Abstract: 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

Key words: Solid fueled ramjet;Oxygen poor fuel rech propellant;Propellant combustion;Low pressure combustion;Flammability limit

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。

关键词: 固体燃料冲压发动机;贫氧富燃料推进剂;推进剂燃烧;低压燃烧;可燃极限