Optimal geometry for lunar swing-by maneuvers aided by solar sails in the restricted four-body problem

As the geometry of the swing-by maneuver greatly influences the outcome of the gain of energy and a possible escape trajectory, a study on the relative positioning between the Earth and the Moon is presented to define the conditions for the best transfers to the terrestrial planets of the solar system in the restricted four-body Sun–Earth–Moon–spacecraft Problem. At the start of the numerical simulation, a solar sail with loading of 164.7 g/m2\documentclass[12pt]{minimal} \usepackage{amsmath} \usepackage{wasysym} \usepackage{amsfonts} \usepackage{amssymb} \usepackage{amsbsy} \usepackage{mathrsfs} \usepackage{upgreek} \setlength{\oddsidemargin}{-69pt} \begin{document}$$^2$$\end{document} is already deployed to conduct transfers towards Venus and Mars.