直升机旋翼桨叶载荷标定新方法研究  

Research New Method of Helicopter Rotor Blade Load Calibration

作　　者：韩玉旺 朱光明 陈功力 

机构地区：[1]中航工业直升机设计研究所,江西景德镇333001

出　　处：《直升机技术》2012年第3期29-33,共5页Helicopter Technique

摘　　要：直升机飞行时桨叶会产生挥舞、摆振和扭转等复杂运动,受到这三种复合载荷的作用,必须辨识、解耦和提取载荷测量信号。为了消除挥舞对摆振的影响,提供一种新的方法以确定桨叶实际预扭角,消除挥舞对摆振的耦合,弥补了以往方法的不足,从而得到了更为真实的载荷数据。When helicopter fly, the blades have the complicated movement such as flapping, lead-lagging and torsion. Due to the three multiple load, we must distinguish, decouple and extract the signal of load measurement. In order to remove the influence on lead-lag from flapping, this paper supplied a new method, by which we could define the pre-twist angle of the blade and avoid the coupling between lead-lagging and flapping. This method perfected the traditional method and has advantages on getting more actual load data.

关 键 词：桨叶 标定 预扭角 挥舞 摆振 解耦 

分 类 号：V21[航空宇航科学与技术—航空宇航推进理论与工程]