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Spacesuit Evaporator-Absorber-Radiator (SEAR)For decades advanced spacesuit developers have pursued a regenerable, robust nonventing 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 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. A engineering development prototype was built and tested in vacuum conditions at a sink temperature of 250 K. The LCAR was able to stably reject 75 W over a 7-hour period. A conceptual design of a full-scale radiator is proposed. Excess heat rejection above 240 W would be accomplished through venting of the evaporant. Loop closure rates were predicted for various exploration environment scenarios.
Document ID
20120004284
Acquisition Source
Johnson Space Center
Document Type
Conference Paper
Authors
Hodgson, Ed
(Hamilton Sundstrand Space Systems International, Inc. Windsor Locks, CT, United States)
Izenson, Mike
(Creare, Inc. Hanover, NH, United States)
Chan, Weibo
(Creare, Inc. Hanover, NH, United States)
Bue, Grant C.
(NASA Johnson Space Center Houston, TX, United States)
Date Acquired
August 25, 2013
Publication Date
January 1, 2012
Subject Category
Man/System Technology And Life Support
Report/Patent Number
JSC-CN-26017
Meeting Information
Meeting: 42nd International Conference on Environmental Systems
Location: San Diego, CA
Country: United States
Start Date: July 15, 2012
End Date: July 19, 2012
Sponsors: American Inst. of Aeronautics and Astronautics
Distribution Limits
Public
Copyright
Public Use Permitted.
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