liquid propellant
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n.
火箭引擎中的液体燃料；
权威例句
Liquid propellantLiquid propellant
Liquid propellant
Liquid-propellant rocket
Modern Engineering for Design of Liquid-Propellant Rocket Engines
Liquid Propellant Rocket Combustion Instability. NASA SP-194
Liquid-Propellant Rocket Engine Injector Dynamics
THEORY OF COMBUSTION INSTABILITY IN LIQUID PROPELLANT ROCKET MOTORS
Transverse Combustion Instability in Liquid Propellant Rocket Motors
Variable structure control of time-delay systems with a simulation study on stabilizing combustion in liquid propellant rocket motors
Recovery of Monomethylhydrazine Liquid Propellant by Pervaporation Technique†
Overview of Combustion Instabilities in Liquid-Propellant Rocket Engines
Liquid-propellant rocket engines health-monitoring—a survey ☆
1. Liquid propellant combustion processes are quite complicated and defy precise analytical description.
液体推进剂燃烧过程是相当复杂的，很难对其进行严谨的分析描述。
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2. This paper attempts to analyse the tendency to develop liquid propellant rocket propulsion technology according to the requirements o launch vehicles and spacecrafts.
本文试图根据运载火箭和航天器的需要来分析液体火箭推进技术的发展趋势。
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3. To appreciate the unsteady environment existing in liquid propellant rocket chambers it is necessary that the steady state be well understood.
为了分析液体推进剂火箭发动机燃烧室中存在的非稳态环境，必须很好地了解稳态状态。
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4. Some stratification exists in the spray produced by any liquid propellant injector.
由任何液体推进剂喷注器所产生的喷雾都存在某些成层现象。
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5. This paper analyzes the leakage that may occur during the liquid propellant store and transport, builds up the leakage fault tree and discusses how the basic incident affects the leakage incident.
对液体推进剂在贮运过程中发生的泄漏情况进行了深入分析，建立了故障树模型，并讨论了底事件对泄漏事件的影响。
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6. Acceptance testing equipment for production of liquid propellant.
生产液体推进剂用的验收试验设备。
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7. Hydroxylammonium nitrate (HAN) is the main active toxic component of the new HAN based liquid propellant.
硝酸羟胺(HAN)是新型硝酸羟胺基液体推进剂的主要毒理活性成分。
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8. 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。
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9. The structure design for sloshing suppression in a liquid propellant tank results in the nonlinear characteristics of liquid sloshing damping.
液体推进剂贮箱的防晃结构设计导致液体晃动阻尼的非线性特性。
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10. 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。
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11. Objective To establish model of the blast-toxicosis combined injury caused by the explosion of the liquid propellant.
目的复制冲击波和液体火箭推进剂中毒致冲毒复合伤的动物模型。
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12. Propellant feeding system is indispensable to laser propulsion thruster with liquid propellant.
工质注入系统是液体推进剂激光推力器必不可少的一个组成部分。
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13. 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。
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14. Theoretically, any liquid propellant may be manufactured into gelled propellant.
从理论上说，任何液体推进剂都可以制成胶体推进剂。
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15. Positive pressure light protective appliance for liquid propellant was manufactured, by using the electric airing technology, the dressed comfortability was enhanced.
研制了一种能有效防护液体火箭推进剂的正压式轻型防护服，利用电动送风技术，极大提高了穿着的舒适性。
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16. The method, called pressure stimulation by gas injection, was introduced in detail for the measurement of liquid propellant residue on the national satellite. A technical scheme in practice was given.
比较全面地介绍了适合我国卫星液体推进剂测量的气体注入压力激励方法，对相关应用技术问题进行了分析讨论。
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17. This method can quickly and accurately check and diagnose the potential fault of the liquid propellant store and transport, which would be benefit for liquid propellant safe store and transport.
该方法能快速准确的检测和诊断液体推进剂贮运的潜在故障，对推进剂安全贮运有一定裨益。
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18. The membrane tank is that one kind of liquid propellant of space system is broad used.
隔膜贮箱是一种空间系统应用较广泛的液体推进剂贮箱。
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19. It was stable, economical, practical and easy to repeat. Conclusions Injury caused by the explosion of liquid propellant can be simulated by using the blast wave tube and the intoxication tank.
结论利用生物激波管冲击和染毒柜染毒相结合的形式可以模拟复制现场液体火箭推进剂爆炸致冲毒复合伤的动物模型。
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20. Aimed at nonsteady spray combustion flow problems of regenerative liquid propellant gun (RLPG) in process of interior ballistic, mathematical model was established, and numerical method was derived.
针对再生式液体发射药火炮(RLPG)内弹道过程中非稳态喷雾燃烧流动问题，建立了数学模型，给出了具体的计算方法。
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21. A theoretical model has been presented to describe the combustion process in a liquid propellant electrothermal chemical launcher.
该文提出描述液体工质电热化学发射装置中燃烧过程的理论模型。
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22. Several key problems existed in field operation of liquid propellant are solved and field experiment results are given also.
解决了液体药现场施工过程中的几个关键问题，并给出了现场试验效果。
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23. This paper presents the development of the liquid propellant rocket engine technology from the viewpoint of combustion chamber pressure, thrust level and power cycle.
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。
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24. This paper relates to the current development, fire mechanism, operating mode and development tendency of liquid propellant gun and presents its features and advantages.
本文简述了舰载液体发射药火炮研制概况、发射机理、工作方式、目前研制方向和重点，分析了液体发射药火炮的特性和优点。
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25. Combustion instability, encountered in the development of researches of liquid propellant engines, is one of the significant challenges, which has tremendous destructivity.
燃烧不稳定性问题是发动机燃烧室研制过程中所遇到的难题之一，它具有极强的破坏作用。
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26. The material which the liquid-propellant rockets burn to make the jet gases is liquid. This is something like gasoline, or kerosene, or alcohol that can brun.
液化推进火箭通过燃烧产生喷气的材料是液体；这种液体有点像汽油、煤油或酒精一类燃料。
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27. In the interior ballistic cycle of regenerative liquid propellant gun, in addition to motion of projectile, there exists motion of piston compressing the liquid propellant.
再生式液体发射药火炮在内弹道循环中，膛内除弹丸运动外，还存在活塞压缩液体燃料的运动。
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28. 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。
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29. This paper studies the problem of tradeoff optimization between damage of reusable liquid propellant rocket engine's turbine blade and control input sequences during the start-up process.
针对可重复使用液体火箭发动机起动过程，研究了系统控制输入序列的变化对以涡轮叶片为代表的关键部件累积损伤的影响。
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30. This paper studies the problem of tradeoff optimization between damage of reusable liquid propellant rocket engine's turbine blade and control input sequences during the start-up process.
针对可重复使用液体火箭发动机起动过程，研究了系统控制输入序列的变化对以涡轮叶片为代表的关键部件累积损伤的影响。
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liquid propellant
