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A Pumped Two-Phase Cooling System for Spacecraft
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English
Abstract
A pumped, two-phase heat-transport system is being developed for possible use for temperature control of scientific instruments on future NASA missions. As compared to a single-phase system, this two-phase system can maintain tighter temperature control with less pumping power. A laboratory model of the system has been built and tested. The measured heat transfer coefficients were approximately the same as in heat pipes, 220 Btu/hr-ft2-F, as compared to 25 Btu/hr-ft2-F for single-phase liquid flow. Heat sharing between experiments has been demonstrated wherein vapor generated in the cold plate of an active experiment was condensed in a cold, unhealed experiment. System stability has been observed. However, additional development is needed. The use of non-azeotropic mixtures of coolants appears especially promising as a simple way to determine exit quality and thus control the flow rates to prevent dryout.
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Citation
Ollendorf, S. and Costello, F., "A Pumped Two-Phase Cooling System for Spacecraft," SAE Technical Paper 831099, 1983, https://doi.org/10.4271/831099.Also In
References
- Almgren, D. W. et al. “The Use of a Thermal Utility with Space Platform Mounted Instruments” AIAA-81-1114
- Chen J. C. 1966 “Correlation for Solving Heat Transfer to Saturated Liquids in Convective Flow” Int. Eng. Chem. Process Design and Development 5 322
- Ellerbrook, H. H. Livingood, J. N. B. Straight D. M. “Fluid Flow and Heat Transfer Problem in Nuclear Rockets” NASA SP-20 Dec. 1962