FIELD: attitude control systems; control of orbit of center of mass of spacecraft. SUBSTANCE: proposed method includes determination of required rate of correction of spacecraft orbit and maintenance of preset attitude by means of powered gyroscopes in the course of correction. Position of total moment of momentum of spacecraft relative to magnitudes in powered gyroscope system (S) is determined. Preset area (Sr) where total moment of momentum of spacecraft shall lie at the moment of completion of orbital correction is predicted. In case of saturation of gyroscopes, change of indicated moment of momentum of spacecraft till the moment of completion of their unloading is predicted. Prediction is made taking into account disconnection of pair of attitude-control motors for unloading. All operating attitude-control motors are taken into account from the end of unloading till completion of correction. Position of predicted total moment of momentum of spacecraft relative to preset area Sr and its present magnitude in area S of magnitude are checked simultaneously. If both these conditions are not fulfilled, orbit correction is continued at simultaneous unloading of gyroscope system. In case even one of conditions is fulfilled, unloading is discontinued. Provision is made for control system containing all units required for performing all operations of proposed method. EFFECT: reduced number of starts of attitude-control motors for unloading powdered gyroscopes; reduced consumption of propulsive mass and reduced effect on spacecraft orbit. 3 cl, 9 dwg
