Stationary configurations of space tether anchored on smaller primary in three-body problem
Spatial dynamics of a system composed by a planet, its moon and a spacecraft tethered to the moon surface is studied in the framework of circular restricted three-body problem. The moon is assumed to be in synchronous condition (1:1 mean motion resonances) so as to keep its orientation with respect...
| Autores: | , , , , |
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| Tipo de recurso: | artículo |
| Estado: | Versión publicada |
| Fecha de publicación: | 2019 |
| País: | Brasil |
| Institución: | Universidade Estadual Paulista (UNESP) |
| Repositorio: | Repositório Institucional da UNESP |
| Idioma: | inglés |
| OAI Identifier: | oai:repositorio.unesp.br:11449/184541 |
| Acceso en línea: | http://dx.doi.org/10.1016/j.actaastro.2019.01.031 http://hdl.handle.net/11449/184541 |
| Access Level: | acceso abierto |
| Palabra clave: | Tether system Space elevator Tether dynamics Moon exploration Small celestial bodies |
| Sumario: | Spatial dynamics of a system composed by a planet, its moon and a spacecraft tethered to the moon surface is studied in the framework of circular restricted three-body problem. The moon is assumed to be in synchronous condition (1:1 mean motion resonances) so as to keep its orientation with respect to the planet; the size of the moon is non-negligible. The tether is considered to be light and inextensible. Equilibrium configurations of the tether are identified; their stability is analyzed. The bifurcation points, where the number of equilibria changes and new branches arise, are determined. The theoretical results are applied to particular cases of the Earth-Moon, Mars-Phobos and Pluto-Charon systems. |
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