Structural optimization of stiffened composite panels for highly flexible aircraft wings

Within this paper, the structural optimization of stiffened composite panels is considered. The application example is a wing of a long–range aircraft, whereby the flexibility has to be increased due to flight physical demands. To develop the new structural design concept, numerical optimization is used. The structural analysis is carried out utilizing detailed finite element models (DFEM) with linear static and linear eigenvalue simulations. Using this DFEM– and gradient–based optimization environment, designs are analyzed and optimized regarding their mass, considering damage tolerance and stability requirements. The advantages of the chosen simulation and optimization approach are presented. The new design concept is used to improve the aircraft wing and the differences to the state of the art wing design are depicted