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。
Soviets started to explore liquid rocket engine technologies as early as 1930s.
苏联早在30年代就开始了液体火箭发动机的研制工作。
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。
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 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。
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。
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。
Rotor dynamic is one of the most complicated problems in development of LOX turbopump of liquid rocket engine.
转子动力学问题是液体火箭发动机研制中最复杂的问题之一。
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。
The hot flow fields in liquid rocket engine combustion chamber with and without baffles are simulated numerically.
用数值方法模拟了液体火箭发动机燃烧室内有无隔板两种情况的热态解。
The detonation wave ignition technique is suitable to synchronization ignition of multi-chamber liquid rocket engine.
爆震波多管点火技术适合用于多燃烧室液体火箭发动机的同步点火。
The complex flow was simulated with sequential and parallel SIMPLE algorithm in the combustion chamber of liquid rocket engine.
用串行和并行SIMPLE算法对液体火箭发动机燃烧室内的复杂流动进行了数值模拟。
Finally, based on the model data, the neural networks are applied to recognize several fault patterns of the liquid rocket engine.
最后，基于模型数据，应用神经网络识别了液体火箭发动机的几种故障模式。
The results show that parallel and distributed method can play an important role on the numerical simulation in liquid rocket engine.
从测试结果可以看出，并行与分布处理技术在液体火箭发动机复杂内流场的数值模拟方面能发挥重要作用。
The loss factors in liquid rocket turbine are analysed in detail and a related mathematical model and calculation method is proposed.
分析了液体火箭发动机中所用涡轮的各种损失因素，并建立了相应的数学模型，给出了计算方法。
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。
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 nonlinear high frequency combustion instability process in the liquid rocket engine is simulated with the method of nonlinear dynamics.
采用非线性动力学方法对液体火箭发动机非线性高频燃烧不稳定工作过程进行了研究。
Unsymmetrical dimethylhydrazine (UDMH) is the main fuel of liquid rocket propellant. Stress is always laid on the pollution of UDMH to water.
偏二甲肼（UDMH）是液体推进剂的主体燃料，其对水体的污染一直倍受重视。
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。
Heat transfer possibly results in the thermal wrinkling of transpiration cooling platelet of the liquid rocket engine (LRE) 's thrust chamber.
液体火箭发动机发汗冷却推力室的结构层板可能出现受热皱损。
Comes to the conclusion that the hybrid bearing can be used to the liquid rocket engine turbopump, and then puts forward the key technique to be solved.
得出了液体动静压滑动轴承可用于液体火箭发动机涡轮泵转子支撑的结论，同时提出了待解决的关键技术。
The pattern of liquid rocket propellant seep and steam diffusion is discussed in this paper, and the model of quantitative analysis is also established.
讨论了航天发射场液体推进剂泄漏及蒸汽逸散的模式，并建立了定量分析模型。
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。
Helmholtz resonators and quarter wave resonators are studied as the high frequency combustion instabilities suppression devices in liquid rocket engines.
本文针对抑制液体火箭发动机不稳定燃烧的声学装置——赫姆·霍兹声腔和四分之一波长管声腔进行了研究。
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。
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。
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。
The experimental research has shown that the artificial neural network has been successful employed in the fault detection of the large turbo-pump liquid rocket engine.
实验研究表明神经网络可以成功地应用于大型泵压式液体火箭发动机的故障检测。
The experimental research has shown that the artificial neural network has been successful employed in the fault detection of the large turbo-pump liquid rocket engine.
实验研究表明神经网络可以成功地应用于大型泵压式液体火箭发动机的故障检测。
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