Aircraft Structural Acoustic Fatigue Life Prediction And Analysis Platform To Build

Being deficient in sonic fatigue testing and owing to the limitations of nomograph method application to the sonic fatigue life prediction, an analysis software program was designed and worked out in present thesis, based on the research achievement in prediction of sonic fatigue life, which strong function, easy use and great extensive capabilities.In first part of the thesis, by a review of the research on aircraft sonic fatigue, the formulas for calculating natural frequencies of the typical aircraft skin-panel structure with four edges simply-supported or four edges fixed-supported were drawn, the response of displacement and stress was analysed under the condition of random white noise loading with the steady-state or unsteady-state . The procedure how to use data of S-N curve under constant loading for predicating the fatigue life of skin-panel subjected to random loading was shown. In second part , a complete design and implement platform was constructed for sonic fatigue life analysis with the oriented-object programming design technique, as a replacement of nomograph method.Finally, the exist data on sonic fatigue life of skin-panel structure was taken as a example to verify the capability of the developed analysis software program. The result was shown that the program runs quickly and in reliability ,It can replace the nomograph method and use easily for predicating sonic fatigue life of aircraft skin-panel structure .