New Method for Analyzing the Flutter Stability of Hingeless Blades with Advanced Geometric Configurations in Hovering
A new method used to analyze the aeroelastic stability of a helicopter hingeless blade in hovering has been developed, which is especially suitable for a blade with advanced geometric configuration. This method uses a modified doublet-lattice method (MDLM) and a 3-D finite element (FE) model for bui...
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| Main Authors: | , , , , |
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| Format: | Article |
| Language: | English |
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Wiley
2020-01-01
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| Series: | International Journal of Aerospace Engineering |
| Online Access: | http://dx.doi.org/10.1155/2020/1891765 |
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| author | Si-wen Wang Jing-long Han Quan-long Chen Hai-wei Yun Xiao-mao Chen |
| author_facet | Si-wen Wang Jing-long Han Quan-long Chen Hai-wei Yun Xiao-mao Chen |
| author_sort | Si-wen Wang |
| collection | DOAJ |
| description | A new method used to analyze the aeroelastic stability of a helicopter hingeless blade in hovering has been developed, which is especially suitable for a blade with advanced geometric configuration. This method uses a modified doublet-lattice method (MDLM) and a 3-D finite element (FE) model for building the aeroelastic equation of a blade in hovering. Thereafter, the flutter solution of the equation is calculated by the V-g method, assuming blade motions to be small perturbations about the steady equilibrium deflection. The MDLM, which is suitable to calculate the unsteady aerodynamic force of nonplanar rotor blade in hovering, is developed from the doublet-lattice method (DLM). The structural analysis tool is the commercial software ANSYS. The comparisons of the obtained results against those in the literatures show the capabilities of the MDLM and the method of structural analysis. The flutter stabilities of swept tip blades with different aspect ratios are analyzed using the new method developed in this work and the usual method on the basis of the unsteady strip theory and beam model. It shows that considerable differences appear in the flutter rotational velocities with the decrease of the aspect ratio. The flutter rotational velocities obtained by the present method are evidently lower than those obtained by the usual method. |
| format | Article |
| id | doaj-art-f86f23382ca04ce9a5d905005674f3e5 |
| institution | Kabale University |
| issn | 1687-5966 1687-5974 |
| language | English |
| publishDate | 2020-01-01 |
| publisher | Wiley |
| record_format | Article |
| series | International Journal of Aerospace Engineering |
| spelling | doaj-art-f86f23382ca04ce9a5d905005674f3e52025-02-03T06:06:55ZengWileyInternational Journal of Aerospace Engineering1687-59661687-59742020-01-01202010.1155/2020/18917651891765New Method for Analyzing the Flutter Stability of Hingeless Blades with Advanced Geometric Configurations in HoveringSi-wen Wang0Jing-long Han1Quan-long Chen2Hai-wei Yun3Xiao-mao Chen4State Key Laboratory of Mechanics and Control of Mechanical Structures, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, ChinaState Key Laboratory of Mechanics and Control of Mechanical Structures, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, ChinaChongqing Enstrom General Aviation Institute of Technology, Chongqing 401135, ChinaState Key Laboratory of Mechanics and Control of Mechanical Structures, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, ChinaState Key Laboratory of Mechanics and Control of Mechanical Structures, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, ChinaA new method used to analyze the aeroelastic stability of a helicopter hingeless blade in hovering has been developed, which is especially suitable for a blade with advanced geometric configuration. This method uses a modified doublet-lattice method (MDLM) and a 3-D finite element (FE) model for building the aeroelastic equation of a blade in hovering. Thereafter, the flutter solution of the equation is calculated by the V-g method, assuming blade motions to be small perturbations about the steady equilibrium deflection. The MDLM, which is suitable to calculate the unsteady aerodynamic force of nonplanar rotor blade in hovering, is developed from the doublet-lattice method (DLM). The structural analysis tool is the commercial software ANSYS. The comparisons of the obtained results against those in the literatures show the capabilities of the MDLM and the method of structural analysis. The flutter stabilities of swept tip blades with different aspect ratios are analyzed using the new method developed in this work and the usual method on the basis of the unsteady strip theory and beam model. It shows that considerable differences appear in the flutter rotational velocities with the decrease of the aspect ratio. The flutter rotational velocities obtained by the present method are evidently lower than those obtained by the usual method.http://dx.doi.org/10.1155/2020/1891765 |
| spellingShingle | Si-wen Wang Jing-long Han Quan-long Chen Hai-wei Yun Xiao-mao Chen New Method for Analyzing the Flutter Stability of Hingeless Blades with Advanced Geometric Configurations in Hovering International Journal of Aerospace Engineering |
| title | New Method for Analyzing the Flutter Stability of Hingeless Blades with Advanced Geometric Configurations in Hovering |
| title_full | New Method for Analyzing the Flutter Stability of Hingeless Blades with Advanced Geometric Configurations in Hovering |
| title_fullStr | New Method for Analyzing the Flutter Stability of Hingeless Blades with Advanced Geometric Configurations in Hovering |
| title_full_unstemmed | New Method for Analyzing the Flutter Stability of Hingeless Blades with Advanced Geometric Configurations in Hovering |
| title_short | New Method for Analyzing the Flutter Stability of Hingeless Blades with Advanced Geometric Configurations in Hovering |
| title_sort | new method for analyzing the flutter stability of hingeless blades with advanced geometric configurations in hovering |
| url | http://dx.doi.org/10.1155/2020/1891765 |
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