基于流固耦合方法的大展弦比机翼非线性颤振特性分析  

Studying Nonlinear Flutter of High-Aspect-Ratio Wing Based on Fluid Solid Coupling

作　　者：马艳峰[1,2] 贺尔铭[1] 曾宪昂[2] 李俊杰[2] 唐长红[2] 

机构地区：[1]西北工业大学航空学院,陕西西安710072 [2]中航工业第一飞机设计研究院,陕西西安710089

出　　处：《西北工业大学学报》2014年第4期536-541,共6页Journal of Northwestern Polytechnical University

基　　金：国家科技部国际合作专项(2013DFA80710)资助

摘　　要：针对大展弦比机翼的柔性大、变形大的特点,基于非定常涡格法求解机翼的非定常气动力,考虑了大展弦比机翼的几何非线性效应,提出了计算大展弦比机翼非线性颤振分析的新方法。以某平板机翼为例:计算了机翼静气动弹性变形、振动特性和颤振特性随着攻角增大的变化规律;比较了颤振结果线性解与非线性解的差别。相关的分析结果表明:大展弦比机翼颤振分析需同时考虑几何非线性效应和气动网格变形。Large deformation and flexibility are significant for high-aspect-ratio wings. In this paper, unsteady vor-tex-lattice method is used to solve for the unsteady aerodynamic force. It considered the effect of structural geometric nonlinearity on the high-aspect-ratio wing in the structure calculation. It presents a new method for calculating the nonlinear flutter analysis of high-aspect-ratio wing. As the angle of attack increases, the characteristics of static aeroelasticity, vibration and flutter are calculated around a flat board wing. Additionally, we compare numerically the linear solution with the nonlinear one. The results and their analysis prove preliminarily that high-aspect-ratio wing flutter must consider both geometrically nonlinear and grid deformation.

关 键 词：非线性颤振 静气动弹性 攻角 大展弦比机翼 

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]