摘要
通过85%H2O2-PE固液火箭发动机中含有液体层的燃料热解模型,计算了PE燃料的热解过程,分析了燃料热解过程对点火时间的影响,计算结果和试验值一致。H2O2的流量对点火过程起决定性作用,当氧化剂流量低于最小点火流量时,发动机将无法点火。
The pyrolysis process of PE fuel was calculated by using fuel pyrolysis model of the 85% H2O2-PE hybrid rocket motor with liquid layers, and the effects of fuel pyrolysis process on the ignition time were analyzed. The calculation results agree well with the experiment data. The H2O2 flow has decisive effect on ignition process, and the motor cannt be ignited when the oxidizer flow rate is less than the minimum ignition flow rate.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2006年第5期346-349,共4页
Journal of Solid Rocket Technology
基金
国家自然科学基金项目(50406023)
航天支撑基金项目
关键词
固液火箭发动机
点火
热解
hybrid rocket motor
ignition
pyrolysis
