Because carbon-carbon (C/C) composites have superior high-temperature thermophysical and mechanical properties than other materials, they are currently the first choice for solid rocket motor nozzle throat linings. During the working process of the engine, the C/C composite throat lining will be damaged due to the erosion and ablation of the heat flow of high temperature, high pressure, high speed and containing erosive particles under the harsh thermal environment, which is manifested as the expansion of the throat diameter. The surface is rough and uneven, the profile is irregular, etc., which affects the working pressure of the engine and reduces the efficiency of the nozzle.