| 利用气动弹性的柔性振翼模型建立及分析(英文) |
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| 作者单位： | 北京航空航天大学航空科学与工程学院 |
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| 基金项目： | Foundation item： National Natural Science Foundation of China （ 10432040, 90716006） |
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| 摘 要： | Making use of modal characteristics of the natural vibration of flexible structure to design the oscillating wing aircraft is proposed. A series of equations concerning the oscillating wing of flexible structures are derived. The kinetic equation for aerodynamic force coupled with elastic movement is set up, and relevant formulae are derived. The unsteady aerodynamic one in that formulae is revised. The design principle, design process and range of application of such oscillating wing analytical method are elaborated. A flexible structural oscillating wing model is set up, and relevant time response analysis and frequency response analysis are conducted. The analytical results indicate that adopting the new-type driving way for the oscillating wing will not have flutter problems and will be able to produce propulsive force. Furthermore, it will consume much less power than the fixed wing for generating the same lift.
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| 关 键 词： | 空气弹性力学 柔性面层 惰态特点 震荡机翼 |
| 收稿时间： | 2007-09-17 |
Analysis and Flexible Structural Modeling for Oscillating Wing Utilizing Aeroelasticity |
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| Shao Ke,Wu Zhigang,Yang Chao. Analysis and Flexible Structural Modeling for Oscillating Wing Utilizing Aeroelasticity[J]. Chinese Journal of Aeronautics, 2008, 21(5): 402-410. DOI: 10.1016/S1000-9361(08)60052-7 |
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| Authors: | Shao Ke Wu Zhigang Yang Chao |
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| Affiliation: | School of Aeronautic Science and Engineering, Beijing University of Aeronautics andAstronautics, Beijing 100191, China |
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| Abstract: | Making use of modal characteristics of the natural vibration of flexible structure to design the oscillating wing aircraft is proposed. A series of equations concerning the oscillating wing of flexible structures are derived. The kinetic equation for aerodynamic force cou-pled with elastic movement is set up, and relevant formulae are derived. The unsteady aerodynamic one in that formulae is revised. The design principle, design process and range of application of such oscillating wing analytical method are elaborated. A flexible structural oscillating wing model is set up, and relevant time response analysis and frequency response analysis are conducted. The analytical re-sults indicate that adopting the new-type driving way for the oscillating wing will not have flutter problems and will be able to produce propulsive force. Furthermore, it will consume much less power than the fixed wing for generating the same lift. |
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| Keywords: | aeroelasticity flexible structure modal characteristics oscillation wing excite analysis |
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