中温固化复合材料层压板分层缺陷注射修补工艺研究

玻璃钢/复合材料 ›› 2017, Vol. 0 ›› Issue (6): 85-88.

中温固化复合材料层压板分层缺陷注射修补工艺研究

龚志红¹,包啸¹,李建川¹,苏建²

1.中航工业成都飞机工业(集团)有限责任公司,成都610000;
2.南京航空航天大学,南京211100

收稿日期:2016-12-23 出版日期:2017-06-28 发布日期:2017-06-28
通讯作者: 崔益华(1970-),男,教授,博士,主要从事复合材料方面的研究,cuiyh@nuaa.edu.cn。
作者简介:龚志红(1984-),女,高级工程师,主要从事碳纤维复合材料构件制造方面的研究。

STUDY ON INJECTING REPAIR TECHNOLOGY OF DELAMINATION FLAW OF MODERATE TEMPERATURE CURING COMPOSITE LAMINATES

GONG Zhi-hong¹, BAO Xiao¹, LI Jian-chuan¹, SU Jian²

1.AVIC Chengdu Aircraft Industrial (Group) Co., Ltd., Chengdu 610000, China;
2.Nanjing University of Aeronautics and Astronautics, Nanjing 211100, China

Received:2016-12-23 Online:2017-06-28 Published:2017-06-28

摘要/Abstract

摘要： 通过预埋石英砂,制备了复合材料层压板分层缺陷试样。采用注射修补法对分层缺陷试样进行了修补。使用电钻在缺陷试样单侧打注胶孔,通过注胶孔将DG-8胶黏剂注入缺陷区域,利用热补仪将注胶后的试样固化。对修补后的试样进行了无损检测、力学性能测试和微观结构分析。结果表明,修补后的试样拉伸和压缩强度恢复率均达85%以上,试样修补区的DG-8胶黏剂固化良好。

关键词: 层压板, 分层缺陷, 注射修补, 强度恢复率

Abstract: In this paper, the delamination flaw samples of composite laminates were prepared by means of pre-buried quartz sand. The delamination flaw samples of composite laminates were repaired by the injecting repair method. The injection hole was punched with an electric drill in the side of sample of delamination flaw. The DG-8 adhesive was injected from the injection hole to delamination flaw area. The samples were heated to cure by the hot bonder. Mechanical property tests of the repaired samples were carried out. Nondestructive testing and microstructure analysis were also performed. The results showed that, tensile and compressive strength of repaired samples recovery rate was more than 85%, and the DG-8 adhesive of repair area achieved good curing condition.

Key words: laminates, delamitation flaw, injecting repair, recovery rate of strength

中图分类号:

TB332

龚志红,包啸,李建川,苏建. 中温固化复合材料层压板分层缺陷注射修补工艺研究[J]. 玻璃钢/复合材料, 2017, 0(6): 85-88.

GONG Zhi-hong, BAO Xiao, LI Jian-chuan, SU Jian. STUDY ON INJECTING REPAIR TECHNOLOGY OF DELAMINATION FLAW OF MODERATE TEMPERATURE CURING COMPOSITE LAMINATES[J]. Fiber Reinforced Plastics/Composites, 2017, 0(6): 85-88.

参考文献

[1] 梁重云, 曾竟成. 复合材料补片胶接修补研究进展[J]. 宇航材料工艺, 2002, 32(4): 7-11.
[2] 孟凡颢, 陈绍杰, 董善艳, 等. 复合材料损伤结构胶接补强修补分析及设计[J]. 飞机设计, 2002(1): 18-21.
[3] 李亮, 贾普荣, 王文贵, 等. 复合材料铺层拼接层间断裂韧性的试验研究[J]. 应用力学学报, 2009, 26(2): 348-351.
[4] Campilho R D S G, Moura M F S F D, Ramantani D A, et al. Tensile behaviour of three-dimensional carbon-epoxy adhesively bonded single-and double-strap repairs[J]. International Journal of Adhesion & Adhesives, 2009, 29(6): 678-686.
[5] 贺福, 孙微. 碳纤维复合材料在大飞机上的应用[J]. 高科技纤维与应用, 2007, 32(6): 5-8.
[6] 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.
[7] Keith Armstrong. Civil Aircraft Composite Structure Repair Technology[J]. 1999, 14(4): 198-210.
[8] 陈绍杰. 复合材料结构修理指南[M]. 北京: 航空工业出版社, 2001.
[9] GV Valente L L, Manso I S, Münchow E A, et al. Repair bond strength of resin composite with experimental primers-effect of formulation variables[J]. Journal of Adhesion Science and Techology, 2016: 1-10.
[10] 肖加余, 肖中璠, 杨金水,等. 碳纤维/双马来酰亚胺复合材料修复性能[J]. 国防科技大学学报, 2016(1): 1-8.
[11] Slattery P G, Mccarthy C T, O′Higgins R M. Assessment of residual strength of repaired solid laminate composite materials through mechanical testing[J]. Composite Structures, 2016(147): 122-130.
[12] 杨龙英. 修补固化方式对树脂基复合材料修补性能的影响研究[J]. 塑料工业, 2015, 43(9): 83-86.
[13] 董柳杉, 孙凯, 孔娇月, 等. 大厚度复合材料层板结构损伤的热补仪修补工艺研究[J]. 航空维修与工程, 2016(1): 69-72.
[14] 曹韦俊, 周光明. 含损伤复合材料加筋板强度分析及修补研究[J]. 玻璃纤维, 2016(2): 22-29.
[15] 王莹. 复合材料缺陷修补技术[J]. 粘接, 2015(6): 83-86.
[16] Bulluck J W, Rix B A. Ultraviolet light curing compositions for composite repair: US, US7291656[P]. 2007.
[17] 魏建义. 航空复合材料结构修补技术与应用[J]. 橡塑技术与装备, 2015(24): 146-148.
[18] 王云英, 孟江燕, 丁祖群, 等. 航空先进聚合物基复合材料的修补[J]. 航空维修与工程, 2008(2): 27-30.