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Design and Characteristics of a Dynamic Cooler for Space Use
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English
Abstract
The design and performance characteristics of a dynamic cooler are described. This unit can be used as a stand-alone refrigerator in spacecraft as well as within a fluid loop system that will provide active thermal control for payloads. The design of the cooler, featuring a vapor compression cycle, satisfies three basic requirements: (1) Heat removal rate at the source (payload or fluid loop) of about 0.8 kW at source temperatures of about 20° C, (2) maintaining the payload at a temperature level as low as -30° C with required heat removal rates of the order of a few tens of Watts, (3) heat rejection to a fluid with an initial temperature up to 45° C.
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Citation
Berner, F. and Savage, C., "Design and Characteristics of a Dynamic Cooler for Space Use," SAE Technical Paper 840964, 1984, https://doi.org/10.4271/840964.Also In
References
- Berner F. Oesch H. Goetz K. Savage C.J. “The Mechanical Design of a Vapor Compressor for a Heat Pump to be Used in Space” 16th Aerospace Mechanisms Symposium John F. Kennedy Space Center FL May 13-14, 1982 NASA Conf. Publ. 2221 1982
- Young J. Fannin Th. “Vapor Evolution Rates from Oil-Refrigerant Mixtures Following Expansion Through a Nozzle” Proceedings of the 1972 Purdue Compressor Technology Conf. July 25 - 27, 1972
- Netter G. Renner U. Eckhardt K. “Development of Surface Tension Tanks for Orbital Transfer Systems” CNES International Conference on The Future of Launchers in Europe January 19 - 21, 1982
- Berner F. Savage C.J. “Development of a Vapor Compression Heat Pump for Space Use” AIAA Paper 81-1113, AIAA 16th Thermophysics Conference June 23 - 25 Palo Alto, CA
- Berner F. Oesch H. Goetz K. “Development of a Reverse-Rankine Cycle Heat Pump for Space Use: Design and Testing of the Engineering Model of the Vapor Compressor” Swiss Federal Aircraft Factory, Doc.No. FO-1568 September 1981