含孔CFRP正交层合板的双轴拉伸力学行为
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摘要
采用加载臂开槽的中心开孔等厚度十字形试样,实验研究了正交对称铺层碳纤维增强聚合物基复合材料(CFRP)层合板在双轴拉伸载荷作用下的力学行为,分析了3种双轴加载比对其拉伸强度和破坏行为的影响。研究表明:纤维被切断的铺层部分在拉伸作用下容易与其相邻铺层脱粘,导致层合板承载力下降;等双轴加载时,在孔边的被切断纤维与连续纤维间基体在横向拉伸和纵向剪切组合作用下首先开裂;非等双轴加载时,在垂直于快速拉伸方向的铺层中沿孔边应力集中处先出现基体裂纹;随着加载比的增大,快速拉伸方向的细观结构损伤随载荷的增大发展更快,刚度下降更快,破坏时主裂纹的扩展方向更趋于垂直于快速拉伸方向;强度包络线的分析表明快速拉伸方向的拉伸强度随加载比的增大呈缓慢增大的趋势。
The biaxial tensile mechanical properties of carbon fiber reinforced polymer(CFRP)cross-ply composite laminates with central hole were experimentally studied using the uniform thickness cruciform specimens with slots in the arms.Three biaxial load ratios were applied to study the effects of load ratio on the biaxial tensile strength and failure characteristics of CFRP cross-ply laminates.The results show that under the biaxial tensile loads,the interfaces between the plies with fibers cut off and their adjacent plies with continuous fibers are prone to delaminate,and resulting in the reduction of load bearing capacity of CFRP cross-ply laminate.Under an equal biaxial tensile load,the cracks initiate at the matrix between the cutting-off and the continuous fibers along the hole edge,resulting from the combined load of the transverse tension and longitudinal shear.Under an unequal biaxial tensile load,matrix crack initiates in the plies perpendicular to the load direction with a higher tensile velocity,and appears at the hole edge with a high stress concentration.With the increasing of the load ratios,the microstructure damage in the regions with a higher tensile velocity develops more rapid,and so does the corresponding stiffness reduction.The propagation direction of the main crack tends to be perpendicular to the tensile direction with a higher tensile velocity.The analysis of the strength envelope of the CFRP cross-ply laminate with central hole shows that the tensile strength in the direction with a higher tensile velocity increases gently with the increasing of load ratio.
The biaxial tensile mechanical properties of carbon fiber reinforced polymer(CFRP)cross-ply composite laminates with central hole were experimentally studied using the uniform thickness cruciform specimens with slots in the arms.Three biaxial load ratios were applied to study the effects of load ratio on the biaxial tensile strength and failure characteristics of CFRP cross-ply laminates.The results show that under the biaxial tensile loads,the interfaces between the plies with fibers cut off and their adjacent plies with continuous fibers are prone to delaminate,and resulting in the reduction of load bearing capacity of CFRP cross-ply laminate.Under an equal biaxial tensile load,the cracks initiate at the matrix between the cutting-off and the continuous fibers along the hole edge,resulting from the combined load of the transverse tension and longitudinal shear.Under an unequal biaxial tensile load,matrix crack initiates in the plies perpendicular to the load direction with a higher tensile velocity,and appears at the hole edge with a high stress concentration.With the increasing of the load ratios,the microstructure damage in the regions with a higher tensile velocity develops more rapid,and so does the corresponding stiffness reduction.The propagation direction of the main crack tends to be perpendicular to the tensile direction with a higher tensile velocity.The analysis of the strength envelope of the CFRP cross-ply laminate with central hole shows that the tensile strength in the direction with a higher tensile velocity increases gently with the increasing of load ratio.
引文
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[14]陈秀华,伍春波,余音,等.复合材料厚板双轴非线性渐进失效分析[J].应用力学学报,2012,29(5):559-565.CHEN Xiuhua,WU Chunbo,YU Yin,et al.Nonlinear progressive failure analysis of thick composite laminate under biaxial load[J].Chinese Journal of Application Mechanics,2012,29(5):559-565(in Chinese).
[15] HU H T,LIN W P,TU P T.Failure analysis of fiber-reinforced composite laminates subjected to biaxial loads[J].Composites Part B:Engineering,2015,83:153-165.
[16] SODEN P D,KITCHING R,TSE P C.Experimental failure stresses for±55°filament wound glass fiber reinforced plastic tubes under biaxial loading[J].Composites,1989,20(2):125-135.
