SPACECRAFT THERMAL CONTROL SYSTEM Russian patent published in 2013 - IPC B64G1/50 

FIELD: transport.

SUBSTANCE: invention relates to thermal control systems of, mainly, telecommunication satellites. Proposed thermal control system comprise fluid circuit accommodating heat exchangers of instrumentation, radiator, hydraulic accumulator and electrically drive pump. Hydraulic accumulator includes gas chamber and fluid chamber separated therefrom by bellow and communicated with fluid circuit nearby inlet of aforesaid pump. Said gas chamber is partially filed with required amount of two-phase working medium (Freon 141b) and, additionally, with minimum necessary amount of nitrogen gas. Said amount is defined by equation of gas state incorporating minimum permissible pressure at pump inlet for pump cavitation-free operation. Other parameters represent maximum possible volume and minimum possible temperature of gas camber in spacecraft operation. Said parameters serve to ensure pump cavitation-free operation with cutting in hydraulic accumulator heater in spacecraft ascent or solar orientation in orbit.

EFFECT: higher efficiency without increase in weight.

2 dwg