摘要
采用细观力学方法来模拟纤维增强陶瓷基复合材料层合板在准静态加载下应力-应变行为.采用层合板修正剪滞模型分析复合材料出现损伤时的细观应力场,通过临界基体应变能准则、Nair脱粘准则确定基体裂纹间隔和界面脱粘长度.最后结合剪滞模型和损伤机制模拟陶瓷基复合材料层合板应力-应变曲线,并与试验数据进行比较,结果吻合较好.
The stress-strain response of cross ply fiber reinforced ceramic composites laminates under quasi-static loading was discussed by using a micromechanical approach. The cross-ply modified shear lag model was used to analyze the micro stress field of the damage composites. The critical matrix strain energy criterion and the Nair de bond criterion were used to determine the matrix crack spacing and interface de-bonded length. At last, the ten- sile stress--strain curves were modeled by combining laminated shear lag theory and failure criterion. The results from the present analysis match well with experimental data.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2008年第10期1854-1858,共5页
Journal of Aerospace Power
基金
航空科学基金(05C52013)
973项目资助博士点基金(20070287039)
关键词
陶瓷基复合材料
层合板
剪滞理论
本构模型
ceramic matrix composites
cross ply laminate
shear lag theory
constitutive laws