Variable structure control for the attitude of flying vehicle with parameter uncertainties

In this paper, a variable structure attitude controller is proposed. it' s based on the timescale separation and with two loops, faster loop and slower loop respectively. Inertia uncertainties and aerodynamic moment uncertainties are taken into consideration simultaneously, In order to track the command signals perfectly, the sliding surface is of integral form, Overall stability of two loops in the reaching phase is analyzed based on the Lyapunov function theoretically, and simulation results demonstrate the validity of the proposed attitude control system.