Trajectory Optimization for a Mission to NEOs, Using Low-Thrust Propulsion and Gravity Assist

This paper deals with the trajectory optimization, through a direct method, for a mission to NEOs, using low-thrust propulsion both for deep space navigation and for Earth escape phase, departing from an Earth orbit. The aim of the work is to demonstrate the possibility to realize a low-cost mission to reach NEOs. First the escape phase has been analyzed, from perigee raising to the border of Earth sphere of influence, verifying the possibility to use the Moon for a gravity assist maneuver. Then the deep space navigation phase has been analyzed considering also more than one NEO as targets.