Orbital maneuvers between the Lagrangian points and the primaries in the Earth-Sun system



Título del documento: Orbital maneuvers between the Lagrangian points and the primaries in the Earth-Sun system
Revista: Journal of the Brazilian Society of Mechanical Sciences and Engineering
Base de datos: PERIÓDICA
Número de sistema: 000312360
ISSN: 1678-5878
Autores: 1
Instituciones: 1Instituto Nacional de Pesquisas Espaciais, Sao Jose dos Campos, Sao Paulo. Brasil
Año:
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
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