A Pumped Two-Phase Cooling System for Spacecraft

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.