飞机机翼结构载荷测量试验力学模型与数据处理

MECHANICAL MODEL AND DATA PROCESSING OF LOAD MEASUREMENT TEST FOR THE AIRPLANE'S WING STRUCTURE

以运七飞机为例,探讨了大型飞机机翼结构部件载荷测量试验力学模型,应变桥路设计和标定加载试验过程,通过对试验数据多元回归分析,建立了飞机机翼、尾翼结构部件载荷输入与应变输出关系方程,以此来获得飞机机翼、尾翼测量截面在实际飞行过程中的载荷-时间历程。

The structure is often directly designed and processed into a sensor measurement system to realize single independent loading measurement when load measurement test is done. The relation equation regarding the strain output of electrical bridge versus the load input is established through indoor calibration test. Thereby the load time history of structural members in the actual service is obtained. But in the real situation, it is difficult or not permitted to design and process a lot of large sized structural members into sensors. The mechanical model of the load measurement test for the large sized structural members of airplane′s wing is investigated where an Yun 7 airplane is taken for example. The relation equation of the load input and strain output for the structural members of the airplane′s wing is created by using multiple linear regression. And, based on this, the load time course for the measurement cross section of the airplane′s wing and tail in the actual flying is obtained.