为开展纤维金属层板(FML)低速冲击有限元数值仿真研究,改进了传统的连续损伤力学(CDM)模型,然后对FML落锤低速冲击试验进行数值仿真,并与实验结果进行对比验证.分别采用5.11J和10.33 J冲击能量对FML进行落锤低速冲击试验,得到冲击载荷、位移和能量时程曲线,分析FML的动态响应和失效模式.建立了考虑塑性应变、压缩刚度衰减特征和纤维拉伸断裂损伤的新CDM模型,描述S2玻璃纤维/环氧树脂(S2 galss/epoxy)复合材料的损伤本构,并编写VUMAT子程序,通过ABAQUS/Explicit求解器对FML落锤冲击试验进行数值仿真.研究结果表明:低能量冲击条件下,FML背面主要为鼓包和裂纹等失效模式,位移峰值随冲击能量的提高而增加,冲击载荷峰值在穿透前也随冲击能量的提高而增加;采用改进的CDM模型描述FML中S2 galss/epoxy复合材料铺层后,有限元数值计算可以较好地预测FML低速冲击载荷下的动态响应;有限元数值仿真结果表明,FML中第2层复合材料铺层发生的纤维断裂损伤比第1层的更严重.
参考文献
| [1] | Vogelesang L B,Vlot A.Development of fibre metal lami nates for advanced aerospace structures[J].Journal of Mate rials Processing Technology,2000,103(1):1-5.,2000. |
| [2] | Woerden H J M,Sinke J,Hoouijmeijer P A.Maintenance of glare structures and glare as riveted or bonded repair material[J].Applied Composite Materials,2003,10(4 5):307-329.,2003. |
| [3] | Vermeeren C A J R.An historic overview of the development of fibre metal laminates[J].Applied Composite Materials,2003,10(4 5):189-205.,2003. |
| [4] | Sadighi M,Alderliesten R C,Benedictus R.Impact resist ance of fiber metal laminates:a review[J].International Journal of Impact Engineering,2012,49:77-90.,2012. |
| [5] | McCarthy C T,McCarthy M A,Lawlor V P.Progressive damage analysis of multi bolt composite joints with variable bolt hole clearances[J].Composites Part B:Engineering,2005,36(4):290-305.,2005. |
| [6] | 古兴瑾,许希武.纤维增强复合材料层板高速冲击损伤数值模拟[J].复合材料学报,2012(01):150-161. |
| [7] | MaaR H,ChengJ H.ACDM based failure model for pre dicting strength of notched composite laminates[J].Com positesPart B:Engineering,2002,33(6):479-489.,2002. |
| [8] | Maimí P,Camanho P P,Mayugo J A,et al.A contiuum damage model for composite laminates:part Ⅰ constitutive model[J].Mechanics of Materials,2007,39(10):897-908.,2007. |
| [9] | Maire J F,Chaboche J L.A new formulation of continuum damage mechanics (CDM) for composite materials[J].Aer ospace Science and Technology,1997,1(4):247-257.,1997. |
| [10] | Ladeveze P,LeDantec E.Damage modelling of the elementa ry ply for laminated composites[J].Composites Science and Technology,1992,43(3):257-267.,1992. |
| [11] | O'Higgins R M,McCarthy C T,McCarthy M A.Identifica tion of damage and plasticity parameters for continuum dam age mechanics modelling of carbon and glass fibre reinforced composite materials[J].Strain,2011,47(1):105-115.,2011. |
| [12] | Frizzell R M,McCarthy C T,McCarthy M A.Predicting the effects of geometry on the behaviour of fibre metal laminate joints[J].Composite Structures,2011,93(7):1877-1889.,2011. |
| [13] | 张彦 .纤维增强复合材料层合结构冲击损伤预测研究[D].上海交通大学,2007. |
| [14] | McCrathy M A,Xiao J R,McCarthy C T,et al.Modelling of bird strike on an aircraft wing leading edge made from fibre metal laminates part 2:modelling of impact with SPH bird model[J].Applied Composite Materials,2004,11(5):317-340.,2004. |
| [15] | McCrathy M A,Xiao J R,Prtrinic N,et al.Modelling of bird strike on an aircraft wing leading edge made from fibre metal laminates Part 1:material modelling[J].Applied Composite Materials,2004,11(5):295-315.,2004. |
| [16] | Laliberté J,Poon C,Straznicky P V.Numerical modelling of low velocity impact damage in fibre metal laminates[C]//ICAS 2002 Congress (The International Council of the Aero nautical Sciences Congress).Toronto,Canada,2002.,2002. |
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%