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火箭     
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  rocket
    Studies on Theory and Strategy of Intelligent Fault Diagnosis for Liquid-Propellant Rocket Engine
    液体火箭发动机智能故障诊断理论与策略研究
短句来源
    Investigation on Performance and Influence Factors of Rocket Ejector Mode of RBCC
    RBCC引射火箭模态性能与影响因素研究
短句来源
    Optimization Design for Cost of Solid Rocket Motors
    固体火箭发动机面向成本优化设计
短句来源
    Fuzzy Reliability Analysis for a Flanged Connection System of Rocket Motors
    火箭发动机法兰连接系统模糊可靠性分析
短句来源
    Research on Working Process of the 85% H_2O_2-PE Hybrid Rocket Motor
    85%H_2O_2-PE固液火箭发动机工作过程研究
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  propellant rocket
    THREE-DIMENSIONAL ANALYSIS OF"FLOW TURNING" INTHE COMBUSTION STABILITY THEORY FOR SOLID PROPELLANT ROCKET MOTORS
    固体火箭发动机燃烧稳定性理论中“Flow turning”的三维分析
短句来源
    The Development of Condition Monitoring and Failure Diagnostic Technique for Liquid Propellant Rocket Engines
    液体火箭发动机状态监控与故障诊断技术的发展
短句来源
    An Application Research of Integral Sol id Propellant Rocket Ramjets
    整体式固体火箭冲压发动机的应用性能探讨
短句来源
    A STUDY ON PERFORMANCE VARIATION OF SOLID PROPELLANT ROCKET ENGINES IN STORAGE
    固体推进剂火箭发动机贮存性能规律研究
短句来源
    REAL TIME ON-LINE FAULT DETECTION ALGORITHM FOR STARTING PROCESS OF LIQUID PROPELLANT ROCKET ENGINES
    液体火箭发动机启动过程实时在线故障检测算法
短句来源
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  rockets
    A nonlinear model on the simulation of pogo vibrations in liquid rockets
    液体火箭Pogo振动蓄压器非线性仿真研究
短句来源
    The problem of numerical prediction of rocket plumes exhausting into supersonic airflow is discussed. The Diagonalized Upwind Navier-Stokes(DUNS) code is applied to simulate the exhaust plume of two different solid rockets.
    采用The Diagonalized Upwind Navier-Stokes(DUNS)程序对两种火箭发动机的喷管-尾喷焰进行了一体化数值仿真。
短句来源
    Review on radiation characteristics and temperature measurement techniques for exhaust flames of solid rockets
    固体火箭羽焰的辐射特性及其温度测量技术述评
短句来源
    Thus,the trajectory of all kinds of rockets and space vehicles can be conveniently and accurately simulated by using TC generalprogram package.
    从而使得通用程序包TC可以方便而准确地对各种类型的火箭与空间飞行器的弹道进行仿真。
短句来源
    A solution algorithm based on coupled solution of the fully elliptic three dimensional steady state Navier Stokes equations was developed for the calculation of turbulent reacting flows occured in ducted rockets.
    用偶合算法求解三维定常椭圆型N-S方程组,计算了火箭冲压发动机内部的湍流反应流场。
短句来源
更多       
  rocket motors
    Optimization Design for Cost of Solid Rocket Motors
    固体火箭发动机面向成本优化设计
短句来源
    Fuzzy Reliability Analysis for a Flanged Connection System of Rocket Motors
    火箭发动机法兰连接系统模糊可靠性分析
短句来源
    THREE-DIMENSIONAL ANALYSIS OF"FLOW TURNING" INTHE COMBUSTION STABILITY THEORY FOR SOLID PROPELLANT ROCKET MOTORS
    固体火箭发动机燃烧稳定性理论中“Flow turning”的三维分析
短句来源
    Three-Dimensional Calculation Method for the Prediction of the Combustion Stability of Solid Rocket Motors
    固体火箭发动机燃烧稳定性预估的三维计算方法
短句来源
    AN INVESTIGATION ON DESIGN CRITERIA FOR THROAT INSERT STRUCTURE OF SOLID ROCKET MOTORS
    固体火箭发动机喷喉结构设计准则的研究
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  rocket
Microbiological Degradation of Asymmetric Dimethylhydrazine, a Toxic Rocket Fuel Ingredient
      
The possibility of microbiological cleaning of water and soil polluted with asymmetric dimethylhydrazine (ADMH), a highly toxic ingredient of rocket fuel (IRF), was studied.
      
Consideration was given to the controlled solid bodies such as aircraft, rocket, and so on moving in the aerodynamic medium.
      
Peculiarities of Estimating the Aircraft Performance Characteristics of the Rocket-and-Space Facilities under Conditions of Fuzz
      
The method is based on the results of measurements of the state parameters and geophysical conditions of the employment of the rocket-and-space facilities under conditions of uncertainty of the a priori data on measurement errors.
      
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  propellant rocket
Monte Carlo simulation algorithms are given which are intended for the calculation of the spectral emissivity of jets of combustion products of solid-propellant rocket motors (SRM).
      
The Outflow of a Two-Phase Gas-Liquid Mixture from the Mixing Head of a Gas Generator when Starting a Liquid-Propellant Rocket E
      
This paper deals with the problems of mathematical simulation of the start-up of a liquid-propellant rocket engine (LPRE), which are associated with two-phase flows in the mixing heads (MH) of combustors and gas generators.
      
The instability of the working process in the combustion chamber of a solid-propellant rocket engine
      
Heat transfer in the thrust chamber is of great importance in the design of liquid propellant rocket engines.
      
更多          
  rockets
Ions with a Mass Number of Two in Mass-Spectrometric Experiments aboard Rockets and Satellites
      
Results of the calculation of the structure of relaxation shock waves in gas suspensions of the solid fuel of rockets are given in [8].
      
The mass-energy and specific characteristics of the propulsive jet discharges of rockets were factorized.
      
Variations in the electron density in the midlatitude ionospheric D region during launches and flights of different-type rockets at various distances from the launching site have been experimentally studied using partial reflections.
      
Coning motion stability of wrap around fin rockets
      
更多          
  rocket motors
The operation of rocket motors is often accompanied by the development of powerful secondary vortices in the combustion chamber [1-3], The superposition of the secondary vortices on the main flow leads to the formation of a cellular flow structure.
      
Monte Carlo simulation algorithms are given which are intended for the calculation of the spectral emissivity of jets of combustion products of solid-propellant rocket motors (SRM).
      
For technological reasons many high-performance solid rocket motors are made from segmented propellant grains with non-uniform port geometry.
      
This research demonstrated that hybrid rockets offer a safe, reliable upper stage option that is a versatile, cost-effective alternative to solid rocket motors.
      
Comprehension of wall-injection flow in a channel in the presence of different geometric discontinuities is necessary as part of the general investigations concerning combustion instabilities of solid propellant rocket motors.
      
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