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Design tradeoffs for a Space Station solar-Brayton power systemMass, area, and station-keeping propellant needs have been estimated for a typical system. And, although important criteria such as cost, Shuttle packaging, and erection/deployment schemes were not considered, the documented trends should aid in many of the design choices to be made. Effects on system characteristics were examined for: three heat storage salts with melting temperatures from 743 to 1121 K; parabolic and Cassegrainian mirrors; module power levels of 20 and 40 kW; and, alternate pumped-loop, tube-and-fin radiator configurations, with and without micrometeoroid armoring.
Document ID
19860040052
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Klann, J. L.
(NASA Lewis Research Center Cleveland, OH, United States)
Staiger, P. J.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
August 12, 2013
Publication Date
January 1, 1985
Subject Category
Spacecraft Propulsion And Power
Accession Number
86A24790
Distribution Limits
Public
Copyright
Other

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