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航空复合材料加筋板压缩屈曲及后屈曲性能

冯宇 何宇廷 邵青 高潮

冯宇, 何宇廷, 邵青, 高潮. 航空复合材料加筋板压缩屈曲及后屈曲性能[J]. 航空动力学报, 2014, 29(12): 2905-2913. doi: 10.13224/j.cnki.jasp.2014.12.017
引用本文: 冯宇, 何宇廷, 邵青, 高潮. 航空复合材料加筋板压缩屈曲及后屈曲性能[J]. 航空动力学报, 2014, 29(12): 2905-2913. doi: 10.13224/j.cnki.jasp.2014.12.017
FENG Yu, HE Yu-ting, SHAO Qing, GAO Chao. Buckling and post-buckling performance of aeronautic composite stiffened panel under compression[J]. Journal of Aerospace Power, 2014, 29(12): 2905-2913. doi: 10.13224/j.cnki.jasp.2014.12.017
Citation: FENG Yu, HE Yu-ting, SHAO Qing, GAO Chao. Buckling and post-buckling performance of aeronautic composite stiffened panel under compression[J]. Journal of Aerospace Power, 2014, 29(12): 2905-2913. doi: 10.13224/j.cnki.jasp.2014.12.017

航空复合材料加筋板压缩屈曲及后屈曲性能

doi: 10.13224/j.cnki.jasp.2014.12.017
详细信息
    作者简介:

    冯宇(1989-), 男, 陕西西安人, 博士生, 主要从事飞机复合材料结构强度、疲劳寿命的研究.

  • 中图分类号: V231;TB332

Buckling and post-buckling performance of aeronautic composite stiffened panel under compression

  • 摘要: 开展了航空复合材料加筋板压缩试验,得到了加筋板的屈曲载荷、破坏载荷及破坏模式.加筋板平均屈曲载荷和平均破坏载荷分别为587.5,968.25kN,后者是前者的1.65倍,表明加筋板在压缩载荷下存在较强的后屈曲承载能力,其破坏模式主要是筋条的脱黏、断裂以及壁板的撕裂,破坏位置通常在加筋板中部.应用有限元软件得到了加筋板的屈曲载荷、破坏载荷及后屈曲损伤过程,其中屈曲载荷、破坏载荷与试验结果较吻合,误差分别为-9.97%和8.45%,验证了有限元模型的有效性.研究了加筋板纤维和基体出现损伤的先后顺序,结果表明在后屈曲过程中加筋板纤维先于基体出现损伤,尤其是筋条中部纤维的损伤最为严重,加筋板破坏之前基体基本不存在损伤.

     

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出版历程
  • 收稿日期:  2014-06-27
  • 刊出日期:  2014-12-28

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