欢迎登录材料期刊网

材料期刊网

高级检索

采用ANSYS/LS-DYNA有限元软件对碳纤维/环氧树脂复合材料薄壁圆筒的低速横向冲击进行模拟,运用大变形损伤本构方程和冲击动力学方程对其进行动态响应分析.采用接触力历程、内能历程和位移历程研究了冲击速度、边界条件和铺层顺序对圆筒动态响应的影响,并评价了不同冲击状态下薄壁圆筒的抗冲击性.结果表明,[553/-553/55/-55/0/90]圆筒试样的抗冲击性与其它铺层顺序试样相比较好.

参考文献

[1] K.S. Krishnamurthy;P. Mahajan;R.K. Mittal .Impact response and damage in laminated composite cylindrical shells[J].Composite Structures,2003(1):15-36.
[2] Kaneko T;Sato K;Ujihashi S et al.Finite-element failure analysis of carbon fiber-reinforced plastic cylinders under transverse impact loading[J].Mater:Des Appl,2007,221(02):103.
[3] Gning P B;Tarfaoui M;Collombet F et al.Damage development in thick composite tubes under impact loading and infiuence on implosion pressure:Experimental observations[J].Composites Part B:Engineering,2005,36(04):306.
[4] M. Tarfaoui;P.B. Gning;L. Hamitouche .Dynamic response and damage modeling of glass/epoxy tubular structures: Numerical investigation[J].Composites. Part A, Applied science and manufacturing,2008(1):1-12.
[5] 万志敏,杜星文,谢志民.玻璃/环氧圆柱壳的冲击响应与稳定性分析[J].复合材料学报,2001(04):82-86.
[6] 钟卫洲,宋顺成,张青平,黄西成,陈刚.碳纤维复合材料圆筒结构抗压性能研究[J].工程力学,2009(12):105-111.
[7] 沃丁柱.复合材料大全[M].北京:化学工业出版社,2000:508.
[8] R. Tiberkak;M. Bachene;S. Rechak;B. Necib .Damage prediction in composite plates subjected to low velocity impact[J].Composite structures,2008(1):73-82.
[9] Tan T M;Sun C T .Use of statical indentation laws in the impact analysis of laminated composite plates[J].Journal of Applied Mechanics,Transactions of the ASME,1985,52(01):6.
[10] Chandrashekara K;Schroeder T .Nonlinear impact analysis of laminated cylindrical and doubly curved shells[J].Journal of Composite Materials,1995,29:2160.
[11] Abrate S.Impact on composite structures[M].Cambridge (England):Cambridge University Press,1998
[12] J.P.Hou;N.Petrinic;C.Ruiz;S.R.Hallett .Prediction of Impact Damage in Composite Plates[J].Composites science and technology,2000(2):273-281.
[13] Moaveni Saeed;王崧;刘丽娟;董春敏.有限元分析-ANSYS理论与应用[M].北京:电子工业出版社,2008:572.
上一张 下一张
上一张 下一张
计量
  • 下载量()
  • 访问量()
文章评分
  • 您的评分:
  • 1
    0%
  • 2
    0%
  • 3
    0%
  • 4
    0%
  • 5
    0%