Options for Optimal Trajectory Design of a Mission to NEOs Using Low-Thrust Propulsion

This paper deals with the refinement process of optimal trajectories for missions that use low-thrust propulsion, that were found using a direct transcription method with multiphase approach. Two different options are considered to refine the trajectories. The first option considers the decay of performances of the engine, with the distance from Sun, in terms of specific impulse and thrust. The second considers the case of constant thrust, and is obtained by splitting each original phase accordingly with the switching scheme found in the original solution. A mission to NEOs has been considered to show the steps of the process.