Research on the microcrack behavior of carbon fiber composites under prestress and ultra-low temperature cycling
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摘要: 低温燃料贮箱复合材料化是实现运载火箭结构减重、提升运载能力的有效途径，但贮箱在服役过程中要承受超低温循环和机械载荷的共同作用，容易导致复合材料内部产生微裂纹，从而威胁结构安全。本文利用简易的预应力加载装置对碳纤维/环氧复合材料正交层合板进行超低温循环试验，研究预应力和超低温循环共同作用下复合材料层合板的微裂纹萌生和演化规律。结果表明：层合板边缘层的微裂纹密度总体大于内层，但中心两个90°叠加层表现出最大的微裂纹密度；与只有低温循环条件相比，引入预应力后层合板在同样的低温循环次数下微裂纹密度更大，增长速率更快；随着循环次数的增加，微裂纹密度的增长速率先快后慢，最终趋于饱和；随着预应力水平的提升，层合板中微裂纹的萌生和扩展速率也进一步加剧。本研究初步揭示了复合材料在载荷及超低温循环耦合作用下的微裂纹萌生和演化机制，可为低温复合材料贮箱的研制和应用提供有意义的参考。
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关键词:
- 碳纤维/环氧复合材料 /
- 层合板 /
- 超低温循环 /
- 预应力 /
- 微裂纹
Abstract: The use of composite materials in low-temperature fuel tanks is an effective approach to achieve weight reduction and enhance carrying capacity for launch vehicle structures. However, as the tank is subjected to both ultra-low temperature cycling and mechanical loads during service, it is prone to internal microcrack formation in composite materials, posing a threat to structural safety. In this study, a simple pre-stressing device was used to conduct ultra-low temperature cycling tests on carbon fiber/epoxy orthotropic laminates. The research focused on the initiation and evolution of microcracks in composite laminates under the combined action of pre-stress and ultra-low temperature cycling. The results indicate that the microcrack density at the edge layers of the laminate is generally higher than that in the inner layers, but the central two 90° stacked layers exhibits the maximum microcrack density. Compared to conditions of only low-temperature cycling, the pre-stress results in a higher microcrack density in the laminate under the same number of low-temperature cycles, with a faster growth rate. With an increase in the number of cycles, the growth rate of microcrack density initially accelerates and then slows down, eventually reaching saturation. As the pre-stress level increases, the initiation and propagation rates of microcracks in the laminate are further intensified. This study provides a preliminary insight into the mechanism of microcrack initiation and evolution in composite materials under the coupled action of load and ultra-low temperature cycling, offering meaningful references for the development and application of low-temperature composite material tanks.-
Key words:
- carbon fiber/epoxy composites /
- laminates /
- ultra-low temperature cycling /
- pre-stress /
- microcrack
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图 1 (a) 试验件尺寸; (b) 碳/环氧复合材料试验件; (c) 预应力加载装置
Figure 1. (a) Specimen sizes; (b) Carbon/epoxy composite specimen;(c) Prestress loading device
图 2 超低温循环试验系统：(a) 系统示意图; (b) 系统实物图; (c) 长周期循环温度曲线; (d) 短周期循环温度曲线
Figure 2. Ultra-low temperature cycling system: (a) Schematic diagram of the system; (b) Photo of the system; (c) Long-cycle temperature curve;(d) Short-cycle temperature curve
图 4 无预应力时碳/环氧复合材料中间层微裂纹随着超低温循环的演化情况：(a) 3次; (b) 6次; (c) 9次; (d) 12次
Figure 4. Microcrack evolution in the middle ply of the carbon/epoxy composite laminate under different ultra-low temperature cycles in the absence of pre-stress: (a) 3 cycles; (b) 6 cycles; (c) 9 cycles; (d) 12 cycles
图 5 施加0.3%预应变时碳/环氧复合材料中间层微裂纹随着超低温循环的演化情况：(a) 3次; (b) 6次; (c) 9次; (d) 12次
Figure 5. Microcrack evolution in the middle ply of the carbon/epoxy composite laminate under different ultra-low temperature cycles with 0.3% pre-strain: (a) 3 cycles; (b) 6 cycles; (c) 9 cycles; (d) 12 cycles
图 6 碳/环氧复合材料微裂纹的扫描电镜表征
Figure 6. Scanning electron microscope characterization of microcracks in the carbon/epoxy composite
图 7 长周期循环不同预应变等级下碳/环氧复合材料的微裂纹密度：(a) 1,8层; (b) 2,7层; (c) 3,6层; (d) 4,5层
Figure 7. Microcrack density of carbon/epoxy composite at different pre-strain levels under long cycle: (a) Plies 1,8; (b) Plies 2,7; (c) Plies 3,6; (d) Plies 4,5
图 8 预应变0.3%时碳/环氧复合材料各层微裂纹密度与超低温循环次数的关系
Figure 8. Microcrack density at various plies of carbon/epoxy composite with 0.3% pre-strain as a function of ultra-low temperature cycle numbers
图 9 短周期循环有无预应变时碳/环氧复合材料的微裂纹密度：(a) 1-3, 6-8层; (b) 4,5层
Figure 9. Microcrack density of carbon/epoxy composite at short cycle with and without pre-strain: (a) Plies 1-3, 6-8; (b) Plies 4,5
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