Optimal Escape from Sun-Earth and Earth-Moon L2 with Electric Propulsion

Optimal low-thrust trajectories for the direct escape from Earth’s sphere of influence, starting Sun-Earth or Earth-Moon L2, are analyzed with an indirect optimization method. The dynamic model considers four-body gravitation and JPL ephemeris; solar radiation pressure is also considered. Specific techniques improvements to method introduced tackle highly chaotic nonlinear dynamics motion close Lagrangian points, which challenges remarkable precision results show that have optimal performance when perturbation acts favorably in both thrust coast phases. effects Moon perturbations more evident L2 escapes compared those L2. EML2 single- two-burn solutions depending on trajectory deflection, needed a favorable perturbation. SEL2 escapes, contrary, mainly single initial burn long arc, but need additional final arc if required C3 high. As applications such Point trajectories, include considerations about maneuvers different high-fidelity Lyapunov orbits interplanetary towards near-earth asteroids.