北京航空航天大学学报 ›› 2001, Vol. 27 ›› Issue (2): 167-170.

• 论文 • 上一篇    下一篇

非对称非均衡层板弯扭耦合效应研究

许德伟1, 郦正能1, 崔德刚2   

  1. 1. 北京航空航天大学 飞行器设计与应用力学系;
    2. 航空工业总公司 科技局
  • 收稿日期:1999-10-18 出版日期:2001-02-28 发布日期:2010-09-27
  • 作者简介:许德伟(1974-),男,湖北宜都人,博士生,100083,北京.
  • 基金资助:

    国家自然科学基金资助项目(59675036)

Bend/Twist Coupling Effects of Unsymmetric and Unbalanced Laminate

XU De-wei1, LI Zheng-neng1, CUI De-gang2   

  1. 1. Beijing University of Aeronautics and Astronautics, Dept. of Flight Vehicle Design and Applied Mechanics;
    2. Science and Technology Bureau of AVIC
  • Received:1999-10-18 Online:2001-02-28 Published:2010-09-27

摘要: 在对称层板的基础上添加铺层使得整个层板成为非对称或非均衡层板,用数值计算方法对添加铺层后的层板在拉或弯载荷下由于弯扭耦合效应产生的端面变形进行了研究,得到了最有利的添加层铺层位置和添加层铺设角,并用蜂窝夹芯板模拟机翼翼盒进行了实验验证.实验表明,从数值计算所得到的结果与实验结果相比具有良好的一致性.

Abstract: In order to obtain particular twist angle of composite structure, utilizing the coupling effects of unsymmetric&unbalanced laminate is a considerable approach. An unsymmetric&unbalanced laminate is formed by adding a sub-laminate into the symmetric laminate. How to lay the sub-laminate and what the optimal orientation angle of the sub-laminate is are studied in order to make the most use of coupling effects by nonlinear finite element methods. Test results of honeycomb core sandwich composite laminate simulating the wing-box under the load of aerodynamics demonstrate that the calculating results well accord with the test results and unsymmetric&unbalanced laminates have prospective engineering applications.

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