考虑几何非线性的复合材料机翼气动弹性分析

本文研究结构几何非线性与气动力非平面效应对大展弦比复合材料机翼的气动弹性行为的影响．将非线性有限元法与曲面涡格法结合，计算机翼静气动弹性变形；通过曲面偶极子格网法结合静气动弹性平衡位置处的结构切线刚度，建立气动弹性方程并求解得到机翼颤振速度．针对板模型机翼，分析了迎角对机翼几何非线性气动弹性特性的影响．结果表明：本文复合材料板模型机翼的颤振形式不受水平弯曲模态影响，属于经典弯扭颤振；在几何非线性的影响下，机翼扭转频率随结构变形增大而明显减小，颤振速度随迎角增大而减小．

Aeroelastic Analysis of Composite Wings Considering Geometric Nonlinearity

The aeroelastic behavior of high-aspect ratio composite wings is studied considering the structural geometrical nonlinearities and the aerodynamic nonplanar effects. The static aeroelastic deformation of wing is calculated by nonlinear finite element method combined with curved vortex lattice method. The flutter velocity is obtained by solving the aeroelastic equation coupling the curved doublet lattice method and the tangential stiffness of the structure at the static aeroelastic equilibrium position. The influence of the attack angle on the geometrical nonlinear aeroelastic characteristics of the plate wing was calculated and analyzed. The results show that the flutter form of the composite plate wing is not affected by the horizontal bending frequency and is the classic bending-torsional coupled flutter. Due to the geometrical nonlinearity, the torsion frequency of the wing decreases with the increase of the structural deformation, and the flutter velocity decreases with the increase of the attack angle.