The purpose of this study is to validate a method which estimates fatigue damage in stress concentration fields under aeronautical type load spectra. The calculation principle is mainly based on the determination of the local conditions (stress and strain) and on the use of the Manson-Coffin curve. This approach is compared with tests carried out on notched test specimens (stress concentration factor equal to 2,8). The materials used are an aluminium alloy, 2024 T351 and a titanium alloy, Ti-6Al-4V annealed. The selected load spectra are representative of narrow body civil aircraft. They cover three typical areas of the airframe: the wing lower surface, the upper fuselage and the engine pylon attachment. The analysis of the results shows a very satisfactory correlation between the prediction by calculation and the experimental data. The use of a local approach is efficient for fatigue damage prediction under spectrum loading in high stress concentration fields. Local stress and strain are easily approximated by Neuber's law or Glinka's energetic approach. In the frame of the investigated spectra, the difference between both estimations is very small. For the mean stress consideration, good results are provided by Morrow's correction.
Fatigue damage calculation in stress concentration fields under variable uniaxial stress
Berechnung der Ermüdungsschädigung in Spannungskonzentrationsfeldern bei veränderlicher einachsiger Spannung
International Journal of Fatigue ; 18 , 4 ; 245-253
1996
9 Seiten, 13 Bilder, 5 Tabellen, 11 Quellen
Aufsatz (Zeitschrift)
Englisch
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