SYSTEM OF SPACE OBJECT THERMAL CONTROL Russian patent published in 2010 - IPC B64G1/50 

FIELD: transport.

SUBSTANCE: invention relates to facilities for providing required thermal conditions of spacecrafts. Device contains interconnected closed circulation heating and cooling loops, fluid flow regulators, temperature sensors and control system. Flow control regulator is made with stepper motor, and sensors are electrically connected with this regulator via control system. The heating loop contains interconnected hydraulic unit and differential pressure sensor, gas-liquid and coiled heat exchangers, heat sinks, hydraulic compensator and drain valve. In the cooling loop, hydraulic unit and differential pressure sensor are installed in series and interconnected by pipelines. The system is equipped with switch regulator which is connected in series with fluid flow regulator. The first outputs of these regulators are connected to cooling loop, and the second outputs are connected to heating loop. The third output of switch regulator interacts with input of fluid flow regulator; herewith temperature sensors are installed on heating loop pipeline. Each of the sensors is electrically connected with switch regulator and fluid flow regulator via control system.

EFFECT: higher reliability of space object thermal control system during long-termed operation.

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