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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2007
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my-upm-ir.52222015-08-06T04:43:39Z Structural Optimization of an Aeroelastically Tailored Composite Wing 2007 Attaran, Abdolhamid 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. 2007 Thesis http://psasir.upm.edu.my/id/eprint/5222/ http://psasir.upm.edu.my/id/eprint/5222/1/FK_2007_31.pdf application/pdf en public masters Universiti Putra Malaysia Faculty of Engineering |
| institution |
Universiti Putra Malaysia |
| collection |
PSAS Institutional Repository |
| language |
English |
| topic |
|
| spellingShingle |
Attaran, Abdolhamid Structural Optimization of an Aeroelastically Tailored Composite Wing |
| description |
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. |
| format |
Thesis |
| qualification_level |
Master's degree |
| author |
Attaran, Abdolhamid |
| author_facet |
Attaran, Abdolhamid |
| author_sort |
Attaran, Abdolhamid |
| title |
Structural Optimization of an Aeroelastically Tailored Composite Wing |
| title_short |
Structural Optimization of an Aeroelastically Tailored Composite Wing |
| title_full |
Structural Optimization of an Aeroelastically Tailored Composite Wing |
| title_fullStr |
Structural Optimization of an Aeroelastically Tailored Composite Wing |
| title_full_unstemmed |
Structural Optimization of an Aeroelastically Tailored Composite Wing |
| title_sort |
structural optimization of an aeroelastically tailored composite wing |
| granting_institution |
Universiti Putra Malaysia |
| granting_department |
Faculty of Engineering |
| publishDate |
2007 |
| url |
http://psasir.upm.edu.my/id/eprint/5222/1/FK_2007_31.pdf |
| _version_ |
1747810377077358592 |