公开(公告)号：US20050049764A1

公开(公告)日：2005-03-03

申请号：US10647958

申请日：2003-08-26

申请人： Hanching Wang ,  Rongsheng Li

发明人： Hanching Wang ,  Rongsheng Li

IPC分类号： B64G1/28 ,  G05D1/08 ,  G06F7/00

CPC分类号： B64G1/28 ,  B64G2001/245 ,  G05D1/0883

摘要： A method and apparatus for estimating spacecraft momentum is disclosed. The method comprises the steps of generating a plurality of spacecraft momentum measurements, fitting the plurality of spacecraft momentum measurements to a parametric model of a spacecraft momentum profile having a time period of tp, determining the momentum of the spacecraft from the parametric model; and generating an estimate of the momentum to be removed from the spacecraft at least in part from the determined momentum of the spacecraft.

摘要翻译： 公开了一种用于估计航天器动量的方法和装置。 该方法包括以下步骤：产生多个航天器动量测量，将多个航天器动量测量拟合到具有时间周期tp的航天器动量分布的参数模型，从参数模型确定航天器的动量; 并且至少部分地从所确定的航天器的动量产生要从航天器移除的动量的估计。

公开(公告)号：US06304822B1

公开(公告)日：2001-10-16

申请号：US09629961

申请日：2000-08-01

申请人： Yong Liu ,  Yeong-Wei Andy Wu ,  Rongsheng Li

发明人： Yong Liu ,  Yeong-Wei Andy Wu ,  Rongsheng Li

IPC分类号： G01C2100

CPC分类号： B64G1/361 ,  B64G2001/245 ,  G01C21/24 ,  G01S3/7867 ,  G05D1/0883

摘要： Methods are provided for dynamically processing successively-generated star tracker data frames and associated valid flags to generate processed star tracker signals that have reduced noise and a probability greater than a selected probability Pslctd of being valid. These methods maintain accurate spacecraft attitude control in the presence of spurious inputs (e.g., impinging protons) that corrupt collected charges in spacecraft star trackers. The methods of the invention enhance the probability of generating valid star tracker signals because they respond to a current frame probability Pfrm by dynamically selecting the largest valid frame combination whose combination probability Pcmb satisfies a selected probability Pslctd. Noise is thus reduced while the probability of finding a valid frame combination is enhanced. Spacecraft structures are also provided for practicing the methods of the invention.

摘要翻译： 提供了用于动态处理连续产生的星形跟踪器数据帧和相关联的有效标志的方法，以产生具有减小的噪声的处理的星形跟踪器信号和大于所选择的有效概率Pslctd的概率。 这些方法在存在损坏航天器星形跟踪器收集的费用的杂散输入（例如撞击质子）的情况下，保持准确的航天器姿态控制。 本发明的方法通过动态地选择组合概率Pcmb满足选定概率Pslctd的最大有效帧组合来响应当前帧概率Pfrm，增强了产生有效星迹跟踪信号的概率。 因此降低了噪声，同时增强了找到有效帧组合的概率。 还提供了航天器结构来实施本发明的方法。

公开(公告)号：US20130085628A1

公开(公告)日：2013-04-04

申请号：US13251785

申请日：2011-10-03

申请人： Rongsheng Li ,  Tung-Ching Tsao ,  Arunkumar P. Nayak

发明人： Rongsheng Li ,  Tung-Ching Tsao ,  Arunkumar P. Nayak

IPC分类号： B64G1/36 ,  G06F19/00 ,  G01C25/00

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。

公开(公告)号：US08370064B1

公开(公告)日：2013-02-05

申请号：US12760221

申请日：2010-04-14

申请人： Rongsheng Li ,  Kamran Ghassemi

发明人： Rongsheng Li ,  Kamran Ghassemi

IPC分类号： G01C21/00

CPC分类号： G01C21/165

摘要： A system for navigation and tracking may include an inertial navigation system adapted to generate a replica GNSS signal and a global navigation satellite system. The global navigation satellite system may include a module to digitize a GNSS signal received from a constellation of global navigation satellites. A correlator receives the digitized GNSS signal and the replica GNSS signal. The correlator correlates the digitized GNSS signal to the replica GNSS signal to generate a correlated GNSS signal. A coherent integration module coherently integrates the correlated GNSS signal to generate an integrated signal having a predetermined rate. A filter receives the integrated signal and generates a data signal for navigation and tracking. An output device may present the navigation and tracking information based on the data signal, or the navigation and tracking information may be used to provide guidance for a vehicle or may be used to track a target.

