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Global search for low-thrust transfers to the Moon in the planar circular restricted three-body problem

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Abstract

This paper globally searches for low-thrust transfers to the Moon in the planar, circular, restricted, three-body problem. Propellant-mass optimal trajectories are computed with an indirect method, which implements the necessary conditions of optimality based on the Pontryagin principle. We present techniques to reduce the dimension of the set over which the required initial costates are searched. We obtain a wide range of Pareto solutions in terms of time of flight and mass consumption. Using the Tisserand–Poincaré graph, a number of solutions are shown to exploit high-altitude lunar flybys to reduce fuel consumption.

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Acknowledgements

This study has been partially supported by Grant-in-Aid for JSPS Fellows No. 15J07090, and by JSPS Grant-in-Aid, No. 26800207.

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Authors and Affiliations

  1. Department of Applied Mechanics and Aerospace Engineering, Waseda University, Tokyo, 169-8555, Japan

    Kenta Oshima & Tomohiro Yanao

  2. Department of Space Flight Systems, ISAS/JAXA, Sagamihara, Kanagawa, 155-0031, Japan

    Stefano Campagnola

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  1. Kenta Oshima
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  2. Stefano Campagnola
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  3. Tomohiro Yanao
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Correspondence to Kenta Oshima.

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Oshima, K., Campagnola, S. & Yanao, T. Global search for low-thrust transfers to the Moon in the planar circular restricted three-body problem. Celest Mech Dyn Astr 128, 303–322 (2017). https://doi.org/10.1007/s10569-016-9748-2

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  • DOI: https://doi.org/10.1007/s10569-016-9748-2

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