Structural Optimization of an Aeroelastically Tailored Composite Wing
Effects of aspect ratio, sweep angle, and stacking sequence of laminated composites were studied to find the optimized configuration of an aeroelastically tailored composite wing idealized as a flat plate in terms of flutter speed. The aeroelastic analysis has been carried out in frequency-domain...
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| 主要作者: | |
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| 格式: | Thesis |
| 语言: | English |
| 出版: |
2007
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| 主题: | |
| 在线阅读: | http://psasir.upm.edu.my/id/eprint/5222/1/FK_2007_31.pdf |
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| 总结: | Effects of aspect ratio, sweep angle, and stacking sequence of laminated composites
were studied to find the optimized configuration of an aeroelastically tailored
composite wing idealized as a flat plate in terms of flutter speed. The aeroelastic
analysis has been carried out in frequency-domain. The modal approach in
conjunction with Doublet-lattice Method (DLM) has been opted for structural and
unsteady aerodynamic analysis, respectively. The interpolation between
aerodynamic boxes and structural nodes has been done using surface spline. To
study the effect of stacking sequence the classical lamination theory (CLT) has been
chosen. The parametric studies showed the effective ply orientation angle to be
somewhere between 15 and 30 degree, while the plates with lower aspect ratio seems
to have higher flutter speed. Forward-swept configurations show higher flutter speed,
yet imposed by divergence constraint. |
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