碳纤维-金属网增强复合材料低速冲击和界面损伤机制

万云; 刘一辉; 李浩; 姚剑; 余粤凯; 赵志博

doi:10.13801/j.cnki.fhclxb.20230222.007

碳纤维-金属网增强复合材料低速冲击和界面损伤机制

doi: 10.13801/j.cnki.fhclxb.20230222.007

万云^1, ,,
刘一辉¹,
李浩¹,
姚剑¹,
余粤凯¹,
赵志博²

1.
华东交通大学　土木建筑学院，南昌 330013
2.
中国人民解放军91049部队，青岛266102

基金项目: 国家自然科学基金青年基金(12002126)；江西省自然科学基金(20224 BAB201016)

详细信息

通讯作者:
万云，博士，副教授，硕士生导师，研究方向为复合材料损伤表征和预报　E-mail：wanyun0505@163.com

中图分类号: TB331
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- 被引次数: 0
出版历程
- 收稿日期: 2022-11-28
- 修回日期: 2023-01-09
- 录用日期: 2023-01-20
- 网络出版日期: 2023-02-22
- 刊出日期: 2023-11-01

Low-velocity impact and interlaminar damage mechanism of carbon fiber-metal mesh reinforced composites

WAN Yun^{1
, ,},
LIU Yihui¹,
LI Hao¹,
YAO Jian¹,
YU Yuekai¹,
ZHAO Zhibo²

1.
School of Civil Engineering and Architecture, East China Jiaotong University, Nanchang 330013, China
2.
91049th Unit, PLA (The Chinese People's Liberation Army), Qingdao 266102, China

Funds: National Natural Science Foundations of China (12002126); Jiangxi Province Science Foundation (20224 BAB201016)

摘要

摘要: 采用热固性环氧斜纹编织预浸料、菱形的不锈钢丝网和铝合金丝网，制备了4种不同铺层结构的复合材料板。通过低速冲击和冲击后压缩(CAI)试验，研究混杂金属网结构在不同能级冲击下的损伤行为及冲击后的剩余压缩强度；同时采用双悬臂梁(DCB)拉伸和末端切口弯曲(ENF)试验，进而研究了金属网层对碳纤维复合材料层间断裂性能的影响。通过使用超声波扫描和二维虚拟图像关联(2D-VIC)测试系统对比了冲击后试件内部的损伤程度及冲击后压缩过程中变形云图，以揭示其增强机制。结果表明：金属网结构的引入可以改善面板的塑性和冲击能量影响范围，提高冲击能量吸收能力、CAI强度和层间剪切性能。此外，在混杂结构的ENF测试中，界面的破坏不仅有基体的破坏，还存在纤维的剪切断裂。
- 碳纤维增强聚合物 /
- 金属丝网增强 /
- 低速冲击 /
- 层间断裂韧性 /
- 损伤机制
Abstract: Four kinds of composite plates with different ply structures were fabricated, which are composed of thermosetting epoxy twill woven prepreg, diamond-shaped stainless steel wire mesh and aluminum alloy wire mesh. Further, low-velocity impact and compression after impact (CAI) experiments were conducted to study their damage behavior and post-impact residual compressive strength of the hybrid metal mesh structure under different energy levels. According to the double cantilever beam (DCB) tensile test and the end-notched flexure (ENF) test, the effects of metal mesh layers on the interlaminar fracture performance of carbon fiber composites were investigated. Ultrasonic scanning and two-dimensional virtual image correlation (2D-VIC) test system were employed to examine the damaged degree inside the specimen after impact and the deformation contour of the surface during the CAI test, then the strengthening mechanism were illuminated. The results show that the addition of metal mesh layers can improve the plasticity of the panel and effect area of incident energy, resulting in the improvement of absorbing impact energy, CAI strength and interlaminar shear performance. It is further found that in the ENF test of the hybrid panel, the interface damage includes not only the damage of matrix, but also the shear fracture of fiber.
- carbon fiber reinforced polymer /
- metal wire mesh reinforced /
- low-velocity impact /
- interlaminar fracture toughness /
- failure mechanism

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图 1 热压成型工艺流程示意图

T—Temperature

Figure 1. Schematic diagram of hot-pressing process

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图 2 低速冲击试验示意图

Figure 2. Schematic diagram of low-velocity impact test

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图 3 压缩试验及二维虚拟图像关联(2D-VIC)测试系统示意图

Figure 3. Schematic diagram of compression test fixture and two-dimensional virtual image correlation (2D-VIC) test system

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图 4 双悬臂梁(DCB)拉伸试验示意图

b, h and α—Span width, thickness and delamination length of the specimen, respectively

Figure 4. Schematic diagram of double cantilever beam (DCB) tensile test

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图 5 末端切口弯曲(ENF)试验示意图

L—Span length of the specimen

Figure 5. Schematic diagram of end-notched flexure (ENF) test

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图 6 同一冲击能量下不同试件的典型接触力-时间及能量-时间曲线

Figure 6. Typical contact force-time and energy-time curves of different specimens under the same impact energy

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图 7 25 J冲击能量下4种试件的形貌：(a) 正面；(b) 背面；(c) 横截面

WN—Wire net

Figure 7. Morphologies of the four specimens under 25 J impact energy: (a) Front; (b) Back; (c) Cross section

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图 8 C16、C14 Al、C14 SS这3种试件在冲击后压缩的接触力-位移曲线及冲击后压缩(CAI)强度

Figure 8. Contact force-displacement curves and compression-after-impact (CAI) strength of C16, C14 Al and C14 SS specimens under post-impact compression

