SPACECRAFT TEMPERATURE CONTROL SYSTEM Russian patent published in 2009 - IPC B64G1/50 

FIELD: physics.

SUBSTANCE: invention relates to temperature control systems of telecommunication satellite devices. The temperature control system comprises a loop with biphase heat transfer fluid. This loop contains a hydraulic pump, collectors for instrument panels and radiator panels, as well as an accumulator, joined together by channels. The accumulator has a case with zones for holding gas and liquid phase of the heat carrier. The liquid phase zone is linked by a connecting pipe with the channel, directed to the input of the hydraulic pump. The heat carrier loop includes a flow switch, the first and second inputs of which are connected to lines running from outputs of collectors of two opened radiator panels. The common output of the flow switch is connected to the line running to the input of the hydraulic pump. In the initial position, the actuating element of the switch is set in the middle position. The opening radiator panels preferably have equal area of radiating surfaces with equal coefficient of absorption of solar and thermal radiation. Collectors of opened radiator panels lie in hydraulically parallel lines. Channels for circulating the heat carrier, lying in these lines, have identical geometrical dimensions and configuration. If the radiator panels are not opened, the flow switch directs the entire heat carrier through the collector whose panel is shadowed (incident solar radiation does not exceed permissible level). That way, operation temperature of devices remains below the maximum permissible value.

EFFECT: more reliable operation of temperature regulation system on orbit.

2 cl, 2 dwg