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涡扇发动机涡轮后框架结构/材料一体化优化设计方法
  • ISSN号:1000-8055
  • 期刊名称:航空动力学报
  • 时间:2013.10.10
  • 页码:2174-2180
  • 分类:V2[航空宇航科学技术]
  • 作者机构:[1]College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing, 210016, P. R. China
  • 相关基金:Supported by the National Natural Science Foundation of China (51075204,51105195) ; the Aeronau- tical Science Foundation of China (2011ZB52024).
  • 相关项目:纤维增强陶瓷基复合材料结构宏细观结合的疲劳寿命预测方法研究
中文摘要:

The non-linear behavior of continuous fiber reinforced C/SiC ceramic matrix composites(CMCs)under tensile loading is modeled by three-dimensional representative volume element(RVE)models of the composite. The theoretical background of the multi-scale approach solved by the finite element method(FEM)is recalled firstly.Then the geometric characters of three kinds of damage mechanisms,i.e.micro matrix cracks,fiber/matrix interface debonding and fiber fracture,are studied.Three kinds of RVE are proposed to model the microstructure of C/SiC with above damage mechanisms respectively.The matrix cracking is modeled by critical matrix strain energy(CMSE)principle while a maximum shear stress criterion is used for modeling fiber/matrix interface debonding. The behavior of fiber fracture is modeled by the famous Weibull statistic theory.A numerical example of continuous fiber reinforced C/SiC composite under tensile loading is performed.The results show that the stress/strain curve predicted by the developed model agrees with experimental data.

英文摘要:

The non-linear behavior of continuous fiber reinforced C/SiC ceramic matrix composites (CMCs) under tensile loading is modeled by three-dimensional representative volume element (RVE) models of the composite. The theoretical background of the multi-scale approach solved by the finite element method (FEM) is recalled first- ly. Then the geometric characters of three kinds of damage mechanisms, i.e. micro matrix cracks, fiber/matrix interface debonding and fiber fracture, are studied. Three kinds of RVE are proposed to model the microstructure of C/SiC with above damage mechanisms respectively. The matrix cracking is modeled by critical matrix strain en- ergy (CMSE) principle while a maximum shear stress criterion is used for modeling fiber/matrix interface debond- ing. The behavior of fiber fracture is modeled by the famous Weibull statistic theory. A numerical example of con- tinuous fiber reinforced C/SiC composite under tensile loading is performed. The results show that the stress/ strain curve predicted by the developed model agrees with experimental data.

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期刊信息
  • 《航空动力学报》
  • 北大核心期刊(2011版)
  • 主管单位:中国科协
  • 主办单位:中国航空学会
  • 主编:陶智
  • 地址:北京市海淀区学院路37号
  • 邮编:100191
  • 邮箱:JAP@buaa.edu.cn
  • 电话:010-82317410
  • 国际标准刊号:ISSN:1000-8055
  • 国内统一刊号:ISSN:11-2297/V
  • 邮发代号:
  • 获奖情况:
  • 国内外数据库收录:
  • 俄罗斯文摘杂志,美国化学文摘(网络版),波兰哥白尼索引,荷兰文摘与引文数据库,美国工程索引,美国剑桥科学文摘,英国科学文摘数据库,日本日本科学技术振兴机构数据库,中国中国科技核心期刊,中国北大核心期刊(2004版),中国北大核心期刊(2008版),中国北大核心期刊(2011版),中国北大核心期刊(2014版),中国北大核心期刊(2000版)
  • 被引量:13986