直升机主轴弯矩标识的幅-相综合相关识别方法

直升机主轴弯矩是新研直升机飞行试验中必须测量、分析与验证的重要技术参数，是主轴设计的结构与强度验证、优化的依据，主轴弯矩测试是飞行试验实时监测、安全保障的重要环节。基于直升机飞行试验主轴弯矩实测方案和大子样结果数据，在理论建模和分析的基础上，提出了幅-相综合相关系数这一新概念，形成直升机主轴弯矩测量标识真伪的谐波幅-相综合相关识别方法，可以简单、量化、精确完成主轴弯矩测量标识真伪的勘别，保障主轴弯矩测量数据处理与分析结果的有效性和准确性，并利用某型直升机试验平台实测数据完成方法验证。该方法为保障新机研制飞行安全和减少技术隐患与风险，提供了一种新思路和新工具，可以推广应用于类似机械旋转轴平行截面正交方向弯矩、直升机桨叶展向不同截面摆振与挥舞弯矩测量通道标识真伪的智能识别。

Distinguish Method of Amplitude-Phase Correlation for Identification of Helicopter Spindle Bending Moment

Helicopter spindle bending moment is an important technical paramenter that must be measured,analyzed and verified in the flight test of the newly developed helicopter.The result of bending moment is the basis of the structure and strength verification and optimization of the spindle design,and also is an important link of real-time monitoring and safety guarantee in flight test.Based on the measured scheme of main shaft bending moment of helicopter flight test and the data of large sub sample results,on the basis of theoretical modeling and analysis,the new concept of amplitude-phase comprehensive correlation coefficient is proposed to form a harmonic amplitude-phase comprehensive correlation identification method for the authenticity of helicopter spindle bending moment measurement identification,which can simply,quantitatively and accurately complete the identification of the authenticity of spindle bending moment measurement identification,and can ensure the validity and accuracy of spindle bending moment measurement data processing and analysis results,and use the measured data of a helicopter test platform to complete the method verification.This method provides a new idea and new tool for ensuring the flight safety of new aircraft development and reducing technical hidden dangers and risks.It can be popularized and applied to the intelligent identification of the authenticity of the measurement channel for measuring the bending moment in the orthogonal direction of the parallel section of the mechancial rotation axis and the shimmy and flap-wise bending moment of the helicopter blade at different cross-sections.