Alternative approach to the DART mission by the use of gravity assist maneuvers with the Moon and solar sails

This section is divided into two parts. In the first of them, a general example for the R4BP is presented to demonstrate the procedures implemented in this paper. In the second one, multiple missions to the NEA Didymos are considered, with different sail loading and launch dates.

Transfer in the restricted four-body sun-earth-moon-spacecraft problem

Following the methodology presented in “Methodology” Section, a vehicle is launched in the farthest reach TGE, described in “Restricted four-body problem and trajectories G” Section, and deploys its solar sail after approximately 22 days from…