SPACECRAFT HEAT TRANSFER DEVICE Russian patent published in 2009 - IPC B64G1/50 F28D15/04 

FIELD: transportation; heating.

SUBSTANCE: proposed device has a closed two-phase line, filled with low-boiling heat carrier. The line comprises a condenser and an evaporator, joined by pipes. The condenser is built into the structure of the radiator panel and has an inner channel with smooth walls. The evaporator is joined to a hydraulic accumulator, thermally linked to the thermostat surface. Inside the evaporator there is a capillary pump, made in form of a main capillary structure, in contact with the inside of its central zone, with a concentric auxiliary capillary structure projecting from the hydraulic accumulator. Near the inner surface of the auxiliary structure with a gap between it and the butt end of the main capillary structure, there is a tail-piece of a pipe for transferring heat carrier from the condenser to the evaporator. Transfer is achieved through the hydraulic accumulator, the housing of which, with a capillary system fitted in it, is joined to the housing of the evaporator through an adapting pipe. The inner volume of the hydraulic accumulator in the zone of the auxiliary capillary structure and near its inner surface has an absorbent with cells smaller than cells in the rest of the zone. Lastly, a pipe section is laid for transferring heat carrier from the condenser to the evaporator, made in form of a spiral. On the outer surface of the hydraulic accumulator, near the evaporator, a variable power electric heater is fitted.

EFFECT: stability of operating characteristics of the device for long periods of operation in outer space conditions.

2 dwg