High velocity aero-gravity assist applied on eccentricity to inclination conversion for reaching solar polar orbit

In order to change the inclination of an orbit around the Sun, a good option is to perform a flyby on Jupiter, where heliocentric speeds are slower than in the inner solar system. The drawback of the resulting orbit is the great orbital period associated with its large semi-major axis. In order to reduce the orbit size and increase even more the inclination, it was suggested to implement an Aero-gravity Assist maneuver at the Earth after the Jupiter flyby. This maneuver would be used within the Eccentricity to Inclination conversion scheme to increase its performance. Results show that such a maneuver could reduce the time required for reaching a short period, highly inclined orbit in lower time than by only using Gravity Assist. The objective of this study is to analyze the performance of using Aero-gravity Assist within the Eccentricity to Inclination conversion.