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公开(公告)号：US08639476B2
公开(公告)日：2014-01-28
申请号：US13385465
申请日：2012-01-31
CPC分类号： F41G7/007 , F41H11/02 , G01P15/18 , G01S7/003 , G01S13/723 , G01S13/878
摘要： A computer-implemented method is provided for generating the estimation of current position, velocity and acceleration state vectors and associated uncertainty estimation (covariance) of a boosting ballistic missile. The method includes constructing a state tensor of the projectile from a plurality of sensor measurements in Earth-Centered, Earth-Fixed (ECEF) coordinates; translating the state tensor to Cartesian coordinates as a transform state; determining a covariance matrix from the transform state; updating the transformed state as an updated transform state; and updating the covariance matrix as an updated covariance. The process can further include adjusting the covariance matrix by an approximate transition matrix and a process noise matrix. The noise matrix can be translated from a local noise matrix based on a propagation time-step, a scaling parameter, and a bias process noise level. A time-of-flight in the state tensor can be updated by smoothing from a launch event.
摘要翻译： 提供了一种计算机实现的方法，用于产生当前位置，速度和加速度状态向量的估计以及增强弹道导弹的相关不确定性估计（协方差）。 该方法包括从以地球为中心的固定（ECEF）坐标中的多个传感器测量结构构建射弹的状态张量; 将状态张量转换为笛卡尔坐标作为变换状态; 从变换状态确定协方差矩阵; 将变换状态更新为更新的变换状态; 并将协方差矩阵更新为更新的协方差。 该过程还可以包括通过近似转换矩阵和过程噪声矩阵来调整协方差矩阵。 可以基于传播时间步长，缩放参数和偏置过程噪声电平，从本地噪声矩阵转换噪声矩阵。 状态张量中的飞行时间可以通过从发射事件平滑来更新。
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公开(公告)号：US20120316819A1
公开(公告)日：2012-12-13
申请号：US13385465
申请日：2012-01-31
CPC分类号： F41G7/007 , F41H11/02 , G01P15/18 , G01S7/003 , G01S13/723 , G01S13/878
摘要： A computer-implemented method is provided for generating the estimation of current position, velocity and acceleration state vectors and associated uncertainty estimation (covariance) of a boosting ballistic missile. The method includes constructing a state tensor of the projectile from a plurality of sensor measurements in Earth-Centered, Earth-Fixed (ECEF) coordinates; translating the state tensor to Cartesian coordinates as a transform state; determining a covariance matrix from the transform state; updating the transformed state as an updated transform state; and updating the covariance matrix as an updated covariance. The process can further include adjusting the covariance matrix by an approximate transition matrix and a process noise matrix. The noise matrix can be translated from a local noise matrix based on a propagation time-step, a scaling parameter, and a bias process noise level. A time-of-flight in the state tensor can be updated by smoothing from a launch event.
摘要翻译： 提供了一种计算机实现的方法，用于产生当前位置，速度和加速度状态向量的估计以及增强弹道导弹的相关不确定性估计（协方差）。 该方法包括从以地球为中心的固定（ECEF）坐标中的多个传感器测量结构构建射弹的状态张量; 将状态张量转换为笛卡尔坐标作为变换状态; 从变换状态确定协方差矩阵; 将变换状态更新为更新的变换状态; 并将协方差矩阵更新为更新的协方差。 该过程还可以包括通过近似转换矩阵和过程噪声矩阵来调整协方差矩阵。 可以基于传播时间步长，缩放参数和偏置过程噪声电平，从本地噪声矩阵转换噪声矩阵。 状态张量中的飞行时间可以通过从发射事件平滑来更新。
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