推力室

同相催化的单组元液体推进器，其关键部件是微小型推力室，包括催化反应腔和喷管等结构，试验样机的冲量输出分辨率优于80μNs。

The key component of the homogeneously catalyzed micro monopropellant thruster is its micro thrust chamber , which consists of the catalytic reaction tank and the micro nozzle . The impulse output resolution of the experimental prototype is better than 80 μ Ns .

UDMH中添加1重量%硅酮后，推进剂使用性质略有改善，推力室总热流下降约33%。

When 1wt % Si is added into UDMH , there is slight improvement in the operational property of pro-pellant ; and the total heat flux of the thrust chamber has been reduced about 33 % .

四氧化二氮/一甲基肼推力室研制＞0，（1一E）。

Research on n_2o_4 / mmh thruster if f1 ( 0 ) .

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 .

在此基础上，应用有限元数值计算的方法，将模型进行轴对称Delaunay非结构化网格剖分，并完成瞬态温度场的模拟计算，进行推力室在轨温度的数值仿真。

, temperature simulation was carried out by FEM with axisymmetric unstructured Delaunay girds generated and transient temperature distribution .

分析了单组元肼催化分解推力室工作过程中产生催化剂床冲蚀（Washout）现象的原因，并采取了相应的消除该现象的措施。

The paper analyzes the cause of catalyst bed washout during the operation of monopropellant hydrazine catalytic decomposition thruster .

600N单组元推力室的研制

Development of a 600N monopropellant thruster

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 .

本文主要介绍90N和490N两种四氧化二氮/一甲基肼推力室的设计及试验概况。

In this paper the design and the test of two N2O4 / MMH thru-sters , with thrust of 98N or 490N , are chiefly described .

推力室槽道式冷却通道尺寸优化设计方法

Optimal design method for channel size of thrust chamber cooling passage

辐射冷却推力室的比冲损失计算

Calculation of the Specific Impulse Loss for Radiative Cooling Thrust Chamber

气氧/煤油发动机水冷推力室壁热分析

Thermal Analysis of GO 2 / Kerosene Rocket Thrust Chamber Wall

带簇式推力室的固液火箭发动机装药设计

Grain design for hybrid rocket engine with cluster type thrust chamber

太阳能火箭发动机吸热/推力室流场及性能计算

Flow and performance calculation of absorber / thruster of solar thermal propulsion

随着冷却剂流量的增大，推力室壁中的最高温度明显下降；

The maximum temperature of the wall decreases with increasing coolant flow .

再生冷却推力室耦合传热数值模拟

Numerical study on coupled heat transfer of thrust chamber with regenerative cooling

三组元火箭发动机推力室试验研究

Experimental research on the thrust chamber of tripropellant rocket engine

单组元推力室在真空深冷环境中的降温分析

Temperature drop analysis on the monopropellant thruster in the vacuum cryogenic environment

研究了飞船推进系统推力室工作过程。

Operating process of thrust chamber in spacecraft propulsion system is studied .

冷却剂不同流动方式对膨胀循环推力室再生冷却换热的影响

Heat transfer characteristics of expander cycle thrust chamber with different cooling routing

液体火箭发动机烧蚀冷却推力室室壁温度响应的计算

Wall Temperature Response Calculation of Ablative Cooling Chamber of LRE

内部再生冷却推力室及其传热分析

The internal regenerative cooling thrust chamber and the analysis of its heat transfer

隔热罩对火箭发动机推力室温度场的影响

The Effect of Heat Shield on Temperature Distribution of Rocket Engine Thrust Chamber

液体火箭发动机推力室粘性流场数值模拟和实验验证

Numerical simulation and experimental validation for viscous flow field in rocket engine chamber

过氧化氢推力室技术研究

A Study of thrust chamber technology using hydrogen peroxide

推力室喉部层板发汗冷却段的结构设计分析

Structural design analysis for platelet transpiration cooling section at throat of thrust chamber

三组元液体火箭发动机推力室燃烧与再生冷却仿真研究

Simulation Investigations of Combustion and Regenerative Cooling of Tripropellant Liquid Rocket Engine Thrust

对于烧蚀冷却的推力室必须解决以下诸问题：a。

The following problems are to be solved for ablative cooling thrust chamber : a.

层板发汗冷却推力室的传热特性

Heat Transfer Characteristics of Platelet Transpiration-Cooling Thrust Chamber

验证调节器转级时发生器点火路和推力室点火路的充填特性，获得了流量调节器和换向阀的工作特性参数。

Operational parameters of the flow rate regulator and the change valve were obtained .