Z-pin增强复合材料帽型单加筋板弯曲性能

doi:10.7527/S1000-6893.2016.0109

材料工程与机械制造

本期目录 | 过刊浏览 | 高级检索

前一篇 | 后一篇

Z-pin增强复合材料帽型单加筋板弯曲性能

李吻, 李勇, 还大军, 褚奇奕, 肖军

南京航空航天大学材料科学与技术学院, 南京 210016

收稿日期:2016-01-13 修回日期:2016-04-01 出版日期:2016-12-15 发布日期:2016-04-06
通讯作者: 李勇,Tel.:025-84892980,E-mail:lyong@nuaa.edu.cn E-mail:lyong@nuaa.edu.cn
作者简介:李吻,女,硕士研究生。主要研究方向:先进复合材料三维增强技术。Tel.:025-84892980,E-mail:liwen1206@126.com;李勇,男,博士,教授,博士生导师。主要研究方向:先进复合材料自动化制造及工艺。Tel.:025-84892980,E-mail:lyong@nuaa.edu.cn
基金资助:
航空科学基金（2015ZE52049）；国家“973”计划（2014CB046501）；江苏高校优势学科建设工程

Bending performance of composite single hat stiffener wall structure reinforced by Z-pin

LI Wen, LI Yong, HUAN Dajun, CHU Qiyi, XIAO Jun

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

Received:2016-01-13 Revised:2016-04-01 Online:2016-12-15 Published:2016-04-06
Supported by:
Aeronautical Science Foundation of China (2015ZE52049); National Basic Research Program of China (2014CB046501); A Project Funded by the Priority Academic Program Development of Jiangsu High Education Institutions

摘要/Abstract

摘要：

针对复合材料帽型加筋壁板结构弯曲承载性能差的缺点，采用Z-pin增强技术提高弯曲承载性能。为研究Z-pin直径、体积分数、增强区长度对复合材料帽型加筋壁板弯曲性能的影响，制备了不同参数的Z-pin增强帽型加筋壁板试样并开展三点弯曲试验，对Z-pin增强机理及试样失效机制进行了分析。结果表明：随着体积分数的增加，由于Z-pin的桥联作用，Z-pin增强帽型加筋壁板弯曲性能提高，同时由于Z-pin植入产生的损伤增加，通过理论分析得到当Z-pin体积分数为2.6%时，弯曲峰值力达到最大值6.1 kN；Z-pin直径对帽型加筋壁板弯曲峰值力影响不显著；当Z-pin增强区长度为总长度的48%时，Z-pin增强帽型加筋壁板弯曲峰值力与全部植入Z-pin时基本相当。

关键词: 树脂基复合材料, 帽型加筋壁板, Z-pin, 连接性能, 三点弯曲

Abstract:

The Z-pin reinforcing technology is used to improve the less good bending bearing performance of composite hat stiffener wall structure. In order to study the influence of Z-pin volume fraction, Z-pin diameter and Z-pin reinforcing region length on the performance of hat stiffener wall structure polymer composites, the samples reinforced by Z-pin with different parameters are prepared and tested under three-point bending load. The Z-pin reinforcing mechanism and samples' failure mechanism are analyzed. The results show that the bending property of hat stiffener wall structures reinforced by Z-pin is improved with the increase of Z-pin volume fraction due to the bridging role of Z-pin, and the damage caused by Z-pin inserting increases. When the volume fraction of Z-pin is 2.6%, the bending peak load reaches the maximum value 6.1 kN through theoretical analysis. The effect of the diameter of Z-pin on the bending load of stiffener wall structures is not obvious. When the length of the Z-pin reinforcing region is 48% of the total length, the bending peak load of hat stiffener wall structure reinforced by Z-pin equals the bending peak load of samples with 100% Z-pin inserting length.

Key words: polymer composites, hat stiffener, Z-pin, joint performance, three-point bending

中图分类号:

V414.8
TB332

李吻, 李勇, 还大军, 褚奇奕, 肖军. Z-pin增强复合材料帽型单加筋板弯曲性能[J]. 航空学报, 2016, 37(12): 3843-3852.

LI Wen, LI Yong, HUAN Dajun, CHU Qiyi, XIAO Jun. Bending performance of composite single hat stiffener wall structure reinforced by Z-pin[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2016, 37(12): 3843-3852.

