, without treatment, aboard the Surface Habitat Lander. This includes trash, 

fecal material, brine from the urine and water processing, extravehicular activity wastes, and used filters and 

cartridges. The toilet is also included in this calculation under the waste subsystem. 

2.4.7.1.6 Water 

Urine is processed by vapor compression distillation. The brine is stored and remains with the vehicle after 

the crew departs. All grey water, including hygiene water, effluent from the vapor compression distillation, and 

condensate from dehumidification, is processed through a water processor. The water processor employs two 

multifiltration units, a volatile removal assembly, phase separators, and an ion exchange bed. A process control 

water quality monitor provides water quality assurance. Efficiency of recovery is high, but many expendables, 

mostly filter cartridges, are needed. Water may enter the life support system directly, such as from moisture within 

prepackaged food, or indirectly, as a human metabolic product from the consumption of the prepackaged food. 

Water may also come from water stores. Due to the high frequency of extravehicular activities, the Surface Habitat 

Lander will probably be “water poor” in the nominal case without additional stores. 

2.4.7.1.7 Extravehicular Activity Support 

The extravehicular mobility unit consumables include oxygen, for metabolic consumption and suit 

pressurization, and water, which is rejected to provide thermal management and consumed by the crew as drinks. 

Though not consumed, water also provides the working fluid for the internal cooling garment. This extravehicular 

mobility unit uses lithium hydroxide for carbon dioxide removal. An airlock pump, which is a compressor, reduces 

the airlock internal pressure to about ten percent of the cabin pressure, reducing gas losses during airlock operations. 

Hardware to generate oxygen specifically for extravehicular activities, oxygen recharge compressor assembly, 18 is 

also included. Additionally, carbon dioxide from the extravehicular mobility unit is dumped to dedicated hardware 

following an extravehicular activity, and the airlock provides a dedicated carbon dioxide removal assembly to 

support activities within the airlock. Atmospheric gas and water losses are actually included as part of the air and 

water subsystems in this calculation, and not as part of the values presented for extravehicular activity support. 

2.4.7.1.8 Human Accommodations 

Clothing is launched from Earth with the Surface Habitat Lander and stays with the vehicle at the end of 

the surface phase. When clothing is deemed too dirty to wear, it is stowed with the other dirty clothing and replaced 

with a clean garment from stores. A usage rate of 0.486 kg/CM-d, in a volume of 0.00285 m3/CM-d, is assumed. 

 

18 The oxygen recharge compressor assembly (ORCA) is an ISS technology for compressing oxygen to serve extravehicular 

mobility units. 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 February 2006 

39 

2.4.7.2 ADVANCED LIFE SUPPORT TECHNOLOGY

The advanced life support suite differs significantly from the baseline approach above. Cryogenic gas 

storage, vapor phase catalytic ammonia removal, and an ambient food system are less massive than similar baseline 

technologies, while Sabatier, lyophilization, and an aqueous laundry help to close various life support commodity 

loops within the vehicle. As above, the salad machine is retained in the advanced suite. The applied cooling-mass 

penalty reflects lightweight radiators constructed from composite materials. See Figure 2.4.14. See Section 8 for a 

list of acronyms used in this figure. 

2.4.7.2.1 Air 

The advanced air suite within the Surface Habitat Lander, compared to the baseline suite detailed in 

Section 2.4.7.1.1, adds a Sabatier carbon dioxide reduction assembly with a gas stream compressor and stores 

pressurization gases as cryogens. Adequate water is available to avoid a supply penalty for any necessary oxygen 

and hydrogen. Specifically, Sabatier reduces carbon dioxide according to the availability of hydrogen from the 

oxygen generation assembly. Any carbon dioxide that is not reduced is vented to space. Other aspects of the 

advanced air suite are identical to the baseline technology suite for air listed in Section 2.4.7.1.1. 

2.4.7.2.2 Biomass 

The biomass subsystem here is identical to the baseline suite in Section 2.4.7.1.2. 

2.4.7.2.3 Food 

Food is provided as individual, ambient storage, prepackaged entrees in the advanced food suite. The diet 

is supplemented with fresh salad, snacks, and steamed entrees from a biomass production chamber. The nominal 

crew metabolic energy requirement for intravehicular activities only is 11.82 MJ/CM-d. Heavier workloads, such as 

those associated with extravehicular activities, generally require greater food intake. For this mission, the crew 

nominally receives 1.138 kg/CM-d of food. Neglecting the dry component, the food mass as-shipped is 

0.463 kg/CM-d with 0.262 kg/CM-d of disposable packaging. The corresponding specialized food storage structure 

adds an additional 0.860 kg/CM-d. Supporting technology includes some food preparation equipment. 

2.4.7.2.4 Thermal 

The advanced suite for the thermal subsystem uses the same technologies as the baseline suite for the 

thermal subsystem described in Section 2.4.7.1.4. 

2.4.7.2.5 Waste 

The advanced suite for waste uses lyophilization to recover moisture from waste. Reclaimed water is 

returned to the water subsystem as grey water. 

2.4.7.2.6 Water 

The advanced water system is built around a vapor phase catalytic ammonia removal assembly to provide 

primary water processing of both urine and grey water. A dedicated lyophilization processor reclaims water from 

the primary processor brine, allowing almost complete water recovery. Product water from the lyophilization 

processor passes to the primary processor. Product water from the vapor phase catalytic ammonia removal assembly 

requires no further polishing, though a process control water quality monitor provides water quality assurance. 

2.4.7.2.7 Extravehicular Activity Support 

The advanced suite for extravehicular activity support is identical to the baseline suite for extravehicular 

activity support. See Section 2.4.7.1.7. 

2.4.7.2.8 Human Accommodations 

The advanced life support system assumes an aqueous laundry. This will significantly increase the daily 

grey water load, but reduce the required mass of clothing compared to the baseline approach. While the actual 

clothing usage rate remains unchanged, the laundry system cleans soiled clothing for reuse, prolonging clothing life 

and reducing associated waste loads. 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 

40 

Figure 2.4.13 Surface Habitat Lander using Baseline Technologies. 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 

41 

T

 HUMAN ACCOMMODATIONS EVA SUPPORT AIR .

Air

Air

Grey Water

Potable Water

Food

O2

EMU Solid Waste

H2O

Grey Water

H2O

Detergent

Clothing

Food 

Preparatio

Food 

Waste

/ Trash Food

Food Waste

to 

O2 from 

Cabin

Air

Heat

H2O

AAA

Tank

Cond. 

Potable Water

Potable Water

Spent H2O

Drink H

2

O

EMU Cooling H

2

O

EMU

Compressor / 

Accumulator

Sabatier

CO

2

CH

4 to Vent

O2 / N2

Regulator

OGA Crew Cabin

Cryogenic 

O2 / N2

Storage

CO2

CO2

H2 O2

FDS

O2 / N2

4BMS

H

2

O

H2O

Tank

Cond. 

Nutrient 

Solution 

Tank

H2O

Potable Water Inedible Biomass

Food Waste

CO2

CCAA

TCCS 

pH 

adjusted 

Nutrients

Urine

HEPA MCA

 WASTE .

Solid Waste 

Storage

Lyophilizer

Urinal

Feces

Commode

WATER .

Potable 

H2O 

Product 

Tank

W W 

VPCAR

Tank Grey Water

MCV

Clean? No

Yes

O2 Generation

CO2 Removal

 (LiOH)

O2

CO2

TCS Workin

Lyophilizer

H2O

Brine Solids

Urine

Grey Water

Air

Air

H2

Nutrient

Solution

Brine

+ H2O

Laundry Hygiene

A/L Air Save Pump

Lost A/L Air

from A/L to Cabin

A/L CO2

Removal

Expended Clothing to Trash

Figure 2.4.14 Surface Habitat Lander using Advanced Technologies. 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 February 2006 

42 

2.4.8 MISSION PARAMETERS

The most significant overall mission parameters, based on Stafford, et al. (2001), Hanford (2005), and 

Hanford (2004a), are provided in Table 2.4.1. Specifically, these values quantify the mission segment duration, 

crew cabin volume, number of pressurized modules, and additional thermal loads aside from those associated with 

the life support system. For example, such loads may represent avionics, experiments, or other functions not 

associated with life support. For these calculations, sixty percent of the thermal loads are removed from the crew 

cabin via the condensing heat exchanger, with coldplates removing the other forty percent. 

Table 2.4.1 Advanced Mission Parameters 

Mission 

Number of 

Pressurized 

Modules 

Total Crew 

Cabin 

Volume 

[m3] 

Additional 

Thermal 

Loads 

[kWth] 

Mission or 

Segment 

Duration 

[d] 

Orbiting Research Facility: 

International Space Station Update Mission 6 1,330 121.0 3,650 

Near-Term Exploration Mission: 118 

Crew Exploration Vehicle 1 22.0 1.0 14 

Lunar Surface Access Module 1 21.5 1.0 6 

Destination Surface System 1 39.6 1.0 98 

Independent Exploration Mission: ~960 19

Mars Transit Vehicle 2 110 5.5 360 

Mars Descent / Ascent Lander 1 25.5 1.0 30 

Surface Habitat Lander 2 110 8.5 600 

Specific input values for each parameter of the ALSSAT menus are listed in Table 2.4.2. ALSSAT entries 

that are not listed here are zero or are not used to compute the current Metric values. 

 

19 The duration of the total surface element is 600 days and the Surface Habitat Lander is sized for the full mission. In reality, 

the crew will probably spend a few days in the Mars Descent / Ascent Lander both just after landing and just before liftoff. 

The total duration for this vehicle is 30 days. 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 

43 

Table 2.4.2 Specific Input Values for Metric Mission Parameters in the Advanced Life Support Sizing Analysis Tool (ALSSA

Parameter Units 

International 

Space Station 

Upgrade 

Value 

Crew 

Exploration 

Vehicle 

Value 

Lun

Surf

Acc

Mod

Val

Mission Definition 

Number of Crewmembers CM 6 4 4 Manned Mission Duration [d] 3,650 14 6 No. of Dockings Requiring PMA Pressurization per Mission -- 0 0 0 Will contingency considerations be included in this mission? -- No No N

Vehicle Definition Parameters 

Number of Modules modules 6 1 1 Maximum Atmospheric Leakage per Module [kg/d•mod] 2.24 × 10 - 3 2.24 × 10 - 3 2.24 × Total Pressurized Atmospheric Volume [m3] 1,330 22.0 21Total PMA Atmosphere Volume [m3] 0 0 0 

Interior Atmosphere Definition (Manned) 

Nominal Total Atmosphere Pressure [kPa] 101.3 65.5 65Nominal Atmosphere Oxygen Partial Pressure [kPa] 21.3 19.7 19Nominal Atmosphere Water Vapor Partial Pressure [kPa] 1.2 0.7759 0Nominal Atmosphere Carbon Dioxide Partial Pressure [kPa] 0.4 0.4 0

Nominal Crew Inputs 

Oral Hygiene Water [kg/CM-d] 0.363 0.5 0Hand / Face Wash Water [kg/CM-d] 4.082 1.5 1Urinal Flush Water [kg/CM-d] 0.494 0.494 0Laundry Water 20 [kg/CM-d] 12.474 0 0 Water Supplied by Fuel Cells [kg/d] 0 0 0 Shower Water [kg/CM-d] 0 0 0 Dishwashing Water [kg/CM-d] 0 0 0 Drinking Water [kg/CM-d] 2.000 3.5 3EHS Sample Water 21 [kg/d] 1.272 22 0 0 

20 When a laundry is part of the life support system. Otherwise this value is zero. 21 This represents water to payloads that is not recovered. 22 This is equivalent to 0.212 kg/CM-d. 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 

44 

Table 2.4.2 Specific Input Values for Metric Mission Parameters in the Advanced Life Support Sizing Analysis Tool (ALSSA

Parameter Units 

International 

Space Station 

Upgrade 

Value 

Crew 

Exploration 

Vehicle 

Value 

Lun

Surf

Acc

Mod

Val

Thermal Control System, Vehicle Characteristics 

Characteristic Vehicle Length [m] 51 1.70 2Characteristic Vehicle Radius [m] 2.2 2.50 1

Thermal Control System, Internal Thermal Control System Fluid Loop 

ITCS Inlet Temperature [K] 275.00 275.00 275ITCS Outlet Temperature [K] 308.15 308.15 308ITCS Working Fluid -- Water Water WaAvionics from Cold Plates 23 [kWth] 48.4 0.4 0Avionics from Heat Exchanger (HX) 23 [kWth] 72.6 0.6 0Percentage from Cold Plates as a fraction 0.4 0.4 0

Thermal Control System, ITCS Loop Characteristics 

ITCS Pump Efficiency (eta) dimensionless 0.45 0.45 0ITCS Line Diameter (Outside Diameter) [m] 0.0635 0.009525 0.ITCS Effective Line Length Multiplier dimensionless 10 10 10 

Thermal Control System, Physical Constants 

Maximum Insolation [kWth/m2] 1.414 1.414 1Solar Incident Angle [degrees] 90 90 30 Albedo dimensionless 0 0 0View Factor of Ground dimensionless 0 0 0Additional Service [m] 2.0 2.0 2Liquid Tankage Mass Penalty as a fraction 0.10 0.10 0Factor for Valves and Fittings in TCS Lines as a fraction 0.15 0.15 0Accumulator Volume Factor as a fraction 0.30 0.30 0Phase Change Material Container Mass as a fraction 0 1.00 1Volume Factor for Re-Entry Containment as a fraction 0 0.25 0Percentage of Re-Entry for Aero-Brake as a fraction 0 0.75 0Percentage of FES Ducting Assumed as a fraction 0 1.00 1

23 The avionics heat load here represents all other vehicle hardware besides life support hardware. 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 

45 

Table 2.4.2 Specific Input Values for Metric Mission Parameters in the Advanced Life Support Sizing Analysis Tool (ALSSA

Parameter Units 

International 

Space Station 

ISS 

Upgrade 

Value 

Crew 

Exploration 

Vehicle 

Value 

Lun

Surf

Acc

Mod

Val

External Interfaces, EVA Support 

Will oxygen required by EVA be generated? -- n/a n/a NTotal Number of EVAs per Day [sorties/d] 0 0 2 Total Number of EVAs per Mission [sorties] 0 0 4 EVA Duration [h] 0 0 8 Crewmembers per EVA [CM/sortie] 0 0 2 Airlock Volume [m3] 0 0 4Airlock Free Gas Volume [m3] 0 0 3Airlock Gas Losses per Cycle [%] 0 0 10 Oxygen Consumption [kg/CM-h] 0 0 0Nominal EMU Waste Water Recovery [%] 0 0 50 EVA Drinking Water [kg/CM-h] 0 0 0Cooling Water Losses [kg/CM-h] 0 0 0Maximum Absorbency Garment [kg/CM-EVA] 0 0 0Waste Water Absorbed by Maximum Absorbency Garment [kg/CM-EVA] 0 0 0

External Interfaces, Human Accommodations 

Mass of Clothing without a Laundry Facility [kg/CM-d] 0.486 0.486 0Volume of Clothing without a Laundry Facility [m3/CM-d] 2.85 × 10 - 3 2.85 × 10 - 3 2.85 × Mass of Clothing with a Laundry Facility [kg/CM-d] 0.02 n/a n/Volume of Clothing with a Laundry Facility [m3/CM-d] 1.173 × 10 - 4 n/a n/

External Interfaces, Integrated Control 

Please select a sensory control level. dimensionless Low Tech Low Tech Low 

Computational Parameters 

Maximum Allowable Iteration Count dimensionless 1,000 1,000 1,000 Maximum Change at Convergence dimensionless 1.0 × 10 - 5 1.0 × 10 - 5 1.0 × 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 

46 

Table 2.4.2 Specific Input Values for Metric Mission Parameters in the Advanced Life Support Sizing Analysis Tool (ALSSA

Parameter Units 

Mars 

Transit 

Vehicle 

Value 

Mars Descent 

/ Ascent 

Lander 

Value 

Mission Definition 

Number of Crewmembers CM 6 6 Manned Mission Duration [d] 360 30 No. of Dockings Requiring PMA Pressurization per Mission -- 0 0 Will contingency considerations be included in this mission? -- No No 

Vehicle Definition Parameters 

Number of Modules modules 2 1 Maximum Atmospheric Leakage per Module [kg/d•mod] 2.24 × 10 - 3 2.24 × 10 - 3 Total Pressurized Atmospheric Volume [m3] 110 25.5 Total PMA Atmosphere Volume [m3] 0 0 

Interior Atmosphere Definition (Manned) 

