考虑多巡航工况的大型飞机气动弹性优化

Aiming at the problem of poor performance at off-design points in the current common single-point optimization design method of large aircraft wings considering multiple cruise conditions, a synthetical aeroelastic optimization framework with multiple cruise conditions is proposed, and the multi-point aeroelastic optimization of a large aircraft composite wing is studied. The laminate thickness of skin, web, flange and other composite components of the jig shape is optimized to minimize the wing structure weight using genetic algorithm, subjected to the constraints of aeroelasticity, stress/strain, strength and other conditions, and the jig shape design is carried out according to the optimization results. The lift-to-drag characteristics of the optimization results are analyzed and verified by the high-precision CFD/CSD coupling method. The results show that the multi-point aeroelastic optimization can effectively reduce the structure weight and maintain the aerodynamic performance of the pre-designed cruise configuration, thus reducing the overall fuel consumption. Furthermore, the results of multi-point optimization and single-point optimization are compared and the relationship between the considered cruise conditions number and the optimization results is analyzed. The results show that the performance of the multi-point aeroelastic optimization is better than that of the single-point aeroelastic optimization, and the overall performance increases with the increase of the number of cruise conditions considered in the optimization.