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    • 1. 发明申请
    • AUTOMATIC RE-INITIALIZATION OF RESONANT SENSORS IN ROCKET AND MISSILE GUIDANCE SYSTEMS
    • 谐振传感器自动重新起动在轨道和导向系统
    • US20120153070A1
    • 2012-06-21
    • US13378070
    • 2011-04-08
    • Derek P. JaniakJames H. Steenson, JR.David SchorrStephen W. Bartlett
    • Derek P. JaniakJames H. Steenson, JR.David SchorrStephen W. Bartlett
    • F42B15/01G01M17/00
    • F42B15/01B64G1/36G01L27/007
    • An apparatus and method improves the fault tolerance of a rocket or missile guidance system which includes a resonant sensor. When improper initialization is detected, the resonant sensor is reinitialized, repeatedly if necessary, until normal operation is achieved. Improper initialization is detected by comparing data from the guidance system with pre-specified physical limits to roll, pitch, yaw, and/or other features of the flight scenario. Embodiments can also detect a fault condition due to an error signal from a “Built-in-Test” (BIT) module. The initialization sequence initiated by the invention can be identical to the power-on sequence, or it can be a separate, reinitiating sequence. Subsequent resets are initiated as needed, for example until the burn of the rocket fuel and the associated vibrations have ceased and the resonant sensor has been successfully initialized.
    • 一种装置和方法提高了包括谐振传感器的火箭或导弹引导系统的容错性。 当检测到不正确的初始化时,如果需要,可以重复初始化谐振传感器,直到达到正常工作。 通过将来自引导系统的数据与预定的物理限制与飞行情景的滚动,俯仰,偏航和/或其他特征进行比较来检测不正确的初始化。 实施例还可以检测来自“内置测试”(BIT)模块的错误信号的故障状况。 由本发明启动的初始化序列可以与上电序列相同,或者可以是单独的再启动序列。 随后的复位根据需要开始,例如直到火箭燃料的燃烧和相关联的振动已经停止并且谐振传感器已被成功初始化。
    • 2. 发明授权
    • Automatic re-initialization of resonant sensors in rocket and missile guidance systems
    • 火箭和导弹引导系统中谐振传感器的自动重新初始化
    • US08563909B2
    • 2013-10-22
    • US13378070
    • 2011-04-08
    • Derek P. JaniakJames H. Steenson, Jr.David SchorrStephen W. Bartlett
    • Derek P. JaniakJames H. Steenson, Jr.David SchorrStephen W. Bartlett
    • G06F11/07G06F11/30F41G9/00G01C19/00F41G7/36
    • F42B15/01B64G1/36G01L27/007
    • An apparatus and method improves the fault tolerance of a rocket or missile guidance system which includes a resonant sensor. When improper initialization is detected, the resonant sensor is reinitialized, repeatedly if necessary, until normal operation is achieved. Improper initialization is detected by comparing data from the guidance system with pre-specified physical limits to roll, pitch, yaw, and/or other features of the flight scenario. Embodiments can also detect a fault condition due to an error signal from a “Built-in-Test” (BIT) module. The initialization sequence initiated by the invention can be identical to the power-on sequence, or it can be a separate, reinitiating sequence. Subsequent resets are initiated as needed, for example until the burn of the rocket fuel and the associated vibrations have ceased and the resonant sensor has been successfully initialized.
    • 一种装置和方法提高了包括谐振传感器的火箭或导弹引导系统的容错性。 当检测到不正确的初始化时,如果需要,可以重复初始化谐振传感器,直到达到正常工作。 通过将来自引导系统的数据与预定的物理限制与飞行情景的滚动,俯仰,偏航和/或其他特征进行比较来检测不正确的初始化。 实施例还可以检测来自“内置测试”(BIT)模块的错误信号的故障状况。 由本发明启动的初始化序列可以与上电序列相同,或者可以是单独的再启动序列。 随后的复位根据需要开始,例如直到火箭燃料的燃烧和相关联的振动已经停止并且谐振传感器已被成功初始化。