Journal of Applied Sciences1812-56541812-5662orgz10.3923/jas.2008.1479.1486JavadiH.RajabiI.YavariV.H. KadivarM.8200888The aim of this study is computing and evaluating the behavior of the laminated composite plate at the contact area in single lap, mechanically fastened joints. The analyses involve three dimensional finite element models performed by ABAQUS 6.4-PR11 code to evaluate the stress distribution in contact surface, separation angle, the magnitude and location of maximum radial stress. Results are determined for composite laminates with different layer configurations and attempts are made to validate the models with previous works. For cross ply and angle ply configurations only symmetric stacking sequences are used while for quasi-isotropic laminate both symmetric and non-symmetric models are generated. In cross-ply laminate symmetric separation about bearing plane could be found while in quasi-isotropic and angle-ply laminates non-symmetric separation occurs. Also, the separation angle is less than 90° in symmetric laminates and greater than 90° in some plies of non-symmetric laminates.]]>Ireman, T.,2001Aktas, A. and H.M. Dirikolu,2003Aktas, A. and H.M. Dirikolu,2004Camanho, P.P., S. Bowron and F.L. Matthews,1998Chang, F.K.,1986Eriksson, L.I.,1986Hyer, M.W., E.C. Klang and D.E. Cooper,1987Çten, B.M. and O. Sayman,2003Ireman, T.,1998Karakuzu, R., T. Gülem and B.M. Çten,2006Kelly, G. and S. Hallström,2004Madenci, E. and L. Ileri,1993McCarthy, C.T. and M.A. McCarthy,2005Mevlüt-Tercan, O.A. and A. Akta,2005Okutan, B.,2002Okutan, B. and R. Karakuzu,2003Truong Chi, T., S.V. Lomov and I. Verpoest,2002