| 疲劳裂纹扩展参数的寿命反推方法 |
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| 引用本文： | 鲍蕊,张建宇,王传胜,费斌军.疲劳裂纹扩展参数的寿命反推方法[J].航空动力学报,2005,20(2):245-249. |
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| 作者姓名： | 鲍蕊 张建宇 王传胜 费斌军 |
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| 作者单位： | 北京航空航天大学,航空科学与工程学院,北京,100083 |
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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。
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| 关 键 词： | 航空、航天推进系统 裂纹扩展 疲劳寿命 腐蚀疲劳 参数估计 |
| 文章编号： | 1000-8055(2005)02-0245-05 |
| 收稿时间： | 2004/3/13 0:00:00 |
| 修稿时间： | 2004年3月13日 |
Method for Determining Crack Growth Parameters Using Fatigue Life |
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| BAO Rui,ZHANG Jian-yu,WANG Chuan-sheng and FEI Bin-jun.Method for Determining Crack Growth Parameters Using Fatigue Life[J].Journal of Aerospace Power,2005,20(2):245-249. |
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| Authors: | BAO Rui ZHANG Jian-yu WANG Chuan-sheng and FEI Bin-jun |
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| Institution: | School of Aeronautic Secience and Technology,Beijing University of Aeronautics and Astronautics,Beijing100083,China;School of Aeronautic Secience and Technology,Beijing University of Aeronautics and Astronautics,Beijing100083,China;School of Aeronautic Secience and Technology,Beijing University of Aeronautics and Astronautics,Beijing100083,China;School of Aeronautic Secience and Technology,Beijing University of Aeronautics and Astronautics,Beijing100083,China |
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| 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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| Keywords: | aerospace propulsion system crack growth fatigue life corrosion fatigue parameter estimation |
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