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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 influence of the formula of aluminum-magnesium oxygen-poor propellant on the flammable limit of low pressure was studied by using the static burning test of propellant and the experiment of non-plugging solid rocket ramjet engine. The research shows that increasing the content of oxidant, adding burning rate catalyst and using ultrafine metal additive can widen the low pressure flammability limit of aluminum-magnesium oxygen-poor propellant to meet the basic requirements of non-plugged solid rocket ramjet engine.