电传直升机人机耦合振荡特性研究  

Research on fly-by-wire rotorcraft-pilot coupling characteristics

作　　者：张宏林[1] ZHANG Honglin(Aircraft Flight Test Technology Institute,CFTE,Xi’an 710089,China)

机构地区：[1]中国飞行试验研究院飞机所,陕西西安710089

出　　处：《飞行力学》2021年第1期35-39,共5页Flight Dynamics

摘　　要：为了分析研究电传直升机的人机耦合振荡特性,将直升机操纵/响应模型与驾驶员诱发振荡(Pilot Induce Oscillation,PIO)判定准则模型相结合,建立了一种适用于电传直升机的PIO预测方法。首先对建立的方法进行了飞行试验验证,然后应用该方法着重开展了PIO参数敏感性分析研究,得到了对降低PIO趋势有指导意义的结果。To analyze the fly-by-wire rotorcraft-pilot coupling characteristics, a method applicable for predicting fly-by-wire helicopter PIO was established by combining the handling-response model with PIO assessment criterion model. Firstly, the method was verified based on the flight test data. Then, the PIO parameter sensitivity was analyzed and studied, and the results which were significant for reducing PIO tendency were obtained.

关 键 词：直升机人机耦合 操纵/响应模型 判定准则 PIO趋势 飞行试验 

分 类 号：V212.4[航空宇航科学与技术—航空宇航推进理论与工程]