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使用遗传/敏度混合优化算法对大展弦比复合材料机翼进行气动弹性优化设计研究。在满足强度、位移、发散速度和颤振速度等约束条件的前提下,以机翼各部件复合材料铺层的厚度为设计变量,对结构进行重量最小化设计。研究表明:弯曲变形严重影响最终的优化重量,是设计大展弦比复合材料机翼结构时应该重点考虑的问题;按照应力设计准则对这类结构进行设计,往往很难满足弯曲变形的要求;使用遗传/敏度混合优化算法对大展弦比复合材料机翼进行气动弹性优化设计能够在可以接受的计算耗费下获得满意的结果。
Aeroelastic optimization design of large aspect ratio composite wing using genetic / sensitivity hybrid optimization algorithm. On the premise of satisfying the constraints of intensity, displacement, divergence velocity and flutter velocity, the thickness of the composite material ply of each wing component is taken as the design variable, and the weight of the structure is minimized. The results show that the bending deformation seriously affects the final optimized weight, which is the key issue to be considered in the design of large aspect ratio composite wing structure. According to the stress design criteria, it is often difficult to meet the requirements of bending deformation. Optimizing the aeroelasticity of a large aspect ratio composite wing using a genetic / sensitivity hybrid optimization algorithm yielded satisfactory results with acceptable computational cost.