Abstract
Pontryagin’s maximum principle is used for solution of topical problems of spacecraft motion control. The dynamic optimal control problem of space orientation of a spacecraft from an arbitrary initial to a given final angular position with minimization of the turning time is studied in detail. The solution to the formulated problem is obtained and numerical expressions for synthesis of optimal control program are given. Results of mathematical simulation of the dynamics of motion of a spacecraft at optimal control are presented; these results demonstrate practical feasibility of the developed control algorithm.
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