Pump, and earth-testable spacecraft capillary heat transport loo

Heat exchange – With vehicle feature

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16510423, 16510426, 16510424, 417 65, 251 65, 1375195, F28F 2700

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058163131

ABSTRACT:
A spacecraft includes heat-generating payload equipment, and a heat transport system with a cold plate thermally coupled to the equipment and a capillary-wick evaporator, for evaporating coolant liquid to cool the equipment. The coolant vapor is coupled to a condenser and in a loop back to the evaporator. A heated coolant reservoir is coupled to the loop for pressure control. If the wick is not wetted, heat transfer will not begin or continue. A pair of check valves are coupled in the loop, and the heater is cycled for augmentation pumping of coolant to and from the reservoir. This augmentation pumping, in conjunction with the check valves, wets the wick. The wick liquid storage capacity allows the augmentation pump to provide continuous pulsed liquid flow to assure continuous vapor transport and a continuously operating heat transport system. The check valves are of the ball type to assure maximum reliability. However, any type of check valve can be used, including designs which are preloaded in the closed position. The check valve may use any ball or poppet material which resists corrosion. For optimum performance during testing on Earth, the ball or poppet would have neutral buoyancy or be configured in a closed position when the heat transport system is not operating. The ball may be porous to allow passage of coolant vapor.

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"Development of a Rugged Hybrid Two-Phase Transport Loop", by Baumann et al., published by American Institute of Aeronautics.
Astronautics, No. AIAA 92-2866, published Jul. 6-8, 1992 at the AIAA 27th Thermophysics Conference, Nashville, TN.

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