The performance tests of the main turbine of a liquid rocket engine are introduced in this paper.
对液体火箭发动机主涡轮的性能试验进行了介绍。
Turbulence two phase flow and combustion process in a liquid rocket engine combustor are analyzed with numerical method, and combustion instability is also studied.
采用数值模拟的方法对液体火箭发动机燃烧室内湍流两相流动与燃烧过程进行了分析，同时研究了燃烧室内高频不稳定燃烧现象。
A nonlinear dynamic mathematical model for describing the transient processes of working conditions has been established according to the fault characteristics in a liquid rocket engine.
针对发动机的故障特点，提出了其工作状态过渡的非线性动态数学模型。
A micro computer system is introduced for condition monitoring and fault diagnosis in the ground testing of a throttling liquid rocket engine.
本文介绍了一种用于变推力液体火箭发动机地面试车的工况监测和故障诊断微机系统。
Flow in injector passages of a variable thrust liquid propellant rocket engine was studied.
本文对变推力液体火箭发动机喷注器通道内介质流动进行求解。
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。
The design and realization of a variable thrust liquid rocket engine control system is present in this paper.
本文讨论了某型变推力液体火箭发动机数字控制系统的设计和实现。
A general method for the cycle power balance calculation of the liquid rocket engine is proposed in this paper.
本文提出了一种新的液体火箭发动机功率平衡通用计算方法。
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。
Thrust regulation is a key technology on the solid liquid rocket ramjet engine.
推力调节是整体式固液火箭冲压发动机研究的一项关键技术。
A pulse width sampled-data control system for a variable thrust liquid rocket engine is studied both theoretically and experimentally.
本文对变推力液体火箭发动机的脉宽采样数字控制系统进行了理论分析和实验研究。
The results of experimental research have shown that the fuzzy neural networks can be successfully employed in the vibration fault detection in the firing tests of a turbo pump liquid rocket engine.
实验研究结果表明：模糊神经网络可以成功地用于泵压式液体火箭发动机热试车的振动故障检测。
The first native liquid-fueled rocket engine used a liquid oxygen and carbon-hydrogen propellant, provided 5.6 tons of thrust, and was installed in unit e.
第一个使用液氧碳氢推进剂的国产液体燃料火箭发动机被安装在了火箭的E段上，它可以提供5.6吨的推力。
Through dynamic time warping analysis to the hot-fire test data and simulated fault data of a certain liquid rocket engine, the warped path sets were obtained.
对某大型液体火箭发动机的热试车数据及通过发动机模型仿真得到的故障数据进行动态时间弯曲分析，得到弯曲路径集，然后结合决策树方法进行了故障检测和诊断。
A numerical model was employed to analyze the tangential combustion instability in liquid rocket engine.
建立了液体火箭发动机切向不稳定燃烧数值分析模型并进行了初步分析。
A neural network classifier that utilizes fuzzy sets as failure classes of a liquid propellant rocket engine is studied.
研究了一种用模糊集表示火箭发动机故障模式的神经网络分类器。
The hydrodynamic design of advanced liquid rocket engine high performance inducers is a challenging technology.
先进液体火箭发动机高性能螺旋轮的流体动力设计是个关键技术。
Base on these, the health condition evaluation system of the liquid hydrogen supplying system of a rocket engine testing platform was set up.
在此基础上，建立了火箭发动机试验台液氢供应系统的健康评价体系。
The original feature of fault of liquid rocket engine is extracted, so that the normal pattern of malfunction can be expressed effectively by a few new features.
对液体火箭发动机故障的原始特征进行特征提取和选择，以使所建立的故障标准模式由少数几个新特征给予有效的表达。
A calculation of the wall temperature distribution in liquid propellant rocket engine chamber with milled grooves was completed by the aid of three-dimensional finite element method.
采用三维有限元模型对液体火箭发动机铣槽推力室进行了壁温分布计算。边界条件按一维经验公式处理。计算中比较了不同冷却剂流量。
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 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。
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