Ablation behavior of C/C-(Hf, Zr, Ti)C-(Hf, Zr, Ti)B2-W-Cu nozzle-throats in a solid rocket motor environment

Conventional ultra-high-temperature ceramic-modified carbon/carbon composites (C/C-UHTCs) face limitations such as excessive erosion in the gas environment of solid rocket motors (SRMs). In contrast, metal-reinforced C/C-UHTCs exhibit enhanced mechanical properties, thermophysical characteristics, and resistance to high-temperature erosion. These advantages indicate significant potential for metal-reinforced C/C-UHTCs to augment the thrust capabilities of SRMs. This study demonstrated the preparation of (Hf, Zr, Ti)C-(Hf, Zr, Ti)B 2 -W-Cu cermet modified C/C composites using slurry infiltration and reactive melt infiltration at 1400°C. The microstructure, formation mechanisms, mechanical properties, and thermophysical properties of C/C-(Hf, Zr, Ti)C-(Hf, Zr, Ti)B 2 -W-Cu composite materials, as well as the ablation behavior of the composite materials under the SRM environment were compared. The results showed that the linear and mass ablation rates of the C/C-(Hf, Zr, Ti)C-(Hf, Zr, Ti)B 2 -W-Cu composite material decreased by 112.1% and 160.4% (0.074 mm s −1 , 0.086 g s −1 ), respectively, compared with those of the C/C-(Hf, Zr, Ti)C composite material. This could be attributed to the formation of a dense, high-strength W-skeleton composite (Hf, Zr, Ti)O 2 oxide layer during the ablation of the C/C-(Hf, Zr, Ti)C-(Hf, Zr, Ti)B 2 -W-Cu composite, which effectively resisted erosion from high-temperature, high-speed and high-particle-concentration two-phase gas flow. This work presents a novel approach to enhancing the ablation resistance of C/C-UHTCs and holds significant promise for the development of structural materials in SRM environments.