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冷胀孔裂纹寿命增长效果估算模型 被引量:1

MODEL FOR PREDICTING EFFECT OF HOLE COLD EXPANDING ON INCREASING CRACK LIFE
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摘要 本文用含孔边穿透裂纹的冷胀孔、未胀孔剩余寿命之比来评价孔冷胀强化工艺延长裂纹扩展寿命的效果。本文提出把理论计算方法与实验测试结果相结合来确定残余应力场:根据实验测量结果确定冷胀孔塑性区半径:把塑性区半径代入残余应力场的理论计算式中求出残余应力场初形;根据最大残余应力值与材料屈服应力之间的规律关系(由冷胀孔残余应力测试结果得出的)修正已计算出的残余应力场。本文用冷胀孔单边穿透裂纹在等幅循环载荷作用下的裂纹扩展寿命试验结果检验了所提出的模型,此估算模型可较保守而又较充分反映孔冷胀强化工艺对孔边裂纹的增寿作用。 The assessment of the increase of crack growth life after hole cold expanding is addressed. Tangential residual stress distribution around cold expanded hole is determined by combining theoretical calculation with experiment results. Radius of plastical zone is determined on the base of experimental results. Theoretical results of residual stress is modified with the relation between the largest residual stress and yield stress collected from measurement results of residual stress field. The method is examined with fatigue test results of cold expanded hole under constant amplitude spectrum.
出处 《工程力学》 EI CSCD 1996年第3期27-32,共6页 Engineering Mechanics
关键词 冷胀孔 残余应力 裂纹扩展寿命 飞机紧固件 cold expanded hole, resuluai stress, crack growth life
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  • 1袁发荣,残余应力测试与计算,1987年
  • 2Chang J B,J Aircraft,1977年,14卷,9期,903页

共引文献17

同被引文献3

  • 1Ball D L,Lowry D R.Experimental investigation on the effects of cold expansion of fastener holes[J].Fatigue and Fracture of Engineering Materials and Structures,1998,17:17-34.
  • 2Ghfiri R,Amrouche A,Imad A,et al.Fatigue life estimation after crack repair in 6005 A-T6 aluminum alloy using the cold expansion hole technique[J].Fatigue and Fracture of Engineering Materials and Structures,2000,23:911-916.
  • 3李亚智,傅祥炯.压缩载荷对冷胀孔残余应力的影响[J].机械科学与技术,1999,18(1):71-72. 被引量:1

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