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IMPULSE RADAR GUIDANCE APPARATUS AND METHOD FOR USE WITH GUIDED PROJECTILES

机译:脉冲雷达制导装置和与制导弹丸一起使用的方法

摘要

An impulse radar guidance system (10) and method (30) for use with a spinning projectile (11). The system and method tracks the flight of the spinning projectile using an all-weather radar (14) or tracker (14). A linearly polarized asymmetric waveform (21) is transmitted at the projectile that comprises a series of repeating pulses (22) having a relatively strong, short, positive electric field pulse (23) followed by a relatively weak, long, negative electric-field baseline (24). The projectile contains a dipole antenna (26) having a switching diode (27) disposed between respective halves thereof. The waveform is reflected from the antenna which spins with the projectile and reflects a relatively strong signal when the electric field pulse of the asymmetric waveform is aligned along a conduction direction of the diode, a relatively weak reflected signal when the antenna and diode are aligned orthogonal to the electric field pulse, and a small, non-zero, signal when the diode is aligned anti-parallel to the electric field pulse and the diode is back-biased so that respective halves of the antenna are disconnected. The radar or tracker measures the instantaneous roll angle of the spinning projectile during its flight as a function of the state of the reflected signal. The projectile has a maneuvering device (16), and a receiver (15) that receives commands that causes the maneuvering device to actuate at one or more specific roll-angles to deflect the flight direction of the projectile at a target.
机译:用于旋转弹丸(11)的脉冲雷达制导系统(10)和方法(30)。该系统和方法使用全天候雷达(14)或跟踪器(14)跟踪旋转的弹丸的飞行。线性极化的非对称波形(21)在弹丸上传输,该波形包括一系列重复脉冲(22),这些重复脉冲具有相对强的,短的,正电场脉冲(23),然后是相对弱的,长的,负电场基线(24)。弹丸包含偶极天线(26),偶极天线(26)具有布置在其相应的两半之间的开关二极管(27)。从天线反射的波形随弹丸旋转,当非对称波形的电场脉冲沿二极管的传导方向排列时,该信号反射相对强的信号,而当天线和二极管垂直排列时,该信号反射相对弱的信号当二极管与电场脉冲反向平行排列并且二极管反向偏置时,天线将产生一个不为零的小信号,从而使天线的各半部分断开。雷达或跟踪器测量旋转的弹丸在飞行过程中的瞬时侧倾角,该角取决于反射信号的状态。弹丸具有操纵装置(16)和接收器(15),接收器(15)接收使操纵装置以一个或多个特定侧倾角致动以将弹丸的飞行方向偏转到目标的命令。

著录项

  • 公开/公告号EP0941484B1

    专利类型

  • 公开/公告日2005-02-16

    原文格式PDF

  • 申请/专利权人 RAYTHEON CO;

    申请/专利号EP19980963740

  • 发明设计人 SCHNEIDER ARTHUR J.;SMALL JAMES G.;

    申请日1998-09-22

  • 分类号G01S1/00;F41G7/30;G01S13/02;G01S13/42;

  • 国家 EP

  • 入库时间 2022-08-21 22:10:51

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