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**Sun-perturbed Earth-to-Moon transfers with low energy and moderate flight time.**
*(English)*
Zbl 1147.70316

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 E. Belbruno [Contemp. Math. 292, 17–45 (2002; Zbl 1021.70012)].

See the author’s article in Physica D 197, No. 3-4, 313–331 (2004; Zbl 1076.70019) and E. Belbruno [Contemp. Math. 292, 17–45 (2002; Zbl 1021.70012)].

Reviewer: Sergei Georgievich Zhuravlev (Moskva)

### Keywords:

celestial mechanics; orbital mechanics; perturbed three-body problem; the solar gravitation perturbation; Earth-to-Moon transfer; optimal transfers### Software:

AUTO
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\textit{K. Yagasaki}, Celest. Mech. Dyn. Astron. 90, No. 3--4, 197--212 (2004; Zbl 1147.70316)

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### References:

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[4] | Belbruno, E. A.: 2002, ’Analytic estimation of weak stability boundaries and low energy transfers’, In: A. Chenciner, R. Cushman, C. Robinson and Z. J. Xia (eds.),Celestial Mechanics, Contemporary Mathematics, Vol. 292, pp. 17–45, American Mathematical Society, Providence. · Zbl 1021.70012 |

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[23] | Yagasaki, K.: 2004, ’Computation of low energy Earth-to-Moon transfers with moderate flight time; Physica (in press). · Zbl 1076.70019 |

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