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The Optimization of Spacecraft Motion with Ion Engine in the Earth – Moon System

The control laws optimization and driving trajectories of spacecraft with the low-thrust engine fulfilling transport problems in a system the Earth - Moon are described. With the usage of formalism of the Pontryagin maximum principle the necessary requirements of control optimality are obtained from the minimum duration view point. The driving is considered within the framework of a flat circular restricted problem of three bodies. The solutions for problems optimum on response of reaching of inconvertible a libration points of a system and flyby of Moon on required angular distance are obtained. The approach for selection of initial parameters of boundary value problems is offered.
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