SPACECRAFT TEMPERATURE CONTROL SYSTEM Russian patent published in 2000 - IPC

FIELD: space engineering; temperature control systems of communication satellites. SUBSTANCE: liquid passage of unit introduced anew is connected with liquid passage at inlet of first cut-off valve (before radiator) and at radiator outlet through hydraulic joints. This unit is provided with compensating device including bellows retainer, second cut-off valve with end valves connected to it, filter and Venturi tube. Outlet of first cut-off valve is communicated with liquid passage before third cut-off valve fitted after hydraulic joints at outlet of above-mentioned unit. Temperature control system has liquid passage for cooling the instruments of service systems located in line of electric pumping unit. Radiator consists of two sections (flat panels with double-sided radiation of heat). Halves of these sections are communicated through liquid passages. In the course of launching the spacecraft, panels are laid on service system compartment; in orbit, these panels are open in plane of minimum thermal fluxes. EFFECT: reduced mass of heat-transfer agent; enhanced operational reliability; increased of service life of temperature control system to 15.5 years. 5 cl, 2 dwg