Higher Order Integral Sliding Mode Control for Spacecraft Formations in Eccentric Reference Orbits

Considering the relative orbit control problem of spacecraft formations in eccentric reference orbits, this paper proposed a higher order integral sliding mode control law. This control law can not only restrain chattering, but also make system states converge to equilibrium points in finite time, and with high accuracy and global robust. Furthermore, the general relative equations of motion were transferred into non-dimensional form by using Lyapunov transformation. This form is easy for design. Numerical simulations demonstrate that the higher order integral sliding mode control can counteract chattering with optimal fuel consuming and high accuracy.