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The stand rig facility for thermo-vacuum testing of Space vehicles (STVT), described in this paper, is intended for simulation of: space vacuum, cold Space environment, electromagnetic radiation by the Sun and Earth, and Earth-albedo, as well as determination of influence of these factors on thermal regime of hardware and instruments of SV.

It's considered an approach to the elaboration of the tubing truss construction for payload accomodation on spacecraft which except support functions can fulfill the heat pipe function - to redistribute heat flows quickly and to equalize temperatures between heated and cold parts of the girder. The eventual thermal state of such constructions is analyzed in circumstances of space operation and in the course of on-Earth tests. Results of compatibility tests of casing material (aluminum alloy AMg-6) and heat-transfer agent (ammonia) at prolonged exploitation are presented.