Vibration Control Analysis of Aircraft Wing by Using Smart Material

Abstract

Many of the mechanical systems exposed to undesired vibrations. These vibrations are removed by using active vibration control (AVC) and hence stability the response of the system. Smart structure technology is used for vibration reduction. Therefore the aircraft wing is embedded by Piezoelectric as a sensor and actuator. This material has fast response times and generates large amounts of force. Active vibration control was achieved by used output feedback control. An aircraft wing is numerically modelled with a used shell element and a couple filed analysis on piezoelectric between the displacement and the voltage. Output feedback control has been inserted to a finite element method by using ANSYS parametric design language (APDL). The control of free and forced vibration for smart structure was investigated. Free vibration is produced by aerodynamic force (lift force) at maximum speed of the aircraft and by the initial condition. Harmonic excitation (sin wave) is considered in the forced vibration control by using a piezoelectric shaker. Active vibration control was studied with different control gains and actuation voltages which affected the vibration control. The effect of changing the position of PZT, collected pair on mass and stiffness of smart structure as passive control (Control OFF) was investigated and then the optimal location was found. Experimental works for active vibration control of smart structure have been presented to verify the closed loop simulations. Free vibration, force vibration and natural frequency are obtained for experimental works by LABVIEW programs. It was observed that APDL ANSYS results were well matched with the experimental results. Settling time for free vibration, when the control OFF, is 15s, and when the control ON it is 3s. Displacement Amplitude for force vibration when the control is OFF it is ± 0.04m and when the control is ON it is ± 0.0005m.

Keywords: Smart material, Aircraft wing, Active vibration control.