SPACE OBJECT TEMPERATURE CONTROL SYSTEM Russian patent published in 2003 - IPC

FIELD: space engineering; temperature control systems for spacecraft, mainly cryogenic stages. SUBSTANCE: proposed system ensures thermal conditions of object whose power (cooling effect) at launch complex is no less than in flight; proposed system also provides for autonomous active thermostatting of space object irrespective of modes of thermostatting and thermal state of payload. System includes closed hydraulic loop of intermediate heat-transfer agent combining at least one gas-to-liquid heat exchanger, heat-transfer engine motion activator and liquid flow rate regulator with control and monitoring units, sectional radiation heat exchanger with bypass hydraulic main, contact heat exchangers, sensors and drain and filling fittings; it is additionally provided with two-cavity liquid-to-liquid heat exchanger; one cavity of this heat exchanger is connected to bypass hydraulic main of sectional radiation heat exchanger and umbilical two-way hydraulic connector consisting of two parts which are hermetically connected together: first part of umbilical two-way hydraulic connector which is stationary is mounted on spacecraft and is connected with second cavity of two-cavity liquid-to-liquid heat exchanger by means of pressure and return hydraulic lines and second separable part of umbilical two-way hydraulic connector is used for mechanical securing on structural member of launch facility; it is provided with two pipe unions for connection of pressure and return lines of ground liquid system. EFFECT: increased cooling effect at launch complex; enhanced economical efficiency. 1 dwg