Singular stress in the interface of composite laminates is seriously related to the fracture and failure of them. Exact analysis and suitable treatment of this character of composite laminates can make to avoid facing accident begun at the singular point of their interface which can exist in structures and machinary using such composite laminates.
For the purpose of analysis of this character, firstly, Mode decomposition is introduced for calculating stress intensity of delamination crack under generalized plane deformation, and the exactness of its solutions is verified. Secondly, Enriched F.E.M. is constructed, and stress intensity and stress distribution for delamination crack under generalized plane deformation is obtained. Finally, the results of delamination crack obtained from Enriched F.E.M. and Mode decomposition are compared with each other. Good coincidence of the results obtained from the two methods is showed.
Through this coincidence, confidence of these results can be produced and they can help manufacturing such composite laminates.
