Volume 33 Issue 3
Mar.  2018
Turn off MathJax
Article Contents
Impact resistance performances of resin matrix composite single lap joints reinforced by Z-pin[J]. Journal of Aerospace Power, 2018, 33(3): 671-682. doi: 10.13224/j.cnki.jasp.2018.03.021
Citation: Impact resistance performances of resin matrix composite single lap joints reinforced by Z-pin[J]. Journal of Aerospace Power, 2018, 33(3): 671-682. doi: 10.13224/j.cnki.jasp.2018.03.021

Impact resistance performances of resin matrix composite single lap joints reinforced by Z-pin

doi: 10.13224/j.cnki.jasp.2018.03.021
  • Received Date: 2016-09-14
  • Publish Date: 2018-03-28
  • To study the impact resistance performances of resin matrix composite joints reinforced by Z-pin, single lap joint specimens reinforced by Z-pin were prepared. The crack propagation along Z-pin/laminates interface was compared with different resins matrix of Z-pin. Z-pin pullout and lap shear tests were carried out to study the after-impact pullout strength of Z-pin and after-impact shear strength of single lap joint, respectively. The ultrasonic C-scan method combined with finite element simulation was utilized to explore the delamination damage area of joint interface. The results showed that compared with the BMI resin matrix Z-pin, the resistance performance between epoxy Z-pin/epoxy laminates was stronger at the same impact energy. With the increase of impact energy, the crack propagation was more significant. Z-pin reinforced resin matrix composites remarkably reduced delamination damage area and improved the after-inpact shear strength. The delamination damage area of joint reinforced by Z-pin was 40%, and its reduction of after-impact shear strength was 24.89% when Z-pins volume fraction was 1.5% and diameter was 0.5mm.With the increase of Z-pin volume fraction, the delamination damage area decreased gradually, while the after-impact shear strength increased firstly and then decreased. The damage area of lap surface increased as the increment of Z-pin diameter while the after-impact shear strength decreased. The results of finite element modeling were consistent with the test results.

     

