铝镁贫氧推进剂低压可燃极限研究  

FLAMMABILITY LIMITS OF ALUMINUM MAGNESIUM FUEL RICH PROPELLANT

作　　者：张炜[1] 朱慧[1] 薛金根[1] 方丁酉 夏智勋 姜春林 万章吉 

机构地区：[1]国防科技大学材料科学与应用化学系

出　　处：《推进技术》1999年第2期95-98,共4页Journal of Propulsion Technology

摘　　要：采用推进剂静态燃速测试和非壅塞式固体火箭冲压发动机实验的方法，研究了铝镁贫氧推进剂配方对其低压可燃极限的影响。研究表明，增加氧化剂的含量、添加燃速催化剂和采用超细金属添加剂，可以拓宽铝镁贫氧推进剂的低压可燃极限，满足非壅塞式固体火箭冲压发动机的基本要求。The effect of the composition of aluminum magnesium fuel rich propellant on the flammability limit was studied by means of the burning rate measurement and the direct connected pipe test of an unchoked solid ramrocket.The methods to broaden the flammability limit of the fuel rich propellant were investigated.The results show that sustained combustion at low pressure and high burning rate can be improved when increasing the oxidizer content and adding burning rate modifiers or the super fine aluminum powder.The improved fuel rich propellant can be used in the unchoked solid ramrocket

关 键 词：冲压发动机 贫氧富燃料 推进剂 燃烧 可燃极限 

分 类 号：V435.12[航空宇航科学与技术—航空宇航推进理论与工程]