There is performed a brief review of results in analysis of a problem for space flight from a low orbit of the Earth satellite to geostationary orbit GSO using Lunar Gravity Assist. An algorithm developed for determination of the flight trajectories is presented for an impulse approach. Using this algorithm and a computer software developed, there are constructed several sets of the trajectories for this flight. These are the trajectories for launch from Baikonur and Plesetsk, for flight in various years, for the Moon flyby near both ascending node of its orbit on the Earth equator and descending one, for changing the Earth-Moon flight time in an admissible range. An analysis of correction properties of these trajectories is carried out. There are evaluated variations of the trajectories parameters via the launch errors. There are determined derivatives of the corrected parameters with respect to components of the correction velocity impulse. There are evaluated the magnitudes of the correction velocity impulses along the trajectories.

spacecraft, geostationary orbit GSO, spacecraft launch to GSO, optimal space trajectories, lunar gravity assist, trajectory correction

Theoretical and applied problems of mechanics