LD10CS腐蚀疲劳裂纹扩展速率评价的可靠性模型  

Reliability Model of Corrosion Fatigue Crack Growth Rate Evaluation of LD10CS Aluminum Alloy

作　　者：贾明明[1] 李旭东[1] 吕航[1] 

机构地区：[1]海军航空工程学院青岛校区,山东青岛266041

出　　处：《新技术新工艺》2014年第12期122-124,共3页New Technology & New Process

摘　　要：腐蚀损伤会加速疲劳载荷下的飞机铝合金结构裂纹的萌生和扩展,威胁结构安全性。针对腐蚀影响下的疲劳裂纹扩展的随机性本质,对预腐蚀LD10CS合金的预腐蚀疲劳试验进行了数据分析,提出了基于可靠性的腐蚀裂纹扩展速率表征方法,与试验结果对比表明,该方法可以给出LD10CS腐蚀疲劳裂纹扩展速率的上下限,进而给出该种材料铝合金构件的疲劳裂纹扩展寿命的上下限,为评估铝合金构件的寿命提供了依据。Fatigue loadings and environmental corrosion damage can decrease the mechanical properties of LD10 CS aluminum alloy.The paper made a research on the fatigue crack growth rate（FCG）of AA LD10 CS with corrosion damage,and proposed a reliability-based method to evaluate FCG.Compare of predicted FCG and experimental results indicated that the proposed method was able to give the lower and upper limit of FCG of LD10 CS with corrosion damage,which provided the basis of aluminum alloy component safe life prediction.

关 键 词：铝合金 腐蚀 可靠性 疲劳裂纹扩展速率 

分 类 号：TG171[金属学及工艺—金属表面处理] V252[金属学及工艺—金属学]