A Dynamic Instability Study of Shallow Shell Panels with Simply Supported Edges

An efficient, general finite element (FE) of triangular shape is employed in investigating the panels (flat and shallow shell curved panels) dynamic instability subjected to supersonic air flow. The all edges of panel are simply-supported (SSSS). The fluid that's on the plate's bottom is not in motion. Linearized piston theory is used to determine aerodynamic loads. Hamilton's principle is used to generate the dynamic instability motion equations, which characterize panels instability during their interaction with the supersonic the airflow. The eigenvalues of Lagrange's motion equation are obtained by conventional methods. Here, aerodynamic damping is excluded. In panels, the basis of thin, very small deformation shells is considered. Critical dynamic pressure was determined. The FE code is corroborated by examining outcomes of a flat square panel (radius of curvature R of shallow shell tends to ∞) with the literature data. In addition, the proposed shallow-shell FE is applied to cylindrical curved plates with SSSS boundary conditions to demonstrate the limited dynamic instability results, corresponding to different curvature parameters available in the literature for different FE formulations. Results and data from the literature compare fairly. It is clear that the dynamic instability limit of the panels grows with an increase in the curvature parameter (in the lower range) of the panels with SSSS edge constraint. It was figured out that in-plane edge constraints had an impact on dynamic instability limits.