碳纤维复合材料大直径孔制孔方法的研究

玻璃钢/复合材料 ›› 2018, Vol. 0 ›› Issue (6): 48-53.

碳纤维复合材料大直径孔制孔方法的研究

王共冬^1,2, 李映池^1*, 彭天¹, 李南¹

1.沈阳航空航天大学航空航天工程学部,沈阳100136;
2.沈阳航空航天大学航空制造工艺数字化国防重点实验室,沈阳100136

收稿日期:2017-12-18 出版日期:2018-06-28 发布日期:2018-06-28
通讯作者: 李映池(1992-),男,在读硕士研究生,主要从事复合材料方面的研究,karldoenitz1@126.com。
作者简介:王共冬(1979-),男,博士,副教授,主要从事复合材料方面的研究。
基金资助:
国家自然科学基金(51303107);国防“十二五”基础科研(A352*******)

RESEARCH ON LARGE DIAMETER HOLE DRILLING METHODOF THE CARBON FIBER REINFORCED PLASTICS

WANG Gong-dong^1,2, LI Ying-chi^1*, PENG Tian¹, LI Nan¹

1.Shenyang Aerospace University, School of Aerospace Engineering, Shenyang 110136, China;
2.Shenyang Aerospace University, Key Laboratory of Fundamental Science for National Defenceof Aeronautical Digital Manufacturing Process, Shenyang 110136, China

Received:2017-12-18 Online:2018-06-28 Published:2018-06-28

摘要/Abstract

摘要： 在航空工业领域中,碳纤维复合材料(CFRP)常常会加工大直径孔。在加工大直径孔时,无预制孔钻削直接加工出的孔会出现纤维撕裂、纤维脱出以及孔内壁分层等严重缺陷。首先重点分析了无预制孔钻削、螺旋铣和不同直径预制孔的加工原理和轴向力情况,并估计临界轴向力值;其次使用无预制孔钻削、螺旋铣和不同直径预制孔三种方法,建立对比实验,并对这三种方法的受力情况以及加工质量进行分析。结果表明,钻削的轴向力主要由麻花钻头的横刃提供,而轴向力是导致分层的主要原因。当轴向力小于临界轴向力时,分层明显减小,而由于消除了横刃的影响使得预制孔方法加工时轴向力降低47%至61%,出口处分层因子较无预制孔钻削减小83%,因此预制孔方法在制造大直径孔时表现突出。

关键词: 碳纤维增强复合材料, 螺旋铣, 预制孔, 分层损伤

Abstract: The Carbon Fiber Reinforced Plastics (CFRP) are often processed large-diameter holes in the aerospace industry. In the processing of large-diameter holes, the drilling without pilot hole will cause fiber tear, delamination in hole wall and other serious defects. This paper focuses on the processing principle and axial force of helical milling and prefabricated holes, and estimates the critical thrust force of drilling. In this paper, three methods of helical milling, pre-drilling with a pilot hole and without pilot hole drilling are used to establish the comparative experiment. And thrust force and quality of processing for these three methods are analyzed. The results show that the thrust force of drilling is mainly provided by the chisel edge of the twist drill bit, and thrust force is the main result of delamination. When the thrust force is less than the critical thrust force, the delamination is significantly reduced. The thrust force is reduced by 47% to 61% due to the elimination of the influence of chisel edge.The delamination factor at the exit level is 83% lower than drilling without pilot hole. Therefore, the method of pre-drilling with a pilot hole is outstanding when manufacturing large-diameter holes.

Key words: CFRP, helical milling, pilot hole, lamination

中图分类号:

TB332

王共冬, 李映池, 彭天, 李南. 碳纤维复合材料大直径孔制孔方法的研究[J]. 玻璃钢/复合材料, 2018, 0(6): 48-53.

WANG Gong-dong, LI Ying-chi, PENG Tian, LI Nan. RESEARCH ON LARGE DIAMETER HOLE DRILLING METHODOF THE CARBON FIBER REINFORCED PLASTICS[J]. Fiber Reinforced Plastics/Composites, 2018, 0(6): 48-53.

参考文献

[1] Sakuma K, Yokoo Y, Seto M. Study on drilling of reinforced plastics (GFRP and CFRP): Relation between tool material and wear behavior[J]. Transactions of the Japan Society of Mechanical Engineers C, 1984, 27(228): 1237-1244.
[2] 王奔, 高航, 郭东明. 树脂固化温度与纤维铺设方式对C/E复合材料制孔质量的影响[J]. 机械工程学报, 2011, 47(12): 19-25.
[3] Wang B, Gao H, Zhang R, et al. Grind-drilling of carbon/epoxy composites based on air cooling method[J]. International Journal of Abrasive Technology, 2011, 4(4): 363-375.
[4] 鲍永杰, 高航, 马海龙,等. 单向C/E复合材料磨削制孔温度场模型的研究[J]. 机械工程学报, 2012, 48(1): 169-176.
[5] König W, Gr aßP. Quality definition and assessment in drilling of fibre reinforced thermosets[J]. CIRP Annals-Manufacturing Technology, 1989, 38(1): 119-124.
[6] Persson E, Eriksson I, Zackrisson L. Effects of hole machining defects on strength and fatigue life of composite laminates[J]. Compos-ites Part A Applied Science & Manufacturing, 1997, 28(2): 141-151.
[7] 王震,刘汉良,李亮, 等. 碳纤维复合材料孔加工质量试验研究[J]. 宇航材料工艺, 2013, 43(6): 88-90.
[8] Denkena B, Boehnke D, Dege J H. Helical milling of CFRP-titanium layer compounds[J]. Cirp Journal of Manufacturing Science & Technology, 2008, 1(2): 64-69.
[9] Kalla D, Sheikh-Ahmad J, Twomey J. Prediction of cutting forces in helical end milling fiber reinforced polymers[J]. International Journal of Machine Tools & Manufacture, 2010, 50(10): 882-891.
[10] Won M S, Dharan C K H. Chisel edge and pilot hole effects in drilling composite laminates[J]. Journal of Manufacturing Science & Engineering, 2002, 124(2): 242-247.
[11] Tsao C C. The effect of pilot hole on delamination when core drill drilling composite materials[J]. International Journal of Machine Tools & Manufacture, 2006, 46(12-13): 1653-1661.
[12] Dharan C K H. Fracture mechanics of composite materials[J]. Journal of Engineering Materials & Technology, 1978, 100(3): 233.
[13] Ho-Cheng H, Dharan C K H. Delamination during drilling in composite laminates[J]. Journal of Engineering for Industry, 1990, 112(3): 236-239.
[14] Saghizadeh H, Dharan C K H. Delamination fracture toughness of graphite and aramid epoxy composites[J]. Journal of Engineering Materials & Technology, 1986, 108(4): 290.
[15] Timoshenko, Stephen P. Theory of plates and shells[J]. Studies in Mathematics & Its Applications Elsevier Amsterdam, 1959, 6(3760):
606.
[16] Karimi N Z, Heidary H, Minak G, et al. Effect of the drilling process on the compression behavior of glass/epoxy laminates[J]. Composite Structures, 2013, 98(3):59-68.
[17] Zhou Z, Sun G, Chen X, et al. Quantitative characterization test of fastening hole delamination in composites with laser ultrasonics[J]. Hangkong Xuebao/acta Aeronautica Et Astronautica Sinica, 2014, 35(8): 2348-2354.
[18] Qi Z, Zhang K, Li Y, et al. Critical thrust force predicting model-ing for delamination-free drilling of metal-FRP stacks[J]. Composite Structures, 2014, 107(1): 604-609.