Computer Science
Scientific paper
Oct 1989
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1989jspro..26..303e&link_type=abstract
Journal of Spacecraft and Rockets (ISSN 0022-4650), vol. 26, Sept.-Oct. 1989, p. 303-307.
Computer Science
Heat Pumps, Radiative Heat Transfer, Spacecraft Radiators, Carnot Cycle, Rankine Cycle, Refrigerators
Scientific paper
Use of two heat-rejection temperatures instead of one for a heat-driven heat pump is shown to reduce spacecraft waste-heat-radiator area and heat-rejection-system mass. The optimum high rejection temperature T(1) is shown to be somewhat less than Kerrebrock's rule, three-fourths of the heat source temperature T(H). The optimum low rejection temperature T(2) is 50-80 K above the cooling-load temperature T(C). General results are presented based upon the assumption of constant fractions of Carnot efficiency for the heat engine and refrigerator, and specific results are reported for a mercury-vapor engine coupled to an isobutane-R113 binary refrigerator. A single dimensionless grouping composed of ratios of equipment mass per unit power to radiator mass per unit area, and the ratios of the sink temperature and T(C) to T(H) are shown to be the major parameters characterizing the advantages of a spacecraft heat pump.
Edwards Kay D.
Richards R. F.
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