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.
Z-shaped morphing wings with variable cross section is a kind of variant wing,and the folded angle has im⁃portant 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 re⁃sponses 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 dy⁃namic model of the Z-shaped morphing wing.This study would provide a reference for the design of morphing wing.
作者
王松松
郭翔鹰
王帅博
Wang Songsong;Guo Xiangying;Wang Shuaibo(College of Mechanical Engineering,Beijing University of Technology,Beijing 100124,China)
出处
《动力学与控制学报》
2020年第6期84-89,共6页
Journal of Dynamics and Control
基金
国家自然科学基金资助项目(11572006,11772010)。
关键词
变体飞行器
折叠机翼
固有频率
模态
variant aircraft
folding wings
natural frequency
modal testing
