The limits of chemical rocket engines.
限制的化学火箭发动机。
There are present rocket engines capable of reaching Mars in 2-3 months.
现有的火箭发动机可以使我们在2到3个月内到达火星。
The plume effects of rocket engines is the crux of developing a launch vehicle.
火箭发动机排气羽流的影响是研制火箭运载器的一个关键问题。
Solid-fuel rocket engines have a much larger capacity than liquid-fueled iterations.
中国已在西北部城市西安完成最大的固体燃料火箭发动机点火测试。
The modeling of priming process of Liquid Propellant Rocket Engines (LPRE) was studied.
研究了常温推进剂液体火箭发动机充填过程的建模问题。
The priming process of feed lines of cryogenic propellant liquid rocket engines was studied.
研究了低温推进剂液体火箭发动机供应管道系统充填过程的建模问题。
However, from what I gather, "hybrid" rocket engines use both solid and liquid or gas propellants.
然而我的理解是，“混合动力”火箭引擎同时使用固体燃料和液态或气态推进剂。
They would be built from shuttle booster rockets, fuel tanks and main engines, as well as moon rocket engines.
新型运载火箭将由飞船助推火箭、燃料箱、主发动机以及月球火箭发动机组成。
In 1969, AC Igniter plugs fire the second and third stage rocket engines that put the first me on the moon.
1969年，人类首次登月，AC火花塞引燃了第二和第三节火箭的引擎。
Steady state fault detection and diagnosis of liquid propellant rocket engines based on decision tree method;
利用液体火箭发动机作动力装置的火箭，又称液体推进剂火箭。
If we can go to space with improved hybrid rocket engines on half the fuel used now, that would be a giant step.
如果我能够坐在相当于只使用现今火箭所需一半燃料的改良型火箭上太空的话，那将会又是迈出了很大的一步。
Our method provides a more convincing consul - ting basis for analysing the exhausting flow field of rocket engines.
本文所建立的方法也为火箭发动机排气流场分析提供了一个更为可信的参考依据。
Based on fuzzy neural networks, a basic system used for vibration fault detection of rocket engines is proposed in this paper.
基于模糊神经网络提出了一种发动机振动故障检测的基本系统。
Lacking of fault samples is a knotty problem in the fault detection of complex systems such as Liquid-propellant Rocket Engines (LRE).
在对类似于液体火箭发动机这种复杂系统的故障检测过程中，一个非常棘手的问题是缺乏故障类样本。
The results of this paper are of practical significance to grain structural integrity analysis and computation of solid rocket engines.
该文的结果对固体火箭发动机装药结构完整性分析计算有重要的实用价值。
A similar effort simulates the launch vehicle digital computer (LVDC) that managed the firing of the rocket engines during ascent into orbit.
类似的工作仿真了在进入轨道期间管理火箭引擎点火的运载火箭数字计算机(LaunchVehicle Digital Computer,LVDC)。
Owing to the dissimilar combustion mode, their working process is different form that of solid rocket motors and the liquid rocket engines.
由于氧化剂和燃料的燃烧方式不同，固液火箭发动机工作过程和液体火箭发动机及固体火箭发动机有很大的区别。
But now our ability to scale up our rocket engines has been catching up, and in some cases surpassing our ability to supply the rocket fuel.
但现在，我们有能力增大我们的火箭引擎，甚至已经超越了提供火箭燃料的能力。
The scarfed nozzle is used in engines which can produce reversal thrust, or to produce revolving torque on turbine rocket engines at high speed.
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。
Over the last decade, the rise of data, or the rise of rocket fuel, got a little ahead of our ability to build rocket engines to absorb that fuel.
过去十年间，数据的积累或者说火箭燃料的增加，超出了我们建造火箭引擎吸收这些燃料的能力。
Helmholtz resonators and quarter wave resonators are studied as the high frequency combustion instabilities suppression devices in liquid rocket engines.
本文针对抑制液体火箭发动机不稳定燃烧的声学装置——赫姆·霍兹声腔和四分之一波长管声腔进行了研究。
The plume temperature is an important parameter, for solid propellant rocket engines and it is useful for determining the combustion process of the engine.
推进剂的羽焰温度是固体推进剂火箭发动机的重要参数，对于研究发动机内的燃烧过程具有重要价值。
Mims explains that hybrid rocket engines do exist, notably in Virgin Galactic's SpaceShipOne spacecraft, but there are several sticking points for widespread adoption.
Mims解释道，混合动力火箭引擎的确存在，那就是维珍银河飞船1号(Virgin Galactic ' sSpaceShipOne)飞行器，不过在广泛投入使用之前还存在着一些关口未被突破。
Dawn is able to perform the trick of moving from one asteroid to another thanks to its ion-rocket engines, pioneered on an earlier NASA mission called Deep Space one.
由于“黎明”号的离子火箭发动机是能够完成从一个小行星移动到另一个小行星上的技巧。曾早些时候，这种技巧在美国国家航空航天局被称作“深太空一号”任务中首次开创。
In this paper, the design principle, structure features and the accuracy analysis method of a test system with accuracy of 0.5% for solid rocket engines are introduced.
本文论述了固体火箭发动机0.5%高精度测试系统的设计原则、结构特点和精度分析方法。
The practical applications of this control system to the hypergolic bipropellant attitude control rocket engines at 30kg and 100kg thrust levels respectively are stated.
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.
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。
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