monopropellant

Temperature Distribution Measurement of High Energetic Monopropellant by Spectroscopic Diagnostic Technology

用光谱诊断技术测定高能单元推进剂的温度分布

On theory of unsteady decomposition combustion for a liquid monopropellant droplet at high temperature and high pressure

液体单元推进剂滴的高温高压非定常分解燃烧理论

Numerical and experimental studies for temperature field of monopropellant hydrazine thruster

单组元肼推力器温度场仿真及试验

Thermal Analysis and Control of Monopropellant Catalytic Decomposition Hydrazine Engines

单元肼催化分解发动机的热分析与热控制

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

单组元推力室在真空深冷环境中的降温分析

Study on extrusion and exhaust process of monopropellant pulse thruster

单组元脉冲推力器挤压和排气过程分析

Investigation of parameter sensitivity in micro monopropellant thruster based on N_2O

N2O单组元微型推进器内参数敏感性的研究

Finite element analysis on preheating process of N_2O monopropellant thruster

N2O单组元推力器预热过程有限元分析PTA过程关键单元建模与流程模拟

Mathematical model and simulation results of equilibrium compositions of OTTO - ⅱ monopropellant 's combustion products

奥托-Ⅱ单组元推进剂燃烧产物平衡组成计算模型及仿真结果

Thermal control of monopropellant catalytic decomposition hydrazine engines in important portion of space propulsive system .

单组元肼分解发动机的热控制与热分析是空间推进系统重要组成部分。

On Combustion of Liquid Monopropellant in Rotating Combustion Chamber

旋转燃烧室中燃烧性能研究

Rigid Element Analysis for Stamping Springback Simulation ; Study on extrusion and exhaust process of monopropellant pulse thruster

冲压成形回弹仿真的刚性单元法研究单组元脉冲推力器挤压和排气过程分析

Technology for space chemical propulsion includes bipropellant propulsion , monopropellant propulsion and micro propulsion .

空间化学推进技术包括双组元推进、单组元推进和微推进技术。

Thermal Decomposition Studies of Monopropellant

单元推进剂的热分解研究

Based on a thermal model of monopropellant thrust chamber system including its components such as adiabatic frame , catalyst bed , nozzle etc.

建立了单组元发动机推力室系统（包括结构部件如隔热框、催化床、喷管等）的传热模型。

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

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。

To evaluate pre-heating process of N_2O monopropellant thruster and reduce pre-heating energy , a numerical model was developed .

为了解决N2O单组元推进器存在的预热能量消耗过大，启动时间过长的问题，在实验基础上建立了推进器预热过程的数学模型。

Numerical investigation on low power monopropellant hydrazine thruster ( I ) Experimental verification and influence of insulative sleeve on temperature field

小推力单元肼推力器温度场数值分析（I）实验验证和保温套筒对温度场影响探析

The research emphasis is restartable nitrous oxide monopropellant thruster suitable for keeping the position and phase of small satellite .

研究重点是可多次启动的一氧化二氮单元推进剂推力室，适用于小卫星的位置保持和相位保持。

Fuel vaporization is identified as the combustion rate limiting process , and determines the decomposition rates of monopropellant gas phase of MMH .

以蒸发作为燃烧速率控制过程，由MMH的分解蒸发速率来控制。

The ( investigation ) results show that the curves of combustion flame temperature distribution in all combustion course are accurately measured by relative intensity method for monopropellant HNIW .

结果表明，相对强度法能准确地测出单元推进剂HNIW在整个燃烧过程的温度分布曲线，测得的最高燃烧火焰温度低于相应压力下的理论计算温度；

Development of a 600N monopropellant thruster

600N单组元推力室的研制

Preliminary scheme and primary design parameters were described for a micro propulsion system used for the attitude control of the spacecraft , which is based on the monopropellant catalytic decomposition of nitrous oxide .

针对利用N2O单组元催化分解产生热气、用于精确控制飞行器姿态的微推进系统，提出了初步的系统方案和主要设计参数。

The comparison between the solid bipropellant firing results and the monopropellant firing results appears to be quite good . Swelling and porosity of the propellant mixture became evident after 6 days at ambient temperature .

固体二元推进剂和单元推进剂的点火试验结果是很相近的。在室温下将药柱放置6天后，推进剂呈现膨胀和气孔。

According to our technical base of monopropellant and bipropellant propulsion systems , and the task requirement of satellites on the life , control precision , operation environments , the preliminary idea on design of dual-mode propellant systems was illustrated .

在此基础上，根据我国已有的航天器单、双组元推进技术基础和航天任务对寿命、控制精度及工作环境提出了新的要求，并指出了发展双模式推进系统的初步设想。

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 .

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。