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Towards imperfection insensitive buckling response of shell structures-shells with plate-like post-buckled responses

Published online by Cambridge University Press:  29 February 2016

S. C. White  and
P. M. Weaver
S. C. White*
Affiliation:
Advanced Composite Centre for Innovation and Science, University of BristolBristol
P. M. Weaver*
Affiliation:
Advanced Composite Centre for Innovation and Science, University of BristolBristol
*
paul.weaver@bristol.ac.uk
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Abstract

The imperfection sensitivity of cylindrical panels under compression loading is shown to be not only reduced but effectively eliminated using stiffness tailoring techniques. Shells are designed with variable angle-tow (VAT) laminae, giving their laminates variable-stiffness properties over the surface co-ordinates. By employing an asymptotic model of the non-linear shell behaviour and a genetic algorithm, the post-buckling stability was maximised with respect to the VAT design variables. Results for optimised straight-fibre and VAT shells are presented in comparison with quasi-isotropic designs. In the straight-fibre case, small improvements in the post-buckling stability are shown to be possible but at the expense of the buckling load. In the VAT case, on the other hand, considerable improvements in the post-buckling stability are obtained and drops in axial stiffness and load associated with buckling are reduced to negligible levels. The improvements are shown to be a result of a benign membrane stress distribution prior to buckling and a localisation of the buckling mode. The asymptotic results are compared with non-linear finite-element analyses and are found to be in good agreement. Potential future multi-objective optimisation studies are discussed.

Keywords

Bucklingpost-bucklingcompositeshellsimperfection-sensitivityvariable stiffnessComposite materials
Type
Research Article
Information
The Aeronautical Journal , Volume 120 , Issue 1224 , February 2016 , pp. 233 - 253
Copyright
Copyright © Royal Aeronautical Society 2016 

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