Software tools have been developed (also under ESA contract) to design optimal low-thrust gravity assisted trajectories. The knowledge acquired in this field is related to the optimal control and optimization techniques, with particular reference to the optimal control problems with both direct and indirect methods, collocation, simple and multiple shooting techniques. Furthermore, the research group is familiar with global optimization algorithms based on heuristic theories to design optimal interplanetary trajectories.
Optimization objective function for a two impulse direct Earth-to-Mars transfer. The ∆V requirements show quasi-periodical features on the date of departure, associable to the synodic periods of the planetary system.