Turbopump is an important part in liquid rocket engine.
涡轮泵是液体火箭发动机的重要组成部份。
The leak of Liquid Rocket Engine (LRE) is very common and dangerous.
火箭发动机的泄漏是常见和极其危险的故障。
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。
It is very important to measure liquid density in cryogenic liquid rocket engine test.
在低温液体火箭发动机的试验中，对液体密度的测量是很重要的。
Conclusion Chronic effect, induced by liquid rocket propellant, was observed in our study.
结论液体火箭推进剂致伤后的远期效应明显。
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。
There are still many problems using current reliability management method for liquid rocket engine.
当前的可靠性增长管理方法在液体火箭发动机中的应用存在诸多问题。
This article has designed the dynamic thrust test-bench for low-thrust liquid rocket engine within 100n.
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。
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。
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。
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。
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。
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。
Owing to the dissimilar combustion mode, their working process is different form that of solid rocket motors and the liquid rocket engines.
由于氧化剂和燃料的燃烧方式不同，固液火箭发动机工作过程和液体火箭发动机及固体火箭发动机有很大的区别。
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。
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。
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