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One major challenge for the aviation industry is the development of airframe structures safer, lighter and more tolerant to damage. A prominent approach in addressing this challenge involves the use of integrally stiffened panels, which have gained widespread acceptance in the aeronautical sector. This choice offers substantial benefits, including weight reduction and cost savings. Moreover, integrally stiffened panels have one key advantage over traditional built-up structures which is the absence of crack initiation sources. Considering that typical load spectra may include high-load cycles, some of which may represent overload, it is valuable to adopt a crack-propagation model that account for the retardation effect induced by overload. This effect plays a crucial role in accurately…
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One major challenge for the aviation industry is the development of airframe structures safer, lighter and more tolerant to damage. A prominent approach in addressing this challenge involves the use of integrally stiffened panels, which have gained widespread acceptance in the aeronautical sector. This choice offers substantial benefits, including weight reduction and cost savings. Moreover, integrally stiffened panels have one key advantage over traditional built-up structures which is the absence of crack initiation sources. Considering that typical load spectra may include high-load cycles, some of which may represent overload, it is valuable to adopt a crack-propagation model that account for the retardation effect induced by overload. This effect plays a crucial role in accurately predicting fatigue crack growth. The primary objective of this study is to compare the crack growth retardation models in predicting the fatigue crack growth behavior of a specific type of integral panel commonly utilized in the aeronautical industry. This investigation focuses on two widely used aluminum alloys. Additionally, this work provides an overview of the current state of the art in crack growth retardation models.