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| Main Authors: | , , , , , |
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| Format: | Preprint |
| Published: |
2025
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| Subjects: | |
| Online Access: | https://arxiv.org/abs/2510.08121 |
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| _version_ | 1866908585047359488 |
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| author | Zucchelli, Umberto Mendez, Miguel Alfonso Urbano, Annafederica Vincent-Bonnieu, Sebastien Wenderski, Piotr Sanfedino, Francesco |
| author_facet | Zucchelli, Umberto Mendez, Miguel Alfonso Urbano, Annafederica Vincent-Bonnieu, Sebastien Wenderski, Piotr Sanfedino, Francesco |
| contents | New-generation space missions require satellites to carry substantial amounts of liquid propellant, making it essential to analyse the coupled control-structure-propellant dynamics in detail. While Computational Fluid Dynamics (CFD) offers high-fidelity predictions, its computational cost limits its use in iterative design. Equivalent Mechanical Models (EMMs) provide a faster alternative, though their predictive performance, especially in closed-loop scenarios, remains largely unexplored. This work presents a comparative analysis of a spacecraft under feedback control, using both CFD and a reduced-order sloshing model. Results show good agreement, validating the simplified model for the manoeuvrer considered. This validation enables efficient sensitivity and stability studies, offering a practical tool for early-stage spacecraft design. |
| format | Preprint |
| id |
arxiv_https___arxiv_org_abs_2510_08121 |
| institution | arXiv |
| publishDate | 2025 |
| record_format | arxiv |
| spellingShingle | Closed-loop control of sloshing fuel in a spinning spacecraft Zucchelli, Umberto Mendez, Miguel Alfonso Urbano, Annafederica Vincent-Bonnieu, Sebastien Wenderski, Piotr Sanfedino, Francesco Systems and Control New-generation space missions require satellites to carry substantial amounts of liquid propellant, making it essential to analyse the coupled control-structure-propellant dynamics in detail. While Computational Fluid Dynamics (CFD) offers high-fidelity predictions, its computational cost limits its use in iterative design. Equivalent Mechanical Models (EMMs) provide a faster alternative, though their predictive performance, especially in closed-loop scenarios, remains largely unexplored. This work presents a comparative analysis of a spacecraft under feedback control, using both CFD and a reduced-order sloshing model. Results show good agreement, validating the simplified model for the manoeuvrer considered. This validation enables efficient sensitivity and stability studies, offering a practical tool for early-stage spacecraft design. |
| title | Closed-loop control of sloshing fuel in a spinning spacecraft |
| topic | Systems and Control |
| url | https://arxiv.org/abs/2510.08121 |