Abstract
For complex engineering systems, there is an increasing interest in the use of structural health monitoring systems to estimate the current state of damage (diagnosis) and to predict the behavior of the damage in the future (prognosis). For fatigue crack growth, one challenge in prognosis is to predict dynamic stress history at the location of damage. In this article, a method of predicting fatigue crack growth in aircraft panels is proposed under variable amplitude loading. A simple analytical–numerical method is proposed to calculate dynamic stress history from the usage monitoring data. A variable amplitude fatigue analysis is then conducted through the use of a fatigue crack growth model with the extended finite element method. Numerical examples show that the effect of underload and overload is significant in fatigue crack growth. It is also indicated that the crack growth rate and direction can significantly change under the multi-axial loading environment.
Sign-in/Register to access full text options 
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.
