For decades advanced spacesuit developers have pursued a regenerable, robust non-venting system for heat rejection. Toward this end, this paper investigates linking together two previously developed technologies, namely NASA's Spacesuit Water Membrane Evaporator (SWME), and Creare's Lithium Chloride Absorber Radiator (LCAR). Heat from a liquid cooled garment is transported to the SWME that provides cooling through evaporation. This water vapor is then captured by solid LiCl in the LCAR with a high enthalpy of absorption, resulting in sufficient temperature lift to reject heat to space by radiation. After the sortie, the LCAR would be heated up and dried in a regenerator to drive off and recover the absorbed evaporant. An engineering development prototype was built and tested in vacuum conditions at a sink temperature of 250 K. The LCAR was able to stably reject over 100 W over a 6 - 7-hour period. A conceptual design of a full-scale radiator is discussed. Excess heat rejection above the radiating capacity would be accomplished through venting of the evaporant.
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