Solar radiation pressure end-of-life disposal for Libration-point orbits in the elliptic restricted three-body problem

This paper proposes an end-of-life propellant-free disposal strategy for Libration-point orbits in the elliptic restricted three-body problem as an extension of a preliminary study performed in the circular problem. The spacecraft is initially disposed into the unstable manifold leaving the Libration-point orbit, before a reflective sun-pointing surface is deployed to enhance the effect of solar radiation pressure. This allows closing the pulsating zero-velocity curves at the pseudo Libration-point, SL2 such that, the consequent increase in energy prevents the spacecraft returning to Earth. An energy approach is used to compute the required area for the Hill's curves closure at the pseudo Libration-point SL2, via numerical optimisation. The Gaia mission is selected as an example scenario since a low deployable area is required in the circular case. Guidelines for the end-of-life disposal of future Libration-point orbit missions are proposed.