Abstract
A damage tolerance analysis methodology for cracks subjected to real loading is presented. A new retardation model, based on material hardening within the overload plastic zone, is developed for irregular stress histories. For the transformation of the irregular stress history into a stress history containing only distinguished cycles, a technique based on the rainflow counting method is used. The methodology is applied to real aircraft loading histories for the conventional 2024-T3 aluminum alloy and the advanced 8090-T8 aluminum–lithium alloy. Predictions agree well with the experimental results. Limitations of the prediction method are also discussed.
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
