摘要
为研究芯棒挤压和开口衬套挤压工艺的疲劳增寿效益,以及应力水平高低对增寿效益的影响,针对飞机结构中常用的铝合金和钛合金,设计孔表面状态分别为未挤压、芯棒挤压和开口衬套挤压的含孔细节模拟试件。通过模拟试件等幅谱下疲劳试验,获得裂纹形成、扩展和总寿命,通过对试验数据的统计对比分析,对芯棒挤压和开口衬套挤压工艺的疲劳增寿效益进行对比,研究应力水平高低对疲劳增寿效益的影响,分析在裂纹形成和扩展阶段的疲劳寿命增益。
Experimental research has been carried out to study the fatigue life enhancing effect of direct mandrel cold-expansion and split sleeve cold-expansion processes,and effect of the stress level.Adopting the widely used aluminum and titanium alloys in aircraft structure three kinds of specimens were designed,i.e.,the surfaces of the specimen s holes were of 3 different conditions including non-expanded(NE),direct mandrel cold-expanded(DMCE) and split sleeve cold-expanded(SSCE).The crack initiation,crack propag...
出处
《机械强度》
CAS
CSCD
北大核心
2010年第3期446-450,共5页
Journal of Mechanical Strength
关键词
冷挤压强化
疲劳寿命
芯棒挤压
开口衬套挤压
Cold-expansion hardening
Fatigue life
Direct mandrel cold-expansion
Split sleeve cold-expansion
