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Thermal Sink for the Advanced Extravehicular Mobility Unit Portable Life Support System
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English
Abstract
A study is being conducted to design, develop, fabricate, integrate, and test a preprototype coolant loop subsystem for an advanced extravehicular mobility unit portable life support system for Space Station Freedom. The overall function of the coolant loop is to remove metabolic and equipment heat loads and provide a comfortable thermal environment for a crewperson during extravehicular activity. The heat loads are transported by water circulating through a liquid-cooled ventilation garment. The thermal environment is regulated using thermal capacitive and/or radiative control. After use, the system must be capable of regenerating relatively rapidly. The key component in the coolant loop is the thermal sink, which is a completely nonventing unit comprising cold-plate heat exchangers, a radiator to reject a fraction of the generated heat load, and a regenerable thermal storage unit to absorb the remaining heat load. No embedded thermoelectric devices are required.
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Citation
Strumpf, H., "Thermal Sink for the Advanced Extravehicular Mobility Unit Portable Life Support System," SAE Technical Paper 891581, 1989, https://doi.org/10.4271/891581.Also In
References
- Pre-Prototype Ventilation Loop Subsystem for the Advanced EMU PLSS LESC SOW PRJ03TECHX688 July 1988
- Dunaway, B. Automatic Liquid and Ventilation Cooling Garment Control Algorithm Final Test Report NASA Johnson Report CTSD-SS-176 39 November 22 1988
- Strumpf, H. J. Coombs M. “Solar Receiver for the Space Station Brayton Engine,” Trans. ASME J. of Eng. for Gas Turbines and Power 110 295 300 1988
- Hale, D.V. Hoover M.J. O'Neill M.J. Phase Change Materials Handbook NASA CR-61363 September 1971
- Thermal Capacitor for Skylab AiResearch Report 72-8440 June 1972