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21. 发明授权

US07149610B2 Momentum estimator for on-station momentum control 失效
标题翻译：车站动量控制的动量估计器
公开(公告)号：US07149610B2
公开(公告)日：2006-12-12
申请号：US10647958
申请日：2003-08-26
申请人： Hanching G. Wang , Rongsheng Li
发明人： Hanching G. Wang , Rongsheng Li
IPC分类号： G05D1/00 , G05D1/08 , B64G1/24 , G06F17/00 , B64G1/36
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值，将多个航天器动量测量值拟合到具有时间段t p p p的航天器动量分布的参数模型，确定航天器从参数模型; 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。

22. 发明授权

US06863244B2 Mitigation of angular acceleration effects on optical sensor data 有权
标题翻译：减小角加速度对光学传感器数据的影响
公开(公告)号：US06863244B2
公开(公告)日：2005-03-08
申请号：US10360020
申请日：2003-02-07
申请人： Richard A. Fowell , Salma I. Saeed , Rongsheng Li , Yeong-Wei Wu
发明人： Richard A. Fowell , Salma I. Saeed , Rongsheng Li , Yeong-Wei Wu
IPC分类号： B64G1/28 , B64G1/36 , B64G1/24
CPC分类号： B64G1/361 , B64G1/288 , B64G1/36 , B64G1/363 , B64G1/365
摘要： A method, apparatus, article of manufacture, and a memory structure for compensating for optical sensor data corrupted by angular acceleration is disclosed. The method comprises the steps of determining an angular acceleration of the optical sensor and modifying the optical sensor data according to the determined angular acceleration of the optical sensor. The apparatus comprises a sensor for determining an angular acceleration of the optical sensor and a navigation system for modifying the optical sensor data according to the determined angular acceleration of the optical sensor.
摘要翻译：公开了一种用于补偿由角加速度损坏的光学传感器数据的方法，装置，制品和存储结构。该方法包括以下步骤：根据确定的光学传感器的角加速度确定光学传感器的角加速度并修改光学传感器数据。该装置包括用于确定光学传感器的角加速度的传感器和用于根据确定的光学传感器的角加速度来修改光学传感器数据的导航系统。

23. 发明授权

US06615117B2 Attitude determination system and method with outer-loop gyro scale-factor non-linearity calibration 失效
标题翻译：具有外环陀螺比例因子非线性校准的姿态测定系统和方法
公开(公告)号：US06615117B2
公开(公告)日：2003-09-02
申请号：US09993022
申请日：2001-11-13
申请人： Rongsheng Li , Yeong-Wei Wu , David L. Augenstein
发明人： Rongsheng Li , Yeong-Wei Wu , David L. Augenstein
IPC分类号： G06F1900
CPC分类号： B64G1/36 , B64G1/26 , B64G1/285 , B64G1/288 , B64G1/32 , B64G1/361 , B64G1/363 , B64G1/365 , B64G1/366
摘要： A method and apparatus for calibrating rate sensor measurements to compensate for rate sensor scale factor non-linearities. An outer loop compensator compares current rate sensor scale factor estimates with the current scale factor non-linearity compensation, and deviations from the current non-linearity compensation are corrected in an updated compensation.
摘要翻译：用于校准速率传感器测量以补偿速率传感器比例因子非线性的方法和装置。外部环路补偿器将当前速率传感器比例因子估计与当前比例因子非线性补偿进行比较，并且在更新的补偿中校正与当前非线性补偿的偏差。

24. 发明授权

US06566640B2 System and method for autonomous correction of star tracker high spatial frequency (HSF) error 有权
标题翻译：星际跟踪器高空间频率（HSF）误差自主校正的系统和方法
公开(公告)号：US06566640B2
公开(公告)日：2003-05-20
申请号：US09961704
申请日：2001-09-24
申请人： Yeong-Wei Wu , Rongsheng Li
发明人： Yeong-Wei Wu , Rongsheng Li
IPC分类号： G01J120
CPC分类号： B64G1/361 , B64G1/288 , G01C21/025
摘要： A method and apparatus for post processing a star tracker measurement to remove a systematic error characterizable at least in part by a pixel phase is disclosed. The method comprises the steps of computing the pixel phase along a first axis from a measured star position and a star tracker characteristic, computing a first axis error correction according to the computed pixel phase, and computing a compensated first axis star tracker measurement according to the measured star position and the first axis error correction.
摘要翻译：公开了用于后处理星形跟踪器测量以去除至少部分由像素相位表征的系统误差的方法和装置。该方法包括以下步骤：从测量的星形位置和星形跟踪器特性计算沿着第一轴的像素相位，根据所计算的像素相位计算第一轴误差校正，以及根据所计算的像素相位计算补偿的第一轴星形跟踪器测量测量星座位置和第一轴误差校正。

