大展弦比夹芯翼大攻角颤振分析

首先导出大展弦比复合材料梁弯扭耦合模态的半解析解，对具有NACA0012翼型的大展弦比的夹芯翼，在模态空间内建立了运动方程。然后采用半经验的ONERA非线性气动力模型描述空气动力，形成了对大展弦比夹芯翼大攻角气动弹性问题的描述。通过结构求解器和空气动力求解器联合求解来完成非线性颧振边界的计算。为了验证非线性颤振边界的求解方法，还利用ONERA气动力模型中的线性部分建立了夹芯翼的线性颤振方程。结果表明：零翼根攻角时，线性颤振速度与用非线性颧振边界求解方法得到的颧振速度完全一致；颤振速度随翼根攻角的增加而迅速减小；复合层铺设方式对颤振速度有较大影响。

Flutter Analysis of a High-Aspect-Ratio Sandwich Wing under Large Angle of Attack

The semi-analytical expressions are established first for the coupled modes of bending and torsion of a high-aspect-ratio composite beam , and then the dynamic equations of a high-aspect-ratio sandwich wing with NACA0012 airfoil shape are derived in modal space. A semi-empirical and nonlinear aerodynamic model ONERA is employed to model aerodynamics that the nonlinear aeroelastic problem of a sandwich wing is well defined. The nonlinear flutter boundary of the sandwich wing is obtained by jointly running structural solver and aerodynamic solver. In order to validate the presented method, the linear flutter equations of the sandwich wing are established using the linear part of the ONERA model. The numerical results show that the linear flutter speed agrees well with those predicted by the method of the nonlinear analysis. The flutter speed decreases rapidly with an increase of the root angle of attack, and the flutter speed of the sandwich wing is significantly influenced by laminate ply angles.