Composite Laminate Wing Box Optimization Using Genetic Algorithm

Aircraft wing is made up of multi panel composite laminate structure. Each panel consists of different combination composite layer. The main objective this paper is to optimize a 14 panel composite wing structure subjected to bending load. The optimization variables are number of layer, laminate thickness, laminate angle, laminate material and sequence. It increases the complexity of the optimization problem. In order to get global solution genetic algorithm has been implemented. The optimization code was developed in ANSYS APDL code.