Abstract
This paper presents various optimal powered aeroassisted orbit transfers using solar electric propulsion. These trajectories use a combination of solar electric propulsion and controlled atmospheric perturbations. Single revolution coplanar and plane change trajectories are considered about Mars. The objective of the coplanar trajectory is to circularize the orbit and the objective of the plane change trajectory is to minimize the absolute value of the inclination. Optimal trajectories are presented for both mission objectives.
| Original language | English (US) |
|---|---|
| Pages (from-to) | 1557-1575 |
| Number of pages | 19 |
| Journal | Advances in the Astronautical Sciences |
| Volume | 108 II |
| State | Published - 2001 |
| Event | Proceedings of the AAS/AIAA Space Flight Mechanics Meeting - Santa Barbara, CA, United States Duration: Feb 11 2001 → Feb 15 2001 |
ASJC Scopus subject areas
- Aerospace Engineering
- Space and Planetary Science