Global Optimization for Trajectory Design via Invariant Manifolds in the Earth-Moon Circular Restricted Three-Body Problem
Fuente:
arXiv
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| Autori principali: | , , , |
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| Natura: | Preprint |
| Pubblicazione: |
2024
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| Soggetti: | |
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| _version_ | 1866914815635619840 |
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| author | Tagliaferri, Flavio Blazquez, Emmanuel Acciarini, Giacomo Izzo, Dario |
| author_facet | Tagliaferri, Flavio Blazquez, Emmanuel Acciarini, Giacomo Izzo, Dario |
| contents | This study addresses optimal impulsive trajectory design within the Circular Restricted Three-Body Problem (CR3BP), presenting a global optimization-based approach to identify minimum $ΔV$ transfers between periodic orbits, including heteroclinic connections. By combining a Monotonic Basin Hopping (MBH) algorithm with a sequential quadratic solver in a parallel optimization framework, a wide range of minimum $ΔV$ transfers are efficiently found. To validate this approach, known connections from the literature are reproduced. Consequently, three-dimensional periodic orbits are explored and a systematic search for minimum propellant trajectories is conducted within a selected interval of Jacobi constants and a maximum time of flight. Analysis of the results reveals the presence of very low $ΔV$ solutions and showcases the algorithm's effectiveness across various mission scenarios. |
| format | Preprint |
| id |
arxiv_https___arxiv_org_abs_2405_18916 |
| institution | arXiv |
| publishDate | 2024 |
| record_format | arxiv |
| spellingShingle | Global Optimization for Trajectory Design via Invariant Manifolds in the Earth-Moon Circular Restricted Three-Body Problem Tagliaferri, Flavio Blazquez, Emmanuel Acciarini, Giacomo Izzo, Dario Space Physics Chaotic Dynamics This study addresses optimal impulsive trajectory design within the Circular Restricted Three-Body Problem (CR3BP), presenting a global optimization-based approach to identify minimum $ΔV$ transfers between periodic orbits, including heteroclinic connections. By combining a Monotonic Basin Hopping (MBH) algorithm with a sequential quadratic solver in a parallel optimization framework, a wide range of minimum $ΔV$ transfers are efficiently found. To validate this approach, known connections from the literature are reproduced. Consequently, three-dimensional periodic orbits are explored and a systematic search for minimum propellant trajectories is conducted within a selected interval of Jacobi constants and a maximum time of flight. Analysis of the results reveals the presence of very low $ΔV$ solutions and showcases the algorithm's effectiveness across various mission scenarios. |
| title | Global Optimization for Trajectory Design via Invariant Manifolds in the Earth-Moon Circular Restricted Three-Body Problem |
| topic | Space Physics Chaotic Dynamics |
| url | https://arxiv.org/abs/2405.18916 |