•  
  •  
 

Corresponding Author

Abou-Amer, S. A.

Subject Area

Mechanical Power Engineering

Article Type

Original Study

Abstract

Exterior panels forming the skin of flight vehicles traveling through the atmosphere at high supersonic speed are often susceptible to the occurrence of limit-cycle type self excited vibrations called flutter. The development of methods for panel flutter control is desirable and it is the objective of this work by using piezoelectric materials. The nonlinear equations of motion for panel flutter using Von-Karman's large deflection plate theory and the quasi-steady aerodynamic theory are modified to consider the composite plate with the piezoelectric layer. The composite plate consists of two piezoelectric layers bonded perfectly to the upper and lower surface of the original panel layer. When a voltage is applied to the piezoelectric layers, an induced strain in the plate material takes place and consequently tensile in-plane load is obtained. These tensile loads shift the onset of flutter point to about twice the value of the critical dynamic pressure for the plate alone. The values of control voltage and the effect of piezoelectric material properties are investigated. The method gives good results and succeeds in suppressing the panel flutter at its operating condition.

Keywords

Panel Flutter; Aerodynamic Loading; Aerodynamic Damping; Structural Damping; Cavity Effect; thermal effect; Smart Structure; Piezoelectric Material

Download

Share

COinS