考虑气动弹性约束的复合材料支撑机翼优化设计

基于遗传-敏度混合算法对复合材料支撑机翼开展考虑气动弹性约束的优化设计，并与常规机翼构型进行比较。在严重载荷状态下，以结构质量最小化为目标，以翼尖变形、屈曲稳定性和颤振速度为约束，设计复合材料机翼铺层和支撑结构参数，并研究不同支撑点位置对于优化设计结果的影响。结果表明，复合材料支撑机翼构型能大幅减少弯曲方向上的铺层材料，有明显的减重优势。支撑点位置对于结构质量、屈曲稳定性和扭转刚度分布有较大影响，支撑结构的屈曲破坏在复合材料支撑机翼的结构设计中要引起重视。

Optimization design of composite strut-braced wings with aeroelastic constraint

The optimization design of composite strut-braced wings with aeroelastic constraint was conducted by using the genetic-gradient hybrid algorithm, and a comparison between the strut-braced wing configuration and conventional configuration was also presented. The objective was to minimize the structural mass subject to the constraints of deformation at wingtip, buckling and flutter speed. The composite layups and structural parameters of strut were designed in the case of critical load conditions. The influences of strut locations on optimal designs were investigated. The results indicate that the material in the bending direction can be dramatically reduced by using the composite strut-braced wing, which has an obvious advantage in reducing structural mass. The structural mass, buckling and distribution of torsion stiffness can be significantly affected by the strut location. The buckling failure of strut should be taken into account in the structural design of composite strut-braced wing.