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missile
相关语句
  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
短句来源
     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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     Mixed H_2 /H_∞ Control of A Missile Electromechanical Actuator
     用电动舵机的混合H_2/H_∞控制器设计
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     The autopilot is the main control equipment of the C801 missile.
     C801导的自动驾驶仪是该上的主要控制设备。
短句来源
     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
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     Design of simulating and testing system for an unnamed training missile based on WIN32
     基于WIN32机载训练模拟测试系统的设计
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     This missile defense system is composed of warning system (warning satellite, improved warning radar and ground based radar),GBI and BM/C 3I system.
     该防御系统由预警系统 (预警卫星、改进的预警雷达和地基雷达 )、地基拦截系统 (GBI)和作战管理与指挥控制通信信息系统 (BM/C3I)等三大部分组成。
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  “missile”译为未确定词的双语例句
     The Mechanism and Effect on the Changes of Heat Shock Protein70, p38 Mitogen-Activated Protein Kinase in Missile Craniocerebral Injuries under High Temperature and High Humidity Environment
     高温高湿环境下颅脑火器伤后HSP70、p38 MAPK变化及其作用机理
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
     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
短句来源
     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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  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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Supersonic speed aircraft and guided aircraft missiles are subjected to rapid aerodynamic heating and rapid loading during their flight. For taking full advantage of the strength of structural materials in design, it is necessary to study the mechanical characteristics of metallic structural materials under rapid loading and heating. This paper describes a short-time high-temperature tensile testing machine, which is capable of constant-rate loading up to 85 kg/sec and heating at a rate up to 80℃/sec,...

Supersonic speed aircraft and guided aircraft missiles are subjected to rapid aerodynamic heating and rapid loading during their flight. For taking full advantage of the strength of structural materials in design, it is necessary to study the mechanical characteristics of metallic structural materials under rapid loading and heating. This paper describes a short-time high-temperature tensile testing machine, which is capable of constant-rate loading up to 85 kg/sec and heating at a rate up to 80℃/sec, the temperature gradient within the gage length for a distance of 50 mm being less than 5℃. All the heating, temperature-controlling and stress-strain measuring processes are done automatically. Experiments such as rapid tension under high temperature, rapid heating under constant loading and short-time creep can be carried out on this tester. Specimens of low carbon steel, R1T and 12F2A have been tested on it. Diagrams and tables have been included here and results from these tests have been preliminarily discussed.

高速飞机及飞航导弹在飞行过程中受到气动力的快速加热和快速加载.为了最充分地利用结构材料强度进行合理设计,必须研究金属结构材料在快速加载、快速加热下的力学性能.本文叙述了一种短时高温拉伸试验设备;这设备能以小于85 kg/s的速率对试件进行恒速加载,以小于80℃/s的速率进行快速升温;试件50mm标距内温度梯度小于5℃;整个加热控温过程和应力应变测量记录过程均系自动进行.在此设备上可进行高温快速拉伸和短时蠕变等实验,并已进行了低碳钢,等材料的短时拉伸、短时蠕变、恒裁等加热率的实验.文内列有图表,并对结果进行了初步讨论.

This Paper is a Part (Chapter Ⅲ) of the reference[1], which was written by the author in 1977.Some computations of the Radar Cross-section of a certain pilotless aircraft, the locations of reflecters, and the effects of reflecters on the radar properties of the pilotless aircraft are presented in this paper. Besides, the effect of the centroid of RCS on the missdistance of the missile is discussed.

本文是文[1]的第三章。介绍了关于某型无人机的雷达截面积的若干计算结果、角反射器的配置及其对无人机的雷达特性的影响。还讨论了反射中心对导弹命中误差的影响。

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。

 
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