Sun-perturbed Earth-to-Moon transfers with low energy and moderate flight time
type: Item
instance of: scholarly article
title: Sun-perturbed Earth-to-Moon transfers with low energy and moderate flight time
zbMATH Open document ID: 1147.70316
author: Kazuyuki Yagasaki
published in: Celestial Mechanics and Dynamical Astronomy
publication date: 2005-02-28T00:00:00Z
review text: 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)].
reviewed by: Sergei Georgievich Zhuravlev
Mathematics Subject Classification ID: 70M20
Mathematics Subject Classification ID: 70F15
zbMATH DE Number: 2139804
zbMATH Keywords: celestial mechanics
zbMATH Keywords: orbital mechanics
zbMATH Keywords: perturbed three-body problem
zbMATH Keywords: the solar gravitation perturbation
zbMATH Keywords: Earth-to-Moon transfer
zbMATH Keywords: optimal transfers
describes a project that uses: AUTO
MaRDI profile type: Publication
full work available at URL: s10569-004-0406-8
OpenAlex ID: W2012885179
cites work: Q4547281
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cites work: Computation of low energy Earth-to-Moon transfers with moderate flight time
DOI: 10.1007/S10569-004-0406-8
description: scientific article; zbMATH DE number 2139804