Active Vibration Control Based On Piezoelectric Smart Composite

The maneuverability, stability, reliability and cruise duration of the aircraft canaffect the results of a war. Front fuselage and airfoil of the two-tail aircraft canproduce unsteady and disordered eddy currents at a high angle of attack flightconditions. Eddy current load is usually exerted repeatedly on the vertical tail of theaircraft in the form of bending moment and torque. That the band of eddy currentload covers the low-order natural frequency of the vertical tail can cause hugevibration and dynamic stress in the vertical tail. It makes the vertical tail structureemerge premature fatigue damage and affects the combat effectiveness andreliability of the aircraft seriously.Macro fiber composite (MFC), as one type of the piezoelectric smartcomposite, not only has the efficiency of high-strain-driven, but also can realizedirectional drive and directional sensing. MFC can be pasted on the surface becauseof its excellent flexibility. And MFC can control the vibration caused by vertical tailstructure, thus it can increase the life of the aircraft and reduce maintenance costs.This paper regards the application of MFC on the active vibration control of verticaltail structure as the research background and studies the driving mechanism andsensing mechanism of MFC. And this paper also establishes the simplified structurefinite element model of vertical tail and carries out active vibration controlexperiment of vertical tail structure. The main research contents of this thesis are asfollows:First, MFC is simplified transverse isotropic materials on the basis of thestructural properties of it. At the same time the three-dimensional linearelasticity-piezoelectric equations are obtained. This paper investigates the drivingmechanism and sensing mechanism of MFC pasted on the surface of plate structureon the basis of the P2type MFC and the P1type MFC. In the end, the equation ofdriving moment and the equation of sensing voltage are derivate.Second, the infinite model of MFC is established by ABAQUS. Andpiezoelectric effects of MFC are simulated and analyzed. And the simplified modelof the vertical tail structure is carried out mode analysis. In the end, this papercarries out vibration control simulation analysis of several aircraft vertical tail structures by UAMP subroutines, and applies equivalent damping ratio to measurethe vibration reduction.Third, this paper conducts active vibration control experiments of vertical tailstructure. And vibration response of different patch position is obtained underdifferent incentive. And the experimental results verify fatherly the application ofMFC on achieving the vertical tail structure damping.