摘要
分析了缩水甘油叠氮聚醚(GAP)的热分解特性和燃烧特性,提出了GAP燃烧初期热分解反应的假说,建立了由化学结构特性计算GAP单元推进剂及GAP高能推进剂的燃速公式,并计算了不同配比GAP高燃速推进剂的燃速特征。计算结果与实测值吻合得很好,大部分偏差在±10%以内,且全部误差在±15%以内。这说明所建立的模型基本合理,编制的GAP高能推进剂燃速计算程序基本可行。
The thermal and combustion characteristics of GAP were analyzed. The hypothesis about GAP decomposition in the initial stage of combustion was proposed. The burning rate equation of GAP and GAP high-energy propellant was derived based on the chemical structure. The calculated burning rates of GAP high-energy propellant agree well with most of the experimental data with the deviation of all data within ±15% and that of a majority of data wihtin ± 10%. It proves that the model and program are reasonable.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2009年第5期535-538,共4页
Journal of Solid Rocket Technology
基金
国家"973"基金资助课题(61337020302)
