FIELD: spacecraft attitude control and mass motion systems.
SUBSTANCE: proposed method includes maintenance of spacecraft attitude by means of powered gyroscopes in the course of correction of orbit by means of jet attitude-control jet engines. Prediction is made for estimation of position of vector of spacecraft momentum of momentum in region of its magnitudes for present and final moments of correction time. Deviation of measured magnitude of this vector from predicted value is maintained within limits of preset region. In case vector does not belong to these regions center of spacecraft mass is shifted depending on configuration of spacecraft inertia tensor and control moment created by attitude-control jet engines. Upon completion of correction, spacecraft center of mass is restored. Proposed method makes it possible to form preset vector of spacecraft moment of momentum at the moment of completion of correction and to minimize number of starts of attitude-control engines in performing the flight program which is necessary for relief of load of powered gyroscopes.
EFFECT: maximum rate of correction at minimum errors of control and minimum consumption of propulsive mass of jet engines.
2 dwg
