THERMAL CONTROL SYSTEM OF SPACECRAFT Russian patent published in 2015 - IPC B64G1/50 

FIELD: heating.

SUBSTANCE: invention relates to a temperature control system (TCS) of the on-board equipment of the spacecraft. TCS is made on the basis of a two-stage heat pump. The on-board instruments are mounted on temperature-controlled panels (1) and give up heat through the steam chambers of the panels to the evaporators (5) of the working body (WB) of the lower cascade (freon). The WB enters to the input of the compressor (2), then - to the intermediate heat exchanger (3) and through the expander (4) to the evaporator (5). In the heat exchanger (3) WB condenses and gives up heat to WB of the upper cascade (a mixture of gases He and Xe). The latter is heated in the regenerator (9) and passes to the input of the compressor (7). After that WB of the upper cascade enters the end heat exchanger (8), where transmits heat to the circuit of radiation heat exchanger (13), then enters to the regenerator (9) and through the expander (10) to the condenser (3). WB of the radiator circuit is a liquid metal coolant pumped by electromagnetic pump (12). After receiving heat in the exchanger (8) from WB of the upper cascade, this coolant gives it to vaporisation zones of heat pipes - the main radiating elements of the heat exchanger (13). Cooling of the compressor-expander turbine unit of each cascade is performed by WB of this cascade through the tubes wound on the walls of the turbine unit casing.

EFFECT: increasing the temperature of the radiation heat exchanger (13), and thus - the improvement of its weight and size characteristics.

1 dwg