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missile
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  导弹
    Theory and Application Study on Underwater Trajectory Dynamic System Modeling of Submarine Launched Missile Carrier
    潜射导弹运载器水弹道动力系统建模及其应用研究
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    Integrated Design of Integral Rocket-Ramjet Missile
    整体式冲压发动机导弹总体一体化设计
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    Wavelet Application in Fault Diagnosis for Air Defense Missile
    小波理论在导弹故障诊断中的应用研究
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    Method and Application of Winged Missile Oriented Multidisciplinary Robust Design Optimization
    面向飞航导弹的多学科稳健优化设计方法及应用
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    The Research of BTT Missile Control System Based on Dynamic Inversion System and Neural Network Theory
    基于动态逆系统和神经网络理论的BTT导弹控制系统研究
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    DESIGN AND EXPERIMENTAL STUDY OF HIGH-SUBSONIC SPEED SUBMERGED AND SEMI-SUBMERGED INTAKE FOR MISSILE
    用高亚音速嵌入式、半嵌入式进气道设计与试验研究
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    The Reliabilty of the Guidance Information Transmission In the Remote Missile
    遥控制导误差信息传输的可靠性
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    A New Progress Applying Nonlinear Vortex Lattice Method to Tactical Missile at High Angles of Attack
    非线性涡格法应用于大攻角战术新进展
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    A Study of Control Circuit for Nomissile Battery Cavity Missile System
    无链供系统控制电路研究
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    Parameter Optimization for a Rotor System used in a Missile Engine
    用发动机转子支承系统参数优化
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  “missile”译为未确定词的双语例句
    Research on the Key Technologies of the Guidance System for Cruise Missile
    巡航导弹制导系统关键技术研究
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    The Study on the Control System of Aerodynamic Missile Based on Fractional Calculus
    基于分数阶微积分的飞航式导弹控制系统设计方法研究
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    OPTIMUM DESIGN FOR ANTIAIRCRAFT MISSILE WARHEADS
    对空近炸战斗部的最优设计
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    China's HQ-2B Surface-to-Air Guided Missile System
    中国的HQ-2B地空导弹武器系统
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    THE ENGINEERING DESIGN PROBLEM OF STRAPDOWN SYSTEM IN VERTICAL LAUNCH TACTICAL MISSILE
    垂直发射战术导弹中捷联系统的工程设计问题
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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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This article presents the significance of phsical simulation for studyinggeneral characteristic parameters of radio proximity fuze and analyses simulativeinitiating Conditions of the fuze in the process of missile-target encounter basedon the theory of simularity. Emphasis is put on the discussion of simulativeprogram to reduce the size of model target and the velocity, and on the analysis of the requirement for various simulated parts of fuze in simulation.

本文讨论了物理模拟在无线电引信总体参数研究中的意义并依据相似理论分析了弹目交会过程中引信启动规律的模拟原则。重点讨论了缩小目标模型尺寸、降低运动速度的模拟方案,分析了各种体制的无线电引信进行物理模拟时对各模拟环节的要求。

This paper briefly describes a self-alignment theory of inertial platform for ballistic missiles, and solves the avanishing of directional contol" problem occuring during alignment when gravity inertial coordinate is taken as the reference of alignment using platform-gyrocompass principle, and thence presents the omnidirectional self-alignment method of convertible directional control. On the basis of equation of misalignment angle derived for the omnidirectional self-alignment system, this paper gives...

This paper briefly describes a self-alignment theory of inertial platform for ballistic missiles, and solves the avanishing of directional contol" problem occuring during alignment when gravity inertial coordinate is taken as the reference of alignment using platform-gyrocompass principle, and thence presents the omnidirectional self-alignment method of convertible directional control. On the basis of equation of misalignment angle derived for the omnidirectional self-alignment system, this paper gives the alignment error analysis of the system, and the major error source effecting alignment accuracy of the system is presented. Finally, the effect of alignment error on the shooting accuracy of a missile is analyzed and the basic requirement of inertial sensor accuracy is presented.

本文概述了弹道式导弹惯性平台自对准原理,解决了利用平台罗经原理在以重力惯性坐标系为对准基准时出现的方位控制信号消隐现象,从而提出转换方位控制的全方位自对准方案。在推导全方位自对准系统失准角方程式基础上,对系统的对准误差进行了分析,从而找出影响系统对准精度的主要误差源。最后分析了对准误差对导弹射击精度的影响,并据此提出惯性器件精度的基本要求。

This paper studies how to determine the spin angular velocity of a spinning missile.First,When the equivalent deflection angle of control mechanism is step function,solves the complex state equation of a spinning missile.Next,analyses how the different spin angular velocity affects the motional steady-state magnitude and dynamic process of the spinning missile.According to the result,takes the adequate spin angular velocity of the spinning missile,so that the vehicle may have good motional...

This paper studies how to determine the spin angular velocity of a spinning missile.First,When the equivalent deflection angle of control mechanism is step function,solves the complex state equation of a spinning missile.Next,analyses how the different spin angular velocity affects the motional steady-state magnitude and dynamic process of the spinning missile.According to the result,takes the adequate spin angular velocity of the spinning missile,so that the vehicle may have good motional property.

本文首先对自旋导弹弹体运动的复数状态方程,在控制机构的等效偏转角为阶跃值的条件下求解。然后分析不同的自旋角速度对弹体运动的稳态性能和动态过程的影响。在此基础上,得出要使弹体具有良好的运动性能时,弹体的自旋角速度应选取的合理范围。

 
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