双组元液体动力环境下3D C/SiC复合材料喷管烧蚀性能

In order to explore the ablation characteristics of C/SiC ceramic composite nozzles in the working environment of liquid rocket engines, 3D C/SiC composite nozzle was prepared by the precursor impregnation pyrolysis(PIP) process, and the ablation test of the nozzle in various working conditions was carried out. The results show that 3D C/SiC composite nozzle can meet the requirements of anti-ablation performance of the liquid rocket engine under various working conditions. The wire ablation rate of nozzle throat is about 3.92×10^-4 mm/s; after the hot test vehicle ablation test, a large amount of white matter SiO₂ remains on the inlet cylindrical section, convergent section, throat section and expansion section outer surface of the nozzle, and the ablation pit appears in the throat; the ablation mechanisms of C/SiC composites under liquid rocket engine are mainly mechanical erosion ablation and oxidation ablation.