Two-phase thermal control system with a spherical wicked reservo

Heat exchange – Intermediate fluent heat exchange material receiving and... – Liquid fluent heat exchange material

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165 41, 16510426, 244163, F28D 1502

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active

049571575

ABSTRACT:
A closed-loop two-phase thermal control loop includes an evaporator which receives subcooled coolant liquid from a condenser and heat from a source, and vaporizes the coolant to form coolant vapor. A condenser which is coupled to a thermal radiator accepts the coolant vapor and radiates thermally to space, thereby condensing the coolant vapor to liquid and subcooling the liquid. As the temperature of the environment surrounding the condenser radiator changes, the mass of vapor within the system tends to change, thereby causing undesirable pressure changes. A spherical wicked coolant reservoir is coupled to the liquid side of the closed thermal control loop. The reservoir is exposed foro thermal radiation and electrically heated, so that the temperature is thereby controlled in order to control vapor pressure within the reservoir. By controlling the reservoir vapor pressure, small pressure differentials are generated, which cause coolant liquid to be accepted or expelled while maintaining the closed loop pressure. The reservoir includes a wick for maintaining liquid coolant adjacent heat transfer areas, and also includes a standpipe supporting shaped vanes. The coolant adheres to the vanes and to the wick under zero-gravity conditions in a manner which allows at least partial simulation in an Earth gravity.

REFERENCES:
patent: 3212565 (1965-10-01), Esleeck
patent: 3923188 (1975-12-01), Lake, Jr.
patent: 3924674 (1975-12-01), Basiulis
patent: 4240405 (1980-12-01), French
patent: 4738304 (1988-04-01), Chalmers et al.
"Selection of a Surface-Tension Propellant Management System for the Viking 75 Orbiter" by Dowdy et al., published at pp. 549-558 of Journal of Spacecraft and Rockets, vol. 10, No. 9, Sep. 1973.
"Development and Qualification of the Propellant Management Systems for Viking 75 Orbiter" by Dowdy et al., published at pp. 133-140 of the Journal of Spacecraft and Rockets, vol. 14, No. 3, Mar. 1977.
"Design of a Two-Phase Capillary Pumped Flight Experiment", by Chalmers et al., published by SAE 18th Intersociety Conference on Environmental Systems, Jul. 11-13, 1988.

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