公开(公告)号：US06047226A

公开(公告)日：2000-04-04

申请号：US105621

申请日：1997-06-26

申请人： Yeong-Wei Andy Wu ,  Garry Didinsky ,  Douglas H. Hein

发明人： Yeong-Wei Andy Wu ,  Garry Didinsky ,  Douglas H. Hein

IPC分类号： B64G1/26 ,  B64G1/28 ,  B64G1/36 ,  G05D1/08 ,  G06F7/70 ,  B64G1/24

CPC分类号： B64G1/361 ,  B64G1/288 ,  B64G1/36 ,  G05D1/0883 ,  B64G1/26

摘要： Spacecraft attitude is efficiently controlled by utilizing spatial noise and temporal noise in the calculation of gains to a Kalman filter. Spatial noise is modeled in a dynamic fashion so as to provide optimal spatial noise attenuation.

摘要翻译： 通过在计算Kalman滤波器的增益时利用空间噪声和时间噪声来有效地控制航天器姿态。 空间噪声以动态方式建模，以提供最佳的空间噪声衰减。

公开(公告)号：US06691033B1

公开(公告)日：2004-02-10

申请号：US09625392

申请日：2000-07-26

申请人： Rongsheng Li ,  Yeong-Wei Andy Wu ,  Douglas H. Hein

发明人： Rongsheng Li ,  Yeong-Wei Andy Wu ,  Douglas H. Hein

IPC分类号： G01C2100

CPC分类号： B64G1/361 ,  G01C21/025

摘要： A method and apparatus for determining star tracker misalignments is disclosed. The method comprises the steps of defining a defining a reference frame for the star tracker assembly according to a boresight of the primary star tracker and a boresight of a second star tracker wherein the boresight of the primary star tracker and a plane spanned by the boresight of the primary star tracker and the boresight of the second star tracker at least partially define a datum for the reference frame for the star tracker assembly; and determining the misalignment of the at least one star tracker as a rotation of the defined reference frame.

摘要翻译： 公开了一种用于确定星形跟踪器未对准的方法和装置。 该方法包括以下步骤：根据主星形跟踪器的视点和第二星形跟踪器的视轴定义用于星形跟踪器组件的参考框架，其中主星形跟踪器的视轴和由主轴的视轴跨越的平面 主星形跟踪器和第二星形跟踪器的视轴至少部分地定义用于星形跟踪器组件的参考系的基准; 以及确定所述至少一个星形跟踪器的未对准作为所述限定的参考帧的旋转。

公开(公告)号：US06272432B1

公开(公告)日：2001-08-07

申请号：US09309034

申请日：1999-05-10

申请人： Rongsheng Li ,  Yeong-Wei A. Wu ,  Douglas H. Hein ,  Garry Didinsky

发明人： Rongsheng Li ,  Yeong-Wei A. Wu ,  Douglas H. Hein ,  Garry Didinsky

IPC分类号： G01C2102

CPC分类号： G01C21/025 ,  B64G1/288 ,  B64G1/361 ,  B64G1/363 ,  B64G1/365 ,  G05D1/0883

摘要： A system and method of estimating the attitude of a spacecraft compares a three-axis inertial-based estimate of spacecraft attitude to a stellar-based estimate of the spacecraft attitude. A Kalman filter having some states associated with low spatial frequency errors compares the stellar-based attitude estimate to the inertial-based estimate of attitude and apportions total attitude error into two time varying matrices. A first time varying matrix is associated with star tracker low spatial frequency errors, a second time varying matrix is associated with gyro bias errors and attitude errors. The time varying matrices are used to apply corrective feedbacks to the stellar-based attitude estimate and the inertial-based estimate of spacecraft attitude, and are adaptively adjusted to minimize total estimated attitude error.

摘要翻译： 估计航天器态度的系统和方法将基于三轴惯性的航天器姿态估计与基于恒星的航天器姿态估计进行比较。 具有与低空间频率误差相关联的一些状态的卡尔曼滤波器将基于星态的姿态估计与基于惯性的姿态估计和总姿态误差分配成两个时变矩阵进行比较。 第一时变矩阵与星形跟踪器低空间频率误差相关联，第二时变矩阵与陀螺仪偏置误差和姿态误差相关联。 时变矩阵用于对基于恒星的姿态估计和基于惯性的航天器姿态估计应用校正反馈，并进行自适应调整以最小化总估计姿态误差。

公开(公告)号：US06236939B1

公开(公告)日：2001-05-22

申请号：US09261727

申请日：1999-03-03

申请人： Yeong-Wei A. Wu ,  Douglas H. Hein ,  Garry Didinsky ,  David L. Augenstein

发明人： Yeong-Wei A. Wu ,  Douglas H. Hein ,  Garry Didinsky ,  David L. Augenstein

IPC分类号： G01C2102

CPC分类号： B64G1/361 ,  B64G2001/245 ,  G01C21/025 ,  G01S3/7867 ,  G01S5/163

摘要： High precision spacecraft attitude determination is produced by specially positioning the spacecraft's star trackers and then filtering out measurement errors produced from star tracker electronics. In addition to the conventional azimuth and elevation controls used for star tracker pointing, the star tracker detector array is rotationally positioned about its boresight so that its pixels are traversed by the imaged star path at an angle within 20° of diagonal. This forces both vertical and horizontal spatial error components in the detector plane to a high frequency range at which they can easily be filtered out in common.

