摘要
针对高氯酸铵/端羟基聚丁二烯(AP/HTPB)混合固体推力器燃烧过程,采用燃速公式和气相化学反应动力学模型相结合的方法建立AP/HTPB固体推进剂的燃烧模型;同时利用用户自定义函数(UDF)来模拟固体推进剂的燃面退移过程,研究得到固体微推力器内复杂的燃烧反应过程,以及AP/HTPB推进剂配比对燃烧过程的影响规律。结果表明,AP/HTPB固态推力器进行着复杂的物理化学过程,所得到的计算结果与实验具有较好的一致性;同时,在推进剂配比逐渐变化过程中,平均推力呈现出先增后减的趋势,得到当AP/HTPB=85/15时,推力器获得最佳性能。
Within the present investigation, the combustion characteristics of ammonium perchlorate/hydroxyl terminated poly- butadiene （AP/HTPB）-based micro-scale thnlster were numerically studied by using the method of the combination of burning rate formula and chemical reaction kinetics mndel. Meanwhile, the combustion surface of solid thruster was described by the user-defined function （UDF）. The eftect of AP/HTPB ratio on tile combustion process was investigated. Based on the calculated results, it can be tound that, the complex physical and ehemical processes were discussed, and the results show a good consistency with the exper- imental resuh. Moreover, the thruster performance showed a trend of first increasing then decreasing with the increasing of AP/HT- PB ratio. When AP/HTPB ratio was 85/15, thruster could acquire better performance.
作者
张涛
李国岫
陈君
虞育松
魏延明
刘旭辉
周广文
ZHANG Tao LI Guo-xiu CHEN Jun YU Yu-song WEI Yan-ming LIU Xu-hui ZHOU Guang-wen(School of Mechanical, Eleetronie and Control Engineering, Beijing Jiaotong University, Beijing 100044, China Beijing Institute of Control Engineering, Beijing 100190, China)
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2016年第5期632-637,共6页
Journal of Solid Rocket Technology
