Ballistic optimization of the L1-L2 and L2-L1 low thrust transfers in the Earth-Moon system
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The paper outlines the optimization of the L1-L2 and L2-L1 missions using electric propulsion. The variational problem of the low thrust spacecraft transfer optimization with the optimization criterion as the total flight time is considered. The optimal control programs were obtained by using the Pontryagin's maximum principle. The optimization results were as follows: for a certain value of acceleration and exhaust velocity of the propulsion system, we determined optimal control programs, corresponding trajectories and minimal total flight times.
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