| Revista: | Journal of the Brazilian Society of Mechanical Sciences and Engineering |
| Base de datos: | PERIÓDICA |
| Número de sistema: | 000312360 |
| ISSN: | 1678-5878 |
| Autores: | Prado, Antonio F.B. Almeida1 |
| Instituciones: | 1Instituto Nacional de Pesquisas Espaciais, Sao Jose dos Campos, Sao Paulo. Brasil |
| Año: | 2006 |
| Periodo: | Abr-Jun |
| Volumen: | 28 |
| Número: | 2 |
| Paginación: | 131-139 |
| País: | Brasil |
| Idioma: | Inglés |
| Tipo de documento: | Artículo |
| Enfoque: | Experimental |
| Resumen en inglés | This paper is concerned with trajectories to transfer a spacecraft between the Lagrangian points of the Sun-Earth system and the primaries. The Lagrangian points have important applications in astronautics, since they are equilibrium points of the equation of motion and very good candidates to locate a satellite or a space station. The planar circular restricted three-body problem in two dimensions is used as the model for the Sun-Earth system, and Lamaître regularization is used to avoid singularities during the numerical integration required to solve the Lambert's three-body problem. The results show families of transfer orbits, parameterized by the transfer time |
| Disciplinas: | Física y astronomía |
| Palabras clave: | Astronomía, Problema de tres cuerpos, Astrodinámica, Astronáutica, Maniobradores, Orbitas |
| Keyword: | Physics and astronomy, Astronomy, Three-body problem, Astrodynamics, Maneuvers, Orbits |
| Texto completo: | Texto completo (Ver PDF) |
