The Earth Affecting Solar Causes Observatory (EASCO)
Flight Dynamics Summary • Baseline Low-Thrust Trajectory to Sun-Earth L5 using Solar-Electric Propulsion • Transfer time: ~2 years • Launch C3: ~2.2 km 2 /s 2 • DV: ~1.5 km/s • Propellant (xenon) required: ~55 kg • Optional High-Thrust Trajectories using Chemical Propulsion • Transfer time: ~2 years