飞控系统极限环抑制对舵机性能的需求计算  

Requirements to Actuator Performance for Limit Cycle Suppression in Flight Control System

作　　者：张西涛[1] 江飞鸿[2] 赵海[2] 

机构地区：[1]西北工业大学航空学院,陕西西安710072 [2]中航第一飞机设计研究院飞行控制系统研究室,陕西西安710089

出　　处：《飞行力学》2009年第4期39-42,共4页Flight Dynamics

摘　　要：舵机是电传飞控系统中非线性因素的重要组成部分,若参数选择不当,常会发生稳态不衰减的小幅值极限环振荡现象。应用非线性控制理论,将飞控系统稳定性要求转化为对舵机的幅频特性、相频特性和不灵敏区范围要求,从而通过舵机设计达到抑制极限环的目的。仿真结果表明,该方法简单、实用,具有较高的工程应用价值。Actuator is one of the main nonlinearities in a FBW flight control system. Once its parameters are not properly selected, a small steady unattenuating limit cycle oscillation will be seen. Application of nonlinear control theory can translate this stability problem of the flight control system into the requirements to frequency response characteristics of the actuator and to the range of insensitive zone of it. In this way, the limit cycle can be suppressed by defining the performances of the actuator. The simulation results show that this method is simple in use, wide in applicability, so it is of high engineering utility.

关 键 词：极限环 飞行控制系统 非线性 舵机性能 

分 类 号：V249.1[航空宇航科学与技术—飞行器设计]