FIELD: space engineering; injection of artificial satellite into geostationary orbit. SUBSTANCE: proposed method includes separation of spacecraft from launch vehicle in initial elliptical orbit and injection of it multi-turn spiral trajectory of transit flight in desired orbit. For forming this trajectory, use is made of set of electric rocket engines at high specific impulse working in continuous mode. Time of first phase of transit flight provides for increase of perigee altitude of orbit and evolution either towards increase or decrease of apogee altitude and reduction of error of inclination of present (osculating) orbit . During second phase of transit flight, apogee altitude is reduced and evolution of perigee altitude is performed and error of inclination is decreased. Transit flight is completed at moment of coincidence of parameters of intermediate orbit with those of final desired orbit. System proposed for realization of this method, includes means for control of orientation of engine thrust vectors (plasma, electric-arc or ion engines) in respective inter-orbital planes. EFFECT: reduction of time required for performing inter-orbital flight; enhanced efficiency and safety; facilitated procedure. 18 cl, 15 dwg
