Trajectory and System Analysis For Outer-Planet Solar-Electric Propulsion Missions

摘要

Outer-planet mission and systems analyses are performed using three next generation solar electric ion thruster models. The impact of variations in thruster model, flight time, launch vehicle, propulsion and power systems characteristics is investigated. All presented trajectories have a single Venus gravity assist and maximize the delivered mass to Saturn or Neptune. The effect of revolution ratio - the ratio of Venusian orbital period to the flight time between launch and flyby dates - is also discussed.