Issue 50

O. Mouhat et alii, Frattura ed Integrità Strutturale, 50 (2019) 126-140; DOI: 10.3221/IGF-ESIS.50.12 132       0 ( - ) = 0   K K x (16) The critical load is determined by Eqn. (16). The static critical load is determined from Eqn. (16), the critical load  is corresponding to the eigenvector   x . Non-linear static buckling analysis Non-linear static buckling usually involves several variables. These variables construct the stability equations and discrete equations of the virtual working equation:   0 N M F u  (17) Either N F is the combined force component up to the th N level in the problem and M u i s the value of the th M variable. The essential objective is the solution for an Eqn. (17). Newton's method is supposed that after iteration i , an approximate i M u of the solution was obtained as the exact solution of the discrete stability Eqn. (17), this shows that:   1 0    N M M i i F u c (18) With 1 M i c  is the difference between this solution and the exact discrete result. By lengthening the left side of this equation in a series of Taylor’s:       2 1 1 1 ... 0 N N N M M P M P Q i i i i i i P P Q F F F u u c u c c u u u             (19) A linear system of equations: 1 0    NP P N i i i K c F (20) NP i K Is the Jacobian matrix. The best way to measure the convergence of Newton's method is to ensure that the entries in N i F and the inflows in 1 M i c  are small enough. ( ABAQUS Documentation ). N UMERICAL EXAMPLES OF STIFFENED PANEL e considered a square panel, where the total length of the panel 357 a mm  and its width 357 b mm  , with a radius 381 R mm  and thickness of stiffened composite panels 1 T t mm  as shown in Fig. 3, the thickness of each layer is 0.125 t mm  , this panel consists of eight layers. The width of the stiffeners 33 a mm  . The layers with orientations are 0, 15, 30, 45, 60, 75, 90       . Epoxy is treated as a matrix material. Tab. 1 shows the mechanical properties of the panels. The mesh convergence studies using non-linear buckling analyses are corresponded to 5128 shell nodes and 5104 linear quadrilateral elements of type S4R. For the representation of boundary conditions used in this study, let u , v a nd w be (the translations), while x r , y r and z r are (the rotations) the slender (or roughly) x , y and z - axes as shown in Fig. 2. The W