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  • 1
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    Deep Space Habitat ECLSS Design Concept (2012)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Life support is vital to human spaceflight, and most current life support systems employ single-use hardware or regenerable technologies that throw away the waste products, relying on resupply to make up the consumables lost in the process. Because the long-term goal of the National Aeronautics and Space Administration is to expand human presence beyond low-earth orbit, life support systems must become self-sustaining for missions where resupply is not practical. From May through October 2011, the life support team at the Johnson Space Center was challenged to define requirements, develop a system concept, and create a preliminary life support system design for a non-planetary Deep Space Habitat that could sustain a crew of four in near earth orbit for a duration of 388 days. Some of the preferred technology choices to support this architecture were passed over because the mission definition has an unmanned portion lasting 825 days. The main portion of the architecture was derived from technologies currently integrated on the International Space Station as well as upcoming technologies with moderate Technology Readiness Levels. The final architecture concept contains only partially-closed air and water systems, as the breakeven point for some of the closure technologies was not achieved with the mission duration.
    Keywords: Man/System Technology and Life Support
    Type: JSC-CN-26219 , 42nd International Conference on Environmental Systems; Jul 15, 2010 - Jul 19, 2010; San Diego, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Life Support Systems for a New Lunar Lander (2012)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A life support system concept has been developed for a new NASA lunar lander concept. The ground rules and assumptions driving the design of this vehicle are different from the Constellation Altair vehicle, and have led to a different design solution. For example, this concept assumes that the lander vehicle arrives in lunar orbit independently of the crew. It loiters in lunar orbit for months before rendezvousing with the Orion Multi-Purpose Crew Vehicle (MPCV), resulting in the use of solar power for this new lander, rather than fuel cells that provided product water to the life support system in the Altair vehicle. Without the need to perform a single Lunar Orbit Insertion burn for both the lander and the MPCV, the modules do not have to be centered in the same way, so the new lander has a smaller ascent module than Altair and a large habitat rather than a small airlock. This new lander utilizes suitport technology to perform EVAs from the habitat, which leads to significantly different requirements for the pressure control system. This paper describes the major trades and resulting concept design for the life support system of a new lunar lander concept. I
    Keywords: Spacecraft Design, Testing and Performance
    Type: JSC-CN-26198 , 42nd International Conference on Environmental Systems; Jul 15, 2012 - Jul 19, 2012; San Diego, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Altair Lander Life Support: Design Analysis Cycles 4 and 5 (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Life support systems are a critical part of human exploration beyond low earth orbit. NASA s Altair Lunar Lander team is pursuing efficient solutions to the technical challenges of human spaceflight. Life support design efforts up through Design Analysis Cycle (DAC) 4 focused on finding lightweight and reliable solutions for the Sortie and Outpost missions within the Constellation Program. In DAC-4 and later follow on work, changes were made to add functionality for new requirements accepted by the Altair project, and to update the design as knowledge about certain issues or hardware matured. In DAC-5, the Altair project began to consider mission architectures outside the Constellation baseline. Selecting the optimal life support system design is very sensitive to mission duration. When the mission goals and architecture change several trade studies must be conducted to determine the appropriate design. Finally, several areas of work developed through the Altair project may be applicable to other vehicle concepts for microgravity missions. Maturing the Altair life support system related analysis, design, and requirements can provide important information for developers of a wide range of other human vehicles.
    Keywords: Man/System Technology and Life Support
    Type: JSC-CN-23319 , 41st International Conference on Environmental Systems (ICES); Jul 17, 2011 - Jul 21, 2011; Portland, OR; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    International Space Station (ISS) Orbital Replaceable Unit (ORU) Wet Storage Risk Assessment (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: The International Space Station (ISS) Program requested the NASA Engineering and Safety Center (NESC) to evaluate the risks posed by the practice of long-term wet storage of ISS Environmental Control and Life Support (ECLS) regeneration system orbital replacement units (ORUs). The ISS ECLS regeneration system removes water from urine and humidity condensate and converts it into potable water and oxygen. A total of 29 ORUs are in the ECLS system, each designed to be replaced by the ISS crew when necessary. The NESC assembled a team to review the ISS ECLS regeneration system and evaluate the potential for biofouling and corrosion. This document contains the outcome of the evaluation.
    Keywords: Space Transportation and Safety
    Type: NASA/TM-2014-218172 , L-20386 , NESC-RP-12-00778 , NF1676L-18400
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Life Support Systems for a New Lunar Lander (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-19
    Description: A life support system concept has been developed for a new NASA lunar lander concept. The ground rules and assumptions driving the design of this vehicle are different from the Constellation Altair vehicle, and have led to a different design solution. For example, this concept assumes that the lander vehicle arrives in lunar orbit independently of the crew. It loiters in lunar orbit for months before rendezvousing with the Orion Multi-Purpose Crew Vehicle (MPCV), resulting in the use of solar power for this new lander, rather than fuel cells that provided product water to the life support system in the Altair vehicle. Without the need to perform a single Lunar Orbit Insertion burn for both the lander and the MPCV, the modules do not have to be centered in the same way, so the new lander has a smaller ascent module than Altair and a large habitat rather than a small airlock. This new lander utilizes suitport technology to perform EVAs from the habitat, which leads to significantly different requirements for the pressure control system. This paper describes the major trades and resulting concept design for the life support system of a new lunar lander concept.
