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高机动目标
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  highly maneuvering target
     The performance of the algorithm is verified by simulating the tracking of a highly maneuvering target, the results show that: the target can be tracked effectively with the method presented and the accuracy of the tracking is satisfied.
     伪测量目标红外光谱辐射功率之比的构造,消除了目标红外光谱辐射强度不确定所产生的不良影响。 通过跟踪一个高机动目标的仿真过程,对算法性能进行了检验,仿真结果表明:本算法对杂波环境下的机动目标能进行有效的跟踪,而且跟踪的精度也令人满意。
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  “高机动目标”译为未确定词的双语例句
     2) From the viewpoint of correlation receiving, the definition of wideband acceleration ambiguity function (WAAF) is given.
     2)从相关接收的角度给出了宽带加速度模糊函数的定义,考虑到今后高机动目标拦截的需要,详细分析了线性调频信号的加速度模糊函数与观测时间和相对带宽的关系。
短句来源
     The performance of the algorithm is verified by simulating the tracking five highly maneuvering targets,the results show that the new algorithm can reduce the number of tracks and computation time,also has the more capability to restrain noises.
     通过跟踪5个高机动目标的仿真过程,对算法性能进行了检验,仿真结果表明,新的算法可以减少航迹数目、减少系统计算时间,并使算法具有更强的抑制噪声的能力。
短句来源
     (4) A new algorithm, adaptive fuzzy α—β—γ filter, is presented for tracking the high flexible object. The feature of adaptive fuzzy α—β—γ filter is analyzed at the various flexible tacks and various noises.
     (4) 为适应高机动目标的跟踪,本文提出了改进的α—β—γ滤波:模糊自适应α—β—γ滤波,研究了各种目标机动的轨迹和噪声条件下模糊自适应α—β—γ滤波的特性。
短句来源
     It is a challengeable problem to track maneuvering targets,especially tracking the high speed and high maneuvering targets,which has both theoretically and practically technical difficulties.
     对机动目标进行跟踪一直是甚具挑战性的问题,特别是跟踪高速高机动目标在理论上和实践上都有较高的技术难度。
短句来源
     To guarantee capture of an engagement in terminal phase, the nonlinear systems geometry theory are used to design command accelerations of a nonlinear terminal guidance system model for an air to air missile attacking evasive target.
     针对未来高机动目标的拦截 ,运用非线性系统几何理论中的精确线性化方法 ,设计了一种空空导弹非线性末制导系统加速度指令。
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  相似匹配句对
     V. C.
     V.C;
短句来源
     System Design of Highly Mobile Radar
     机动雷达的系统设计
短句来源
     Radar Data Processing on the High Maneuvering Platform
     机动平台下雷达数据处理
短句来源
     A New Method of Maneuver Detection Based on Higher-Order Cumulants
     基于阶累积量的目标机动检测新方法
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     2) When the slurry is set, the compressive strength is high.
     抗压强度
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  highly maneuvering target
Some simulations were conducted to track a highly maneuvering target in a cluttered environment using two sensors.
      
The interception scenario of a highly maneuvering target is formulated as a zero-sum pursuitevasion game.
      


Conventional Proportional Navigation (Pro. Nav.) for tactical missiles is simple, requires minimal computation and therefore is easy to implement. It is, however, not effective against high speed or maneuvering targets. Numerous studies have been made to improve the performance of Pro. Nay. [2,5,7]. The optimal controllers derived in these studies, as compared to Pro. Nay. with a constant navigation ratio, either change the constant ratio to time-varying ones [1,8], or introduce target acceleration into guidance...

Conventional Proportional Navigation (Pro. Nav.) for tactical missiles is simple, requires minimal computation and therefore is easy to implement. It is, however, not effective against high speed or maneuvering targets. Numerous studies have been made to improve the performance of Pro. Nay. [2,5,7]. The optimal controllers derived in these studies, as compared to Pro. Nay. with a constant navigation ratio, either change the constant ratio to time-varying ones [1,8], or introduce target acceleration into guidance laws [4]. Although these modified Pro. Nav. laws have higher accuracy than the original one, they all require bigger missile control power. Furthermore, the authors have not found any report in open literature which investigates the dynamic and static performances of guidance systems (i.e. the interaction between guidance lairs and guidance systems). This paper's main contribution is that an optimal PID type guidance approach is presented; it has higher accuracy, requires lower missile control power than Pro. Nay. and can improve the dynamic and static performances of guidance systems. The optimal controllers obtained by the minimization of generalized line of sight angle error can guarantee quasi-constant-bearing-course. Suboptimality will be attained with linear controllers which are PID type Pro. Nav., but have different structure from those in ref. [3]. Theoretical studies demonstrate that PID type Pro. Nay. also possesses better robustness against the perturbations of guidancc law parameters and missile autopilot parameters than Pro. Nav. Simulation results substantiate the above deductions.