  • loading
  • [1]
    张鹏,朱强,秦鹤勇,等.航空发动机用耐高温材料的研究进展[J].材料导报,2014,28(11):27-31.ZHANG Peng,ZHU Qiang,QIN Heyong,et al.Research progress of high temperature materials for aero-engine[J].Materials Review,2014,28(11):27-31.(in Chinese)
    [2]
    谢鸣九.复合材料连接[M].上海:上海交通大学出版社,2011:4-5.
    [3]
    KIM K S,YOO J S,YI Y M,et al.Failure mode and strength of unidirectional composite single lap bonded joints with different bonding methods[J].Composite Structures,2006,72(4):477-485.
    [4]
    VAIDYA U K,GAUTAM A R S,HOSUR M,et al.Experimental-numerical studies of transverse impact response of adhesively bonded lap joints in composite structures[J].International Journal of Adhesion and Adhesives,2006,26(3):184-198.
    [5]
    KIM J H,PARK B J,HAN Y W.Evaluation of fatigue characteristics for adhesively-bonded composite stepped lap joint[J].Composite Structures,2004,66(1):69-75.
    [6]
    孙志刚,宋迎东,廉英琦,等.弱界面粘结对复合材料有效性能的影响[J].航空动力学报,2005,20(6):915-919.SUN Zhigang,SONG Yingdong,LIAN Yingqi,et al.Composite mechanical behavior with weak interfacial bonding[J].Journal of Aerospace Power,2005,20(6):915-919.(in Chinese)
    [7]
    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.Pultrusion and properties of the twisted carbon fiber/phenolic resin Z-pin[J].Journal of Aerospace Power,2015,30(7):1638-1644.(in Chinese)
    [8]
    孙先念,郑长良.层合复合材料z-pinning增强技术的力学进展[J].航空学报,2006,27(6):1194-1202.SUN Xiannian,ZHENG Changliang.Advance on modeling through-the-thickness reinforcement of laminated composite by z-pinning[J].Acta Aeronautica et Astronautica Sinaca,2006,27(6):1194-1202.(in Chinese)
    [9]
    CARTI D D R,TROULIS M,PARTRIDGE I K.Delamination of Z-pinned carbon fibre reinforced laminates[J].Composites Science and Technology,2006,66(6):855-861.
    [10]
    RUGG K L,COX B N,MASSABO R.Mixed mode delamination of polymer composite laminates reinforced through the thickness by Z-fibers[J].Composites:Part A Applied Science and Manufacturing,2002,33(2):177-190.
    [11]
    CHANG P,MOURITZ A P,COX B N.Properties and failure mechanisms of pinned composite lap joints in monotonic and cyclic tension[J].Composites Science and Technology,2006,66(13):2163-2176.
    [12]
    GREENHALGH E,LEWIS A,BOWEN R,et al.Evaluation of toughening concepts at structural features in CFRP:Part Ⅰ stiffener pull-off[J].Composites:Part A Applied Science and Manufacturing,2006,37(10):1521-1535.
    [13]
    陶永强.Z-pin增强陶瓷基复合材料接头的连接性能[D].西安:西北工业大学,2007.TAO Yongqiang.The connecting performance of 2-dceramic matrix composite joint reinforced by Z-pins[D].Xian:Northwestern Polytechnical University,2007.(in Chinese)
    [14]
    董晓阳,李勇,张向阳,等.Z-pin增强树脂基复合材料单搭接连接性能[J].航空学报,2014,35(5):1302-1310.DONG Xiaoyang,LI Yong,ZHANG Xiangyang,et al.Performance of polymer composite single lap joins reinforced by Z-pin[J].Acta Aeronautica et Astronautica Sinica,2014,35(5):1302-1310.(in Chinese)
    [15]
    GRASSI M,ZHANG X,MEO M.Prediction of stiffness and stresses in z-fibre reinforced composite laminates[J].Composites:Part A Applied Science and Manufacturing,2002,33(12):1653-1664.
    [16]
    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(1):209-216.TENG Jin,LI Bintai,ZHUANG Zhuo.A study on low-velocity impact danmage of Z-pin reinforced laminates[J].Engineering Mechanics,2006,23(1):209-216.(in Chinese)
    [17]
    KOH T M,ISA M D,FEIH S,et al.Experimental assessment of the damage tolerance of z-pinned T-stiffened composite panels[J].Composites:Part B Engineering,2013,44(1):620-627.
    [18]
    董晓阳.Z-pin增强树脂基复合材料单搭接接头连接性能研究[D].南京:南京航空航天大学,2013.DONG Xiaoyang.Study on performance of polymer composites single lap joints reinforced by Z-pin[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2013.(in Chinese)
    [19]
    DAI S C,YAN W,LIU H Y,et al.Experimental study on Z-pin bridging law by pullout test[J].Composites Science and Technology,2004,64(16):2451-2457.
    [20]
    崔海坡,温卫东,张阿龙.不同冲击能量对层合板损伤及剩余强度的影响[J].航空动力学报,2015,30(10):2331-2337.CUI Haipo,WEN Weidong,ZHANG Along.Influence of different impact energies on damage[J].Journal of Aerospace Power,2015,30(10):2331-2337.(in Chinese)
    [21]
    HALDAR S,CAPUTO D,BUESKING K,et al.Flexural behavior of singly curved X-Cor sandwich composite structures:experiment and finite element modeling[J].Composite Structures,2015,129(1):70-79.
    [22]
    CHANG P,MOURITZ A P,COX B N.Properties and failure mechanisms of Z-pinned laminates in monotonic and cyclic tension[J].Composites:Part A Apllied Science and Manufacturing,2006,37(10):1501-1513.
    [23]
    CHANG P,MOURITZ A P,COX B N.Flexural properties of Z-pinned laminates[J].Composites:Part A Apllied Science and Manufacturing,2007,38(2):244-251.
    [24]
    MOURITZ A P.Delamination properties of Z-pinned composites in hot-wet environment[J].Composites:Part A Apllied Science and Manufacturing,2013,52:134-142.
    [25]
    SONG M C,SANKAR B V,SUBHASH G.et al.Analysis of mode Ⅰ delamination Z-pinned composites using a non-dimensional analytical model[J].Composites:Part B Engineering,2012,43(4):1776-1784.
    [26]
    MOURITZ A P.Review of z-pinned composite laminates[J].Composite:Part A Applied Science and Manufacturing,2007,38(12):2383-2397.
    [27]
    REIS P N B,ANTUNES F J V,FERREIRA J A M.Influence of superposition length on mechanical resistance of single-lap adhesive joints[J].Composite Structures,2005,67(1):125-133.
    [28]
    马丹.Z-pin增强双马来酰亚胺层合板制备及力学性能研究[D].南京:南京航空航天大学,2011.MA Dan.Research on preparation process and mechanical properties Z-pinned BMI composites laminates[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2011.(in Chinese)
  • 加载中

Catalog

    通讯作者: 陈斌, bchen63@163.com
    • 1. 

      沈阳化工大学材料科学与工程学院 沈阳 110142

    1. 本站搜索
    2. 百度学术搜索
    3. 万方数据库搜索
    4. CNKI搜索

    Article Metrics

    Article views (949) PDF downloads(606) Cited by()
    Proportional views
    Related

    /

    DownLoad:  Full-Size Img  PowerPoint
    Return
    Return