Z-pin增强复合材料开孔层合板压缩性能
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摘要
针对复合材料开孔层合板孔边应力集中而导致承载能力降低现象,采用Z-pin增强技术提高性能。重点了研究开孔层合板的压缩性能,制备了不同Z-pin植入体积分数的开孔层合板试样并进行了压缩试验,在试验基础上,应用有限元分析方法对Z-pin增强开孔层合板进行建模分析,基于渐进损伤分析法和内聚单元法模拟了复合材料基体以及Z-pin的增强效果。试验结果表明:Z-pin的植入可以显著提高开孔层合板的抗压性能,且随着Z-pin植入体积分数的提高,压缩性能不断上升,压缩强度最高可以提高23.06%;只有沿载荷方向,位于开孔两侧的Z-pin可以提高结构的承载能力;在Z-pin桥联力的作用下,降低了损伤的扩展速度,但并没有改变层合板的最终失效模式。模拟结果表明:压缩损伤从孔边向两侧扩展,位于层合板中心的铺层最先出现损伤,其中第6层与第10层的增强单元最先发生破坏。模拟计算结果与试验结果得到了较好的吻合,该有限元模型对于Z-pin增强复合材料开孔层合板的适用性得到了验证。
Z-pin reinforced technique was used to improve the performance of open-hole composite laminates,in view of load capacity reduction because of the stress concentration at the edge of the hole.The influence of the Z-pin insertion percentage on the compression performance of open-hole composite laminates was analyzed by testing the compression properties of laminates with different Z-pin inserted percentages,finite element models of the classical cohesive elements and open-hole composite laminates were established to analyze the influencing mechanism.Results showed that the reinforcing pins increased the compressive strength by 23.06% maximally.Only along the compressive loading direction,the Z-pin located on both sides of the hole can reduce the damage expansion speed by bridging force,but the ultimate failure mode of laminates was not changed.Numerical results showed that the compression damage extended from the edge of the hole to both sides,and the lamination in the center of the laminate was the first to be damaged,among which the cohesive elements in the 6 th and 10 th layers were the first to be damaged.The simulation results were in good agreement with the test results.
Z-pin reinforced technique was used to improve the performance of open-hole composite laminates,in view of load capacity reduction because of the stress concentration at the edge of the hole.The influence of the Z-pin insertion percentage on the compression performance of open-hole composite laminates was analyzed by testing the compression properties of laminates with different Z-pin inserted percentages,finite element models of the classical cohesive elements and open-hole composite laminates were established to analyze the influencing mechanism.Results showed that the reinforcing pins increased the compressive strength by 23.06% maximally.Only along the compressive loading direction,the Z-pin located on both sides of the hole can reduce the damage expansion speed by bridging force,but the ultimate failure mode of laminates was not changed.Numerical results showed that the compression damage extended from the edge of the hole to both sides,and the lamination in the center of the laminate was the first to be damaged,among which the cohesive elements in the 6 th and 10 th layers were the first to be damaged.The simulation results were in good agreement with the test results.
引文
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[21]BARBERO E J.Finite element analysis of composite materials using AbaqusTM[M].Gainesville,Florida,USA:Cyclic Redundancy Check(CRC)Press,2013:365-371.
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[23]周睿,关志东,李星,等.复合材料开孔层板压缩渐进损伤分析[J].北京航空航天大学学报,2015,41(6):1066-1072.ZHOU Rui,GUAN Zhidong,LI Xing,et al.Analysis of compression progressive damage of perforated laminates of composite materials[J].Journal of Beijing University of Aeronautics and Astronautics,2015,41(6):1066-1072.(in Chinese)
[2]郑锡涛,罗贵,李宇徒.复合材料层间性能改善方法研究进展[J].航空制造技术,2013,435(15):26-29.ZHENG Xitao,LUO Gui,LI Yutu.Research progress in improving the properties between layers of composite materials[J].Aeronautical Manufacturing Technology,2013,435(15):26-29.(in Chinese)
[3]郑锡涛,李泽江,杨帆.Z-pin增强复合材料层合板断裂韧性试验研究[J].复合材料学报,2010,27(4):180-188.ZHENG Xitao,LI Zejiang,YANG Fan.Experimental study on fracture toughness of Z-pin reinforced composite laminates[J].Acta Materiae Compositae Sinica,2010,27(4):180-188.(in Chinese)
[4]YASAEE M,BIGG L,MOHAMED G,et al.Influence of Z-pin embedded length on the interlaminar traction response of multi-directional composite laminates[J].Materials and Design,2017,115:26-36.
[5]MOURITZ A P,CHANG P,ISA M D.Z-pin composites:aerospace structural design considerations[J].Journal of Aerospace Engineering,2011,24(4):425-432.
