高能低燃速NEPE推进剂的研究  

Study on Low Burning Rate NEPE Propellant

作　　者：李晓萌[1] 刘云飞[1] 姚维尚[1] 谭惠民[1] 

机构地区：[1]北京理工大学化工与材料学院,北京100081

出　　处：《火炸药学报》2001年第3期1-3,9,共4页Chinese Journal of Explosives & Propellants

摘　　要：采用调节 NEPE推进剂的配方组分、添加降速剂等手段进行了一系列降低燃速的研究。研究结果表明 ,增大 AP粒径、降低 NG/DEGDN的比例、适当降低 AP含量、添加少量降速剂 ,可达到降低燃速的目的。通过对 NEPE推进剂配方组分的调节 ,在没有添加降速剂时 ,其 4.0 MPa下燃速可达到 4.7mm/ s,并且实测标准比冲可达到 2 2 39.3N·s/ kg。A low burning rate NEPE propellant were investigated by means of adding some burning rate inhibitors and adjusting its composition. The compatibility of additives with nitrite ester, combustion properties of the propellant and the standard specific pulse of Φ40 rocket motor were measured. It was observed that the burning rate of the propellant could be depressed by more bigger particle diameter AP , low ratio of NG/DEGDN, less AP content and presence of burning rate inhibitors. The burning rate under 4.0MPa could be 4.7mm/s, and standard specific pulse was 2239.3N·s/kg without additives.

关 键 词：高能固体推进剂 低燃速推进剂 燃烧性能 燃速 降速剂 比冲 

分 类 号：V512[航空宇航科学与技术—航空宇航推进理论与工程]