根据完整复合材料修补模型进行分析与验证,在此基础上针对小型非对称脱胶建立了脱胶分析有限元模型,引入脱胶影响“当量距离”的概念,分析了不同尺寸与位置的脱胶对于维修效果的影响.结果表明:脱胶直径较小时,裂纹强度对于脱胶位置的改变不敏感;当脱胶尺寸足够大时,在裂纹尖端附近存在一个脱胶敏感区域,在此区域内发生脱胶对于修补强度影响较大,而且该影响区域随着裂纹长度增加而增大.
参考文献
[1] | Baker A A .Fiber composite repair of cracked metallic aircraft component,practical and basic aspects[J].Composites,1987,18(4):293-307. |
[2] | Baker A A .Bonded composite repair of fatigue-cracked primary aircraft structures[J].Composite Structure,1999,47:431-443. |
[3] | Baker A A.Joining and repair of aircraft composite structures[M].Composite engineering handbook.New York:Marcel Dekker,1997 |
[4] | Baker A A.Repair of cracked or defective metallic aircraft components with advanced fibre composites-an overview of Australian work[J].Compos.Struct,1984(2):53-161. |
[5] | Denney J J .Fatigue Response of Cracked Aluminum Panel with Partially Bonded Composite Patch[D].ADA306361,1995. |
[6] | Denney J J;Mall S.Effect of disbond on fatigue behavior of cracked aluminum panel with bonded composite patch[J].AIAA-96-1332,1996 |
[7] | A. Megueni;B. Bachir Bouiadjra;M. Belhouari .Disbond effect on the stress intensity factor for repairing cracks with bonded composite patch[J].Computational Materials Science,2004(4):407-413. |
[8] | Bachir Bouiadjra B;Belhouari M .Computation of the stress intensity factors for repaired cracks with bond composite patch in mode Ⅰ and mix modes[J].Composite Structures,2002,56:401-406. |
[9] | Shin-etsu Fujimoto;Hideki Sekine .Identification of crack and disbond fronts in repaired aircraft structural panels with bonded FRP composite patches[J].Composite structures,2007(4):533-545. |
[10] | Palaniappan J;Ogin S L.Disbond growth detection in composite-composite single-lap joints using chirped FBG sensors[J].Composite Science and Technology,2008 |
[11] | Rose L R F .An application of the inclusion analogy for bonded reinforcements[J].Int.J.Solid Struct,1981,17:827-838. |
上一张
下一张
上一张
下一张
计量
- 下载量()
- 访问量()
文章评分
- 您的评分:
-
10%
-
20%
-
30%
-
40%
-
50%