Optimal low-thrust trajectories combined with an aeroassist maneuver

Various optimal powered aeroassisted orbit transfers using solar electric propulsion are presented. These trajectories use a combination of solar electric propulsion and controlled atmospheric perturbations. Single revolution coplanar and plane change trajectories are considered. The objective of the coplanar trajectory is to circularize the orbit, and the objective of the plane change trajectory is to maximize the reduction in orbital inclination. Optimal trajectories are presented for both cases to show the benefits of combining atmospheric perturbations and solar electric propulsion.