气动伺服弹性系统结构陷幅滤波器优化设计  

OPTIMAL DESIGN FOR NOTCH FILTER OF AEROSERVOELASTIC SYSTEMS

作　　者：蒲利东 罗务揆 严泽洲 PU Li-dong;LUO Wu-kui;YAN Ze-zhou(Aeroelastic Department,The First Aircraft Institute of AVIC,Xi’an,Shanxi 710089,China)

机构地区：[1]中航工业第一飞机设计研究院气动弹性研究室,陕西西安710089

出　　处：《工程力学》2018年第4期235-241,共7页Engineering Mechanics

基　　金：国家科技部国际科技合作项目(2013DFA80710)

摘　　要：为解决飞机气动伺服弹性耦合频率低且随飞机重量构型变化大,使用结构陷幅滤波器改善飞机气动伺服弹性稳定性易于影响飞机操稳特性的问题,建立了一种基于多目标遗传算法的结构陷幅滤波器优化设计方法。以气动伺服弹性系统的弹性模态频响峰值最小作为优化目标,刚体模态频响特性作为设计约束,通过设计罚函数修正个体适应度对陷幅滤波器的频率与阻尼参数进行优化。结果表明:该文方法能够兼顾飞机的气动伺服弹性与刚体运动特性,有利于充分利用高增益控制系统提升飞行性能。The interaction between an aeroelastic system and a flight control system(FCS),namely aeroservoelasticity,may result in aircraft instability,and the corresponding frequencies are lower and vary with aircraft weight configurations significantly.The traditional approach,adopting notch filter for suppressing aeroservoelastic interaction,may have adverse effects on the aircraft controllability and stability.A notch filter optimal design methodology,based on a multi-objective genetic algorithm,is developed with the function of minimizing adverse effects on the rigid fight dynamics.The objective is to minimize the elastic modal frequency response peaks of aeroservoelastic systems subjected to the constraints of the frequency response characteristics of rigid aircraft flight dynamics.Firstly,a penalty function is developed to correct individual fitness functions,and then the frequency and damping parameters of notch filters are optimized.The optimized results indicate that the aeroservoelastic dynamic responses are suppressed while rigid aircraft flight dynamics performance degradation is minimized.Thusly,the proposed method can make full use of high-gain control systems to improve flight performance.

关 键 词：气动伺服弹性 陷幅滤波器 优化设计 遗传算法 操稳特性 

分 类 号：V215.3[航空宇航科学与技术—航空宇航推进理论与工程]