FIELD: combined control of attitude and motion of center of mass of spacecraft. SUBSTANCE: present total angular momentum of spacecraft 
is determined according to proposed method by vector of angular momentum in powered gyroscope system and by vector of angular velocity of spacecraft. Electric rocket jet engines are selected at projections of thrusts on preset direction of orbit correction and are grouped in all probable combinations. Change of vector 
is predicted for each group at definite interval of correction. Besides that, effect of external magnetic, gravitational and solar light fluxes on spacecraft is taken into account in addition to effect of engines. Moment and interval of time of arrival of this vector 
at boundary of permissible magnitudes are determined. During this interval magnitudes of correction pulses of each group of engines are determined and group with maximum pulse is included into action. In the course of correction of orbit, difference of predicted and present magnitudes of vector 
is tracked for this group. Correction is continued if modulus of this difference is lesser than permissible magnitude, otherwise correction is discontinued and present moment of time is considered to be initial moment for repeated selection of group of engines. EFFECT: enhanced accuracy of control; reduced consumption of working medium; low effect of gyroscope relief on SC orbit. 3 dwg
