Propulsion is provided by a rocket engine, rather than a propeller and rudder, which makes steering difficult.
推进器是由火箭发动机提供的，而不是螺旋桨和方向舵，这使得转向变得困难。
How can a rocket engine that generates 5,000 degree steam and 13,800 pounds of thrust form icicles at the rim of its nozzle?
一个能制造出5000度高温蒸汽和13800磅推力的火箭推进器，是怎样使喷口边缘结冰的呢？
Some satellites come equipped with a rocket engine and propellant tank so controllers can aim their descent into an ocean instead of a neighborhood, but not all.
而有些卫星则装配了火箭发动机和推进剂贮箱，这样可以控制它们的坠落路线，将其引导坠落到海洋之中，而不是坠落到居民区里。
The company claims it has used experience gained in fields such as rocket engine manufacturing, nanotechnology and particle physics to have created the new blade.
该公司声称其使用了火箭引擎生产、纳米技术与粒子物理学等领域的经验技术，使这款新的刀片得以问世。
An analogy is to building a space rocket: you need a huge rocket engine, and you need a lot of fuel.
以造火箭来打个比方：你需要一台巨大的火箭引擎，你还要有足够的燃料。
Flow in injector passages of a variable thrust liquid propellant rocket engine was studied.
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。
Launch capability of liquid rocket engine can be improved by propellant utilization system.
采用推进剂利用系统可以提高运载火箭的发射能力。
The spray process in the rocket engine is described with the theory of high pressure evaporation.
用高压蒸发理论对火箭发动机喷雾过程进行了描述。
Then several proposals are put forward in order to ensure the ignition reliability of rocket engine.
根据工作实践对如何确保发动机点火可靠性提出了几点建议。
It is a new experience to apply magnetic levitation technique to thrust measurement for rocket engine.
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。
The paper introduces a new method of measuring combustion time with CAT technique for solid rocket engine.
介绍一种应用CAT技术确定固体火箭发动机燃烧时间的新方法。
The design and realization of a variable thrust liquid rocket engine control system is present in this paper.
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。
Rotor dynamic is one of the most complicated problems in development of LOX turbopump of liquid rocket engine.
转子动力学问题是液体火箭发动机研制中最复杂的问题之一。
A general method for the cycle power balance calculation of the liquid rocket engine is proposed in this paper.
本文提出了一种新的液体火箭发动机功率平衡通用计算方法。
The basic theory, main characteristic and technic al state of all kinds of electric rocket engine were discussed.
论述了各种电火箭发动机的工作原理、主要特点和研究现状。
The hot flow fields in liquid rocket engine combustion chamber with and without baffles are simulated numerically.
用数值方法模拟了液体火箭发动机燃烧室内有无隔板两种情况的热态解。
The detonation wave ignition technique is suitable to synchronization ignition of multi-chamber liquid rocket engine.
爆震波多管点火技术适合用于多燃烧室液体火箭发动机的同步点火。
A neural network classifier that utilizes fuzzy sets as failure classes of a liquid propellant rocket engine is studied.
研究了一种用模糊集表示火箭发动机故障模式的神经网络分类器。
The complex flow was simulated with sequential and parallel SIMPLE algorithm in the combustion chamber of liquid rocket engine.
用串行和并行SIMPLE算法对液体火箭发动机燃烧室内的复杂流动进行了数值模拟。
The mode shapes of the high-speed shaft in rotating test-bed for rocket engine within working excited frequencies were studied.
研究了火箭发动机高速旋转试验台高速轴在工作激振频率内的振型。
Finally, based on the model data, the neural networks are applied to recognize several fault patterns of the liquid rocket engine.
最后，基于模型数据，应用神经网络识别了液体火箭发动机的几种故障模式。
The results show that parallel and distributed method can play an important role on the numerical simulation in liquid rocket engine.
从测试结果可以看出，并行与分布处理技术在液体火箭发动机复杂内流场的数值模拟方面能发挥重要作用。
A pulse width sampled-data control system for a variable thrust liquid rocket engine is studied both theoretically and experimentally.
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 variable structure control system for the start up process of staged combustion cycle liquid rocket engine is presented in this paper.
针对分级燃烧循环液体火箭发动机启动过程的特点，提出了一种变结构控制系统。
The general integral equations are derived for liquid and gas components of space propulsion systems with liquid propellant rocket engine.
针对采用液体推进剂火箭发动机的空间推进系统，推导了系统液路和气路的通用积分形式方程。
The nonlinear high frequency combustion instability process in the liquid rocket engine is simulated with the method of nonlinear dynamics.
采用非线性动力学方法对液体火箭发动机非线性高频燃烧不稳定工作过程进行了研究。
This paper established the mathematical models of the whole operation process of gelled propellant rocket engine based on system disassembly.
基于系统分解方式，建立凝胶推进剂火箭发动机工作过程的数学模型，并采用液流试验数据对其进行修正。
A micro computer system is introduced for condition monitoring and fault diagnosis in the ground testing of a throttling liquid rocket engine.
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。
The ablative property requirements and the studies on the insulation layer of solid rocket engine in oxidizer rich environment were presented.
介绍了富氧环境下固体火箭发动机对绝热层性能的要求，以及在该特殊条件下对绝热层所开展的研究工作。
Results of subscale engine test show that the insulation (PFDH-2) can be used for heat protection of oxidizer rich solid rocket engine chamber.
试车结果表明，PFDH - 2绝热层可以对富氧环境下工作的发动机燃烧室实施有效热防护。
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