Aerodynamic/structural integrated design for aircraft wing with static aeroelasticity effect

For the problem of aerodynamic/structural integrated design about a transonic aircraft, an aerodynamic/structural integrated design method is developed in consideration of the influence of static aeroelasticity. The numerical evaluation method in the integrated design is established on the basis of full potential equations and boundary layer correction. A loose coupled method based on three dimension radial basis functions (RBF) interpolation is adopted to analyze the static aeroelasticity. An improved differential evolution algorithm is chosen as the optimization algorithm for the design. The comparisons between the numerical results and the experiment data for benchmark models CRM and DLR-F6 show that the numerical technology and the loose coupled static aeroelasticity analysis method are reliable. By respectively choosing twist angle distributions and airfoil sections as the design parameter, together with the static aeroelasticity effect taken into account, the optimization method established is used in aerodynamic/structural integrated design for a transonic aircraft. Due to these two optimizations, the flying ranges are increased by 5.63% and 3.05%, respectively. The improvement in range owes to the distribution changes in the wing load and the structural thickness. In the twist distribution design case, 6.53% improvement in lift-drag ratio is obtained at the expense of 3.2% increase in the structural weight. However, in the airfoil sections design case, the lift-drag ratio is increased by 1.53%, and the structural weight is decreased by 3.56%. The design results' is increased by 1.53%, and the structural weight is decreased by 3.56%. The design results show that the integrated optimization design method constructed in this paper is reasonable and practical.