参考文献

[1] 韩旭. 帽型复合材料加筋壁板结构优化设计[D]. 南京:南京航空航天大学, 2009:1-5. HAN X. Structure optimization of composite hat-stiffened panel[D]. Nanjing:Nanjing University of Aeronautics and Astronautics, 2009:1-5(in Chinese).
[2] 李玉成, 温海波, 安静波. 复合材料加筋壁板设计、分析与试验研究[J]. 纤维复合材料, 2011(4):14-18. LI Y C, WEN H B, AN J B. Design, analysis, experimental studies of composite stiffened panel[J]. Fiber Composite, 2011(4):14-18(in Chinese).
[3] KRUEGER R, CVITKOVICH M K, O'BRIEN T K, et al. Testing and analysis of composite skin/stringer debonding under multi-axial loading[J]. Journal of Composite Materials, 2000, 34(15):1263-1300.
[4] KRUEGER R, MINGUET P J. Analysis of composite skin-stiffener debond specimens using a shell/3D modeling technique[J]. Composite Structures, 2007, 81(1):41-59.
[5] BERTOLINI J, CASTANIE B, BARRAU J J, et al. An experimental and numerical study on omega stringer debonding[J]. Composite Structures, 2008, 86(1-3):233-242.
[6] 叶强, 夏翔, 肖闪闪, 等. 复合材料整体加筋板的七点弯曲试验和数值分析[J]. 南京航空航天大学学报, 2011, 43(4):470-474. YE Q, XIA X, XIAO S S, et al. Numerical and experimental analysis on seven-point bending test of integrated composite panels[J]. Journal of Nanjing University of Aeronautics & Astronautics, 2011, 43(4):470-474(in Chinese).
[7] 孙晶晶, 张晓晶, 宫占峰, 等. 复合材料帽型筋条脱粘的失效机理分析[J]. 航空学报, 2013, 34(7):1615-1626. SUN J J, ZHANG X J, GONG Z F, et al. Failure mechanism study on omega stringer debonding[J]. Acta Aeronautica et Astronautica Sinica, 2013, 34(7):1615-1626(in Chinese).
[8] 孙晶晶, 张晓晶, 汪海, 等. 复合材料帽型加筋结构界面脱粘的实验和数值分析[C]//第17届全国复合材料学术会议论文集. 北京:中国复合材料学会, 2012:80-86. SUN J J, ZHANG X J, WANG H, et al. An experimental and numerical study on composite omega stringer debonding[C]//17th National Conference Proceedings on Composite Materials. Beijing:Chinese Society for Composite Materials, 2012:80-86(in Chinese).
[9] 徐建, 印春伟, 童明波. 复合材料T型加筋结构连接界面性能研究[J]. 江苏航空, 2012(S1):111-113. XU J, YIN C W, TONG M B. The study of joint interface performance of composite T stiffener wall structure[J]. Jiangsu Aviation, 2012(S1):111-113(in Chinese).
[10] MOURITZ A P, BANNISTER M K, FALZON P J, et al. Review of application for advanced three-dimensional fiber textile composites[J]. Composites Part A:Applied Science and Manufacturing, 1990, 30(12):1445-1461.
[11] PATRIDGE I K, CARTIE D D R, BONNINGTON T. Manufacture and performance of Z-pinned composite[C]//Advanced Polymeric Composite. Katz Boca Raton:CRC Press, 2003:103-139.
[12] MOURITZ A P. Review of z-pinned composite laminates[J]. Composites Part A:Applied Science and Manufacturing, 2007, 38(12):2383-2397.
[13] 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.
[14] BYRD L W, BIRMAN V. Effect of temperature on stresses and delamination failure of Z-pinned joints[J]. International Journal of Mechanical Sciences, 2006, 48(9):938-949.
[15] 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.
[16] GREENHALGH E, LEWIS A, BOWEN R, et al. Evaluation of toughening concepts at structural features in CFRP-Part I:Stiffener pull-out[J]. Composites Part A:Applied Science and Manufacturing, 2006, 37(10):1521-1535.
[17] NANAYAKKARA A M, FEIH S, MOURITZ A P. Improving the fracture resistance of sandwich composite T-joints by z-pinning[J]. Composite Structures, 2013, 96:207-215.
[18] JI H, KWEON J H, CHOI J H. Fatigue characteristics of stainless steel pin-reinforced composite hat joints[J]. Composite Structure, 2014, 108:49-56.
[19] 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, 2007:3. TAO Y Q. The connecting performance of the single-lap joint reinforced by Z-pin[D]. Xi'an:Northwestern Polytechnical University, 2007:3(in Chinese).
[20] 董晓阳, 李勇, 张向阳, 等. Z-pin增强树脂基复合材料单搭接接头连接性能研究[J]. 航空学报, 2013, 35(5):1302-1310. DONG X Y, LI Y, ZHANG X Y, et al. Study on performance of polymer composites single lap joints reinforced by Z-pin[J]. Acta Aeronautica et Astronautica Sinica, 2013, 35(5):1302-1310(in Chinese).
[21] 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 C H, YAN Y. Modeling and analysis of z-pin reinforcing in through-thickness direction of composite T-joint[J]. Acta Materiae Composite Sinica, 2010, 27(6):152-157(in Chinese).
[22] KIM G H, CHOI J H, KWEON J H. Manufacture and performance evaluation of the composite hat-stiffened panel[J]. Composite Structures, 2010, 92(9):2276-2284.
[23] 蒲永伟, 湛利华. 航空先进复合材料帽型加筋构件制造关键技术探究[J]. 航空制造技术, 2015(4):78-81. PU Y W, ZHAN L H. Study on the key manufacturing technology of aeronautical advanced composite hat-stiffened structures[J]. Aeronautical Manufacturing Technology, 2015(4):78-81(in Chinese).