Nominal Total Atmosphere Pressure [kPa] 70.3 70.3 Nominal Atmosphere Oxygen Partial Pressure [kPa] 21.3 21.3 Nominal Atmosphere Water Vapor Partial Pressure [kPa] 1.2 1.2 Nominal Atmosphere Carbon Dioxide Partial Pressure [kPa] 0.4 0.4 

Nominal Crew Inputs 

Oral Hygiene Water [kg/CM-d] 0.363 0.363 Hand / Face Wash Water [kg/CM-d] 4.082 4.082 Urinal Flush Water [kg/CM-d] 0.494 0.494 Laundry Water 24 [kg/CM-d] 12.474 0 Water Supplied by Fuel Cells [kg/d] 0 0 Shower Water [kg/CM-d] 2.722 0 Dishwashing Water [kg/CM-d] 0 0 Drinking Water [kg/CM-d] 2.000 2.000 EHS Sample Water 25 [kg/d] 0 0 

24 When a laundry is part of the life support system. Otherwise this value is zero. 25 This represents water to payloads that is not recovered. 
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Table 2.4.2 Specific Input Values for Metric Mission Parameters in the Advanced Life Support Sizing Analysis Tool (ALSSA

Parameter Units 

Mars 

Transit 

Vehicle 

Value 

Mars Descent 

/ Ascent 

Lander 

Value 

Thermal Control System, Vehicle Characteristics 

Characteristic Vehicle Length [m] 5.6 3.61 Characteristic Vehicle Radius [m] 2.5 1.5 

Thermal Control System, Internal Thermal Control System Fluid Loop 

ITCS Inlet Temperature [K] 275.00 275.00 ITCS Outlet Temperature [K] 308.15 308.15 ITCS Working Fluid -- Water Water Avionics from Cold Plates 26 [kWth] 2.2 0.4 Avionics from Heat Exchanger (HX) 26 [kWth] 3.3 0.6 Percentage from Cold Plates as a fraction 0.4 0.4 

Thermal Control System, ITCS Loop Characteristics 

ITCS Pump Efficiency (eta) dimensionless 0.45 0.45 ITCS Line Diameter (Outside Diameter) [m] 0.0127 0.009525 ITCS Effective Line Length Multiplier dimensionless 10 10 

Thermal Control System, Physical Constants 

Maximum Insolation [kWth/m2] 1.414 1.414 Solar Incident Angle [degrees] 90 30 Albedo dimensionless 0 0.1 View Factor of Ground dimensionless 0 0.5 Additional Service [m] 2.0 2.0 Liquid Tankage Mass Penalty as a fraction 0.10 0.10 Factor for Valves and Fittings in TCS Lines as a fraction 0.15 0.15 Accumulator Volume Factor as a fraction 0.30 0.30 Phase Change Material Container Mass as a fraction 1.00 1.00 Volume Factor for Re-Entry Containment as a fraction 0.25 0.25 Percentage of Re-Entry for Aero-Brake as a fraction 0.75 0.75 Percentage of FES Ducting Assumed as a fraction 1.00 1.00 

26 The avionics heat load here represents all other vehicle hardware besides life support hardware. 
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Table 2.4.2 Specific Input Values for Metric Mission Parameters in the Advanced Life Support Sizing Analysis Tool (ALSSA

Parameter Units 

Mars 

Transit 

Vehicle 

Value 

Mars Descent 

/ Ascent 

Lander 

Value 

External Interfaces, EVA Support 

Will oxygen required by EVA be generated? -- n/a No Total Number of EVAs per Day [sorties/d] 0 1 Total Number of EVAs per Mission [sorties] 0 1 EVA Duration [h] 0 4 Crewmembers per EVA [CM/sortie] 0 6 Airlock Volume [m3] 0 25.5 Airlock Free Gas Volume [m3] 0 23.75 Airlock Gas Losses per Cycle [%] 0 100 Oxygen Consumption [kg/CM-h] 0 0.15 Nominal EMU Waste Water Recovery [%] 0 50 EVA Drinking Water [kg/CM-h] 0 0.24 Cooling Water Losses [kg/CM-h] 0 0.19 Maximum Absorbency Garment [kg/CM-EVA] 0 0.173 Waste Water Absorbed by Maximum Absorbency Garment [kg/CM-EVA] 0 0.55 

External Interfaces, Human Accommodations 

Mass of Clothing without a Laundry Facility [kg/CM-d] 0.486 0.486 Volume of Clothing without a Laundry Facility [m3/CM-d] 2.85 × 10 - 3 2.85 × 10 - 3 Mass of Clothing with a Laundry Facility [kg/CM-d] 0.03 n/a Volume of Clothing with a Laundry Facility [m3/CM-d] 1.759 × 10 - 4 n/a 

External Interfaces, Integrated Control 

Please select a sensory control level. dimensionless Low Tech Low Tech 

Computational Parameters 

Maximum Allowable Iteration Count dimensionless 1,000 1,000 Maximum Change at Convergence dimensionless 1.0 × 10 - 5 1.0 × 10 - 5 
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49 

2.4.9 INFRASTRUCTURE COSTS/EQUIVALENCIES

Infrastructure equivalencies, from Hanford (2005) and Hanford (2004a), are assumed as shown in 

Table 2.4.3 for each mission vehicle. The corresponding infrastructure technologies are noted above with each 

mission. With regard to both volume, which accounts for vehicle structure, and power, which represents power 

generation, both the baseline and advanced technology suites use the same infrastructure equivalencies. 

Table 2.4.3 Advanced Mission Cost Equivalencies 

Mission 

Volume 

[kg/m3] 

Power 

[kg/kWe] 

Cooling 27

[kg/kWth] 

Orbiting Research Facility: 

International Space Station Update Mission 66.7 476.0 323.9 

Near-Term Exploration Mission: 

Crew Exploration Vehicle 131.9 341.5 19.4 

Lunar Surface Access Module 49.6 179.6 56.0 

Destination Surface System 100.0 226.0 53.6 

Independent Exploration Mission: 

Mars Transit Vehicle 9.16 237.0 40.0/ 

30.0 

Mars Descent / Ascent Lander 66.7 228.0 145.0/ 

121.0 

Surface Habitat Lander 9.16 87.0 145.0/ 

121.0 

For cooling, two equivalencies appear in Table 2.4.3 for each vehicle within the Independent Exploration 

Mission. The first cooling equivalency simulates current cooling technology using aluminum, flow-through 

radiators. This first equivalency is applied to assessments using the baseline technology suite. The second cooling 

equivalency represents advanced radiators that are under development for life-support thermal loads. This second 

equivalency is applied to assessments using the advanced technology suite. All cooling equivalencies here are listed 

in Hanford (2004a). Note that the differences between the cooling infrastructure values reflect only changes in 

thermal hardware material, and not changes in overall thermal management architecture. 

For the International Space Station Update Mission, the same cooling equivalency, based upon current ISS 

cooling technology and architecture, is used for estimates employing both life support system technology suites. 

This approach is equivalent to assuming that ISS cooling technology is unlikely to change regardless of which 

technologies supply life support functions within ISS. 

 

27 When two infrastructure equivalencies are listed for cooling, the first assumes current technology using aluminum, flowthrough radiators, while the second assumes advanced technologies with some form of lightweight radiators. 
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3 ADVANCED LIFE SUPPORT 

RESEARCH AND TECHNOLOGY DEVELOPMENT METRIC

3.1 SUBSYSTEM TECHNOLOGY DATA

The tables below list overall subsystem attributes for the various vehicles and missions considered in this 

Metric computation. Except as noted above, these classifications are consistent with advanced terminology as 

presented within Hanford (2004a) and Stafford, et al. (2001). See Section 6 for assessments at the assembly-level. 

Table 3.1.1 Orbiting Research Facility: International Space Station Upgrade Mission 

using Baseline Technologies 

Subsystem / Interface 

Mass 

[kg] 

Volume

[m3] 

Power 

[kWe] 

Cooling

[kWth] 

Crewtime 

[CM-h] 

ESM 

[kg] 

Air 33,085 34.97 4.399 2.815 129.58 38,517 

Biomass 0 0.00 0.000 0.000 0.00 0 

Food 31,304 129.74 4.272 4.272 0.00 43,375 

Thermal 763 2.70 0.769 0.769 20.28 1,573 

Waste 3,917 107.93 0.014 0.014 0.00 11,127 

Water 25,677 13.82 1.322 1.322 0.00 27,657 

Extravehicular Activity Support 0 0.00 0.000 0.000 0.00 0 

Human Accommodations 22,799 79.59 0.000 0.000 0.00 28,107 

Totals 117,545 368.75 10.776 9.192 149.86 

The total life support system ESM for the International Space Station Upgrade Mission using baseline technologies, 

rounded to the nearest 10 kg, is 150,360 kg. The computed crewtime-mass penalty for this assessment is 

0.724 kg/CM-h. 

Table 3.1.2 Orbiting Research Facility: International Space Station Upgrade Mission 

using Advanced Technologies 

Subsystem / Interface 

Mass 

[kg] 

Volume

[m3] 

Power 

[kWe] 

Cooling

[kWth] 

Crewtime 

[CM-h] 

ESM 

[kg] 

Air 10,420 14.04 4.556 2.974 129.58 14,531 

Biomass 0 0.00 0.000 0.000 0.00 0 

Food 23,593 105.79 0.960 0.960 0.00 31,417 

Thermal 750 2.68 0.769 0.769 20.28 1,551 

Waste 1,467 22.04 0.947 0.909 5,475.00 5,505 

Water 1,483 2.07 2.143 2.143 0.00 3,335 

Extravehicular Activity Support 0 0.00 0.000 0.000 0.00 0 

Human Accommodations 12,727 20.00 0.633 0.633 0.00 14,567 

Totals 50,439 166.62 10.008 8.388 5,624.86 

The total life support system ESM for the International Space Station Upgrade Mission using advanced 

technologies, rounded to the nearest 10 kg, is 70,910 kg. The computed crewtime-mass penalty for this assessment 

is 0.333 kg/CM-h. 
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51 

Table 3.1.3 Near-Term Exploration Mission: Crew Exploration Vehicle using Baseline Technologies

Subsystem / Interface 

Mass 

[kg] 

Volume

[m3] 

Power 

[kWe] 

Cooling

[kWth] 

Crewtime 

[CM-h] 

ESM 

[kg] 

Air 681 1.29 0.317 0.317 0.00 966 

Biomass 0 0.00 0.000 0.000 0.00 0 

Food 97 0.37 0.960 0.960 0.00 492 

Thermal 268 0.86 0.772 0.772 0.08 661 

Waste 46 0.39 0.014 0.014 0.00 102 

Water 1,168 0.90 0.042 0.026 0.00 1,301 

Extravehicular Activity Support 0 0.00 0.000 0.000 0.00 0 

Human Accommodations 59 0.21 0.000 0.000 0.00 86 

Totals 2,318 4.02 2.105 2.089 0.08 

The total life support system ESM for the Crew Exploration Vehicle in the Near-Term Exploration Mission using 

baseline technologies, rounded to the nearest 10 kg, is 3,610 kg. The computed crewtime-mass penalty for this 

assessment is 7.42 kg/CM-h. 

Table 3.1.4 Near-Term Exploration Mission: Crew Exploration Vehicle using Advanced Technologies 

Subsystem / Interface 

Mass 

[kg] 

Volume

[m3] 

Power 

[kWe] 

Cooling

[kWth] 

Crewtime 

[CM-h] 

ESM 

[kg] 

Air 429 1.01 0.336 0.336 0.00 638 

Biomass 0 0.00 0.000 0.000 0.00 0 

Food 84 0.36 0.960 0.960 0.00 478 

Thermal 271 0.87 0.774 0.774 0.08 666 

Waste 46 0.39 0.014 0.014 0.00 102 

Water 449 2.22 0.433 0.433 0.00 898 

Extravehicular Activity Support 0 0.00 0.000 0.000 0.00 0 

Human Accommodations 59 0.21 0.000 0.000 0.00 86 

Totals 1,337 5.06 2.517 2.517 0.08 

The total life support system ESM for the Crew Exploration Vehicle in the Near-Term Exploration Mission using 

advanced technologies, rounded to the nearest 10 kg, is 2,910 kg. The computed crewtime-mass penalty for this 

assessment is 6.09 kg/CM-h. 
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Table 3.1.5 Near-Term Exploration Mission: Lunar Surface Access Module using Baseline Technologies 

Subsystem / Interface 

Mass 

[kg] 

Volume

[m3] 

Power 

[kWe] 

Cooling

[kWth] 

Crewtime 

[CM-h] 

ESM 

[kg] 

Air 519 1.04 0.317 0.317 0.00 645 

Biomass 0 0.00 0.000 0.000 0.00 0 

Food 64 0.23 0.960 0.960 0.00 302 

Thermal 268 0.86 0.771 0.771 0.03 493 

Waste 41 0.25 0.014 0.014 0.00 56 

Water 608 0.44 0.028 0.019 0.00 636 

Extravehicular Activity Support 98 0.41 1.000 1.000 0.00 354 

Human Accommodations 25 0.09 0.000 0.000 0.00 30 

Totals 1,623 3.32 3.090 3.081 0.03 

The total life support system ESM for the Lunar Surface Access Module in the Near-Term Exploration Mission 

using baseline technologies, rounded to the nearest 10 kg, is 2,520 kg. The computed crewtime-mass penalty for 

this assessment is 10.66 kg/CM-h. 

Table 3.1.6 Near-Term Exploration Mission: Lunar Surface Access Module using Advanced Technologies 

Subsystem / Interface 

Mass 

[kg] 

Volume

[m3] 

Power 

[kWe] 

Cooling

[kWth] 

Crewtime 

[CM-h] 

ESM 

[kg] 

Air 346 0.84 0.345 0.345 0.00 469 

Biomass 0 0.00 0.000 0.000 0.00 0 

Food 58 0.21 0.960 0.960 0.00 294 

Thermal 271 0.87 0.773 0.773 0.03 496 

Waste 41 0.25 0.014 0.014 0.00 56 

Water 408 2.23 0.437 0.437 0.00 621 

Extravehicular Activity Support 98 0.41 1.000 1.000 0.00 354 

Human Accommodations 25 0.09 0.000 0.000 0.00 30 

Totals 1,247 4.90 3.529 3.529 0.03 

The total life support system ESM for the Lunar Surface Access Module in the Near-Term Exploration Mission 

using advanced technologies, rounded to the nearest 10 kg, is 2,320 kg. The computed crewtime-mass penalty for 

this assessment is 9.84 kg/CM-h. 
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Table 3.1.7 Near-Term Exploration Mission: Destination Surface System using Baseline Technologies 

Subsystem / Interface 

Mass 

[kg] 

Volume

[m3] 

Power 

[kWe] 

Cooling

[kWth] 

Crewtime 

[CM-h] 

ESM 

[kg] 

Air 3,185 3.68 1.108 1.108 0.76 3,864 

Biomass 0 0.00 0.000 0.000 0.00 0 

Food 460 2.00 0.960 0.960 0.00 928 

Thermal 279 0.88 0.783 0.783 0.54 586 

Waste 115 2.31 0.014 0.014 0.00 350 

Water 883 2.50 0.833 0.833 0.00 1,366 

Extravehicular Activity Support 235 0.73 1.000 1.000 0.00 588 

Human Accommodations 408 1.43 0.000 0.000 0.00 551 

Totals 5,564 13.53 4.698 4.698 1.30 

The total life support system ESM for the Destination Surface System in the Near-Term Exploration Mission using 

baseline technologies, rounded to the nearest 10 kg, is 8,230 kg. The computed crewtime-mass penalty for this 

assessment is 2.14 kg/CM-h. 

