SPACECRAFT TEMPERATURE CONTROL SYSTEM

摘要

FIELD: space engineering; temperature control systems of communication satellites. SUBSTANCE: input of standby flow regulator of proposed system is communicated via sensitive elements of main and auxiliary thermoregulators with output of liquid instrument panel. Second output of standby thermo-regulator is connected with input and first output is connected with first output of main thermo-regulator and then with inlet of bypass valve. Second and first outlets of said valve are communicated with inlet of satellite radiator through liquid passage of panel mounted on satellite and directed to Sun. EFFECT: simplified construction; reduced power requirements. 3 dwg