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.
分析了四机并联全辐射冷却推力室的热特点。
Heat transfer in four parallel connecting thrust Chambers with radiation cooling was analyzed.
然后，和现在一样，系统的核心仍将是推力室。
And then, as now, the heart of the system will remain the thrust chamber.
成功制造出带冷却通道的火箭发动机推力室身部样件。
A sample of rocket engine thrust chamber with cooling channels was successfully manufactured by APEF.
液体火箭发动机发汗冷却推力室的结构层板可能出现受热皱损。
Heat transfer possibly results in the thermal wrinkling of transpiration cooling platelet of the liquid rocket engine (LRE) 's thrust chamber.
据此编制通用程序，可以计算任意辐射冷却推力室的不稳定温度场。
According to this can be compiled general program and has been calculated unsteady temperature history for any thrust chamber with radiation cooling.
叙述了添加剂——甲基硅酮的性质和用添加剂降低推力室热流强的机理。
The properties of additive methyl silicone and the mechanism of heat flux reduction in the thrust chamber are described.
我们这里的讨论，不过，将关注更多的基本方面，这些引擎-尤其是，火箭发动机推力室。
Our discussion here, however, will be concerned with more basic aspects of those engines-in particular, the rocket engine thrust chamber.
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。
Based on a thermal model of monopropellant thrust chamber system including its components such as adiabatic frame, catalyst bed, nozzle etc.
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。
The research emphasis is restartable nitrous oxide monopropellant thruster suitable for keeping the position and phase of small satellite.
对推力室冷却通道内的人为粗糙度强化换热机理进行了分析，讨论了影响人为粗糙度强化换热的因素。
The mechanism and influence factors of artificial roughness (ar) on enhanced heat transfer in chamber cooling channels have been analyzed.
为了能够快速而准确地得到再生冷却推力室的温度分布，建立了一种计算再生冷却推力室温度场的方法。
To quickly and accurately obtain temperature distribution in regeneratively-cooled thrust chamber, a method of computing temperature field in thrust chamber was developed.
针对典型的层板发汗冷却结构，提出了利用一个推力室的实验数据来计算另一推力室所需发汗流强的方法。
A new calculation method was proposed for the typical structure of the platelet transpiration flux in the rocket thrust chamber based on the test data of another chamber.
仿真结果表明，利用M - c方法对推力室进行数值仿真是完全可行的，所用的非线性模型是足够准确的。
The simulation result indicates that the simulation of the engine chamber performances by using Monte-Carlo method is feasible and that the non linear model is accurate enough.
其次建立了推力室的冷却套二维导热模型，使用数值模拟的方法和一维计算的结果，得到了冷却套的温度场。
Secondly, two dimensional conductive model of cooling jacket was set up and numerical simulation was carried out using one dimensional results. Temperature field in cooling jacket was computed.
然后使用这种方法研究了气壁材料、气壁厚度和冷却液流量对推力室再生冷却的影响，获得了比较满意的结果。
Then using this method, influence of gas wall material, gas wall thickness and flow rate of coolant on regenerative cooling of thrust chamber was investigated. The results were satisfactory.
计算结果表明：增加通道深宽比对推力室壁面能够起到强化传热的作用，但同时也增加了冷却通道的进出口压差。
The simulation results show that the heat transfer of rocket chamber will be enhanced when increasing the aspect ratio, but the pressure drop will increase simultaneously.
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.
这些子级上安装了瓦·彼·格鲁什科设计的四推力室主发动机和谢·帕·科罗廖夫设计的用来控制推力矢量的新型姿态控制发动机。
The main four-chamber engines designed by V. P. Glushko and new control engines from s. P. Korolev for controlling the thrust vector were installed in these units.
采用三维有限元模型对液体火箭发动机铣槽推力室进行了壁温分布计算。边界条件按一维经验公式处理。计算中比较了不同冷却剂流量。
A calculation of the wall temperature distribution in liquid propellant rocket engine chamber with milled grooves was completed by the aid of three-dimensional finite element method.
腔室成功达到了100000Ibf的全推力。
The chamber successfully achieved a full thrust of 100000 Ibf.
MSH系列产品作为针对高压应用的设计，轴向推力通过平衡室系统和圆盘一起进行平衡。
The MSH range is designed for high pressure applications and the axial thrust is balanced by the combination of the drum and disc.
入口推力器，磨米室，大米筛，大米铰刀，米辊，出口等。
It is consisted of entry thruster, rice grinding room, rice griddle, rice reamer, rice roller, exit etc.
在文中所研究的引射燃烧室结构条件下，存在一个最佳二次喷管出口面积，它能使引射火箭的推力达到最大。
There exists an optimal exit area of secondary nozzle to result in a maximum thrust of rocket ejector in the light of the investigated ejector chamber structure.
本文从燃烧室压力、系统工作循环方式以及最大推力三个方面叙述了世界各国液体火箭发动机的技术水平。
This paper presents the development of the liquid propellant rocket engine technology from the viewpoint of combustion chamber pressure, thrust level and power cycle.
结果分析表明，压缩室直径对推力器性能具有较大影响。
The results show that constrictor diameters have significant influence on operating performance of the thrusters.
结果显示喉栓能够有效改变发动机燃烧室压力和推力，满足发动机推力控制要求。
Results show that pintle could change the nozzle throat area and thus the motor pressure and thrust, which provided the capability for thrust control.
本文讨论了单室双推力星形装药固体火箭发动机的结构优化方法。
This paper presents a method of optimum design for single-chamber double-thrust solid rocket motors.
该项研究主要测量了发动机的推力和燃烧室压力。
The combustion chamber pressure and propulsive force were tested.
这些气体的形式迅速扩大，并通过燃烧室，并通过喷嘴（打击）提供前进推力出后用尽。
The gases which form expand rapidly, and are exhausted through the rear of the combustion chambers and out through the nozzle (blow) providing the forward thrust.
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