An approach to solve the problem of optimizing multi-revolution thrust limited trajectories with constant exhaust velocity between the Earth orbit and the orbit around the Moon is considered. An indirect approach is used to solve the lunar trajectory optimization problem, based on the application of the Pontryagin's maximum principle and continuation method. At all segments of the trajectory, the gravities of the Earth, the Moon and the Sun are taken into account. The trajectory to the Moon is divided into geocentric and selenocentric segments, which are connected at the libration point EML1 of the Earth-Moon system. To ensure the choice of the optimal relation between the angular distance and the transfer duration of each segment, the problem of optimizing the trajectory with a fixed angular distance and free time of flight is considered. Solving a sequence of optimization problems for the limited power trajectory, the minimum-thrust trajectory and the minimum-fuel trajectory avoids the need to choose an initial guess for unknown initial costate variables. The numerical examples of optimizing the multi-revolution low-thrust transfers from the highly elliptical orbit around the Earth to the circular orbit around the Moon are given.
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