铝合金板预腐蚀坑萌生疲劳裂纹的几何构型
Geometry of Pre-corrosion Pit-induced Fatigue Crack on Aluminum Alloy Panel
摘 要
由于腐蚀坑不同位置的应力状态的差异,由腐蚀坑萌生的裂纹扩展行为仅仅用应力强度因子分析无法得到准确预测。考虑裂纹闭合效应的存在,本工作对于这种裂纹的应力场进行了分析,研究了其几何尺寸在裂纹扩展过程中的变化,理论分析表明这种几何形状的变化与材料形状以及应力范围的大小关系不大。对于裂纹扩展的几何形状变化的验证性试验的试验结果与理论分析的结果吻合程度良好。
断裂力学
疲劳裂纹扩展
corrosion pit induced crack
fracture mechanics
fatigue crack growth
Abstract
Corrosion pit induced fatigue crack propagation can not be adequately predicted solely by stress-intensity factor (SIF) analysis,due to variation in the stress field along the pit border. Analysis of surface pit-induced cracks was performed considering the variation in stress field using the concept of crack closure. Changes in geometric parameters describing the pit-induced crack were studied. It was shown that the geometry variation of pit-induced crack was independent of stress range and material properties. Experiments were performed to assess the accuracy of the analysis,which yielded excellent results.
中图分类号 TG174
所属栏目 失效分析
基金项目 国家自然科学基金(1072124)
收稿日期 2014/3/3
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备注李旭东(1984-),讲师,硕士,从事金属的腐蚀疲劳研究,13793269197.
引用该论文: LI Xu-dong,MU Zhi-tao,KONG Guang-ming. Geometry of Pre-corrosion Pit-induced Fatigue Crack on Aluminum Alloy Panel[J]. Corrosion & Protection, 2015, 36(1): 72
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参考文献
【1】李旭东,刘治国,穆志韬,等. 基于飞行载荷的LC9铝合金腐蚀疲劳裂纹扩展研究[J].腐蚀与防护,2013,34(11):985-988.
【2】李旭东,刘治国,穆志韬. 基于短裂纹的LD10CZ铝合金腐蚀预疲劳裂纹扩展[J].海军航空工程学院学报,2013,28(1):47-52.
【3】WEI R P,HARLOW D G. Corrosion and corrosion fatigue of aluminium alloys-an aging aircraft issue[C]//Proceedings of the Seventh International Fatigue Congress,Houston:[s.l.],1999:2197-2204.
【4】李旭东,穆志韬,刘治国. 应力比对航空高强度铝合金腐蚀疲劳裂纹扩展的影响[J].理化检验-物理分册,2012,49(12):781-784.
【5】NWEMAN J C,RAJU IS. An empirical stress-intensity factor equation for the surface crack[J].Engineering Fracture Mechanics,1981,15(5):185-192.
【6】ASTM STP 486-1971Damage tolerance in aircraft structures[S].
【2】李旭东,刘治国,穆志韬. 基于短裂纹的LD10CZ铝合金腐蚀预疲劳裂纹扩展[J].海军航空工程学院学报,2013,28(1):47-52.
【3】WEI R P,HARLOW D G. Corrosion and corrosion fatigue of aluminium alloys-an aging aircraft issue[C]//Proceedings of the Seventh International Fatigue Congress,Houston:[s.l.],1999:2197-2204.
【4】李旭东,穆志韬,刘治国. 应力比对航空高强度铝合金腐蚀疲劳裂纹扩展的影响[J].理化检验-物理分册,2012,49(12):781-784.
【5】NWEMAN J C,RAJU IS. An empirical stress-intensity factor equation for the surface crack[J].Engineering Fracture Mechanics,1981,15(5):185-192.
【6】ASTM STP 486-1971Damage tolerance in aircraft structures[S].
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