Structural-Optimization Strategy for Composite Wing Based on Equivalent Finite Element Model

Abstract

To improve the efficiency of wing structural optimization in the aircraft preliminary design, an equivalent finite element model and a three-step optimization strategy were developed, taking the displacement, stiffness, buckling, and flutter requirements into account. The finite element model of a wing is reduced by the equivalent-strength-and-stiffness method instead of modeling the stiffener. It is beneficial to parameterize the modeling process for the wing primary structure. The composite wing of a regional aircraft is used to verify the equivalent finite element model with the static, buckling, and flutter analyses. The accuracy of this method is demonstrated through the comparison with the detailed finite element model. Then, the three-step optimization strategy was performed for the same case. The results show that the optimization strategy for the composite-wing design is efficient, and the equivalent finite element model in conjunction with the rapid modeling is suitable for the preliminary structural optimization with the static and dynamic constraints.