Output constraints vibration control for a flexible aircraft wing with prescribed performance

This study focuses on the vibration control and boundary output constraint problems for a flexible wing system. The coupled twist-bending dynamic model of the flexible wing contains several partial differential equations (PDEs) and ordinary differential equations (ODEs). With the help of prescribed performance functions, an innovative boundary controller is designed to achieve the vibration suppression without the violation of prescribed performance. The proposed controller can make the boundary deformations converge to an arbitrarily small residual set. In addition, a disturbance observer is proposed to eliminate the adverse effect caused by unknown external disturbances. Then the asymptotic stability of the closed-loop system is justified by the Lyapunov’s direct method. Finally, numerical simulations are carried out to demonstrate the effectiveness of the proposed control scheme.