liquid rocket的例句大全

The Effect of Density Measurement in Cryogenic Liquid Rocket Engine Test

密度测量在低温液体火箭发动机试验中的作用

Acoustic analysis of resonators for combustion instability suppression in liquid rocket engines

液体火箭发动机中声腔抑制不稳定燃烧的声学分析

Research and Parameter Analysis of POGO Vibration in Liquid Rocket

液体火箭的POGO振动研究与参数分析

The article hereunder describes the history of liquid rocket propulsion in France through the last 50 years.

本文回顾了法国液体火箭推进技术在过去50年间的发展历史。

This gas generator cycle for pump-fed liquid rocket engine was chosen.

发动机采用泵压式燃气发生器动力循环系统。

Numerical simulation of heat transfer in a transpiration cooled liquid rocket thrust chamber(ⅱ) numerical method and results

液体火箭发动机推力室发汗冷却传热过程的数值模拟（Ⅱ）数值方法与计算结果

Study on Fault Monitoring and Diagnosis Techniques for Thrust Chamber and Turbo pump Systems of Liquid Rocket Engines

液发推力室和涡轮泵故障监测与诊断技术研究

Hydrogen and oxygen orbital maneuver thruster, based on gas-dynamic resonance ignition, is a new liquid rocket propulsion technology, and is especially applicable to space station.

基于气动谐振点火技术的氢/氧变轨发动机是一项新型的液体火箭推进技术，尤其适用于空间站应用。

Fuzzy min-max neural networks and its application to liquid rocket engine failure classification

模糊极小极大神经网络在火箭发动机故障分类中的应用

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。

The results of static firing test shows that the thermal erosion properties, mechanical properties, tand thermal shock resistance of the C/ SiC composites can meet a demand for thermal-structure application in the area of Aerospace such as liquid rocket thruster.

试验发动机地面热试车结果表明，该C/SIC复合材料的力学性能、烧蚀性能和热震性能优良，可满足宇航工程中诸如液体火箭发动机推力室等对热结构材料的使用性能要求。

Measurement technology of thermocouple sensor in the liquid rocket engine test

液体火箭发动机试验热电偶传感器测量工艺

Thermal control for platelet transpiration cooled preburner of liquid rocket engine using liquid oxygen

液体火箭发动机层板式预燃室液氧发汗冷却热控制

Numerical Simulation and Experimental Validation of Chemical Reaction Viscous Turbulent Flow Field in the Nozzle of Liquid Rocket Motor

液体火箭发动机喷管化学反应黏性流场数值模拟和实验验证

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。

In the field of aerospace manufacturing, the processing of the spiral cooling channel, which is on the combustion chamber nozzle of liquid rocket engine, is a key technology.

在航天制造领域中，液体火箭发动机燃烧室喷管的螺旋式冷却通道加工是一项关键技术。

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

Primary analysis of deep cooled turbojet liquid rocket engine combined cycle

深冷涡喷火箭组合循环发动机初步分析

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

Effect of aspect ratio on heat transfer and fluid flow in regenerative cooling channel of liquid rocket engine thrust chamber

通道深宽比对液体火箭发动机推力室再生冷却的影响