Abstract Scope |
There is a significant body of research work addressing micromechanical and physics-based modeling of fatigue phenomena in structural alloys, as well as their experimental characterization. This research has important practical implications in high-impact industries such as aerospace, medical and nuclear applications. However, in order to realize its full potential, it is important to understand how such modeling and experimental capabilities can support specific design objectives and certification requirements. This presentation will discuss how various elements of the “total life” approach, including crack nucleation, small crack growth and long crack growth, map into design and certification considerations for aviation applications. The intent is to provide scientists typically working in the lower TRL domain with a better understanding of the practical implications of their research from the end-user perspective, including design, qualification and certification of high criticality aircraft and engine components produced using both conventional and advanced manufacturing technologies |