O efeito de enrijecimento por tensão piezeletricamente induzida na estabilidade aeroelástica de painéis aeronáuticos

Abstract

This work aims to study the aeroelastic stability boundary of flutter in aircraft panels, curved or flat, subject to the stress stiffening caused by the piezoelectric actuator (PZT). The Hamilton's principle was used to obtain the equilibrium equations and boundary conditions of the problem. The finite element method was employed to solve the equations. Panels manufactured in composite material (boron-epoxy) or conventional material (aluminum 2024- T3) with two symmetric layers of piezoelectric material (PZT-5A), bonded to the top and bottom faces of the plates were investigated. Voltage was applied to the piezoelectric actuator to determine the dynamic pressure corresponding to the point of occurrence of flutter of the structure. The analysis was extended to various panel configurations and effects such as variation of elongation of the plate, the curvature, lamination angle of the plate, boundary conditions, reverse voltage and the variation at the thickness of the panel on the flutter velocity were investigated. The study showed that mechanical strain-induced piezoelectric effect increases the rate of occurrence of flutter, stabilizing the plate. This stiffening of the structure is related to the voltage applied on the actuators and the geometrical parameters of the plate. Thus, one can control the occurrence of flutter speed by controlling the voltage applied and the proper design of the geometric properties of the panel.