Abstract
Structural health monitoring of cracked aircraft structural panels repaired with bonded FRP composite patches has received wide attention to extend service life of aging aircraft. In this paper is presented the method to identify the location and shape of a fatigue crack front in aircraft structural panels repaired with a bonded FRP composite patch by use of a tunneling method. As measured values, strains on a measurement plane in the FRP composite patch are utilized. Several numerical examples of the identification of location and shape of fatigue crack fronts are examined, and the effects of number of strain measurement points, position of a strain measurement plane and measurement errors of strains on the identification results are discussed. The validity of the present identification method is verified by comparing the identification results with the exact ones.
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
More From: JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
Disclaimer: 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.