FIELD: space engineering; injection of payloads into geostationary orbits. SUBSTANCE: according to invention, satellite (L) is first injected by means of final stage (F) of launch vehicle into concealment circular orbit (C). This orbit is close to geostationary orbit (G) but is laid at adequate distance from it (about 300 km) to avoid contact with geostationary space objects. The, satellite is separated from final stage (L) and is brought into geostationary orbit (G) by means of its own power plant. Shifting may be effected by means of two-pulse scheme ((R1, R2)) where total change in orbital velocity is about 11 m/s. EFFECT: avoidance of space debris (engine stages); enhanced efficiency of injection of satellite into required orbit. 6 cl, 4 dwg
