纤维金属层板铆接损伤机理与预测的研究
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摘要
纤维金属层板铆接损伤是连接件、被连接件以及铆钉等多个复杂结构的耦合损伤行为。为了预测纤维金属层板铆接损伤行为,采用Johnson-Cook失效准则预测金属层损伤,采用三维Hashin损伤准则预测复合材料层损伤,采用脱层失效理论预测层间开裂,理论预测模型的合理性通过了实验验证。通过损伤预测模型分别考察层板铺层数量、铆接预紧力、铝合金分数和结构几何对纤维金属层板铆接损伤行为及铆接刚度的影响,为FMLs铆接设计提供可行性建议。结果表明:铺层数量的增加加剧了层板自由端层间脱层剥离现象,从而降低了层板铆接强度;铝合金分数的增加能够提高层板的铆接强度,但铝合金分数大于50%时铆接强度和铆接比强度反而下降;预紧力的增大能够延缓纤维和基体的萌生,并且提升铆接刚度,使得纤维金属铆接承受更大载荷;随着横宽径比W/D和纵宽径比E/D的递增,铆接极限强度有所提高,当W/D≥3或E/D≥3时,铆接强度不再明显提高。
Fiber metal laminates(FMLs) rivetdamage is a coupling damage behavior caused by a complex structure composed of connecting pieces,the connectedparts and the rivets.In order to predict rivet damage behavior of FMLs,Johnson-Cook failure criterionis used to predict Aluminum damage,three-dimensional Hashin damage criterion is used to evaluate the damage of fiber layers,and the cohesive model is applied to delamination prediction.And experimental comparative analysis was performed to verify the rationality of the coupling damagemodel. Effects of laminate layers,riveting pretension,aluminum alloy fraction and geometric coefficients on FMLs damage and stiffness of plate riveting were studied by this damage prediction model,and it provides the feasible advice for the design of FMLs rivet. The results show that laminates with more layers are much easier to debond at the bi-material interface,and the interlaminar delamination at free endsdirectly reduces the rivet strength. Rivet strength increases with increasing aluminum fraction,but it will decrease when the aluminum contentis greater than 50%. Pretensioncan delay the damage initiation at fiber and matrix,and enhance the stiffness of the rivet joint,which consequently endow it with the ability to withstand greater external load. The riveting ultimate strength increases with increasing weight-diameter ratio W/D,and end distance-diameter ratio E/D of fiber metal laminate riveting strength have different effects until W/D = 3 and E/D = 3. Further increase of W/D and E/D will not improve the rivet strength.
Fiber metal laminates(FMLs) rivetdamage is a coupling damage behavior caused by a complex structure composed of connecting pieces,the connectedparts and the rivets.In order to predict rivet damage behavior of FMLs,Johnson-Cook failure criterionis used to predict Aluminum damage,three-dimensional Hashin damage criterion is used to evaluate the damage of fiber layers,and the cohesive model is applied to delamination prediction.And experimental comparative analysis was performed to verify the rationality of the coupling damagemodel. Effects of laminate layers,riveting pretension,aluminum alloy fraction and geometric coefficients on FMLs damage and stiffness of plate riveting were studied by this damage prediction model,and it provides the feasible advice for the design of FMLs rivet. The results show that laminates with more layers are much easier to debond at the bi-material interface,and the interlaminar delamination at free endsdirectly reduces the rivet strength. Rivet strength increases with increasing aluminum fraction,but it will decrease when the aluminum contentis greater than 50%. Pretensioncan delay the damage initiation at fiber and matrix,and enhance the stiffness of the rivet joint,which consequently endow it with the ability to withstand greater external load. The riveting ultimate strength increases with increasing weight-diameter ratio W/D,and end distance-diameter ratio E/D of fiber metal laminate riveting strength have different effects until W/D = 3 and E/D = 3. Further increase of W/D and E/D will not improve the rivet strength.
