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Description of design principles of thermocontrol system for small subsatellites “Magion - 4, 5” is presented. Passive type of system is intended to support the temperature level (-10…50) °C in inner volume of equipment compartment at solar subsatellite orientation and in temporary Earth shadow. Heat energy balance of object at necessary temperature range is provided by utilization of radiating surfaces with defined areas, by thermal connection of hot and cold subsatellite parts and by adaptation of constructive subsatellite elements to solve thermal tasks. Stages of heat pipe design, its development and testing separately and installed into object, thermovacuum test of subsatellite are presented. Initial time range of flight operation of thermocontrol system is analyzed as well.

The substantiation of heat pipe usage in passive radiative cooling systems on temperature level (190…240) K for space optical sensors is presented. Heat pipes can be sound practice like heat conducting lines between sensor and radiator particularly at distances more 0.2 m and irreplaceable at distances (0.5…2) m. Embedding heat pipe with radiator allows to create the uniform temperature basis in case of several sensors connection to single radiator and to improve radiator efficiency. It is analyzed approach to design of thermocontrol and cooling radiative systems with heat pipes to reduce sensitiveness to external light disturbances and to enlarge area of radiative system application. The results of design, thermovacuum test and flight operation of thermocontrol radiative system samples are under discussion as well.