Buckling analysis for anisotropic laminated plates under combined inplane loadsThe buckling analysis presented considers rectangular flat or curved general laminates subjected to combined inplane normal and shear loads. Linear theory is used in the analysis. All prebuckling deformations and any initial imperfections are ignored. The analysis method can be readily extended to longitudinally stiffened structures subjected to combined inplane normal and shear loads.
Viswanathan, A. V.
Baker, L. L. (Boeing Commercial Airplane Co. Renton, Wash., United States)