Heat transfer system having a flexible deployable condenser tube
OwnerBrent A. Cullimoreinventor
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OwnerBrent A. Cullimoreinventor
Estimating the term…
A two-phase capillary pumped loop heat transfer system adapted primarily for use on space vehicles, includes a wickless condenser tube which receives gaseous phase working fluid from the evaporator capillaries, rejects heat from the working fluid to a heat sink (e.g. outer space) and thereby converts the gaseous phase working fluid to its liquid phase, and returns the liquid phase working fluid to the evaporator to complete the thermal cycle. A portion of the condenser tube is supported by a rigid radiator structure external to the spacecraft. At least a portion of the condenser tube is deformable to permit the radiator structure to be deployed from a first predetermined position to a second predetermined position with respect to the spacecraft. The deformable segment of the condenser tube can be formed into a helical coil used as a spring to assist deployment of the radiator panel.
A closed-loop heat transfer system adapted to transfer heat from a heat source within a housing to an external heat sink by means of a working fluid having a liquid phase and a gaseous phase, said heat transfer system comprising:
Dependencies are inferred from the claim text.