Fracture Performance Study of Carbon-Fiber-Reinforced Resin Matrix Composite Winding Layers under UV Aging Effect
Abstract
:1. Introduction
2. Experiment
2.1. Experimental Materials and Sample Preparation
2.2. UV Aging Experiment
2.3. Interlaminar Fracture Performance Testing
2.3.1. Mode I Interlaminar Fracture Test
2.3.2. Mode II Interlaminar Fracture Test
2.3.3. Mixed-Mode Interlaminar Fracture Test
3. Experimental Results and Discussion
3.1. Analysis of Mode I Interlaminar Fracture Toughness Results
3.2. Analysis of Mode II Interlaminar Fracture Toughness Results
3.3. Analysis of Mixed-Mode Interlaminar Fracture Toughness Results
4. XFEM-Based Finite Element Simulation Method
4.1. Wound Composite Modeler (WCM) and XFEM Technology
4.2. Modeling of Type IV Hydrogen Storage Cylinder with Cracks
T700S/Epoxy Composite | Non-Aging | After Aging |
---|---|---|
(Mpa) | 149,200 | 128,250 |
(Mpa) | 8150 | 8330 |
0.28 | 0.28 | |
0.336 | 0.336 | |
(Mpa) | 4260 | 4490 |
(Mpa) | 3710 | 3710 |
(Mpa) | 2585.11 | 2239 |
(Mpa) | 50.5 | 50.69 |
(Mpa) | 1477 | 1158.4 |
(Mpa) | 180 | 180 |
(Mpa) | 72.47 | 74.45 |
4.3. The Influence of UV Aging on the Crack Propagation of Winding Layers
5. Conclusions
- (1)
- UV aging has a significant impact on both Mode I and Mode II fracture toughness. With increasing aging duration, Mode I fracture toughness increases, while Mode II fracture toughness decreases. After 50 days of aging at 70 °C, compared to the non-aged specimens, increases by 22.1%, and decreases by 18.2%. The experiments indicate that as the aging time extends, the interlayer bonding strength of the CFRP laminate weakens, leading to a decrease in Mode II fracture toughness. However, the number of fiber bridging between layers gradually increases, significantly enhancing Mode I fracture toughness.
- (2)
- UV aging also has a noticeable influence on mixed-mode interlaminar fracture toughness. With the increasing aging duration, mixed-mode fracture toughness exhibits a trend of initial increase followed by a subsequent decrease. Under the conditions of 70 °C aging, as the aging time increases, reaches its peak, showing a maximum increase of 7.2%. Even after 50 days of aging, there is still a 2% improvement. The experiments reveal that in the early stages of UV aging, the post-curing of the resin enhances the material’s toughness. However, in the later stages, the damaging effect of UV radiation surpasses the beneficial effects of post-curing, leading to a significant reduction in interlayer bonding strength.
- (3)
- Due to the actual operating conditions of high-pressure hydrogen storage cylinders, cracks perpendicular to the length direction of the vessel are more likely to cause damage than parallel cracks. Transverse damage may result in various failure modes, including fiber fracture, matrix deformation and cracking, fiber-matrix separation (fiber debonding), and fiber pull-out. Therefore, the analysis of crack propagation in Type IV hydrogen storage cylinders cannot be simplified based solely on fracture toughness. The effect of UV aging on the cross-layer expansion of cracks in Type IV hydrogen storage cylinders was simulated and analyzed by XFEM. The results indicate that the cracks in the aged composite winding layer are more sensitive, exhibiting lower initiation loads and longer crack propagation lengths under the same load. UV aging reduces the tensile strength and modulus of CFRP, causing a decline in the maximum stress fibers and matrices can withstand. At the same stress level, the material layers enter failure states earlier after aging. UV aging diminishes the overall load-bearing capacity and crack resistance of hydrogen storage cylinders, posing greater safety risks during service.
Author Contributions
Funding
Institutional Review Board Statement
Informed Consent Statement
Data Availability Statement
Conflicts of Interest
References
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Fiber Type | Filaments | Tensile Strength (MPa) | Young’s Modulus (GPa) | Elongation (%) | Density (g/cm3) |
---|---|---|---|---|---|
T700S | 12 k | 4900 | 230 | 2.1 | 1.8 |
Epoxy Resin | Appearance | Viscosity (Pa.s) | Epoxy Value (eq/100 g) | Volatile Components (%) |
---|---|---|---|---|
Y04 | Light yellow viscous liquid | 10–16 | 0.48–0.54 | ≤2 |
Aging Cycle | Aging Phase | Wavelength (nm) | UV Irradiance (W/m2·nm) | Blackboard Temperatures (°C) | |
---|---|---|---|---|---|
T1 | 8 h dry 4 h condensation | 340 | 1 ± 0.02 0.00 | 70 ± 3 50 ± 3 | |
T2 | 8 h dry 4 h condensation | 340 | 1 ± 0.02 0.00 | 60 ± 3 50 ± 3 | |
T3 | 8 h dry 4 h condensation | 340 | 1 ± 0.02 0.00 | 50 ± 3 50 ± 3 |
AL6061-T6 | PA6 | |
---|---|---|
E, MPa | 69,000 | 358.11 |
0.33 | 0.4 | |
Tensile strength, MPa | 368 | ~ |
Yield Strength, MPa | 241 | 18 |
NO. | Layer Type | Wind Angle (°) | Thickness (mm) | Band Width (mm) |
---|---|---|---|---|
1 | Hoop | 90 | 6.754 | 20 |
2 | Helical | 12 | 1.228 | 20 |
3 | Helical | 18 | 1.228 | 20 |
4 | Helical | 23 | 1.228 | 20 |
5 | Helical | 36 | 1.228 | 20 |
6 | Hoop | 90 | 6.754 | 20 |
7 | Helical | 12 | 1.228 | 20 |
8 | Helical | 12 | 1.228 | 20 |
9 | Helical | 18 | 1.228 | 20 |
10 | Helical | 30 | 1.228 | 20 |
11 | Hoop | 90 | 6.754 | 20 |
12 | Helical | 36 | 0.614 | 20 |
13 | Helical | 30 | 0.614 | 20 |
14 | Helical | 23 | 0.614 | 20 |
15 | Helical | 12 | 0.614 | 20 |
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Liu, Z.; Zhou, F.; Zou, C.; Zhao, J. Fracture Performance Study of Carbon-Fiber-Reinforced Resin Matrix Composite Winding Layers under UV Aging Effect. Materials 2024, 17, 846. https://doi.org/10.3390/ma17040846
Liu Z, Zhou F, Zou C, Zhao J. Fracture Performance Study of Carbon-Fiber-Reinforced Resin Matrix Composite Winding Layers under UV Aging Effect. Materials. 2024; 17(4):846. https://doi.org/10.3390/ma17040846
Chicago/Turabian StyleLiu, Zhen, Feiyu Zhou, Chao Zou, and Jianping Zhao. 2024. "Fracture Performance Study of Carbon-Fiber-Reinforced Resin Matrix Composite Winding Layers under UV Aging Effect" Materials 17, no. 4: 846. https://doi.org/10.3390/ma17040846