FIELD: space engineering; reaction control systems of orientation and motion of center of mass of spacecraft. SUBSTANCE: system includes correcting or vernier electrical rocket engines and orientation and stabilization thermal rocket engines which are provided with heat accumulator; control system is additionally provided with temperature control unit. These engines may be extended to distance of 2 to 5 diameters of spacecraft case. Thermal engines may be combined with cruising or vernier engines by working medium. EFFECT: enhanced economical efficiency; increased life of spacecraft. 4 cl, 2 dwg
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