The effect of piezoelectrically induced stress stiffening on the aeroelastic stability of curved composite panels

Aeroelastic analysis and active flutter suppression of an electro-rheological sandwich cylindrical panel under yawed supersonic flow

“…(6), and subsequently using the results of the Hamilton's principle (Eq. (5)), after some very tedious but standard manipulations [19,22], one obtains the final displacement equations of motion for the electrorheological-fluid-based composite cylindrical panel in the form δu i :…”

“…Wang et al [50] used the eigen-vector orientation method and finite element modeling in a linear optimal (LQR) control design context to actively suppress the subsonic and supersonic flutter of panels via piezo-electric actuator layers. Almeida et al [6] employed the finite element method to study the aeroelastic stability boundary modification of supersonic flutter in aircraft composite curved panels subjected to voltageinduced stress stiffening effect caused by the action of surfacebonded piezo-electric (PZT) actuators. It was concluded that the occurrence of flutter speed can be suppressed by controlling the applied voltage as well as proper geometric design and tailoring of the composite panel.…”

Nonlinear Flutter Response of Heated Curved Composite Panels with Embedded Macrofiber Composite Actuators

“…where n is the number of the truncation modal. By substituting equation (18) into equation 17, modal coordinate transformation relations can be introduced: e equations of motion (17) are transformed into the following reduced nonlinear system in the modal coordinate as…”

“…Most of the studies on panel flutter suppression mainly rely on smart materials, and piezoelectric materials are the most representative smart materials because piezoelectric materials are capable of altering the structure's response through sensing, actuation, and control. By now on, the main piezoelectric materials such as piezoceramic [15][16][17] and MFC [18,19] are used in panel flutter suppression. Lai et al [20] studied to control the nonlinear flutter of a simply supported isotropic plate by using piezoelectric actuators.…”

Dynamical analysis of a thin-walled rectangular plate with preload force

“…By studying the stress-Stiffening effects on laminated plates with piezoelectric actuators, Almeida [26] concluded that the importance of the stress-stiffness effect depends on the magnitude of the in-phase actuation and geometric arrangement of the piezoelectric actuators, boundary conditions, geometry of the problem, and material properties. Almeida et al [27] investigated the effects of stress stiffening on the aero-elastic stability boundary of flutter in aircraft composite components, and they found that stress stiffening can increase the rate of occurrence of flutter. Ha et al [28] investigated the asymmetric bending of the Allomyrina dichotoma beetle's hind wing via FE model.…”