摘要
针对挤压强化件裂纹形成寿命的特点，用孔的原始疲劳质量表征挤压工艺状态，用当量初始缺陷尺寸分布表征挤压工艺的分散性，裂纹扩展采用ｂ＝ １的确定性裂纹扩展模型，从而建立了一套适用于冷挤压强化件的耐久性分析方法。
According to the characteristic of crack initiation life in cold extrusion strengthening specimen, the strengthening appearance is described by the Initial Fatigue Quality, and the technical scatter of cold extrusion is described by the Equivalent Initial Flaw Size distribution. For crack propagation the deterministic crack growth rate model of b =1 is applied. So a new durability analysis method is established for cold extrusion strengthening specimen.
出处
《机械强度》
CAS
CSCD
北大核心
1999年第4期296-298,共3页
Journal of Mechanical Strength
关键词
冷挤压强化件
原始疲劳质量
耐久性分析
飞机
cold extrusion, initial fatigue quality, equivalent initial flaw size, time to crack initiation
