Abstract:

In full scale fatigue testing for airplane structures, the loads, which are used to simulate the load spectrum of various flying status in airplane service, are imposed on finite loading spots. Whether the loading is accurate or not, the testing loads calculation is needed to guarantee its precision. In this paper, the method of finding extremum for load error is proposed. The method realizes calculation of minimum error control. The load optimum design is completed through rational error distribution by using error synthetical control of weighted precision coefficients. This method is applied to fatigue testing loads calculation for a type of airplane. It is the basis of the successful full scale fatigue testing of the airplane.

Key words: load of fat igue test ing, load erro r, w eigh ted coefficients of loading p recision, op t imal load simultaneous equat ions