[17] SMITS A,HEMELRIJCK D V,PHILIPPIDIS T P,et al.Design of a cruciform specimen for biaxial testing of fibre reinforced composite laminates[J].Composites Science and Technology,2006,66:964-975.
[18] RASHEDI A,SRIDHAR I,TSENG K J.Fracture characterization of glass fiber composite laminate under experimental biaxial loading[J].Composite Structures,2016,138:17-29.
[19] WELSH J S,DONALD F A.An experimental investigation of the biaxial strength of IM6/3501-6carbon/expoxy crossply laminates using cruciform specimens[J].Composites Part A:Applied Science and Manufacturing,2002,33:829-839.
[20] LAMKANFI E,PAEPEGEM W V,DEGRIECK J,et al.Strain distribution in cruciform specimens subjected to biaxial loading conditions:Part 2—Influence of geometrical discontinuities[J].Polymer Testing,2010,29:132-138.
[21] MAKRIS A,VANDENBERGH T,RAMAULT C,et al.Shape optimization of a biaxially loaded cruciform specimen[J].Polymer Testing,2010,29:216-223.
[22]贾文斌.复合材料层合板低速冲击与双轴剩余强度分析研究[D].南京:南京航空航天大学,2016.JIA Wenbin.Analysis and research on low velocity impact damage and residual strength under biaxial load of composite laminated plates[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2016(in Chinese).
[23] SHI T B,CHEN W J,GAO C J,et al.Biaxial strength determination of woven fabric composite for airship structural envelope based on novel specimens[J].Composite Structures,2018,184:1126-1136.
[24] TIERNAN P,A.HANNON.Design optimisation of biaxial tensile test specimen using finite element analysis[J].International Journal of Material Forming,2014,7:117-123.
[25] ASTM Committee.Standard test method for open hole tensile strength of polymer matrix composite laminates:ASTM D 5766/D 5766M-02a[S].Pennsylvania:ASTM International,2002.
[26]温泉,郭东明,高航,等.碳纤维/环氧树脂复合材料制孔损伤综合测评方法[J].复合材料学报,2016,33(2):265-272.WEN Quan,GUO Dongming,GAO Hang,et al.Comprehensive evaluation method for carbon/epoxy composite holemaking damages[J]. Acta Materiae Compositae Sinica,2016,33(2):265-272(in Chinese).
[2] HAN G C,NEWCOMB B A,GULGUNJE P V,et al.High strength and high modulus carbon fibers[J].Carbon,2015,93:81-87.
[3]杜善义.先进复合材料与航空航天[J].复合材料学报,2007,24(1):1-12.DU Shanyi.Advanced composite materials and aerospace engineering[J].Acta Materiae Compositae Sinica,2007,24(1):1-12(in Chinese).
[4]陈燕,葛恩德,傅玉灿,等.碳纤维增强树脂基复合材料制孔技术研究现状与展望[J].复合材料学报,2015,32(2):301-315.CHEN Yan,GE Ende,FU Yucan,et al.Review and propect of drilling technologies for carbon fiber reinforced polymer[J].Acta Materiae Compositae Sinica,2015,32(2):301-315(in Chinese).
[5]黎增山,关志东,何为,等.复合材料层合板开孔拉伸损伤分析[J].复合材料学报,2012,29(1):169-175.LI Zengshan,GUAN Zhidong,HE Wei,et al.Damage analysis of open-hole tension laminates[J].Acta Materiae Compositae Sinica,2012,29(1):169-175(in Chinese).
[6]汪裕炳,张全纯.复合材料的结构连接[M].北京:国防工业出版社,1992:148-149.WANG Yubing,ZHANG Quanchun.Connecting of composite structures[M].Beijing:National Defence Industry Press,1992:148-149(in Chinese).
[7] CHANG F K,LESSARD L B.Damage tolerance of laminated composites containing an opening hole and subjected to compressive loading:Part I—Analysis[J].Journal of Composite Materials,1991,25(1):2-43.
[8] CHANG K Y,LIU S,CHANG F K.Damage tolerance of laminated composites containing an opening hole and subjected to tensile loadings[J].Journal of Composite Materials,1991,25(3):274-301.
[9] MAA R H,CHENG J H.A CDM-based failure model for predicting strength of notched composite laminates[J].Composites Part B:Engineering,2002,33(6):479-489.
[10]王震宇,刘玲,宫占峰,等.NCF/环氧层合板开孔拉伸渐进损伤分析[J].复合材料学报,2013(s1):147-152.WANG Zhenyu,LIU Ling,GONG Zhanfeng,et al.Progressive damage of an open-hole NCF/epoxy laminate subjected to tensile load[J].Acta Materiae Compositae Sinica,2013(s1):147-152(in Chinese).
