FIELD: space.
SUBSTANCE: invention relates to space engineering and can be used in temperature control systems of instrument compartments. Thermal stabilization system of the spacecraft instrument compartment comprises a radiator-emitter and heat pipes. Radiator-emitter is made in the form of a cylindrical screen with circular heat pipes on the surface arranged along the edge of the screen. System providing thermal control of fuel elements includes low-temperature heat pipes arranged with a possibility for direct thermal contact with said elements and equipped with interface for connection with low-temperature heat pipe of a spacecraft for removing heat into space. Temperature control and adjustment system is equipped with electric heaters, connected with temperature sensors via control unit, located with electric heaters in heat-insulating gaps.
EFFECT: invention technical result is increase in accuracy and reliability of thermal control.
1 cl, 2 dwg
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