Abstract
This study is focused on a novel high-thermal-conductive C/C composite used in heat-redistribution thermal protection systems. The 3D mesophase pitch-based carbon fiber (CFMP) preform was prepared using CFMP in the X (Y) direction and polyacrylonitrile carbon fiber (CFPAN) in the Z direction. After the preform was densified by chemical vapor infiltration (CVI) and polymer infiltration and pyrolysis (PIP), the 3D high-thermal-conductive C/C (CMP/C) composite was obtained. The prepared CMP/C composite has higher thermal conduction in the X and Y directions. After an ablation test, the CFPAN becomes needle-shaped, while the CFMP shows a wedge shape. The fiber/matrix and matrix/matrix interfaces are preferentially oxidized and damaged during ablation. After being coated by SiC coating, the thermal conductivity plays a significant role in decreasing the hot-side temperature and protecting the SiC coating from erosion by flame. The SiC-coated CMP/C composite has better ablation resistance than the SiC-coated CPAN/C composite. The mass ablation rate of the sample is 0.19 mg·(cm−2·s−1), and the linear ablation rate is 0.52 μm·s−1.
Highlights
Carbon-fiber-reinforced carbon matrix (C/C) composite has been widely studied due to its high-temperature strength, low coefficient of thermal expansion, and good anti-ablation ability [1,2].Because of its excellent performance, C/C composite has become a promising structural material in high-temperature applications, including rocket nozzles, aeronautic jet engines, leading edges, and so on.C/C composite is a promising functional material for thermal management systems due to its high thermal conductivity [3,4]
Because it can decrease the temperature of hot components and increase their reliability, C/C composite has been used in heat-redistribution thermal-protection systems of hypersonic aircraft that have undergone long-time ablation and oxidation [5]
We report the ablation behavior of a novel homemade 3D CMP /C composite with high thermal conductivity
Summary
Carbon-fiber-reinforced carbon matrix (C/C) composite has been widely studied due to its high-temperature strength, low coefficient of thermal expansion, and good anti-ablation ability [1,2]. CFMP is an ideal reinforcement for CMP /C composite with high thermal conductivity. Yuan et al [17] prepared a 1D ribbon-shaped carbon-fiber-reinforced CMP /C composite, and the longitudinal thermal conductivity was about 900 W·(m−1 K−1 ) after graphitization. It can be speculated that CMP /C composite using CFMP as reinforcement will have some different ablation features. Such understanding of the ablation behavior of CMP /C composite is helpful in applying this composite to thermal protection systems of hypersonic vehicles, especially in explaining the failure mechanisms after the thermal protection coating is damaged. This study can provide guidance for the design and fabrication of CMP /C composite with high thermal conductivity for application in hypersonic aircrafts
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