Abstract:

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.

Key words: wings, load tests, models, load equation