Modeling and Optimization of Aero-Ballistic Capture

In this paper a novel paradigm for Mars missions is modeled and optimized. This concept consists in a maneuver that combines aerocapture and ballistic capture upon Mars arrival, and is labelled aero-ballistic capture. The idea is reducing the final mass by exploiting the interaction with the planet atmosphere as well as the Sun-Mars gravitational field. The problem is stated by using optimal control theory, and optimal solutions are sought. An assessment of aero-ballistic capture shows the superiority compared to classical maneuvers when medium-to-high final orbits around Mars are wanted.