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利用高能物质缩水甘油叠氮聚醚（ＧＡＰ）和贫氧高氯酸铵（ＡＰ）系复合推进剂作燃气混合火箭发动机的燃烧剂，用四氧化二氮（ＮＴＯ）、硝酸（ＨＮＯ３）和一氧化二氮（Ｎ２Ｏ）作氧化剂进行试验，取得燃气混合火箭发动机的燃烧特性。同时利用开关控制液体氧化剂的流量求出了对推力的控制效果。以ＮＴＯ，ＨＮＯ３和Ｎ２Ｏ作氧化剂时，燃烧效率可达９２％以上。利用开关控制流量不仅可以平滑控制推力，而且容易点火，从而得出主发动机也可作为推力控制装置的结论。
The combustion of gas-mixed rocket motor was carried out by using GAP and AP composite propellants as combustible agent. Nitrogen oxides (NNO3), nitric acid (HNO3) and nitric acid Nitrous oxide (N2O) as an oxidant was tested to obtain the combustion characteristics of a gas-fired rocket engine. At the same time using the switch to control the flow of liquid oxidant to determine the effect of the thrust control. With NTO, HNO3 and N2O as oxidant, the combustion efficiency can reach more than 92%. Using the switch to control the flow not only smoothly controls the thrust but also ignites easily, so that the main engine can also be used as the thrust control device.