A pumped two-phase cooling system for spacecraftA 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-sq ft-F, as compared to 25 Btu/hr-sq ft-F for single-phase liquid flow. Heat shearing between experiments has been demonstrated wherein vapor generated in the cold plate of an active experiment was condensed in a cold, unheated 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.
Document ID
19840046247
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Ollendorf, S. (NASA Goddard Space Flight Center Greenbelt, MD, United States)
Costello, F. A. (Frederic A. Costello, Inc. Herndon, VA, United States)