直升机桨叶摆振量的全场景视觉测量及分析

直升机旋翼桨叶在高速旋转时，进行全场景桨叶摆振测量和分析，对直升机桨叶载荷设计和旋翼结构设计具有重要意义。本文设计了桨叶摆振量立体视觉测量系统，并进行摆振模式拟合分析。首先，对课题组已有立体视觉测量系统进行改进，并在风洞试验中完成不同总距及周期变距下的旋转桨叶标记点三维坐标测量；其次，解算桨毂坐标系下的桨叶摆振量；最后，采用一阶多项式对桨叶在特定时刻下的摆振模式进行拟合分析，采用复合正弦函数对桨叶旋转过程中的摆振规律进行拟合分析。风洞测量实验结果表明，在4.6 m×4.6 m场景中测量的摆振量均方根误差小于1 mm;桨叶摆振模式和规律模型拟合度好，其均方根误差小于1 mm,为直升机桨叶设计提供了数据支撑。

Full-scene measurement and analysis of helicopter blade lead-lags based on vision

When a helicopter rotor blade rotates at high speed, the measurement and analysis of blade lead-lag motion in the full field are of great significance for the load design of helicopter blades and rotor structure design. In this article, a stereo vision measurement system for blade lead-lag motion is designed, and the lead-lag motion mode fitting analysis is carried out. First, the existing stereo vision measurement system of the subject group is improved, and the 3D coordinates of the rotating blade marker points at different collective pitch and cyclic pitch are measured in wind tunnel tests. Secondly, the blade lead-lag motion in the hub coordinate system is calculated. Finally, the first order polynomial is used to fit the blade lead-lag motion pattern at a specific moment, and the compound sine function is used to fit the blade lead-lag motion law during rotation. Experimental results of wind tunnel measurements show that the root mean square error of the measured lead-lag motion in the 4. 6 m×4. 6 m scenario is less than 1 mm. Blade lead-lag motion modes and law models fit well, with root mean square error less than 1 mm, providing data support for helicopter blade design.