Nonlinear finite element analyses of tee joints of laminated composites

Geometrically nonlinear finite element analysis is conducted to determine three dimensional stress components of a composite tee joint, which is formed when a right angled plate is adhesively bonded to a base plate. Two different boundary conditions of the tee joint, such as assuming the base plate of the tee joint as rigid and flexible, have been considered. The stress components of the tee joint with three different laminate stacking sequence viz. unidirectional [0]8, cross ply [(0/905)s]2 and angle ply [(+45/-45)s]2 laminates have been evaluated when it is subjected to an out-of-plane loading through the right angled plate, and the effects of laminate stacking sequence on three-dimensional stresses have been studied. Conclusions about the stresses of the composite tee joint with different boundary conditions, stacking sequence, and ply styles are drawn.