Interlaminar stress analysis of carbon fiber-reinforced laminated plate with a hole

The interlaminar stresses of a carbon fiber-reinforced laminated plate with a hole were analyzed using three-dimensional finite element numerical simulation. This laminated plate was subjected to uniaxial forces and composed of layers with typical ply angles . The effects of the ply parameters on the interlaminar stress distribution were investigated; in the meantime, the maximum value and detailed distribution of interlaminar stresses in different typical interfaces were presented. The results show that the location of interfaces along thickness only affects the magnitudes of interlaminar stresses but not the trend of distribution, and the stacking sequence ( or ) affects neither the magnitudes of interlaminar stresses nor the trend of distribution. Furthermore, the maximum normal stress of interface occurs between layers at 90° from the loading axis with its value reaching 51% of the value of applied stress, the maximum interlaminar shearing stress occurs between layers: the maximum circle shearing stress occurs at 74° with its value reaching 64% of the value of applied stress, and the maximum radial shearing stress occurs at 66° with its value reaching 25% of the value of applied stress.