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The report presents the results of developing, ground testing and space exploitation of the systems providing the low temperature cooling of the onboard equipment of the spacecraft at stationary and elliptic orbits when it is arbitrarily oriented on the Sun and the planet. The complex under consideration has been developed at Lavochkin Association and consists of two systems which function eiter autonomously or jointly.

The mathematical model of capillary pump loop (CPL) with the capillary pump for a conditions of radiative heat removal in the condenser has been considered. The CPL calculation results of both functional characteristics are being analised with the presence of in flow heat from the outside sources and the influence of non-condensing gases and mass forces on the starting and dynamic characteristics of the installation. The heat transfer system is shown to possess controlling properties.