A general framework has been developed to investigate dynamic stability of composite plates under dynamic and static compressive loads. A variationally consistent, higher-order shear deformation theory has been used to model the displacement field. The linear strain-displacement relationship corresponding to the small deformation assumption is used first. Both transverse shear and rotary inertia effects are taken into account. The mathematical model

Large amplitude vibration of simply supported rectangular cross-ply plates paper of Singh et al. [1] is re-visited. One of the presented coefficients for simply supported boundary conditions, namely T8, is found to be erroneously determined. The observed error influences the nonlinear to linear frequency ratio results for the first mode of the simply supported cross-ply symmetric and anti-symmetric square and rectangular plates. The present computations

The focus of this investigation is on the development and validation of non-linear structural dynamic reduced order models of structures undergoing large deformations, with particular emphasis on aircraft panels. Significant efforts are devoted to the formulation and assessment of ‘‘dual modes’’ which when combined with the linear transverse modes form an excellent basis for the representation of the displacement and stress fields in the

A refined higher order shear deformation theory is used to investigate the instability associated with delaminated composite plates subject to dynamic loads. Both transverse shear and rotary inertia effects are taken into account. The theory is capable of modeling the displacement field above and bellow the delamination. All stress free boundary conditions at free surfaces as well as delaminated interfaces are satisfied by this theory. The procedure

A variationaly consistent mathematical model based on the refined higher order theory is used to develop a finite element procedure for analyzing the dynamic instability under biaxial buckling loads of rectangular composite plates. Laminates with various thicknesses and stacking sequence under various biaxial loads and boundary conditions are considered. The natural frequencies and mode shapes as well as the buckling loads and deformed shapes are

This paper focuses on the validation of a reduced order modeling strategy for aircraft panels subjected to combined thermal effects and an incident acoustic wave strong enough to induce a severe geometrically nonlinear behavior. The response of flat panels to two different excitations scenarios serves as a basis to assess the appropriateness of several modal bases for the reduced order modeling. This comparison emphasizes the importance of the in-plane

This paper focuses on the formulation and validation of a reduced order model for the prediction of the response - displacements, stresses, fatigue life - of aircraft panels subjected to a severe thermo-acoustic loading. The reduced order modeling starts with a finite element model from a standard package (MSC.NASTRAN) and produces a set of cubic nonlinear differential equations which are efficiently marched in time. The basis for the representation

A higher order shear deformation theory is used to investigate the instability associated with delaminated composite plates subject to dynamic loads. Both transverse shear and rotary inertia effects are taken into account. The procedure is implemented using the finite element method. Delamination is modeled using the penalty parameter approach. The natural frequencies are computed and compared with NASTRAN 3D results and available experimental data.

A higher order shear deformation theory is used to investigate the instability associated with composite plates subject to dynamic loads. Both transverse shear and rotary inertia effects are taken into account. The procedure is implemented using the finite element approach. The natural frequencies and the critical buckling load are computed and compared with the results based on the classical laminate plate theory and the first-order shear deformation

A refined higher order shear deformation theory is used to investigate the dynamic instability associated with composite plates with delamination that are subject to dynamic compressive loads. Both transverse shear and rotary inertia effects are taken into account. The theory is capable of modeling the independent displacement field above and below the delamination. All stress free boundary conditions at free surfaces as well as delamination interfaces