[11]肖梦丽,张勇波,王治华,等.国产纤维复合材料开孔拉伸失效分析与预测[J].航空动力学报,2015,30(12):2857-2862.XIAO Mengli,ZHANG Yongbo, WANG Zhihua,et al.Failure analysis and prediction on the open-hole tension of domestic carbon fiber composite[J].Journal of Aerospace Power,2015,30(12):2857-2862(in Chinese).
[12]许承海,孟松鹤,齐菲,等.三维机织碳/碳复合材料双轴压缩载荷下的力学行为[J].复合材料学报,2012,29(6):206-211.XU Chenghai,MENG Songhe,QI Fei,et al.Mechanical behaviors of the three-dimensional woven carbon/carbon composite materials under biaxial compression[J].Acta Materiae Compositae Sinica,2012,29(6):206-211(in Chinese).
[13]蔡登安,周光明,曹然,等.双轴载荷下复合材料十字型试样几何形状对中心测试区系数的影响[J].复合材料学报,2015,32(4):1138-1144.CAI Deng’an,ZHOU Guangming,CAO Ran,et al.Influence of geometry of composite cruciform specimen under biaxial loading on coefficients of central testing zone[J].Acta Materiae Compositae Sinica,2015,32(4):1138-1144(in Chinese).
[14]陈秀华,伍春波,余音,等.复合材料厚板双轴非线性渐进失效分析[J].应用力学学报,2012,29(5):559-565.CHEN Xiuhua,WU Chunbo,YU Yin,et al.Nonlinear progressive failure analysis of thick composite laminate under biaxial load[J].Chinese Journal of Application Mechanics,2012,29(5):559-565(in Chinese).
[15] HU H T,LIN W P,TU P T.Failure analysis of fiber-reinforced composite laminates subjected to biaxial loads[J].Composites Part B:Engineering,2015,83:153-165.
[16] SODEN P D,KITCHING R,TSE P C.Experimental failure stresses for±55°filament wound glass fiber reinforced plastic tubes under biaxial loading[J].Composites,1989,20(2):125-135.
[17] SMITS A,HEMELRIJCK D V,PHILIPPIDIS T P,et al.Design of a cruciform specimen for biaxial testing of fibre reinforced composite laminates[J].Composites Science and Technology,2006,66:964-975.
[18] RASHEDI A,SRIDHAR I,TSENG K J.Fracture characterization of glass fiber composite laminate under experimental biaxial loading[J].Composite Structures,2016,138:17-29.
[19] WELSH J S,DONALD F A.An experimental investigation of the biaxial strength of IM6/3501-6carbon/expoxy crossply laminates using cruciform specimens[J].Composites Part A:Applied Science and Manufacturing,2002,33:829-839.
[20] LAMKANFI E,PAEPEGEM W V,DEGRIECK J,et al.Strain distribution in cruciform specimens subjected to biaxial loading conditions:Part 2—Influence of geometrical discontinuities[J].Polymer Testing,2010,29:132-138.
[21] MAKRIS A,VANDENBERGH T,RAMAULT C,et al.Shape optimization of a biaxially loaded cruciform specimen[J].Polymer Testing,2010,29:216-223.
[22]贾文斌.复合材料层合板低速冲击与双轴剩余强度分析研究[D].南京:南京航空航天大学,2016.JIA Wenbin.Analysis and research on low velocity impact damage and residual strength under biaxial load of composite laminated plates[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2016(in Chinese).
[23] SHI T B,CHEN W J,GAO C J,et al.Biaxial strength determination of woven fabric composite for airship structural envelope based on novel specimens[J].Composite Structures,2018,184:1126-1136.
[24] TIERNAN P,A.HANNON.Design optimisation of biaxial tensile test specimen using finite element analysis[J].International Journal of Material Forming,2014,7:117-123.
[25] ASTM Committee.Standard test method for open hole tensile strength of polymer matrix composite laminates:ASTM D 5766/D 5766M-02a[S].Pennsylvania:ASTM International,2002.
[26]温泉,郭东明,高航,等.碳纤维/环氧树脂复合材料制孔损伤综合测评方法[J].复合材料学报,2016,33(2):265-272.WEN Quan,GUO Dongming,GAO Hang,et al.Comprehensive evaluation method for carbon/epoxy composite holemaking damages[J]. Acta Materiae Compositae Sinica,2016,33(2):265-272(in Chinese).