الفهرس 
Title : Optimum design of a composite wing using finite element analysis and genetic algorithm
SummaryOnly 14 pages are availabe for public view
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Abstract
In this research the layup sequence of a fixed thickness lamina of a composite wing parts is optimized using genetic algorithm and finite elements method. Composite materials are widely used in the aerospace industry for their weight saving characteristics. The composite materials save weight because of their high strength-to- weight ratio, and because they are easily tailored to carry the specific forces applied on the structure. Composite material used in this thesis are laminates of plies placed at certain angles, each ply is of 0.005 inch thick. The ply angles used in this thesis are limited to 0{u00BA}, ±45{u00BA}, and 90{u00BA} for manufacturing purposes. Weight saving is vital in aerospace manufacturing to save fuel, which costs nearly 30% of the total costs for the airlines. In this thesis an aluminum wing is converted to a composite wing, and is optimized for the minimum weight and compared to the composite wing. The aluminum wing is analyzed using the finite elements analysis. A model wing is checked with a simplified analytic model. The difference between finite elements and analytic analysis is 15%, which is a reasonable difference. The material is then changed to carbon fiber. The MATLAB is connected to the finite element solver, to predict the optimum layup sequence, to check buckling stability, to measure the maximum strain of the composite, and to check if the wing will undergo a divergence. Divergence occurs when the angle of attack changes, causing the lift to increase, which in turn cause the angle of attack to increase, leading to wing failure