OPTIMUM DESIGN OF A COMPOSITE WING USING FINITE ELEMENT ANALYSIS AND GENETIC ALGORITHM
Radwa Abd El-Aziz Mohamed El-Morsy;
Abstract
Keywords: Genetic Algorithm, Buckling, Finite Elements Analysis, Divergence, Composites Ply Sequence.
Summary: Aerospace manufacturers are increasingly using laminated composites to replace metallic materials in primary structures in order for their high strength-to-weight ratio in order to minimize the aircraft weight. The main objective of this thesis is to convert an aluminum wing to an optimized composite wing, under stiffness, buckling and divergence constraints, so that the weight is minimum.
Structural analysis is performed using finite elements. A genetic algorithm code is written in Matlab, which is connected with a finite elements software to check the stability and divergence constraints. The divergence constraint is evaluated using the lifting line theory.
Changing the wing from aluminum to composite decreased the weight by 40%.
Summary: Aerospace manufacturers are increasingly using laminated composites to replace metallic materials in primary structures in order for their high strength-to-weight ratio in order to minimize the aircraft weight. The main objective of this thesis is to convert an aluminum wing to an optimized composite wing, under stiffness, buckling and divergence constraints, so that the weight is minimum.
Structural analysis is performed using finite elements. A genetic algorithm code is written in Matlab, which is connected with a finite elements software to check the stability and divergence constraints. The divergence constraint is evaluated using the lifting line theory.
Changing the wing from aluminum to composite decreased the weight by 40%.
Other data
| Title | OPTIMUM DESIGN OF A COMPOSITE WING USING FINITE ELEMENT ANALYSIS AND GENETIC ALGORITHM | Other Titles | التصميم الأمثل لجناح من المواد المركبة باستخدام طريقة العناصر المحدودة و الخوارزميات الجينية | Authors | Radwa Abd El-Aziz Mohamed El-Morsy | Issue Date | 2016 |
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