Table 3.1.8 Near-Term Exploration Mission: Destination Surface System using Advanced Technologies 

Subsystem / Interface 

Mass 

[kg] 

Volume

[m3] 

Power 

[kWe] 

Cooling

[kWth] 

Crewtime 

[CM-h] 

ESM 

[kg] 

Air 1,258 1.53 1.129 1.129 0.76 1,728 

Biomass 0 0.00 0.000 0.000 0.00 0 

Food 367 1.88 0.960 0.960 0.00 823 

Thermal 282 0.89 0.789 0.789 0.54 593 

Waste 110 2.17 0.014 0.014 0.00 331 

Water 649 1.30 1.428 1.428 0.00 1,178 

Extravehicular Activity Support 235 0.73 1.000 1.000 0.00 588 

Human Accommodations 408 1.43 0.000 0.000 0.00 551 

Totals 3,309 9.93 5.321 5.321 1.30 

The total life support system ESM for the Destination Surface System in the Near-Term Exploration Mission using 

advanced technologies, rounded to the nearest 10 kg, is 5,790 kg. The computed crewtime-mass penalty for this 

assessment is 1.50 kg/CM-h.
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54 

Table 3.1.9 Independent Exploration Mission: Mars Transit Vehicle using Baseline Technologies

Subsystem / Interface 

Mass 

[kg] 

Volume

[m3] 

Power 

[kWe] 

Cooling

[kWth] 

Crewtime 

[CM-h] 

ESM 

[kg] 

Air 2,190 3.32 4.199 2.710 12.78 3,334 

Biomass 761 17.03 6.099 6.099 0.00 2,607 

Food 2,840 13.12 1.860 1.860 0.00 3,475 

Thermal 329 1.00 0.888 0.888 2.00 586 

Waste 382 9.73 0.014 0.014 0.00 475 

Water 3,353 5.50 1.127 1.127 0.00 3,715 

Extravehicular Activity Support 0 0.00 0.000 0.000 0.00 0 

Human Accommodations 1,763 6.87 0.000 0.000 0.00 1,826 

Totals 11,617 56.57 14.187 12.698 14.78 

The total life support system ESM for the Mars Transit Vehicle in the Independent Exploration Mission using 

baseline technologies, rounded to the nearest 10 kg, is 16,020 kg. The computed crewtime-mass penalty for this 

assessment is 0.728 kg/CM-h. 

Table 3.1.10 Independent Exploration Mission: Mars Transit Vehicle using Advanced Technologies 

Subsystem / Interface 

Mass 

[kg] 

Volume

[m3] 

Power 

[kWe] 

Cooling

[kWth] 

Crewtime 

[CM-h] 

ESM 

[kg] 

Air 1,367 2.94 4.350 2.863 12.78 2,518 

Biomass 761 17.03 6.099 6.099 0.00 2,546 

Food 2,343 10.45 0.960 0.960 0.00 2,695 

Thermal 336 1.01 0.914 0.914 2.00 591 

Waste 254 6.19 0.014 0.014 0.00 315 

Water 1,011 2.92 3.048 3.048 180.00 1,953 

Extravehicular Activity Support 0 0.00 0.000 0.000 0.00 0 

Human Accommodations 863 1.35 0.633 0.633 0.00 1,044 

Totals 6,935 41.89 16.019 14.532 194.78 

The total life support system ESM for the Mars Transit Vehicle in the Independent Exploration Mission using 

advanced technologies, rounded to the nearest 10 kg, is 11,660 kg. The computed crewtime-mass penalty for this 

assessment is 0.565 kg/CM-h. 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 February 2006 

55 

Table 3.1.11 Independent Exploration Mission: Mars Descent / Ascent Lander using Baseline Technologies 

Subsystem / Interface 

Mass 

[kg] 

Volume

[m3] 

Power 

[kWe] 

Cooling

[kWth] 

Crewtime 

[CM-h] 

ESM 

[kg] 

Air 1,071 2.16 4.251 2.742 1.07 2,586 

Biomass 0 0.00 0.000 0.000 0.00 0 

Food 620 3.37 2.128 2.128 0.00 1,638 

Thermal 296 0.92 0.822 0.822 0.17 665 

Waste 69 1.02 0.014 0.014 0.00 142 

Water 737 2.88 0.896 0.896 0.00 1,263 

Extravehicular Activity Support 22 0.25 0.000 0.000 0.00 38 

Human Accommodations 188 0.65 0.000 0.000 0.00 231 

Totals 3,001 11.25 8.111 6.602 1.24 

The total life support system ESM for the Mars Descent / Ascent Lander in the Independent Exploration Mission 

using baseline technologies, rounded to the nearest 10 kg, is 6,560 kg. The computed crewtime-mass penalty for 

this assessment is 3.71 kg/CM-h. 

Table 3.1.12 Independent Exploration Mission: Mars Descent / Ascent Lander 

using Advanced Technologies 

Subsystem / Interface 

Mass 

[kg] 

Volume

[m3] 

Power 

[kWe] 

Cooling

[kWth] 

Crewtime 

[CM-h] 

ESM 

[kg] 

Air 670 0.96 0.489 0.489 0.01 904 

Biomass 0 0.00 0.000 0.000 0.00 0 

Food 189 0.92 0.960 0.960 0.00 585 

Thermal 280 0.89 0.784 0.784 0.17 613 

Waste 67 0.99 0.014 0.014 0.00 138 

Water 445 1.30 1.548 1.548 0.00 1,072 

Extravehicular Activity Support 22 0.25 0.000 0.000 0.00 38 

Human Accommodations 188 0.65 0.000 0.000 0.00 231 

Totals 1,860 5.96 3.795 3.795 0.18 

The total life support system ESM for the Mars Descent / Ascent Lander in the Independent Exploration Mission 

using advanced technologies, rounded to the nearest 10 kg, is 3,580 kg. The computed crewtime-mass penalty for 

this assessment is 2.03 kg/CM-h. 
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56 

Table 3.1.13 Independent Exploration Mission: Surface Habitat Lander using Baseline Technologies 

Subsystem / Interface 

Mass 

[kg] 

Volume

[m3] 

Power 

[kWe] 

Cooling

[kWth] 

Crewtime 

[CM-h] 

ESM 

[kg] 

Air 4,195 5.52 5.847 3.732 21.30 5,315 

Biomass 898 17.03 6.099 6.099 0.00 2,469 

Food 7,580 38.39 4.272 4.272 0.00 8,923 

Thermal 382 1.17 1.032 1.032 3.33 636 

Waste 668 17.66 0.014 0.014 0.00 833 

Water 10,380 9.82 1.285 1.285 0.00 10,768 

Extravehicular Activity Support 1,292 2.91 2.500 2.500 0.00 1,899 

Human Accommodations 2,938 11.45 0.000 0.000 0.00 3,043 

Totals 28,333 103.95 21.048 18.934 24.63 

The total life support system ESM for the Surface Habitat Lander in the Independent Exploration Mission using 

baseline technologies, rounded to the nearest 10 kg, is 33,890 kg. The computed crewtime-mass penalty for this 

assessment is 0.957 kg/CM-h. 

Table 3.1.14 Independent Exploration Mission: Surface Habitat Lander using Advanced Technologies 

Subsystem / Interface 

Mass 

[kg] 

Volume

[m3] 

Power 

[kWe] 

Cooling

[kWth] 

Crewtime 

[CM-h] 

ESM 

[kg] 

Air 2,198 4.17 6.016 3.903 21.30 3,242 

Biomass 898 17.03 6.099 6.099 0.00 2,323 

Food 3,881 17.35 0.960 0.960 0.00 4,239 

Thermal 376 1.16 0.999 0.999 3.33 596 

Waste 392 6.69 0.353 0.353 360.00 694 

Water 1,533 3.32 3.104 3.104 300.00 2,348 

Extravehicular Activity Support 1,292 2.91 2.500 2.500 0.00 1,839 

Human Accommodations 1,349 1.87 0.633 0.633 0.00 1,498 

Totals 11,919 54.50 20.664 18.552 684.63 

The total life support system ESM for the Surface Habitat Lander in the Independent Exploration Mission using 

advanced technologies, rounded to the nearest 10 kg, is 16,780 kg. The computed crewtime-mass penalty for this 

assessment is 0.465 kg/CM-h.
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57 

3.2 ADVANCED LIFE SUPPORT RESEARCH AND TECHNOLOGY DEVELOPMENT METRIC

3.2.1 METRIC VALUES

Metric values were calculated for each of the mission vehicles described above. The ESM for each mission 

segment was estimated separately by applying the appropriate equivalencies or cost factors. The mission segment 

ESM values were summed to derive a total vehicle ESM. The vehicle ESM values were also summed to provide an 

overall mission ESM. Metrics were calculated for each vehicle and mission by dividing the ESM for the life support 

system using baseline technologies by the corresponding ESM for the life support system using advanced 

technologies. Different extravehicular activity models were used for the various vehicles, as applicable. The results 

are tabulated in Table 3.2.1. 

As noted earlier, the International Space Station mission employs a single vehicle here, thus the mission 

and the vehicle are equivalent. The Lunar Reference Mission and the Mars Independent Exploration mission each 

use three different vehicles to place a single crew on Luna or Mars and return that crew safely to Earth. The overall 

mission ESM and Metric are listed on the first line for these latter two missions, and the individual vehicle ESM and 

Metric values are listed on the lines below. 

Table 3.2.1 Equivalent System Mass and Metric Values for a Range of Missions and Technologies 

Mission / Vehicle 

Baseline 

Technology 

ESM 

[kg] 

Advanced 

Technology 

ESM 

[kg] 

ALS 

R&TD 

Metric 

Orbiting Research Facility: 

International Space Station Upgrade Mission 150,360 70,910 2.12 

Near-Term Exploration Mission: 14,360 11,020 1.30 

Crew Exploration Vehicle 3,610 2,910 1.24 

Lunar Surface Access Module 2,520 2,320 1.08 

Destination Surface System 8,230 5,790 1.42 

Independent Exploration Mission: 56,470 32,020 1.76 

Mars Transit Vehicle 16,020 11,660 1.37 

Mars Descent / Ascent Lander 6,560 3,580 1.83 

Surface Habitat Lander 33,890 16,780 2.02 

Table 3.2.1 with Figure 3.3.1, Figure 3.3.2, and Figure 3.3.3 summarize calculations supporting the Fiscal 

Year 2005 Advanced Life Support Research and Technology Development Metric. Figure 3.3.1 presents the overall 

equivalent masses for both reference missions used for the Fiscal Year 2005 Metric. Figure 3.3.2 presents the 

individual equivalent system masses for the vehicles of the Near-Term Exploration Mission to Luna. Finally, 

Figure 3.3.3 provides equivalent masses for each of the vehicles within the Independent Exploration Mission to 

Mars. 

3.2.2 DISCUSSION

Examination of Figure 3.3.1, which provides a graphical breakdown of equivalent system mass by 

subsystem, reveals that food, air, and water are the most massive systems associated with supporting a human crew. 

The human accommodations external interface, which represents clothing primarily, can be significant for longduration missions such as the Orbiting Research Facility. The advanced configurations reduce most crew-support 

system masses. 

Most trends noted below are likely a strong function of mission duration more than any other variable. 

Thus, in order from shortest to longest in terms of mission duration, the vehicles assessed for the Fiscal Year 2005 

Metric computation are the Lunar Surface Access Module, the Crew Exploration Vehicle, the Mars Descent / Ascent 

Lander, the Destination Surface System, the Mars Transit Vehicle, the Surface Habitat Lander, and the International 

Space Station. 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 February 2006 

58 

The current evaluation, which considered several alternate technology suites available within ALSSAT, 

selected several technologies over the range of vehicles and mission durations. For the air system, oxygen 

generation via electrolysis and carbon dioxide reduction, via Sabatier, were more economical for long-duration 

vehicles such as the International Space Station, the Mars Transit Vehicle, and the Surface Habitat Lander. Shorter 

duration vehicles, such as all elements of the Near-Term Exploration Mission and the Mars Descent / Ascent 

Lander, were more economical with using stored, cryogenic gases in place of generating oxygen by any means. 

Cryogenic gas storage was also more economical for long-duration elements. 

A frozen food diet was heavier in all cases than a shelf-stable, ambient storage food system. More 

surprisingly, a low-moisture Shuttle Training Menu diet was more economical only for the short-duration vehicles 

including all within the Near-Term Exploration Mission and the Mars Descent / Ascent Lander. Assessments for the 

longer-duration vehicles universally selected the “standard moisture” Shuttle Training Menu diet probably to offset 

water losses. Additionally, though not evident in the values here, a salad machine is only reasonable if required by 

mission protocols, because current assessments and hardware are not frugal enough to reduce the life support system 

costs simply based on other benefits of a small biomass production chamber. 

For the waste system, long-duration missions benefit from water recovery, usually via lyophilization. The 

short-duration vehicles, including the Destination Surface System, appear to require nothing more than storage when 

considering the available options within ALSSAT. However, ALSSAT did not provide a “compaction only with 

storage” option which may be more economical than storage alone, especially for vehicles with a mission duration 

greater than something on the order of 10 days. 

Within the water system assessments, vapor phase catalytic ammonia removal was significantly more 

economical for longer-duration mission segments such as the International Space Station, the Surface Habitat 

Lander, the Mars Transit Vehicle, the Destination Surface System, and the Mars Descent / Ascent Lander. 

Assessments of the Crew Exploration Vehicle and the Lunar Surface Access Module selected versions of the 

International Space Station Water Recovery System without urine treatment. 

3.3 METRIC REPORTING RECOMMENDATIONS

3.3.1 METRIC RECOMMENDATION FOR FISCAL YEAR 2005 

It is recommended that the following values of the Advanced Life Support Research and Technology 

Development Metric be reported to the Office of Biological and Physical Research and the Advanced Human 

Support Technology Program for Government Fiscal Year 2005: 

Orbiting Research Facility: 2.12 

Near-Term Exploration Mission: 1.30 

Independent Exploration Mission: 1.76 

3.3.2 COMPARISON WITH PAST ASSESSMENTS

Table 3.3.1 provides recent values of the Advanced Life Support Research and Technology Development 

Metric with associated sources. These values are plotted in Figure 3.3.4. Please note that each annual assessment to 

date, though similar in overall approach, has really been unique in one or more ways when compared to the other 

assessments, so the progressions of values are not directly comparable. 

Table 3.3.1 Previous Advanced Life Support Research and Technology Development Metric Values 

Government Fiscal Year References 

Mission 2001 2002 2003 2004 2005 

Orbiting Research Facility 1.32 (1) 1.53 (2) 1.47 (3) 2.03 (4) 2.12 (5)

Near-Term Exploration Mission 1.30 (5)

Independent Exploration Mission 1.28 (1) 1.37 (2) 1.36 (3) 1.62 (4) 1.76 (5)

(1) Drysdale and 

Hanford (2002) 

(2) Hanford (2003a) 

(3) Hanford (2003b) 

(4) Hanford (2004c) 

(5) This document 

The values in Table 3.3.1 generally increase as a function of time for the first and third reference missions. 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 

59 

Figure 3.3.1 Equivalent system mass summary for the Fiscal Year 2005 ALS Research and Technology Development Metric 

suites. 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 

60 

Figure 3.3.2 Equivalent system mass summary for the components of the Near-Term Exploration Mission. 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 

61 

Figure 3.3.3 Equivalent system mass summary for the components of the Independent Exploration Mission. 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 

62 

1.01.21.41.61.82.02.2

2001 2002 2003 2004 

Government Fiscal Year

ALS Research & Technology Development Metric

Orbiting Research FacilityNear-Term Exploration MissionIndependent Exploration Mission

Figure 3.3.4 Historical progression of Advanced Life Support Research and Technology Development Metric values as a function 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 February 2006 

63 

4 CAUTIONS AND DISCLAIMERS

This type of analysis includes several inescapable sources of variation from actual flight systems. The first 

is that these estimations fail to consider contingency or redundancy in any detail. Further, inclusion of contingency 

or redundancy invariably increases the overall equivalent system mass of all configurations, although this may have 

little significant impact on the overall conclusions and, therefore, the implied direction, above. The second source of 

uncertainty, which is related to the first, is that all calculations above use only single-string life support system 

architecture. Multi-string systems, where each life support processor is sized to handle a larger load should one 

processor fail, are essential to meeting actual flight requirements for safety. Because processor physical attributes 

do not, in general, scale linearly with capacity, two processors in place of one will be more massive, even excluding 

the extra capability to insure redundancy. Again, this impact would apply to all configurations; therefore, it may not 

affect the direction implied above. The third source of uncertainty resides in the preliminary nature of the data 

employed for the advanced equipment. While it is desirable that flight equipment will be more economical than the 

values assumed here, it is possible that real systems may actually be less economical due to unforeseen difficulties 

during development or added components to assure safe operation in the flight environment. Fourthly, as ALS 

research and technology development continues, new technologies and architectural ideas may drastically change 

current doctrine about providing life support, producing profound savings for future human spaceflight. Thus, these 

estimates should be considered preliminary and not definitive, although they provide one measure of where NASA 

and the ALS Project are today. 

5 SPECIAL RECOGNITION OF WORK

The author would like to thank many people, both within and outside of NASA, for their thoughts and input 

into both what is presented above and what has come before. Many metric formulations were considered by a group 

of life support analysts and researchers, and it is due to their excellent input that the Metric now exists in its current 

form. In particular, Dr. A. E. Drysdale of The Boeing Company deserves recognition for developing equivalent 

system mass in its current form for the ALS Project and guiding the Metric in previous years. 

