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充气式机翼的颤振特性分析

谢长川 王伟建 杨超

谢长川, 王伟建, 杨超等 . 充气式机翼的颤振特性分析[J]. 北京航空航天大学学报, 2011, 37(7): 833-838.
引用本文: 谢长川, 王伟建, 杨超等 . 充气式机翼的颤振特性分析[J]. 北京航空航天大学学报, 2011, 37(7): 833-838.
Xie Changchuan, Wang Weijian, Yang Chaoet al. Flutter analysis of inflatable wings[J]. Journal of Beijing University of Aeronautics and Astronautics, 2011, 37(7): 833-838. (in Chinese)
Citation: Xie Changchuan, Wang Weijian, Yang Chaoet al. Flutter analysis of inflatable wings[J]. Journal of Beijing University of Aeronautics and Astronautics, 2011, 37(7): 833-838. (in Chinese)

充气式机翼的颤振特性分析

基金项目: 国家自然科学基金资助项目(90716006,10902006); 高等学校博士点基金资助项目(20091102110015)
详细信息
    作者简介:

    谢长川(1976-),男,陕西西安人,博士后,xiechangc@163.com.

  • 中图分类号: V 211.47

Flutter analysis of inflatable wings

  • 摘要: 充气式机翼的结构刚度由内充气压决定,其颤振特性需要建立静、动力学耦合的分析方法.机翼结构刚度和固有振动特性需要在静力分析基础上计算,进一步计算非定常气动力,从而采用传统的颤振计算方法分析其颤振特性.针对某一充气式机翼采用膜单元建立了有限元模型.在不同内充压条件下,对充气机翼进行了静力分析得到其结构刚度;然后对机翼进行模态计算和颤振分析.研究表明:各阶模态的频率随内充气压的升高而升高;除典型的弯扭模态外,充气机翼的弦向弯曲模态频率较低;充气机翼的颤振形式除常规的弯扭模态耦合外,弦向弯曲模态同样会发生颤振;机翼的临界颤振速度随内充压的变化近似呈分段线性变化;临界颤振模态及耦合分支在一定气压范围内保持不变.

     

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出版历程
  • 收稿日期:  2010-07-08
  • 网络出版日期:  2011-07-30

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