FIELD: methods and systems for control of angular motion of spacecraft.
SUBSTANCE: proposed method includes measurement of parameters of spacecraft orientation at flight interval with the aid of control moment reactive flywheels, measurement of present vectors of reactive flywheels, determination of vector 
of total moment of momentum of spacecraft. If belongs to area S of its magnitudes, control of spacecraft is carried out with relief of reactive flywheel, otherwise control is carried out without relief of reactive flywheel. At control of spacecraft, "n" versions of change of signs of angular velocities of reactive flywheel are checked distributing the moment of momentum among reactive flywheels and keeping the parameters of orientation within permissible ranges. If this condition is observed, control of spacecraft is continued and is these conditions are not observed, respective "k" versions of change of angular velocities are noted. Upon completion of all "n" versions of change of signs of flywheel angular velocities, change of vector is predicted at subsequent flight interval separating vector from vector 
of moment of momentum of reactive flywheel system. According to prediction of , versions of change of signs of flywheel angular velocity change are determined at indicated interval and are compared with previous "k" versions. According to comparison, initial conditions are found for vector 
for observing definite conditions for change of signs of reactive flywheel angular velocities, belonging of magnitude to area S and allowance of spacecraft orientation parameters. Duration of flight interval may be corrected. For realization of this method, control system with reactive flywheel relief unit and other units with couplings is proposed.
EFFECT: avoidance of jump-type change of control moments of reactive flywheel; enhanced accuracy of maintenance of spacecraft orientation.
3 cl, 8 dwg, 1 tbl
