Heat transfer system having a flexible deployable condenser tube

Heat exchange – Movable heating or cooling surface

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Details

165 41, 16510426, 16510427, 244163, F28D 1502, B64G 150

Patent

active

051179016

ABSTRACT:
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.

REFERENCES:
patent: 3152260 (1964-10-01), Cummings
patent: 4040478 (1977-08-01), Pogson et al.
patent: 4765396 (1988-08-01), Seidenberg
patent: 4869313 (1989-09-01), Fredley
patent: 5016705 (1991-05-01), Bahrle et al.

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