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.
Highlights
Thin-walled structures with characteristics of lightweight, flexible, and low damping have been broadly applied in advanced aircraft
When the external skin of aircraft is subjected to complex aerodynamic flow conditions, the aeroelastic self-excited oscillation, termed the aeroelastic flutter, occurs
Prakash and Ganapathi [1] investigated the supersonic flutter features of functionally graded plates based on the finite element procedure
Summary
Thin-walled structures with characteristics of lightweight, flexible, and low damping have been broadly applied in advanced aircraft. Numerically evaluated influences of the panel geometry, material parameters, boundary conditions, and airflow direction on the supersonic flutter characteristics and critical aerodynamic pressure of laminated composite cylindrical panels and plates. Oh and Lee [23] developed geometrically nonlinear finite elements for the aero-thermoelastic investigation of cylindrical piezoelectric laminated shells They concluded that active piezoelectric actuation could efficiently improve the aerodynamic performance of the shell. Song et al [36,37] investigated the vibration characteristics, buckling, and dynamic responses of multilayer graphene nanoplatelet reinforced plates subjected to the combination of axial compression and transversal loads. The combined piezoelectric and graphenereinforced materials make good candidates for the suppression of structural flutter It seems to be limited for studies in the field of aeroelastic flutter and vibration reduction of plates consisting of graphene reinforced composite and piezoelectric patch. The influence of feedback gain on flutter boundaries and the response near the critical flutter point is discussed in detail
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