缝合复合材料T型接头拉伸载荷下的有限元数值模拟

doi:10.7527/S1000-6893.2020.24231

固体力学与飞行器总体设计

本期目录 | 过刊浏览 | 高级检索

前一篇 | 后一篇

缝合复合材料T型接头拉伸载荷下的有限元数值模拟

文立伟, 余坤, 宦华松

南京航空航天大学材料科学与技术学院, 南京 210016

收稿日期:2020-05-15 修回日期:2020-06-16 发布日期:2020-08-31
通讯作者: 文立伟 E-mail:wenliwei@nuaa.edu.cn
基金资助:
国防基础科研计划（JCKY2019204A001）；上海航天科技创新基金（SAST2019-117）

Finite element numerical simulation of stitched composite T-joint under tensile load

WEN Liwei, YU Kun, HUAN Huasong

College of Materials Science and Technology, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

Received:2020-05-15 Revised:2020-06-16 Published:2020-08-31
Supported by:
Defense Industrial Technology Development Program (JCKY2019204A001);Shanghai Aerospace Science and Technology Innovation Foundation(SAST2019-117)

摘要/Abstract

摘要： 利用ABAQUS软件对拉伸载荷下的缝合T型接头进行建模与分析，采用基于内聚力模型（CZM）的黏聚接触方法来模拟筋条与蒙皮的脱粘行为，以基于细观力学的非线性弹簧模拟缝线在上下界面的增强作用。在模型基础上对缝线直径进行参数化分析，研究其对T型接头拉伸性能的影响。结果表明：随缝线直径增大，接头极限破坏载荷提高，即拉伸承载能力提高。有限元分析结果与试验值吻合较好。值得注意的是，当缝线直径增大到1 500旦尼尔时，模拟结果与试验数据存在10.4%的误差，这是因为模型未考虑缝合对层合板面内性能的影响，忽略了缝线可能造成的材料损伤。考虑到T型接头在拉伸载荷作用下的破坏模式主要是I型和Ⅱ型破坏，因此宜采用二维有限元模型进行参数化分析，计算效率高并且与试验结果吻合较好。

关键词: 有限元, 缝合, 复合材料, T型接头, 拉伸载荷

Abstract: Software ABAQUS is used to model and analyze the stitched T-joint under tensile load. The cohesive contact method based on the Cohesive Zone Model (CZM) is adopted to simulate the debonding behavior of the stiffener flange and skin. The reinforcement effect of stitching at the interface is simulated with the nonlinear spring element based on mesomechanics. On the basis of finite element model, the influence of stitching on tensile properties of the T-joint is studied by parametric analysis. Results show that the ultimate failure load increases with the increase of the thread diameter. That is, the tensile bearing capacity improves. The analysis results of the finite element method are in good agreement with the experimental values. It is worth noting that there is a 10.4% deviation between the simulation results and the experimental values when the thread diameter increases to 1 500 denier, because the model does not consider the effect of stitching on the in-plane performance and ignores the possible damage caused by stitching. Since the failure modes of the T-joint under tensile load are mainly Type I and Type Ⅱ failures, it is advisable to use two-dimensional finite element model for parametric analysis for its high calculation efficiency and good agreement with the test results.

Key words: finite element, stitching, composites, T-joint, tensile load

中图分类号:

V258
TB332

文立伟, 余坤, 宦华松. 缝合复合材料T型接头拉伸载荷下的有限元数值模拟[J]. 航空学报, 2021, 42(2): 224231-224231.

WEN Liwei, YU Kun, HUAN Huasong. Finite element numerical simulation of stitched composite T-joint under tensile load[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021, 42(2): 224231-224231.

