期刊文献+

含开口复合材料柱面壳压缩性能 被引量:7

Compressive behaviour of composite cylindrical shell with open hole
下载PDF
导出
摘要 实验研究了含开口补强三分之一弧长复合材料柱面壳结构的压缩行为.测试的开口补强件在开口处最终发生屈曲破坏,其最终屈曲载荷为65.922 kN.利用ABAQUS有限元软件建立相应有限元模型研究其屈曲行为,将屈曲破坏形式及载荷的计算结果与实验结果进行比较,证明所建立的模型正确有效.研究结果表明:在不补强情况下,随着开口面积增加,压缩屈曲载荷并非完全递减,而是在某一个开口面积范围内具有极大和极小值;在补强情况下,如果开口面积一定,屈曲载荷与开口高度成正比,与开口宽度成反比.因此,在设计和工艺允许的情况下,应尽量增加开口高度. The compressive behavior of one-third composite cylindrical shell with opening reinforcement was studied under a compress load.The reinforced specimen was tested and failed in buckling at 65.922 kN near the open hole.A finite element model was established in ABAQUS to investigate the buckling behavior of the composite cylindrical shell.The computational results and experimental results of buckling failure mode and buckling load were compared to verify the validity of the finite element model.The results show that as opening area increases,the buckling load of the shell without reinforcement does not decrease progressively.However,in a certain range of opening area,the structure gets maximum and minimum buckling load values.While in the case of reinforcement,with the opening area being constant,the buckling load is in direct proportion with opening height,and is in inverse proportion with opening width.To considering design and workmanship,opening height should be increased.
出处 《北京航空航天大学学报》 EI CAS CSCD 北大核心 2012年第7期920-924,共5页 Journal of Beijing University of Aeronautics and Astronautics
关键词 柱面壳 开口 压缩 屈曲分析 composite cylindrical shell open compression buckling analysis
  • 相关文献

参考文献11

二级参考文献54

  • 1吴德隆,郝兆平.五向编织结构复合材料的分析模型[J].宇航学报,1993,14(3):40-51. 被引量:60
  • 2KHALIFA A,NANNI A.Improving shear capacity of existing RC T-section beams using CFRP composites[J].Cement & Concrete Composites,2000,22(1):165-174.
  • 3LI J C,BAKOSSA S L,SAMALIA B,et al.Reinforcement of concrete beam or column connections with hybrid FRP sheet[J].Composite Structures,1999,47(3):805-812.
  • 4LIGNOLA G,PROTA A,MANFREDI G,et al.Non-linear modeling of RC rectangular hollow piers confined with CFRP[J].Composite Structures,2009,88(1):56-64.
  • 5ALAWI H,SALEH I E.Fatigue crack growth retardation by bonding patches[J].Engineering Facture Mechanics,1992,42(5):861-868.
  • 6SEN R,LIBY L,MULLINS G.Strengthening steel bridge sections using CFRP laminates[J].Composites Part B:Engineering,2001(2):309-322.
  • 7Hu Hsuan-Teh, Yang Jiing-Sen. Buckling optimization of laminated cylindrical panels subjected to axial compressive load[J]. Composite Structures, 2007, 81(5): 374-385.
  • 8Andrianov I V, Verbonol V M, Awrejcewicz J. Buckling analysis of discretely stringer-stiffened cylindrical shells[J]. International Journal of Mechanical Sciences, 2006, 48(12): 1505-1515.
  • 9Weaver P M, Driesen J R, Roberts P. Anisotropic effects in the compression buckling of laminated composite cylindrical shells[J]. Composites Science and Technology, 2002, 62(1): 91-105.
  • 10李 媛, 利凤祥, 李越森, 王锟, 胡春波. 复合材料壳体外压稳定性分析 //首届全国航空航天领域汇总的力学问题学术研讨会文集. 北京: 北京航空航天大学出版社, 2004: 90-93..

共引文献24

同被引文献54

  • 1赵阳,金锋.轴压作用下矩形开口圆柱壳的稳定性[J].工程设计学报,2004,11(5):249-255. 被引量:3
  • 2陈汝训.复合材料壳体的轴压稳定性[J].固体火箭技术,2001,24(1):13-15. 被引量:14
  • 3修英姝,崔德刚.复合材料层合板稳定性的铺层优化设计[J].工程力学,2005,22(6):212-216. 被引量:63
  • 4何东晓.先进复合材料在航空航天的应用综述[J].高科技纤维与应用,2006,31(2):9-11. 被引量:79
  • 5牛春匀.实用飞机复合材料结构设计与制造[M].北京:航空工业出版社,2010.
  • 6Kang J H, Kim C G. Minimum-weight design of compressively |oaded composite plates and stiffened panels for postbuckling strength by genetic a|gorithm [ J ]. Composite Structures,2005,69 (2) :239-246.
  • 7Vaziri A. On the buckling of cracked composite cylindrical shells under axial compression [ J ]. Composite Structures, 2007,80 (1):152-158.
  • 8Khoramishad H, Crocombe A D, Katnam K B, et al. Fatigue damage modelling of adhesively bonded joints under variable amplitude loading using a cohesive zone model [- J ]. Engineering Fracture Mechanics, 2011, 78: 3212-3225.
  • 9Atas A, Mohamed G F, Soutis C. Modelling delamination onset and growth in pin loaded composite laminates [J]. Composites Science and Technology, 2012, 72: 1096-1101.
  • 10Aymerieh F, Dote F, Priolo P. Prediction of impact-induced delamination in cross ply composite laminates using cohesive interface elements [J]. Composites Science and Technology, 2008, 68: 2383-2390.

引证文献7

二级引证文献40

相关作者

内容加载中请稍等...

相关机构

内容加载中请稍等...

相关主题

内容加载中请稍等...

浏览历史

内容加载中请稍等...
;
使用帮助 返回顶部