Abstract: In this paper, the delamination solution of composite laminates,ortho-gonally and symmetrically stacked under axial tension is given.First of all,the eigen function expansions of strass and displacement fields, satisfying all of the basic equations,boundary conditions on crack surfaces and conditions of continuities between different plies are derived.Furthermore, the stress intensity factors as the coefficients of leading terms in the above expansions are determined by the generalized variational principle for multi-regions,to satisfy the boundary conditions.There are only line integrals in the variational equations due to the previous satisfaction of all basic Pquations.The computations shoe that this method of solution has the advantages of rapid convergency and time-saving.