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公开(公告)号：US06289268B1
公开(公告)日：2001-09-11
申请号：US09516854
申请日：2000-03-02
申请人： Garry Didinsky , Arunkumar P. Nayak , Rongsheng Li , Yeong-Wei A. Wu , Jeffrey A. Kurland , David D. Needelman
发明人： Garry Didinsky , Arunkumar P. Nayak , Rongsheng Li , Yeong-Wei A. Wu , Jeffrey A. Kurland , David D. Needelman
IPC分类号： G06F700
CPC分类号： G05D1/0883
摘要： A star tracker coupled to the spacecraft having a star catalog associated therewith. A sun sensor is coupled to the spacecraft. A control processor is coupled to the star tracker and the sun sensor. The processor obtains star data using a star tracker and an on-board star catalog. The processor generates a coarse attitude of the spacecraft as a function of the star data, and establishes a track on at least one star in the on-board star catalog. The processor calculates a sun tracking rate, and obtains a normal phase attitude as a function of the star data and the coarse attitude. The information is used to slew the spacecraft to a desired attitude.
摘要翻译： 耦合到具有与之相关联的星形目录的航天器的星形跟踪器。 太阳传感器耦合到航天器。 控制处理器耦合到星形跟踪器和太阳传感器。 处理器使用星形跟踪器和板载星形目录获取星形数据。 处理器根据星型数据产生航天器的粗略姿态，并在车载星形目录中的至少一颗恒星上建立轨道。 处理器计算太阳跟踪率，并且作为星数据和粗略姿态的函数获得正常相位姿态。 该信息用于将飞船旋转到所需的姿态。
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公开(公告)号：US20130085628A1
公开(公告)日：2013-04-04
申请号：US13251785
申请日：2011-10-03
CPC分类号： G01C21/165 , G05D1/0883
摘要： Methods, systems, and computer-readable media are described herein for using a modified Kalman filter to generate attitude error corrections. Attitude measurements are received from primary and secondary attitude sensors of a satellite or other spacecraft. Attitude error correction values for the attitude measurements from the primary attitude sensors are calculated based on the attitude measurements from the secondary attitude sensors using expanded equations derived for a subset of a plurality of block sub-matrices partitioned from the matrices of a Kalman filter, with the remaining of the plurality of block sub-matrices being pre-calculated and programmed into a flight computer of the spacecraft. The propagation of covariance is accomplished via a single step execution of the method irrespective of the secondary attitude sensor measurement period.
摘要翻译： 本文描述了使用修改的卡尔曼滤波器来产生姿态误差校正的方法，系统和计算机可读介质。 从卫星或其他航天器的主要和次要姿态传感器接收姿态测量。 基于来自二级姿态传感器的姿态测量，使用从卡尔曼滤波器的矩阵分割的多个块子矩阵的子集导出的扩展方程式来计算来自主姿态传感器的姿态测量值的姿态误差校正值， 多个块子矩阵的剩余部分被预先计算并编程到航天器的飞行计算机中。 无论二次姿态传感器测量周期如何，通过该方法的单步执行来实现协方差的传播。
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公开(公告)号：US08543266B2
公开(公告)日：2013-09-24
申请号：US13251785
申请日：2011-10-03
IPC分类号： B64G1/36
CPC分类号： G01C21/165 , G05D1/0883
摘要： Methods, systems, and computer-readable media are described herein for using a modified Kalman filter to generate attitude error corrections. Attitude measurements are received from primary and secondary attitude sensors of a satellite or other spacecraft. Attitude error correction values for the attitude measurements from the primary attitude sensors are calculated based on the attitude measurements from the secondary attitude sensors using expanded equations derived for a subset of a plurality of block sub-matrices partitioned from the matrices of a Kalman filter, with the remaining of the plurality of block sub-matrices being pre-calculated and programmed into a flight computer of the spacecraft. The propagation of covariance is accomplished via a single step execution of the method irrespective of the secondary attitude sensor measurement period.
摘要翻译： 本文描述了使用修改的卡尔曼滤波器来产生姿态误差校正的方法，系统和计算机可读介质。 从卫星或其他航天器的主要和次要姿态传感器接收姿态测量。 基于来自二级姿态传感器的姿态测量，使用从卡尔曼滤波器的矩阵分割的多个块子矩阵的子集导出的扩展方程式来计算来自主姿态传感器的姿态测量值的姿态误差校正值， 多个块子矩阵的剩余部分被预先计算并编程到航天器的飞行计算机中。 无论二次姿态传感器测量周期如何，通过该方法的单步执行来实现协方差的传播。
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公开(公告)号：US06978966B2
公开(公告)日：2005-12-27
申请号：US10770903
申请日：2004-02-02
CPC分类号： H01Q15/147 , B64G1/222 , B64G1/66 , H01Q1/288
摘要： A system and method for performing in-orbit alignment calibration using on-board attitude sensors to improve reflector alignment after deployment to improve spacecraft pointing.
摘要翻译： 一种用于使用车载姿态传感器执行轨道内对准校准的系统和方法，以在部署之后改善反射器对准以改善航天器指向。
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