For compiling an archival source detailing the current definition of equivalent system mass, special 

recognition is due J. A. Levri of Ames Research Center. 

For the current work, the author especially recognizes J. Yeh and C. Brown of Hamilton Sundstrand within 

the Engineering and Science Contract Group, Houston, Texas, for their continuing support of the Advanced Life 

Support Sizing Analysis Tool during the computation of the Metric. 

This document is available electronically from the Advanced Life Support Project of the National Aeronautics and 

Space Administration at Lyndon B. Johnson Space Center at: 

http://advlifesupport.jsc.nasa.gov/ 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 February 2006 

64 

6 SUBSYSTEM COMPONENTS IN FISCAL YEAR 2005 ALS R&TD METRIC

This section describes the assembly level for the subsystem summations presented in Section 3.1. The 

values in the tables below, Table 6.1 through Table 6.14, list the assemblies, using the organization and names 

within the Advanced Life Support Sizing Analysis Tool (ALSSAT) for each ALS element. These tables specifically 

detail mass, volume, power, cooling, and crewtime. 

The overall subsystem values are listed on the line following each subsystem entry. These values are 

consistent with those reported in Section 3.1 for each vehicle. Any deviations between these values and those above 

arise from variations when individual numerical values were rounded to prepare each table, and, therefore, the 

resulting minor differences should not concern even a careful reader. Section 3.1 uses the units kWe and kWth for 

power and cooling, respectively, while the nomenclature below uses We and Wth, which is consistent with the native 

units within ALSSAT. 

The assemblies, as specified within ALSSAT, are listed in bold below their respective subsystems. When 

recognizable assembly components are not listed within ALSSAT, a summary of the assembly is provided on the 

same line as the entry for the assembly. Assemblies with one or more recognizable components are further 

described by the indented entries below them. See Yeh, et al. (2002), Yeh, et al. (2003), Yeh, et al. (2004a), Yeh, 

et al. (2004b), Yeh, et al. (2005a), and Yeh, et al. (2005b) for details about ALSSAT organization. Except for the 

dry food mass listed within the Food Processing, Packaging, and Storage within the Food Subsystem, total values 

for assemblies would be the sum of their components. The Dry Food Mass, however, is that portion of the food 

system that was excluded during the computation of the Fiscal Year 2005 ALS R&TD Metric. It is listed here to 

provide a reference, but it is otherwise ignored in the overall totals. When applicable, the technology label from 

ALSSAT is listed in the second column, and the associated abbreviations are listed in Section 8. For more details of 

the technologies assumed for each mission, please see Section 2.4 for descriptions of each subsystem and overall life 

support system schematics. 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 

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Table 6.1 Subsystem Breakdown for Orbiting Research Facility: International Space Station Upgrade Mission using Baselin

Subsystem or Component Technology 

Mass 

[kg] 

Volume 

[m3] 

Power 

[We] 

Cooling 

[Wth] 

C

Air Subsystem 33,084.77 34.97 4,398.74 2,814.93 Atmospheric Control System 

Atmospheric Pressure Control ISS 119.40 0.26 70.50 70.50 

Atmosphere Revitalization System 

Carbon Dioxide Removal 4BMS/ISS 182.17 0.43 546.29 546.29 Carbon Dioxide Reduction None 0.00 0.00 0.00 0.00 Oxygen Generation SPE/ISS 1,549.80 1.03 3,482.62 1,898.81 Gaseous Trace Contaminant Control ISS 327.22 3.94 194.35 194.35 Atmosphere Composition Monitoring Assembly ISS 149.99 0.25 103.50 103.50 Sample Delivery System ISS 35.11 0.04 0.00 0.00 Airlock Carbon Dioxide Removal n/a 0.00 0.00 0.00 0.00 

Gas Storage 

Nitrogen Storage High Pressure 27,390.53 27.16 0.00 0.00 Oxygen Storage High Pressure 3,322.25 1.82 0.00 0.00 

Fire Detection and Suppression 

Fire Detection System ISS 1.50 0.00 1.48 1.48 Fire Suppression System ISS 6.80 0.04 0.00 0.00 

Biomass Subsystem 0.00 0.00 0.00 0.00 Crop Storage n/a 0.00 0.00 0.00 0.00 Plant Growth Chamber / Salad Machine n/a 0.00 0.00 0.00 0.00 Food Subsystem 31,303.68 129.74 4,272.00 4,272.00 Food Processing, Packaging, and Storage 

Food Processing 0.00 0.00 0.00 0.00 Food Packaging 0.00 0.00 0.00 0.00 Food Storage STM + Frozen 46,236.03 129.74 4,272.00 4,272.00 Dry Food Mass (neglected) -14,932.35 0.00 0.00 0.00 

Thermal Subsystem 762.82 2.70 769.15 769.15 Temperature and Humidity Control 

Common Cabin Air Assembly ISS 119.72 0.51 530.52 530.52 Avionics Air Assembly ISS 12.40 0.03 175.00 175.00 Atmosphere Circulation ISS 9.80 0.02 61.00 61.00 Atmospheric Microbial Control ISS 529.53 2.00 0.00 0.00 

Internal Thermal Control System 91.37 0.14 2.63 2.63 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 

66 

Table 6.1 Subsystem Breakdown for Orbiting Research Facility: International Space Station Upgrade Mission using Baselin

Subsystem or Component Technology 

Mass 

[kg] 

Volume 

[m3] 

Power 

[We] 

Cooling 

[Wth] 

C

Waste Subsystem 3,917.04 107.93 14.00 14.00 Solid Waste Collection ESDM 36.36 0.13 14.00 14.00 Solid Waste Processing System 

Solid Waste Treatment Storage 3,880.68 107.80 0.00 0.00 Solid Waste Processing System Tankage 0.00 0.00 0.00 0.00 Microbial Check Valve 0.00 0.00 0.00 0.00 Process Controller 0.00 0.00 0.00 0.00 Solid Product Quality Monitoring 0.00 0.00 0.00 0.00 Solid Product Delivery System 0.00 0.00 0.00 0.00 

Water Subsystem 25,677.42 13.82 1,322.21 1,322.21 Urine / Waste Water Collection System ISS 41.11 0.02 4.00 4.00 Water Recovery System 

Water Treatment Process ISS WRS 10,785.18 2.35 712.61 712.61 Urine, Hygiene & Potable Water, & Brine Storage Tankage 242.39 0.26 10.73 10.73 Microbial Check Valve 20.37 0.01 0.00 0.00 Process Controller 51.57 0.08 156.18 156.18 Water Quality Monitoring 49.74 0.04 4.72 4.72 Product Water Delivery System 46.23 0.07 2.08 2.08 

Water Storage 

Hygiene Water Storage 0.00 0.00 0.00 0.00 Potable Water Storage 14,440.83 10.99 431.89 431.89 Urine Storage 0.00 0.00 0.00 0.00 Waste Water Storage 0.00 0.00 0.00 0.00 

Extravehicular Activity 0.00 0.00 0.00 0.00 Maximum Absorbency Garments 0.00 0.00 0.00 0.00 Carbon Dioxide Removal (LiOH) 0.00 0.00 0.00 0.00 Airlock Recycle Pump for EVA 0.00 0.00 0.00 0.00 Oxygen Recharge Compressor Assembly for EVA 0.00 0.00 0.00 0.00 Human Accommodations 22,798.79 79.59 0.00 0.00 Clothing 10,643.40 62.42 0.00 0.00 Laundry Equipment 

Washer / Dryer 0.00 0.00 0.00 0.00 Detergent 0.00 0.00 0.00 0.00 

Miscellaneous Items 7,227.66 7.23 0.00 0.00 Wipes 

Hand/Face Wet Wipes 0.00 0.00 0.00 0.00 Shower Wet Wipes 4,927.73 9.94 0.00 0.00 

Totals 117,545 368.75 10,776 9,192 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 

67 

Table 6.2 Subsystem Breakdown for Orbiting Research Facility: International Space Station Upgrade Mission using Advanc

Subsystem or Component Technology 

Mass 

[kg] 

Volume 

[m3] 

Power 

[We] 

Cooling 

[Wth] 

C

Air Subsystem 10,419.62 14.04 4,555.66 2,973.85 Atmospheric Control System 

Atmospheric Pressure Control ISS 119.40 0.26 70.50 70.50 

Atmosphere Revitalization System 

Carbon Dioxide Removal 4BMS/ISS 182.19 0.43 546.37 546.37 Carbon Dioxide Reduction Sabatier 146.09 0.20 151.05 151.05 Oxygen Generation SPE/ISS 1,548.03 1.03 3,478.62 1,896.81 Gaseous Trace Contaminant Control ISS 327.22 3.94 194.35 194.35 Atmosphere Composition Monitoring Assembly ISS 149.99 0.25 103.50 103.50 Sample Delivery System ISS 35.11 0.04 0.00 0.00 Airlock Carbon Dioxide Removal n/a 0.00 0.00 0.00 0.00 

Gas Storage 

Nitrogen Storage Cryogenic 7,196.60 5.48 6.85 6.85 Oxygen Storage Cryogenic 706.69 2.01 2.94 2.94 

Fire Detection and Suppression 

Fire Detection System ISS 1.50 0.00 1.48 1.48 Fire Suppression System ISS 6.80 0.04 0.00 0.00 

Biomass Subsystem 0.00 0.00 0.00 0.00 Crop Storage n/a 0.00 0.00 0.00 0.00 Plant Growth Chamber / Salad Machine n/a 0.00 0.00 0.00 0.00 Food Subsystem 23,593.30 105.79 960.00 960.00 Food Processing, Packaging, and Storage 

Food Processing 0.00 0.00 0.00 0.00 Food Packaging 0.00 0.00 0.00 0.00 Food Storage STM 38,500.08 105.79 960.00 960.00 Dry Food Mass (neglected) -14,906.78 0.00 0.00 0.00 

Thermal Subsystem 750.13 2.68 768.73 768.73 Temperature and Humidity Control 

Common Cabin Air Assembly ISS 119.72 0.51 530.52 530.52 Avionics Air Assembly ISS 12.40 0.03 175.00 175.00 Atmosphere Circulation ISS 9.80 0.02 61.00 61.00 Atmospheric Microbial Control ISS 529.53 2.00 0.00 0.00 

Internal Thermal Control System 78.68 0.12 2.21 2.21 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 

68 

Table 6.2 Subsystem Breakdown for Orbiting Research Facility: International Space Station Upgrade Mission using Advanc

Subsystem or Component Technology 

Mass 

[kg] 

Volume 

[m3] 

Power 

[We] 

Cooling 

[Wth] 

C

Waste Subsystem 1,466.71 22.04 947.08 908.87 Solid Waste Collection ESDM 36.36 0.13 14.00 14.00 Solid Waste Processing System 

Solid Waste Treatment Lyophilization + PMWC + Storage 1,430.35 21.91 933.08 894.87 Solid Waste Processing System Tankage 0.00 0.00 0.00 0.00 Microbial Check Valve 0.00 0.00 0.00 0.00 Process Controller 0.00 0.00 0.00 0.00 Solid Product Quality Monitoring 0.00 0.00 0.00 0.00 Solid Product Delivery System 0.00 0.00 0.00 0.00 

Water Subsystem 1,482.78 2.07 2,142.98 2,142.98 Urine / Waste Water Collection System ISS 41.11 0.02 4.00 4.00 Water Recovery System 

Water Treatment Process VPCAR; no AES 473.44 1.45 1,934.15 1,934.15 Urine, Hygiene & Potable Water, & Brine Storage Tankage 574.46 0.44 16.86 16.86 Microbial Check Valve 52.56 0.01 0.00 0.00 Process Controller 212.04 0.00 180.00 180.00 Water Quality Monitoring 49.74 0.04 4.72 4.72 Product Water Delivery System 79.43 0.11 3.25 3.25 

Water Storage 

Hygiene Water Storage 0.00 0.00 0.00 0.00 Potable Water Storage 0.00 0.00 0.00 0.00 Urine Storage 0.00 0.00 0.00 0.00 Waste Water Storage 0.00 0.00 0.00 0.00 

Extravehicular Activity 0.00 0.00 0.00 0.00 Maximum Absorbency Garments 0.00 0.00 0.00 0.00 Carbon Dioxide Removal (LiOH) 0.00 0.00 0.00 0.00 Airlock Recycle Pump for EVA 0.00 0.00 0.00 0.00 Oxygen Recharge Compressor Assembly for EVA 0.00 0.00 0.00 0.00 Human Accommodations 12,726.66 20.00 633.33 633.33 Clothing 438.00 2.57 0.00 0.00 Laundry Equipment 

Washer / Dryer 80.00 0.26 633.33 633.33 Detergent 53.27 0.00 0.00 0.00 

Miscellaneous Items 7,227.66 7.23 0.00 0.00 Wipes 

Hand/Face Wet Wipes 0.00 0.00 0.00 0.00 Shower Wet Wipes 4,927.73 9.94 0.00 0.00 

Totals 50,439 166.62 10,008 8,388 
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69 

Table 6.3 Subsystem Breakdown for Near-Term Exploration Mission: Crew Exploration Vehicle using Baseline Technologie

Subsystem or Component Technology 

Mass 

[kg] 

Volume 

[m3] 

Power 

[We] 

Cooling 

[Wth] 

C

Air Subsystem 681.04 1.29 317.16 317.16 Atmospheric Control System 

Atmospheric Pressure Control ISS 119.40 0.26 70.50 70.50 

Atmosphere Revitalization System 

Carbon Dioxide Removal LiOH 108.66 0.49 0.00 0.00 Carbon Dioxide Reduction None 0.00 0.00 0.00 0.00 Oxygen Generation Storage 0.00 0.00 0.00 0.00 Gaseous Trace Contaminant Control ISS 13.29 0.02 141.68 141.68 Atmosphere Composition Monitoring Assembly ISS 54.30 0.09 103.50 103.50 Sample Delivery System ISS 35.11 0.04 0.00 0.00 Airlock Carbon Dioxide Removal n/a 0.00 0.00 0.00 0.00 

Gas Storage 

Nitrogen Storage High Pressure 87.41 0.09 0.00 0.00 Oxygen Storage High Pressure 254.57 0.26 0.00 0.00 

Fire Detection and Suppression 

Fire Detection System ISS 1.50 0.00 1.48 1.48 Fire Suppression System ISS 6.80 0.04 0.00 0.00 

Biomass Subsystem 0.00 0.00 0.00 0.00 Crop Storage n/a 0.00 0.00 0.00 0.00 Plant Growth Chamber / Salad Machine n/a 0.00 0.00 0.00 0.00 Food Subsystem 96.95 0.37 960.00 960.00 Food Processing, Packaging, and Storage 

Food Processing 0.00 0.00 0.00 0.00 Food Packaging 0.00 0.00 0.00 0.00 Food Storage STM 135.07 0.37 960.00 960.00 Dry Food Mass (neglected) -38.12 0.00 0.00 0.00 

Thermal Subsystem 268.41 0.86 771.61 771.61 Temperature and Humidity Control 

Common Cabin Air Assembly ISS 118.08 0.50 530.52 530.52 Avionics Air Assembly ISS 12.40 0.03 175.00 175.00 Atmosphere Circulation ISS 9.80 0.02 61.00 61.00 Atmospheric Microbial Control ISS 100.00 0.27 0.00 0.00 

Internal Thermal Control System 28.13 0.04 5.09 5.09 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 

70 

Table 6.3 Subsystem Breakdown for Near-Term Exploration Mission: Crew Exploration Vehicle using Baseline Technologie

Subsystem or Component Technology 

Mass 

[kg] 

Volume 

[m3] 

Power 

[We] 

Cooling 

[Wth] 

C

Waste Subsystem 45.70 0.39 14.00 14.00 Solid Waste Collection ESDM 36.36 0.13 14.00 14.00 Solid Waste Processing System 

Solid Waste Treatment Storage 9.34 0.26 0.00 0.00 Solid Waste Processing System Tankage 0.00 0.00 0.00 0.00 Microbial Check Valve 0.00 0.00 0.00 0.00 Process Controller 0.00 0.00 0.00 0.00 Solid Product Quality Monitoring 0.00 0.00 0.00 0.00 Solid Product Delivery System 0.00 0.00 0.00 0.00 

Water Subsystem 1,167.58 0.90 41.81 26.15 Urine / Waste Water Collection System ISS 4.55 0.02 4.00 4.00 Water Recovery System 

