大展弦比复合材料机翼气动弹性优化  

AEROELASTIC OPTIMIZATION OF A HIGH-ASPECT-RATIO COMPOSITE WING

作　　者：万志强[1] 杨超[1] 

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100083

出　　处：《复合材料学报》2005年第3期145-149,共5页Acta Materiae Compositae Sinica

基　　金：国家自然科学基金(03A51050);航空基础科学基金(10372013)

摘　　要：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。This paper presents design studies of aeroelastic optimization of a high-aspect-ratio composite wing using a genetic/sensitivity-based hybrid algorithm. The design studies were carried out under the conditions of meeting multiple constraints including strength, displacement, divergence speed and flutter speed. In the course of optimization, the thickness of plies of wing components was considered as design variables, while the minimum of the structural weight as an objective function. The present work has made it clear that the problems with the bending deformation should be given serious consideration in the structural design of high-aspect-ratio composite wings because it has great effects on the final optimized weight. It is also obvious that the wing structures formed on the basis of stress design criteria could hardly fulfill the requirements on the bending deformation. A satisfactory result could be obtained at a reasonable cost of computational work by means of the genetic/sensitivity-based hybrid algorithm in the aeroelastic optimization design of high-aspect-ratio composite wings.

关 键 词：气动弹性 结构优化 大展弦比机翼 复合材料 遗传算法 

分 类 号：V211.47[航空宇航科学与技术—航空宇航推进理论与工程] TB330.1[一般工业技术—材料科学与工程]