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干涉配合紧固件的疲劳裂纹扩展寿命分析 被引量:2

AN ANALYSIS OF THE CRACK PROPAGATION LIFE OF THE INTERFERENCE-FITTED FASTENER
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摘要 利用权函数法给出了含紧固件孔的平板受干涉、双向拉压、各种形式的分布钉载和旁路载荷各种方式的组合作用时孔边穿透裂纹和角裂纹的张开型应力强度因子的数学表达式,可以方便地实施快速积分法求得裂纹扩展寿命。分析了干涉销钉通过填充作用和与孔壁的摩擦对疲劳裂纹扩展寿命的影响。发现钉载及双向载荷条件的不同,干涉增寿效果不同。与实验结果的对比表明方法是有效的。 A method was presented for obtaining stress intensity factors (SIFs) for both through and corner cracks emanating from interference-fitted fastener holes in finite plates subjected to biaxial loading and pin-loading. The SIFs are presented as mathematical formnlas instead of integration, and have the same accuracy as in the case of open and pin-loaded holes. For corner cracks the SIFs are obtained by introducing a geometrical modfication factor. The results are in good agreement with the published results for corner cracks from holes in finite plates subjectei to uniaxial loading when d/B<1.The paper made a further detailed analysis for the effects of different combinations of pin-load, biaxial stress and interference. Some interesting conclusions have been drawn from the analysis: The life of a fastener is sensitive to pin-loading and its distribution, biaxial loadiag, crack shape and interference condition, espicially to the slip condition at the bolt-plate interface.
机构地区 西北工业大学
出处 《航空学报》 EI CAS CSCD 北大核心 1991年第2期B106-B111,共6页 Acta Aeronautica et Astronautica Sinica
关键词 干涉配合 紧固件 孔边裂纹 疲劳 interference-fitted fastener, crack at holes, SIF, fatigue propagation life of crack.
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参考文献2

  • 1郭万林,1990年
  • 2郭万林,西北工业大学学报,1987年,5卷,1期,129页

同被引文献31

  • 1肖寿庭,傅祥炯,刘一兵.随机载荷作用下锥形螺栓干涉配合的疲劳寿命增益[J].航空学报,1993,14(3). 被引量:3
  • 2何世平,关锷,束永生,伍小平.应用干涉云纹测量工艺应力分布[J].力学学报,1993,25(4):485-491. 被引量:9
  • 3中国航空科学技术研究院编著.飞机结构抗疲劳断裂强化工艺手册[M].北京,航空工业出版社,1993.110.
  • 4McCarthy M A, McCarthy C T, Lawlor V P, et al. Three-dimensional finite element analysis of single-bolt, single-lap composite bolted joints: part 1 -model develop ment and validation[J]. Composite Structures, 2005, 71 (2) : 140-158.
  • 5Crews Jr J H. Analytical and experimental investigation of fatigue in a sheet specimen with an interference-fit bolt, NASA TN D-7926 [R]. Washington D. C. : National Aeronautics and Space Administration, 1975.
  • 6Wang S P, Li Y J, Yao M, et al. Compressive residual stress introduced by shot peening[J]. Journal of Materials Processing Technology, 1998, 73(1-3) : 64-73.
  • 7Landy M A, Armen J H, Eidnoff H L. Enhanced stop- drill repair procedure for cracked structures[J]. Fatigue in Mechanically Fastened Composite and Metal Joints, 1986, 927: 190.
  • 8Papanikosal P, Meguid S A. Three-dimensional finite ele ment analysis of cold expansion of adjacent holes[J]. In- ternational Journal of Mechanical Sciences, 1998, 40 (10) : 1019-1028.
  • 9Champoux R L, Landy M A. Fatigue life enhancement and high interference bushing installation using the Force- Mate bushing installation technique[J]. Special Technical Publication no American Society Testing Materials, 1986, 927:39-52.
  • 10Chakherlou T N, Mirzajanzadeha M, Vogwell J. Experi- mental and numerical investigations into the effect of an interference fit on the fatigue life of double shear lap joints [J]. Engineering Failure Analysis, 2009, 16 (7) : 2066- 2080.

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