A DAMAGE MODEL FOR FIBER REINFORCED COMPOSITE LAMINATE.

In this paper a technique for analyzing mixed mode delamination in laminate plates under in-plane loading conditions is developed. There is used the interface methodology which adopts the first-order shear laminate plate theory. The 2D numerical model of delamination is obtained by using of Finite Element Method in program ANSYS. Displacement, interface reaction and strain energy release rate distribution along the delamination front are illustrated. The results obtained from each mode response analysis are compared. [ABSTRACT FROM AUTHOR]