Low-Thrust Many-Revolution Transfer between Near Rectilinear Halo Orbit and Low Lunar Orbit Using Hybrid Differential Dynamic Programming
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arXiv
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| Format: | Preprint |
| Published: |
2025
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| _version_ | 1866917981991206912 |
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| author | Oue, Kohei Ozaki, Naoya Chujo, Toshihiro |
| author_facet | Oue, Kohei Ozaki, Naoya Chujo, Toshihiro |
| contents | 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. |
| format | Preprint |
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arxiv_https___arxiv_org_abs_2504_07723 |
| institution | arXiv |
| publishDate | 2025 |
| record_format | arxiv |
| spellingShingle | Low-Thrust Many-Revolution Transfer between Near Rectilinear Halo Orbit and Low Lunar Orbit Using Hybrid Differential Dynamic Programming Oue, Kohei Ozaki, Naoya Chujo, Toshihiro Earth and Planetary Astrophysics Instrumentation and Methods for Astrophysics Optimization and Control 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. |
| title | Low-Thrust Many-Revolution Transfer between Near Rectilinear Halo Orbit and Low Lunar Orbit Using Hybrid Differential Dynamic Programming |
| topic | Earth and Planetary Astrophysics Instrumentation and Methods for Astrophysics Optimization and Control |
| url | https://arxiv.org/abs/2504.07723 |