航空铝合金薄板在循环拉伸载荷下孔洞聚合的试验研究  

Experimental Investigation for an Aluminum-Alloy Strip with Two Holes under Cyclic Tensile Loading

作　　者：王芳文[1] 左宏[1] 李群[1] 文毅[1] 

机构地区：[1]西安交通大学航天航空学院强度与振动国家重点实验室,陕西西安710049

出　　处：《凿岩机械气动工具》2013年第3期11-15,共5页Rock Drilling Machinery & Pneumatic Tools

基　　金：国家自然科学基金重点项目(10932007);陕西省自然科学基础研究计划项目(2013JM1013)资助

摘　　要：通过试验发现循环拉伸载荷下含两孔洞的铝合金长条,由于两孔洞的方位不同,至少有七种疲劳裂纹引起的破坏型式。在七种不同的破坏情况下,疲劳裂纹初始寿命和疲劳裂纹扩展寿命均不同,必须分阶段评估,这也直接影响到整体疲劳寿命的预计;此时常规的、经典的疲劳裂纹扩展理论难以直接应用。This note reports seven failure styles found in our experimental investigation for the failure between two neighborly holes located at different angle in an Aluminum-Alloy strip under cycle tensile loadings. The fatigue crack initiation life and the fatigue crack propagation life are quite different in every failure style. It becomes necessary to e- valuate the initiation life and the fatigue crack propagation life in the different stage ,which mainly affect the calcula- tion of total fatigue crack life., while the classical theories of fatigue fracture can not be employed directly.

关 键 词：铝合金 循环拉伸载荷 疲劳裂纹初始寿命 疲劳裂纹扩展寿命 破坏型式 

分 类 号：O346.4[理学—固体力学]