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