FIELD: space engineering; spacecraft temperature control systems; compensation for change in volume of liquid of heat-transfer agent. SUBSTANCE: device for maintenance of pressure of heat-transfer agent in loop of spacecraft temperature control system has hermetic housing with tubular heater, phase separators, heat-transfer agent supply and discharge branch pipe, vapor discharge branch pipe with radially mounted thermal cellular structures which are in contact with inner surface of housing and with surface of tubular heater combined in sections which form spatial lattice- type structure dividing working volume of device into equal zones. Tubular heater is secured as cantilever on one of bottoms of heater; its outer surface is made in form of developed capillary structure; tubular electric heater, temperature sensors and thermal tube whose length is equal to length of tubular heater are mounted inside it at thermal contact with its inner surface. Phase separators are made in form of perforated tubes enclosed in envelopes which are in contact with surface of housing; they are made from material of capillary structure and are smoothly located in space of device in areas where sections of radial thermal cellular structures approach surface of housing and are combined with heat-transfer agent supply and discharge branch pipe by means of collector. Vapor discharge branch pipe combines systems of vapor discharge tubes together with collector. Developed capillary structure of tubular heater surface is made in form of cut grooves or envelope made from material of capillary structure. EFFECT: improved service characteristics; enhanced reliability; increased guaranteed service life; reduced mass and overall dimensions. 2 cl, 5 dwg
