疲劳裂纹扩展参数的寿命反推方法
Method for Determining Crack Growth Parameters Using Fatigue Life
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摘要: 为解决腐蚀疲劳条件下无法由断口判读获得(a,N)数据集以确定裂纹扩展公式参数的问题,提出了确定疲劳裂纹扩展参数的寿命反推方法。通过与用(a,N)数据集全部数据拟合结果的比较,证明该方法在指数b=1的情况下适用,而在b≠1时偏差较大;指定破坏概率的载荷循环数和裂纹长度的比较结果,说明该方法的结果可用于概率损伤容限分析。Abstract: Since the (a,N) databank can not be easily obtained in corrosion fatigue,the method for determine the parameters of crack growth parameters in terms of fatigue life is presented.Via results comparison,the method shows its good capability under the general condition of b=1.The small relative error of the estimation of crack length and number of load cycles for given damage probability proves that the method given in this paper can be used in probability damage tolerance analysis.
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Key words:
- aerospace propulsion system /
- crack growth /
- fatigue life /
- corrosion fatigue /
- parameter estimation
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