Non-Singular Finite-Time Adaptive Attitude Control of Rigid Spacecraft

In this paper, a finite-time adaptive control method is developed for attitude stabilization of rigid spacecraft with inertia uncertainties and external disturbances. A non-singular fast terminal sliding surface is proposed to circumvent the singularity problem. Then, a finite-time controller is designed to guarantee that the attitude and angular velocity converge into a small region within a finite time. By using an adaptive update laws, no prior knowledge on the bound of uncertainty is needed. The effectiveness of the proposed method is verified through comparative simulation results.