Fatigue crack growth test for cracked metallic plate of LY12CZ aluminum alloy repaired with adhesive bonding Carbon/epoxy composite patch is conducted to validate the crack growth behaviour of crack patching.The main fatigue failure modes observed in the test are crack growth and adhesive debonding.The crack length and debonding area are measured with different numbers of cycles.The nonlinear 3D finite element model considering adhesive debonding and crack growth are developed.The experimental and analytical results are in good agreement with each other.
SU Wei-guo, MU Zhi-tao, WANG Shuo
. Research on crack growth behavior of blade-body juncture horseshoe vortex[J]. Journal of Shenyang Aerospace University, 2014
, 31(1)
: 37
-40
.
DOI: 10.3969/j.issn.2095-1248.2014.01.009
[1]Baker A A.Repair of cracked or defective metallic aircraft components with advanced fibre composites[J].Composite Structure, 1984, 2(2):153-234.
[2]Jones R, Callian R J, Aggarwal K C.Analysis of bonded repair to damaged fiber composite structures[J].Engineering Fracture Mechanics, 1983, 17(1):37-46.
[3]徐建新.复合材料补片胶接修理技术的研究进展[J].航空学报, 1999(4):381-383.
[4]徐建新, 张开达.复合材料补片止裂性能的方法研究[J].工程力学, 1999, 16(2):93-98.
[5]王清远, 陶华.复合材料修补件的强度和疲劳性能[J].材料工程, 2003(1):21-24.
[6]Jones R, Callian R J, Aggarwal K C.Analysis of bonded repair to damaged fiber composite structures[J].Engineering Fracture Mechanics, 1983, 17(1):37-46.
[7]Sun C T, Klug J, Arendt C.Analysis of cracked aluminum plates repaired with bonded composite patches[J].AIAA Journal, 1996, 134(2):3143-3151.
[8]Naboulsi S, Mall S.Modeling of cracked metallic structure with bonded composite patch using three layer technique[J].Composite Structure, 1996, 35(3):295-308.
[9]孙洪涛, 刘元镛.改进的金属裂纹板复合材料胶接修补的有限元模型[J].西北工业大学学报, 2000, 18(3):446-451.
[10]杨孚标.复合材料修补含中心裂纹铝合金板的静态与疲劳特性研究[D].长沙:国防科学技术大学, 2006.