中国从1958年开始复合固体推进剂火箭发动机的探索和研制工作。
China has undertaken to research and develop composite solid propellant rocket motors since 1958.
直径300毫米的固体推进剂火箭发动机采用了复合推进剂端燃药柱。
The 300mm diameter solid propellant rocket motor employs a composite propellant end burning grain.
推进剂的羽焰温度是固体推进剂火箭发动机的重要参数，对于研究发动机内的燃烧过程具有重要价值。
The plume temperature is an important parameter, for solid propellant rocket engines and it is useful for determining the combustion process of the engine.
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