Water Treatment Process Storage 0.00 0.00 0.00 0.00 Urine, Hygiene & Potable Water, & Brine Storage Tankage 0.00 0.00 0.00 0.00 Microbial Check Valve 0.00 0.00 0.00 0.00 Process Controller 0.00 0.00 0.00 0.00 Water Quality Monitoring 0.00 0.00 0.00 0.00 Product Water Delivery System 0.00 0.00 0.00 0.00 

Water Storage 

Hygiene Water Storage 251.36 0.14 8.14 8.14 Potable Water Storage 368.82 0.27 14.01 14.01 Urine Storage 332.32 0.15 1.29 0.00 Waste Water Storage 210.53 0.32 14.37 0.00 

Extravehicular Activity 0.00 0.00 0.00 0.00 Maximum Absorbency Garments 0.00 0.00 0.00 0.00 Carbon Dioxide Removal (LiOH) 0.00 0.00 0.00 0.00 Airlock Recycle Pump for EVA 0.00 0.00 0.00 0.00 Oxygen Recharge Compressor Assembly for EVA 0.00 0.00 0.00 0.00 Human Accommodations 58.53 0.21 0.00 0.00 Clothing 27.22 0.16 0.00 0.00 Laundry Equipment 

Washer / Dryer 0.00 0.00 0.00 0.00 Detergent 0.00 0.00 0.00 0.00 

Miscellaneous Items 18.48 0.02 0.00 0.00 Wipes 

Hand/Face Wet Wipes 0.00 0.00 0.00 0.00 Shower Wet Wipes 12.83 0.03 0.00 0.00 

Totals 2,318 4.02 2,105 2,089 
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Table 6.4 Subsystem Breakdown for Near-Term Exploration Mission: Crew Exploration Vehicle using Advanced Technolog

Subsystem or Component Technology 

Mass 

[kg] 

Volume 

[m3] 

Power 

[We] 

Cooling 

[Wth] 

C

Air Subsystem 428.58 1.01 336.42 336.42 Atmospheric Control System 

Atmospheric Pressure Control ISS 119.40 0.26 70.50 70.50 

Atmosphere Revitalization System 

Carbon Dioxide Removal LiOH 108.87 0.49 0.00 0.00 Carbon Dioxide Reduction None 0.00 0.00 0.00 0.00 Oxygen Generation Storage 0.00 0.00 0.00 0.00 Gaseous Trace Contaminant Control ISS 13.29 0.02 141.68 141.68 Atmosphere Composition Monitoring Assembly ISS 54.30 0.09 103.50 103.50 Sample Delivery System ISS 35.11 0.04 0.00 0.00 Airlock Carbon Dioxide Removal n/a 0.00 0.00 0.00 0.00 

Gas Storage 

Nitrogen Storage Cryogenic 23.02 0.02 6.10 6.10 Oxygen Storage Cryogenic 66.29 0.05 13.16 13.16 

Fire Detection and Suppression 

Fire Detection System ISS 1.50 0.00 1.48 1.48 Fire Suppression System ISS 6.80 0.04 0.00 0.00 

Biomass Subsystem 0.00 0.00 0.00 0.00 Crop Storage n/a 0.00 0.00 0.00 0.00 Plant Growth Chamber / Salad Machine n/a 0.00 0.00 0.00 0.00 Food Subsystem 84.04 0.36 960.00 960.00 Food Processing, Packaging, and Storage 

Food Processing 0.00 0.00 0.00 0.00 Food Packaging 0.00 0.00 0.00 0.00 Food Storage STM with LMC 121.58 0.36 960.00 960.00 Dry Food Mass (neglected) -37.54 0.00 0.00 0.00 

Thermal Subsystem 271.19 0.87 773.71 773.71 Temperature and Humidity Control 

Common Cabin Air Assembly ISS 118.08 0.50 530.52 530.52 Avionics Air Assembly ISS 12.40 0.03 175.00 175.00 Atmosphere Circulation ISS 9.80 0.02 61.00 61.00 Atmospheric Microbial Control ISS 100.00 0.27 0.00 0.00 

Internal Thermal Control System 30.91 0.05 7.19 7.19 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 

72 

Table 6.4 Subsystem Breakdown for Near-Term Exploration Mission: Crew Exploration Vehicle using Advanced Technolog

Subsystem or Component Technology 

Mass 

[kg] 

Volume 

[m3] 

Power 

[We] 

Cooling 

[Wth] 

C

Waste Subsystem 45.61 0.39 14.00 14.00 Solid Waste Collection ESDM 36.36 0.13 14.00 14.00 Solid Waste Processing System 

Solid Waste Treatment Storage 9.25 0.26 0.00 0.00 Solid Waste Processing System Tankage 0.00 0.00 0.00 0.00 Microbial Check Valve 0.00 0.00 0.00 0.00 Process Controller 0.00 0.00 0.00 0.00 Solid Product Quality Monitoring 0.00 0.00 0.00 0.00 Solid Product Delivery System 0.00 0.00 0.00 0.00 

Water Subsystem 449.24 2.22 433.21 433.21 Urine / Waste Water Collection System ISS 4.55 0.02 4.00 4.00 Water Recovery System 

Water Treatment Process ISS WRS Opt 3 111.00 1.74 250.52 250.52 Urine, Hygiene & Potable Water, & Brine Storage Tankage 116.07 0.19 8.75 8.75 Microbial Check Valve 0.86 0.00 0.00 0.00 Process Controller 36.11 0.08 156.18 156.18 Water Quality Monitoring 14.07 0.04 4.72 4.72 Product Water Delivery System 20.84 0.05 1.65 1.65 

Water Storage 

Hygiene Water Storage 0.00 0.00 0.00 0.00 Potable Water Storage 145.74 0.10 7.39 7.39 Urine Storage 0.00 0.00 0.00 0.00 Waste Water Storage 0.00 0.00 0.00 0.00 

Extravehicular Activity 0.00 0.00 0.00 0.00 Maximum Absorbency Garments 0.00 0.00 0.00 0.00 Carbon Dioxide Removal (LiOH) 0.00 0.00 0.00 0.00 Airlock Recycle Pump for EVA 0.00 0.00 0.00 0.00 Oxygen Recharge Compressor Assembly for EVA 0.00 0.00 0.00 0.00 Human Accommodations 58.53 0.21 0.00 0.00 Clothing 27.22 0.16 0.00 0.00 Laundry Equipment 

Washer / Dryer 0.00 0.00 0.00 0.00 Detergent 0.00 0.00 0.00 0.00 

Miscellaneous Items 18.48 0.02 0.00 0.00 Wipes 

Hand/Face Wet Wipes 0.00 0.00 0.00 0.00 Shower Wet Wipes 12.83 0.03 0.00 0.00 

Totals 1,337 5.06 2,517 2,517 
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73 

Table 6.5 Subsystem Breakdown for Near-Term Exploration Mission: Lunar Surface Access Module using Baseline Technol

Subsystem or Component Technology 

Mass 

[kg] 

Volume 

[m3] 

Power 

[We] 

Cooling 

[Wth] 

C

Air Subsystem 519.03 1.04 317.16 317.16 Atmospheric Control System 

Atmospheric Pressure Control ISS 119.40 0.26 70.50 70.50 

Atmosphere Revitalization System 

Carbon Dioxide Removal LiOH 58.18 0.36 0.00 0.00 Carbon Dioxide Reduction None 0.00 0.00 0.00 0.00 Oxygen Generation Storage 0.00 0.00 0.00 0.00 Gaseous Trace Contaminant Control ISS 10.31 0.01 141.68 141.68 Atmosphere Composition Monitoring Assembly ISS 54.30 0.09 103.50 103.50 Sample Delivery System ISS 35.11 0.04 0.00 0.00 Airlock Carbon Dioxide Removal n/a 0.00 0.00 0.00 0.00 

Gas Storage 

Nitrogen Storage High Pressure 69.70 0.07 0.00 0.00 Oxygen Storage High Pressure 163.73 0.17 0.00 0.00 

Fire Detection and Suppression 

Fire Detection System ISS 1.50 0.00 1.48 1.48 Fire Suppression System ISS 6.80 0.04 0.00 0.00 

Biomass Subsystem 0.00 0.00 0.00 0.00 Crop Storage n/a 0.00 0.00 0.00 0.00 Plant Growth Chamber / Salad Machine n/a 0.00 0.00 0.00 0.00 Food Subsystem 64.05 0.23 960.00 960.00 Food Processing, Packaging, and Storage 

Food Processing 0.00 0.00 0.00 0.00 Food Packaging 0.00 0.00 0.00 0.00 Food Storage STM 81.11 0.23 960.00 960.00 Dry Food Mass (neglected) -17.06 0.00 0.00 0.00 

Thermal Subsystem 267.94 0.86 770.81 770.81 Temperature and Humidity Control 

Common Cabin Air Assembly ISS 118.08 0.50 530.52 530.52 Avionics Air Assembly ISS 12.40 0.03 175.00 175.00 Atmosphere Circulation ISS 9.80 0.02 61.00 61.00 Atmospheric Microbial Control ISS 100.00 0.27 0.00 0.00 

Internal Thermal Control System 27.66 0.04 4.29 4.29 
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74 

Table 6.5 Subsystem Breakdown for Near-Term Exploration Mission: Lunar Surface Access Module using Baseline Technol

Subsystem or Component Technology 

Mass 

[kg] 

Volume 

[m3] 

Power 

[We] 

Cooling 

[Wth] 

C

Waste Subsystem 40.77 0.25 14.00 14.00 Solid Waste Collection ESDM 36.36 0.13 14.00 14.00 Solid Waste Processing System 

Solid Waste Treatment Storage 4.41 0.12 0.00 0.00 Solid Waste Processing System Tankage 0.00 0.00 0.00 0.00 Microbial Check Valve 0.00 0.00 0.00 0.00 Process Controller 0.00 0.00 0.00 0.00 Solid Product Quality Monitoring 0.00 0.00 0.00 0.00 Solid Product Delivery System 0.00 0.00 0.00 0.00 

Water Subsystem 607.73 0.44 27.77 18.67 Urine / Waste Water Collection System ISS 4.55 0.02 4.00 4.00 Water Recovery System 

Water Treatment Process Storage 0.00 0.00 0.00 0.00 Urine, Hygiene & Potable Water, & Brine Storage Tankage 0.00 0.00 0.00 0.00 Microbial Check Valve 0.00 0.00 0.00 0.00 Process Controller 0.00 0.00 0.00 0.00 Water Quality Monitoring 0.00 0.00 0.00 0.00 Product Water Delivery System 0.00 0.00 0.00 0.00 

Water Storage 

Hygiene Water Storage 127.43 0.06 5.35 5.35 Potable Water Storage 210.71 0.15 9.32 9.32 Urine Storage 147.41 0.06 0.59 0.00 Waste Water Storage 117.63 0.15 8.51 0.00 

Extravehicular Activity 98.09 0.41 1,000.00 1,000.00 Maximum Absorbency Garments 1.38 0.00 0.00 0.00 Carbon Dioxide Removal (LiOH) 26.41 0.27 0.00 0.00 Airlock Recycle Pump for EVA 70.30 0.14 1,000.00 1,000.00 Oxygen Recharge Compressor Assembly for EVA 0.00 0.00 0.00 0.00 Human Accommodations 25.21 0.09 0.00 0.00 Clothing 11.66 0.07 0.00 0.00 Laundry Equipment 

Washer / Dryer 0.00 0.00 0.00 0.00 Detergent 0.00 0.00 0.00 0.00 

Miscellaneous Items 7.92 0.01 0.00 0.00 Wipes 

Hand/Face Wet Wipes 0.00 0.00 0.00 0.00 Shower Wet Wipes 5.63 0.01 0.00 0.00 

Totals 1,623 3.32 3,090 3,081 
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75 

Table 6.6 Subsystem Breakdown for Near-Term Exploration Mission: Lunar Surface Access Module using Advanced Techn

Subsystem or Component Technology 

Mass 

[kg] 

Volume 

[m3] 

Power 

[We] 

Cooling 

[Wth] 

C

Air Subsystem 346.49 0.84 345.00 345.00 Atmospheric Control System 

Atmospheric Pressure Control ISS 119.40 0.26 70.50 70.50 

Atmosphere Revitalization System 

Carbon Dioxide Removal LiOH 58.27 0.36 0.00 0.00 Carbon Dioxide Reduction None 0.00 0.00 0.00 0.00 Oxygen Generation Storage 0.00 0.00 0.00 0.00 Gaseous Trace Contaminant Control ISS 10.31 0.01 141.68 141.68 Atmosphere Composition Monitoring Assembly ISS 54.30 0.09 103.50 103.50 Sample Delivery System ISS 35.11 0.04 0.00 0.00 Airlock Carbon Dioxide Removal n/a 0.00 0.00 0.00 0.00 

Gas Storage 

Nitrogen Storage Cryogenic 18.23 0.01 9.28 9.28 Oxygen Storage Cryogenic 42.57 0.03 18.56 18.56 

Fire Detection and Suppression 

Fire Detection System ISS 1.50 0.00 1.48 1.48 Fire Suppression System ISS 6.80 0.04 0.00 0.00 

Biomass Subsystem 0.00 0.00 0.00 0.00 Crop Storage n/a 0.00 0.00 0.00 0.00 Plant Growth Chamber / Salad Machine n/a 0.00 0.00 0.00 0.00 Food Subsystem 57.80 0.21 960.00 960.00 Food Processing, Packaging, and Storage 

Food Processing 0.00 0.00 0.00 0.00 Food Packaging 0.00 0.00 0.00 0.00 Food Storage STM with LMC 74.60 0.21 960.00 960.00 Dry Food Mass (neglected) -16.80 0.00 0.00 0.00 

Thermal Subsystem 270.82 0.87 772.67 772.67 Temperature and Humidity Control 

Common Cabin Air Assembly ISS 118.08 0.50 530.52 530.52 Avionics Air Assembly ISS 12.40 0.03 175.00 175.00 Atmosphere Circulation ISS 9.80 0.02 61.00 61.00 Atmospheric Microbial Control ISS 100.00 0.27 0.00 0.00 

Internal Thermal Control System 30.54 0.05 6.15 6.15 
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Table 6.6 Subsystem Breakdown for Near-Term Exploration Mission: Lunar Surface Access Module using Advanced Techn

Subsystem or Component Technology 

Mass 

[kg] 

Volume 

[m3] 

Power 

[We] 

Cooling 

[Wth] 

C

Waste Subsystem 40.73 0.25 14.00 14.00 Solid Waste Collection ESDM 36.36 0.13 14.00 14.00 Solid Waste Processing System 

Solid Waste Treatment Storage 4.37 0.12 0.00 0.00 Solid Waste Processing System Tankage 0.00 0.00 0.00 0.00 Microbial Check Valve 0.00 0.00 0.00 0.00 Process Controller 0.00 0.00 0.00 0.00 Solid Product Quality Monitoring 0.00 0.00 0.00 0.00 Solid Product Delivery System 0.00 0.00 0.00 0.00 

Water Subsystem 407.78 2.23 436.89 436.89 Urine / Waste Water Collection System ISS 4.55 0.02 4.00 4.00 Water Recovery System 

Water Treatment Process ISS WRS Opt 3 116.77 1.78 255.45 255.45 Urine, Hygiene & Potable Water, & Brine Storage Tankage 116.83 0.20 8.91 8.91 Microbial Check Valve 0.95 0.00 0.00 0.00 Process Controller 36.11 0.08 156.18 156.18 Water Quality Monitoring 14.07 0.04 4.72 4.72 Product Water Delivery System 21.40 0.05 1.69 1.69 

Water Storage 

Hygiene Water Storage 0.00 0.00 0.00 0.00 Potable Water Storage 97.10 0.06 5.94 5.94 Urine Storage 0.00 0.00 0.00 0.00 Waste Water Storage 0.00 0.00 0.00 0.00 

Extravehicular Activity 98.09 0.41 1,000.00 1,000.00 Maximum Absorbency Garments 1.38 0.00 0.00 0.00 Carbon Dioxide Removal (LiOH) 26.41 0.27 0.00 0.00 Airlock Recycle Pump for EVA 70.30 0.14 1,000.00 1,000.00 Oxygen Recharge Compressor Assembly for EVA 0.00 0.00 0.00 0.00 Human Accommodations 25.21 0.09 0.00 0.00 Clothing 11.66 0.07 0.00 0.00 Laundry Equipment 

