Finite-time output feedback attitude control for spacecraft using “Adding a power integrator” technique

This paper investigates the problem of finite-time output feedback control for spacecraft attitude stabilization with attitude-only measurement. First, a finite-time filter is proposed to generate the pseudo-angular-velocity signal, which is fed to the controller, and then a continuous finite-time attitude controller is designed based on the proposed filter. The overall finite-time stability of entire filter-controller closed-loop system is given through the adding a power integrator technique. The rigorous proof shows that the attitude will converge to its equilibrium states in the absence of disturbance. When considering disturbance, states will be eventually stabilized to a residual set of equilibrium in a finite time. Numerical simulation results illustrate the proposed method can provide the fast transient response, energy-efficient and robust attitude control performance.