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Corresponding Author

Abou-Amer, S.

Subject Area

Mechanical Power Engineering

Article Type

Original Study

Abstract

Exterior panels forming the exterior 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 the prevention and control of flutter, without adversely affecting the weight and cost, is desirable and it is the objective of this work by using damping materials. The nonlinear equations of motion for panel flutter using Von-Karman's farge deflection plate theory are modified to include damping material layers. At first, a viscoelastic damping layer is considered to be perfectly bonded to the surface of the plate to investigate the extension damping treatment. Secondly, the viscoelastic damping layer over the plate is constrained by a third layer called constrained layer to investigate the shear damping treatment. The two types of damping treatment proved to be able to prevent panel flutter successfully at prescribed operating conditions. But for the same panel weight, the constrained damping layer technique is more efficient than the free damping layer technique.

Keywords

Panel Flutter; Aerodynamic Loading. Aerodynamic Damping. Structural Damping; Cavity Effect; thermal effect; damping material; Extension Damping Treatment; and Shear Damping Treatment

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