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Engineering aspects of a thermal control subsystem for the 25 kW power moduleThe paper presents the key trade study results, analysis results, and the recommended thermal control approach for the 25 kW power module defined by NASA. Power conversion inefficiencies and component heat dissipation results in a minimum heat rejection requirement of 9 kW to maintain the power module equipment at desired temperature levels. Additionally, some cooling capacity should be provided for user payloads in the sortie and free-flying modes. The baseline thermal control subsystem includes a dual-loop-pumped Freon-21 coolant with the heat rejected from deployable existing orbiter radiators. Thermal analysis included an assessment of spacecraft orientations, radiator shapes and locations, and comparison of hybrid heat pipe and all liquid panels.
Document ID
19790067912
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Schroeder, P. E.
(Lockheed Missiles and Space Co., Inc. Sunnyvale, Calif., United States)
Date Acquired
August 9, 2013
Publication Date
January 1, 1979
Subject Category
Spacecraft Design, Testing And Performance
Meeting Information
Meeting: Intersociety Energy Conversion Engineering Conference
Location: Boston, MA
Start Date: August 5, 1979
End Date: August 10, 1979
Accession Number
79A51925
Distribution Limits
Public
Copyright
Other

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