FIELD: mechanical engineering.
SUBSTANCE: invention relates to thermal control systems (TCS) of mainly powerful telecommunication spacecrafts (SC). Spacecraft loop heat pipe consists of evaporator with compensator, capillary structures, heat exchanger, condenser and tubes of steam line and condensate line, which are located in open space. Wall thickness of steam line and condensate line is determined by ratios of hydrogen, nitrogen and hydrazine gases.
EFFECT: providing trouble-free operation of the TCS and spacecraft as a whole, as well as reducing the weight of heat transfer devices.
3 cl, 2 dwg
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