[6]MOHAMED G,ALLEGRI G,YASAEE M,et al.Cohesive element formulation for Z-pin delamination bridging in fibre reinforced laminates[J].International Journal of Solids and Structures,2017,132:232-244.
[7]PEGORIN F,PINGKARAWAT K,DAYNES S,et al.Influence of Z-pin length on the delamination fracture toughness and fatigue resistance of pinned composites[J].Composites:Part B,2015,78:298-307.
[8]MEMBE B,GANNON S,YASAEE M,et al.ModeⅡdelamination resistance of composites reinforced with inclined Z-pins[J].Materials and Design,2016,94:565-572.
[9]滕锦,李斌太,庄茁.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,2006,23(增刊1):209-216.TENG Jin,LI Bintai,ZHUANG Zhuo.Study on low-speed impact damage process of Z-pin toughened composite laminates[J].Engineering Mechanics,2006,23(Suppl.1):209-216.(in Chinese)
[10]陶永强,李晶,宋月娥.Z-pins增强陶瓷基复合材料层间Ⅰ型开裂性能预测[J].航空动力学报,2017,32(5):1099-1104.TAO Yongqiang,LI Jing,SONG Yuee.Z-pins reinforced ceramic matrix composite interlayerⅠcracking performance prediction[J].Journal of Aerospace Power,2017,32(5):1099-1104.(in Chinese)
[11]张向阳,李勇,褚奇奕,等.碳纤维/酚醛树脂体系Z-pin加捻拉挤工艺及其性能[J].航空动力学报,2015,30(7):1638-1644.ZHANG Xiangyang,LI Yong,CHU Qiyi,et al.The technology and properties of Z-pin twist extrusion for carbon fiber/phenolic resin system[J].Journal of Aerospace Power,2015,30(7):1638-1644.(in Chinese)
[12]KNAUPP M,BAUDACH F,FRANK J,et al.Impact and post-impact properties of CFRP laminates reinforced with rectangular Z-pins[J].Composites Science and Technology,2013,87(9):218-223.
[13]王延荣,李宏新,袁善虎,等.考虑应力梯度的缺口疲劳寿命预测方法[J].航空动力学报,2013,28(6):1208-1214.WANG Yanrong,LI Hongxin,YUAN Shanhu,et al.The notch fatigue life prediction method considering stress gradient[J].Journal of Aerospace Power,2013,28(6):1208-1214.(in Chinese)
[14]BIAN T,GUAN Z,LIU F.Compressive experiment and numerical simulation of 3Dcarbon/carbon composite openhole plates[J].Archive of Applied Mechanics,2018,88(1/2):913-932.
[15]BORKOWSKI L,KUMAR R S.Inverse method for estimation of composite kink-band toughness from open-hole compression strength data[J].Composite Structures,2018,186:183-192.
[16]ZHOU S,SUN Y,CHEN B,et al.Progressive damage simulation of open-hole composite laminates under compression based on different failure criteria[J].Journal of Composite Materials,2017,51(9):1239-1251.
[17]DI L,FENZA R D,BARILE A,et al.Performances'estimation by tests of composite material structures with respect to the lay-up configuration and mixing the position of tape and fabric laminae[J].Archive of Mechanical Engineering,2015,62(4):553-564.
[18]HASHIN Z.Failure criteria for unidirectional fiber composites[J].Journal of Applied Mechanics,1980,47(2):329-334.
[19]李成虎,燕瑛.Z-pin增强复合材料T型接头层间性能的建模与分析[J].复合材料学报,2010,27(6):152-157.LI Chenghu,YAN Ying.Modeling and analysis of the interlaminar properties of Z-pin reinforced composite T-joints[J].Acta Materiae Compositae Sinica,2010,27(6):152-157.(in Chinese)
[20]BENZEGGAGH M L,KENANE M.Measurement of mixed-mode delamination fracture toughness of unidirectional glass/epoxy composites with mixed-mode bending apparatus[J].Composites Science and Technology,1996,56(4):439-449.
[21]BARBERO E J.Finite element analysis of composite materials using AbaqusTM[M].Gainesville,Florida,USA:Cyclic Redundancy Check(CRC)Press,2013:365-371.
[22]HALDAR S,CAPUTO D,BUESKING K,et al.Flexural behavior of singly curved X-Cor(R)sandwich composite structures:experiment and finite element modeling[J].Composite Structures,2015,129:70-79.
[23]周睿,关志东,李星,等.复合材料开孔层板压缩渐进损伤分析[J].北京航空航天大学学报,2015,41(6):1066-1072.ZHOU Rui,GUAN Zhidong,LI Xing,et al.Analysis of compression progressive damage of perforated laminates of composite materials[J].Journal of Beijing University of Aeronautics and Astronautics,2015,41(6):1066-1072.(in Chinese)