Adaptive fault-tolerant boundary vibration control for a flexible aircraft wing against actuator and sensor faults

The vibration control problem was investigated in this study in the presence of unknown loss of actuator effectiveness fault and loss of sensor effectiveness fault in a flexible aircraft wing system. A series of partial differential equations was used as the mathematical model of the wing with unknown boundary disturbances. An adaptive fault-tolerant boundary controller was designed accordingly. All signals of the closed-loop control system are globally uniformly bounded and the controlled state asymptotically converges. Numerical simulations were conducted to validate the proposed control scheme.

Automated summary

This study investigated the vibration control problem in a flexible aircraft wing system with unknown loss of actuator effectiveness fault and loss of sensor effectiveness fault. An adaptive fault-tolerant boundary controller was designed to ensure globally uniformly bounded signals and asymptotic convergence of the controlled state in the closed-loop control system. Numerical simulations were conducted to validate the proposed control scheme.