Aircraft Vertical Tail Fatigue Loading To Determine The Research

The relationship between the load measured by strainmethod and the load calculated according to flightparameters and the wind tunnel test data has beeninvestigated in this thesis .The result showed that thecalculation load based on the flight parameters and windtunnel test data is acceptable in subsonic speed and getsgood agreement, with the load measured by strain method.In the paper, through the calibration test of ground load,the relationship between outputs of electrical resistanceof strain gauges and the external load applied on thestructure has been gotten ,and then the load history candirectly be deduced from the measured strain history. Sothe fatigue load can be compiled. In present paper ,thedesign method of the parameter test measurement systemand the error analysis principle are also investigated .Theresult showed that the measurement system accords withthe design demand, and the test data are reliable.Meanwhile, the soft of measured load calculation basedon strain method and the soft of theory calculating loadon vertical tail are programmed by FORTRAN language.