期刊
ENGINEERING FRACTURE MECHANICS
卷 194, 期 -, 页码 262-280出版社
PERGAMON-ELSEVIER SCIENCE LTD
DOI: 10.1016/j.engfracmech.2018.03.020
关键词
Aluminum lithium alloy; Crack propagation; Stress intensity factor; Residual fatigue life
类别
资金
- National Natural Science Foundation of China [51575535]
- Project of Innovation-driven Plan in Central South University [2015CX002]
- Science and Technology Planning Project of Hunan Province, China [2016RS2015]
A method for residual-fatigue-life estimation of repaired aluminium-lithium alloy structures designed for use in aerospace applications is presented. Crack propagation was investigated using the Abaqus software package while the stress intensity factor was calculated using the FRANC3D package. Paris equation was applied to estimate the fatigue-crack growth rate. The residual fatigue life of and corresponding a-N curve for the repaired structure were obtained via post-processing under varying conditions of repair-structure shape, size, position, and stress levels. Results demonstrate that structural repairs possessing relative width, height, and thickness values of 35.7%, 50%, and 83.3%, respectively, tend to increase the residual fatigue life of the overall structure.
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