SEMI-A VIBRATION SUPPRESSION OF AIRCRAFT PANEL USING PIEZOELECTRIC ACTUATOR WITH SYNCHRONIZED SWITCH DAMPING TECHNIQUE

摘要

Owing to low power consumption and easy implementation, semi-active vibration control methods were more and more applied to solve kinds of structural vibration problems. Among these semi-active treatments, Synchronized Switch Damping (SSD) technique was proved to be an effective method. Compared with the passive ways, this control system possessed good immunity against structural dynamic properties shift due to environmental changes. They were also compact, lightweight which was convenient to apply to specific structure with weight or size restriction. In this study, the principle of SSD technique was introduced. An electromechanical coupling equation of this technique was proposed by employing a state space representation. Then, the mathematical model of SSDI technique was verified by using Matlab/Simulink software. Finally, an experiment was carried out on an aircraft panel which was fixed on a progressive wave tube under acoustical load. Experimental results showed that the vibration amplitude of this aircraft panel was attenuated to 75% of its original at its first resonant frequency when SSD technique was enabled. It was also found that the damping efficiency decreased with the vibration level increasing.