火箭发动机

固体火箭发动机工业CT探测系统

Industrial CT inspecting system for solid rocket motor

固体火箭发动机燃烧室X射线探伤中像质计的应用

Application of Image Quality Indicator in X-Radiographic Examination of Solid Rocket Motor Chamber

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 .

固体火箭发动机集成初步设计CAD系统研究

Some Progress in Development of Chinese Integrated Preliminary CAD Design of Solid Rocket Motors

认识到建立固体火箭发动机燃烧室X射线探伤像质计标准势在必行。

It was considered that the establishment of radiographic IQI standard for solid rocket motor chamber was necessary .

介绍一种应用CAT技术确定固体火箭发动机燃烧时间的新方法。

The paper introduces a new method of measuring combustion time with CAT technique for solid rocket engine .

火箭发动机可靠性增长评估的Bayes方法

The Bayes Method for Rocket Engine Reliability Growth Evaluation

基于爆破试验的CFRP固体火箭发动机壳体的可靠性设计

Reliability design of CFRP solid rocket motor vessel based on the burst experiment

H2O2-PE固液火箭发动机低频不稳定燃烧研究

Research on low frequency unstable combustion of H_2O_2-PE hybrid rocket motors

H2O2-PE固液混合火箭发动机试验研究

Experimental study on hydrogen peroxide and polyethylene hybrid rocket motors

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

用激光瞬态F-P干涉仪对火箭发动机真实燃气射流进行高速摄影

To Take the High-Speed Photography for Real Exhaust Plumes of Rocket Engine with Laser Transient F-P Interferometer

85%H2O2-PE固液火箭发动机工作过程研究

Research on Working Process of the 85 % H_2O_2-PE Hybrid Rocket Motor

Weibull寿命模型下火箭发动机可靠性增长试验的LS-Bayes分析

The LS-Bayes Analysis for Rocket Engine Reliability Growth Test under Weibull Life Model

在此基础上，将MDF方法应用于固体火箭发动机内弹道计算，通过算例验证了MDF方法的适用性。

Basing research above , the MDF method has been used for SRM internal ballistics calculation , which has been test by two cases .

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 .

讨论光纤布拉格光栅（FBG）传感技术用于固体火箭发动机结构应变场、温度场和损伤状况健康监测的可行性。

The feasibility of applying fiber gratings sensing on health monitoring of solid rocket motor ( SRM ) is discussed , including the strain measurement , temperature measurement and damage measurement .

试验结果表明，与使用EPDM绝热层材料相比，使用RTV绝热层材料，火箭发动机燃烧室羽流具有较高的信号透过率；

The test results show that the plume from the rocket chamber using RTV insulation material has higher signature penetrating rate than that using EPDM insulation material .

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 .

在大约时速200英里时他将启动为火箭发动机传送HTP的泵。

At about 200mph he will start the pump to deliver the HTP into the rocket .

利用N2O催化分解原理，设计了一个用于启动N2O混合火箭发动机的催化点火器。固液混合火箭发动机是采用液体作为氧化剂，固体作为燃料的一种典型的混合火箭发动机。

An innovative igniter based on catalytic decomposition of N2O was designed and manufactured . In a typical hybrid , the fuel is a solid and the oxidizer is a liquid .

用RTR技术研究固体火箭发动机燃烧室中粒子运动轨迹（I）可行性分析与试验研究

Experimental study of particles trajectory in firing solid rocket motor with RTR TECHNIQUE part ( I ) analysis of feasibility and experimental results

本文选用SSTK-ω湍流模型对采用烧结多孔介质进行发汗冷却的液体O2/H2火箭发动机推力室进行了全场耦合数值模拟研究。

In this study , the SST k - ω turbulence model was used to simulate the coupled whole field for the transpiration cooling of a thruster in a liquid O2 / H2 propellant rocket engine .

用Fluent计算流体力学软件对固体火箭发动机喷管流场进行了数值计算，研究了喷管收敛半角、喷管喉部上游圆弧曲率半径和喉部圆柱段长度对喷管流场的影响。

Nozzle flow field of SRM was numerically simulated with Fluent software . The effects of nozzle convergent half angle , radius of curvature on upstream of throat section and length of throat cylinder on flow field are investigated .

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

采用新型的Flash单片机、信号采集电路与温控电路等构成一个对固体火箭发动机温控系统，满足其固体火药的初始温度设计要求。

The paper states the way of incorporating a new type of flash singlechip , signal acquisition circuits , temperature-control circuits into a temperature-control system for a soild rocket motor , so as to fulfil the settings on the initial temperature of its charge .

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 .

CRTP火箭发动机测试系统

CRTP Rocket Engine Testing System

介绍了一种以数据采集卡为底层硬件，基于VC++界面和MATLAB数据处理混合编程开发的虚拟仪器技术，并将它用于火箭发动机推进剂药柱粘弹性性能测试。

The paper presents a development method of virtual instrument technology , which uses plug-in DAQ board as hardware and the hybrid programm on the basis of VC + + interface and MATLAB data treatment . The method is used to measure the viscoelastic properties of the propellant grain .

文中将小波分析理论、神经网络技术与D-S证据理论引入到火箭发动机故障诊断中，提出了一种适于发动机故障诊断的小波神经网络信息融合方法。

This text puts forward a kind of information fusion methods according to wavelet neural network that be suitable for fault diagnosis of rocket engine by leading into wavelet analysis theories , neural network technique and D-S evidence theory .