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miss distance
相关语句
  脱靶量
     DETECTION PROBABILITY ANALYSIS OF PROJECTILE MISS DISTANCE FOR MILLIMETER WAVE PHASED ARRAY RADAR
     毫米波相控阵雷达弹丸脱靶量检测概率分析
短句来源
     Estimating Method of Miss Distance Based on Fuse's Doppler Frequency Signal
     基于引信多普勒频率信号的脱靶量估算方法
短句来源
     Error Compensation Algorithm of Miss Distance Measurement Based on Narrow Pulse
     基于窄脉冲的脱靶量测量误差补偿算法
短句来源
     Measurement algorithm of scalar miss distance based on narrow pulse
     基于窄脉冲的标量脱靶量测量算法
短句来源
     Research on Measurement Method of Missile Miss Distance
     导弹脱靶量测量方法研究
短句来源
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  脱靶距离
     Miss distance is an important data in aircraft survivability evaluation and the main criterion to infrared decoy efficiency.
     脱靶距离是飞机生存力评估的重要数据,红外诱饵弹对红外制导导弹的干扰效果也可通过脱靶距离来衡量。
短句来源
     Miss distance of infrared guidance missile under infrared decoy influence
     红外诱饵弹对红外制导导弹脱靶距离影响
短句来源
     The influence of aircraft radar cross section (RCS) on miss distance are considered in calculating the probability of hit
     在计算击中概率时,考虑了飞机的雷达散射截面(RCS)对脱靶距离的影响。
短句来源
     Simulations indicate that the guidance system employing PI guidance law can achieve smaller miss distance for maneuverable targets, especially for highly maneuverable targets, than that with PN guidance law.
     仿真结果表明: 它比比例导引律能使制导系统在攻击机动目标, 特别是大机动目标时, 达到更小的脱靶距离
短句来源
     The result shows that the evaluation model of lethal effect for air to air missiles comprehensively considering characteristics,miss distance and vulnerability of target aircrafts,accords with reality.
     通过分析得出,综合考虑导弹特性、脱靶距离和目标机易损性的空空导弹杀伤效果评估模型更加附合实际。
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  “miss distance”译为未确定词的双语例句
     MATRIXx adjoint system for miss distance analysis
     导弹制导精度MATRIXx伴随分析系统
短句来源
     Test error for the miss distance is analyzed and analysis result is given.
     分析了脱靶量的测量误差,并给出了分析结果;
短句来源
     The miss distance caused by guidance method error and the effects of perturbation are compensated in this initial guidance law.
     该初制导方法能补偿制导方法误差和轨道摄动对拦截脱靶量的影响。
短句来源
     The results of the calculations show that the miss distance for various situations remains at least 1/2 d2.
     计算结果表明,对不同态势的来船,照新方案避碰的结果,都可以保持1/2d_2的最小距离.
短句来源
     In comparison with the results obtained by direct integration oftrajectory equations the method described in this paper gives a relationerror on miss distance of less than 2% and an absolute error of about30 meters.
     就本文提供的方法与直接积分弹道方程的计算结果而言,脱靶量的相对误差小于2%,绝对误差约为30米。
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  miss distance
It is shown that the interceptor can guarantee an arbitrarily small miss distance without exceeding the control constraints if it has sufficient maneuverability and if the penalty coefficients are chosen properly.
      
Having a resource of impulse control, the pursuer tries to minimize the miss distance.
      
The implementation scheme and the effect on miss distance due to errors in guidance are discussed.
      
Necessary conditions and sufficient conditions are employed to deduce optimal strategies for a simple differential game with state equationd2x/dt2=au+v,a = Const, |u|≤1, |v|≤1, fixed transfer time, and terminal miss distance as payoff.
      
Initial orbital parameter errors are used to examine the miss distance between a spacecraft and an ensemble of tracked objects by a Monte Carlo-type analysis.
      
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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...

