摘要
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。
Reactive parameters are important to study nozzle erosion mechanism of C/C composites in SRM.According to the important reactivity C＋CO2→2CO for C/C nozzle erosion in SRM,a method based on heat-weight method for the kinetic parameter was developed.Hereinto,SiC coating was adopted to achieve single-surface regression process of the sample,and accurate data was obtained.Based on with the reaction control mechanism from simulating approach,the multi-directional weaving C/C composite was prepared,temperature ranging from 1 100 K to 1 700K,the reaction order is 0.5,the pre-exponential factor is 1 995.08 kg/（m^2·s·MPa0.5）,and the activation energy is 191.28 kJ/mol.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2012年第5期694-697,710,共5页
Journal of Solid Rocket Technology
基金
国家自然科学基金项目(50776073)
