FIELD: space technology.
SUBSTANCE: invention relates to the operation of high-power spacecraft, for example, telecommunication satellites with a repeater installed in an instrument compartment having ventilation openings and an active temperature control system (TCS). According to the method, when the working main fluid circuit (FC) of the TCS is depressurized, the spacecraft responder is immediately turned off, then the specified FC, and then the backup FC is activated. The responder is switched on if the design pressure in the instrument compartment after the expiration of the reserve of the compensating volume of the coolant from the liquid cavity of the compensator of the volume of the main FC is set less than the permissible for the responder devices. Otherwise, these devices are put into operation after the predicted complete effluence of the coolant from the main FC.
EFFECT: exclusion of the failure of the spacecraft responder of the spacecraft in case of depressurization of the main FC of the TCS.
1 cl, 5 dwg
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