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1.发明申请GYROSCOPIC FAILURE DETECTION IN A NAVIGATION DEVICE THROUGH SENSOR CORRELATION 审中-公开通过传感器相关的导航设备中的GYROSCOPIC FAILURE检测公开(公告)号：US20100243791A1
公开(公告)日：2010-09-30
申请号：US11565173
申请日：2006-11-30
申请人： Zygmunt Zubkow , Robert R. Bacon
发明人： Zygmunt Zubkow , Robert R. Bacon
CPC分类号： G01C21/16 , F42B15/01 , G01C25/005
摘要： A method of determining the integrity of a gyro in a navigation system is provided. The method includes detecting a relatively sudden change in one of a pitch, yaw and roll signal from a respective pitch, yaw and roll gyro and reviewing at least one other of the pitch, yaw and roll signals to verify the relatively sudden change.
摘要翻译： 提供了一种在导航系统中确定陀螺仪的完整性的方法。 该方法包括检测来自相应俯仰，偏航和滚动陀螺仪的俯仰，偏航和滚动信号中的一个相对突然的变化，并且检查俯仰，偏转和滚转信号中的至少一个以验证相对突然的变化。
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2.发明授权Inertial measurement unit fault detection isolation reconfiguration using parity logic 有权惯性测量单元使用奇偶校验逻辑进行故障检测隔离重新配置公开(公告)号：US07805245B2
公开(公告)日：2010-09-28
申请号：US11736825
申请日：2007-04-18
申请人： Robert R. Bacon , Zygmunt Zubkow
发明人： Robert R. Bacon , Zygmunt Zubkow
CPC分类号： G01C21/16 , G01C25/005 , G06F11/183 , G06F11/20
摘要： A method of implementing a fault-tolerant-avionic architecture in a vehicle includes using parity logic to monitor the functionality of at least three non-fault-tolerant inertial measurement units during a parity check and calculating a threshold from expected inertial measurement unit performance during a parity check. If a failure of an inertial measurement unit is detected based on the calculated threshold, then the method further includes identifying the failed inertial measurement units based on a direction of a parity vector in parity space. Each inertial measurement unit comprises at least one triad of sensors.
摘要翻译： 在车辆中实现容错航空电子体系结构的方法包括在奇偶校验期间使用奇偶校验逻辑来监视至少三个非容错惯性测量单元的功能，并且在期望的惯性测量单元性能期间计算阈值 奇偶校验 如果基于所计算的阈值检测到惯性测量单元的故障，则该方法还包括基于奇偶校验空间中的奇偶校验向量的方向来识别失效的惯性测量单元。 每个惯性测量单元包括至少一个三元组的传感器。
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3.发明申请INERTIAL MEASUREMENT UNIT FAULT DETECTION ISOLATION RECONFIGURATION USING PARITY LOGIC 有权惯性测量单元故障检测分离使用奇偶校验逻辑重新配置公开(公告)号：US20080262729A1
公开(公告)日：2008-10-23
申请号：US11736825
申请日：2007-04-18
申请人： Robert R. Bacon , Zygmunt Zubkow
发明人： Robert R. Bacon , Zygmunt Zubkow
IPC分类号： G01C21/00
CPC分类号： G01C21/16 , G01C25/005 , G06F11/183 , G06F11/20
摘要： A method of implementing a fault-tolerant-avionic architecture in a vehicle includes using parity logic to monitor the functionality of at least three non-fault-tolerant inertial measurement units during a parity check and calculating a threshold from expected inertial measurement unit performance during a parity check. If a failure of an inertial measurement unit is detected based on the calculated threshold, then the method further includes identifying the failed inertial measurement units based on a direction of a parity vector in parity space. Each inertial measurement unit comprises at least one triad of sensors
摘要翻译： 在车辆中实现容错航空电子体系结构的方法包括在奇偶校验期间使用奇偶校验逻辑来监视至少三个非容错惯性测量单元的功能，并且在期望的惯性测量单元性能期间计算阈值 奇偶校验 如果基于所计算的阈值检测到惯性测量单元的故障，则该方法还包括基于奇偶校验空间中的奇偶校验向量的方向来识别失效的惯性测量单元。 每个惯性测量单元包括至少一个三元组的传感器
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