Cycler orbits utilizing low thrust propulsion systems

Earth return orbits are investigated using continuous acceleration provided by low-thrust propulsion system. The problem is formulated as an optimal control problem, and solved by calculus of variation approach. The applicability of low-thrust Earth return trajectories to cycler orbits between the Earth and Mars is to be discussed. Cycler orbits are trajectories, which encounter the same planets on a regular interval repeatedly. Future study aims at constructing the cycler orbits with low thrust propulsion analytically in the restricted three body problem and Hill's equations.