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missile
相关语句
  导弹
    INDUCED ROLLING MOMENT ON WINGS OF A MISSILE WITH TILT-WINGS IN "X-X" CONFIGURATION AT SUPERSONIC SPEEDS
    超音速旋转弹翼式“X-X”型导弹弹翼部分的诱导滚转力矩
短句来源
    DECOUPLING OF A KIND OF MISSILE CONTROL SYSTEM MODES
    一类导弹控制系统的模态解耦
短句来源
    ANALOG SIMULATION SYSTEM FOR THE OPERATION AND TRAINING OF STRATEGIC MISSILE LIQUID PROPELLANT ROCKET ENGINES
    战略导弹液体火箭发动机操作训练仿真模拟系统
短句来源
    DESIGN AND ANALYSIS OF AN OPTIMAL GUIDANCE LAW FOR BTT-90 MISSILE
    BTT-90导弹的一种最优导引规律的设计与分析
短句来源
    APPLICATION OF SENSITIVITY AND ROBUST STABILITY THEORY ON THE DECISION OF MISSILE LAUNCHING
    灵敏度及鲁棒稳定性理论在导弹发射决策中的应用
短句来源
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    Performance monitoring and diagnosis system for missile turbojet engine
    用涡喷发动机性能监视与诊断系统软件研制
短句来源
    A New Kind of Missile Control Computer Based on DSP
    基于DSP的新型载控制计算机
短句来源
    Simulation and analysis of the nonlinear clearance characteristics between the missile and launcher
    -架间隙的非线性模拟与特性分析
短句来源
    Starting and acceleration control law design for a missile turbojet engine
    某型用涡喷发动机启动加速控制规律设计
短句来源
    Analysis on Methods of Missile Turbojet Engine Condition Monitoring
    用涡喷发动机的状态监控方法分析
短句来源
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  “missile”译为未确定词的双语例句
    THE MIDCOURSE GUIDANCE AND CONTROL OF THE BALLISTIC MISSILE
    弹道式导弹的中段制导与控制
短句来源
    The following flight test results meet the missile requirement: attitude accuracy 1.9′(1σ),heading accuracy 4.5′(1σ),alignment time <40 s.
    试飞结果表明,所设计方案的姿态对准精度为1.9′(1σ),航向对准精度为3.4′(1σ),整个传递对准过程可在40秒之内完成,满足了预定的指标要求。
短句来源
    Application of Nonlinear Predictive Control in Cruise Missile Terrain Following
    非线性预测控制在巡航导弹地形跟踪中的应用
短句来源
    Finite Element Structure Vibration Characteristic Analysis of a Solid Missile in Transportation Environment
    运输环境中某战术导弹结构振动特性分析
短句来源
    COMPREHENSIVE RELIABILITY EVALUATING OF MISSILE DATA RECORDING SYSTEMS
    某飞行器数据记录设备的可靠性综合评估
短句来源
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  missile
On the development of future missile complexes for strategic nuclear forces
      
Possibilities of defense from a missile attacking from the back hemisphere by a vertical maneuver
      
The possibilities to defend an aircraft attacked from the back hemisphere by an air-air missile are investigated.
      
A model problem of determining an optimal vertical maneuver of the aircraft evading a missile that moves in the exponential atmosphere according to a given law of approach subject to aerodynamic drag forces and the Earth's gravitation is studied.
      
With a delay caused by the fact that the missile-flight time is finite, these distributions contain passive zones (i.e., time intervals where shooting makes no sense).
      
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Reentry plasma sheath surrounding high-speed vehicles greatly destroys the electromagnetic wave radiating by antenna. From calculating propagation parameters of high-temperature ionized air, this paper gives power transmission properties of ballistic intercontinental missile during reentry, and discusses the problem about selecting of reentry communication bands and so forth.

高速飞行器周围的“再入等离子鞘”对天线所辐射的电磁波产生严重的干扰。本文从计算高温电离空气的传播参数出发,给出了弹道式洲际导弹再入时等离子鞘的功率传输特性,并讨论了再入通讯频段选择等问题。

A new type of inertial navigation system combining customary platform type with strap-down one is put forward. In this system the azimuth rate platform without azimuth stabilized loop, coordinate-resolver and azimuth syn chronzer is adopted. The azimuth angles of platform and vehicle will be obtained by an integrator from azimuth rate signals measured by an azimuth gyroscope supported on a horizontal gimbal. This type of inertial navigation system is suitable for vehicles without large-pitching maneuver, such...

A new type of inertial navigation system combining customary platform type with strap-down one is put forward. In this system the azimuth rate platform without azimuth stabilized loop, coordinate-resolver and azimuth syn chronzer is adopted. The azimuth angles of platform and vehicle will be obtained by an integrator from azimuth rate signals measured by an azimuth gyroscope supported on a horizontal gimbal. This type of inertial navigation system is suitable for vehicles without large-pitching maneuver, such as transports, aerodynamic and ballistic missiles.Operational principles of the azimuth rate platform, mechanization equations, distinguishing features of initial alignment, and calibration and compensation for drifts of gyroscopes are discussed in this paper. Error propagation characteristics caused by various error sources for navigation positioning, velocity and attitude are simulated on a digital computer. Simplicity in platform structure, small volume and weight, high reliability, possibility of calibration and compensation for drifts of the azimuth gyroscope are the distinctive advantages of this inertial navigation system.Moreover, by using a specific optical system referring to given azimuth angles of land marks and geographical latitudes, it is possible to accomplish not only fast alignment, but also calibration and compensation of horizontal gyroscope.

本文提出一种把平台式和捷联式惯导系统结合在一起的新的惯性导航系统。在该系统中使用的速率方位平台没有方位稳定回路、方位坐标分解器及同步器。平台和运载器的方位角是根据由水平环架支承的方位速率陀螺讯号借助积分运算得到的。这种惯导系统适用于运输机、飞航式及弹道式导弹等不作大角度俯仰机动的运载器。文中叙述了方位速率平台的工作原理、力学编排方程、初始对准的特点以及陀螺漂移的标定和补偿;同时对各主要误差源所引起的姿态、速度和导航定位误差的传播特性进行了模拟计算。在结论中指出:平台的结构简单、体积小、重量轻、可靠性好、可对方位陀螺的漂移进行标定和补偿是其独特优点。另外,如果利用专门的光学系统,配合已知地标的方位角和纬度,不仅能够实现快速对准,而且还可进行水平陀螺的标定和补偿。

Modal test and parameter identification of a wind tunnel flutter model,similar to a wing with external missiles,are presented in this paper.The emphasis is laid on the way of obtaining high reliability and accuracy of the results.By using our own developed identifiction program,which is based on complex mode theory,the first nine order modal parameters are identified with the help of digital computers.Four data ' examining approaches are applied to guarantee the reliability and accuracy of test data and...

Modal test and parameter identification of a wind tunnel flutter model,similar to a wing with external missiles,are presented in this paper.The emphasis is laid on the way of obtaining high reliability and accuracy of the results.By using our own developed identifiction program,which is based on complex mode theory,the first nine order modal parameters are identified with the help of digital computers.Four data ' examining approaches are applied to guarantee the reliability and accuracy of test data and identified results.

本文介绍了带外挂风洞颤振模型模态试验与参数识别方法。重点放在如何提高结果的可靠性和精度上。利用我们研制的识别程序,在通用计算机上识别了前九阶模态的全部模态参数。采用了四种数据检验手段以保证试验数据和识别结果的可靠性与精度。

 
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