Study of asteroid redirection techniques through collisions with spacecraft
The threat posed by near-Earth objects (NEOs) has transformed planetary defence from a theoretical concern into a vital field of study. In this work, a detailed analysis is conducted on orbital deviation strategies using a kinetic impactor, with asteroid (99942) Apophis serving as the baseline scena...
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| Tipo de recurso: | tesis de maestría |
| Fecha de publicación: | 2025 |
| País: | España |
| Institución: | Universitat Politècnica de Catalunya (UPC) |
| Repositorio: | UPCommons. Portal del coneixement obert de la UPC |
| Idioma: | inglés |
| OAI Identifier: | oai:upcommons.upc.edu:2117/446998 |
| Acceso en línea: | https://hdl.handle.net/2117/446998 |
| Access Level: | acceso abierto |
| Palabra clave: | Orbital mechanics Impact Collisions (Astrophysics) Navigation (Astronautics) Asteroid Spacecraft collision Kinetic impactor Orbit determination space Mecànica orbital Impacte Col·lisions (Astrofísica) Navegació espacial Àrees temàtiques de la UPC::Física::Astronomia i astrofísica |
| Sumario: | The threat posed by near-Earth objects (NEOs) has transformed planetary defence from a theoretical concern into a vital field of study. In this work, a detailed analysis is conducted on orbital deviation strategies using a kinetic impactor, with asteroid (99942) Apophis serving as the baseline scenario. A full methodology has been developed to simulate the effects of an impact during Apophis’s fly-by through Earth's Sphere of Influence (SoI), relying on a two-body problem approximation to predict the asteroid’s future orbital evolution. By designing transfer trajectories through Hohmann and bi-elliptic manoeuvres and optimizing the approach using Lambert solutions, this project evaluates different mission architectures and their impact on the asteroid’s path. Special attention is given to how different parking orbits, impact timings, and spacecraft velocities influence the overall effect of the deflection strategy. Impact scenarios were assessed based on changes to Apophis's future encounters with Earth, particularly focusing on the 2029, and 2051 flybys. Despite the constraints of the model — such as neglecting third-body perturbations — the simulations reveal that even minimal velocity changes can significantly alter future encounters. The results showed that although immediate post-impact changes in Apophis’s trajectory are small, their effects become more pronounced in subsequent decades, though not always in the desired direction. The findings demonstrate that collision timing, impact geometry, and mission design are critical to successfully deviating hazardous objects. While some mission profiles explored were not feasible with current propulsion capabilities, this study highlights key areas for future development, including n-body simulations, advanced propulsion systems, and gravity assist strategies. Ultimately, the overall study contributes valuable insights into the complex dynamics of asteroid deflection and provides a baseline for future, more detailed planetary defence mission designs. |
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