Optimization of a Low-Thrust Heliocentric Trajectory between the Collinear Libration Points of Different Planets

The aim of this study is to optimize a low-thrust interplanetary trajectory using collinear libration points L 1 and L 2 as the junction points of the geocentric or planetocentric segments of the trajectory with the heliocentric segment. The problem of optimizing the heliocentric segment of perturbed low-thrust interplanetary transfer is considered in the four-body ephemeris model, which includes the Sun, Earth, target planet, and spacecraft. To optimize the trajectories, an indirect approach is used based on Pontryagin’s maximum principles and the continuation method. The possibility of reducing the characteristic velocity in comparison with the estimates obtained through the method of zero sphere of influence is shown.