Continuous Finite-time Control for Spacecraft Formation Flying on Elliptical Orbits

This paper investigates the problem of relative control for spacecraft formation flying on an arbitrary elliptical orbit. The nonlinear dynamic model describing the relative motion between the leader spacecraft and the follower spacecraft is established in the presence of system model uncertainty and external disturbance. A continuous finite-time control scheme is designed by using a new form of terminal sliding modes. Theoretical analysis and simulation results demonstrate the robustness and fast convergence rate of the proposed method.