New Engineering Model Validity Study of Fatigue Crack Growth Rate Affected by the Compressive Loading in LY12M Aluminum Alloy
To improve the fatigue performance of metal materials which are applied in the aeroplane structure is a significant objective of new material research.In recent decades,it becomes a common view that compressive loading in the tension-compression fatigue spectrum can accelerate the fatigue crack growth rate of the aluminum alloy.It is dangerous in the fatigue crack growth life prediction as a result of neglect of the effect of compressive stress,as provided in the former fatigue test standards.In the actual crack growth fitting formulas of aircraft design company,which have taken compressive stress acceleration effect into consideration,generally,there are several materials parameters should be determinate by a large number of test.It has been found that for a tension-compression stress cycle the crack tip parameters are determined mainly by two loading parameters,the maximum stress intensity Kmax in the tension part of the stress cycle and the maximum compressive stress maxcom in the compression part of the stress cycle.
Elastic-plastic finite element fatigue crack growth compressive loading crack tip
Xin Song Li Hongping Jun Pengshao Jia Zhenzhang
eronautical Science and Technology Research Institute of COMAC, Beijing, China 100083 chool of Mecha Shanghai Aircraft Design and Research Institute of COMAC, Shanghai, China 200232 chool of Mechanical and Power Engineering, Harbin University of Science and Technology, Harbin, Chin eronautical Science and Technology Research Institute of COMAC, Beijing, China 100083; Composite Res
国际会议
上海
英文
30-30
2012-10-19（万方平台首次上网日期，不代表论文的发表时间）