FIELD: space and aeronautics.
SUBSTANCE: invention is referred to matching missions, in particular that of a manned space vehicle from an international space station. The mode involves active space object (ASO) final orbit insertion by a launch vehicle with deviations along the longitude of ascending node, and passive space object (PSO) orbit inclination. Thereby, ASO and PSO latitude argument orbits mismatch is prescribed. In orbits intersection in a direction orthogonal to plane, leading outs do maneuvers for the elimination of the stated deviations. Thereby, they form a speed pulse, which leads to the match of orbit planes of ASO and PSO.
EFFECT: reduced amount of time for matching of ASO and PSO without additional corrections of the orbit of PSO.
9 dwg, 1 dwg, 2 tbl
