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Human life support during interplanetary travel and domicile. III - Mars expedition system trade studySeveral alternative configurations of life-support systems (LSSs) for a Mars missions are compared analytically on a quantitative basis in terms of weight, volume, and power. A baseline technology set is utilized for the illustrations of systems including totally open loop, carbon dioxide removal only, partially closed loop, and totally closed loop. The analytical model takes advantage of a modular, top-down hierarchical breakdown of LSS subsystems into functional elements that represent individual processing technologies. The open-loop systems are not competitive in terms of weight for both long-duration orbiters and short-duration lander vehicles, and power demands are lowest with the open loop and highest with the closed loop. The closed-loop system can reduce vehicle weight by over 70,000 lbs and thereby overcome the power penalty of 1600 W; the closed-loop variety is championed as the preferred system for a Mars expedition.
Document ID
19920039130
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Seshan, P. K.
(Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Ferrall, Joseph F.
(Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Rohatgi, Naresh K.
(JPL Pasadena, CA, United States)
Date Acquired
August 15, 2013
Publication Date
July 1, 1991
Subject Category
Systems Analysis
Report/Patent Number
SAE PAPER 911323
Accession Number
92A21754
Distribution Limits
Public
Copyright
Other

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