Abstract
The global buckling of a composite plate with a single rectangular delamination is studied using a smearing method and employing exact stiffness analysis and the Wittrick–Williams algorithm. Computational efficiency is achieved by avoiding discretisation into elements and non-linear analyses, making the method suitable for parametric studies in preliminary aircraft design. Numerical results for longitudinal compressive loading show the level of reduction in buckling load with increasing length and width of delamination. Global buckling strength is increased as the delamination is moved towards the plate surface, but is relatively insensitive to its widthwise and lengthwise location. The results are validated by finite element analysis.
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.
