Closed cycle, space-based heat rejection systems depend solely on radiation to achieve their heat dissipation function. Since the payload heat rejection temperature is typically 50 K above that of the radiation sink in near earth orbit, the size and mass of these systems can be appreciable. Size (and potentially mass) reductions are achievable by increasing the rejection temperature via a heat pump. Two heat pump concepts were examined to determine if radiator area reductions could be realized without increasing the mass of the heat rejection system. The first was a conventional, electrically-driven vapor compression system. The second is an innovative concept using a solid-vapor adsorption system driven by reject heat from the prime power system. The mass and radiator area of the heat pump/radiator systems were compared to that of a radiator only system to determine the merit of the heat pump concepts. Results for the compressor system indicated that the mass minimum occurred at a temperature lift of about 50 K and radiator area reductions of 35 % were realized. With a radiator specific mass of 10 kg/m2 the heat pump system is 15 % lighter than the radiator only baseline system. The complex compound chemisorption systems showed more promising results. Using water vapor as the working fluid in a single stage heat amplifier resulted in optimal temperature lifts exceeding 150 K. This resulted in a radiator area reduction of 83 % with a mass reduction of 64 %.
Heat pump augmented radiator for low-temperature space applications
Mit Waermepumpe verstaerkter Radiator fuer Niedertemperatur-Weltraumanwendung
IECEC, 23rd Intersociety Energy Conversion Engineering Conf., ASME ; 1 , Aug ; 379-383
1988
5 Seiten, 9 Bilder, 7 Quellen
Conference paper
English
Heat pipe technology development for high temperature space radiator applications
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