摘要翻译： 通过专门定位航天器的星形跟踪器，然后滤除由星形跟踪器电子产生的测量误差，产生高精度航天器姿态测定。 除了用于星形跟踪器指向的常规方位和仰角控制之外，星形跟踪器检测器阵列围绕其视轴旋转地定位，使得其像素以对角线的20°内的角度被成像的星形路径穿过。 这迫使检测器平面中的垂直和水平空间误差分量都到高频范围，在这个高频范围内，它们可以容易地被共同滤除。

公开(公告)号：US06441776B1

公开(公告)日：2002-08-27

申请号：US09479701

申请日：2000-01-07

申请人： Douglas H. Hein ,  Rongsheng Li

发明人： Douglas H. Hein ,  Rongsheng Li

IPC分类号： G01S502

CPC分类号： B64G1/242 ,  B64G1/24 ,  B64G1/26 ,  B64G1/288 ,  B64G1/36 ,  B64G1/361 ,  B64G1/363 ,  B64G1/365 ,  B64G2001/245 ,  G01S19/53

摘要： A method, apparatus, and article of manufacture for directing a payload coupled to a spacecraft substantially at a target location is disclosed. The method comprises the steps of determining spacecraft orbital parameters and spacecraft payload attitude parameters; and directing the payload at the target location by applying a spacecraft bus steering law determined at least in part from the orbit and attitude parameters. The apparatus comprises a navigation system for determining spacecraft orbit parameters and spacecraft attitude parameters, and for applying a spacecraft bus steering law to direct the payload substantially at the target location. The spacecraft bus steering law is determined at least in part from the determined spacecraft orbital parameters, the determined spacecraft attitude, and determined payload attitude parameters. In one embodiment, the apparatus includes a payload attitude control system for directing the payload relative to the spacecraft bus. The article of manufacture comprises a program storage device tangibly embodying a series of instruction for performing the above method steps.

摘要翻译： 公开了一种用于引导耦合到航天器的有效载荷基本上在目标位置处的方法，装置和制品。 该方法包括确定航天器轨道参数和航天器有效载荷姿态参数的步骤; 以及通过应用至少部分地从轨道和姿态参数确定的航天器总线导向法，将有效载荷指向目标位置。 该装置包括用于确定航天器轨道参数和航天器姿态参数的导航系统，以及用于应用航天器总线指导规则以将有效载荷基本上引导到目标位置。 至少部分地根据确定的航天器轨道参数，确定的航天器姿态和确定的有效载荷姿态参数来确定航天器总线导向规律。 在一个实施例中，该装置包括用于将有效载荷相对于航天器总线引导的载荷姿态控制系统。 该制品包括有形地体现用于执行上述方法步骤的一系列指令的程序存储装置。

公开(公告)号：US08186626B1

公开(公告)日：2012-05-29

申请号：US12486989

申请日：2009-06-18

申请人： Ketao Liu ,  Qinghong W. Wang ,  Douglas H. Hein

发明人： Ketao Liu ,  Qinghong W. Wang ,  Douglas H. Hein

IPC分类号： B64G1/10

CPC分类号： B64G1/24 ,  B64G1/242 ,  B64G1/26 ,  B64G1/283 ,  B64G1/286 ,  B64G1/36

摘要： A system for determining and controlling an orbit of a spacecraft may include a GPS receiver mounted to the spacecraft to receive GPS information from a plurality of GPS satellites visible to the GPS receiver for determining a position of the spacecraft relative to a reference coordinate system. The system may also include a filter configuration control module to sense a thruster maneuver operation to adjust the orbit of the spacecraft. The system may also include an orbit determination filter to determine at least one of a spacecraft position, velocity, and residue acceleration based on the GPS information and information from the filter configuration control module related to the thruster maneuver operation.

摘要翻译： 用于确定和控制航天器的轨道的系统可以包括安装到航天器的GPS接收器，以从GPS接收器可见的多个GPS卫星接收GPS信息，以确定航天器相对于参考坐标系的位置。 该系统还可以包括用于感测推进器操纵操作以调整航天器的轨道的过滤器配置控制模块。 该系统还可以包括轨道确定滤波器，用于基于GPS信息和来自与推进器机动操作相关的过滤器配置控制模块的信息来确定航天器位置，速度和残余加速度中的至少一个。