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.
将电磁悬浮技术用于火箭发动机推力测试试验台是一次新的尝试。
It is a new experience to apply magnetic levitation technique to thrust measurement for rocket engine.
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.
理论的运作：一火箭发动机推力对一个充满水的注射器，这产生的压力读数，就一连接压力计。
Theory Of Operation: a rocket engine thrusts against a water filled syringe. This produces pressure readings on a connected pressure gauge.
推力测试台架是准确测量火箭发动机推力的关键技术之一，但现有的测试台架能够很好兼顾长、短脉冲测试的较少。
Thrust test-bench is one of the key technologies for accurate measure of rocket engine thrust. But test-benches that can compromise with both long and short burst measurement are quite few.
并指出，随着研究工作的深入，该项技术还可望用于高马赫数飞行体表面气体流动控制、火箭发动机推力方向控制等。
Along with the deep development of study, the microjet technology will be possibly applied to control the aerodynamic flow of the high speed aircraft surface and the thrust vector of rocket engine.
重点介绍了一种用于测量火箭发动机推力矢量的压电式测试系统，并设计了对测试系统进行静态标定和动态标定的装置。
A piezoelectricity measuring system used for measuring rocket thrust vector is introduced. A devices to static accomplish, calibration and dynamic calibration on the system is designed.
发动机工作性能对火箭飞行性能的严重影响已引起众多研究人员的重视，尤其是火箭发动机推力总冲及其工作时间等重要参数。
The severe influence of the rocket engine property, especially its total thrust impulse and work time on the rocket flight performance has aroused great attention among technological workers.
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.
“如果这些研究项目能获得批准，那么像送人上月球之类的事情，只有具有600吨推力的火箭发动机才能认为是合乎情理的”，Li Tongyu告诉BBC的新闻记者。
"Rockets (with 600-tonne thrust engines) would only be justified for things like sending humans to the Moon, if such projects are approved," told BBC News.
说明了该控制系统在30公斤级与100公斤级的双组元燃料变推力姿控火箭发动机中的具体应用情况。
The practical applications of this control system to the hypergolic bipropellant attitude control rocket engines at 30kg and 100kg thrust levels respectively are stated.
本文对变推力液体火箭发动机喷注器通道内介质流动进行求解。
Flow in injector passages of a variable thrust liquid propellant rocket engine was studied.
在研制变推力火箭发动机的过程中，低工况时遇到了燃烧振荡问题，我们采用横向挡流板很好地解决了这个问题。
On the development process of the variable thrust rocket engine combustion vibra ions are encountered in the low working conditions, we solved this problem finely by lateral baffle.
本文讨论了某型变推力液体火箭发动机数字控制系统的设计和实现。
The design and realization of a variable thrust liquid rocket engine control system is present in this paper.
脉冲爆震火箭发动机是一种利用脉冲式爆震波产生高温、高压燃气发出的冲量来产生推力的新型推进系统。
A pulse detonation rocket engine (PDRE) is a new propulsion system that generates thrust by using high-temperature and high-pressure air produced by pulse detonation waves.
本文设计了100n范围内小推力液体火箭发动机动态推力测试台架。
This article has designed the dynamic thrust test-bench for low-thrust liquid rocket engine within 100n.
本文对变推力液体火箭发动机的脉宽采样数字控制系统进行了理论分析和实验研究。
A pulse width sampled-data control system for a variable thrust liquid rocket engine is studied both theoretically and experimentally.
斜切喷管+常用于产生反向推力，或产生旋转力矩使火箭高速旋转的涡轮式火箭发动机中。
The scarfed nozzle is used in engines which can produce reversal thrust, or to produce revolving torque on turbine rocket engines at high speed.
本文介绍了一种用于变推力液体火箭发动机地面试车的工况监测和故障诊断微机系统。
A micro computer system is introduced for condition monitoring and fault diagnosis in the ground testing of a throttling liquid rocket engine.
本文提出了一种推力可调的固体火箭发动机的设想方案。
A conception of adjustable solid propellant rocket motor was proposed.
结果表明在喷喉尺寸固定且在喷口强度允许的条件下，喷口直径越大越有利于提高火箭发动机的推力。
The result show that the bigger of the diameter the higher of the assisted power of the rocket engine with the dimension of the throat is constant and the permit of the spout intensity.
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.
第一个使用液氧碳氢推进剂的国产液体燃料火箭发动机被安装在了火箭的E段上，它可以提供5.6吨的推力。
The first native liquid-fueled rocket engine used a liquid oxygen and carbon-hydrogen propellant, provided 5.6 tons of thrust, and was installed in unit e.
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.
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.
通过测量固体火箭发动机水下工作过程中的推力和侧向力，研究了扰流片和摆喷管两种推力矢量方式的水下推力矢量特性。
By measuring the thrust and lateral forces of solid rocket motor during firing conditions, the thrust vector control performances of jet TAB TVC and movable nozzle TVC were studied.
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.
本文介绍了固体火箭发动机水下推力矢量特性试验。
The thrust vector control(TVC) performance test of solid rocket motor is presented in this paper.
研究表明，九分力模型和九分力推力矢量试车台提高了推力矢量测量的精度，适合用于测量大型固体火箭发动机的推力矢量。
The study shows that the nine-component model and nine-component thrust vector stand can improve the precision of thrust vector measurement greatly.
研究表明，九分力模型和九分力推力矢量试车台提高了推力矢量测量的精度，适合用于测量大型固体火箭发动机的推力矢量。
The study shows that the nine-component model and nine-component thrust vector stand can improve the precision of thrust vector measurement greatly.
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