航空学报 > 2003, Vol. 24 Issue (2): 144-146

2024-T42铝合金疲劳裂纹扩展曲线的拟合方法研究

田秀云, 孙智强   

  1. 中国民航学院机电学院 天津 300300
  • 收稿日期:2002-04-04 修回日期:2002-06-06 出版日期:2003-04-25 发布日期:2003-04-25

Curve Fitting Study on 2024-T42 Aluminium-Alloy Fatigue Crack G rowth

TIAN Xiu-yun, SUN Zhi-qiang   

  1. College of Mechanical & Electrical Engineering; CAIC; Tianjin 300 300; China
  • Received:2002-04-04 Revised:2002-06-06 Online:2003-04-25 Published:2003-04-25

摘要: 提出了一种疲劳裂纹扩展曲线( a-N 曲线) 的新拟合方法,并采用这种新的拟合方法对2024-T42 铝合金CCT 试样的疲劳裂纹扩展数据进行了拟合分析。通过疲劳裂纹扩展寿命计算结果和试验结果的对比分析,证明这种新的裂纹扩展曲线拟合方法具有较高拟合精度。经过实验和计算分析,还给出了2024-T42 铝合金的疲劳裂纹扩展速率材料常数c 和n 值。

关键词: 疲劳裂纹扩展速率, 疲劳裂纹扩展寿命, 曲线拟合, 铝合金

Abstract: A curve fitting method on the fatigue crack growth is developed. Adopting this method,this paper provides the fatigue crack growth data curve fitting analysis of 2024-T42 aluminum alloy CCT specimens.By comparingthe experimental result with calculated results on fatigue crack growth life,it is proved that this new curve fitting hashigher precision. Analyzing experimental and calculated results, this paper provides the fatigue crack growth rateconstants c, n.

Key words: fatigue crack growth rate, fatigue crack growth life, curve fitting, aluminum alloy

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