Development and testing of a prototype low-lift heat pump for spacecraft thermal control

Details Development and testing of a prototype low-lift heat pump for spacecraft thermal control Development and testing of a prototype low-lift heat pump for spacecraft thermal control

Feb 2001

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2001aipc..552..271g&link_type=abstract

Space Technology and Applications International Forum - 2001. AIP Conference Proceedings, Volume 552, pp. 271-276 (2001).

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Spaceborne And Space Research Instruments, Apparatus, And Components, Environmental Effects On Instruments

Scientific paper

Active thermal control systems are currently being considered for high-power spacecraft applications. Analysis has shown that a low-lift heat pump thermal control system has lower radiator area and system mass than other types of active thermal control systems, such as pumped loops. Therefore, the development and demonstration of a low-lift heat pump was undertaken. This paper will describe the development and demonstration of a low-lift heat pump for high-power spacecraft thermal control. The low-lift heat pump was designed to provide 25 kW of cooling at 303.15 K and transport this waste heat to a radiator for heat rejection. To accomplish this, a demonstration heat pump with an evaporation temperature of 298.15 KC and a condensing temperature of 301.45 K was designed and built. This paper will present detailed information on the design and fabrication of the system and its components, including working fluid selection, compressor design and fabrication, evaporative cold plate design and fabrication, condenser design, expansion device selection, and future testing plans. .

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