引文
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[15]Linde P,Pleitner J,De Boer H,et al.Modelling and simulation of fibre metal laminate[R]ABAQUS Users'Conference,2004,421-439.
[16]Lapczyk I,Hurtado J A.Progressive damage modeling in fiber-reinforced materials[J].Composites Part A Applied Science&Manufacturing,2007,38(11):2333-2341.
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[18]庄茁,张帆,岑松.ABAQUS非线性有限元分析与实例[M].北京:科学出版社,2004.
[19]滕锦.Z-pin增韧复合材料层合板低速冲击损伤过程研究[J].工程力学,2006,6(23):209-216.
[20]平学成,李烽,吴卫星.一种精确控制铆接结构中铆钉预紧力的加载装置:104596695A[P].2015-05-06.
[2]沈观林,胡更开.复合材料力学[M].北京:清华大学出版社,2013.
[3]陶杰,李华冠,潘蕾,等.纤维金属层板的研究与发展趋势[J].南京航空航天大学学报,2015,47(5):626-636.
[4]Sinmaz9elik T,Avcu E,Bora M,et al.A review:Fibre metal laminates,background,bonding types and applied test methods[J].Materials&Design,2011,32(7):3671-3685.
[5]Yeh P C,Chang P Y,Yang J M,et al.Blunt notch strength of hybrid boron/glass/aluminum fiber metal laminates[J].Materials Science&Engineering A,2011,528(4-5):2164-2173.
[6]Payeganeh G H,Ghasemi F A,Malekzadeh K.Dynamic response of fiber-metal laminates(FMLs)subjected to low-velocity impact[J].Thin-Walled Structures,2010,48(1):62-70.
[7]Vries T J D.Blunt and sharp notch behaviour of glare laminate.Ph.D dissertation[J].Delft University Press,2001.
[8]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.
[9]Frizzell R M,Mccarthy C T,Mccarthy M A.A comparative study of the pin-bearing responses of two glass-based fibre metal laminates[J].Composites Science&Technology,2008,68(15):3314-3321.
[10]Johnson G R,Cook W H.Fracture characteristics of three metals subjected to various strains,strain rates,temperatures and pressures[J].Engineering Fracture Mechanics,1985,21(1):31-48.
[11]Hashin,Z.Failure criteria for unidirectional fiber composites[J].Journal of Applied Mechanics,1980,47(2):329-334.
[12]Hashin Z.Analysis of stiffness reduction of cracked cross-ply laminated[J].Engineering of Fracture Mechanics,1986,25(5):771-778.
[13]Chang F,Chang K.A progressive damage model for laminated composites containing stress concentrations[J].Journal of Composite Materials,1987,21(9):834-855.
[14]Preusch K.,Linde P.,Pleitner J.,et al.Modelling of fibre metal laminate shells applied to the inter rivet buckling phenomenon[J].European Congress on Computational Methods in Applied Sciences and Engineering,2004.
[15]Linde P,Pleitner J,De Boer H,et al.Modelling and simulation of fibre metal laminate[R]ABAQUS Users'Conference,2004,421-439.
[16]Lapczyk I,Hurtado J A.Progressive damage modeling in fiber-reinforced materials[J].Composites Part A Applied Science&Manufacturing,2007,38(11):2333-2341.
[17]Karakuzu R,Taylak N,Icten B M,et al.Effects of geometric parameters on failure behavior in laminated composite plates with two parallel pin-loaded holes[J].Composite Structures,2008,85(1):1-9.
[18]庄茁,张帆,岑松.ABAQUS非线性有限元分析与实例[M].北京:科学出版社,2004.
[19]滕锦.Z-pin增韧复合材料层合板低速冲击损伤过程研究[J].工程力学,2006,6(23):209-216.
[20]平学成,李烽,吴卫星.一种精确控制铆接结构中铆钉预紧力的加载装置:104596695A[P].2015-05-06.