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   guidance 在 武器工业与军事技术 分类中 的翻译结果: 查询用时:0.011秒
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guidance
相关语句
  制导
    Study and Simulation of Control and Guidance system of Spinning Maneuver Warhead with Variable-Centroid
    旋转弹头变质心机动控制、制导系统的研究和仿真
短句来源
    Study on Missle-borne MMW PD Radar Guidance Information Processing
    弹载毫米波脉冲多普勒雷达制导信息处理研究
短句来源
    Research on Signal Processing Methods of Doppler Guidance Radar in MMW
    毫米波多卜勒制导雷达信号处理方法研究
短句来源
    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
短句来源
    Study on Photoelectric Detection Technique and Information Identification Technique for Countermeasuring Tunable Laser Guidance Weapon
    对可调谐激光制导武器的光电探测与信息识别技术研究
短句来源
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  导引
    Research on the Target Motion Analysis with Bearings-only and Intelligent Guidance Laws of Torpedo
    纯方位目标运动分析与鱼雷智能导引律研究
短句来源
    Guidance Law to High Altitude Interception
    高空拦截的导引规律
短句来源
    Application of Singular-Perturbation Method to Develop Missile Guidance Laws
    奇异扰动法在计算导弹导引规律中的应用
短句来源
    THE OPTIMIZATION OF ALL-DIRECTION ATTACK PROPORTIONAL GUIDANCE LAW AND THE STUDY OF ATTACK CHARACTERISTICS
    全向攻击比例导引律的优化及其攻击特性研究
短句来源
    DESIGNING OF A NONLINEAR OPTIMAL TERMINAL GUIDANCE LAW FOR SPACE INTERCEPTION
    空间拦截非线性最优末端导引规律研究
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  导航
    Design of a Navigation Filter for Combined Guidance Missiles
    一种复合制导导弹的导航滤波器设计
短句来源
    Research on the Application of GPS Navigation on the Guidance System
    GPS导航在制导中的应用研究
短句来源
    Application of CO_2 Laser Coherent Imaging Radar in the Navigation of the Cruising Missile and the terminal Guidance of Tactics Ballistic Missile
    CO_2激光相干成像雷达在巡航导弹导航及战术弹道导弹末制导中的应用
短句来源
    Hardware-in-the-Loop Simulation for Combined Guidance with SINS/GPS and Homing Head
    SINS/GPS组合导航和末端寻的复合制导半实物仿真
短句来源
    INS (Inertial Navigation System) /GPS/TERCOM (Terrain Contour Matching) /SMNS (Scene Matching Navigation System) integrated guidance technology for continent-based cruise missile is discussed in this paper.
    对陆基巡航导弹四组合制导技术,以一条典型轨迹进行了全航线仿真研究,包括初始对准段以及INS/GPS组合段、INS/TERCOM(地形轮廓匹配)组合段、INS/GPS/TERCOM组合段和INS/SMNS(景像匹配导航系统)组合段等共24个航段的研究。
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  “guidance”译为未确定词的双语例句
    ANALYTICAL MODEL OF FLUCTUATION ERROR OF HOMING GUIDANCE SYSTEM
    寻的制导系统起伏误差解析模型
短句来源
    Infrared/Millimeter Wave Dual Mode Guidance Technology
    红外/毫米波双模制导技术简介
短句来源
    ANALYSIS OF RETICLE FOR IR GUIDANCE MISSILE HONGYING5
    红缨5号调制盘分析
短句来源
    Development and Analysis of Accurate Guidance Techniques of Tactics Missiles
    战术导弹精确制导技术发展分析
短句来源
    Study of the Data Fusion Model for Multimode Homing Guidance Based on Fuzzy Reasoning
    基于模糊推理的多模导引头数据融合模型研究
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  guidance
Frames and Coorbit Theory on Homogeneous Spaces with a Special Guidance on the Sphere
      
This work may provide theoretical guidance for choosing solvents for these kinds of reactions and also may serve as basis for further industrialization.
      
Based on the actual local data in a 300 MW unit, the operation optimization value in typical load ranges is found out by data mining to provide better adjustment guidance in industry process.
      
The SSCP profiles could identify the difference in microbial community structures in wastewater treatment processes, monitor some of the functional microbes in these processes, and consequently provide useful guidance for improving their efficiency.
      
