Abstract
In this work the reconfiguration of spacecrafts flying in formation with low-thrust propulsion has been faced. The aim is the development of a control strategy that reduces the propellant use for reconfiguration maneuvers and that can be applied in real time. First a method to generate the optimal trajectory for the entire formation has been developed using a direct approach and a simplified model of the relative dynamics with respect to elliptic reference orbits, then the same method has been applied to control the maneuvers. Finally simulations considering a complete model have been carried out for different kind of reconfigurations.