Kinematic algorithms for optimal program-controlled turn of spacecraft

The problem of a spacecraft reorientation from its initial angular position to a required final angular rule during preset time with the minimum kinetic moment, is considered and solved. It is shown that the optimal control of reorientation can be determined within the class of regular precession fulfilled by the spacecraft. The moment to start braking is defined proceeding from the principles of terminal control on actual kinematic parameters of the spacecraft motion that essentially increases the reorientation accuracy. The results of mathematical modelling verify a high efficiency of the proposed reorientation procedure.