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Heat transfer in space power and propulsion systemsNASA's planned Space Station has projected power requirements in the 75-300 kW range; attention is presently given to the range of power system configurations thus far proposed. These are a silicon solar cell system incorporating regenerative fuel cell or battery storage, with a 10-year lifetime, a solar-dynamic power system with phase-change or regenerative fuel cell energy storage, and a combination of these two alternatives. A development status evaluation is also given for the propulsion systems that may be used by next-generation boosters. These include such novel airbreathing systems as turboramjets, air liquefaction cycle rockets, airturboramjet/rockets, and supersonic combustion ramjets.
Document ID
19860041754
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Hendricks, R. C.
(NASA Lewis Research Center Cleveland, OH, United States)
Simoneau, R. J.
(NASA Lewis Research Center Cleveland, OH, United States)
Dunning, J. W., Jr.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
August 12, 2013
Publication Date
February 1, 1986
Publication Information
Publication: Mechanical Engineering
Volume: 108
ISSN: 0025-6501
Subject Category
Spacecraft Propulsion And Power
Accession Number
86A26492
Distribution Limits
Public
Copyright
Other

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