Abstract
The aerospace industry is striving to design less conservative and hence more efficient structures in order to meet weight reduction targets, and consequently give improvements in fossil fuel use. With this focus comes the need for the development of more accurate techniques for the assessment of the structural integrity of complex, lightweight, safety-critical components. Examples of such components are wing skin panels, which, with their array of stiffeners and holes, present a complex mixed-mode loading problem where cracks can change their growth direction. This paper focuses on the exploration of experimental mechanics methods which can be used to understand such mixed-mode fatigue failure problems.
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Tomlinson, R.A. (2011). Crack tip stress fields under biaxial loads using TSA. In: Proulx, T. (eds) Experimental and Applied Mechanics, Volume 6. Conference Proceedings of the Society for Experimental Mechanics Series. Springer, New York, NY. https://doi.org/10.1007/978-1-4419-9792-0_44
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DOI: https://doi.org/10.1007/978-1-4419-9792-0_44
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