Modelling delaminations in postbuckling stiffened composite shear panels |
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Authors: | R S Thomson M L Scott |
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Affiliation: | (1) Cooperative Research Centre for Advanced Composite Structures Limited, 506 Lorimer Street, Fishermens Bend, Victoria, 3207, Australia, AU;(2) Sir Lawrence Wackett Centre for Aerospace Design Technology, Department of Aerospace Engineering, Royal Melbourne Institute of Technology, GPO Box 2476V, Melbourne, Victoria, 3001, Australia, AU |
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Abstract: | A method has been developed to predict the effect of delaminations in a postbuckling stiffened structure manufactured from
laminated composite materials. The emphasis of the technique, driven by aircraft certification requirements, was towards establishing
whether delamination growth would initiate under given loading conditions. A geometric nonlinear finite element analysis was
used to calculate the strain energy release rate around the circumference of a circular delamination using the virtual crack
closure technique. In order to deal with the complex structural response in a computationally efficient manner, the structure
was modelled using plate elements with two layers of plate elements used in the delaminated region. The effect of delamination
size on the strength of postbuckling panels was shown to be a complex phenomenon in which trends were difficult to predict.
Large delaminations could significantly affect the global and sub-laminate buckling modes and therefore be less critical than
smaller delaminations. It was concluded that the method could accurately predict the load and location at which delamination
growth would initiate, given suitable critical strain energy release rate data.
Received 16 February 2000 |
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