基于某振动场景的直升机飞控系统陷波器设计  

The Notch Filter Design based on Certain Vibration Scenario forHelicopter Flight Control System

作　　者：付益恺 孟文杰[1] 何野[1] FU Yikai;MENG Wenjie;HE Ye(China Helicopter Research and Development Institute,Jingdezhen 333001,China)

机构地区：[1]中国直升机设计研究所,江西景德镇333001

出　　处：《直升机技术》2022年第2期23-27,共5页Helicopter Technique

摘　　要：直升机的振动是由于旋翼本身的特性而与直升机长期共存的固有问题。通常来说,直升机的振动可以分为周期激励和随机激励,而随机激励常会随反馈信号进入飞控系统的反馈控制回路,存在加剧全机异常振动的风险,给飞控系统的设计带来了困难。针对上述问题,利用实际试飞数据,结合一种基于无限冲击响应(IIR)滤波器的滤波算法,对异常输入激励的抑制效果进行了仿真。随后,针对直升机飞行状态(挂载、重量、重心)不同造成的频率点偏差问题,设计了一种高带宽多频率点的陷波带阻滤波器,给出了理论分析,并通过试飞数据的仿真验证了滤波效果。Helicopter vibration is an inherent problem which coexists with the helicopter for a long time due to the characteristics of the rotor itself.Generally speaking,helicopter vibration can be divided into periodic excitation and random excitation,and random excitation often enters the feedback control loop of the flight control system with the feedback signal,which has the risk of flight control system.To solve these problems,this paper simulated the suppression effect of impact response(IIR)filter.Then,aiming at the problem of frequency point deviation caused by multi-frequency notch band stop filter was designed,theoretical analysis was given,and the filtering effect was verified by flight data simulation.

关 键 词：飞行控制系统 陷波滤波器 振动抑制 

分 类 号：V249.122[航空宇航科学与技术—飞行器设计] V214.33