基于流固耦合方法的大展弦比机翼非线性颤振特性分析

摘要

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.%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。