FATIGUE-CRACK GROWTH-RETARDATION ASSESSMENT OF 2024-T3 AND 6061-T6 ALUMINUM SPECIMENS

被引:21
作者
PANTELAKIS, SG
KERMANIDIS, TB
PAVLOU, DG
机构
[1] Laboratory of Technology and Strength of Materials, Mechanical Engineering Dept., University of Patras
关键词
D O I
10.1016/0167-8442(94)00046-4
中图分类号
TH [机械、仪表工业];
学科分类号
0802 ;
摘要
A fatigue crack growth retardation model is developed. It considers a strip plastic zone with material hardening effect which is taken as one of the basic mechanisms controlling fatigue crack growth. Crack growth is treated incrementally and corresponds to the failure of material elements ahead of an existing crack after a certain critical number of low cycle fatigue. Computed curves are correlated to test data obtained from the 2024-T3 and 6061-T6 aluminium specimens. Deviations from test data increase with increasing crack length.
引用
收藏
页码:35 / 42
页数:8
相关论文
共 31 条
[1]  
ALIAGA D, 1988, ASTM STP, V982, P491
[2]  
[Anonymous], 1966, ASTM SPEC TECH PUBL
[3]  
BLOM AF, 1990, 4TH P INT C FAT FAT, V1, P13
[4]   PREDICTION OF FATIGUE CRACK GROWTH UNDER FLIGHT-BY-FLIGHT LOADING [J].
BROEK, D ;
SMITH, SH .
ENGINEERING FRACTURE MECHANICS, 1979, 11 (01) :123-141
[5]   A NEW DAMAGE VARIABLE FOR LOW-CYCLE FATIGUE OF METALLIC MATERIALS [J].
CHENG, GX ;
LOU, ZW ;
KUANG, ZB .
ENGINEERING FRACTURE MECHANICS, 1994, 48 (02) :281-287
[6]  
COFFIN LF, 1962, ASME, V84, P533
[7]  
De Koning A., 1981, ASTM STP
[8]  
Elber W., 1971, SIGNIFICANCE FATIGUE, V486, P230
[9]  
Fuchs HO., 1980, METAL FATIGUE ENG, V103, P346
[10]  
Ghosh S.K., 1981, ASTM STP, P85, DOI DOI 10.1520/E0748-02R08