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火箭     
相关语句
  rocket
    Study on Dynamics of Long Range Multiple Launch Rocket System and Its Application
    远程多管火箭动力学及其应用研究
短句来源
    Laser radar test results on rocket and tube launched projectiles
    激光雷达对火箭发射导弹和发射管发射导弹的试验结果
短句来源
    Experimental Investigation of Rocket Exhaust Pulmes——Concurrent Discussion of the Problem about Corrdination of an Experiment with Electronic Digital Computer
    火箭燃气射流实验研究——兼论实验与电子数字计算机相配合
短句来源
    An Investigation of the Early Supersonic Regime of Rocket Gas Jets
    火箭燃气射流初始超音速流态研究
短句来源
    The Computation and Analysis of Concentration of ×× Rocket
    ××火箭密集度计算分析
短句来源
更多       
  rockets
    A MULTI-COEFFICIENT FITTING METHOD FOR HIGH-SPIN ROCKETS
    涡轮式野战火箭多系数符合方法
短句来源
    REDUCE DISPERSION OF UNGUIDED ROCKETS WITH ENERGY CONTROL
    利用能量控制减小非制导火箭的射弹散布
短句来源
    A New Way to Reduce Dispersion of Finstabilized Rockets—Spin Deceleration
    减小尾翼火箭散布的新途径—减速旋转
短句来源
    Engineering Drawings Management System on Rockets
    火箭导弹工程图管理系统
短句来源
    SIMULATED CALCULATION OF THE INTERIOR BALLISTICS SYNCHRONISM OF SOLID BOOSTING ROCKETS
    固体火箭助推器内弹道同步性仿真计算
短句来源
更多       
  a rocket
    Simulated Calculation and Analysis for a Rocket Mine-sweeping Arms System Open up Probability of the Thoroughfare
    火箭扫雷武器系统开辟通路概率模拟计算及其分析
短句来源
    This paper analyses a rocket assisted torpedo's aerial motion, water entry motion and underwater motion It establishes equations of motion for each phase and presents the ballistic characteristics of each section It thus provides a basis for the design and calculation of rocket assisted torpedoes
    对火箭助飞鱼雷的空中运动、入水运动和水下运动进行了分析 ,建立了各自的运动方程 ,指出了各弹道段上主要的弹道特性 ,为火箭助飞鱼雷的设计和弹道计算提供依据。
短句来源
    Used in the visualization of exhaust plumes of a rocket engine, multiple-frame interferograms of the shock wave development processes and of the near field structure can be obtained. It provides powerful experimental means for studying the fundamental characteristics of the whole flow field.
    它们可以应用于火箭发动机燃气射流中,由此可获得冲击波发展过程和近场结构的多幅干涉图,为理论上研究整个流场的基本特征,提供有力的实验依据。
短句来源
    According to the "solid particle" theory model, a theory model of the dynamic burining velocity of a rocket portfire in its igniting delay time cannulation is established, a theory model of the dynamic delay time is educed. The factors are analyzed, setting position and shape of a igniting delay time cannulation that affect its igniting delay time.
    根据“固体粒子”效应理论 ,建立了点火延期管动态燃速数学模型 ,导出了点火延期管动态延时时间计算模型 ,并分析了底排一火箭复合增程弹火箭空中点火延期管的安装位置及其形态对其延期时间的影响。
短句来源
  multiple-rocket
    GLOBAL-TRAJECTORY SIMULATION OF A MULTIPLE-ROCKET/LAUNCHER SYSTEM
    多管火箭/发射装置系统全弹道模拟技术研究
短句来源
    A 7-degree-of-freedom nonlineer,random,and time dependent model has been established for a multiple-rocket/launcher system.
    建立了多管火箭/发射装置系统7自由度的全弹道模拟多体动力学随机非线性时变系统模型。
短句来源

 

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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.
          
    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          
      a rocket
    Equations of motion of ball lightning in a rocket airstream
          
    Phenomena accompanying the injection of a dense plasma beam from the payload of a rocket into ionospheric plasma are analyzed.
          
    It has been indicated that a change in the total electron content is caused by the propagation of an acoustic gravity wave pulse, generated during a rocket flight along the horizontal trajectory leg, in the ionosphere.
          
    The proposed model was successfully used to analyze two emergency events: a failure of a steam turbine's cast diaphragm and a failure of a rocket engine's oxygen pump booster stage.
          
    Regenerative cooling is an advanced method which can ensure not only the proper running but also higher performance of a rocket engine.
          
    更多          


    In this paper, the random process theory is used to study the problem of the dispersion of rockets effected by the random wind in the exterior ballistics. When the mathematical model of the dispersion was obtained, we analysed some basic laws of the dispersion, represented the physical nature of these laws according to the spectral structure of the wind field and proved that the gust intensity σ_w and the scale of turbulence L are two important physical parameters upon which the dispersion depends.

    本文应用随机过程理论,研究了火箭外弹道学中随机风场作用下,火箭弹的散布问题。在导出描述散布的数学模型之后,分析了散布的若干基本规律,并根据风场的谱结构,阐明了这些规律的物理特性,证明了风场的阵性强度σ_w与扰动尺度L是决定散布的二个重要物理参量。

    The mechanism of sub-supersonic nonliner rotational speed of inclined cutwing-body-turbine complex is analysed on the basis of profile theory. A morepractical and reliable calculating method of its rotational speed is given, thosevalues are also compared with those from experiments. This discusion may beused as reference for the design, exterior ballistics calculation and wind tunnel rotational experiment of rocket projectile.

    从翼剖面理论分析着手对亚、超音速非线性平衡转速进行了机理探讨,对十字斜切翼-弹身-涡轮组合体给出了较实用而可靠的转速计算方法,并与实验值作了比较。本文可供火箭弹(丸)设计、外弹道计算以及风洞旋转试验参考。

    This paper studies the factors influencing zero-wind deviation from. the tra-jectories of Rocket-Assisted Anti-Tank Projectiles. How to determine the variousparameters is invistigated and some cantions problems are also provided. Thisdiscussion gives a better set of calculating formulas for the said anti-tank projectiles.

    本文分析了影响零风偏反坦克火箭增程弹散布的因素,研究了确定此种增程弹的各种参数的方法及注意的问题,为较好地设计上述增程弹提供了理论依据。

     
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