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.
Trajectory and System Analysis For Outer-Planet Solar-Electric Propulsion Missions
2004-01-01
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Trajectory and System Analysis for Outer-Planet Solar Electric Propulsion Missions
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