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Thermal management system options for high power space platformsThermal Management System (TMS) design options for a high power (75kWe), low earth orbit, multimodule space platform were investigated. The approach taken was to establish a baseline TMS representative of current technology, and to make incremental improvements through successive subsystem trades that lead to a candidate TMS. The TMS trades included centralized and decentralized transport, single-phase and two-phase transport, alternate working fluids, liquid loop and heat pipe radiators, deployed fixed, body mounted and steerable radiators, and thermal storage. The subsystem options were evaluated against criteria such as weight, TMS power requirement, reliability, system isothermality penalty, and growth potential.
Document ID
19850055515
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Sadunas, J. A.
(Rockwell International Corp. Seal Beach, CA, United States)
Lehtinen, A.
(Rockwell International Corp. Satellite Systems Div., Seal Beach, CA, United States)
Parish, R.
(NASA Johnson Space Center Houston, TX, United States)
Date Acquired
August 12, 2013
Publication Date
June 1, 1985
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 85-1047
Accession Number
85A37666
Funding Number(s)
CONTRACT_GRANT: NAS9-16782
Distribution Limits
Public
Copyright
Other

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