Minimum Weight Design of a Composite Wing Structure Using a Global/Local Design Methodology

The application of a global/local design methodology to a composite wing structure is described. A global finite element model of the wing is used to compute the overall response of the structure and to design the inplane properties of each skin and rib panel. The global level design variables include the total thicknesses of the 0°, ±45°, and 90° plies in each skin and rib panel, which are allowed to vary continuously. At the local level, a genetic algorithm designs the stacking sequences of each skin and rib panel for maximum buckling load given the number of plies of each orientation and a set of inplane loads. The global and local design levels are coordinated with one another using a set of response surface models