气动伺服弹性系统的自适应陷波器算法设计

Adaptive Notch Filter Design Approach for Aeroservoelastic System

随着空空导弹长细比的增加,导弹的弹性特性逐渐凸显,随之带来的气动伺服弹性问题也越来越受到研究人员的关注。有研究表明串联在反馈通道上的陷波器能够有效解决机械系统弹性振动带来的伺服问题,但传统的固定极点式陷波器无法解决导弹飞行过程中振动频率变化的问题。因此,本文提出一种新的自适应陷波器的设计方法,通过反馈测量信号对弹性振动频率进行实时估计更新,从而改变陷波器的陷波频率。仿真结果表明,提出的自适应陷波器设计方法能够有效滤除空空导弹过载跟踪控制时产生的振动信号,避免了气动伺服弹性问题的发生,实现纵向加速度的稳定快速跟踪。

With the increase of the slenderness ratio,the elastic characteristics of the air-to-air missiles have become more and more prominent,and the resulting aeroservoelastic problems have also attracted lots of attention from researchers.Studies have shown that the notch filter in the feedback loop can effectively tackle the elastic vibration problems of mechanical systems.However,the notch filter with fixed notch frequency cannot eliminate effects of elastic vibration in missile closed-loop system because of the varying vibration frequency during the missile's flight.This paper proposes an adaptive notch filter design approach for asroservoelastic system.This method estimates the elastic vibration frequency of missiles utilizing the measured signal and updates the notch frequency by this real-time estimated frequency.The simulation results show that the proposed method can effectively filter out the elastic vibration signal which varies with time and avoid the occurrence of aeroservoelastic problem.Moreover,the closedloop system with the adaptive notch filter is stable and the longitudinal acceleration command is quickly and accurately tracked.