METHOD OF INJECTION OF SEVERAL SATELLITES INTO NONCOMPLANAR ORBITS BY MEANS OF LUNAR GRAVITY FORCE

摘要

FIELD: performing active gravitational maneuvers of artificial satellites injected into initial orbits by one launch vehicle. SUBSTANCE: proposed method includes injection of one or several second satellites into their final orbits after separation of first satellite from launch vehicle. This injection includes first orbital maneuver of transfer of satellite to high-altitude elliptical orbit at apogee of 50000 to 400000 km. Larger half-axis of this orbit overlaps toroidal space formed by motion of sphere of gravitational lunar effect over its orbit. Second orbital maneuver includes transfer of satellite at perigee of said orbit to phased transfer lunar waiting orbit. Third maneuver includes correction of parameters of entry of satellite into sphere of lunar gravitational effect. Fourth maneuver includes change of perigee altitude and inclination of intermediate orbit of second satellite due to circumlunar fly-by and fifth maneuver completes transfer of second satellite into its final orbit. Orbit into which said first satellite is injected during its separation from launch vehicle may be low-altitude helio-synchronous orbit of transfer from geostationary (super-geostationary) orbit at low inclination. Final orbits of second satellites may be low-altitude circular orbits of different inclination. For performing orbital maneuvers, use is made of chemical and/or electrical rocket engines and flywheels (gyroscopes). EFFECT: enhanced economical efficiency. 11 cl, 7 dwg, 1 tbl