This paper describes current progress on the development of an innovative heat pump system for spacecraft thermal control. Increasingly stringent thermal requirements are projected for future spacecraft. Compliance with these requirements necessitates the development of thermal control techniques with capabilities far exceeding those in current use. A fundmental consideration is a heat transport and thermal rejection system capable of accommodating large heat loads, high energy densities, long transport distances, variable duty cycles, and varying operational parameters. Previous Mainstream efforts have indicated the significant benefits in terms of reductions in system mass (2-28 %), reduction in system complexity, and reduction in radiator area (28-58 %) that are possible with a heat pump loop (HPL) spacecraft thermal management system. This paper discusses the thermal performance benefits of an electrically powered HPL system.
Thermal response of heat pump augmented spacecraft heat rejection systems
Thermische Beanspruchung eines Wärmeentzugssystemes für Raumfahrzeuge mit Wärmepumpenunterstützung
Advances in Heat Pumps 1989, The Winter Annual Meeting of the ASME ; AES-7 , Dec ; 67-72
1989
6 Seiten, 5 Bilder, 14 Quellen
Aufsatz (Konferenz)
Englisch
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