| 变截面Z型折叠机翼振动特性的有限元与实验分析 |
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| 引用本文： | 王松松,郭翔鹰,王帅博.变截面Z型折叠机翼振动特性的有限元与实验分析[J].动力学与控制学报,2020,18(5):84-89. |
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| 作者姓名： | 王松松 郭翔鹰 王帅博 |
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| 作者单位： | 北京工业大学机械工程与应用电子技术学院,北京工业大学机械工程与应用电子技术学院,北京工业大学机械工程与应用电子技术学院 |
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| 基金项目： | 国家自然科学基金项目（面上项目,重点项目,重大项目） |
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| 摘 要： | Z型变截面折叠机翼作为一种可变体机翼结构,不同的折叠角对机翼稳定性有着重要的影响,因此研究不同折叠角度下的特性参数对机翼动态稳定性有着重要的意义.本文首先设计加工了Z型变截面可折叠机翼结构的实验模型,通过建立与实验模型相匹配的有限元模型,仿真得到不同折叠角度下机翼的前5阶固有频率和振型,针对不同折叠角度下机翼的固有特性,通过扫频实验得到机翼前5阶固有频率和模态振型,以及横向外激励作用下三段翼的频响曲线,对比分析有限元仿真与实验结果,验证结果的可靠性,这将对机翼结构设计以及特性参数的选取提供参考依据.
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| 关 键 词： | 变体飞行器 折叠机翼 固有频率 模态 |
| 收稿时间： | 2019/7/15 0:00:00 |
| 修稿时间： | 2019/9/19 0:00:00 |
FINITE ELEMENT ANALYSIS AND EXPERIMENT ON VIBRATION OF Z-SHAPED MORPHING WING WITH VARIABLE SECTION |
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| Wang Songsong,Guo Xiangying,Wang Shuaibo.FINITE ELEMENT ANALYSIS AND EXPERIMENT ON VIBRATION OF Z-SHAPED MORPHING WING WITH VARIABLE SECTION[J].Journal of Dynamics and Control,2020,18(5):84-89. |
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| Authors: | Wang Songsong Guo Xiangying Wang Shuaibo |
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| Affiliation: | </Section> <Section> College of Mechanical Engineering,Beijing University of Technology,</Section> <Section> College of Mechanical Engineering,Beijing University of Technology,</Section> <Section> College of Mechanical Engineering,Beijing University of Technology |
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| Abstract: | Z variable cross-section morphing wings, as a kind of variant wing structure, different folded angle has important influence on the stability of the wing, so the characteristic parameters of different folding angle of wing dynamic stability have important significance. This paper design the processing of the Z experimental model of variable cross-section folding wing structure, by establishing a finite element model of match the experimental model, simulation with different folding angle under the wing of the first five order natural frequency and vibration mode, the intrinsic characteristics of angles for different morphing wing, wing is obtained by frequency sweep test before five order natural frequency and modal vibration mode, and under the transverse outside the frequency response of three wings curve, comparative analysis of finite element simulation and experimental results to verify the reliability of the results, which will provide a reference for the design of wing structure and the selection of characteristic parameters. |
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| Keywords: | Variant Aircraft folding wings natural frequency modal |
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