FIELD: orientation of spacecraft controlled by powered gyroscopes. SUBSTANCE: proposed method realized by means of reactive actuating members includes determination of required rate of correction of spacecraft orbit and maintenance of preset orientation of spacecraft by means of main and reserve powered gyroscopes. Measurement of vector of moment of momentum in powered gyroscope system is performed by known moment of inertia of spacecraft and by measured magnitudes of vector of spacecraft angular velocity and moment of momentum in powered gyroscope system. Spacecraft control system includes units for determination of present, predicted and available magnitudes of moment of momentum of main and reserve powered gyroscopes, comparison units and control parameter shaping unit. Proposed method ensures forming required vector of moment of momentum of spacecraft at the moment of completion of correction and minimizing number of switching-on of orientation engines for relief of powered gyroscopes. EFFECT: enhanced efficiency and reliability. 3 cl, 9 dwg
