Experimentally Determined Overall Heat Transfer Coefficients for Spacesuit Liquid Cooled Garments

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dc.creatorBue, Grant
dc.creatorWatts, Carly
dc.creatorRhodes, Richard
dc.creatorAnchondo, Ian
dc.creatorWestheimer, David
dc.creatorCampbell, Colin
dc.creatorVogel, Matt
dc.creatorVonau, Walt
dc.creatorConger, Bruce
dc.creatorStein, James
dc.date.accessioned2015-10-29T17:42:03Z
dc.date.available2015-10-29T17:42:03Z
dc.date.issued2015-07-12
dc.descriptionBellevue, Washington
dc.descriptionGrant Bue, NASA Johnson Space Center, USA
dc.descriptionRichard Rhodes, NASA Johnson Space Center, USA
dc.descriptionIan Anchondo, NASA Johnson Space Center, USA
dc.descriptionDavid Westheimer, NASA Johnson Space Center, USA
dc.descriptionColin Campbell, NASA Johnson Space Center, USA
dc.descriptionCarly Watts, NASA Johnson Space Center, USA
dc.descriptionMatt Vogel,Jacobs Engineering Group, Inc., USA
dc.descriptionWalt Vonau, Jacobs Engineering Group, Inc., USA
dc.descriptionBruce Conger, Jacobs Engineering Group, Inc., USA
dc.descriptionJames Stein, Oceaneering Space Systems, USA
dc.descriptionThe 45th International Conference on Environmental Systems was held in Bellevue, Washington, USA on 12 July 2015 through 16 July 2015.
dc.description.abstractA Human-In-The-Loop Portable Life Support System (PLSS) 2.0 test has been conducted at NASA Johnson Space Center in the PLSS Development Laboratory from October 27, 2014, to December 18, 2014. These closed-loop tests of the PLSS 2.0 integrated with human subjects in the Mark III Suit at 3.7 psi to 4.3 psi above ambient pressure performing treadmill exercise at various metabolic rates from standing rest to 3000 BTU/hr (880 W). The bulk of the PLSS 2.0 was at ambient pressure, but effluent water vapor from the Spacesuit Water Membrane Evaporator and the Auxiliary Membrane Evaporator, and effluent carbon dioxide from the Rapid Cycle Amine were ported to vacuum to test performance of these components in flight-like conditions. One of the objectives of this test was to determine the overall heat transfer coefficient (UA) of the liquid cooling garment (LCG). The UA, an important factor for modeling the heat rejection of an LCG, was determined in a variety of conditions by varying inlet water temperature, flowrate, and metabolic rate. Three LCG configurations were tested: the Extravehicular Mobility Unit LCG, the Oceaneering Space Systems LCG, and the Oceaneering Space Systems auxiliary LCG. Other factors influencing accurate UA determination, such as overall heat balance, LCG fit, and the skin temperature measurement, will also be discussed.en_US
dc.format.mimetypeapplication/pdf
dc.identifier.otherICES-2015-330
dc.identifier.urihttp://hdl.handle.net/2346/64551
dc.language.isoengen_US
dc.publisher45th International Conference on Environmental Systemsen_US
dc.titleExperimentally Determined Overall Heat Transfer Coefficients for Spacesuit Liquid Cooled Garmentsen_US
dc.typePresentationen_US

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