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为研究不同尺度下Kevlar 49单丝(微观)和单束(细观)的拉伸力学性能,首先,分别采用MTI微型拉伸试验机和MTS微机控制电子万能试验机对纤维丝和纤维束进行了单向拉伸试验,发现纤维丝和纤维束的力学性能与试样的标距及结构尺度存在很大相关性,试样的拉伸强度会随着其标距的增加和结构尺度从纤维丝增大到纤维束而降低;随后,按照Weibull分布对试验数据进行统计分析,量化了不同标距下纤维丝和纤维束拉伸强度的随机变化程度;接着,考虑到纤维丝的拉伸强度符合Weibull分布随机破坏,利用ANSYS中的用户自定义子程序(USERMAT)建立了纤维丝本构模型;最后,采用纤维丝本构模型模拟纤维束的拉伸破坏行为,并讨论了关键参数对纤维束拉伸破坏行为的影响.结果表明:纤维束的模拟结果与试验结果吻合程度较好,所建模型可以较准确地预测纤维束的拉伸性能.

参考文献

[1] Dooraki BF;Nemes JA;Bolduc M.Study of parameters affecting the strength of yarns[J].Journal de Physique.IV,20060(0):1183-1188.
[2] 汪洋;夏源明.不同应变率下Kevlar49纤维束拉伸力学性能的实验研究[J].复合材料学报,1999(1):45-51.
[3] D. Zhu;B. Mobasher;J. Erni.Strain rate and gage length effects on tensile behavior of Kevlar 49 single yarn[J].Composites, Part A. Applied science and manufacturing,201211(11):2021-2029.
[4] V.P.W. Shim;C.T. Lim;K.J. Foo.Dynamic mechanical properties of fabric armour[J].International journal of impact engineering,20011(1):1-15.
[5] C.T. Lim;V.P.W. Shim;Y.H. Ng.Finite-element modeling of the ballistic impact of fabric armor[J].International journal of impact engineering,20031(1):13-31.
[6] H.H. Billon;D.J. Robinson.Models for the ballistic impact of fabric armour[J].International journal of impact engineering,20014(4):411-422.
[7] Ala Tabiei;Ivelin Ivanov.Computational micro-mechanical model of flexible woven fabric for finite element impact simulation[J].International Journal for Numerical Methods in Engineering,20026(6):1259-1276.
[8] Z. Stahlecker;B. Mobasher;S.D. Rajan;J.M. Pereira.Development Of Reliable Modeling Methodologies For Engine Fan Blade Out Containment Analysis. Part Ⅱ: Finite Element Analysis[J].International journal of impact engineering,20093(3):447-459.
[9] Gaurav Nilakantan.Filament-level modeling of Kevlar KM2 yarns for ballistic impact studies[J].Composite structures,2013Oct.(Oct.):1-13.
[10] R. Jiang.A drawback and an improvement of the classical Weibull probability plot[J].Reliability engineering & system safety,2014Jun.(Jun.):135-142.
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