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.
固体燃料火箭发动机的构造更简单、分量更轻，而且相对更安全。 在固体燃料火箭发动机里，燃料和氧化剂被预先混合成稳定的液态推进剂，然后被塞满火箭发动机的燃料箱里。
Solid-fuel rockets, in which the fuel and oxidiser are pre-mixed into a stable, solid propellant and then packed inside the case of the rocket, are simpler, lighter and relatively safer.
分析了固液发动机推进剂的燃烧特性和发动机性能特性、与液体和固体火箭发动机的不同，以及研制的技术难度等。
The propellant feature of burning behavior and engine in hybrid engine, the differences to liquid and solid engine and the difficulties of technology in development were analyzed.
衬层是推进剂与绝热层或壳体之间的高分子弹性体涂层，衬层成型是固体火箭发动机生产中的一种特种工序。
The liner is a polymeric elastomer coating between propellant and insulation layer or case. The liner-forming is a special step in production of solid rocket motor.
衬层是推进剂与绝热层或壳体之间的高分子弹性体涂层，衬层成型是固体火箭发动机生产中的一种特种工序。
The liner is a polymeric elastomer coating between propellant and insulation layer or case. The liner-forming is a special step in production of solid rocket motor.
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