Lyapunov-Floquet control of satellite relative motion in elliptic orbits

This paper proposes a method for continuous-thrust control of satellite formations in elliptic orbits. A previously calculated Lyapunov-Floquet transformation relates the linearized equations of relative motion for elliptic chief orbits to the Hill-Clohessy-Wiltshire equations describing circular chiefs. Using a control law based on Lyapunov-Floquet theory, a time-varying feedback gain is computed that drives a deputy satellite toward rendezvous with an elliptic chief. This control law stabilizes the relative motion across a wide range of chief eccentricities.