发动机喷管的英文

• engine exit
• engine jet pipepiston
• motor exit
• motor nozzle
• powerplant nozzle

• "发动机"英文翻译    engine; motor
• "发动机喷管喉道" 英文翻译 :    motor throat
• "火箭发动机喷管" 英文翻译 :    rocket nozzle; rocket tube
• "远地点发动机喷管" 英文翻译 :    apogee motor nozzle
• "电成型火箭发动机喷管" 英文翻译 :    electroformed rocket nozzle
• "发动机喷管喉道直径" 英文翻译 :    motor throat diameter
• "固体火箭发动机喷管" 英文翻译 :    solid nozzle
• "经绕式火前发动机喷管" 英文翻译 :    filament-wound rocket nozzle
• "实际的火箭发动机喷管" 英文翻译 :    actual-rocket nozzle
• "涡轮喷气发动机喷管" 英文翻译 :    turbojet nozzle
• "自冷式火箭发动机喷管" 英文翻译 :    self-cooled rocket nozzle
• "发动机喷流" 英文翻译 :    engine blast
• "发动机喷咀圈" 英文翻译 :    engine burner ring
• "发动机喷口盖" 英文翻译 :    motor end closure
• "发动机喷水箱" 英文翻译 :    water-injection storage container
• "发动机喷洗器" 英文翻译 :    engine cleaner
• "发动机喷油嘴" 英文翻译 :    injectors for engines
• "主发动机喷嘴" 英文翻译 :    nozzle of the main engine
• "发动机喷口面积" 英文翻译 :    engine exit area
• "火箭发动机喷流" 英文翻译 :    rocket flow; rocket jet
• "火箭发动机喷嘴" 英文翻译 :    rocket motor injector
• "升力发动机喷流" 英文翻译 :    lifting system efflux
• "升力发动机喷气流" 英文翻译 :    lift-jet exhaust
• "多喷管发动机" 英文翻译 :    multinozzle engine
• "双喷管发动机" 英文翻译 :    double-nozzled engine

• Through the analysis of the configuration of scramjet nozzle flow field , some design methods of scramjet nozzle and the characteristics of its performance variation were found
  通过对流场结构和喷管性能的分析,得出了一些超燃冲压发动机喷管设计方法和喷管性能变化的规律。
• Variation tendency of nozzle gap and contact stress was obtained in terms of multi - time computational results , and some modification suggestions , which are available for designers of solid rocket motor nozzle , were presented by the tendency
  综合多个时刻的计算结果得到发动机工作过程中喷管结构缝隙和接触应力的变化趋势，并据此对设计缝隙提出了修改意见，结果可为发动机喷管设计提供参考。
• In this thesis , based on pershing ii surface to surface missile , a new kind of ballistic missile was designed with an additional rocket engine , which can be ignited twice . firstly , aerodynamic computational models of missile body and warhead which reentry with supersonic are built according to the task requirements ; secondly , the propulsion system model of missile is built whose first two stages are solid rocket engines and the third stage is liquid - solid combined rocket engine . the nozzle and the shape of the engine are designed to meet the needs of the populsion project ; thirdly , the trajectory model of the mass point is built and a wavy trajectory is designed & optimized ; finally , the ability of a missile ' s breaking through defence is analyzed
  以美国潘兴导弹为原型，增加可两次点火的末级发动机，改装成具有跳跃能力的地地弹道导弹；首先，根据任务需求，建立了导弹的气动模型，并建立了弹头再入时高超声速气动模型；其次，建立了导弹推进系统模型，前两级采用了固体火箭发动机，第三级采用了固?液组合火箭发动机，并在总体方案要求下，对发动机喷管和外形进行了设计；第三部分，建立了导弹质点弹道模型，设计了一条跳跃式弹道，并对跳跃式弹道进行了优化设计；最后，对导弹进行了突防能力分析，从分析的结果可以看出，跳跃式弹道的突防能力比常规的抛物线弹道要强。
• Abstract : this paper briefly presents th e application of advanced brazing techniques for a larye number of assemblies of space vehicles , such as thrust chamber and turbine rotor of launch rock et engine , titanium tube of satellite , attitude control engine injector and wave guide component of satell ite , reflector , tube and honeycomb panel of manned spacecraft , main engine nozzl e and preburner of space shuttle as well as the pipeline systems of space statio n
  文摘:简略地介绍了先进钎焊技术在航天器部件，例如运载火箭发动机的推力室和涡轮转子、人造卫星的钛导管、姿控发动机喷注器和波导器件、载人飞船的反射器、导管和蜂窝壁板、航天飞机的主发动机喷管和预燃室以及空间站的管路系统等的广泛应用情况。