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| Main Authors: | , , |
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| Format: | Preprint |
| Published: |
2024
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| Subjects: | |
| Online Access: | https://arxiv.org/abs/2404.03926 |
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| _version_ | 1866913453197754368 |
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| author | Wang, Kun Chen, Zheng Li, Jun |
| author_facet | Wang, Kun Chen, Zheng Li, Jun |
| contents | In this paper, we consider a trajectory planning problem arising from a lunar vertical landing with minimum fuel consumption. The vertical landing requirement is written as a final steering angle constraint, and a nonnegative regularization term is proposed to modify the cost functional. In this way, the final steering angle constraint will be inherently satisfied according to Pontryagin's Minimum Principle. As a result, the modified optimal steering angle has to be determined by solving a transcendental equation. To this end, a transforming procedure is employed, which allows for finding the desired optimal steering angle by a simple bisection method. Consequently, the modified optimal control problem can be solved by the indirect shooting method. Finally, some numerical examples are presented to demonstrate and verify the developments of the paper. |
| format | Preprint |
| id |
arxiv_https___arxiv_org_abs_2404_03926 |
| institution | arXiv |
| publishDate | 2024 |
| record_format | arxiv |
| spellingShingle | Fuel-Optimal Trajectory Planning for Lunar Vertical Landing Wang, Kun Chen, Zheng Li, Jun Optimization and Control In this paper, we consider a trajectory planning problem arising from a lunar vertical landing with minimum fuel consumption. The vertical landing requirement is written as a final steering angle constraint, and a nonnegative regularization term is proposed to modify the cost functional. In this way, the final steering angle constraint will be inherently satisfied according to Pontryagin's Minimum Principle. As a result, the modified optimal steering angle has to be determined by solving a transcendental equation. To this end, a transforming procedure is employed, which allows for finding the desired optimal steering angle by a simple bisection method. Consequently, the modified optimal control problem can be solved by the indirect shooting method. Finally, some numerical examples are presented to demonstrate and verify the developments of the paper. |
| title | Fuel-Optimal Trajectory Planning for Lunar Vertical Landing |
| topic | Optimization and Control |
| url | https://arxiv.org/abs/2404.03926 |