| Texto completo | |
| Autor(es): |
Santana, S. H. S.
;
De Melo, C. F.
;
Macau, E. E. N.
;
Winter, O. C.
Número total de Autores: 4
|
| Tipo de documento: | Artigo Científico |
| Fonte: | COMPUTATIONAL & APPLIED MATHEMATICS; v. 35, n. 3, p. 10-pg., 2016-10-01. |
| Resumo | |
Escape trajectories from the Earth-Moon system can be obtained through a single gravity assist maneuver of a spacecraft with the Moon. This paper presents a semi-analytical study of variations in the semi-major axis and the eccentricity of a spacecraft for a geocentric frame-before and after a close encounter of the spacecraft with the Moon. Studies on the swing-by dynamics between a spacecraft and the Moon were performed in order to establish a set of initial conditions in terms of eccentricities and semi-major axes of geocentric initial orbits. This way, it was possible identify which orbits, launched from Earth parking orbits, accomplish swing-bys with the Moon and generate escape trajectories. (AU) | |
| Processo FAPESP: | 11/50151-0 - Fenômenos dinâmicos em redes complexas: fundamentos e aplicações |
| Beneficiário: | Elbert Einstein Nehrer Macau |
| Modalidade de apoio: | Auxílio à Pesquisa - Temático |
| Processo FAPESP: | 11/08171-3 - Dinâmica orbital de pequenos corpos |
| Beneficiário: | Othon Cabo Winter |
| Modalidade de apoio: | Auxílio à Pesquisa - Temático |