FIELD: control of angular and orbital motion of spacecraft. SUBSTANCE: proposed method employs turns of solar batteries of spacecraft through different angles in solar flux for forming control actions which are determined by measured direction to Sun and preset increment of characteristic velocity of spacecraft. Method includes also measurement of kinetic moment in powered gyroscope system and determination of total kinetic moment of spacecraft. Angles of turn of solar batteries are determined taking into account maximum permissible difference between current generated by batteries and current consumed on board spacecraft. Besides that, saturation of powered gyroscopes from moments of forces of solar pressure is predicted and if necessary, some solar batteries are turned in advance through angles sufficient for relief of gyroscopes. Proposed method makes it possible to change direction of force relative to direction to Sun without special solar sail forming control actions continuously and ensuring considerable change in spacecraft characteristic velocity. EFFECT: enhanced efficiency. 4 dwg
