航空学报 > 1985, Vol. 6 Issue (2): 194-200

裂纹扩展寿命的类比计算法

张福泽   

  1. 空军研究所
  • 收稿日期:1982-08-09 修回日期:1900-01-01 出版日期:1985-04-25 发布日期:1985-04-25

AN ANALOGUE METHOD FOR CRACK PROPAGATION LIFE PREDICTION

Zhang Fuze   

  1. Air Force Research Institute
  • Received:1982-08-09 Revised:1900-01-01 Online:1985-04-25 Published:1985-04-25

摘要: 本文是本刊1982年第3卷第2期发表的“裂纹形成寿命的类比计算法”的后续篇。介绍一种机械设备零部件在裂纹扩展阶段寿命的类比计算法。用己知寿命的零部件类比计算出未知寿命零部件的寿命,它是建立在试验(或使用)基础上的,通过类比方法可以减少Miner公式中难以确定的常数值Q的影响,从而提高寿命计算的准确性和可靠性。

Abstract: A method for crack propagation life prediction of aircraft components is proposed which employs the life of a given component tested under spectrum load to predict the life of another untested one of same type by analogy.The lives of specimens under five different loading conditions are predicted by this analogue method. The results are quite consistent with the fatigue test results (see table 1 ).