Geometrical Nonlinear Aeroelastic Stability Analysis of a Composite High-Aspect-Ratio Wing
A composite high-aspect-ratio wing of a high-altitude long-endurance (HALE) aircraft was modeled with FEM by MSC/NASTRAN, and the nonlinear static equilibrium state is calculated under design load with follower force effect, but without load redistribution. Assuming the little vibration amplitude of...
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| Format: | Article |
| Language: | English |
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Wiley
2008-01-01
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| Series: | Shock and Vibration |
| Online Access: | http://dx.doi.org/10.1155/2008/957561 |
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| _version_ | 1832555097182175232 |
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| author | Chang Chuan Xie Jia Zhen Leng Chao Yang |
| author_facet | Chang Chuan Xie Jia Zhen Leng Chao Yang |
| author_sort | Chang Chuan Xie |
| collection | DOAJ |
| description | A composite high-aspect-ratio wing of a high-altitude long-endurance (HALE) aircraft was modeled with FEM by MSC/NASTRAN, and the nonlinear static equilibrium state is calculated under design load with follower force effect, but without load redistribution. Assuming the little vibration amplitude of the wing around the static equilibrium state, the system is linearized and the natural frequencies and mode shapes of the deformed structure are obtained. Planar doublet lattice method is used to calculate unsteady aerodynamics in frequency domain ignoring the bending effect of the deflected wing. And then, the aeroelastic stability analysis of the system under a given load condition is successively carried out. Comparing with the linear results, the nonlinear displacement of the wing tip is higher. The results indicate that the critical nonlinear flutter is of the flap/chordwise bending type because of the chordwise bending having quite a large torsion component, with low critical speed and slowly growing damping, which dose not appear in the linear analysis. Furthermore, it is shown that the variation of the nonlinear flutter speed depends on the scale of the load and on the chordwise bending frequency. The research work indicates that, for the very flexible HALE aircraft, the nonlinear aeroelastic stability is very important, and should be considered in the design progress. Using present FEM software as the structure solver (e.g. MSC/NASTRAN), and the unsteady aerodynamic code, the nonlinear aeroelastic stability margin of a complex system other than a simple beam model can be determined. |
| format | Article |
| id | doaj-art-26d41c41adea4a369a4fd10dcbf42f78 |
| institution | Kabale University |
| issn | 1070-9622 1875-9203 |
| language | English |
| publishDate | 2008-01-01 |
| publisher | Wiley |
| record_format | Article |
| series | Shock and Vibration |
| spelling | doaj-art-26d41c41adea4a369a4fd10dcbf42f782025-02-03T05:49:31ZengWileyShock and Vibration1070-96221875-92032008-01-01153-432533310.1155/2008/957561Geometrical Nonlinear Aeroelastic Stability Analysis of a Composite High-Aspect-Ratio WingChang Chuan Xie0Jia Zhen Leng1Chao Yang2Aeroelasticity Branch, Aircraft Design Institute, Beijing University of Aero. & Astro., Beijing 100083, ChinaAeroelasticity Branch, Aircraft Design Institute, Beijing University of Aero. & Astro., Beijing 100083, ChinaAeroelasticity Branch, Aircraft Design Institute, Beijing University of Aero. & Astro., Beijing 100083, ChinaA composite high-aspect-ratio wing of a high-altitude long-endurance (HALE) aircraft was modeled with FEM by MSC/NASTRAN, and the nonlinear static equilibrium state is calculated under design load with follower force effect, but without load redistribution. Assuming the little vibration amplitude of the wing around the static equilibrium state, the system is linearized and the natural frequencies and mode shapes of the deformed structure are obtained. Planar doublet lattice method is used to calculate unsteady aerodynamics in frequency domain ignoring the bending effect of the deflected wing. And then, the aeroelastic stability analysis of the system under a given load condition is successively carried out. Comparing with the linear results, the nonlinear displacement of the wing tip is higher. The results indicate that the critical nonlinear flutter is of the flap/chordwise bending type because of the chordwise bending having quite a large torsion component, with low critical speed and slowly growing damping, which dose not appear in the linear analysis. Furthermore, it is shown that the variation of the nonlinear flutter speed depends on the scale of the load and on the chordwise bending frequency. The research work indicates that, for the very flexible HALE aircraft, the nonlinear aeroelastic stability is very important, and should be considered in the design progress. Using present FEM software as the structure solver (e.g. MSC/NASTRAN), and the unsteady aerodynamic code, the nonlinear aeroelastic stability margin of a complex system other than a simple beam model can be determined.http://dx.doi.org/10.1155/2008/957561 |
| spellingShingle | Chang Chuan Xie Jia Zhen Leng Chao Yang Geometrical Nonlinear Aeroelastic Stability Analysis of a Composite High-Aspect-Ratio Wing Shock and Vibration |
| title | Geometrical Nonlinear Aeroelastic Stability Analysis of a Composite High-Aspect-Ratio Wing |
| title_full | Geometrical Nonlinear Aeroelastic Stability Analysis of a Composite High-Aspect-Ratio Wing |
| title_fullStr | Geometrical Nonlinear Aeroelastic Stability Analysis of a Composite High-Aspect-Ratio Wing |
| title_full_unstemmed | Geometrical Nonlinear Aeroelastic Stability Analysis of a Composite High-Aspect-Ratio Wing |
| title_short | Geometrical Nonlinear Aeroelastic Stability Analysis of a Composite High-Aspect-Ratio Wing |
| title_sort | geometrical nonlinear aeroelastic stability analysis of a composite high aspect ratio wing |
| url | http://dx.doi.org/10.1155/2008/957561 |
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