The modeling of priming process of Liquid Propellant Rocket Engines (LPRE) was studied.
研究了常温推进剂液体火箭发动机充填过程的建模问题。
Steady state fault detection and diagnosis of liquid propellant rocket engines based on decision tree method;
利用液体火箭发动机作动力装置的火箭，又称液体推进剂火箭。
Lacking of fault samples is a knotty problem in the fault detection of complex systems such as Liquid-propellant Rocket Engines (LRE).
在对类似于液体火箭发动机这种复杂系统的故障检测过程中，一个非常棘手的问题是缺乏故障类样本。
The plume temperature is an important parameter, for solid propellant rocket engines and it is useful for determining the combustion process of the engine.
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 priming process of feed lines of cryogenic propellant liquid rocket engines was studied.
研究了低温推进剂液体火箭发动机供应管道系统充填过程的建模问题。
The priming process of feed lines of cryogenic propellant liquid rocket engines was studied.
研究了低温推进剂液体火箭发动机供应管道系统充填过程的建模问题。
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