Wing box transonic-flutter suppression using piezoelectric self-sensing actuators attached to skin

Abstract

The main objective of this research is to study the capability of piezoelectric (PZT) self-sensing actuators to suppress the transonic wing box flutter, which is a flow-structure interaction phenomenon. The unsteady general frequency modified transonic small disturbance (TSD) equation is used to model the transonic flow about the wing. The wing box structure and piezoelectric actuators are modeled using the equivalent plate method, which is based on the first order shear deformation plate theory (FSDPT). The piezoelectric actuators are bonded to the skin. The optimal electromechanical coupling conditions between the piezoelectric actuators and the wing are collected from previous work. Three main different control strategies, a linear quadratic Gaussian (LQG) which combines the linear quadratic regulator (LQR) with the Kalman filter estimator (KFE), an optimal static output feedback (SOF), and a classic feedback controller (CFC), are studied and compared. The optimum actuator and sensor locations are determined using the norm of feedback control gains (NFCG) and norm of Kalman filter estimator gains (NKFEG) respectively. A genetic algorithm (GA) optimization technique is used to calculate the controller and estimator parameters to achieve a target response.

A study of the natural modes of vibration and aeroelastic stability of a plate with a piezoelectric material

“…(1) a piezoelectric potential difference is applied over the wing, (2) the corresponding stresses are calculated using the elastostatic equation (same as equation (1), but without the dynamic term, i.e. u tt =0), and (3) the geometric stiffness matrix is obtained using equation (24).…”

“…In aeroelasticity, smart wings (wings equipped with piezoelectric sensors and actuators) have been studied. One example is a model developed by Otiefy and Negm [24,25] for the control of a smart wing using an equivalent plate model. They compared three different control theories for wing aeroelastic control: linear quadratic regulator, the optimal static output feedback, and the linear quadratic Gaussian control.…”

Active Flutter Suppression and Aeroelastic Response of Functionally Graded Multilayer Graphene Nanoplatelet Reinforced Plates with Piezoelectric Patch

“…In order to control the flutter of a composite panel with piezoelectric actuators in supersonic airflow, Moon and Hwang [25] proposed an optimal control algorithm to improve the aeroelastic performance of the panel with a lower control input. Based on three different control strategies, Otiefy and Negm [26] utilized piezoelectric self-sensing actuators to reduce the flutter response of a transonic wing.…”