FIELD: space; heat exchange.
SUBSTANCE: invention relates to thermal control systems of spacecraft. Method comprises measuring temperature in zones of radiation panels (RP) with temperature sensors, maintaining temperature in RP zones within permitted range by changing temperature by means of temperature regulators, breaking period of revolution of spacecraft around the Earth into fixed time intervals defined by orientation of spacecraft relative to the Sun and planets. Determined by certificate data arranged in zones of service systems permissible range of temperatures, maximum possible temperature error in installation places of four temperature sensors in each zone. Breaking down each of fixed time intervals of period of revolution of spacecraft around the Earth in each zone into local time intervals, in which are observed identical temperature conditions are repeating on orbit passes. During flight of spacecraft, measuring and transmitting to a ground-based system for control of temperature values of each zone and current consumed by heat controllers.
EFFECT: higher efficiency and durability of spacecraft thermal control system.
1 cl, 6 dwg
