CNT树脂基复合材料断裂韧性的优化设计

doi:10.7527/S1000-6893.2023.28971

Abstract

Abstract:

Compared with carbon fiber， Carbon Nanotube （CNT） is the ideal reinforcement phase for the epoxy composites，which has higher mechanical properties and lower density and， the great potential application in the aerospace field. A processing scheme was proposed for the CNT-epoxy Single-Edge Notched Bend （SENB） specimens， and the measuring methods of microscopic structure and parameters were proposed. The fracture toughness tests were conducted on the SENB specimens with different MWCNT lengths and oxidation times. The effects of the interfacial length and interfacial C—C bond density on the fracture toughness were quantitatively analyzed， and the fracture toughness optimization scheme was proposed. The experimental results show that： the interfacial C—C bond density and ozone oxidation time of CNTs show linear relationship； the relative fracture toughness enhancement rate increases rapidly with the increase of the ozone oxidation time， and then decreases dramatically. This means that there exists a critical interfacial C—C bond density， where the relative fracture toughness enhancement rate reaches maximum； for the weak interface， the relative fracture toughness enhancement rate increases rapidly with the increase of the interfacial length， and then decreases slightly； for the strong interface， the relative fracture toughness enhancement rate increases rapidly with the increase of the interfacial length， and then decreases dramatically； the fracture toughness reaches maximum， when the amounts of CNT pullout and CNT fracture are approximately equal，which means that the fracture toughness reaches maximum under the transition condition of the failure mode from the CNT pullout to CNT fracture.

Key words: interfacial length, interfacial C—C bond density, CNT composites, fracture toughness, optimal design

CLC Number:

V258

Wenbin JIA, Lei FANG, Gen ZHANG, Jian SHI, Zekan HE, Haijun XUAN. Optimal design of fracture toughness for CNT⁃epoxy composites[J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(7): 428971-428971.

Figures/Tables 17

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Table 2

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试件编号	临界应力强度因子K_IC/（MPa·m^1/2）	相对增韧率 $Δ$ $K ˙$ /%
E0	0.85±0.02
S0	1.07±0.03	27
S1	1.21±0.03	42
S2	1.25±0.03	47
S3	1.32±0.03	56
S4	1.15±0.05	35
M0	1.18±0.02	39
M1	1.29±0.04	53
M2	1.36±0.03	60
M3	1.43±0.02	69
M4	1.21±0.05	42
L0	1.16±0.06	37
L1	1.28±0.05	52
L2	1.34±0.05	58
L3	1.39±0.06	64
L4	1.13±0.06	33

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Optimal design of fracture toughness for CNT⁃epoxy composites

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References 24

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材料	长度/μm	臭氧处理时间/min
S0-MWCNTs	2	0
S1-MWCNTs	2	15
S2-MWCNTs	2	30
S3-MWCNTs	2	60
S4-MWCNTs	2	120
M0-MWCNTs	10	0
M1-MWCNTs	10	15
M2-MWCNTs	10	30
M3-MWCNTs	10	60
M4-MWCNTs	10	120
L0-MWCNTs	30	0
L1-MWCNTs	30	15
L2-MWCNTs	30	30
L3-MWCNTs	30	60
L4-MWCNTs	30	120