本文提出了一种PID型导引方法。这种导引方法以广义视线角误差(视线角速度积分,比例,微分的函数)绝对值极小为准则,可以实现准平行接近法导引,它对弹体的过载要求低,可以攻击高机动目标。线性制导方式即为PID型比例导引,它是一种次最佳制导策略。PID型比例导引使制导系统的稳定性,动态品质和准确度得到协调提高,对制导参数,导弹自动驾驶仪参数摄动的鲁棒性高。本文的PID型比例导引克服了[3]的PID型比例导引结构上存在的缺陷,仿真结果证明了上述结论。

In this paper, the trends of solid rocket propulsion technology are discussed. It isnecessary that the intercontinental missiles be made small scale and are launched on anautomobile, a train or a plane. So the main trend of SRM for intercontinental missile isto improve performance of SRM. In order to make anti-aircraft missiles tackle the high-speed, high-maneuverable target, and to hide the missile site and missile itself, the maintrend of SRM for anti-aircraft missiles is to develop the technology of controlled...

In this paper, the trends of solid rocket propulsion technology are discussed. It isnecessary that the intercontinental missiles be made small scale and are launched on anautomobile, a train or a plane. So the main trend of SRM for intercontinental missile isto improve performance of SRM. In order to make anti-aircraft missiles tackle the high-speed, high-maneuverable target, and to hide the missile site and missile itself, the maintrend of SRM for anti-aircraft missiles is to develop the technology of controlled thrustand smokeless propellants. The main trends of boosters for launch vehicles and SRM forsmall launch vehicles are lower cost and higher reliability. In addition, it is also an im-portant tendency that the technology of SRM is applied to economical construction.

本文介绍了固体火箭推进技术的发展趋势;对于战略导弹发动机,主要是提高发动机性能,使导弹小型化,能在汽车上、火车上或飞机上机动发射,对于防空导弹发动机,主要是发展推力可控技术和无烟推进剂,使导弹能对付高速、高机动的目标,并使发射场和导弹本身不被烟雾暴露;对于运载火箭助推器和小型运载火箭发动机,主要是降低成本和提高可靠性。固体火箭推进技术应用于国民经济建设,也是其发展的一个重要方面。

PN(proportional navigation) law is in wide use. After a great deal of careful research, we decided to make PN law a variable structure one in order to make it less difficult to implement while satisfying two stringent requirements: (1) the IR(infrared) homing airtoair missile should be effective against highly maneuverable targets; (2) even large offboresight angle launching can be effective. When implementing ordinary PN law, the assumption of small offboresight angle launching is usually made. The implementation...

PN(proportional navigation) law is in wide use. After a great deal of careful research, we decided to make PN law a variable structure one in order to make it less difficult to implement while satisfying two stringent requirements: (1) the IR(infrared) homing airtoair missile should be effective against highly maneuverable targets; (2) even large offboresight angle launching can be effective. When implementing ordinary PN law, the assumption of small offboresight angle launching is usually made. The implementation of our variable structure PN law has no need of such assumption. In our research we considered target normal acceleration, related to target maneuverability, to be bounded disturbance. We utilized variable structure control to overcome such disturbance by making dq/dt, lineofsight rate, approach zero in a limited time. We derived eq.(10) as the model of our variable structure PN law. Simulation results are presented in Fig.2(a). Fullline curve shows the variation of dq/dt with time for PN law; dottedline curve shows the variation of dq/dt with time for variable structure PN law(dq/dt indistinguishable from zero after only about one second for our numerical xample). The comparison shows that highperformance of IR homing missile appears to be attainable with variable structure PN law. Our method is simple and requires no signals additional to dq/dt; thus it is less difficult to implement.

经典的比例导引律不能满足近距格斗导弹大离轴发射和攻击高机动目标的要求。前人提出了多种解决此问题的制导规律,除需要目标视线角速度信息外,还需相对速度、目标加速度和剩余时间等信息,这在被动红外制导导弹上实现是十分困难的。本文以变结构控制理论为基础,给出一种只需目标视线角速度信息的新型制导律,实现了在目标机动的条件下、有限时间内目标视线角速度的零化,大幅度地改善了制导性能。仿真结果证实了设计方法的正确性。

 
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