FIELD: attitude control systems; control of orbit of center of mass of spacecraft. SUBSTANCE: proposed method includes determination required magnitude of rate of correction of spacecraft orbit and maintenance of preset attitude of spacecraft by means of powered gyroscopes in the course of correction. Preset area where vector of moment of momentum of spacecraft shall lie at the moment of completion of orbital correction is predicted at this. At absence of saturation in gyroscope system, accumulation of moment of momentum of spacecraft is predicted from the present moment of correction by steps in time taking into account disconnection of one of attitude-control motors or connection of pair of such motors. Magnitudes of vector of moment of momentum of spacecraft predicted at steps are summed-up with its preset magnitude. If total vector lies in preset area, control moment are applied to spacecraft from the moment of termination of prediction by disconnecting one of the above-mentioned motors. If these moments are not unloading moments, pair of motors not used in correction of orbit whose moment has maximum projection on direction opposite to vector of moment of momentum of spacecraft are started. No motor is disconnected at this. Provision is also made for control system including units required for realization of all operations. EFFECT: minimization of starts of attitude-control motors for unloading powered gyroscopes; reduced consumption of propulsive mass; reduced effect on spacecraft orbit. 3 cl, 8 dwg
