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missile
相关语句
  导弹
    Random Simulation of Sequential Probability Ratio Test for Spread of Impact Point of Missile
    导弹落点散布的序贯概率比(SPR)检验的随机模拟
短句来源
    THE THERMORHEOLOGICAL MECHANISM AND FORMING PROCESS ANALYSIS FOR A CERTAIN OF MISSILE BRACKET
    某导弹弹托热流变机制及成形过程分析(英文)
短句来源
    THE SEQUENTIAL METHOD CHECKING MISSILE ACCURACY UNDER THE GENERALIZED CHI-SQUARED DISTRIBUTION
    广义 x~2分布下检验导弹精度的序贯法
短句来源
    The Estimation of Exterior Ballistic Measuring System Error for Missile Flight Test
    导弹飞行试验外测系统误差的估计
短句来源
    THE STATISTICAL LINEARIZATION ADJOINT METHOD APPLIED TO STATISTICAL ANALYSIS OF MISSILE SYSTEM PERFORMANCE
    用于导弹系统性能统计分析的统计线性化伴随法
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  “missile”译为未确定词的双语例句
    Model of Annual Investment Intension for Ground-to-Air Missile System Development
    地空导弹武器系统研制阶段年度投资强度模型
短句来源
    Approximate Calculation of the Return Missile Orbit
    再入弹道的近似计算
短句来源
    Multi Targets Decision on Choosing Launching Position for Ground Based Long Range Cruise Missile
    陆基远程巡航导弹发射阵地选址多目标决策
短句来源
    Research in the evaluating methods of the blind area radius of missile bullets.
    子母弹抛散盲区半径评定方法研究
短句来源
    A Control Algorithm for Designing Anti-Ballistic Missile Terminal Guidance Law
    一类不确定非线性系统变结构自适应鲁棒控制
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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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In this paper two kinds of multiple independently targeted guidance equation for Multiple Reentry Vehicle(MRV) and Multiple Independently Targeted Reentry Vehicle(MIRV) are developed.The contents of the paper include three parts. The first part is devoted to the discussion of the dissemination rule of impact points of the daughtermissile around mother-missile, the relation between the impact point of the daughter-missile and the trajectory parameters at ihdependently targeted point, the preeission...

In this paper two kinds of multiple independently targeted guidance equation for Multiple Reentry Vehicle(MRV) and Multiple Independently Targeted Reentry Vehicle(MIRV) are developed.The contents of the paper include three parts. The first part is devoted to the discussion of the dissemination rule of impact points of the daughtermissile around mother-missile, the relation between the impact point of the daughter-missile and the trajectory parameters at ihdependently targeted point, the preeission of the dissemination equation and realizability using onboard digital computer for MRV. The second part contains the optimal mathematical model of exoatmospheric flight, the quantitative results about initial point of guidance for a few kinds of special trajectory, selection of optimal thrust direction the quasi—optimal ε—and ε~(?)—guidance scheme, and many numerical resutts about MIRV. Lastly the influence of the rotating earth on guidunce is considered and some guidance schemes are presented. The dission about Multiple Independeutly Targeted Maneuvering Reentry Vehicle and theirs perturbed guidance realization were made in references [3] and [4].

本文论述了散弹式和分放式两种类型的多弹头分导的制导方程。全文分为三部分。第一部分讨论了散弹式子弹落点围绕母弹落点的散布规律,子弹落点同分导点的弹道参数的关系,散布方程的精确度和利用弹上数字计算机的现实可能性。第二部分是分放式,包括大气层外分导最佳化的数学模型,一类特殊弹道分导起点的定量结果,最佳推力方向的选择,准最佳ε—和ε~*—制导方案及若干数值结果。最后考虑了地球旋转对制导的影响,同时提出一些制导法。关于多弹头再入机动飞行器及摄动制导的实现问题曾在[3]和[4]中作了研究。

This paper describes the effect of gravity anomaly on impact accuracy for inertially-guided inter continental ballistitic missiles.The transition matrix analytic solution of perturbation equations which was widely used in inertial guidance engineering are derived. The maximum error due to omitting mathematical model detail, is less than 0.1%.Based upon the analytic solution of transition matrix approximate solutions of impact position error due to gravity anomaly are obtained. They are derived in a closed...

This paper describes the effect of gravity anomaly on impact accuracy for inertially-guided inter continental ballistitic missiles.The transition matrix analytic solution of perturbation equations which was widely used in inertial guidance engineering are derived. The maximum error due to omitting mathematical model detail, is less than 0.1%.Based upon the analytic solution of transition matrix approximate solutions of impact position error due to gravity anomaly are obtained. They are derived in a closed form of simple function expressing the relations between the impact accuracy, the gravity anomaly, the flight time of missiles and the launch condition.Using these relations, the impact position error in any launch condition can be calculated without to integrate differential equations. The numerical results calculated for 18 launch conditions shown excellent agreement with the machine results by direct integration of perturbation equations. In all cases, the maximum error due to the approximate so, is less than 2~3 meters.

本文讨论引力异常对惯性制导洲际导弹命中精度的影响。本文导出了惯性制导工程中广泛应用的摄动方程转移矩阵的解析解。忽略数学模型的细节所招致的最大误差小于0.1%。在此基础上得到引力异常造成落点偏差的近似解。这些解以简单函数的形式表达了命中精度、引力异常、导弹飞行时间和发射条件之间的关系。利用这些关系式,可以计算任意发射条件下的落点偏差而无需解微分方程组。对于18个不同发射条件的计算结果表明,近似解与直接积分摄动方程所得的计算机解非常一致。在所有的情况下,近似解的最大误差均小于2~3米。

The electromagnetic radiation of the horn antenna with metal flat flange in H plane has been calculated according to the diffraetion theory of vector field, and its approximate solution obtained. The result of our experiments coincides well with the theoretical calculation. By using this aerial in producing millimeterwave radar on some missile, the directional diagram in E plane has been broadened more than 50 percent.

本文从矢量場的繞射理論出发,計算了带有金属平面法兰的H面扇形喇叭天綫的电磁場輻射問題,得到它的近似解。理論計算与实驗結果符合的較好。在研制某气行体上的毫米波段雷达时采用了这种天綫,从而把E面方向图展寬了50%以上。

 
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