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   high specific impulse 在 航空航天科学与工程 分类中 的翻译结果: 查询用时:0.192秒
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high specific impulse
相关语句
  高比冲
    Research on the High Specific Impulse Bipropellant Liquid Apogee Engine
    高比冲双组元液体远地点火箭发动机研究
短句来源
    The scramjet has some advantages of high flow velocity, high specific impulse and wide operating range which become a viewpoint in the research field of power of Aeronautics and Astronautics.
    超燃冲压发动机以其高速、高比冲和工作范围宽广的特点,正逐渐成为当今航空航天动力领域的研究焦点。
短句来源
    Stationary plasma thruster (SPT) is a kind of advanced electric propulsion concept. Because of its high specific impulse, high efficiency, small bulk and low weight, it is being widely used in tasks such as pose control, orbit correct, position retain, and so on.
    稳态等离子发动机(SPT)是一种先进的电推进技术,具有高比冲、高效率、体积小、重量轻等特点,广泛应用于航天器姿态控制、轨道修正、位置保持等任务。
短句来源
    According to theoretical and experimental results achieved up to date, it is concluded that MPT is a kind of advanced thruster with high specific impulse, long lifetime, low thrust and thus especially fitting for space propulsion such as orbit transfer, attitude control, station keeping, docking and rendezvous, planetary.
    分析现有理论与实验研究结果后认为,MPT是一种高比冲、长寿命的小推力动力装置,特别适合用作空间动力,进行航天器的轨道转移、姿态控制、位置保持、对接交会和星际航行。
短句来源
    Arcjet is the highlight of investigation and application in world because of its high specific impulse, high ratio of thrust and power.
    电弧等离子体发动机 (Arcjet)因其高比冲、高推力 功率比等特点成为当前国际上电火箭研究和应用的热点。
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  “high specific impulse”译为未确定词的双语例句
    Electric Propulsion (EP) has many advantages of high specific impulse, long lifetime, high controlling precision. It can perform many kinds of space mission.
    电推进(EP)具有比冲高、寿命长、控制精度高等优点,可完成多种空间任务。
短句来源
    To develop a micro/mini- chemical propulsion system with a low thrust and a high specific impulse, this work seeks to elucidate the underlying characteristics unique to the flow and combustion process in each micro- component of the propulsion system and investigate its whole operation cycle of combustion and propulsion analytically and numerically.
    为了发展具有高分辨率推力和高比冲的微小型化学推进系统,本文采用理论分析和数值模拟的方法,对微推进系统中单个部件内的流动与燃烧过程以及整个系统的燃烧推进过程进行了研究。
短句来源
    Microwave Plasma Thruster (MPT) is a new type of electro-thermal thruster, which has widely applied prospect because of its high specific impulse, long lifetime, low plume contaminant and so on.
    微波等离子推力器(MPT)是一种新型的电热型推力器,它具有比冲高、寿命长、羽流污染小等优点,具有广阔的应用前景。
短句来源
    4. Presenting the performance evaluation methods of STP according to the law of energy conservation, radiation heat transfer principle and heat transfer theory, showing the result that STP has advantages of high specific impulse (5000-9000 m/s), wide thrust level (0.6-60 N) using hydrogen as the propellant, and drawing the change relations of performance parameters among concentration ratio, solar radiation flux density and mass flow rate.
    (4)针对所设计的STP方案类型,利用能量守恒原理、辐射换热原理和传热学理论给出了STP性能预示的工程算法和结果。 计算结果显示,以氢气为工质,STP具有比冲较高(5000~9000 m/s),推力范围宽(0.6~60 N)的特点。
短句来源
    PDRE has great potential to become one of important propulsive devices of spacecraft in 21~(st) century because PDRE has many desirable advantages, including high thermodynamics cycle efficiency, simple configuration and high specific impulse.
    由于脉冲爆震火箭发动机具有热循环效率高、结构简单、比冲大等优点,所以它将是21世纪一种极具潜力的航空航天飞行器动力装置。
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  high specific impulse
When little thrust with a high specific impulse is required, ions should be emitted.
      
The heat of formation of the binder should be as high as possible to achieve high specific impulse.
      
The coupling of high specific impulse and small size makes electric propulsion an ideal technology for small spacecraft.
      
The activities initiated at NASA GRC are in the second-year of a multi-year effort involved in development of this high specific impulse ion engine.
      
There is a potential need for high specific impulse propulsion for small spacecraft.
      
