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This paper outlines the optimization of the L1-L2 and L2-L1 missions using electric propulsion. The optimization criterion is the total flight time. The optimal control laws are obtained using the Fedorenko method to estimate the derivatives, the gradient method to optimize the control laws and the Runge-Kutta method for the numerical integration of the differential equation system. The study of these transfers is based on the restricted circular three-body problem. As the results of the optimization we obtained optimal control laws, corresponding trajectories and minimal total flight times. Keywords-spacecraft; low thrust engine; control laws; ballistic optimization; circular orbit; libration point; earth-moon system

The Stepwise Control Laws in the Problem of the Motion Optimization of the Electric Powered Transfers in the Earth-Moon System, Including L1-L2 and L2-L1 Missions