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。

The problem of optimal intercept guidance laws for missiles have been studied by a lot of authors at home and abroad. But the mathematical models for missiles were assumed too simple, i. e. either as an ideal particle or as a first order delay link.As a primary contribution this paper has made researches on the optimal intercept guidance laws based on a mathematical model with second order charac- teristics. By taking minimum control energy consumption as the performance index, the optimal intercept guidance...

The problem of optimal intercept guidance laws for missiles have been studied by a lot of authors at home and abroad. But the mathematical models for missiles were assumed too simple, i. e. either as an ideal particle or as a first order delay link.As a primary contribution this paper has made researches on the optimal intercept guidance laws based on a mathematical model with second order charac- teristics. By taking minimum control energy consumption as the performance index, the optimal intercept guidance laws have been derived from the minimum principle in the following two cases of terminal state:1. The terminal miss-distance is zero;2. The intercepting curved surface of out-of-control.The conjugate state equations and the state equations have been solved by use of Laplace Transformation. Through considerably complex computation, the optimal intercept guidance laws have been deduced in the following analytical formsThrough appropriate selection of the terminal time lf or the time of lead T, the results obtained above may be transformed into the optimal guidance laws which are composed of the proportional navigation with varied coefficients and the correctional terms associated with acceleration and angular acceleration of sight-line rotation. These results are similar to those of missiles with first order delay link in form and have no need of any additional parameter. However, the computation is more complex and the results are more accurate.Finally, the optimal intercept guidance laws are studied in the case of the proper frequency of a missile ω approaching to infinity, i. e. in the case of an ideal particle. The results are the same as those obtained by the other authors.

本文研究了具有二阶环节的导弹其对目标的最优导引律。利用极小值原理分别研究了1)脱靶量为零、最小控制能量指标的最优导引律;2)终态为零控拦截曲面、最小能量指标的最优导引律。最后得出了与具有一阶延迟环导弹所得结果类似,但计算工作量更大,结果应更准确。

In this paper, effect of deflection of vertical on ballistic missileimpact accuracy is discussed. By analysing the effect of deflection of vertical in the powered stepsof flight the perturbations of the cut-off condition are obtained. Onanalysing the miss coefficient we arrived at the conclusion that it isnecessary to use the cut-off parameters taking in account the earthsrotation for computing the miss coefficients. Analytical formulas forobtaining the cut-off parameters taking in account the earth's rotationfrom...

In this paper, effect of deflection of vertical on ballistic missileimpact accuracy is discussed. By analysing the effect of deflection of vertical in the powered stepsof flight the perturbations of the cut-off condition are obtained. Onanalysing the miss coefficient we arrived at the conclusion that it isnecessary to use the cut-off parameters taking in account the earthsrotation for computing the miss coefficients. Analytical formulas forobtaining the cut-off parameters taking in account the earth's rotationfrom those without taking earth's rotation into account are derived.These formulas used to compute the cut-off parameters under any lauchconditions without the integration of the system of differential eq-uations. The cut-off parameters thus obtained can be used to computethe miss coefficients. In comparison with the results obtained by direct integration oftrajectory equations the method described in this paper gives a relationerror on miss distance of less than 2% and an absolute error of about30 meters. Finally, this paper puts formulas for computing the miss distancedue to deflection of the vertical and methods for correcting the missdistance of inertial guidance are briefly discussed.

本文讨论垂线偏差对弹道导弹命中精度的影响。首先,通过导弹主动段飞行中垂线偏差影响的分析,获得关机点条件的摄动。然后,通过对脱靶系数的分析,得出结论:必须用考虑地球旋转的关机点参数来计算脱靶系数。文章导出利用不考虑地球旋转的关机点参数求取考虑地球旋转关机点参数的解析表达式。利用这个解析结果,可以计算在任意发射条件下的关机点参数,而无需去积分微分方程组,用这些关机点参数即可计算脱靶系数。就本文提供的方法与直接积分弹道方程的计算结果而言,脱靶量的相对误差小于2%,绝对误差约为30米。最后,本文给出全程制导下计算垂线偏差的脱靶量的表达式,并对惯性制导修正脱靶量的方法进行了讨论。

 
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