Washer / Dryer 0.00 0.00 0.00 0.00 Detergent 0.00 0.00 0.00 0.00 

Miscellaneous Items 7.92 0.01 0.00 0.00 Wipes 

Hand/Face Wet Wipes 0.00 0.00 0.00 0.00 Shower Wet Wipes 5.63 0.01 0.00 0.00 

Totals 1,247 4.90 3,529 3,529 
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Table 6.7 Subsystem Breakdown for Near-Term Exploration Mission: Destination Surface System using Baseline Technolog

Subsystem or Component Technology 

Mass 

[kg] 

Volume 

[m3] 

Power 

[We] 

Cooling 

[Wth] 

C

Air Subsystem 3,184.90 3.68 1,108.24 1,108.24 Atmospheric Control System 

Atmospheric Pressure Control ISS 119.40 0.26 70.50 70.50 

Atmosphere Revitalization System 

Carbon Dioxide Removal 4BMS/ISS 137.31 0.29 394.08 394.08 Carbon Dioxide Reduction None 0.00 0.00 0.00 0.00 Oxygen Generation Storage 0.00 0.00 0.00 0.00 Gaseous Trace Contaminant Control ISS 42.05 0.08 141.68 141.68 Atmosphere Composition Monitoring Assembly ISS 54.30 0.09 103.50 103.50 Sample Delivery System ISS 35.11 0.04 0.00 0.00 Airlock Carbon Dioxide Removal ISS 181.30 0.23 397.00 397.00 

Gas Storage 

Nitrogen Storage High Pressure 434.29 0.41 0.00 0.00 Oxygen Storage High Pressure 2,172.84 2.24 0.00 0.00 

Fire Detection and Suppression 

Fire Detection System ISS 1.50 0.00 1.48 1.48 Fire Suppression System ISS 6.80 0.04 0.00 0.00 

Biomass Subsystem 0.00 0.00 0.00 0.00 Crop Storage n/a 0.00 0.00 0.00 0.00 Plant Growth Chamber / Salad Machine n/a 0.00 0.00 0.00 0.00 Food Subsystem 459.89 2.00 960.00 960.00 Food Processing, Packaging, and Storage 

Food Processing 0.00 0.00 0.00 0.00 Food Packaging 0.00 0.00 0.00 0.00 Food Storage STM 727.44 2.00 960.00 960.00 Dry Food Mass (neglected) -267.55 0.00 0.00 0.00 

Thermal Subsystem 278.50 0.88 782.52 782.52 Temperature and Humidity Control 

Common Cabin Air Assembly ISS 118.08 0.50 530.52 530.52 Avionics Air Assembly ISS 12.40 0.03 175.00 175.00 Atmosphere Circulation ISS 9.80 0.02 61.00 61.00 Atmospheric Microbial Control ISS 100.00 0.27 0.00 0.00 

Internal Thermal Control System 38.22 0.06 16.00 16.00 
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78 

Table 6.7 Subsystem Breakdown for Near-Term Exploration Mission: Destination Surface System using Baseline Technolog

Subsystem or Component Technology 

Mass 

[kg] 

Volume 

[m3] 

Power 

[We] 

Cooling 

[Wth] 

C

Waste Subsystem 114.69 2.31 14.00 14.00 Solid Waste Collection ESDM 36.36 0.13 14.00 14.00 Solid Waste Processing System 

Solid Waste Treatment Storage 78.33 2.18 0.00 0.00 Solid Waste Processing System Tankage 0.00 0.00 0.00 0.00 Microbial Check Valve 0.00 0.00 0.00 0.00 Process Controller 0.00 0.00 0.00 0.00 Solid Product Quality Monitoring 0.00 0.00 0.00 0.00 Solid Product Delivery System 0.00 0.00 0.00 0.00 

Water Subsystem 882.85 2.50 833.31 833.31 Urine / Waste Water Collection System ISS 4.55 0.02 4.00 4.00 Water Recovery System 

Water Treatment Process ISS WRS 481.78 1.93 647.17 647.17 Urine, Hygiene & Potable Water, & Brine Storage Tankage 81.28 0.21 9.24 9.24 Microbial Check Valve 1.23 0.00 0.00 0.00 Process Controller 36.11 0.08 156.18 156.18 Water Quality Monitoring 14.07 0.04 4.72 4.72 Product Water Delivery System 23.16 0.05 1.79 1.79 

Water Storage 

Hygiene Water Storage 0.00 0.00 0.00 0.00 Potable Water Storage 240.67 0.17 10.21 10.21 Urine Storage 0.00 0.00 0.00 0.00 Waste Water Storage 0.00 0.00 0.00 0.00 

Extravehicular Activity 234.94 0.73 1,000.00 1,000.00 Maximum Absorbency Garments 19.38 0.00 0.00 0.00 Carbon Dioxide Removal (LiOH) 145.26 0.59 0.00 0.00 Airlock Recycle Pump for EVA 70.30 0.14 1,000.00 1,000.00 Oxygen Recharge Compressor Assembly for EVA 0.00 0.00 0.00 0.00 Human Accommodations 408.31 1.43 0.00 0.00 Clothing 190.51 1.12 0.00 0.00 Laundry Equipment 

Washer / Dryer 0.00 0.00 0.00 0.00 Detergent 0.00 0.00 0.00 0.00 

Miscellaneous Items 129.37 0.13 0.00 0.00 Wipes 

Hand/Face Wet Wipes 0.00 0.00 0.00 0.00 Shower Wet Wipes 88.43 0.18 0.00 0.00 

Totals 5,564 13.53 4,698 4,698 
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79 

Table 6.8 Subsystem Breakdown for Near-Term Exploration Mission: Destination Surface System using Advanced Technolo

Subsystem or Component Technology 

Mass 

[kg] 

Volume 

[m3] 

Power 

[We] 

Cooling 

[Wth] 

C

Air Subsystem 1,258.28 1.53 1,129.46 1,129.46 Atmospheric Control System 

Atmospheric Pressure Control ISS 119.40 0.26 70.50 70.50 

Atmosphere Revitalization System 

Carbon Dioxide Removal 4BMS/ISS 137.31 0.29 394.75 394.75 Carbon Dioxide Reduction None 0.00 0.00 0.00 0.00 Oxygen Generation Storage 0.00 0.00 0.00 0.00 Gaseous Trace Contaminant Control ISS 42.05 0.08 141.68 141.68 Atmosphere Composition Monitoring Assembly ISS 54.30 0.09 103.50 103.50 Sample Delivery System ISS 35.11 0.04 0.00 0.00 Airlock Carbon Dioxide Removal ISS 181.30 0.23 397.00 397.00 

Gas Storage 

Nitrogen Storage Cryogenic 115.12 0.11 5.02 5.02 Oxygen Storage Cryogenic 565.39 0.39 15.53 15.53 

Fire Detection and Suppression 

Fire Detection System ISS 1.50 0.00 1.48 1.48 Fire Suppression System ISS 6.80 0.04 0.00 0.00 

Biomass Subsystem 0.00 0.00 0.00 0.00 Crop Storage n/a 0.00 0.00 0.00 0.00 Plant Growth Chamber / Salad Machine n/a 0.00 0.00 0.00 0.00 Food Subsystem 366.71 1.88 960.00 960.00 Food Processing, Packaging, and Storage 

Food Processing 0.00 0.00 0.00 0.00 Food Packaging 0.00 0.00 0.00 0.00 Food Storage STM with LMC 630.19 1.88 960.00 960.00 Dry Food Mass (neglected) -263.48 0.00 0.00 0.00 

Thermal Subsystem 282.18 0.89 788.85 788.85 Temperature and Humidity Control 

Common Cabin Air Assembly ISS 118.08 0.50 530.52 530.52 Avionics Air Assembly ISS 12.40 0.03 175.00 175.00 Atmosphere Circulation ISS 9.80 0.02 61.00 61.00 Atmospheric Microbial Control ISS 100.00 0.27 0.00 0.00 

Internal Thermal Control System 41.90 0.07 22.33 22.33 
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80 

Table 6.8 Subsystem Breakdown for Near-Term Exploration Mission: Destination Surface System using Advanced Technolo

Subsystem or Component Technology 

Mass 

[kg] 

Volume 

[m3] 

Power 

[We] 

Cooling 

[Wth] 

C

Waste Subsystem 109.65 2.17 14.00 14.00 Solid Waste Collection ESDM 36.36 0.13 14.00 14.00 Solid Waste Processing System 

Solid Waste Treatment Storage 73.29 2.04 0.00 0.00 Solid Waste Processing System Tankage 0.00 0.00 0.00 0.00 Microbial Check Valve 0.00 0.00 0.00 0.00 Process Controller 0.00 0.00 0.00 0.00 Solid Product Quality Monitoring 0.00 0.00 0.00 0.00 Solid Product Delivery System 0.00 0.00 0.00 0.00 

Water Subsystem 648.95 1.30 1,428.45 1,428.45 Urine / Waste Water Collection System ISS 4.55 0.02 4.00 4.00 Water Recovery System 

Water Treatment Process VPCAR; no AES 199.39 0.80 1,218.06 1,218.06 Urine, Hygiene & Potable Water, & Brine Storage Tankage 89.10 0.21 9.26 9.26 Microbial Check Valve 1.23 0.00 0.00 0.00 Process Controller 63.00 0.00 180.00 180.00 Water Quality Monitoring 14.07 0.04 4.72 4.72 Product Water Delivery System 23.16 0.05 1.79 1.79 

Water Storage 

Hygiene Water Storage 0.00 0.00 0.00 0.00 Potable Water Storage 254.45 0.18 10.62 10.62 Urine Storage 0.00 0.00 0.00 0.00 Waste Water Storage 0.00 0.00 0.00 0.00 

Extravehicular Activity 234.94 0.73 1,000.00 1,000.00 Maximum Absorbency Garments 19.38 0.00 0.00 0.00 Carbon Dioxide Removal (LiOH) 145.26 0.59 0.00 0.00 Airlock Recycle Pump for EVA 70.30 0.14 1,000.00 1,000.00 Oxygen Recharge Compressor Assembly for EVA 0.00 0.00 0.00 0.00 Human Accommodations 408.31 1.43 0.00 0.00 Clothing 190.51 1.12 0.00 0.00 Laundry Equipment 

Washer / Dryer 0.00 0.00 0.00 0.00 Detergent 0.00 0.00 0.00 0.00 

Miscellaneous Items 129.37 0.13 0.00 0.00 Wipes 

Hand/Face Wet Wipes 0.00 0.00 0.00 0.00 Shower Wet Wipes 88.43 0.18 0.00 0.00 

Totals 3,309 9.93 5,321 5,321 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 

81 

Table 6.9 Subsystem Breakdown for Independent Exploration Mission: Mars Transit Vehicle using Baseline Technologies 

Subsystem or Component Technology 

Mass 

[kg] 

Volume 

[m3] 

Power 

[We] 

Cooling 

[Wth] 

C

Air Subsystem 2,190.10 3.32 4,198.66 2,709.73 Atmospheric Control System 

Atmospheric Pressure Control ISS 119.40 0.26 70.50 70.50 

Atmosphere Revitalization System 

Carbon Dioxide Removal 4BMS/ISS 179.12 0.42 535.98 535.98 Carbon Dioxide Reduction None 0.00 0.00 0.00 0.00 Oxygen Generation SPE/ISS 379.16 1.00 3,292.85 1,803.92 Gaseous Trace Contaminant Control ISS 85.81 0.40 194.35 194.35 Atmosphere Composition Monitoring Assembly ISS 54.30 0.09 103.50 103.50 Sample Delivery System ISS 35.11 0.04 0.00 0.00 Airlock Carbon Dioxide Removal n/a 0.00 0.00 0.00 0.00 

Gas Storage 

Nitrogen Storage High Pressure 1,028.73 0.92 0.00 0.00 Oxygen Storage High Pressure 300.17 0.15 0.00 0.00 

Fire Detection and Suppression 

Fire Detection System ISS 1.50 0.00 1.48 1.48 Fire Suppression System ISS 6.80 0.04 0.00 0.00 

Biomass Subsystem 761.03 17.03 6,099.43 6,099.43 Crop Storage 205.88 0.00 0.00 0.00 Plant Growth Chamber / Salad Machine 555.15 17.03 6,099.43 6,099.43 Food Subsystem 2,839.53 13.12 1,860.00 1,860.00 Food Processing, Packaging, and Storage 

Food Processing 0.00 0.00 0.00 0.00 Food Packaging 0.00 0.00 0.00 0.00 Food Storage STM + Frozen + Salad 4,301.15 13.12 1,860.00 1,860.00 Dry Food Mass (neglected) -1,461.62 0.00 0.00 0.00 

Thermal Subsystem 329.08 1.00 887.95 887.95 Temperature and Humidity Control 

Common Cabin Air Assembly ISS 118.08 0.50 530.52 530.52 Avionics Air Assembly ISS 12.40 0.03 175.00 175.00 Atmosphere Circulation ISS 9.80 0.02 61.00 61.00 Atmospheric Microbial Control ISS 100.00 0.27 0.00 0.00 

Internal Thermal Control System 88.80 0.18 121.43 121.43 
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82 

Table 6.9 Subsystem Breakdown for Independent Exploration Mission: Mars Transit Vehicle using Baseline Technologies (c

Subsystem or Component Technology 

Mass 

[kg] 

Volume 

[m3] 

Power 

[We] 

Cooling 

[Wth] 

C

Waste Subsystem 381.96 9.73 14.00 14.00 Solid Waste Collection ESDM 36.36 0.13 14.00 14.00 Solid Waste Processing System 

Solid Waste Treatment Storage 345.60 9.60 0.00 0.00 Solid Waste Processing System Tankage 0.00 0.00 0.00 0.00 Microbial Check Valve 0.00 0.00 0.00 0.00 Process Controller 0.00 0.00 0.00 0.00 Solid Product Quality Monitoring 0.00 0.00 0.00 0.00 Solid Product Delivery System 0.00 0.00 0.00 0.00 

Water Subsystem 3,353.03 5.50 1,126.62 1,126.62 Urine / Waste Water Collection System ISS 4.55 0.02 4.00 4.00 Water Recovery System 

Water Treatment Process ISS WRS 2,463.74 4.31 919.74 919.74 Urine, Hygiene & Potable Water, & Brine Storage Tankage 181.57 0.47 17.80 17.80 Microbial Check Valve 5.72 0.02 0.00 0.00 Process Controller 36.11 0.08 156.18 156.18 Water Quality Monitoring 14.07 0.04 4.72 4.72 Product Water Delivery System 51.73 0.12 3.44 3.44 

Water Storage 

Hygiene Water Storage 0.00 0.00 0.00 0.00 Potable Water Storage 595.54 0.44 20.74 20.74 Urine Storage 0.00 0.00 0.00 0.00 Waste Water Storage 0.00 0.00 0.00 0.00 

Extravehicular Activity 0.00 0.00 0.00 0.00 Maximum Absorbency Garments 0.00 0.00 0.00 0.00 Carbon Dioxide Removal (LiOH) 0.00 0.00 0.00 0.00 Airlock Recycle Pump for EVA 0.00 0.00 0.00 0.00 Oxygen Recharge Compressor Assembly for EVA 0.00 0.00 0.00 0.00 Human Accommodations 1,762.62 6.87 0.00 0.00 Clothing 1,049.76 6.16 0.00 0.00 Laundry Equipment 

Washer / Dryer 0.00 0.00 0.00 0.00 Detergent 0.00 0.00 0.00 0.00 

Miscellaneous Items 712.86 0.71 0.00 0.00 Wipes 

Hand/Face Wet Wipes 0.00 0.00 0.00 0.00 Shower Wet Wipes 0.00 0.00 0.00 0.00 

Totals 11,617 56.57 14,187 12,698 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 

83 

Table 6.10 Subsystem Breakdown for Independent Exploration Mission: Mars Transit Vehicle using Advanced Technologies 

Subsystem or Component Technology 

Mass 

[kg] 

Volume 

[m3] 

Power 

[We] 

Cooling 

[Wth] 

C

Air Subsystem 1,367.03 2.94 4,350.34 2,863.40 Atmospheric Control System 

Atmospheric Pressure Control ISS 119.40 0.26 70.50 70.50 

Atmosphere Revitalization System 

Carbon Dioxide Removal 4BMS/ISS 179.14 0.42 536.06 536.06 Carbon Dioxide Reduction Sabatier 143.53 0.19 148.59 148.59 Oxygen Generation SPE/ISS 378.86 1.00 3,288.88 1,801.94 Gaseous Trace Contaminant Control ISS 85.81 0.40 194.35 194.35 Atmosphere Composition Monitoring Assembly ISS 54.30 0.09 103.50 103.50 Sample Delivery System ISS 35.11 0.04 0.00 0.00 Airlock Carbon Dioxide Removal n/a 0.00 0.00 0.00 0.00 

