摘要
采用固体推进剂燃烧过程实时监测与燃速测定系统对六硝基六氮杂异伍兹烷(HNIW)的燃烧性能和催化燃烧性能进行了研究;在固体推进剂燃烧火焰温度分布测试系统中,采用相对强度法对HNIW的燃烧火焰温度分布进行了测定。结果表明,HNIW在低压强范围内(1～6MPa,7～13MPa,1～13MPa)具有较高的压强指数,15～19MPa的压强范围内,存在一平台燃烧区。在1～13MPa的压强范围内催化剂OME能显著地降低HNIW压强指数;HNIW的最高燃烧火焰温度随压强的升高接近于理论燃烧温度,说明相对光强法更适合于测定高压条件下高燃速推进剂的燃烧火焰温度分布。
Combustion properties of hexanitrohexaazaisowurtzitane(HNIW) were studied by means of real-time monitoring system and burning rate measurement system for solid propellants , and relative light intensity method was used to determine temperature distribution of HNIW combustion flame in the measurement system of the combustion flame temperature distribution. The results show that the pressure exponent of HNIW is higher under the range of low pressure of 1～13MPa, and the use of catalyst OME can obviously decrease the pressure exponent. There is a platform combustion zone under 15MPa to 19MPa pressure. Along with raising of the pressure, the highest combustion temperature will approach the theoretical combustion temperature, which means that the relative light intensity method is more suited to measure temperature distribution of high burning rate propellants combustion flame under high pressure.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2004年第3期190-192,215,共4页
Journal of Solid Rocket Technology
基金
高等学校优秀青年教师基金资助项目(1755)。