25. 发明授权

US06330988B1 System for star catalog equalization to enhance attitude determination 有权
标题翻译：星级目录均衡系统，增强态度确定
公开(公告)号：US06330988B1
公开(公告)日：2001-12-18
申请号：US09628779
申请日：2000-07-29
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： B64G124
CPC分类号： B64G1/361
摘要： An apparatus for star catalog equalization to enhance attitude determination includes a star tracker, a star catalog and a controller. The star tracker is used to sense the positions of stars and generate signals corresponding to the positions of the stars as seen in its field of view. The star catalog contains star location data that is stored using a primary and multiple secondary arrays sorted by both declination (DEC) and right ascension (RA), respectively. The star location data stored in the star catalog is predetermined by calculating a plurality of desired star locations, associating one of a plurality of stars with each of the plurality of desired star locations based upon a neighborhood association angle to generate an associated plurality of star locations: If an artificial star gap occurs during association, then the neighborhood association angle for reassociation is increased. The controller uses the star catalog to determine which stars to select to provide star measurement residuals for correcting gyroscope bias and spacecraft attitude.
摘要翻译：用于星型目录均衡以增强姿态确定的装置包括星形跟踪器，星形目录和控制器。星形跟踪器用于感测恒星的位置，并产生与其视场中所见的恒星位置相对应的信号。星型目录包含使用分别由偏角（DEC）和右升高（RA）排序的主要和多个辅助阵列存储的星形位置数据。存储在星形目录中的星形位置数据是通过计算多个所需的星形位置来预先确定的，所述星形位置基于邻域关联角将多个恒星中的一个与多个所需星形位置中的每一个相关联，以产生相关联的多个星形位置：如果在关联期间发生人造星差距，则重新关联的邻域关联角度增加。控制器使用星形目录来确定选择哪颗星以提供星测量残差来校正陀螺仪偏差和航天器姿态。

26. 发明授权

US06288671B1 Beacon-assisted spacecraft attitude control systems and methods 有权
标题翻译：信标辅助航天器姿态控制系统和方法
公开(公告)号：US06288671B1
公开(公告)日：2001-09-11
申请号：US09557378
申请日：2000-04-25
申请人： Yeong-Wei Andy Wu , Umesh S. Ketkar , Rongsheng Li , Richard Y. Chiang
发明人： Yeong-Wei Andy Wu , Umesh S. Ketkar , Rongsheng Li , Richard Y. Chiang
IPC分类号： H04B7185
CPC分类号： G01S3/30 , G01S5/0247 , G01S19/38
摘要： Control systems and methods are provided which enhance acquisition range, transient response and offset pointing accuracy in beacon-assisted orientation of a spacecraft to a desired spacecraft attitude Adsrd. The methods receive a beacon signal with antennas that are arranged in a fixed angular relationship to thereby form an attitude error signal Serr whose magnitude is a measure of the attitude difference between a current spacecraft attitude Acrnt and the desired spacecraft attitude Adsrd. A sum power P&Sgr; that is the sum of the signal powers from the antennas is sensed and a signal modifier Smod is generated that increases with decreases in the sum power P&Sgr;. The attitude error signal Serr is then modified with a term (1+Smod) to form an enhanced attitude error signal Serrenhd. In one embodiment, the signal modifier Smod is n|Pmax−P&Sgr;|m wherein n and m are positive numbers and Pmax is the sum power P&Sgr; when the attitude error is zero.
摘要翻译：提供了控制系统和方法，其增强了航天器信标辅助定向到期望的航天器姿态的采集范围，瞬态响应和偏移指向精度Adsrd。该方法接收具有以固定角度关系布置的天线的信标信号，从而形成姿态误差信号Serr，其大小是当前航天器姿态Acrnt与期望的航天器姿态Adsrd之间的姿态差的度量。检测作为来自天线的信号功率的总和的总功率PSIGMA，并且产生信号修正器Smod，其随和功率PSIGMA的减小而增加。然后用项（1 + Smod）修改姿态误差信号Serr，以形成增强的姿态误差信号Serrenhd。在一个实施例中，信号修正器Smod是n | Pmax-PSIGMA | m，其中n和m是正数，Pmax是姿态误差为零时的和功率PSIGMA。

27. 发明申请

US20130085628A1 Modified Kalman Filter for Generation of Attitude Error Corrections 有权
标题翻译：用于产生姿态误差校正的改进卡尔曼滤波器
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。

28. 发明授权

US08370064B1 Integrated global navigation satellite system and inertial navigation system for navigation and tracking 有权
标题翻译：综合全球导航卫星系统和导航跟踪惯性导航系统
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。

29. 发明授权

US08259012B2 Software GNSS receiver for high-altitude spacecraft applications 有权
标题翻译：软件GNSS接收机用于高空飞船应用
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。

30. 发明申请

US20110254734A1 Software GNSS Receiver for High-Altitude Spacecraft Applications 有权
标题翻译：用于高空航天器应用的软件GNSS接收机
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。

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