Sun-perturbed Earth-to-Moon transfers with low energy and moderate flight time
The planar circular restricted three-body problem (the Earth, the Moon and a spacecraft) is used to construct Earth-to-Moon transfers with low cost and moderate flight time. The spacecraft motion in the frame of the restricted three-body problem is perturbed by the solar gravitation. The nonlinear boundary value problem is stated to compute the optimal (with the low energy) Earth-to-Moon transfers. Using a computer software called AUTO the authors solve the above mentioned optimal problem and then continue its solutions numerically to obtain the optimal transfers. It is noted that the use of the solar gravitation can further lower the transfer cost drastically. A short review of previous results is given. See the author's article in Physica D 197, No. 3-4, 313--331 (2004; Zbl 1076.70019) and \textit{E. Belbruno} [Contemp. Math. 292, 17--45 (2002; Zbl 1021.70012)].
scientific article; zbMATH DE number 2139804