Our results indicate that m-calpain-mediated GAP-43 proteolysis regulated by PKC and calmodulin is of physiological relevance, particularly in axonal growth cone guidance.
      
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This paper describes guidance problems of the high altitude interception with emphasis on the most effective use of the maneuverability of the interceptors.The method of treatment is based on the so-called predicfive miss distance conception to establish equations of the predictive miss distance, and to invert the guidance problem of the interception into the control problem of the final point miss distance. Application of the principle of the minimum to this simplified equivalent problem gives straightforward...

This paper describes guidance problems of the high altitude interception with emphasis on the most effective use of the maneuverability of the interceptors.The method of treatment is based on the so-called predicfive miss distance conception to establish equations of the predictive miss distance, and to invert the guidance problem of the interception into the control problem of the final point miss distance. Application of the principle of the minimum to this simplified equivalent problem gives straightforward the analytical formula of the guidance law. The advantage of this method is clear and simple for the mathematical treatment.This paper discusses two guidance laws for minimum, effort interception and minimum time interception, Moreover the determination of the interception time tp is also presented. The result obtained can be applied to the radio command guidance, and with some modification, could be applied to the terminal homing guidance too.

本文讨论高空拦截的导引问题。出发点是要使拦截器的有限机动能力得到最有效利用,以保证所要求的拦截精度。我们解决问题的方法是利用予计脱靶量的概念,建立予计脱靶方程,把拦截导引问题转述为终点脱靶量控制问题。应用极小值原理于这个简化的等效问题。直接得出导引规律的解析表达式。这样做的好处是概念明确、数学处理简单。本文讨论了省力、快速两种导引规律在主动段拦截和被动段拦截情况下的导引公式。对文献中很少涉及的拦截时刻的确定进行了讨论,给出在特定条件下导引规律的实时计算公式。所得结果可用于无线电指令制导。稍加变换也可用于自动瞄准末制导。本文最后基于予计脱靶方程对导引规律特性进行了分析。其结果与数字计算结果一致。

This paper is continuous part of previously published paper[1]. Some aspects about guidance for genuine MIRV is mainly discussed. They are the guiding scheme for space maneuvering vehicle, the roll control program of attitude for the body, the design of maneuvering penetrating trajectory in longitudinal plane and the mechanization of perturbed guidance equation.

本文是前已发表的文章[1]的续篇。主要讨论有关全导式分导制导的若干问题。它们是。空间机动飞行器的导引法,弹体的滚动姿态控制方案,纵平面内机动突防弹道的设计以及摄动制导方程的编排。

This paper presented the concept of the imaging“track of the descent point” of the heads,and on this base demonstrated the chosen diretion of the guidance parameters of the single head. Secondary part of the paper discussed“the track of the descent point”of the respective heads during the multiple indepedently targetable guidance and the chosen direction of guidance parameters of the respective heads.Results of demonstration shown:for the fundamental guidance equation can be used the...

This paper presented the concept of the imaging“track of the descent point” of the heads,and on this base demonstrated the chosen diretion of the guidance parameters of the single head. Secondary part of the paper discussed“the track of the descent point”of the respective heads during the multiple indepedently targetable guidance and the chosen direction of guidance parameters of the respective heads.Results of demonstration shown:for the fundamental guidance equation can be used the unified mode of the disturbing guidance in relation to the single head,rocket vehicles and the multiple independently targetable reentry vehicles,not be necessary for develop various modes. In the final part of the paper is simply discussed the concept of“the descent point”control and the fundamental guidance mode at a more general case. This paper only introduced the conceptual discussion not concerning the realization,simplification and error analysis for the concrete modes.

本文提出了虚拟的弹头“落点运动轨迹”的概念,并在此基础上论证了单弹头导弹制导参数所应选定的方向。文章的第二部分讨论了多头分导时各子弹头的“落点运动轨迹”以及分导各子弹头所应选定制导参数的方向。论证结果表明:对基本制导方程来说,单弹头、运载火箭以及多弹头分导的摄动制导可以在同一个模型之下统一起来,而不必各自拟定不同的方案。文章最后部份简要地讨论了在更一般的情况之下“落点轨迹”控制的概念及基本导引模型。本文仅作概念性讨论而不涉及具体方案的实现、简化、误差分析等等。

 
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