摘要
基于国产碳纤维复合材料含孔层合板失效模式和损伤机理研究,结合试验分析建立了符合其失效机理的有限元模型,并在有限元模型中研究了不同失效准则对剩余强度计算结果的影响,通过比较试验数据与数值模拟结果表明:二维模型能比较准确地预测国产碳纤维复合材料含孔层合板的剩余强度,破坏载荷的数值模拟与试验数据的相对误差为7.9%,而拉伸模量的相对误差为5.6%.
Based on the research of the failure mode and damage mechanism of the not- ched domestic carbon fiber composite laminates and the experimental analysis, finite element models were established. Then the effect of different failure criterias on the residual strength of notcked domestic carbor fiber composite laminates was studied in the corresponding finite element model. Through the comparison between experimental data and simulation results, it was found that the two-dimensional model could predict the residual strength of the not- ched domestic carbon fiber composite laminates accurately, the relative error between numer- ical simulation result and experimental data of failure load was 7.9%, while the relative er- ror of tensile modulus was 5.6 %.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2015年第12期2857-2862,共6页
Journal of Aerospace Power
基金
国家自然科学基金(11501022)
北京市自然科学基金(3154034)
关键词
复合材料层合板
拉伸试验
渐进失效分析
有限元法
剩余强度
composite laminates l tension experiment
progressive failure analysis^finite element method
residual strength