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A newly discoved nitramine——1, 3, 3, 5, 5, 7, 7-hexanitro-1, 5-diazocydic octane(here after HCO),showing a property similar to HMX, is discussed in this investigation. The oxygen content of HCO is higher than HMX, and no crystalloblastesis has been found while being heated up to its melting point at 250℃ The theoretical specific impulse for HCO monopropellant is 269.28 s., 4 s., higher than HMX. Smokeless propellants with HCO all show to give higher specific impulse (theoretical)...

A newly discoved nitramine——1, 3, 3, 5, 5, 7, 7-hexanitro-1, 5-diazocydic octane(here after HCO),showing a property similar to HMX, is discussed in this investigation. The oxygen content of HCO is higher than HMX, and no crystalloblastesis has been found while being heated up to its melting point at 250℃ The theoretical specific impulse for HCO monopropellant is 269.28 s., 4 s., higher than HMX. Smokeless propellants with HCO all show to give higher specific impulse (theoretical) than those with HMX. Many new features are shown besides the relatively higher theoretical specific impulse. HCO propellants show much lower pressure exponent (a decrease of 0.109 without catalyst, or of 0.148 with the addition of catalyst; HMX propellants show a decrease of 0.129 with catalyst). It is certain that a even lower pressure exponent can be expected when suitable catalysts are being used. As a new type of smokeless propellant therefore, it is worthy of further investigation.

本文研究一种与奥克托金(HMX)相类似的新型硝胺化合物——1,3,3,5,7,7-六硝基-1,5二氮杂环辛烷(简称HCO)。这种硝胺炸药比HMX含氧量高,熔点250℃,加热时,在250℃温度范围内无晶型转变。HCO单元推进剂标准理论比冲比HMX单元推进剂约高4s。以HCO取代HMX作为无烟推进剂的高能添加剂,其理论比冲都高于HMX无烟推进剂。这种推进剂的燃烧性质比HMX无烟推进剂有明显改善,压力指数比HMX无烟推进剂低得多。无催化剂时,压力指数下降了0.109;加催化剂时,压力指数下降了0.148。而HMX推进剂只下降0.129,改进催化剂,其压力指数有可能进一步下降,故这种推进剂是有发展前途,值得进一步研究的新型无烟推进剂。

In this paper it is described that the integrated solid propellant ramrocket engine is available for surface-air missilse due to its advanteges such as high specific impulse, light weight, full flight thrust provision, convenient u-se and maintenance, and low cost. It is also discussed that the missile performance can be greatly improved by means of increasing the available engine attack angle, accepting BTT technique adjusting the fuel flow and using oxidizer-lean propellant.

整体式固体火箭冲压发动机在面空导弹上应用具有比冲高、质量轻、可全程主动攻击、使用维护方便、成本低等优点.而进一步提高发动机可用攻角、采用BTT技术、调节主级燃料流量和采用高能贫氧推进剂还可大幅度地提高以这种发动机为动力的导弹性能.

In the present paper the achievement of aerospace technology in advanced countries is reviewed. The results of the R&D of main engines for heavy lift launch vehicles and space transportation systems have shown that hydrogen is the most prospective fuel in aerospace technology because of its high specific impulse and other special properties. This paper deals with the high pressure LO_2 / LH_2 rocket engines with stage combustion cycle. It is shown that they can be used not only for the central stage...

In the present paper the achievement of aerospace technology in advanced countries is reviewed. The results of the R&D of main engines for heavy lift launch vehicles and space transportation systems have shown that hydrogen is the most prospective fuel in aerospace technology because of its high specific impulse and other special properties. This paper deals with the high pressure LO_2 / LH_2 rocket engines with stage combustion cycle. It is shown that they can be used not only for the central stage of heavy lift launch vehicles, but also for the reusable orbiter of space transportation systems. In this paper the three-component(hydrogen, hydrocarbon and oxygen) rocket engine for heavy lift launch vehicles is discussed. Finally, a review of the investigation in the field of air breathing combined engines using liquid hydrogen is also presented. It shows that there will be a great possibility for application of this kind of engines in reusable transportation systems.

本文通过世界发展航天技术的先进国家在探索、研究大型运载火箭与天地往返运输系统动力装置方面所取得的成就说明液氢燃料(由于其具有高比冲等独特的优越性)在航空航天技术发展中越来越显示了无比的竞争力。论述了高压分级燃烧氢氧发动机是大型运载火箭芯级动力装置,也是天地往返系统轨道级重复使用动力装置的发展方向,同时指出氢、氧、烃双燃料三组元发动机是大型运载火箭动力装置的新发展方向。论述了以氢为燃料的吸气式组合发动机是发展天地往返运输系统空天飞机动力装置的可能趋势。

 
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