摘要翻译： 用于导航和跟踪的系统可以包括适于生成副本GNSS信号和全球导航卫星系统的惯性导航系统。 全球导航卫星系统可以包括用于数字化从全球导航卫星星座接收的GNSS信号的模块。 相关器接收数字化的GNSS信号和副本GNSS信号。 相关器将数字化GNSS信号与复制GNSS信号相关联，以产生相关的GNSS信号。 相干集成模块将相关的GNSS信号相互整合，以产生具有预定速率的积分信号。 滤波器接收积分信号并产生用于导航和跟踪的数据信号。 输出设备可以基于数据信号呈现导航和跟踪信息，或者导航和跟踪信息可以用于为车辆提供指导，或者可以用于跟踪目标。

公开(公告)号：US08259012B2

公开(公告)日：2012-09-04

申请号：US12760294

申请日：2010-04-14

申请人： Rongsheng Li ,  Kamran Ghassemi ,  Clifford W. Kelley

发明人： Rongsheng Li ,  Kamran Ghassemi ,  Clifford W. Kelley

IPC分类号： G01S19/37

CPC分类号： G01S19/246 ,  G01S19/14 ,  G01S19/23 ,  G01S19/46

摘要： A system that provides GPS-based navigation/orbit determination capabilities for high-altitude spacecraft. The system uses an existing spacecraft processor and an easy-to-space-qualify minimum-hardware front end to minimize the need for new space-qualified hardware. The system also uses coherent integration to acquire and track the very weak GPS signals at high altitudes. The system also uses diurnal thermal modeling of a spacecraft clock and precision orbit propagation to enable longer coherent integration, a special Kalman filter to allow weak signal tracking by integrated operation of orbit determination and GPS signal tracking, and a segment-by-segment, post-processing, delayed-time approach to allow a low-speed spacecraft processor to provide the software GPS capability.

摘要翻译： 一种为高空飞行器提供基于GPS的导航/轨道确定能力的系统。 该系统使用现有的航天器处理器和易于空间限定的最低硬件前端，以最小化对新的空间合格硬件的需求。 该系统还使用相干集成来获取和跟踪高海拔的非常弱的GPS信号。 该系统还使用航天器时钟和精密轨道传播的日间热建模，以实现更长的相干积分，一种特殊的卡尔曼滤波器，可通过轨道确定和GPS信号跟踪的综合操作来实现弱信号跟踪，以及逐段式 处理，延迟时间方法，允许低速航天器处理器提供软件GPS功能。

公开(公告)号：US20110254734A1

公开(公告)日：2011-10-20

申请号：US12760294

申请日：2010-04-14

申请人： Rongsheng Li ,  Kamran Ghassemi ,  Clifford W. Kelley

发明人： Rongsheng Li ,  Kamran Ghassemi ,  Clifford W. Kelley

IPC分类号： G01S19/37

CPC分类号： G01S19/246 ,  G01S19/14 ,  G01S19/23 ,  G01S19/46

摘要： A system that provides GPS-based navigation/orbit determination capabilities for high-altitude spacecraft. The system uses an existing spacecraft processor and an easy-to-space-qualify minimum-hardware front end to minimize the need for new space-qualified hardware. The system also uses coherent integration to acquire and track the very weak GPS signals at high altitudes. The system also uses diurnal thermal modeling of a spacecraft clock and precision orbit propagation to enable longer coherent integration, a special Kalman filter to allow weak signal tracking by integrated operation of orbit determination and GPS signal tracking, and a segment-by-segment, post-processing, delayed-time approach to allow a low-speed spacecraft processor to provide the software GPS capability.

摘要翻译： 一种为高空飞行器提供基于GPS的导航/轨道确定能力的系统。 该系统使用现有的航天器处理器和易于空间限定的最低硬件前端，以最小化对新的空间合格硬件的需求。 该系统还使用相干集成来获取和跟踪高海拔的非常弱的GPS信号。 该系统还使用航天器时钟和精密轨道传播的日间热建模，以实现更长的相干积分，一种特殊的卡尔曼滤波器，可通过轨道确定和GPS信号跟踪的综合操作来实现弱信号跟踪，以及逐段式 处理，延迟时间方法，允许低速航天器处理器提供软件GPS功能。

