کد مقاله | کد نشریه | سال انتشار | مقاله انگلیسی | نسخه تمام متن |
---|---|---|---|---|
1583322 | 1514886 | 2007 | 4 صفحه PDF | دانلود رایگان |

The early 1950s led to high performance aluminum skinned aircraft for which metal fatigue and fatigue crack growth became extremely important considerations. Virtually, no significant range of data on fatigue crack growth existed prior to McEvily's work [A.J. McEvily Jr., W. Illg, The rate of fatigue crack propagation in two aluminium alloys, NACA (now NASA), TN 4394, 1958], and controlling parameters were left to be further developed. His pioneering work allowed others to resolve some of the critical issues, and yet a few still remain open even today. This discussion will trace historical milestones in the field, as well as some more recent investigations, with the intention of exposing the major trends in determining “effective stress intensity factor ranges”, the main mechanical cause of crack growth.
Journal: Materials Science and Engineering: A - Volumes 468–470, 15 November 2007, Pages 70–73