液体火箭

基于免疫Agent的液体火箭发动机故障诊断

Fault diagnosis of liquid rocket engine based on immune Agent

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AHP的液体火箭发动机地面试验监测参数的选取方法研究

Study of Monitoring Parameter Selection Based on AHP for LRE in Ground Test

基于CFD的液体火箭发动机喷管型面优化

Nozzle optimization of liquid rocket engine based on CFD

液体火箭发动机失效的Weibull分布环境因子

Environmental factor of Weibull distribution for liquid rocket engine failure

本文的主要工作面向液体火箭发动机设计CAD技术，并选择再生冷却式液体火箭发动机推力室设计CAD技术研究作为方向。

This paper mainly focuses on CAD of LRE design , and present studies on CAD technique of recycled cooling LRE combustion chamber .

应用BP神经网络，提出了一种液体火箭发动机故障实时检测系统。

A fault detection system for a liquid propellant rocket engine was proposed in the realtime conditions using the back propagation ( BP ) neural network .

Elman型神经网络在液体火箭发动机故障预测中的应用

Application of Elman Neural Network on Liquid Rocket Engine Fault Prediction

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

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

对计算流体动力学（CFD）在液体火箭发动机中的应用情况进行了全面的回顾与分析，提出了今后的发展趋势与方向。

This paper overviews the application of computational fluid dynamics in liquid propellant rocket engine , presents its trends of development in future .

基于Gompertz模型的液体火箭发动机可靠性增长分析

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

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。

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

液体火箭Pogo振动蓄压器非线性仿真研究

A nonlinear model on the simulation of pogo vibrations in liquid rockets

以平台液体火箭发动机为研究对象，改进和完善了用于发动机实时故障检测的自适应阈值门限算法（ATA算法），提高了算法检测的适用性。

The ATA algorithm was improved for the platform for liquid-propellant rocket engines and the applicability of the algorithm was improved .

捆绑液体火箭跷振（POGO）稳定性分析

POGO analysis of cluster liquid rocket

因此，MATA适合于液体火箭发动机涡轮泵的实时故障检测。

As a conclusion , MATA is suitable for the real time fault detection of LRE turbopump .

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。

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 .

基于化学平衡和化学动力学理论，用C++和FORTRAN编写了液体火箭发动机喷管性能一维计算软件。

Based on the theory of chemical equilibrium and kinetic methods , one software for one dimensional nozzle performance calculation written by C + + and FORTRAN is introduced in this paper .

环形不稳定性计算模型在FY-20液体火箭发动机上的应用

Application of annular instability model to FY-20 liquid propellant rocket engine

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

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

详细描述了液体火箭推进剂（N2O4／UDMH）爆炸试验装置及其爆炸热过程特性测量。

Est facility , measurement methods of heat process and measurement system for liquid propellant ( N2O4 / UDMH ) explosion are described .

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。

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 .

以YF-75发动机为平台的三组元液体火箭发动机系统设计

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

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。

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 .

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。

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

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 .

液体火箭发动机寿命可靠性的贝叶斯下限

Bayesian Lower Limit of Life-time Reliability for Liquid Propellant Rocket Engine

液体火箭发动机热试车数据微机自动采集系统

A microcomputer data auto-acquisition system in liquid rocket engine firing tests

模态区间在液体火箭发动机故障诊断中的应用

Application of Modal Intervals in the Diagnosis of Liquid-propellant Rocket Engine