    Keywords: Spacecraft Design, Testing and Performance
    Type: JSC-CN-25059 , 42nd International Conference on Environmental Systems; Jul 15, 2012 - Jul 19, 2012; San Diego, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    AN-Type Fittings in the International Space System (ISS) Node 2 Ammonia System Technical Assessment Report (2009)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Based on an anonymous request, an NESC Assessment Team was formed to investigate potential leakage problems from the ISS Program's Node 2 Anhydrous Ammonia System AN fittings. The Team's charter was to provide the ISS Program with a path to follow, which could include testing, to ensure the ISS Program felt confident that the AN fittings' leakage would not exceed specified limits in orbit. The findings from that assessment are contained in this document.
    Keywords: Space Transportation and Safety
    Type: NASA/TM-2009-215729 , NESC-RP-05-117/04-038-E , L-19667 , LF99-8782
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Altair Lander Life Support: Requirements Analysis Cycles 1 and 2 (2010)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Life support systems are a critical part of human exploration beyond low earth orbit. NASA's Altair Lunar Lander has unique missions to perform and will need a unique life support system to complete them. Initial work demonstrated a feasible minimally -functional Lander design. This work was completed in Design Analysis Cycles (DAC) 1, 2, and 3 were reported in a previous paper'. On October 21, 2008, the Altair project completed the Mission Concept Review (MCR), moving the project into Phase A. In Phase A activities, the project is preparing for the System Requirements Review (SRR). Altair has conducted two Requirements Analysis Cycles (RACs) to begin this work. During this time, the life support team must examine the Altair mission concepts, Constellation Program level requirements, and interfaces with other vehicles and spacesuits to derive the right set of requirements for the new vehicle. The minimum functionality design meets some of these requirements already and can be easily adapted to meet others. But Altair must identify which will be more costly in mass, power, or other resources to meet. These especially costly requirements must be analyzed carefully to be sure they are truly necessary, and are the best way of explaining and meeting the true need. If they are necessary and clear, they become important mass threats to track at the vehicle level. If they are not clear or do not seem necessary to all stakeholders, Altair must work to redefine them or push back on the requirements writers. Additionally, the life support team is evaluating new technologies to see if they are more effective than the existing baseline design at performing necessary functions in Altair's life support system.
    Keywords: Man/System Technology and Life Support
    Type: JSC-CN-20582 , International Conference on Environmental Systems; Jul 11, 2010 - Jul 15, 2010; Barcelona; Spain
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Altair Lander Life Support: Requirement Analysis Cycles 1 and 2 (2009)
    In:  Other Sources
    Details
    Publication Date: 2019-08-14
    Description: Life support systems are a critical part of human exploration beyond low earth orbit. NASA s Altair Lunar Lander has unique missions to perform and will need a unique life support system to complete them. Initial work demonstrated a feasible minimally-functional Lander design. This work was completed in Design Analysis Cycles (DAC) 1, 2, and 3 were reported in a previous paper. On October 21, 2008, the Altair project completed the Mission Concept Review (MCR), moving the project into Phase A. In Phase A activities, the project is preparing for the System Requirements Review (SRR). Altair has conducted two Requirements Analysis Cycles (RACs) to begin this work. During this time, the life support team must examine the Altair mission concepts, Constellation Program level requirements, and interfaces with other vehicles and spacesuits to derive the right set of requirements for the new vehicle. The minimum functionality design meets some of these requirements already and can be easily adapted to meet others. But Altair must identify which will be more costly in mass, power, or other resources to meet. These especially costly requirements must be analyzed carefully to be sure they are truly necessary, and are the best way of explaining and meeting the true need. If they are necessary and clear, they become important mass threats to track at the vehicle level. If they are not clear or do not seem necessary to all stakeholders, Altair must work to redefine them or push back on the requirements writers. Additionally, the life support team is evaluating new technologies to see if they are more effective than the existing baseline design at performing necessary functions in Altair s life support system.
    Keywords: Man/System Technology and Life Support
    Type: JSC-CN-19265 , 40th International Conference on Environmental Systems; Jul 11, 2010 - Jul 15, 2010; Barcelona; Spain
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Altair Lander Life Support: Design Analysis Cycles 4 and 5 (2010)
    In:  CASI
    Details
    Publication Date: 2019-07-19
    Description: Life support systems are a critical part of human exploration beyond low earth orbit. NASA s Altair Lunar Lander team is pursuing efficient solutions to the technical challenges of human spaceflight. Life support design efforts up through Design Analysis Cycle (DAC) 4 focused on finding lightweight and reliable solutions for the Sortie and Outpost missions within the Constellation Program. In DAC-4 and later follow on work, changes were made to add functionality for new requirements accepted by the Altair project, and to update the design as knowledge about certain issues or hardware matured. In DAC-5, the Altair project began to consider mission architectures outside the Constellation baseline. Selecting the optimal life support system design is very sensitive to mission duration. When the mission goals and architecture change several trade studies must be conducted to determine the appropriate design. Finally, several areas of work developed through the Altair project may be applicable to other vehicle concepts for microgravity missions. Maturing the Altair life support system related analysis, design, and requirements can provide important information for developers of a wide range of other human vehicles.
    Keywords: Man/System Technology and Life Support
    Type: JSC-CN-22009 , International Conference on Environmental Systems; Jul 17, 2011 - Jul 21, 2011; Portland, OR; United States
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
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