一种飞机操纵面驼峰型颤振随高度变化特性研究

Research on Hump Mode Flutter Characteristic with Altitude Change of Aircraft Control Surface

摘要:

飞机操纵面旋转和安定面弯曲模态频率较近时易耦合形成一种速度阻尼特性随高度显著变化的驼峰型颤振。某飞机垂尾颤振分析表明超过一定高度后驼峰型颤振分支阻尼峰值会超过结构阻尼系数,成为临界颤振型,并且随飞行高度增加阻尼峰值迅速增加。针对上述情况采用了三种方案抑制驼峰型颤振,算例表明降低30%安定面弯曲刚度,增加25% 结构质量,操纵面旋转频率增加60% 以上均能有效抑制高空驼峰型颤振。

Abstract:

A hump mode flutter which is very sensitive to altitude may be induced by coupling of control surface rotation and its stabilizer bending mode. The results of calculation show that hump mode flutter will exceed structure damping ratio and become the critical flutter when the vertical tail flutter for some aircraft is over a certain altitude,and the peak value of damping ratio rises dramatically with altitude increasing. Three methods are adopted to suppression the altitude hump mode flutter, including decreased 30% stabilizer bending stiffness, added 25% of structure mass, and enhanced 60% or more control surface rotation frequency.