Low-Thrust Many-Revolution Trajectory Design Under Operational Uncertainties for DESTINY+ Mission
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arXiv
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| Auteurs principaux: | , , , , , |
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| Format: | Preprint |
| Publié: |
2025
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| _version_ | 1866913670721699840 |
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| author | Ozaki, Naoya Akiyama, Yuki Hatakeyama, Akira Ito, Shota Chikazawa, Takuya Yamamoto, Takayuki |
| author_facet | Ozaki, Naoya Akiyama, Yuki Hatakeyama, Akira Ito, Shota Chikazawa, Takuya Yamamoto, Takayuki |
| contents | DESTINY+ is a planned JAXA medium-class Epsilon mission from Earth to deep space using a low-thrust, many-revolution orbit. Such a trajectory design is a challenging problem not only for trajectory design but also for flight operations, and in particular, it is essential to evaluate the impact of operational uncertainties to ensure mission success. In this study, we design the low-thrust trajectory from Earth orbit to a lunar transfer orbit by differential dynamic programming using the Sundman transformation. The results of Monte Carlo simulations with operational uncertainties confirm that the spacecraft can be successfully guided to the lunar transfer orbit by using the feedback control law of differential dynamic programming in the angular domain. |
| format | Preprint |
| id |
arxiv_https___arxiv_org_abs_2501_17867 |
| institution | arXiv |
| publishDate | 2025 |
| record_format | arxiv |
| spellingShingle | Low-Thrust Many-Revolution Trajectory Design Under Operational Uncertainties for DESTINY+ Mission Ozaki, Naoya Akiyama, Yuki Hatakeyama, Akira Ito, Shota Chikazawa, Takuya Yamamoto, Takayuki Instrumentation and Methods for Astrophysics Earth and Planetary Astrophysics Systems and Control Optimization and Control DESTINY+ is a planned JAXA medium-class Epsilon mission from Earth to deep space using a low-thrust, many-revolution orbit. Such a trajectory design is a challenging problem not only for trajectory design but also for flight operations, and in particular, it is essential to evaluate the impact of operational uncertainties to ensure mission success. In this study, we design the low-thrust trajectory from Earth orbit to a lunar transfer orbit by differential dynamic programming using the Sundman transformation. The results of Monte Carlo simulations with operational uncertainties confirm that the spacecraft can be successfully guided to the lunar transfer orbit by using the feedback control law of differential dynamic programming in the angular domain. |
| title | Low-Thrust Many-Revolution Trajectory Design Under Operational Uncertainties for DESTINY+ Mission |
| topic | Instrumentation and Methods for Astrophysics Earth and Planetary Astrophysics Systems and Control Optimization and Control |
| url | https://arxiv.org/abs/2501.17867 |