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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 speeds are often susceptible to the occurrence of limit-cycle type self-excited vibrations called flutter. Panel flutter is resulting from the dynamic instability of the aerodynamic, inertia, and elastic forces of the system. The equations of motion for panel flutter are derived using Von Karman's large deflection plate theory and quasi-steady aerodynamic theory. The equations are given in terms of the displacement and are presented in non-dimensional form. Galerkins method is used to transform the system of nonlinear partial differential equations into a system of nonlinear ordinary differential equations in time variables. The obtained equations are then solved by the method of harmonic balance and Newton-Raplison algorithm. The results are compared with both theoretical and experimental results given in publications. Then, a parametric study is performed to study the effects of aerodynamic loading, aerodynamic damping, structural damping, in-plane applied loads, thermal stresses and cavity pressure.

Keywords

Panel Flutter; Aerodynamic Loading; Aerodynamic Damping; Structural Damping; Cavity Effect; thermal effect; Von Karman's Large Deflection Plate Theory; Quasi-Steady Aerodynamic Theory; Galerkis Method; Newton-Raphson Algorithm; Harmonic Balance Method

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