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图 9 20 J冲击能量下C14 SS试样在压缩过程中的面外变形

E_yy—Strain on the surface of the specimen along the longitudinal direction

Figure 9. Out of plane deformation during compression for the C14 SS specimen at 20 J impact energy

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图 10 25 J冲击后压缩4种试件的破坏形貌：(a) 正面；(b) 侧面；(c) 断面

Figure 10. Failure morphologies of the four specimens under 25 J post-impact compression: (a) Front; (b) Side; (c) Cross section

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图 11 碳纤维增强聚合物(CFRP)和碳纤维-金属网增强聚合物(CFMRP)的双悬臂梁(DCB)拉伸试验示意图：(a) 拉伸试验过程；(b) 拉伸后形貌

Figure 11. Schematic diagram of double cantilever beam (DCB) tensile test for carbon fiber reinforced polymer (CFRP) and carbon fiber-metal mesh reinforced polymer (CFMRP): (a) Tensile test process; (b) Morphology after tensile

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图 12 CFRP和CFMRP的DCB拉伸试验接触力-位移曲线

Figure 12. Contact force-displacement curves of DCB tensile test for CFRP and CFMRP

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图 13 (a) 末端切口弯曲(ENF)测试夹具及样品；(b) CFRP和CFMRP试件中间层的界面形貌

Figure 13. (a) End-notched flexure (ENF) test fixture and specimen; (b) Interfacial morphology of the middle layer of the CFRP and CFMRP specimens

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图 14 CFRP和CFMRP试件的ENF试验接触力-位移曲线

Figure 14. Contact force-displacement curves of ENF tensile test for CFRP and CFMRP

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表 1 材料力学性能和物理性能

Table 1. Mechanical and physical property of the raw materials

Specimen	Tensile strength /MPa	Tensile modulus /GPa	Elongation /%	Density /(g·cm⁻³)	Gram mass /(g·m⁻²)	Curing temperature /°C
T300	3530	230	1.5	1.76	330.0	130
SSWN	550	208	5.0	7.93	1260.0	–
AIWN	100	70	6.0	2.70	430.0	–
Notes: T300—The grade of carbon fiber used to prepare the specimen is T300; SSWN—Stainless steel wire mesh; AIWN—Aluminum wire mesh.

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表 2 不同试件的组成及尺寸

Table 2. Composition and size of different specimens

Specimen	Configuration of lay-up	Thickness/mm	Areal density /(g·m⁻²)
C16	WCF₁₆	3.2	4867.3
C14 Al	WCF₇Al₁WCF₇	3.2	4934.7
C14 SS	WCF₇SS₁WCF₇	3.2	5566.0
C14	WCF₁₄	2.8	4259.3
Notes: WCF₁₆—Specimen is composed of 16 layers of carbon fiber stacked; WCF₇Al₁WCF₇—Specimen is composed of 14 layers of carbon fiber and one layer of aluminum alloy wire net stacked; WCF₇SS₁WCF₇—Specimen is composed of 14 layers of carbon fiber and one layer of stainless steel wire net stacked; WCF₁₄—Specimen is composed of 14 layers of carbon fiber stacked.

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表 3 4种试件在不同冲击能量下的峰值力对应的位移及回弹情况

Table 3. Displacement and rebound of peak force corresponding to the four specimens under different impact energies

Impact energy	Experimental results	C14	C14 SS	C14 Al	C16
10 J	Displacement/mm	3.907	4.695	4.730	3.124
	Force-max/kN	2.404	2.509	2.575	2.739
	Energy absorption rate/%	96.81	96.48	97.92	95.21
	Rebound	○	○	○	○
15 J	Displacement/mm	5.271	5.776	5.755	5.775
	Force-max/kN	2.426	2.754	2.783	2.981
	Energy absorption rate/%	97.42	97.69	97.43	97.29
	Rebound	×	○	○	○
20 J	Displacement/mm	6.819	6.760	7.202	6.643
	Force-max/kN	2.443	2.622	3.042	3.327
	Energy absorption rate/%	97.19	97.50	97.22	96.50
	Rebound	×	×	×	○
25 J	Displacement/mm	5.211	5.509	8.240	7.244
	Force-max/kN	2.337	2.630	3.023	3.223
	Energy absorption rate/%	95.72	96.76	96.37	96.20
	Rebound	×	×	×	×
Notes: ○—Specimens have rebound phenomenon during the impact process; ×—Specimens have not rebound phenomenon during the impact process.

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表 4 CFRP和CFMRP的DCB试验参数

Table 4. Parameters of CFRP and CFMRP specimens in DCB test

Case	P_max /N	δ /mm	b /mm	a /mm	G_I /(kJ·m⁻²)
CFMRP	42.51±1.05	13.47±0.57	24.05±0.25	4.75±0.23	0.65±0.034
CFRP	42.94±1.45	12.28±0.37	24.45±0.05	4.52±0.24	0.59± 0.035
Notes: P_max—Maximum applied load during DCB test; G_I—Mode I interlaminar fracture toughness.

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表 5 ENF试验CFRP和CFMRP试件参数

Table 5. Parameters of CFRP and CFMRP specimens in ENF test

Case	P_max/N	m	h /mm	B /mm	G_II /(kJ·m⁻²)
CFMRP	875.64±25.09	252.98±4.87	3.98±0.08	24.35±0.05	10.75±0.821
CFRP	623.48±4.19	251.15±1.32	3.97±0.03	24.15±0.15	5.46±0.068
Notes: m—Slope obtained by regression analysis; B—Width; G_II—Mode II interlaminar fracture toughness.

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