Abstract: The effect of delamination on the flutter boundary of two‐dimensional laminated plates are investigated theoretically. Linear‐plate theory and qusai‐steady aerodynamic theory are employed. A simple beam‐plate‐theory model ...

Abstract: This paper presents a simple mathematical model that can be used to predict the vortex‐excited resonant response of two flexible cylindrical structures in line with the wind direction. A modified van der Pol equation is ...

Abstract: Free vibration behavior of buckled composite plates are studied by using a high precision triangular plate element. This element is developed based on a simplified high order plate theory and ...

Abstract: A high precision triangular plate element is developed for the free vibration analysis of thermally buckled composite sandwich plates. Due to an uneven thermal expansion in the two principal ...

Abstract: The effect of transverse shear deformation on the supersonic flutter of composite panels has been investigated using the finite element method. First‐order shear‐deformation laminated‐plate theory and quasi‐steady aerodynamic ...

Abstract: By considering the total transverse displacement of a sandwich plate as the sum of the displacement due to bending of the plate and that due to shear deformation of the core, a 72 degrees of freedom high precision high ...

Abstract: A simple mathematical model for predicting the vortex‐excited resonant response of two cylinders in line with the wind direction is presented. For the model, a modified van der Pol equation is employed to account for the ...

Abstract: The effects of in-plane load on flutter characteristics of delaminated two-dimensional homogeneous beam plates at high supersonic Mach number are investigated theoretically. Linear plate theory and ...