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Dynamic stabilization of L2 periodic orbits using attitude-orbit coupling effects
Cita
Peláez Álvarez, Jesús 
ORCID: https://orcid.org/0000-0001-9755-1674, Bombardelli, Claudio ORCID: https://orcid.org/0000-0002-9181-1487, Lara, M., Lucas, Fernando R., Sanjurjo Rivo, Manuel, Curreli, D., Lorenzini, Enrico C. and Scheeres, D.
(2011).
Dynamic stabilization of L2 periodic orbits using attitude-orbit coupling effects.
En: "22nd International Symposium on Space Flight Dynamics - 22nd ISSFD", 28/02/2011 - 04/03/2011, Säo José dos Campos, Brasil. pp. 73-81.
ORCID: https://orcid.org/0000-0001-9755-1674, Bombardelli, Claudio ORCID: https://orcid.org/0000-0002-9181-1487, Lara, M., Lucas, Fernando R., Sanjurjo Rivo, Manuel, Curreli, D., Lorenzini, Enrico C. and Scheeres, D.
(2011).
Dynamic stabilization of L2 periodic orbits using attitude-orbit coupling effects.
En: "22nd International Symposium on Space Flight Dynamics - 22nd ISSFD", 28/02/2011 - 04/03/2011, Säo José dos Campos, Brasil. pp. 73-81.
Descripción
| Título: | Dynamic stabilization of L2 periodic orbits using attitude-orbit coupling effects |
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| Autor/es: |
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| Tipo de Documento: | Ponencia en Congreso o Jornada (Artículo) |
| Título del Evento: | 22nd International Symposium on Space Flight Dynamics - 22nd ISSFD |
| Fechas del Evento: | 28/02/2011 - 04/03/2011 |
| Lugar del Evento: | Säo José dos Campos, Brasil |
| Título del Libro: | 22nd International Symposium on Space Flight Dynamics - 22nd ISSFD |
| Fecha: | 28 Febrero 2011 |
| Materias: | |
| ODS: | |
| Palabras Clave Informales: | roto-orbital dynamics, Hill problem, periodic orbits, stability |
| Escuela: | E.T.S.I. Aeronáuticos (UPM) [antigua denominación] |
| Departamento: | Física Aplicada a la Ingeniería Aeronáutica [hasta 2014] |
| Licencias Creative Commons: | Reconocimiento - Sin obra derivada - No comercial |
Resumen
Numerical explorations show how the known periodic solutions of the Hill problem are modified in the case of the attitude-orbit coupling that may occur for large satellite structures. We focus on the case in which the elongation is the dominant satellite’s characteristic and find that a rotating structure may remain with its largest dimension in a plane parallel to the plane of the primaries. In this case, the effect produced by the non-negligible physical length is dynamically equivalent to the perturbation produced by an oblate central body on a mass-point satellite. Based on this, it is demonstrated that the attitude-orbital coupling of a long enough body may change the dynamical characteristics of a periodic orbit about the collinear Lagrangian points.
Más información
| ID de Registro: | 21139 |
|---|---|
| Identificador DC: | https://oa.upm.es/21139/ |
| Identificador OAI: | oai:oa.upm.es:21139 |
| Depositado por: | Memoria Investigacion |
| Depositado el: | 28 Mar 2014 19:05 |
| Ultima Modificación: | 27 Feb 2024 11:14 |
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