Gas Storage 

Nitrogen Storage Cryogenic 275.81 0.31 4.09 4.09 Oxygen Storage Cryogenic 86.77 0.19 2.89 2.89 

Fire Detection and Suppression 

Fire Detection System ISS 1.50 0.00 1.48 1.48 Fire Suppression System ISS 6.80 0.04 0.00 0.00 

Biomass Subsystem 761.03 17.03 6,099.43 6,099.43 Crop Storage 205.88 0.00 0.00 0.00 Plant Growth Chamber / Salad Machine 555.15 17.03 6,099.43 6,099.43 Food Subsystem 2,342.86 10.45 960.00 960.00 Food Processing, Packaging, and Storage 

Food Processing 0.00 0.00 0.00 0.00 Food Packaging 0.00 0.00 0.00 0.00 Food Storage STM + Salad 3,801.98 10.45 960.00 960.00 Dry Food Mass (neglected) -1,459.12 0.00 0.00 0.00 

Thermal Subsystem 336.20 1.01 913.74 913.74 Temperature and Humidity Control 

Common Cabin Air Assembly ISS 118.08 0.50 530.52 530.52 Avionics Air Assembly ISS 12.40 0.03 175.00 175.00 Atmosphere Circulation ISS 9.80 0.02 61.00 61.00 Atmospheric Microbial Control ISS 100.00 0.27 0.00 0.00 

Internal Thermal Control System 95.92 0.19 147.22 147.22 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 

84 

Table 6.10 Subsystem Breakdown for Independent Exploration Mission: Mars Transit Vehicle using Advanced Technologies 

Subsystem or Component Technology 

Mass 

[kg] 

Volume 

[m3] 

Power 

[We] 

Cooling 

[Wth] 

C

Waste Subsystem 254.37 6.19 14.00 14.00 Solid Waste Collection ESDM 36.36 0.13 14.00 14.00 Solid Waste Processing System 

Solid Waste Treatment Storage 218.01 6.06 0.00 0.00 Solid Waste Processing System Tankage 0.00 0.00 0.00 0.00 Microbial Check Valve 0.00 0.00 0.00 0.00 Process Controller 0.00 0.00 0.00 0.00 Solid Product Quality Monitoring 0.00 0.00 0.00 0.00 Solid Product Delivery System 0.00 0.00 0.00 0.00 

Water Subsystem 1,010.77 2.92 3,048.42 3,048.42 Urine / Waste Water Collection System ISS 4.55 0.02 4.00 4.00 Water Recovery System 

Water Treatment Process VPCAR + Lyophilization 582.42 2.02 2,831.45 2,831.45 Urine, Hygiene & Potable Water, & Brine Storage Tankage 266.78 0.65 23.67 23.67 Microbial Check Valve 8.67 0.02 0.00 0.00 Process Controller 63.00 0.00 180.00 180.00 Water Quality Monitoring 14.07 0.04 4.72 4.72 Product Water Delivery System 71.28 0.17 4.58 4.58 

Water Storage 

Hygiene Water Storage 0.00 0.00 0.00 0.00 Potable Water Storage 0.00 0.00 0.00 0.00 Urine Storage 0.00 0.00 0.00 0.00 Waste Water Storage 0.00 0.00 0.00 0.00 

Extravehicular Activity 0.00 0.00 0.00 0.00 Maximum Absorbency Garments 0.00 0.00 0.00 0.00 Carbon Dioxide Removal (LiOH) 0.00 0.00 0.00 0.00 Airlock Recycle Pump for EVA 0.00 0.00 0.00 0.00 Oxygen Recharge Compressor Assembly for EVA 0.00 0.00 0.00 0.00 Human Accommodations 862.93 1.35 633.33 633.33 Clothing 64.80 0.38 0.00 0.00 Laundry Equipment 

Washer / Dryer 80.00 0.26 633.33 633.33 Detergent 5.27 0.00 0.00 0.00 

Miscellaneous Items 712.86 0.71 0.00 0.00 Wipes 

Hand/Face Wet Wipes 0.00 0.00 0.00 0.00 Shower Wet Wipes 0.00 0.00 0.00 0.00 

Totals 6,935 41.89 16,019 14,532 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 

85 

Table 6.11 Subsystem Breakdown for Independent Exploration Mission: Mars Descent / Ascent Lander using Baseline Techn

Subsystem or Component Technology 

Mass 

[kg] 

Volume 

[m3] 

Power 

[We] 

Cooling 

[Wth] 

C

Air Subsystem 1,070.64 2.16 4,250.98 2,742.06 Atmospheric Control System 

Atmospheric Pressure Control ISS 119.40 0.26 70.50 70.50 

Atmosphere Revitalization System 

Carbon Dioxide Removal 4BMS/ISS 182.77 0.43 548.32 548.32 Carbon Dioxide Reduction None 0.00 0.00 0.00 0.00 Oxygen Generation SPE/ISS 382.21 1.00 3,332.83 1,823.91 Gaseous Trace Contaminant Control ISS 25.46 0.05 194.35 194.35 Atmosphere Composition Monitoring Assembly ISS 54.30 0.09 103.50 103.50 Sample Delivery System ISS 35.11 0.04 0.00 0.00 Airlock Carbon Dioxide Removal n/a 0.00 0.00 0.00 0.00 

Gas Storage 

Nitrogen Storage High Pressure 173.01 0.17 0.00 0.00 Oxygen Storage High Pressure 90.08 0.08 0.00 0.00 

Fire Detection and Suppression 

Fire Detection System ISS 1.50 0.00 1.48 1.48 Fire Suppression System ISS 6.80 0.04 0.00 0.00 

Biomass Subsystem 0.00 0.00 0.00 0.00 Crop Storage n/a 0.00 0.00 0.00 0.00 Plant Growth Chamber / Salad Machine n/a 0.00 0.00 0.00 0.00 Food Subsystem 619.72 3.37 2,128.00 2,128.00 Food Processing, Packaging, and Storage 

Food Processing 0.00 0.00 0.00 0.00 Food Packaging 0.00 0.00 0.00 0.00 Food Storage STM with Frozen 743.00 3.37 2,128.00 2,128.00 Dry Food Mass (neglected) -123.28 0.00 0.00 0.00 

Thermal Subsystem 296.40 0.92 822.24 822.24 Temperature and Humidity Control 

Common Cabin Air Assembly ISS 118.08 0.50 530.52 530.52 Avionics Air Assembly ISS 12.40 0.03 175.00 175.00 Atmosphere Circulation ISS 9.80 0.02 61.00 61.00 Atmospheric Microbial Control ISS 100.00 0.27 0.00 0.00 

Internal Thermal Control System 56.12 0.10 55.72 55.72 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 

86 

Table 6.11 Subsystem Breakdown for Independent Exploration Mission: Mars Descent / Ascent Lander using Baseline Techn

Subsystem or Component Technology 

Mass 

[kg] 

Volume 

[m3] 

Power 

[We] 

Cooling 

[Wth] 

C

Waste Subsystem 68.56 1.02 14.00 14.00 Solid Waste Collection ESDM 36.36 0.13 14.00 14.00 Solid Waste Processing System 

Solid Waste Treatment Storage 32.20 0.89 0.00 0.00 Solid Waste Processing System Tankage 0.00 0.00 0.00 0.00 Microbial Check Valve 0.00 0.00 0.00 0.00 Process Controller 0.00 0.00 0.00 0.00 Solid Product Quality Monitoring 0.00 0.00 0.00 0.00 Solid Product Delivery System 0.00 0.00 0.00 0.00 

Water Subsystem 736.68 2.88 895.54 895.54 Urine / Waste Water Collection System ISS 4.55 0.02 4.00 4.00 Water Recovery System 

Water Treatment Process ISS WRS 462.20 2.35 712.07 712.07 Urine, Hygiene & Potable Water, & Brine Storage Tankage 98.86 0.26 10.74 10.74 Microbial Check Valve 2.01 0.01 0.00 0.00 Process Controller 36.11 0.08 156.18 156.18 Water Quality Monitoring 14.07 0.04 4.72 4.72 Product Water Delivery System 28.17 0.07 2.08 2.08 

Water Storage 

Hygiene Water Storage 0.00 0.00 0.00 0.00 Potable Water Storage 90.71 0.05 5.75 5.75 Urine Storage 0.00 0.00 0.00 0.00 Waste Water Storage 0.00 0.00 0.00 0.00 

Extravehicular Activity 21.74 0.25 0.00 0.00 Maximum Absorbency Garments 1.04 0.00 0.00 0.00 Carbon Dioxide Removal (LiOH) 20.70 0.25 0.00 0.00 Airlock Recycle Pump for EVA 0.00 0.00 0.00 0.00 Oxygen Recharge Compressor Assembly for EVA 0.00 0.00 0.00 0.00 Human Accommodations 187.62 0.65 0.00 0.00 Clothing 87.48 0.51 0.00 0.00 Laundry Equipment 

Washer / Dryer 0.00 0.00 0.00 0.00 Detergent 0.00 0.00 0.00 0.00 

Miscellaneous Items 59.41 0.06 0.00 0.00 Wipes 

Hand/Face Wet Wipes 0.00 0.00 0.00 0.00 Shower Wet Wipes 40.73 0.08 0.00 0.00 

Totals 3,001 11.25 8,111 6,602 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 

87 

Table 6.12 Subsystem Breakdown for Independent Exploration Mission: Mars Descent / Ascent Lander using Advanced Tech

Subsystem or Component Technology 

Mass 

[kg] 

Volume 

[m3] 

Power 

[We] 

Cooling 

[Wth] 

C

Air Subsystem 669.74 0.96 488.92 488.92 Atmospheric Control System 

Atmospheric Pressure Control ISS 119.40 0.26 70.50 70.50 

Atmosphere Revitalization System 

Carbon Dioxide Removal SAVD 134.30 0.28 92.10 92.10 Carbon Dioxide Reduction None 0.00 0.00 0.00 0.00 Oxygen Generation Storage 0.00 0.00 0.00 0.00 Gaseous Trace Contaminant Control ISS 25.46 0.05 194.35 194.35 Atmosphere Composition Monitoring Assembly ISS 54.30 0.09 103.50 103.50 Sample Delivery System ISS 35.11 0.04 0.00 0.00 Airlock Carbon Dioxide Removal n/a 0.00 0.00 0.00 0.00 

Gas Storage 

Nitrogen Storage Cryogenic 78.11 0.06 8.29 8.29 Oxygen Storage Cryogenic 214.76 0.14 18.70 18.70 

Fire Detection and Suppression 

Fire Detection System ISS 1.50 0.00 1.48 1.48 Fire Suppression System ISS 6.80 0.04 0.00 0.00 

Biomass Subsystem 0.00 0.00 0.00 0.00 Crop Storage n/a 0.00 0.00 0.00 0.00 Plant Growth Chamber / Salad Machine n/a 0.00 0.00 0.00 0.00 Food Subsystem 188.68 0.92 960.00 960.00 Food Processing, Packaging, and Storage 

Food Processing 0.00 0.00 0.00 0.00 Food Packaging 0.00 0.00 0.00 0.00 Food Storage STM with LMC 309.87 0.92 960.00 960.00 Dry Food Mass (neglected) -121.19 0.00 0.00 0.00 

Thermal Subsystem 280.23 0.89 783.55 783.55 Temperature and Humidity Control 

Common Cabin Air Assembly ISS 118.08 0.50 530.52 530.52 Avionics Air Assembly ISS 12.40 0.03 175.00 175.00 Atmosphere Circulation ISS 9.80 0.02 61.00 61.00 Atmospheric Microbial Control ISS 100.00 0.27 0.00 0.00 

Internal Thermal Control System 39.95 0.07 17.03 17.03 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 

88 

Table 6.12 Subsystem Breakdown for Independent Exploration Mission: Mars Descent / Ascent Lander using Advanced Tech

Subsystem or Component Technology 

Mass 

[kg] 

Volume 

[m3] 

Power 

[We] 

Cooling 

[Wth] 

C

Waste Subsystem 67.42 0.99 14.00 14.00 Solid Waste Collection ESDM 36.36 0.13 14.00 14.00 Solid Waste Processing System 

Solid Waste Treatment Storage 31.06 0.86 0.00 0.00 Solid Waste Processing System Tankage 0.00 0.00 0.00 0.00 Microbial Check Valve 0.00 0.00 0.00 0.00 Process Controller 0.00 0.00 0.00 0.00 Solid Product Quality Monitoring 0.00 0.00 0.00 0.00 Solid Product Delivery System 0.00 0.00 0.00 0.00 

Water Subsystem 444.88 1.30 1,548.42 1,548.42 Urine / Waste Water Collection System ISS 4.55 0.02 4.00 4.00 Water Recovery System 

Water Treatment Process VPCAR; no AES 228.40 0.92 1,347.02 1,347.02 Urine, Hygiene & Potable Water, & Brine Storage Tankage 105.24 0.25 10.63 10.63 Microbial Check Valve 1.94 0.01 0.00 0.00 Process Controller 63.00 0.00 180.00 180.00 Water Quality Monitoring 14.07 0.04 4.72 4.72 Product Water Delivery System 27.68 0.06 2.05 2.05 

Water Storage 

Hygiene Water Storage 0.00 0.00 0.00 0.00 Potable Water Storage 0.00 0.00 0.00 0.00 Urine Storage 0.00 0.00 0.00 0.00 Waste Water Storage 0.00 0.00 0.00 0.00 

Extravehicular Activity 21.74 0.25 0.00 0.00 Maximum Absorbency Garments 1.04 0.00 0.00 0.00 Carbon Dioxide Removal (LiOH) 20.70 0.25 0.00 0.00 Airlock Recycle Pump for EVA 0.00 0.00 0.00 0.00 Oxygen Recharge Compressor Assembly for EVA 0.00 0.00 0.00 0.00 Human Accommodations 187.62 0.65 0.00 0.00 Clothing 87.48 0.51 0.00 0.00 Laundry Equipment 

Washer / Dryer 0.00 0.00 0.00 0.00 Detergent 0.00 0.00 0.00 0.00 

Miscellaneous Items 59.41 0.06 0.00 0.00 Wipes 

Hand/Face Wet Wipes 0.00 0.00 0.00 0.00 Shower Wet Wipes 40.73 0.08 0.00 0.00 

Totals 1,860 5.96 3,795 3,795 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 

89 

Table 6.13 Subsystem Breakdown for Independent Exploration Mission: Surface Habitat Lander using Baseline Technologies 

Subsystem or Component Technology 

Mass 

[kg] 

Volume 

[m3] 

Power 

[We] 

Cooling 

[Wth] 

C

Air Subsystem 4,194.56 5.52 5,846.50 3,732.19 Atmospheric Control System 

Atmospheric Pressure Control ISS 119.40 0.26 70.50 70.50 

Atmosphere Revitalization System 

Carbon Dioxide Removal 4BMS/ISS 179.14 0.42 536.05 536.05 Carbon Dioxide Reduction None 0.00 0.00 0.00 0.00 Oxygen Generation SPE/ISS 586.98 1.25 4,543.62 2,429.31 Gaseous Trace Contaminant Control ISS 103.41 0.66 194.35 194.35 Atmosphere Composition Monitoring Assembly ISS 54.30 0.09 103.50 103.50 Sample Delivery System ISS 35.11 0.04 0.00 0.00 Airlock Carbon Dioxide Removal ISS 181.30 0.23 397.00 397.00 

Gas Storage 

Nitrogen Storage High Pressure 2,183.84 2.02 0.00 0.00 Oxygen Storage High Pressure 742.78 0.51 0.00 0.00 

Fire Detection and Suppression 

Fire Detection System ISS 1.50 0.00 1.48 1.48 Fire Suppression System ISS 6.80 0.04 0.00 0.00 

Biomass Subsystem 898.28 17.03 6,099.43 6,099.43 Crop Storage 343.13 0.00 0.00 0.00 Plant Growth Chamber / Salad Machine 555.15 17.03 6,099.43 6,099.43 Food Subsystem 7,579.74 38.39 4,272.00 4,272.00 Food Processing, Packaging, and Storage 

Food Processing 0.00 0.00 0.00 0.00 Food Packaging 0.00 0.00 0.00 0.00 Food Storage STM + Frozen + Salad 10,016.14 38.39 4,272.00 4,272.00 Dry Food Mass (neglected) -2,436.40 0.00 0.00 0.00 

