Synthesis of optimal control of spacecraft partial rotation by moments method

The problems of optimal control of threefold integrator which models spacecraft angular motion in one of the orientation control paths with regard for their cross-connections are considered. The problems are reduced to the optimal moments problem and their solution for minimum functionals of the norm type in space ( for ) are found using Krasovsky's maximum principle. Optimal control programmes for the minimum generalized control energy tasks, minimum maximal control influence level and in accordance for minimum consumption control or for minimum of control influence full impulse, which is the same, are obtained.