Formation Flying: Relative Orbits' Modelling and Control Through Eulerian Orbital Elements

This work deals with the dynamics of spacecrafts in formation. The relative motion is described through the difference between the Eulerian orbital elements of the deputy satellite and the chief's ones. Eulerian orbital elements are defined from the constants of motion of the Intermediary Motion: they include perturbations till part of the 4th zonal harmonic of the Earth's gravity potential. A target relative motion insensitive up to the J(3) is defined by matching the time variations of the Eulerian angular elements. Reconfiguration manoeuvres are performed by a relative orbit control where errors in the orbital elements are feed-back.