北京航空航天大学学报 ›› 2016, Vol. 42 ›› Issue (7): 1368-1376.doi: 10.13700/j.bh.1001-5965.2015.0448

• 论文 • 上一篇    下一篇

电动伺服舵系统动力学建模及颤振分析

张仁嘉, 吴志刚, 杨超   

  1. 北京航空航天大学航空科学与工程学院, 北京 100083
  • 收稿日期:2015-07-03 出版日期:2016-07-20 发布日期:2016-07-29
  • 通讯作者: 吴志刚,Tel.: 010-82317510 E-mail: wuzhigang@buaa.edu.cn E-mail:wuzhigang@buaa.edu.cn
  • 作者简介:张仁嘉 男,博士研究生。主要研究方向:气动伺服弹性力学。Tel.: 010-82313376 E-mail: zhrj559@163.com;吴志刚 男,博士,副教授。主要研究方向:气动伺服弹性力学。Tel.: 010-82317510 E-mail: wuzhigang@buaa.edu.cn
  • 基金资助:
    国家自然科学基金(11372023)

Dynamic modeling and flutter analysis of a fin-actuator system

ZHANG Renjia, WU Zhigang, YANG Chao   

  1. School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100083, China
  • Received:2015-07-03 Online:2016-07-20 Published:2016-07-29

摘要: 舵机动力学对舵系统颤振有最直接影响,其动力学模型的准确建立是颤振分析的关键。以某电动伺服舵系统为对象,分别建立了电机、减速器及控制回路模型。基于其地面振动试验(GVT)数据特征,考虑了减速器中零部件间隙及滚珠丝杠间接触刚度2类非线性因素。动力学仿真结果复现了试验现象,证明了接触刚度和间隙对该伺服舵系统动力学特征的主导作用。在颤振分析中,对比了接触刚度和常数刚度2种假设下,舵机在不同阶跃角指令下的舵偏角响应。发现常数刚度下舵系统仅存在极限环(LCO)和失稳2个域,临界速度不会随间隙大小而变化;而接触刚度下存在稳定、LCO和失稳3个域,且相同风速下,其临界指令角较常数刚度假设更高,但其临界速度却会随间隙增大而减小,甚至小于常数刚度假设,应引起足够重视。

关键词: 气动弹性, 颤振, 非线性, 接触刚度, 间隙, 舵机

Abstract: Dynamics of an actuator has a direct impact on the flutter characteristics of a fin structure. Thus it is important to build the dynamic model of the fin-actuator system precisely before a flutter analysis. A typical fin-actuator system is investigated by constructing its motor model, reducer model and controller model, respectively. Based on the characteristics of the ground vibration test (GVT) data, two nonlinear factors are considered including the contact stiffness between the screw and the balls, as well as the freeplay. Simulation results reproduce what were seen in the test. It is found that the contact stiffness and freeplay dominate the dynamic characteristics of the fin-actuator system. In the flutter analysis, the angular responses of the actuator stimulated by different angular step commands under both contact stiffness assumption and constant stiffness assumption are compared. The results show that a limit cycle ossllation (LCO) domain and an unstable domain exist under the constant stiffness. Its critical velocities do not vary with the freeplays. However, besides the LCO and unstable domains, a stable domain appears under the contact stiffness. At a specific flow velocity, its critical command angle is higher than the one under constant stiffness. But its critical velocity decreases as the freeplay increases, and even reaches a lower level than the critical velocity under constant stiffness. Enough attention should be paid to this issue.

Key words: aeroelasticity, flutter, nonlinear, contact stiffness, freeplay, actuator

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