Prediction of the comparative fatigue performance for realistic loading distributions

Abstract Calculation methods are reviewed for prediction and comparison of fatigue performance of various elements under aircraft loading spectra. Discussion is presented of standardized SN lines, used for damage calculation, and of test results obtained for standardized aircraft wing loading 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 frequency distribution, specimen geometry and material) is discussed for realistic loading spectra. The limitations of the considered fatigue life calculation methods are pointed out.

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