FIELD: space engineering; temperature control systems of spacecraft with radiating radiators operation of spacecraft designed for protracted flights on orbits. SUBSTANCE: method consists in change of ratio of flow rate of heat-transfer agent between radiating radiator and bypass main depending on temperature of setting, internal and external thermal loads during operation of spacecraft at constant internal and external thermal loads; proposed method includes also measurement of temperature at radiating radiator inlet and outlet, after which total flow rate in system is set according to the following relationship: 
where Δτ is time of one pitch of change-over of heat-transfer agent flow regulator; τc-o is total time of change-over of heat-transfer agent flow regulator; tset is heat-transfer flow regulator setting time; ΔT is temperature control range; trad = (trad.in+trad.out)/2 is average temperature of radiator in orbit at constant external and internal loads exerted on system; trad.in is steady magnitude of heat-transfer agent temperature at radiator inlet; trad.out is steady magnitude of heat-transfer agent temperature at radiator outlet; Q is magnitude of fixed internal heat release of spacecraft; kF is characteristics of radiator (fixed magnitude); then, radiator is kept at subsequent similar modes of functioning of spacecraft. EFFECT: reduced power requirements; avoidance of alternating loads; enhanced accuracy of temperature control. 1 dwg
