Optimum Buckling Design for Composite Wing Cover Panels with Manufacturing Constraints
Author:
Affiliation:
1. University of Bath
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.2007-2215
Reference17 articles.
1. Optimization of laminate stacking sequence for buckling load maximization by genetic algorithm
2. 2Nagendra S., Haftka, R. T., Gürdal, Z. "Design of a Blade Stiffened Composite Panel by a Genetic Algorithm," AIAA Paper 1993-1584,1993.
3. Post-buckling optimisation of composite stiffened panels using neural networks
4. Two-level optimization technique of composite laminate panels by genetic algorithms
5. 5Herencia, J. E., Weaver, P. M., and Friswell, M. I. "Local Optimization of Long Anisotropic Laminated Fibre Composite Panels with TShapeStiffeners," AIAA Ppaer,2006-2171,2006.
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