FIELD: cosmonautics. SUBSTANCE: proposed method consists in determination of parameters of turn from preset moment of time, acceleration of space vehicle, its free rotation and deceleration. At stage between acceleration and deceleration, angle of turn is continuously measured between present and preset final angular positions and angle of turn between present and initial angular positions is measured; at moment when these angles are equal, present angular position is noted and is compared with designed position at the same moment; then parameters of sighting position are determined and angular motion of vehicle is corrected for taking the sighting position. Then angle of turn between present and noted angular positions is measured. At moment when angle of turn exceeds angle of deflection from final position by more than preset number of times, angular position of vehicle is corrected. Correction consists in determination of designed magnitude of angular momentum required for shifting the space vehicle (at its free rotation) from present angular position to preset final angular position and applying the pulse control moment to the space vehicle till actual angular moment is determined automatically from solving the boundary-value problem of orientation by method of successive approximation at prediction. EFFECT: enhanced efficiency. 2 dwg
