FIELD: space engineering; manufacture and updating of temperature control systems of communication satellites. SUBSTANCE: proposed system includes liquid line filled with heat carrier, volume compensator with bellows, liquid cavity and liquid line of detachable unit (dismantled before launch).Line is communicated with electric pump and liquid cavity is communicated with payload cooling passage. Cooling passage of detachable unit is provided with heat exchanger and two compensating units with bellows. Mounted in bottom of volume compensator bellows is permanent magnet and hermetically-sealed reed relays are mounted on housing on side of liquid cavity. When all hermetically-sealed reed relays are open, bottom of bellows of second compensating unit is set in motion till one of hermetically-sealed relays closes; actual volume of gas cavity of volume compensator is found according to number of relay (by means of graduation scale) and is compared with required magnitude. Proposed system retains its efficiency during 15.5 years. EFFECT: simplified construction; reduced mass of system; improved quality; enhanced reliability. 3 cl, 3 dwg
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Authors
Dates
2003-08-10—Published
2001-04-27—Filed