根据固体火箭发动机燃烧中氧化性组分扩散控制喷管喉衬烧蚀和 A12 O3 沉积对喉衬的保护 ,提出 C/C喉衬稳态烧蚀的工程计算方法。 3个实验发动机的烧蚀预示结果与实测结果吻合 ,该计算方法具有较高的精度 According to the protection of throat linings by diffusion control of throat linings and A12 O3 deposition during the combustion of solid rocket motors, the engineering calculation method of steady state ablation of C / C throat linings is proposed. The ablation prediction results of the three experimental engines are in good agreement with the measured results. The calculation method has higher accuracy