通过对含有离散源损伤的复合材料加筋板的拉伸试验和有限元模拟,研究了离散源损伤的损伤扩展与破坏特性.结果表明:复合材料加筋板的离散源损伤用穿透蒙皮切断桁条的切口来模拟是合适的,蒙皮上的穿透切口前端有很高的应力集中,桁条被切断导致加筋板传力路线改变;基于Hashin失效准则的渐进损伤有限元数值模拟方法,可以有效地模拟含切口加筋板的宏观损伤扩展和破坏过程,计算结果与试验值吻合较好.
参考文献
| [1] | Walker T H,Minguet P J,Flynn B W,et al.Advanced technology composite fuselage-Structure performance,NASA-CR-4732[R].1997. |
| [2] | Keral Michael.ATS composite wing program-Executive summary,NASA/CR-2001-210650[R].2001. |
| [3] | Wang John T,Lotts Christine G,Sleight David W.Analysis of discrete-source damage progression in a tensile stiffened composite panel.AIAA99-1336[R].St Louis,MO:AIAA,1999. |
| [4] | Wang John T,Poe Clarence C,Jr,Ambur Damodar R,Sleight David W.Residual strength prediction of damaged composite fuselage panel with R-curve method[J].Composites Science and Technology,2006,66(13):2557-2565. |
| [5] | McGowan David M,Ambur Damoder R,Glen Hanna T,McNeill Stephen R.Evaluation of the compressive response of notched composite panels using a full-field displacement measurement system,AIAA99-1406[R].St Louis,MO:AIAA,1999. |
| [6] | Lovejoy Andrew E.Finite element analysis of a composite semi-span test article with and without discrete damage,NASA/CR-2000-210308[R].2000. |
| [7] | 矫桂琼,杜凯,杨成鹏,卢智先.含离散源损伤复合材料加筋板的压缩特性研究[J].航空学报,2007,29(6):1383-1388.Jiao Guiqiong,Du Kai,Yang Chengpeng,Lu Zhixian.Compressive properties of stiffened composite panels with discrete-source damage[J].Acta Aeronautica et Astronautica Sinica,2007,28(6):1383-1388. |
| [8] | Davila Garlos G,Ambur Damodar R,McGowen David M.Analytical prediction of damage growth in notched composite panels loaded in axial compression,AIAA99-1435[R].St Louis,MO:AIAA,1999. |
| [9] | Hashin Z.Fatigue failure criteria for unidirectional fiber composites[J].Journal of Applied Mechanics,1981,47(4):329-334. |
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