一种改进后的尾桨叶安装角测量方法  

作　　者：耿丽松 杨茜茜 焦帅克 王泽峰[1] 

机构地区：[1]中国飞行试验研究院飞机所,陕西西安710089 [2]中国飞行试验研究院测试所,陕西西安710089

出　　处：《科技创新与应用》2022年第10期118-123,共6页Technology Innovation and Application

摘　　要：安装角测量是尾桨叶载荷校准之前必须完成的工作。首先采用传统的工程方法进行安装角测量,数据显示其结果重复性较差。针对该问题,系统分析静态加载情况下,挥舞电桥输出的影响因素,得到重力力矩项是造成该差异的主要原因;提出对已有试验数据的修正办法和一种改进后的安装角测量方法,并验证新方法的正确性。该技术可应用于后续直升机型号主尾桨叶同类试验中。The measurement of installation angle is a task that must be completed before the load calibration of tail blades.First of all,the traditional engineering method is used to measure the installation angle,and the data show that the repeatability of the result is poor.In view of this problem,the influencing factors of wielding bridge output under static loading are analyzed system atically.It is obtained that the gravity moment term is the main reason for the difference.A correction method for the existing test data and an improved installation angle measurement method are proposed,and the correctness of the new method is verified.This technique can be applied to the similar tests of the main tail blades of subsequent helicopter models.

关 键 词：直升机 尾桨叶 载荷校准 安装角 重力影响 

分 类 号：V216[航空宇航科学与技术—航空宇航推进理论与工程]