Future long term missions in space require the development of a thermal management system capable of collecting, transporting and rejecting waste heat from various components in the nominal temperature range of 0-100°C. A summary of four, two-phase heat transport systems currently under consideration at NASA-JSC is presented. The comparative merits of four systems, which include a mechanically pumped two-phase loop, a capillary pumped loop, an osmotic pumped loop and a loop using a biomorph pump, are presented based on a comprehensive literature review and contractor reports supplied by NASA-JSC.A recommended conceptual design for a thermal utility using a capillary pumped loop is proposed along with an evaluation of its strengths and weaknesses. System start up and control are discussed and areas of continued investigation are identified.
Concept Evaluation of Four Thermal Utility Systems for Low Orbit Spacecraft
Sae Technical Papers
Intersociety Conference on Environmental Systems ; 1983
1983-07-11
Conference paper
English
Concept evaluation of four thermal utility systems for low orbit spacecraft
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