旋翼气动提前操纵角研究  

The Study of Rotor Aero-preoperation Angle

作　　者：彭勇[1] 朱国民[1] 

机构地区：[1]中国直升机设计研究所,景德镇333001

出　　处：《直升机技术》2008年第3期98-102,共5页Helicopter Technique

摘　　要：为了保证某型直升机操纵系统设计的顺利进行,本文基于国内外相关资料对气动提前操纵角进行了深入的研究,得出该角度主要取决于桨叶挥舞基阶固有频率ωβ1。而ωβ1与挥舞铰外伸量e、桨叶根部弹性约束Kβ和挥舞调节系数KP密切相关。通过分析e,Kβ和KP对气动提前操纵角△ψ的影响,推导出计算该角度的具体公式。采用该公式对几个型号进行计算,经校核与验证后,表明本文提供的计算方法可行,能满足工程精度,可应用于工程研究,从而为布置助力器提供理论依据。In order to keep the design of a certain helicopter control system successfully,it's necessary to study the phase lag in detail.This paper presented that the phase angle △ψ is dominated by the natural frequency of blade fundamental flap mode ωβ1.The ωβ1 is related to flap hinge offset e,flap hinge spring Kβ and pitch-flap coupling KP.After analyzing the influence of e,Kβ,KP to △ψ,an accurate method of calculation of △ψ was given.The verification and validation of △ψ was accomplished by calculating the △ψ of several helicopters in CHRDI,which concluded that the method of calculation of △ψ is reasonable and can be used to engineering research.Meanwhile this method provided the theoretical basis of locating position of MRA.

关 键 词：直升机 气动提前操纵角 助力器安装位置 

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]