Aeroelastic Optimization Design for High-Aspect-Ratio Wings with Large Deformation
This paper presents a framework of aeroelastic optimization design for high-aspect-ratio wing with large deformation. A highly flexible wing model for wind tunnel test is optimized subjected to multiple aeroelastic constraints. Static aeroelastic analysis is carried out for the beamlike wing model,...
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| Main Authors: | , , , |
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| Format: | Article |
| Language: | English |
| Published: |
Wiley
2017-01-01
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| Series: | Shock and Vibration |
| Online Access: | http://dx.doi.org/10.1155/2017/2564314 |
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| _version_ | 1849410072455675904 |
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| author | Changchuan Xie Yang Meng Fei Wang Zhiqiang Wan |
| author_facet | Changchuan Xie Yang Meng Fei Wang Zhiqiang Wan |
| author_sort | Changchuan Xie |
| collection | DOAJ |
| description | This paper presents a framework of aeroelastic optimization design for high-aspect-ratio wing with large deformation. A highly flexible wing model for wind tunnel test is optimized subjected to multiple aeroelastic constraints. Static aeroelastic analysis is carried out for the beamlike wing model, using a geometrically nonlinear beam formulation coupled with the nonplanar vortex lattice method. The flutter solutions are obtained using the P-K method based on the static equilibrium configuration. The corresponding unsteady aerodynamic forces are calculated by nonplanar doublet-lattice method. This paper obtains linear and nonlinear aeroelastic optimum results, respectively, by the ISIGHT optimization platform. In this optimization problem, parameters of beam cross section are chosen as the design variables to satisfy the displacement, flutter, and strength requirements, while minimizing wing weight. The results indicate that it is necessary to consider geometrical nonlinearity in aeroelastic optimization design. In addition, optimization strategies are explored to simplify the complex optimization process and reduce the computing time. Different criterion values are selected and studied for judging the effects of the simplified method on the computing time and the accuracy of results. In this way, the computing time is reduced by more than 30% on the premise of ensuring the accuracy. |
| format | Article |
| id | doaj-art-764eb0cf48374b73bd62be0c15ffb5f0 |
| institution | Kabale University |
| issn | 1070-9622 1875-9203 |
| language | English |
| publishDate | 2017-01-01 |
| publisher | Wiley |
| record_format | Article |
| series | Shock and Vibration |
| spelling | doaj-art-764eb0cf48374b73bd62be0c15ffb5f02025-08-20T03:35:16ZengWileyShock and Vibration1070-96221875-92032017-01-01201710.1155/2017/25643142564314Aeroelastic Optimization Design for High-Aspect-Ratio Wings with Large DeformationChangchuan Xie0Yang Meng1Fei Wang2Zhiqiang Wan3School of Aeronautic Science and Engineering, Beihang University, Beijing, ChinaSchool of Aeronautic Science and Engineering, Beihang University, Beijing, ChinaChengdu Aircraft Design & Research Institute, Chengdu, ChinaSchool of Aeronautic Science and Engineering, Beihang University, Beijing, ChinaThis paper presents a framework of aeroelastic optimization design for high-aspect-ratio wing with large deformation. A highly flexible wing model for wind tunnel test is optimized subjected to multiple aeroelastic constraints. Static aeroelastic analysis is carried out for the beamlike wing model, using a geometrically nonlinear beam formulation coupled with the nonplanar vortex lattice method. The flutter solutions are obtained using the P-K method based on the static equilibrium configuration. The corresponding unsteady aerodynamic forces are calculated by nonplanar doublet-lattice method. This paper obtains linear and nonlinear aeroelastic optimum results, respectively, by the ISIGHT optimization platform. In this optimization problem, parameters of beam cross section are chosen as the design variables to satisfy the displacement, flutter, and strength requirements, while minimizing wing weight. The results indicate that it is necessary to consider geometrical nonlinearity in aeroelastic optimization design. In addition, optimization strategies are explored to simplify the complex optimization process and reduce the computing time. Different criterion values are selected and studied for judging the effects of the simplified method on the computing time and the accuracy of results. In this way, the computing time is reduced by more than 30% on the premise of ensuring the accuracy.http://dx.doi.org/10.1155/2017/2564314 |
| spellingShingle | Changchuan Xie Yang Meng Fei Wang Zhiqiang Wan Aeroelastic Optimization Design for High-Aspect-Ratio Wings with Large Deformation Shock and Vibration |
| title | Aeroelastic Optimization Design for High-Aspect-Ratio Wings with Large Deformation |
| title_full | Aeroelastic Optimization Design for High-Aspect-Ratio Wings with Large Deformation |
| title_fullStr | Aeroelastic Optimization Design for High-Aspect-Ratio Wings with Large Deformation |
| title_full_unstemmed | Aeroelastic Optimization Design for High-Aspect-Ratio Wings with Large Deformation |
| title_short | Aeroelastic Optimization Design for High-Aspect-Ratio Wings with Large Deformation |
| title_sort | aeroelastic optimization design for high aspect ratio wings with large deformation |
| url | http://dx.doi.org/10.1155/2017/2564314 |
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