Abstract
Aeroelastic characteristics of supersonic panels with different boundary conditions are analyzed. The classical thin plate theory is used in the structural modeling. The unsteady aerodynamic pressure is evaluated using the supersonic piston theory. To formulate the governing equation of motion for the aeroelastic structural system, Hamilton’s principle is carried out. The assumed mode method (AMM) and the finite element method are used to obtain the discrete equation of motion. Frequency-domain method is conducted to analyze the aeroelastic performances of the panel with different boundary conditions. The special flutter properties of panels with elastically restrained boundary condition are also investigated. The accuracy of the AMM in the flutter analysis of panels with different constraints is researched. Aeroelastic characteristics of the panels with different boundary conditions are also investigated.
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