变燃速发射药燃烧性能计算及实验研究  

Calculation and experimental study on combustion performance of variable-burning rate propellant

作　　者：张楠 贺增弟 王书记 ZHANG Nan;HE Zengdi;WANG Shuji(North University of China,School of Environment and Safety Engineering,Taiyuan 030051,China)

机构地区：[1]中北大学环境与安全工程学院,太原030051

出　　处：《固体火箭技术》2019年第2期205-209,216,共6页Journal of Solid Rocket Technology

摘　　要：为研究管状变燃速发射药的能量释放规律,根据其结构特点建立燃烧模型,采用理论计算方法分析管状变燃速发射药外内层燃速比及长径比对其燃烧性能的影响规律;采用挤压成型工艺制备了不同硝基胍含量的管状变燃速发射药,并进行密闭爆发器实验。结果表明,模拟计算中管状发射药的外内层燃速比K=0.2,长径比n=8. 0时,发射药相对燃烧表面较为理想,燃烧渐增性相对较强,添加NQ变燃速发射药密闭爆发器实验结果与模拟计算结果有较高契合度。In order to study the energy release rule of variable burning rate propellant,the combustion model has been established according to its structural characteristics.The effects of the burning-rate ratios and length-to-diameter ratios of variable-burning rate propellant have been analyzed by numerical simulations.Tubular variable-burning rate of propellant as a function of nitrocarbonitrile(NQ)content has been tested by closed bomb vessel.The results show that,when the burning rate-ratio of the external layer to internal layer of the propellant is 0.2 and length-to-diameter ratio is 8.0,the propellant burns relatively to the burning surface,which shows a good progressive combustion process.Closed bomb vessel testing results and simulations agree very well with each other.

关 键 词：变燃速发射药 燃烧性能 相对燃烧表面 

分 类 号：V512[航空宇航科学与技术—航空宇航推进理论与工程]