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

Abstract

This paper investigates the aeroelastic flutter and vibration reduction of functionally graded (FG) multilayer graphene nanoplatelets (GPLs) reinforced composite plates with piezoelectric patch subjected to supersonic flow. Activated by the control voltage, the piezoelectric patch can generate the active mass and active stiffness that can accordingly increase the base plate’s stiffness and mass. As a result, it changes the GPLs reinforced plate’s dynamic characteristics. The motion equation of the plate-piezoelectric system is derived through the Hamilton principle. Based on the modified Halpin–Tsai model, the effects of graphene nanoplatelets weight fraction and distribution pattern on the dynamic behaviors of the plate are numerically studied in detail. The result illustrates that adding a few amounts of grapheme nanoplatelets can effectually enhance the aeroelastic properties of the plates. Two kinds of control strategies, including the displacement and acceleration feedback control, are applied to suppress the occurrence of the flutter of the plate. It shows that the displacement and acceleration feedback control can improve the critical flutter Mach number of the plate by attaching active stiffness and active mass, respectively. Furthermore, the combined displacement and acceleration feedback control has a better control effect than that of considering only one of them.

Three-Dimensional Thermoelasticity Analysis of Viscoelastic FGM Plate Embedded in Piezoelectric Layers under Thermal Load

“…Here F p is the coefficient matrix introduced in Equation (A13) in the Appendix A. The general solutions for Equation (34) for the sensor and actuator layers are, respectively:…”

“…Utilizing a meshless local Petrov-Galerkin technique and considering thermo-mechanical loads, an exact solution for thermo-viscoelastic behaviors of fiber-reinforced polymer composites was performed by Liu and Shi [33] using viscoelastic constitutive equations. The exact solution for active control performance, vibration dampening, and aeroelastic behavior of simply supported FG-GPLR composite plates bonded with piezoelectric patches as sensors and actuators under supersonic airflow was examined by Chen et al [34].…”

Research on Panel Flutter Considering the Effect of Convective Active Cooling

“…Culler et al [14] developed a comprehensive aerothermoelastic model for the analysis of panel structures in hypersonic flow, and investigated the impact of fluid-thermal-structural coupling on aerothermoelastic behavior using Galerkin's method and the third-order piston theory. Chen et al [15] analyzed the aeroelastic flutter of a composite panel with functionally graded material. The result illustrated that adding a few amounts of grapheme nanoplatelets can effectually enhance the aeroelastic properties of the plates.…”

Experimental and Numerical Flutter Analysis Using Local Piston Theory with Viscous Correction

“…Approximate unsteady aerodynamic models, including piston theory [4], Van Dyke second-order theory [5], shock-expansion theory [6], Newtonian impact theory [7] and lifting surface/panel approaches [8], are based on linear potential flow theory and the quasi-steady flow assumption, which produce sufficiently accurate results at limited AOAs [9]. Therein, piston theory is attractive at the stage of preliminary design and has been extensively used and developed [10][11][12][13][14]. Local piston theory (LPT) [15] integrates classical piston theory with the CFD method, ensuring both high computational precision and efficiency.…”