SPACECRAFT THERMAL CONTROL SYSTEM

摘要

FIELD: transport.SUBSTANCE: invention relates to thermal control systems (TCS) of spacecrafts (SC), predominantly telecommunication satellites. TCS comprises two independent on-board circulation paths identical in composition with heat carrier, which are arranged next to each other in honeycomb panels (or on them). Each one of paths comprises inlet and outlet fluid connectors for connection with fluid connectors of detachable TCS unit. In the latter, liquid-liquid heat exchanger is installed which has cooling capacity exceeding its required value for one path not less than by 2.1-2.2 times. During SC electric testing the detachable unit is connected to one of circulation paths according to SC testing program. At the same time the other path is looped back by liquid path having the same hydraulic resistance as liquid path of detachable unit.EFFECT: simplification of TCS detachable unit design, reducing its dimensions and mass which simplifies mounting and dismantling detachable unit on SC board.3 dwg