Thermal Subsystem 382.25 1.17 1,032.03 1,032.03 Temperature and Humidity Control 

Common Cabin Air Assembly ISS 118.08 0.50 530.52 530.52 Avionics Air Assembly ISS 12.40 0.03 175.00 175.00 Atmosphere Circulation ISS 9.80 0.02 61.00 61.00 Atmospheric Microbial Control ISS 131.33 0.40 0.00 0.00 

Internal Thermal Control System 110.64 0.22 265.51 265.51 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 

90 

Table 6.13 Subsystem Breakdown for Independent Exploration Mission: Surface Habitat Lander using Baseline Technologies 

Subsystem or Component Technology 

Mass 

[kg] 

Volume 

[m3] 

Power 

[We] 

Cooling 

[Wth] 

C

Waste Subsystem 667.58 17.66 14.00 14.00 Solid Waste Collection ESDM 36.36 0.13 14.00 14.00 Solid Waste Processing System 

Solid Waste Treatment Storage 631.22 17.53 0.00 0.00 Solid Waste Processing System Tankage 0.00 0.00 0.00 0.00 Microbial Check Valve 0.00 0.00 0.00 0.00 Process Controller 0.00 0.00 0.00 0.00 Solid Product Quality Monitoring 0.00 0.00 0.00 0.00 Solid Product Delivery System 0.00 0.00 0.00 0.00 

Water Subsystem 10,380.48 9.82 1,284.51 1,284.51 Urine / Waste Water Collection System ISS 7.22 0.02 4.00 4.00 Water Recovery System 

Water Treatment Process ISS WRS 3,836.35 4.33 909.85 909.85 Urine, Hygiene & Potable Water, & Brine Storage Tankage 182.13 0.47 17.85 17.85 Microbial Check Valve 9.50 0.02 0.00 0.00 Process Controller 36.11 0.08 156.18 156.18 Water Quality Monitoring 14.07 0.04 4.72 4.72 Product Water Delivery System 51.89 0.12 3.45 3.45 

Water Storage 

Hygiene Water Storage 0.00 0.00 0.00 0.00 Potable Water Storage 6,243.21 4.74 188.46 188.46 Urine Storage 0.00 0.00 0.00 0.00 Waste Water Storage 0.00 0.00 0.00 0.00 

Extravehicular Activity 1,292.18 2.91 2,500.00 2,500.00 Maximum Absorbency Garments 242.20 0.00 0.00 0.00 Carbon Dioxide Removal (LiOH) 817.20 2.43 0.00 0.00 Airlock Recycle Pump for EVA 70.30 0.14 1,000.00 1,000.00 Oxygen Recharge Compressor Assembly for EVA 162.48 0.34 1,500.00 1,500.00 Human Accommodations 2,937.71 11.45 0.00 0.00 Clothing 1,749.60 10.26 0.00 0.00 Laundry Equipment 

Washer / Dryer 0.00 0.00 0.00 0.00 Detergent 0.00 0.00 0.00 0.00 

Miscellaneous Items 1,188.11 1.19 0.00 0.00 Wipes 

Hand/Face Wet Wipes 0.00 0.00 0.00 0.00 Shower Wet Wipes 0.00 0.00 0.00 0.00 

Totals 28,333 103.95 21,048 18,934 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 

91 

Table 6.14 Subsystem Breakdown for Independent Exploration Mission: Surface Habitat Lander using Advanced Technologi

Subsystem or Component Technology 

Mass 

[kg] 

Volume 

[m3] 

Power 

[We] 

Cooling 

[Wth] 

C

Air Subsystem 2,198.26 4.17 6,015.56 3,903.01 Atmospheric Control System 

Atmospheric Pressure Control ISS 119.40 0.26 70.50 70.50 

Atmosphere Revitalization System 

Carbon Dioxide Removal 4BMS/ISS 179.16 0.42 536.13 536.13 Carbon Dioxide Reduction Sabatier 160.43 0.23 164.83 164.83 Oxygen Generation SPE/ISS 586.62 1.25 4,540.09 2,427.54 Gaseous Trace Contaminant Control ISS 103.41 0.66 194.35 194.35 Atmosphere Composition Monitoring Assembly ISS 54.30 0.09 103.50 103.50 Sample Delivery System ISS 35.11 0.04 0.00 0.00 Airlock Carbon Dioxide Removal ISS 181.30 0.23 397.00 397.00 

Gas Storage 

Nitrogen Storage Cryogenic 581.44 0.59 4.55 4.55 Oxygen Storage Cryogenic 188.79 0.36 3.13 3.13 

Fire Detection and Suppression 

Fire Detection System ISS 1.50 0.00 1.48 1.48 Fire Suppression System ISS 6.80 0.04 0.00 0.00 

Biomass Subsystem 898.28 17.03 6,099.43 6,099.43 Crop Storage 343.13 0.00 0.00 0.00 Plant Growth Chamber / Salad Machine 555.15 17.03 6,099.43 6,099.43 Food Subsystem 3,880.67 17.35 960.00 960.00 Food Processing, Packaging, and Storage 

Food Processing 0.00 0.00 0.00 0.00 Food Packaging 0.00 0.00 0.00 0.00 Food Storage STM + Salad 6,312.90 17.35 960.00 960.00 Dry Food Mass (neglected) -2,432.23 0.00 0.00 0.00 

Thermal Subsystem 375.93 1.16 999.36 999.36 Temperature and Humidity Control 

Common Cabin Air Assembly ISS 118.08 0.50 530.52 530.52 Avionics Air Assembly ISS 12.40 0.03 175.00 175.00 Atmosphere Circulation ISS 9.80 0.02 61.00 61.00 Atmospheric Microbial Control ISS 131.33 0.40 0.00 0.00 

Internal Thermal Control System 104.32 0.21 232.84 232.84 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 

92 

Table 6.14 Subsystem Breakdown for Independent Exploration Mission: Surface Habitat Lander using Advanced Technologi

Subsystem or Component Technology 

Mass 

[kg] 

Volume 

[m3] 

Power 

[We] 

Cooling 

[Wth] 

C

Waste Subsystem 391.83 6.69 352.68 352.68 Solid Waste Collection ESDM 36.36 0.13 14.00 14.00 Solid Waste Processing System 

Solid Waste Treatment Lyophilization 355.47 6.56 338.68 338.68 Solid Waste Processing System Tankage 0.00 0.00 0.00 0.00 Microbial Check Valve 0.00 0.00 0.00 0.00 Process Controller 0.00 0.00 0.00 0.00 Solid Product Quality Monitoring 0.00 0.00 0.00 0.00 Solid Product Delivery System 0.00 0.00 0.00 0.00 

Water Subsystem 1,532.67 3.32 3,103.92 3,103.92 Urine / Waste Water Collection System ISS 7.22 0.02 4.00 4.00 Water Recovery System 

Water Treatment Process VPCAR + Lyophilization 591.23 2.05 2,868.96 2,868.96 Urine, Hygiene & Potable Water, & Brine Storage Tankage 282.16 0.66 24.04 24.04 Microbial Check Valve 14.65 0.02 0.00 0.00 Process Controller 63.00 0.00 180.00 180.00 Water Quality Monitoring 14.07 0.04 4.72 4.72 Product Water Delivery System 72.53 0.17 4.65 4.65 

Water Storage 

Hygiene Water Storage 0.00 0.00 0.00 0.00 Potable Water Storage 487.81 0.36 17.55 17.55 Urine Storage 0.00 0.00 0.00 0.00 Waste Water Storage 0.00 0.00 0.00 0.00 

Extravehicular Activity 1,292.18 2.91 2,500.00 2,500.00 Maximum Absorbency Garments 242.20 0.00 0.00 0.00 Carbon Dioxide Removal (LiOH) 817.20 2.43 0.00 0.00 Airlock Recycle Pump for EVA 70.30 0.14 1,000.00 1,000.00 Oxygen Recharge Compressor Assembly for EVA 162.48 0.34 1,500.00 1,500.00 Human Accommodations 1,348.88 1.87 633.33 633.33 Clothing 72.00 0.42 0.00 0.00 Laundry Equipment 

Washer / Dryer 80.00 0.26 633.33 633.33 Detergent 8.77 0.00 0.00 0.00 

Miscellaneous Items 1,188.11 1.19 0.00 0.00 Wipes 

Hand/Face Wet Wipes 0.00 0.00 0.00 0.00 Shower Wet Wipes 0.00 0.00 0.00 0.00 

Totals 11,919 54.50 20,664 18,552 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, CR-2006-213694 February 2006 

93 

7 REFERENCES

Drysdale, A. E., and Hanford, A. J. (2002) “Advanced Life Support Research and Technology 

Development Metric – Fiscal Year 2001,” JSC 47787 (CTSD-ADV-482), National Aeronautics and Space 

Administration, Lyndon B. Johnson Space Center, Houston, Texas, 17 January 2002. 

Hanford, A. J. (2003a) “Advanced Life Support Research and Technology Development Metric - Fiscal 

Year 2002,” JSC 60313 (CTSD-ADV-510), Revision A, National Aeronautics and Space Administration, 

Lyndon B. Johnson Space Center, Houston, Texas, 24 July 2003. 

Hanford, A. J. (2003b) “Advanced Life Support Research and Technology Development Metric - Fiscal 

Year 2003,” NASA/CR-2004-208939 (JSC 60455, CTSD-ADV-524), National Aeronautics and Space 

Administration, Lyndon B. Johnson Space Center, Houston, Texas, 30 September 2003. 

Hanford, A. J., Editor (2004a) “Advanced Life Support Baseline Values and Assumptions Document,” 

NASA/CR-2004-208941 (JSC 47804 A, CTSD-ADV-484 A), National Aeronautics and Space 

Administration, Lyndon B. Johnson Space Center, Houston, Texas. 

Hanford, A. J. (2004b) “Subsystem Details for the Fiscal Year 2004 Advanced Life Support Research and 

Technology Development Metric,” MSAD-04-0306A, Lockheed Martin Space Operations, Houston, 

Texas, September 2004. 

Hanford, A. J. (2004c) “Advanced Life Support Research and Technology Development Metric – Fiscal 

Year 2004,” NASA/CR-2004-208944, National Aeronautics and Space Administration, Lyndon B. Johnson 

Space Center, Houston, Texas, October 2004. 

Hanford, A. J. (2005) “A Lunar Reference Mission for Advanced Life Support,” ESCG-4007-05-TEANDO-0082, Engineering and Science Contract Group, Jacobs Sverdrup, Houston, Texas, 08 July 2005. 

Henninger, D. L., et al. (2002) “Advanced Life Support Project Plan,” JSC 39168 (CTSD-ADV-348), 

Revision C, National Aeronautics and Space Administration, Lyndon B. Johnson Space Center, Houston, 

Texas. 

Levri, J. A., Drysdale, A. E., Ewert, M. K., Fisher, J. W., Hanford, A. J., Hogan, J. A., Jones, H. W., 

Joshi, J. A., and Vaccari, D. A. (2003) “Advanced Life Support Equivalent System Mass Guidelines 

Document,” NASA/TM-2003-212278, National Aeronautics and Space Administration, Ames Research 

Center, Moffett Field, California. 

Stafford, K. W., Jerng, L. T., Drysdale, A. E., Maxwell, S., Levri, J. A., Ewert, M. K., and Hanford, A. J. 

(2001) “Advanced Life Support Systems Integration, Modeling, and Analysis Reference Missions 

Document,” JSC 39502, Revision A, National Aeronautics and Space Administration, Lyndon B. Johnson 

Space Center, Houston, Texas. 

Yeh, J., Brown, C., and Jeng, F. (2002) “Advanced Life Support Sizing Analysis Tool (ALSSAT) v.2.0 

User’s Guide,” LMSEAT 34082, Lockheed Martin Space Operations, Houston, Texas. 

Yeh, J., Brown, C., and Jeng, F. (2003) “Advanced Life Support Sizing Analysis Tool (ALSSAT) v.3.0,” 

MSAD-03-0279, Lockheed Martin Space Operations, Houston, Texas. 

Yeh, J., Brown, C., and Jeng, F. (2004a) “FY04 ALSSAT Upgrade,” MSAD-04-0261, Lockheed Martin 

Space Operations, Houston, Texas. 

Yeh, J., Brown, C., and Jeng, F. (2004b) “Reference Manual for the Advanced Life Support Sizing 

Analysis Tool (ALSSAT),” MSAD-04-0303, Lockheed Martin Space Operations, Houston, Texas. 

Yeh, J., Brown, C., and Jeng, F. (2004c) “Water Recovery Subsystem (WRS) Options Trade Studies Using 

ALSSAT,” MSAD-04-0353, Lockheed Martin Space Operations, Houston, Texas. 

Yeh, J., Brown, C., and Jeng, F. (2005a) “FY05 ALSSAT Upgrade,” MSAD-05-0098, Lockheed Martin 

Space Operations, Houston, Texas. 

Yeh, J., Brown, C., and Jeng, F. (2005b) “Advanced Life Support Sizing Analysis Tool (ALSSAT) 

Upgrade for FY05,” ESCG-4470-05-TEAN-DOC-0141, Engineering and Science Contract Group, Jacobs 

Sverdrup, Houston, Texas. 
Advanced Life Support Research and Technology Development Metric – Fiscal Year 2005, ESCG-4470-05-TEAN-DOC-0157 October 2005 

94 

8 ABBREVIATIONS AND ACRONYMS

 4BMS four-bed molecular sieve 

 AAA avionic air assembly 

 AES air evaporation subsystem 

 A/L airlock 

 ALS Advanced Life Support 

 ALSSAT Advanced Life Support Sizing Analysis 

Tool 

 AS ambient storage 

 ATCO ambient temperature catalytic oxidizer 

(for carbon monoxide removal) 

 CCAA common cabin air assembly 

 CH4

 methane 

 CM crewmember (i.e., units for enumerating 

people) 

 CM-d crewmember-day (i.e., the time from 

one crewmember for one day.) 

 CM-h crewmember-hour (i.e., the time from 

one crewmember for one hour.) 

 CO2 carbon dioxide 

 Cond. HX anti-microbial condensing heat 

exchanger 

 Cond. Tank condensate tank 

 d day (i.e., units of time.) 

 ECLSS environmental control and life support 

system 

 EMU extravehicular mobility unit 

 ESDM Environmental Control and Life 

Support System Design Model 

 ESM equivalent system mass 

 EVA extravehicular activity 

 FDS fire detection and suppression 

 G/L gas/liquid (separator) 

 h hour (i.e., units of time) 

 H2

 hydrogen 

 H2

O water 

 H2

SO4 sulfuric acid 

 HEPA high efficiency particulate air 

 HP high-pressure (gas) 

 HX heat exchanger 

 ITCS internal thermal control system 

 ISS International Space Station 

 IX ion exchange 

 kg kilogram (i.e., units of mass.) 

 kPa kilo Pascal (i.e., units of pressure.) 

 kWe kilo Watt, electric 

(i.e., units of electric power.) 

 kWth kilo Watt, thermal 

(i.e., units of heat transfer rate.) 

 LiOH lithium hydroxide 

 LMC low-moisture content (food) 

 m meter (i.e., units of length) 

 m3 cubic meters (i.e., units of volume.) 

 MCA major constituent analyzer 

 MCV microbial check valve 

 MF multifiltration 

 MJ mega Joule (i.e., units of energy.) 

 MLS mostly liquid separator 

 mod modules (i.e., units for enumerating 

modules) 

 n/a not applicable 

 N2

 nitrogen 

 NASA National Aeronautics 

and Space Administration 

 O2

 oxygen 

 OGA oxygen generation assembly 

 ORCA oxygen recharge compressor assembly 

 pH potential of hydrogen 

 PMA pressurized mating adaptor 

 PMWC plastic melt waste compaction 

 RFR refrigerator freezer rack 

 SAVD solid amine vacuum desorption 

 SIMA Systems Integration, Modeling, 

and Analysis Project Element 

 SPE solid polymer [water] electrolysis 

 STM Shuttle Training Menu 

 TCCS trace contaminant control subsystem 

 TCS thermal control subsystem 

 TRL technology readiness level 

(See Table 1.2.1) 

 USOS United States On-Orbit Segment (of the 

International Space Station) 

 VCD vapor compression distillation 

 VPCAR vapor phase catalytic ammonia removal 

 VRA volatile removal assembly 

 WRS water recovery subsystem 

 WRS Opt 3 [ISS] water recovery subsystem without 

urine recovery [VCD]; urine dumped 

overboard. See text. 

 WW wastewater (tank) 
95
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Advanced Life Support Research and Technology Development Metric--Fiscal Year 2005 

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Anthony J. Hanford, PhD 

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This document provides the official calculation of the Advanced Life Support (ALS) Research and Technology Development Metric 

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