对液体火箭发动机主涡轮的性能试验进行了介绍。
The performance tests of the main turbine of a liquid rocket engine are introduced in this paper.
研究了常温推进剂液体火箭发动机充填过程的建模问题。
The modeling of priming process of Liquid Propellant Rocket Engines (LPRE) was studied.
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。
Rotor dynamic is one of the most complicated problems in development of LOX turbopump of liquid rocket engine.
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 general method for the cycle power balance calculation of the liquid rocket engine is proposed in this paper.
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。
Flow in injector passages of a variable thrust liquid propellant rocket engine was studied.
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。
Heat transfer possibly results in the thermal wrinkling of transpiration cooling platelet of the liquid rocket engine (LRE) 's thrust chamber.
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。
The hydrodynamic design of advanced liquid rocket engine high performance inducers is a challenging technology.
提出了一种新的液体火箭发动机分级燃烧循环最高室压计算方法。
A new modular method for calculating the maximum combustion chamber pressure with stage combustion cycles is proposed 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。
The design and realization of a variable thrust liquid rocket engine control system is present in this paper.
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 detonation wave ignition technique is suitable to synchronization ignition of multi-chamber liquid rocket engine.
本文设计了100n范围内小推力液体火箭发动机动态推力测试台架。
This article has designed the dynamic thrust test-bench for low-thrust liquid rocket engine within 100n.
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.
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 hot flow fields in liquid rocket engine combustion chamber with and without baffles are simulated numerically.
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 numerical model was employed to analyze the tangential combustion instability in 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。
Finally, based on the model data, the neural networks are applied to recognize several fault patterns of the liquid rocket engine.
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 variable structure control system for the start up process of staged combustion cycle liquid rocket engine is presented in this paper.
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 pulse width sampled-data control system for a variable thrust liquid rocket engine is studied both theoretically and experimentally.
液体火箭发动机试验的原始测量数据中存在着噪声，影响了数据的准确性和可信性。
Noise in the raw acquired data of liquid propellant rocket engine test can reduce accuracy and creditability of the data.
通过转子试验平台实时数据和液体火箭发动机历史试车数据，验证了TP-FDS。
Then, with the help of historical data from LRE test as well as real-time data from rotor test platform, the TP-FDS was validated.
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。
A micro computer system is introduced for condition monitoring and fault diagnosis in the ground testing of a throttling liquid rocket engine.
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。
The nonlinear high frequency combustion instability process in the liquid rocket engine is simulated with the method of nonlinear dynamics.
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。
The complex flow was simulated with sequential and parallel SIMPLE algorithm in the combustion chamber of 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。
Attributing to the large flow rate, high efficiency level reaction turbine is adoptive in 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。
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.
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。
Firstly, the static and dynamic mathematic model of the Liquid Propellant Rocket Engine of pressure-fed providing system was established in centralized parameter method.
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 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.
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。
The loss factors in liquid rocket turbine are analysed in detail and a related mathematical model and calculation method is proposed.
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。
Lacking of fault samples is a knotty problem in the fault detection of complex systems such as Liquid-propellant Rocket Engines (LRE).
本文用环形不稳定性计算模型计算、分析了FY -20液体火箭发动机的切向高频燃烧不稳定性。
This paper presents computation and analysis of tangential mode of high frequency combustion instability in FY-20 liquid propellant rocket engine by means of the annular instability model.
建立了任意斜交曲线坐标系下液体火箭发动机(LRE)内部工作过程的气液两相湍流化学反应流模型。
Two-phase turbulent reacting flow model of the internal operating processes in Liquid Rocket Engine (LRE) is set up in non-orthogonal curvilinear coordinates.
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