Flexural analysis of symmetric laminated composite beams using C1 finite element

A two-noded C1 finite element of 8 d.o.f. per node, based on a higher-order shear deformation theory, has been developed for flexural analysis of symmetric laminated composite beams in this note. The element assumes a parabolic variation of shear stress across the thickness of beams to avoid layer-dependent shear correction factors. Numerical results are given for simply supported, symmetric laminated composite beams, loaded equally at the top and bottom surfaces of the beams and are compared with the exact elasticity solution of Pagano. The special feature of the element is that transverse normal stress across the thickness of the beams, which is playing a crucial role in delamination, is reasonably accurately calculated using constitutive law even though unrealistic discontinuities at the interfaces of laminates are shown by the element.