PREDICTION OF THE COMPARATIVE FATIGUE PERFORMANCE FOR REALISTIC LOADING DISTRIBUTIONS

Calculation methods are reviewed for prediction and comparison of fati gue performance of various elements under aircraft loading spectra. Di scussion is presented of standardized S-N lines, used for damage calcu lation, and of test results obtained for standardized aircraft wing lo ading frequency distributions. The predictive accuracy of the relative nominal-stress-approach and of the relative local-strain-approach is verified for various related aircraft loading cases. The prediction of the effect of different design factors (design stress, loading freque ncy distribution, specimen geometry and material) is discussed for rea listic loading spectra. The limitations of the considered fatigue life calculation methods are pointed out. (C) 1997 Elsevier Science Ltd.