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In term of sonic fatigue, initiation tests are commonly stopped at 10 8 cycles assuming that a fatigue limit exists, whereas feedback experience from in service aircraft has shown that structural elements can fail even after 10 11 cycles. Thus, it is important to explore the gigacycle fatigue domain and an accelerated fatigue testing method which is presented in this paper. A method of accelerated durability testing for failure modes and life cycle based on the results of theory derivation and testing analysis are accomplished. And an acceptable estimation of acceleration factor calculation method based on the stress-lifetime approach (S-N curve) under narrow-band random acoustic condition is proved. The experimental results show that the application of the reduced time model can be a possible method for accelerated lifetime testing of time-dependent aircraft metal materials.

Accelerated sonic fatigue testing methodology for reliability assessments of aircraft structure based on linear load intensification