FIELD: control of orientation and motion of center of mass of space vehicles. SUBSTANCE: method includes determination of rate of space vehicle orbit correction and parameters of its orientation and control forces and moments are formed by means of attitude-control engine; orientation of space vehicle is maintained by means of powered gyroscopes. Process of saturation of gyroscopes is tracked and predicted so that respective magnitudes of angular momentum in powered gyroscope system belong to field of preset magnitudes; according to the results thus obtained, time sequence and vectors of control moments of powered gyroscope unloading are determined for forming these moments, some attitude-control engines are disconnected or pair of attitude-control engines which are not used for correction of orbit are connected. Spacecraft control system includes units for determination of present, predicted and available magnitude of angular momentum vectors, comparison units and control parameters forming unit including selection of attitude-control engine for correction of orbit and pair of attitude-control engines for unloading the powered gyroscopes. EFFECT: increased rate of correction of spacecraft orbit at minimum control errors. 3 cl, 7 dwg
