TEMPERATURE CONTROL SYSTEM OF THE SPACECRAFT Russian patent published in 2012 - IPC B64G1/50 

FIELD: space and aeronautics.

SUBSTANCE: invention relates to thermal control system, mainly of telecommunications satellites. The system contains a liquid coolant, which includes collectors honeycomb panels, electrical pumping unit (ENA) and accumulator (SAC). SJC has a fluid chamber and cross connection, connected to the rest of the liquid circuit at the input to the ANE. From this cavity bellows separated gas chamber, dressed two-phase working fluid, and has a set on the bottom of the main and standby electric heaters. The gas chamber is located on the SJC maximum distance from the center of mass of the satellite along its longitudinal axis. In this connection the oral liquid SJC is located in the bottom of the gas cavity and the liquid in the bottom of the cavity facing towards the center of mass of the satellite, an additional electric heater. Electric power the latter is chosen in a certain temperature depending on the vapor coolant and working fluid, under which a quantity of vapor pressure in the fluid cavity pressure not lower than SAC cavitation ENA. Also takes into account the average temperature of the surrounding structural elements of SAC and the main electrical power (or reserve) electric heater of a gas cavity SJC. The technical result of the present invention is to maintain stable satellite thermal system performance. In orbit, in particular, in case of failure, bellows, or both heaters gas chamber, or simultaneously both the bellows and electric heaters gas cavity SJC.

EFFECT: stability of satellite cooling system performance.

1 dwg, 2 dwg