Structural optimization of composite wing using equivalent finite element model

In the process of wing design, equivalent finite element model (EFEM) method was utilized for the optimization of wing structure with static and dynamic constraints. An structure optimization strategy with three steps, which convert a multivariable complex optimization problem to a series of simple optimization problems with a few design variables, was proposed for a composite wing of regional civil jet design. Firstly, the ratio of composite layers was optimized with displacement, static strength and flutter speed as constraints. Then each stiffened panel between ribs was optimized for minimizing structure weight and structure efficiency with the static strength and structure stability as constraints. Finally, the overall stiffness of the wing structure was optimized with displacement and flutter speed as constraints. The results show that the EFEM method is suitable for wing structure preliminary optimization for the advantage of rapid modeling and low computational cost. And the strategy with three steps in the structural optimization has higher efficiency.