Phasing Delta-V for transfers from Sun–Earth halo orbits to the Moon
Phasing Delta-V for transfers from Sun–Earth halo orbits to the Moon
Inspired by successful extended missions such as the ISEE-3, an investigation for the extended mission that involves a lunar encounter following a Sun-Earth halo orbit mission is considered valuable. Most previous studies present the orbit-to-orbit transfers where the lunar phase is not considered. Intended for extended missions, the present work aims to solve for the minimum phasing ∆V for various initial lunar phases. Due to the solution multiplicity of the two-point boundary value problem, the general constrained optimization algorithm that does not identify multiple feasible solutions is shown to miss minima. A two-step differential corrector with a two-body Lambert solver is developed for identifying multiple solutions. The minimum ∆V associated with the short-way and long-way approaches can be recovered. It is acquired that the required ∆V to cover all initial lunar phases is around 45 m/s for the halo orbit with out-of-plane amplitude Az greater than 3.5×105 km, and 14 m/s for a small halo orbit with Az=1×105 km. In addition, the paper discusses the phasing planning based on the ∆V result and the shift of lunar phase with halo orbit revolution.
Circular restricted three-body problem, Extended missions, Halo orbits, Lunar transfers, Two-point boundary value problem
464-473
Chen, Hongru
8286469d-afe1-46e5-b107-694017de4d97
Kawakatsu, Yasuhiro
ac1d6736-32d7-45ea-b65c-b446a8557a11
Hanada, Toshiya
6a914261-4634-4e52-8605-7c7579869145
29 June 2016
Chen, Hongru
8286469d-afe1-46e5-b107-694017de4d97
Kawakatsu, Yasuhiro
ac1d6736-32d7-45ea-b65c-b446a8557a11
Hanada, Toshiya
6a914261-4634-4e52-8605-7c7579869145
Chen, Hongru, Kawakatsu, Yasuhiro and Hanada, Toshiya
(2016)
Phasing Delta-V for transfers from Sun–Earth halo orbits to the Moon.
Acta Astronautica, 127, .
(doi:10.1016/j.actaastro.2016.05.003).
Abstract
Inspired by successful extended missions such as the ISEE-3, an investigation for the extended mission that involves a lunar encounter following a Sun-Earth halo orbit mission is considered valuable. Most previous studies present the orbit-to-orbit transfers where the lunar phase is not considered. Intended for extended missions, the present work aims to solve for the minimum phasing ∆V for various initial lunar phases. Due to the solution multiplicity of the two-point boundary value problem, the general constrained optimization algorithm that does not identify multiple feasible solutions is shown to miss minima. A two-step differential corrector with a two-body Lambert solver is developed for identifying multiple solutions. The minimum ∆V associated with the short-way and long-way approaches can be recovered. It is acquired that the required ∆V to cover all initial lunar phases is around 45 m/s for the halo orbit with out-of-plane amplitude Az greater than 3.5×105 km, and 14 m/s for a small halo orbit with Az=1×105 km. In addition, the paper discusses the phasing planning based on the ∆V result and the shift of lunar phase with halo orbit revolution.
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More information
Accepted/In Press date: 3 May 2016
e-pub ahead of print date: 26 May 2016
Published date: 29 June 2016
Additional Information:
Publisher Copyright:
© 2016 IAA
Keywords:
Circular restricted three-body problem, Extended missions, Halo orbits, Lunar transfers, Two-point boundary value problem
Identifiers
Local EPrints ID: 490808
URI: http://eprints.soton.ac.uk/id/eprint/490808
ISSN: 0094-5765
PURE UUID: 43a489b0-fef0-4e31-878a-717a92c9e179
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Date deposited: 06 Jun 2024 17:04
Last modified: 07 Jun 2024 02:09
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Contributors
Author:
Hongru Chen
Author:
Yasuhiro Kawakatsu
Author:
Toshiya Hanada
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