liquid rocket

Based on the condition that the performance test data of liquid rocket engine is subject to normal distribution with constant standard deviation, the Bayes method is used to analyze the environment factor of ground and space performance test.

基于液体火箭发动机性能试验数据服从正态分布的条件，假定天地试验环境下分布的标准差不变，运用Bayes方法对正态分布天地试验条件下的环境因子进行分析。

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Numerical Analysis and Application of Wall Temperature History for Liquid Rocket Engine Thrust chamber with Radiation Cooling

液体火箭发动机辐射冷却推力室壁温响应的数值分析及应用

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As to reliability growth management being an uncertain decision based on imperfect information, FMEA and fault diagnosis model have been built for liquid rocket engine.

针对液体火箭发动机可靠性增长过程管理是不完备信息下的不确定性决策问题，分别建立了液体火箭发动机的FMEA模型和故障诊断模型。

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This paper presents POGO analysis of cluster liquid rocket, summaries POGO approximation, points out important parameters influencing POGO, gives a example and conclusion.

本文提出捆绑液体火箭跷振（POGO）稳定性分析模型，简述近似方法，指出影响跷振的重要参数，给出了算例与结论。

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Application of Electrochemical Gas Sensor on Detection of Liquid Rocket Propellant

控制电位电解型气体传感器在液体推进剂检测中的应用

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BP ( Back Propagation) neural network used in liquid rocket engine ( LRE) failure simulation and detection was described.

研究了用于液体火箭发动机（LRE）故障仿真与故障检测的神经网络BP（BackPropanation）算法。

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Method of Sensor Fault Diagnosis in Liquid Rocket Engine Ground Testing Bed Hydrogen Providing System Based on MSPCA

基于MSPCA的液体火箭发动机试车台氢供应系统传感器故障诊断方法

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Finally, the applicability and effectiveness of the proposed methodology is illustrated by some sensors in the rocket engine ground testing bed liquid hydrogen providing system.

最后，以液体火箭发动机试车台氢供应系统几个关键传感器的故障诊断为例验证了这种方法实用性和有效性。

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POGO analysis of cluster liquid rocket

捆绑液体火箭跷振（POGO）稳定性分析

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Nozzle optimization of liquid rocket engine based on CFD

基于CFD的液体火箭发动机喷管型面优化

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As one of the few advanced countries in liquid propulsion, France actually began to study and develop liquid rocket engine on the morrow of World War II.

法国是开展液体推进技术研究较早的国家之一，也是当前世界上液体推进技术比较先进的一个国家，但他们在这一领域也经历了一个漫长曲折的发展过程。

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Through two methods measuring cutoff thrust and pressure of com-bustion chamber when testing liquid propellant rocket engine on ground, cu-toff impulse as simulated altitude condition is obtained. These methods are revie-wed simply, too.

本文叙述在地面条件下试验液体火箭发动机时，通过测量发动机后效段推力与测量发动机燃烧室压力两种方法来求得模拟高空后效冲量，并对这两种方法作简单评论。

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In this paper the power cycle s of liquid propellant rocket engines are divided into open cycle and close cycle and analyzed. Through the analysis, formulae for the power cycle efficiency of liquid propellant rocket engines are set up.

本文将液体火箭发动机的动力循环过程分为开式循环和闭式循环，并通过分析的办法，建立了发动机动力循环的效率公式。

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The leak of Liquid Rocket Engine ( LRE ) is very common and dangerous.

液体火箭发动机的泄漏是常见和极其危险的故障.

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A two-component rocket propellant, such as liquid hydrogen and liquid oxygen chamber as fuel and oxidizer.

一种蓝色透明、有磁性的液体,由压缩气态氧获得,用作火箭推进物中的氧化剂.

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The statistic estimation for the maximum flight time of a liquid rocket

液体火箭最大可飞行时间的统计评定方法

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Application of Elman Neural Network on Liquid Rocket Engine Fault Prediction

Elman型神经网络在液体火箭发动机故障预测中的应用

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Fault diagnosis of liquid rocket engine based on immune Agent

基于免疫Agent的液体火箭发动机故障诊断

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Considering the typical application background of the LH2/ LOX rocket engine turbopump, this paper discusses the development of the investigation about the hybrid bearing for the liquid rocket engine turbopump.

以液体火箭发动机涡轮泵为典型应用背景，讨论了液体动静压滑动轴承的技术特点及其用于液体火箭发动机涡轮泵转子支撑的研究进展情况；

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System Design of Tripropellant Liquid Rocket Engine Based on YF-75 Rocket Engine

以YF-75发动机为平台的三组元液体火箭发动机系统设计

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The two phase turbulent combustion steady process and high combustion instability in the liquid rocket engine are simulated with the method of computational combustion dynamics.

采用计算燃烧学的方法对发动机燃烧室内的湍流两相燃烧过程的稳定燃烧状态和高频不稳定燃烧现象进行了数值模拟。

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The major failure models of liquid rocket engines of foreign countries and china are analyzed.

分析了国内外液体火箭发动机主要故障模式；

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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。

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Using the definition of hydraulic coefficient and existent measurements of pressure or flow in pipes of liquid rocket engine, the pressure and the change amount of hydraulic coefficient will be determined according to appropriate calculation of a certain separate pipe.

利用水力系数（C（ADE））的性质和现有液体火箭发动机管路系统中压力或流量的测量值，进行适当分段组合，计算出相应的压力和水力系统改变量。

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A new modular method is proposed for static simulation of liquid rocket engine.

提出了一种新的液体火箭发动机静态仿真模块化计算方法.

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The Reliability Growth Analysis for Liquid Rocket Engine According to The Gompertz Model

基于Gompertz模型的液体火箭发动机可靠性增长分析

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Environmental factor of Weibull distribution for liquid rocket engine failure

液体火箭发动机失效的Weibull分布环境因子

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A Real-time Fault Diagnosis Approach to Liquid Rocket Propulsion Systems Using Mechanism Model and SOM Neural Networks

一种应用机理模型和SOM神经网络的液体火箭推进系统实时故障诊断方法

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Analysis of the tank pressurization calculation formula for a liquid propellant rocket

液体火箭贮箱增压计算公式的分析

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Disigning coolant channel on the firebox of liquid rocket engine to loxodrome ( equal-angle helix) groove can improve firebox coolant capability greatly.

将液体火箭发动机燃烧室的冷却通道设计为斜航线（等倾角螺旋线）槽形，可以大幅度改善燃烧室的冷却性能。

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