Nonlinear Bending of Composite Singly Curved Stiffened Shells Under Temperature Stresses

The laminated composite shell panels have different applications in civil, marine, and aerospace structures where the temperature stresses play a key role in overall performance. Such structural applications are vulnerable under residual stresses. The literature confirms that there is a dearth of research studies on relative performances of stiffened cylindrical panels made of laminated composite applied under varying temperatures. This paper works on that area. A C0 isoparametric FE code with von-Karman nonlinear strains and constant transverse shear is adopted. The reduced integration technique evaluates the element matrices, and the global ones are achieved by combining the element matrices considering the shell geometry. The correctness of the proposed approach is confirmed through solutions of benchmark problems. The deflections are studied for different laminations, stiffener numbers and orientations.