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
30 pages
Report
No indication
English
Extraterrestrial Exploration , Space Launch Vehicles & Support Equipment , Rocket Engines & Motors , Solar Energy , Propulsion system performance , Auxiliary propulsion , Solar electric propulsion , Spacecraft propulsion , Propulsive efficiency , Systems analysis , Space missions , Variations , Impacts , Flight time , Launch vehicles , Venus , Power systems , Solar electric ion thruster models , Revolution ratio , Outer-planet destinations
Trajectory and System Analysis for Outer-Planet Solar Electric Propulsion Missions
Online Contents | 2005
|Nuclear Electric Propulsion for Outer Planet Missions
AIAA | 2003
|High Power Electric Propulsion for Outer Planet Missions
NTRS | 2003
|