传动间隙对舵面颤振的影响分析

Analysis of the effect on actuator flutter by driving space

针对一类超声速导弹小展弦比舵面的特点，忽略其弯曲方向的模态变化，当舵机／舵面系统旋转方向引入间隙非线性因素时，会使系统产生谐振和耦合颤振问题，因此，首先建立了舵机／舵面系统在模态试验和飞行状态下的单自由度非线性振动模型，通过渐近法求解这一自由度下间隙对系统的影响，以及预载和飞行速度抑制间隙的变化规律，为避免系统发生抖动和结构耦合颤振提供分析依据。

For the characteristic of Supersonic Missile＇s low aspect-ratio of the rudder of, ignoring the mode changes in inflect direction, resonance and coupling flutter will happen when nonlinear factor with clearance is considered in rolling direction of the rudder. The one degree of freedom nonlinear model of the rudder in model experiment and flight regime is designed. In this model, the influence of clearance to the system through gradual methods, and variation characteristics of the lode and flight velocity are both developed. And gists to avoid reso- nance and configuration coupling flutter is offered.