航空学报 > 1987, Vol. 8 Issue (2): 33-38

受拉螺栓和耳片的疲劳寿命估算

薜景川, 贺恭泰, 杨玉恭   

  1. 飞机强度研究所
  • 收稿日期:1985-11-17 修回日期:1900-01-01 出版日期:1987-02-25 发布日期:1987-02-25

PREDICTION OF FATIGUE LIFE FOR TENSION BOLTS AND LUGS

Xue Jingchuan, He Gongtai, Yang Yugong   

  1. Aircraft Strength Research Institute
  • Received:1985-11-17 Revised:1900-01-01 Online:1987-02-25 Published:1987-02-25

摘要: 本文介绍了一种估算结构疲劳寿命的新途径:在结构名义应力谱、应力严重系数/知名义应力等寿命图已知时,把结构件的名义应力等寿命图转换成真实应力等寿命图,用计算出的真实应力、应变查该等寿命图来估算出结构的寿命,或者把用诺伯法确定出的局部应力、应变历程转换成当量名义应力水平后查结构名义应力等寿命图来估算结构的疲劳寿命。这样,同时运用了名义摩力法和局部应力、应变法的优点,使寿命计算更合理。

Abstract: A new structural fatigue life prediction method is presented in this paper.Nominal stress spectrum, stress severity factors and constant life curves according to nominal stress for a structure are known. The curves can be changed into the structural constant life plots of local stress(strain) , then the structural life is estimated in accor-dence with calculated local stress-strain histories and the plots. Still calculated local stress-strain histories can be changed into nominal stress histories, then the structural life is estimated, by means of the structural constant life curves according to nominal stress.The method has the advantage of nominal stress method and local strain method to counteract themselves weakness.