公开(公告)号：US07665695B2

公开(公告)日：2010-02-23

申请号：US11199932

申请日：2005-08-09

申请人： H. Grant Wang ,  Rongsheng Li

发明人： H. Grant Wang ,  Rongsheng Li

IPC分类号： B64G1/24

CPC分类号： B64G1/281 ,  B64G1/00 ,  B64G1/007 ,  B64G1/10 ,  B64G1/24 ,  B64G1/242 ,  B64G1/26 ,  B64G1/28 ,  B64G1/283 ,  B64G1/285 ,  B64G1/288 ,  B64G1/36 ,  B64G1/361 ,  B64G1/363 ,  B64G1/40 ,  B64G1/401 ,  B64G1/405 ,  B64G1/44 ,  B64G1/443 ,  G01C21/02 ,  G01C21/025 ,  G05D1/08 ,  G05D1/0883

摘要： A method of controlling attitude of a spacecraft during a transfer orbit operation is provided. The method includes providing a slow spin rate, determining the attitude of the spacecraft using a unified sensor set, and controlling the attitude of the spacecraft using a unified control law. The use of a unified set of sensors and a unified control law reduces spacecraft complexity, cost, and weight.

摘要翻译： 提供了一种在转移轨道操作期间控制航天器姿态的方法。 该方法包括提供缓慢的旋转速率，使用统一的传感器组来确定航天器的姿态，并使用统一的控制律来控制航天器的姿态。 使用统一的传感器和统一的控制规则可以降低航天器的复杂性，成本和重量。

公开(公告)号：US20060186274A1

公开(公告)日：2006-08-24

申请号：US11200215

申请日：2005-08-09

申请人： H. Wang ,  Rongsheng Li

发明人： H. Wang ,  Rongsheng Li

IPC分类号： B64G1/10

CPC分类号： B64G1/281 ,  B64G1/007 ,  B64G1/242 ,  B64G1/26 ,  B64G1/28 ,  B64G1/283 ,  B64G1/285 ,  B64G1/288 ,  B64G1/36 ,  B64G1/361 ,  B64G1/363 ,  B64G1/401 ,  B64G1/405 ,  B64G1/44 ,  B64G1/443 ,  G01C21/025 ,  G05D1/0883

摘要： A system for, and method of recovering a solar-powered spacecraft from an anomaly that renders the attitude of the spacecraft unknown includes maintaining a power-safe attitude by switching between two orthogonal axes using solar panel current sensors. The system and method may also include simultaneously determining spacecraft attitude using a star sensor. The system is applicable to spacecraft operating in a solar wing-stowed configuration.

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：US06460809B1

公开(公告)日：2002-10-08

申请号：US09769637

申请日：2001-01-25

申请人： Yeong-Wei Wu ,  Rongsheng Li ,  James H. Green

发明人： Yeong-Wei Wu ,  Rongsheng Li ,  James H. Green

IPC分类号： B64G136

CPC分类号： G05D1/0883 ,  B64G1/26 ,  B64G1/288 ,  B64G1/361 ,  B64G2001/245

摘要： Structures and methods are provided for deriving corrected star coordinates Ccrctd from measured star coordinates Cms that include star tracker charge transfer efficiency (CTE) errors. The structures and methods are based on a recognition that measured star coordinates Cms of star image centroids include CTE errors which are functions of the CCD path lengths over which the associated electrical charges traveled. In particular, the errors are substantially a product of a respective path length and a star-coordinate error factor &xgr; which, in turn, is a function of the star image magnitudes msi. Information contained in different measured star coordinates Cms is organized to facilitate the derivation of an estimate &xgr;* of the star-coordinate error factor &xgr; with conventional estimation processes. The measured star coordinates Cms are then corrected with the error factor estimate &xgr;* to realize the corrected star coordinates Ccrctd and, thereby, improve the accuracy of spacecraft attitude control.

摘要翻译： 提供了结构和方法，用于从包括星形跟踪器电荷转移效率（CTE）误差的测量的星座坐标Cms导出校正星座标Ccrctd。 结构和方法基于识别，星形图像质心的测量星座坐标Cms包括作为相关电荷行进的CCD路径长度的函数的CTE误差。 特别地，误差基本上是相应的路径长度和星坐标误差因子＆xgr的乘积; 这又是星形图像幅度msi的函数。 包含在不同测量星座坐标Cms中的信息被组织以便于推导星坐标误差因子＆xgr的估计＆xgr * 与传统的估计过程。 然后用误差因子估计＆xgr *来校正测量的星座Cms，以实现校正的星座Ccrctd，从而提高航天器姿态控制的精度。