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A direct-interface, fusible heat sink for astronaut coolingAstronaut cooling during extravehicular activity is a critical design issue in developing a portable life support system that meets the requirements of a space station mission. Some of the requirements are that the cooling device can be easily regenerable and nonventing during operation. In response to this, a direct-interface, fusible heat sink prototype with freezable quick-disconnects was developed. A proof-of-concept prototype was constructed and tested that consists of an elastic container filled with normal tap water and having two quick-disconnects embedded in a wall. These quick-disconnects are designed so that they may be frozen with the ice and yet still be joined to the cooling system, allowing an immediate flow path. The inherent difficulties in a direct-interface heat sink have been overcome, i.e., (1) establishing an initial flow path; (2) avoiding low-flow freeze-up; and (3) achieving adequate heat-transfer rates at the end of the melting process. The requirements, design, fabrication, and testing are discussed.
Document ID
19900015976
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Lomax, Curtis (NASA Ames Research Center Moffett Field, CA, United States)
Webbon, B. W. (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
September 6, 2013
Publication Date
May 1, 1990
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
NAS 1.15:102835
A-90189
NASA-TM-102835
Meeting Information
Meeting: SAE/ICES 20th International Conference on Environmental Systems
Location: Williamsburg, VA
Country: United States
Start Date: July 9, 1990
Accession Number
90N25292
Funding Number(s)
PROJECT: RTOP 506-41-21
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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