A variable structure control system for the start up process of staged combustion cycle liquid rocket engine is presented in this paper.
针对分级燃烧循环液体火箭发动机启动过程的特点，提出了一种变结构控制系统。
A fuzzy control is studied, which is used for the feedback control in the changing condition process of the staged combustion cycle liquid rocket engine.
研究了一种模糊控制方法，并用于分级燃烧循环液体火箭发动机变工况过程的反馈控制。
Attributing to the large flow rate, high efficiency level reaction turbine is adoptive in staged combustion cycle liquid rocket engine.
基于闭式补燃循环液体火箭发动机流量大的特点，欲设计效率水平高的航天反力式涡轮。
The dynamic models of engine parts in a new high-performance staged combustion cycle liquid propellant rocket through the module codified were built.
通过模块化编程，建立了新一代高性能补燃发动机启动过程的部件模型。
The mathematical models of the static characteristics of the full-flow staged combustion cycle rocket engine were presented.
建立了全流量补燃循环发动机的静态特性的数学模型。
The mathematical models of the static characteristics of the full-flow staged combustion cycle rocket engine were presented.
建立了全流量补燃循环发动机的静态特性的数学模型。
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