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

Z-pin增强复合材料帽型单加筋板弯曲性能

Bending performance of composite single hat stiffener wall structure reinforced by Z-pin

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]	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.
[2]	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.
[3]	张伟, 王彬文, 樊俊铃, 詹绍正, 焦婷, 杨宇. 基于多模式超声成像的CFRP冲击损伤无损表征与冲击后压缩强度预测[J]. 航空学报, 2023, 44(1): 426635-426635.
[4]	姜春阳, 吴利辉, 常云龙, 薛鹏, 倪丁瑞, 肖伯律, 马宗义. 铝合金与树脂基复合材料的铆接/搅拌摩擦搭接复合焊接[J]. 航空学报, 2022, 43(2): 625190-625190.
[5]	程晖, 樊新田, 徐冠华, 杨语, 王岚. 航空复合材料结构精密干涉连接技术综述[J]. 航空学报, 2021, 42(10): 524876-524876.
[6]	崔文斌, 陈煊, 陈超, 程礼, 丁均梁, 张晖. CFRP超高周疲劳损伤演化过程[J]. 航空学报, 2020, 41(1): 223212-223212.
[7]	熊文磊, 苏佳智, 刘小林, 韩小勇, 戚经革, 宋天成. 热压罐工艺帽型加筋壁板长桁胶接变形问题[J]. 航空学报, 2019, 40(12): 423108-423108.
[8]	沈裕峰, 李勇, 王鑫, 还大军. 湿热环境下K-cor夹层复合材料的力学性能[J]. 航空学报, 2016, 37(7): 2303-2311.
[9]	李吻, 李勇, 还大军, 褚奇奕, 陈浩然. Z-pin增强复合材料帽型加筋壁板接头拉伸性能[J]. 航空学报, 2016, 37(6): 2003-2012.
[10]	沈裕峰, 李勇, 还大军, 王鑫. 低速冲击对K-cor夹层结构力学性能的影响[J]. 航空学报, 2016, 37(12): 3853-3863.
[11]	田文平, 肖军, 李金焕, 徐挺, 刘婷. 空间光学结构用改性氰酸酯树脂及其复合材料性能[J]. 航空学报, 2016, 37(11): 3520-3527.
[12]	褚奇奕, 肖军, 李勇, 张向阳, 王敏. 碳纤维增强环氧Z-pin拔脱性能[J]. 航空学报, 2015, 36(4): 1312-1319.
[13]	董晓阳, 李勇, 张向阳, 肖军, 李吻. 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.
[14]	张向阳, 李勇, 褚奇奕, 肖军, 董晓阳. Z-pin点阵分布对层合板面内压缩性能的影响[J]. 航空学报, 2014, 35(1): 195-202.
[15]	郝继军;张佐光;张蕾;李敏;孙志杰. Z-pin植入参数对X-Cor夹层复合材料力学性能的影响[J]. 航空学报, 2008, 29(3): 763-768.