目的 提高C/C复合材料在超高温下的抗烧蚀性能。方法 采用化学气相沉积法，在C/C复合材料表面制备SiC过渡层，然后以惰性气体保护等离子喷涂工艺在带有SiC过渡层的C/C材料表面制备W涂层，研究所制备的W-SiC-C/C复合材料的微观形貌与结构特征。以200 kW超大功率等离子焰流，考核W-SiC-C/C材料的抗烧蚀性能，并与无涂层防护的C/C材料进行对比分析。结果 W涂层主要为层状的柱状晶结构。W涂层与SiC过渡层、过渡层与基体界面呈镶嵌结构，结合良好。SiC过渡层阻止了W、C元素相互迁移与反应。在驻点压力为4.5 MPa、温度约5000 K、热流密度为36 MW/m²的烧蚀条件下，当烧蚀时间小于10 s时，涂层对C/C材料起到了较好的保护作用，W涂层发生氧化烧蚀，基体未发现烧蚀，平均线烧蚀率为0.0523 mm/s;当烧蚀时间超过15 s后，涂层防护作用基本失效，基体C/C材料发生烧蚀现象。结论 以W涂层、SiC过渡层为防护的C/C复合材料，能够适用于短时间超高温的烧蚀环境，如固体火箭发动机等。W涂层的熔融吸热、氧化耗氧以及SiC过渡层的氧化熔融缓解涂层热应力和氧扩散阻碍的联合作用，提高了C/C材料的抗烧蚀性能。

This paper aims to improve the ablation resistance of C/C composites at ultra-high temperatures. SiC transition layer was prepared on the surface of C/C composite material by a chemical vapor deposition method, then Tungsten coating was prepared on SiC coated C/C composites by inert gas protecting atmospheric plasma spraying. In this paper, the morphology and composition of the W-SiC-C/C composites were studied, and the ablation resistance of the W-SiC-C/C materials was evaluated by a 200 kW ultra-high-power plasma flame, which was compared and analyzed with C/C materials for coating protection. Results show that the interface between the W coating and the SiC transition layer, and the interface between the transition layer and the substrate is a mosaic structure. The tungsten coating, SiC transition layer and the C/C substrate had a good adhesive interface. The SiC transition layer prevented the mutual migration and reaction of W and C elements from generating brittle WC. Under the ablation conditions of stagnation point pressure of 4.5 MPa, the temperature of about 5000 K, and heat flux of 36 MW/m2, when the ablation time is less than 10 s, the coating has a good protective effect on the C/C material. W Oxidative ablation occurred in the coating, the ablation was not found in the substrate, and the average linear ablation rate was 0.0523 mm/s. When the ablation is longer than 15 s, the protective effect of the coating fails, and the substrate C/C material is ablated. It is concluded that C/C composites protected by tungsten coating and SiC transition layer are suitable for short time ultra-high temperature ablation environment, such as solid rocket motors, etc. The combined effect of melt heat absorption of tungsten coating, oxidation oxygen depletion, oxidation melting of SiC transition layer to relieve the thermal stress of the coating and oxygen diffusion hindrance improves the ablation resistance of C/C materials.