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Optimal Two- and Three-Dimensional Earth–Moon Orbit Transfers

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Abstract

The determination of minimum-propellant-consumption trajectories represents a crucial issue for the purpose of planning robotic and human missions to the Moon in the near future. This work addresses the problem of identifying minimum-fuel orbit transfers from a specified low Earth orbit (LEO) to a low Moon orbit (LMO), under the assumption of employing high-thrust propulsion. The problem at hand is solved in the dynamical framework of the circular restricted three-body problem. First, the optimal two-dimensional LEO-to-LMO transfer is determined. Second, three-dimensional transfers are considered, in a dynamical model that includes the Cassini’s laws of lunar motion. The propellant consumption associated with three-dimensional transfers turns out to be relatively insensitive to the final orbit inclination and exceeds only marginally the value of the globally optimal two-dimensional orbit transfer.

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Authors and Affiliations

  1. Faculty of Civil and Industrial Engineering, Sapienza University of Rome, via Eudossiana 18, 00184, Rome, Italy

    E. M. Leonardi

  2. Department of Astronautical, Electrical, and Energy Engineering, Sapienza University of Rome, via Salaria 851, 00138, Rome, Italy

    M. Pontani

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  1. E. M. Leonardi
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  2. M. Pontani
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Correspondence to E. M. Leonardi.

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Leonardi, E.M., Pontani, M. Optimal Two- and Three-Dimensional Earth–Moon Orbit Transfers. Aerotec. Missili Spaz. 99, 195–202 (2020). https://doi.org/10.1007/s42496-020-00046-2

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  • DOI: https://doi.org/10.1007/s42496-020-00046-2

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