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.
固液混合火箭发动机的燃面后退速率低是制约该类发动机应用的主要因素。
The low fuel regression rate in hybrid motor is the principal factor affecting the application of the motor.
由于氧化剂和燃料的燃烧方式不同，固液火箭发动机工作过程和液体火箭发动机及固体火箭发动机有很大的区别。
Owing to the dissimilar combustion mode, their working process is different form that of solid rocket motors and the liquid rocket engines.
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