参考文献

[1] 李陵, 徐峰, 郑绍文. 复合材料T型接头力学性能分析及优化研究[J]. 玻璃钢/复合材料, 2015(4):41-46. LI L, XU F, ZHENG S W. Research and analysis on the mechanical properties and optimization for composite T-joint[J]. Fiber Reinforced Plastics/Composites, 2015(4):41-46(in Chinese).
[2] BORTOLUZZI D B, GOMES G F, HIRAYAMA D, et al. Development of a 3D reinforcement by tufting in carbon fiber/epoxy composites[J]. The International Journal of Advanced Manufacturing Technology, 2019,100(5/8):1593-1605.
[3] BIGAUD J, ABOURA Z, MARTINS A T, et al. Analysis of the mechanical behavior of composite T-joints reinforced by one side stitching[J]. Composite Structures, 2018, 184:249-255.
[4] 程小全, 赵龙, 张怡宁. 缝合复合材料可用性——简单层合板的基本性能[J]. 北京航空航天大学学报, 2003,29(11):1001-1005. CHENG X Q, ZHAO L, ZHANG Y N. Properties of stitched composite laminates——the principle properties of simple laminates[J]. Journal of Beijing University of Aeronautics and Astronautics, 2003,29(11):1001-1005(in Chinese).
[5] 燕瑛, 韩凤宇, 杨东升, 等. 缝合复合材料弹性性能的三维有限元细观分析与试验验证[J]. 航空学报, 2004,25(3):267-269. YAN Y, HAN F Y, YANG D S, et al. Finite element micromechanical analysis and experimental confirmation of the elastic properties of stitched composite materials[J]. Acta Aeronautica et Astronautica Sinica, 2004,25(3):267-269(in Chinese).
[6] MIGNERY L A, TAN T M, SUN C T. The use of stitching to suppress delamination in laminated composites[C]//ASTM STP. West Conshohocken:ASTM International, 1985:371-385.
[7] VELMURUGAN R, SOLAIMURUGAN S. Influence of in-plane fibre orientation on mode I interlaminar fracture toughness of stitched glass/polyester composites[J]. Composites Science and Technology, 2008, 68(7):1742-1752.
[8] 朱华东, 矫桂琼, 杨宝宁. 缝合复合材料Ⅱ型层间断裂韧性研究[J]. 复合材料学报, 2001, 18(2):85-89. ZHU H D, JIAO G Q, YANG B N. Investigation into the effect of stitching in CFRP on mode Ⅱ delamination toughness[J]. Acta Materiae Compositae Sinica, 2001, 18(2):85-89(in Chinese).
[9] 张国利, 李嘉禄, 李学明. T型壁板RFI缝合复合材料的屈曲性能[J]. 纺织学报, 2006(3):67-70. ZHANG G L, LI J L, LI X M. Buckling performance of T-shape RFI stitched composites panel[J]. Journal of Textile Research, 2006(3):67-70(in Chinese).
[10] KIM C H, JO D H, CHOI J H. Failure strength of composite T-joints prepared using a new 1-thread stitching process[J]. Composites Structures, 2017,178:225-231.
[11] 叶强, 陈普会. 复合材料粘聚区模型的强度参数预测[J]. 固体力学学报, 2012,33(6):566-573. YE Q, CHEN P H. Prediction on the strength parameters of cohesive zone model for simulation composite delamination[J]. Chinese Journal of Solid Mechanics, 2012,33(6):566-573(in Chinese).
[12] 孔斌, 陈普会, 李梦佳, 等. Z-pin/缝合对复合材料T型接头剪切承载能力的影响[J]. 复合材料学报, 2018,35(4):834-842. KONG B, CHEN P H, LI M J, et al. Effect of Z-pin/stitching on the shear carrying capacity of composite T-joints[J]. Acta Materiae Compositae Sinica, 2018,35(4):834-842(in Chinese).
[13] IWAHORI Y, NAKANE K, WATANABE N. DCB test simulation of stitched CFRP laminates using interlaminar tension test results[J]. Composites Science and Technology, 2009,69(14):2315-2322.
[14] 李梦佳, 陈普会, 孔斌, 等. Z-pin参数对复合材料T型接头拉脱承载能力的影响[J]. 复合材料学报, 2015,32(2):571-578. LI M J, CHEN P H, KONG B,et al. Effect of Z-pin parameters on pull-off carrying capacity of composite T-joints[J]. Acta Materiae Compositae Sinica, 2015, 32(2):571-578(in Chinese).
[15] GRASSI M, ZHANG X. Finite element analysis of mode I interlaminar delamination in z-fiber reinforced composite laminates[J]. Composites Science and Technology, 2003, 63(12):1815-1832.
[16] TAN K T, WATANABE N. Impact damage resistance, response, and mechanisms of laminated composites reinforced by through-thickness stitching[J]. International Journal of Damage Mechanics, 2012,21(1):51-80.
[17] 程小全, 邹健, 张纪奎,等. 缝合复合材料可用性——含孔层合板的疲劳性能[J]. 航空学报, 2009, 30(5):867-871. CHENG X Q, ZOU J, ZHANG J K,et al. Properties of stitched composite laminates——fatigue performance of composite laminates with an open-hole[J]. Acta Aeronautica et Astronautica Sinica, 2009, 30(5):867-871(in Chinese).
[18] 尹昌平, 李建伟, 刘钧, 等. 缝合/RTM复合材料层合板的力学性能研究[J]. 材料导报, 2007, 21(11):136-138. YIN C P, LI J W, LIU J, et al. Research on mechanical properties of stitched/RTM composite laminates[J]. Materials Reports, 2007, 21(11):136-138(in Chinese).
[19] 盛仪, 熊克, 卞侃, 等. 拉伸状态下碳纤维复合材料T型接头的断裂行为[J].复合材料学报, 2013,30(6):185-190. SHENG Y, XIONG K, BIAN K. Fracture behavior of carbon fiber T-joints under tensile load[J]. Acta Materiae Compositae Sinica, 2013,30(6):185-190(in Chinese).
[20] TURON A, DÀVILA C G, CAMANHO P P, et al. An engineering solution for mesh size effects in the simulation of delamination using cohesive zone models[J]. Engineering Fracture Mechanics, 2007, 74(10):1665-1682.
[21] BIANCHI F, KOH T M, ZHANG X, et al. Finite element modelling of z-pinned composite T-joints[J]. Composites Science and Technology, 2012, 73:48-56.
[22] HUAN D J, LI Y, TAN Y, et al. On the assessment of the load-bearing capacity of Z-pinned composite T-joint under out-of-plane tension[J]. Journal of Reinforced Plastics and Composites, 2017, 36(22):1639-1650.
[23] LI M J, CHEN P H, LI X P, et al. Experimental and numerical study on the tensile properties of T-joints with low Z-pin volume density[J]. Polymer Composites, 2020, 41(1):258-270.

