| Full text | |
| Author(s): |
Santana, S. H. S.
;
De Melo, C. F.
;
Macau, E. E. N.
;
Winter, O. C.
Total Authors: 4
|
| Document type: | Journal article |
| Source: | COMPUTATIONAL & APPLIED MATHEMATICS; v. 35, n. 3, p. 10-pg., 2016-10-01. |
| Abstract | |
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) | |
| FAPESP's process: | 11/50151-0 - Dynamical phenomena in complex networks: fundamentals and applications |
| Grantee: | Elbert Einstein Nehrer Macau |
| Support Opportunities: | Research Projects - Thematic Grants |
| FAPESP's process: | 11/08171-3 - Orbital dynamics of minor bodies |
| Grantee: | Othon Cabo Winter |
| Support Opportunities: | Research Projects - Thematic Grants |