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    • 1. 发明授权
    • Nonlinear guidance gain factor for guided missiles
    • 导弹非线性引导增益系数
    • US5975460A
    • 1999-11-02
    • US967158
    • 1997-11-10
    • Mark E. ElkanickJames A. Bacon
    • Mark E. ElkanickJames A. Bacon
    • F41G7/22F41G7/00
    • F41G7/22
    • A system (10') for generating a missile guidance gain factor adapted for use with guided missiles. The inventive system includes a guidance control system (52) for obtaining current guidance parameters(55, 57) including ideal navigation gain, closing rate, line of sight rate, missile maneuverability, and missile velocity parameters. Software (56) running on a guidance control processor (54) computes a current guidance gain factor reflective of the current maneuverability of the missile from the guidance parameters (55, 57). In the illustrative embodiment, the system 10' further includes a nonlinear notch circuit (56) that generates an acceleration command (59) from the guidance parameters (55, 57) that varies in response to varying missile maneuverability parameters (57). The guidance control system (10') includes a conventional guidance law computation circuit (54, 55) and electromagnetic sensing equipment (52). An autopilot circuit (58) included in the system (10') provides the missile maneuverability parameters (57). In a specific embodiment, the nonlinear notch circuit (56) is implemented via software running on a guidance processor (54) which performs the following computation for generating the acceleration command (59): A.sub.new =G.sub.nl .times.A, where A.sub.new is the acceleration command (59), A is a pre-existing acceleration command (53), and G.sub.nl is the missile guidance gain factor of the present invention. The guidance gain factor is a function of the ratio of the measured line of sight rate with respect to the ideal line of sight rate maximum, and is tailored to existing missile characteristics and performance requirements.
    • 一种用于产生适于与导弹一起使用的导弹引导增益因子的系统(10')。 本发明的系统包括用于获得包括理想的导航增益,关闭速率,视线速度,导弹机动性和导弹速度参数的当前引导参数(55,57)的引导控制系统(52)。 在引导控制处理器(54)上运行的软件(56)根据引导参数(55,57)计算反映导弹当前可操作性的当前引导增益因子。 在说明性实施例中,系统10'还包括非线性陷波电路(56),该非线性陷波电路根据导弹参数(55,57)产生加速度指令(59),所述引导参数响应于变化的导弹机动性参数而变化。 引导控制系统(10')包括常规的引导律计算电路(54,55)和电磁感测设备(52)。 包括在系统(10')中的自动驾驶仪电路(58)提供导弹机动性参数(57)。 在特定实施例中,非线性陷波电路(56)通过在引导处理器(54)上运行的软件来实现,所述引导处理器执行以下用于生成加速命令(59)的计算:Anew = GnlxA,其中Anew是加速命令(59 ),A是预先存在的加速指令(53),Gnl是本发明的导弹引导增益因子。 引导增益因子是测量视线比相对于理想视线速度最大值的比率的函数,并且是针对现有导弹特性和性能要求而定制的。