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a pumped, two-phase flow heat transport system for orbiting instrument payloadsA pumped two-phase (heat absorption/heat rejection) thermal transport system for orbiting instrument payloads is investigated. The thermofluid characteristics necessary for the system design are discussed. A preliminary design with a series arrangement of four instrument heat stations and six radiators in a single loop is described in detail, and the total mass is estimated to be 134 kg, with the radiators, instrument heat stations, and fluid reservoir accounting for approximately 86, 24, and 12 kg, respectively. The evaluation of preliminary test results shows that the system has potential advantages; however, further research is necessary in the areas of one-g and zero-g heat transfer coefficients/fluid regimes, fluid by-pass temperature control, and reliability of small pumps.
Document ID
19810054680
Document Type
Conference Paper
Authors
Fowle, A. A.
(Arthur D. Little, Inc. Cambridge, MA, United States)
Date Acquired
August 11, 2013
Publication Date
June 1, 1981
Subject Category
SPACECRAFT DESIGN, TESTING AND PERFORMANCE
Report/Patent Number
AIAA PAPER 81-1075
Meeting Information
Thermophysics Conference(Palo Alto, CA)
Funding Number(s)
CONTRACT_GRANT: NAS5-26350
Distribution Limits
Public
Copyright
Other