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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北京工业大学 机械工程与应用电子技术学院,北京 100124

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E-mail: eagle2008guo@yeah.net

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国家自然科学基金资助项目(11572006,11772010)


FINITE ELEMENT ANALYSIS AND EXPERIMENT ON VIBRATION OF Z-SHAPED MORPHING WING WITH VARIABLE SECTION
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College of Mechanical Engineering, Beijing University of Technology, Beijing 100124, China

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The project supported by the National Natural Science Foundation of China(11572006,11772010)

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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.

    Abstract:

    Z-shaped morphing wings with variable cross section is a kind of variant wing, and the folded angle has important influence on the dynamic stability of the wing. This paper studied the vibration characteristics of the Z-shaped morphing wing for different folded angles through both finite element analysis and experiment. Firstly, the experimental prototype of the Z-shaped folding wing was designed and fabricated. And then, a finite element model of the prototype was established, and simulations for different folding angles were conducted to obtain the first five natural frequencies and modes of the wing. Furthermore, frequency sweep tests on the prototype wing were carried out to obtain frequency responses under transverse excitations, and thus to reveal the first five natural frequencies and modes experimentally. Comparison between finite element simulations and experimental results showed good agreement, which verified the dynamic model of the Z-shaped morphing wing. This study would provide a reference for the design of morphing wing.

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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(6):84~89; 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(6):84-89.

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  • 收稿日期:2019-07-15
  • 最后修改日期:2019-09-19
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  • 在线发布日期: 2021-01-05
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