反应参数对固体火箭发动机C/C喉衬烧蚀机理的研究至关重要。针对喉衬烧蚀的重要反应C+CO2→2CO,发展了一套以热重法为基础的反应参数测试方法。实验中利用SiC涂层的方法实现了试件的单面退移,获得高精度热重数据,并结合数值模拟预测的反应体系控制机制,获得文中所用多向编织C/C复合材料,温度范围1 100～1 700 K,其反应级数n=0.5,指前因子A=1 995.08 kg/(m2·s·MPa0.5),活化能E=191.28 kJ/mol。 The study of reaction parameters on the mechanism of C / C throat lining of solid rocket motor is very important. Aiming at the important reaction of throat lining ablation, C + CO2 → 2CO, a set of reaction parameter testing methods based on thermogravimetry was developed. Experiments using SiC coating method to achieve the single side of the specimen back to obtain high-precision thermogravimetric data, combined with numerical simulation of the reaction system to predict the control mechanism to obtain the paper used in the multi-directional braided C / C composites, the temperature range The reaction order n = 0.5, the pre-exponential factor A = 1 995.08 kg / (m2 · s · MPa0.5) and the activation energy E = 191.28 kJ / mol.