Aeroelastic modeling and analysis of honeycomb plates in high-speed airflow with acoustic load and general boundary conditions

This paper investigates the modeling and aeroelastic properties of laminated plates with honeycomb core by a semi-analytical approach, where both acoustic load and general boundary conditions are considered. The equivalent material properties of the honeycomb structures are determined by the corrected Gibson’s formula. The energy functional of the plate is derived based on the first-order shear deformation theory (FSDT) and the effect of aerodynamic pressure is taken into account by introducing the supersonic piston theory. A modified shear correction factor is adopted in this study to improve the accuracy of the method. The Hamilton’s principle is employed to formulate the governing equations of the system, and the solutions of the problem with both classical and elastic boundary conditions are solved by a modified Ritz approach. The results obtained by the proposed method show good agreement with those by the finite element method and in open literature. Finally, parametric studies on the aeroelastic behaviors of the plate concerning the boundary conditions, layer thickness and honeycomb geometry are carried out.