Abstract
Laminated composite structures are widely used for aerospace components because of their high specific strength and specific stiffness. For laminated composite structures, stacking sequence optimization is indispensable. Although fracture of the laminated composites is usually used as a constraint, it is very important to obtain an accurate approximation of the fracture of the laminated composites for the optimization of surrogate models. Approximating the fracture of laminated composites, however, is quite difficult because the fracture index is very noisy. In the present study, a new surrogate model using the Kriging model for the fracture of laminated composites is proposed and tested for the most severe plate bending problems.
