Critical buckling of delaminated composite plates using exact stiffness analysis

Damghani, Mahdi; Kennedy, David; Featherston, Carol

Abstract

The critical buckling of composite plates with through-the-length delaminations is studied using exact stiffness analysis and the Wittrick-Williams algorithm. Computational efficiency is achieved by avoiding discretisation into elements, making the method suitable for preliminary aircraft design. Numerical results for longitudinal, transverse and shear loading show a transition from global to local buckling modes as the delamination width is increased. The critical buckling strength is dramatically reduced as the delamination is moved towards the plate surface, but is relatively insensitive to its widthwise location or to the edge conditions. The results are compared with finite element analysis. © 2011 Elsevier Ltd. All rights reserved.

Citation

Damghani, M., Kennedy, D., & Featherston, C. (2011). Critical buckling of delaminated composite plates using exact stiffness analysis. Computers and Structures, 89(13-14), 1286-1294. https://doi.org/10.1016/j.compstruc.2011.04.003

• Journal Article Type: Article
• Acceptance Date: Apr 10, 2011
• Publication Date: Jul 1, 2011
• Deposit Date: Jul 27, 2016
• Journal: Computers and Structures
• Print ISSN: 0045-7949
• Publisher: Elsevier
• Peer Reviewed: Peer Reviewed
• Volume: 89
• Issue: 13-14
• Pages: 1286-1294
• DOI: https://doi.org/10.1016/j.compstruc.2011.04.003
• Keywords: aerospace structures, composites, buckling, delamination, exact strip, Wittrick–Williams algorithm
• Public URL: https://uwe-repository.worktribe.com/output/967810
• Publisher URL: http://dx.doi.org/10.1016/j.compstruc.2011.04.003