liquid-propellant rocket engine experimental system 液体火箭发动机实验台系统
Launch capability of liquid rocket engine can be improved by propellant utilization system.
采用推进剂利用系统可以提高运载火箭的发射能力。
Firstly, the static and dynamic mathematic model of the Liquid Propellant Rocket Engine of pressure-fed providing system was established in centralized parameter method.
首先采用集中参数法，建立了挤压式供应系统的液体火箭发动机各部件的静态及动态数学模型。
The structural candidates of centrifugal impeller were designed respectively from single-objective and multi-objective optimization based on the system design of liquid propellant rocket engine.
根据液体火箭发动机系统设计确定的离心泵的性能参数，对泵叶轮的几何参数分别进行了单目标和多目标优化设计。
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