Co-optimization of spacecraft and low-thrust trajectory with direct methods
Fuente:
arXiv
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| Autori principali: | , |
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| Natura: | Preprint |
| Pubblicazione: |
2024
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| _version_ | 1866917761753546752 |
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| author | Saloglu, Keziban Taheri, Ehsan |
| author_facet | Saloglu, Keziban Taheri, Ehsan |
| contents | Solar-powered electric propulsion systems can operate in multiple modes and their operation is coupled to the power generated by solar arrays. However, the power produced by the solar arrays is a function of the solar array size and heliocentric distance to the Sun, which also depends on the to-be-optimized trajectory. The optimization of spacecraft solar array size, thruster modes, and trajectory can be performed simultaneously, capitalizing on the inherent couplings. In this work, we co-optimize the spacecraft's solar array size, thruster modes, and trajectory using a direct optimization, which allows for maximizing the net delivered mass. A particular challenge arises due to the existence of discrete operating modes. We proposed a method for smoothly selecting optimal operation modes among a set of finite possible modes. The utility of the proposed method is demonstrated successfully by solving a benchmark problem, i.e., the Earth to Comet 67P fixed-time rendezvous problem. The results indicate that utilizing multiple modes increases the net useful mass compared to a single mode and leads to a smaller solar array size for the spacecraft. |
| format | Preprint |
| id |
arxiv_https___arxiv_org_abs_2408_15943 |
| institution | arXiv |
| publishDate | 2024 |
| record_format | arxiv |
| spellingShingle | Co-optimization of spacecraft and low-thrust trajectory with direct methods Saloglu, Keziban Taheri, Ehsan Optimization and Control Solar-powered electric propulsion systems can operate in multiple modes and their operation is coupled to the power generated by solar arrays. However, the power produced by the solar arrays is a function of the solar array size and heliocentric distance to the Sun, which also depends on the to-be-optimized trajectory. The optimization of spacecraft solar array size, thruster modes, and trajectory can be performed simultaneously, capitalizing on the inherent couplings. In this work, we co-optimize the spacecraft's solar array size, thruster modes, and trajectory using a direct optimization, which allows for maximizing the net delivered mass. A particular challenge arises due to the existence of discrete operating modes. We proposed a method for smoothly selecting optimal operation modes among a set of finite possible modes. The utility of the proposed method is demonstrated successfully by solving a benchmark problem, i.e., the Earth to Comet 67P fixed-time rendezvous problem. The results indicate that utilizing multiple modes increases the net useful mass compared to a single mode and leads to a smaller solar array size for the spacecraft. |
| title | Co-optimization of spacecraft and low-thrust trajectory with direct methods |
| topic | Optimization and Control |
| url | https://arxiv.org/abs/2408.15943 |