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

Autor(es)

Antônio F. B. Almeida Prado

• Tipo de documento: Artigo Científico
• Fonte: Journal of the Brazilian Society of Mechanical Sciences and Engineering; v. 28, n. 2, p. 131-139, 2006-06-00.

Resumo

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. (AU)

• Processo FAPESP: 00/14769-4 - Astrodinâmica aplicada à manobra de veículos espaciais
• Beneficiário: Antônio Fernando Bertachini de Almeida Prado
• Modalidade de apoio: Auxílio à Pesquisa - Regular