尾段主梁刚度变化对T型尾翼颤振特性的影响

由于T型尾翼结构和气动布局的特殊性,其颤振特性的分析比较复杂.T型尾翼安装在机身尾部,这体现在有限元结构模型中即为T型尾翼与尾段主梁相连接.为了研究尾段主梁的刚度变化对T型尾翼颤振特性的影响,以某T型尾翼飞机的尾段为研究对象,根据其原始刚度,分别改变其垂直弯曲刚度和扭转刚度,并计算分析相应刚度下的固有振动特性与颤振特性.最后分别以这两个刚度为变量,另一个刚度的原始值为常量进行分析.结果表明尾段主梁的刚度变化对垂尾弯扭耦合颤振的影响较为显著.

Effect of stiffness variation of tail main beam on flutter characteristics of t tail

Analysis on the flutter characteristics of T tails is complicated because of their special structure and aerodynamic configuration. The T empennage is fixed on the afterbody, and in a structure finite element model, this can be represented by connecting the T tails and the main beam. To study the influences of stiffness variations of tail main beam on flutter characteristics, the empennage of a T tail aircraft is studied according to its original stiffness, considering the change of vertical bending stiffness and torsional stiffness. And the corresponding characteristics of natural vibration and flutter are analyzed. Finally, the flutter characteristics of models with two variable of above stiffness (vertical bending stiffness and torsional stiffness) and one constant of the original value of either stiffness are analyzed. The results demonstrate that the influences of stiffness variations of tail main beam on bending torsion coupled flutter of vertical tail are significant.