Low-Thrust Many-Revolution Transfer between Near Rectilinear Halo Orbit and Low Lunar Orbit Using Hybrid Differential Dynamic Programming

Kohei Oue; Naoya Ozaki; Toshihiro Chujo

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arXiv · 2504.07723

Low-Thrust Many-Revolution Transfer between Near Rectilinear Halo Orbit and Low Lunar Orbit Using Hybrid Differential Dynamic Programming

Kohei Oue·Naoya Ozaki·Toshihiro Chujo

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Abstract

Low-thrust, many-revolution transfers between near-rectilinear halo orbits and low lunar orbits are challenging due to the many-revolutions and is further complicated by three-body perturbation. To address these challenges, we extend hybrid differential dynamic programming by enhancing with a continuation of dynamical system. The optimization begins with the Sundman-transformed two-body problem and gradually transitions to the Sundman-transformed circular restricted three-body problem expressed in the moon-centered inertial frame. Numerical examples demonstrate the robust convergence of our method, where optimal transfers from low lunar orbit to near-rectilinear halo orbit are obtained with a poor initial guess of low lunar orbit.

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Kohei Oue, Naoya Ozaki, Toshihiro Chujo. 2025-04-10. Low-Thrust Many-Revolution Transfer between Near Rectilinear Halo Orbit and Low Lunar Orbit Using Hybrid Differential Dynamic Programming. https://arxiv.org/abs/2504.07723

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