期刊
COMPOSITES SCIENCE AND TECHNOLOGY
卷 68, 期 15-16, 页码 3150-3160出版社
ELSEVIER SCI LTD
DOI: 10.1016/j.compscitech.2008.07.017
关键词
Delamination; Debonding; Buckling; Damage mechanics; Finite element analysis
资金
- European Commission, Priority Aeronautics and Space [AST3-CT-2003-502723]
- Australian Postgraduate Awards Scheme
- Cooperative Research Centre for Advanced Composite Structures (CRC-ACS)
- German Academic Exchange Service (DAAD)
- Italian Ministry of Foreign Affairs
- Australian Government under both the Innovation Access Programme International Science and Technology
Experimental and numerical investigations were conducted into the damage growth and collapse behaviour of composite blade-stiffened structures. Four panel types were tested, consisting of two secondary-bonded skin-stiffener designs in both undamaged and pre-damaged configurations. The pre-damaged configurations were manufactured by replacing the skin-stiffener adhesive with a centrally located, full-width Teflon strip. All panels were loaded in compression to collapse, which was characterised by complex post-buckling deformation patterns and ply damage, particularly in the stiffener. For the pre-damaged panels, significant crack growth was seen in the skin-stiffener interface prior to collapse, which caused a reduction in load-carrying capacity. In the numerical analysis of the undamaged panels, collapse was predicted using a ply failure degradation model, and a global-local approach that monitored a strength-based criterion in the skin-stiffener interface. The pre-damaged models were analysed with ply degradation and a method for capturing interlaminar crack growth based on multi-point constraints controlled using the Virtual Crack Closure Technique. The numerical approach gave close correlation with experimental results, and allowed for an in-depth analysis of the damage growth and failure mechanisms contributing to panel collapse. The successful prediction of collapse under the combination of deep post-buckling deformations and several composite damage mechanisms has application for the next generation of composite aircraft designs. (c) 2008 Elsevier Ltd. All rights reserved.
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