As for the characteristics of a folding wing, a parametric aeroelastic model for flutter analysis is proposed in this paper. Parametric structural model is achieved based on modal synthesis method. Parametric aerodynamic model is established using doublet lattice method. And the flutter boundary prediction of an aeroelastic system is e?laborated using Gram matrix norm. The fully extended and completely folded configurations are taken as examples. The results of this method are compared with those of eigenvalue method to verify the correctness. Some analyses of different folding angles are performed. Flutter boundary is very sensitive to the folding angle. With increasing folding angle, the flutter mode changes. Higher modal damping ratio can raise flutter speed and delay flutter phenomenon.%针对折叠机翼的特点建立了颤振分析的参数化气动弹性模型. 参数化的结构模型基于模态综合法实现;参数化的气动力模型采用偶极子网格法建立;并且阐述了基于Gram矩阵范数对于气动弹性系统颤振边界的预测方法. 以折叠机翼完全展开和完全折叠构型为例,将文中方法获得的颤振边界与特征值法获得的结果进行了对比,验证了该方法的正确性. 通过对不同折叠角度下的颤振边界的分析可以得出:颤振边界对折叠角度很敏感;随着折叠角度的增加,颤振模态发生了变化;较高的结构模态阻尼比可以提高颤振速度,推迟颤振现象的发生.
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