北京航空航天大学学报 ›› 2014, Vol. 40 ›› Issue (6): 834-838.doi: 10.13700/j.bh.1001-5965.2013.0431

• 论文 • 上一篇    下一篇

复合材料加筋板筋条修理后的压缩性能

赵闯, 聂恒昌, 郭霞, 关志东   

  1. 北京航空航天大学 航空科学与工程学院, 北京 100191
  • 收稿日期:2013-07-29 出版日期:2014-06-20 发布日期:2014-07-03
  • 作者简介:赵 闯(1989- ),男,天津人,硕士生,zcmacaron@sina.cn.

Compression performance of composite stiffened panel after stiffener repair

Zhao Chuang, Nie Hengchang, Guo Xia, Guan Zhidong   

  1. School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China
  • Received:2013-07-29 Online:2014-06-20 Published:2014-07-03

摘要: 承受压缩载荷时,筋条损伤往往造成复合材料加筋板结构的严重失效.针对筋条壁板脱黏、腹板分层、上缘条损伤3种情况分别设计了相应的修理方案并制作了试验件.为保证压缩载荷的均匀施加,设计制作了加筋板试验专用夹具,含有固定试验件的卡槽和保证加载方向沿竖直方向的导轨.筋条修理后的复合材料加筋板的轴向压缩试验表明不同修理部位、不同修理方法对加筋板的力学性能影响不同.有限元分析表明加筋板的屈曲模态、整体破坏模式以及板-筋胶层的破坏情况都受到修理方案的影响.

Abstract: Subjected to compressive load, stiffener injury often causes serious failure of stiffened composite panels. In consideration of stiffener-skin debonding, delamination in web and damage to upper flange, corresponding repair programs were designed and necessary specimens were manufactured. In order to ensure a uniform compressive load during experiment, test fixture for composite stiffened panel was designed and fabricated, containing two slots to fix the stiffened panel and four guides to ensure the vertical loading direction. All the experiments that were taken using that fixture show the influences of different repair parts, different repair methods to the mechanical properties of stiffened panels are different. Finite element analysis shows that buckling mode, failure mode of stiffened panel and skin-stiffener glue injury are both influenced by repair programs.

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