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基于连续介质损伤力学方法提出了适用于针刺陶瓷基复合材料的各向异性损伤本构模型.该模型考虑了拉伸与剪切损伤的影响.通过试验得到了材料的拉伸和剪切的应力-应变曲线,采用曲线拟合获得了本构模型的参数.应用用户子程序技术将本构模型写入商用有限元软件,计算所得拉伸和剪切的应力-应变曲线与试验曲线比较吻合,最大误差分别为5.62%和1.47%.使用该损伤本构模型及弹性模型计算了航空发动机尾喷管调节片在气动和温度载荷下的力学响应,两者计算所得应力分布相似,但损伤本构模型计算值明显小于弹性模型计算值.
Based on the continuum damage mechanics method, an anisotropic damage constitutive model suitable for acupuncture of ceramic matrix composites is proposed. The model considers the effects of tensile and shear damage. The tensile and shear properties Stress-strain curve, the parameters of constitutive model were obtained by curve fitting.The constitutive model was written into the commercial finite element software by user subroutine technique, and the calculated stress-strain curves of tensile and shear were in good agreement with the experimental curves , And the maximum errors are 5.62% and 1.47% respectively.Using this damage constitutive model and the elastic model, the mechanical responses of the aeroengine tail nozzle vane under aerodynamic and temperature loads are calculated. The calculated stress distributions are similar, but the damage The calculated value of the model is obviously less than the calculated value of the elastic model.