E-mail：hkxb@buaa.edu.cn

关于我们

期刊社服务

专业学科

封面文章

友情链接

主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

缝合复合材料T型接头拉伸载荷下的有限元数值模拟

Finite element numerical simulation of stitched composite T-joint under tensile load

RichHTML

PDF (PC)

可视化

摘要/Abstract

引用本文

使用本文

参考文献

相关文章 15

编辑推荐

Metrics

本文评价

[1]	龚煜廉, 张建国, 吴志刚, 褚光远, 范晓铎, 黄赢. 主动学习基自适应PC⁃Kriging模型的复合材料结构可靠度算法[J]. 航空学报, 2024, 45(8): 228982-228982.
[2]	贾文斌, 方磊, 张根, 史剑, 何泽侃, 宣海军. CNT树脂基复合材料断裂韧性的优化设计[J]. 航空学报, 2024, 45(7): 428971-428971.
[3]	张春云, 陈雄斌, 刘健, 崔苗. 酚醛树脂气凝胶复合材料热物性参数预测方法[J]. 航空学报, 2024, 45(6): 428848-428848.
[4]	黄领才. 纤维增强聚合物复合材料无损检测方法进展[J]. 航空学报, 2024, 45(5): 529697-529697.
[5]	高志廷, 马壮, 柳彦博. CVD-SiC阵列结构对ZrB₂/SiC涂层抗烧蚀性影响[J]. 航空学报, 2024, 45(3): 428842-428842.
[6]	张超, 曹勇, 赵振强, 张海洋, 孙建波, 王志华, 蔚夺魁. 树脂基复合材料在民用航空发动机中的应用与关键技术研究进展[J]. 航空学报, 2024, 45(2): 28556-028556.
[7]	马莹, 陈奡, 邓聪颖, 陈翔, 禄盛, 曾宪君. 纺织复合材料多尺度网格划分方法[J]. 航空学报, 2024, 45(10): 429180-429180.
[8]	杨倩, 王彦哲, 杨迪, 李泽众, 曲巍崴. 基于数据驱动的纤维增强复合材料自动铺放速度预测与规划[J]. 航空学报, 2024, 45(10): 429313-429313.
[9]	盛方怡, 杨国林, 孟凡通, 董志刚, 康仁科. 沉头孔螺旋铣削加工有限元仿真分析[J]. 航空学报, 2024, 45(1): 428690-428690.
[10]	王四季, 张羽薇, 黄开明, 吕彪, 赵海凤, 王虎, 廖明夫. 基于改进粒子群算法的直升机动力涡轮转子系统优化方法[J]. 航空学报, 2024, 45(1): 228608-228608.
[11]	黄永杰, 倪章松, 潘捷. 考虑冰层断裂与界面脱粘的电脉冲除冰仿真[J]. 航空学报, 2023, 44(S2): 729306-729306.
[12]	王宏越, 王兵, 方国东, 孟松鹤. 2.5D机织浅交弯联复合材料数字单元建模分析[J]. 航空学报, 2023, 44(9): 227478-227478.
[13]	韩剑, 孙士勇, 牛斌, 杨睿, 吴东江. 树脂基复合材料点阵结构的制造技术研究进展[J]. 航空学报, 2023, 44(9): 628255-628255.
[14]	王震宇, 王计真, 杨婧艺, 何鹏远, 潘成浩, 周凌波, 何成, 何欢. 基于新型粒子群算法的结构动力学热振模型修正[J]. 航空学报, 2023, 44(7): 226559-226559.
[15]	程旋, 赵亦希, 尤舒曼. 机器人柔性翻边成形轨迹优化[J]. 航空学报, 2023, 44(4): 426886-426886.