Abstract
The analysis of the phase space geometry around the artificial equilibrium points of the circular restricted three-body problem, including solar radiation pressure, is used to investigate “propellant-free” transfers between Lissajous orbits in the Sun-Earth system. It is assumed that the required transfer maneuvers are achieved by means of instantaneous changes in the spacecraft’s lightness parameter and/or in the incidence angle of the sail with respect to the Sun-line direction. Using a semi-analytic solution of the linearized equations of motion around the libration points , this paper develops a systematic methodology for general solar radiation pressure assisted maneuvers.
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