单室双推力固体火箭发动机用NEPE低燃速推进剂的燃烧性能  

Combustion property of low burning rate of NEPE propellant applied to single chamber dual thrust rocket motor

作　　者：代志高[1] 宋琴[1] 吴京汉[1] 项丽[1] 尹必文[1] 

机构地区：[1]湖北航天化学技术研究所,襄阳441003

出　　处：《固体火箭技术》2018年第1期47-52,共6页Journal of Solid Rocket Technology

摘　　要：开展了AP含量、粒度和HMX粒度、胺类化合物、有机化合物RTA和RTJ对推进剂燃烧性能的影响研究,并对RTJ/RTA组合催化剂在推进剂中的作用机理进行了初步分析。结果表明,配方中加入RTJ/RTA组合催化剂,实现了降低4、17.5 MPa燃速的同时降低低压段、高压段压强指数,通过DSC研究表明,RTJ/RTA对AP的分解有抑制作用。通过合理调节AP/HMX的相对含量、AP粒度和HMX的粒度以及采用RTJ/RTA组合催化剂,得到了固体含量为80%的低燃速配方。The factors on combustion property of low burning rate of NEPE propellant applied to a single chamber dual thrust rocket motor were investigated, which includes the content of AP, the granularity of AP and HMX, the amine-based compounds, the organic compounds such as RTJ and RTA. Besides, the effects on RTJ and RTA on the combustion properties were analyzed. The results showed that the burning rate at 4 MPa and 17.5 MPa was lowered by the combination of RTJ and RTA, as well as the pressure exponent at low and high pressures. There was inhibitory effect on AP by the combination of RTJ and RTA according to DSC results. The formulations with 80% solid content and low burning rate was obtained through adjusting reasonably the relative content of HMX and AP, the granularity of AP and HMX, and adding the combination of RTJ and RTA.

关 键 词：低燃速推进剂 降速剂 单室双推力发动机 

分 类 号：V512[航空宇航科学与技术—航空宇航推进理论与工程]