Design of an Active Disturbance Rejection Control for Transonic Flutter Suppression

Conventional controls, such as an optimal control with a notch filter, are able to remove the flutter instability under subsonic flows but may need higher adaptability to make the controllers stable under transonic flows with oscillating shocks, especially for the wing model with parameter uncertainties. In this paper, an error-based control law designed via the active disturbance rejection control algorithm is proposed for the transonic flutter suppression of a wing model with parameter uncertainties and measurement noises taken into account. With the proposed control law, the observed output signal and its time derivative, the unmodeled dynamics, and the measurement noises are consistently estimated. The observed output signal and its time derivative are used to design a feedback control law for adjusting the output errors, whereas the observed unmodeled dynamics and the measurement noises are used to guarantee the adaptability and anti-interference of the proposed controller. To demonstrate the control performances, the wing of benchmark active control technology is studied for the transonic flutter suppression. The numerical results show that the present control law can effectively suppress the transonic flutter at a wide range of Mach numbers and has noticeable adaptability to the variation in stiffness parameters.