Abstract. The necessity of optimal (relative to the speed of action) control angular motion of spacecraft approaching an orbital object, is justified. A spacecraft with propulsion motor fixed stationary on its body and flywheel drives used as execution units of angular motion control system is considered. Dependence of angular speed of on the spacecraft turn angle is derived for the case of optimally fast rotation around the axis directed along the required angular speed. The main moments of inertia of the spacecraft are taken into account as well as gyroscopic moment of forces along the cross axis and restrictions to moment of forces exerting by the flywheel drives. It is shown that under optimally fast control, one of the projections of resulting moment on the axes along which the execution units are mounted, attains its limitation. The algorithms of evaluation of control moments making it possible to turn the spacecraft for the minimum time are developed. The algorithms also allow calculation of position of any axis bounded to the spacecraft body during the turn. The algorithms performance is tested with the use of mathematical modeling of spacecraft body turn through a specified angle, comparison with the known solution is carried out.

Keywords: angular motion, extensive control, quaternion, operation speed

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