Low-thrust propulsion formation flying around libration points

Abstract

We consider families of artificial Halo orbits with a fixed period in the Earth-Sun circular restricted three body problem. The orbits can be used for formation flying missions around Lagrange points. Families of artificial Halo periodic orbits with a fixed period are determined using numerical continuation from a known Halo orbit. The orbits are then used to construct reference trajectories for the satellites to track. The extremum seeking method is used for tuning the gains of the time delay feedback mechanism and of the PD controller.