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发展了文献[1]中提出的变形模型,研究了短纤维增强金属基复合材料热残留应力的分布及其对拉伸和压缩载荷下应力分布的影响.研究表明,在拉伸和压缩载荷下,热残留应力可导致不对称的应力分布和基体塑性,热残留应力降低拉伸时的应力传递,加强压缩时的应力传递.

参考文献

[1] 连建设, 江中浩, 杨德庄,等. 短纤维增强金属基复合材料应力分布的剪切滞后分析[J]. 复合材料学报,1999,16(4):94.
[2] Arsenault R J, Taya M. Thermal residual stress in metal matrix composites [J]. Acta metall, 1987, 35: 651.
[3] Withers P J, Stobbs W M, Pedersen O B. The application of the Eshelby method of internal stress determination to short fiber metal matrix composites [J]. Acta metall, 1989, 37: 3061.
[4] Arsenault R J, Wu S B. The strength difference and Bauschinger effects in SiC-Al composites[J]. Mater Sci Engng, 1987, A96: 77.
[5] Povirk G L, Needleman A, Nutt S R. An analysis of residual stress and deformation and damage mechanisms in Al-SiC composites [J]. Mater Sci Engng, 1991, A132: 31.
[6] Levy A, Papaziam J M. Elastic plastic finite element analysis of short-fiber-reinforced SiC/Al composites: effects of thermal treatment [J]. Acta metall mater, 1991, 39: 2255.
[7] Shi N, Wilner B, Arsenault R J. A FEM study of the plastic deformation process of whisker reinforced SiC/Al composites [J]. Acta metall mater, 1992, 40: 2841.
[8] Dutta I, Sims J D, Seigenhaler D M. An analytical study of residual stress effects on uni-axial deformation [J]. Acta metall mater, 1993, 41: 885.
[9] Shen Y L, Finot M, Needleman M, et al. Effective elastic response of two-phase composites [J]. Acta metall mater, 1994, 42: 77.
[10] Daymond M R, Withers P J. Examination of tensile/compressive loading asymmetries in aluminum based metal matrix composites using finite element method [J]. Mater Sci Tech, 1995, 11: 228.
[11] Shi N, Arsenault R J, Karwitz A D, et al. Deformation-induced residual stress changes SiC whisker-reinforced 6061 Al composites [J]. Metall Trans A, 1993, 24: 187.
[12] Nardone V C, Prewo K M. On the strength of short-fiber composites with variables fiber length and orientation [J]. Scripta metall, 1986, 20: 43.
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