大展弦比复合材料机翼气动剪裁设计新方法  

New Method for Aeroelastic Tailoring of High Aspect Ratio Composite Wings

作　　者：任智毅[1] 金海波[1] 丁运亮[1] 

机构地区：[1]南京航空航天大学航空宇航学院,南京210016

出　　处：《南京航空航天大学学报》2011年第1期18-24,共7页Journal of Nanjing University of Aeronautics & Astronautics

摘　　要：根据机翼气动载荷和机翼弹性变形之间存在的关系,以机翼的总升力不变和结构强度作为约束条件,提出一种新的气动/结构耦合的刚度设计方法。该方法首先通过数值实验设计研究机翼扭转变形和弯曲变形对机翼气动载荷的影响,并用主成分回归方法构建了机翼变形和气动载荷之间的响应面模型。然后以该模型为基础,构建气动/结构一体化设计模型,此模型仅考虑强度约束和总升力不变的要求,放弃了传统优化设计模型中的挠度和扭转约束。通过2种优化模型的对比,说明应用该方法设计出的机翼结构,重量减轻1.23%,机翼总体扭转变形减小33%,刚度设计更为合理。According to the relationship between aerodynamic loads and elastic deformation of wings,a new method is proposed for stiffness design considering aerodynamic and structural coupling.It takes the strength and the constant total lift as constraint conditions.This paper firstly studies the influence of wing bending and twist deformation on aerodynamic loads through numerical experiments,and a response surface model of aerodynamic loads and wing deformation is established by using principle component regression. Then,based on the response surface model,an integrated aerodynamic and structural design is made.Disregarding bending and twist deformation in the optimum wing structure,the method only considers the strength and the constant total lift constraint.Compared with two kinds of optimum models,the result shows that the method reduces 1.23% of the weight and 33% of global twist deformation of wings,thus the stiffness design is more reasonable.

关 键 词：气动弹性 结构优化 复合材料结构 响应面模型 主成分分析 

分 类 号：V214.8[航空宇航科学与技术—航空宇航推进理论与工程] V215.3