摘要
研究了超声速来流中含间隙舵系统的颤振问题。通过建立舵机传动机构的动力学方程并采用翼段模型和活塞理论,导出了俯仰方向含有间隙的舵面的非线性气动弹性动力学方程,利用Hopf分叉理论计算了舵面的颤振速度,并采用描述函数法分析了含间隙舵面的气动弹性响应。在此基础上,研究了传动机构的动态特性和间隙对舵面的颤振速度和极限环振荡行为的影响。研究表明:舵机静刚度较低时,需要考虑其动刚度对颤振速度的影响;仅当间隙内的俯仰刚度较小时,舵面的气弹响应才会发生亚临界Hopf分叉;在飞行速度一定的情况下,间隙量增大1倍,极限环振荡的振幅近似增加1倍。
The flutter characteristics of a fin of missiles system with freeplay nonlinearity in a supersonic flow were analyzed. Firstly, by adopting the typical section model and the piston theory and considering the dynamic properties of the transform mechanism of the fin system, the nonlinear aeroelastic dynamic equation of the fin with freeplay nonlinearity in the pitch degree of freedom was constructed. Then, the Hopf bifurcation theory and the describing function method were utilized to obtain the flutter velocity and the limit cycle oscillation response of the fin. The effects of the freeplay and dynamic properties of the transform mechanism on the flutter velocity and limit cycle oscillation （LCO） were investigated in ~detail. It is found that when the static stiffness of the transform mechanism is comparatively small, it is necessary to consider the effect of its dynamic stiffness on the flutter speed; only when the pitch stiffness within the freeplay is small, will the subcritical Hopf bifurcation phenomena happen and be at a fixed speed, and if the magnitude of freeplay doubles, the amplitude of LCO also approximately doubles.
出处
《兵器装备工程学报》
CAS
2016年第1期136-141,160,共7页
Journal of Ordnance Equipment Engineering
关键词
间隙非线性
动刚度
颤振
极限环振荡
HOPF分叉
描述函数法
freeplay nonlinearity
dynamic stiffness
flutter
limit cycle oscillation （LCO）
Hopf bifurcation
describing function method
作者简介
张恩阳（1987-），男，硕士，主要从事飞行器结构、机构研究。
