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System and method for obtaining precise missile range information for semiactive missile systems

机译:用于获得半主动导弹系统的精确导弹射程信息的系统和方法

摘要

A system (10) for determining the range between a missile (14) and a target (18) adapted for use with a semi-active missile system. The system (10) includes a first circuit (12) for generating a periodic signal (24) that is periodically frequency modulated. A second circuit (16) determines a closing rate at which the missile 14 is approaching the target 18 via the periodic signal 24. A third circuit (16) determines a value containing information corresponding to the range and the closing rate via the periodic signal. A fourth circuit (16) determines the range from the closing rate and the value. In a specific embodiment, the first circuit (12) includes an illumination system (12). The illumination system (12) includes a periodically modulated carrier signal generator (32) that generates the periodic signal (24). The periodically modulated carrier signal generator (32) includes a frequency source, a frequency modulator, and an illumination system computer. The illumination system computer runs software for adjusting the modulation parameters of the frequency modulator. The second, third and fourth circuits (16) are included in a receiver system (16) onboard the missile (14). The receiver system (16) includes a front receiver located near the front of the missile and a rear receiver located near the rear of the missile (14). A receiver system computer runs software that implements the fourth circuit (16). The receiver system (16) includes a local oscillator for providing a reference frequency for the receiver system. The local oscillator derives the reference frequency from the periodic signal provided by the first circuit. In illustrative embodiment, the fourth circuit (16) runs computer software that subtracts the closing rate from the combination of closing rate and range and provides the range in response thereto.
机译:用于确定导弹( 14 )与目标( 18 )之间距离的系统( 10 ),该系统适用于半主动导弹导弹系统。系统( 10 )包括用于生成周期信号( 24 )的第一电路( 12 ),该信号周期性地进行了频率调制。第二个电路( 16 )通过周期信号 24确定导弹 14 接近目标 18 的关闭速率。 第三电路( 16 )通过周期信号确定一个值,该值包含与范围和关闭率相对应的信息。第四电路( 16 )根据闭合率和值确定范围。在特定实施例中,第一电路( 12 )包括照明系统( 12 )。照明系统( 12 )包括一个周期性调制的载波信号生成器( 32 ),它生成周期性信号( 24 )。周期性调制的载波信号发生器( 32 )包括频率源,频率调制器和照明系统计算机。照明系统计算机运行用于调整频率调制器的调制参数的软件。第二,第三和第四电路( 16 )包括在导弹( 14 )的接收器系统( 16 )中。接收器系统( 16 )包括位于导弹前部附近的前接收器和位于导弹后部( 14 )后部的后接收器。接收器系统计算机运行实现第四电路( 16 )的软件。接收器系统( 16 )包括一个本地振荡器,用于为接收器系统提供参考频率。本机振荡器从第一电路提供的周期信号中得出参考频率。在说明性实施例中,第四电路( 16 )运行计算机软件,该计算机软件从闭合率和范围的组合中减去闭合率并响应于此提供范围。

著录项

  • 公开/公告号US6204801B1

    专利类型

  • 公开/公告日2001-03-20

    原文格式PDF

  • 申请/专利权人 RAYTHEON COMPANY;

    申请/专利号US19980134024

  • 发明设计人 DAVID SHARKA;HARVEY J. MELTZER;

    申请日1998-08-14

  • 分类号G01S137/20;

  • 国家 US

  • 入库时间 2022-08-22 01:04:48

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