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1. 发明申请

US20040098177A1 ATTITUDE-ACQUISITION METHODS AND SYSTEMS FOR CONTROLLED SPACECRAFT ATTITUDE 有权
标题翻译：用于控制的空间姿态的姿态采集方法和系统
公开(公告)号：US20040098177A1
公开(公告)日：2004-05-20
申请号：US10300454
申请日：2002-11-19
申请人： The Boeing Company
发明人： David D. Needelman , Yeong-Wei A. Wu , Rongsheng Li
IPC分类号： G06F017/00
CPC分类号： G01C21/025 , B64G1/26 , B64G1/285 , B64G1/288 , B64G1/361 , G05D1/0883
摘要： Attitude acquisition methods and systems are provided which reduce the time generally required to acquire spacecraft attitude estimates and enhance the probability of realizing such estimates. The methods and systems receive, over a time span nullt, successive frames of star-sensor signals that correspond to successive stellar fields-of-view, estimate spacecraft rotation nullr throughout at least a portion of the time span nullt, and, in response to the spacecraft rotation nullr, process the star-sensor signals into a processed set of star-sensor signals that denote star positions across an expanded field-of-view that exceeds any of the successive fields-of-view. The expanded field-of-view facilitates identification of the stars that generated the processed set of star-sensor signals to thereby acquire an initial attitude estimate.
摘要翻译：提供了姿态获取方法和系统，减少了获取航天器态度估计所需的时间，并提高了实现此类估计的可能性。方法和系统在时间跨度Deltat中接收对应于连续的恒星视场的星形传感器信号的连续帧，在至少一部分时间段Deltat中估计航天器旋转Deltar，并响应于航天器旋转Deltar，将星形传感器信号处理成一组经过处理的恒星传感器信号，它们表示超过任何连续视场的扩展视场中的星形位置。扩展的视野有助于识别产生经处理的星形传感器信号集合的恒星，从而获得初始姿态估计。

2. 发明申请

US20030222816A1 Satellite methods and structures for improved antenna pointing and wide field-of-view attitude acquisition 有权
标题翻译：用于改善天线指向和广视野姿态采集的卫星方法和结构
公开(公告)号：US20030222816A1
公开(公告)日：2003-12-04
申请号：US10162465
申请日：2002-06-03
申请人： The Boeing Company
发明人： Ketao Liu , Richard Fowell , Yeong-Wei A. Wu , Rongsheng Li
IPC分类号： H04B007/185 , H01Q003/00
CPC分类号： H01Q3/005
摘要： Methods and structures are provided for reducing pointing errors null of satellite antennas and for generating broad field-of-view satellite attitude acquisition patterns. In one method embodiment, satellite transmit beams have estimated pointing attitudes null and are transmitted to overlap on a ground-based receiving terminal which has a known terminal location null and which measures received signal strengths null. Pointing errors null of the transmit beams are then determined from the estimated pointing attitudes null, the terminal location null and the signal strengths null and the pointing errors null are subsequently reduced by revising the pointing attitudes null. Other method embodiments utilize known signal-strength functions and antenna signals with known signal parameters such as frequencies and/or modulations.
摘要翻译：提供了用于减少卫星天线的指向误差zeta和产生广泛的视野卫星姿态采集模式的方法和结构。在一个方法实施例中，卫星发射波束具有估计的指向姿态β，并且在具有已知终端位置λ并且测量接收信号强度α的基于地面的接收终端上被发送以重叠。然后从估计的指向态度β确定发射波束的指向误差zeta，随后通过修正指向态度β来减少终端位置λ和信号强度α和指向误差zeta。其他方法实施例利用具有已知信号参数（例如频率和/或调制）的已知信号强度函数和天线信号。

3. 发明申请

US20030057354A1 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）错误自动校正的系统和方法
公开(公告)号：US20030057354A1
公开(公告)日：2003-03-27
申请号：US09961704
申请日：2001-09-24
申请人： THE BOEING COMPANY
发明人： Yeong-Wei Wu , Rongsheng Li
IPC分类号： G01J001/20
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。

4. 发明申请

US20030171855A1 SPACECRAFT METHODS AND STRUCTURES WITH ENHANCED ATTITUDE CONTROL THAT FACILITATES GYROSCOPE SUBSTITUTIONS 有权
标题翻译：具有增强姿态控制的补充方法和结构，有助于取代GYROSCOPE
公开(公告)号：US20030171855A1
公开(公告)日：2003-09-11
申请号：US10039488
申请日：2001-10-28
申请人： BOEING COMPANY
发明人： Rongsheng Li , Jeffrey A. Kurland , Alec M. Dawson , Yeong-Wei A. Wu , David S. Uetrecht
IPC分类号： G05D001/00 , G06F007/00
CPC分类号： G05D1/0883 , B64G1/26 , B64G1/28 , B64G1/285 , B64G1/288 , B64G1/32 , B64G1/36 , G05B13/024
摘要： Methods and structures are provided that enhance attitude control during gyroscope substitutions by insuring that a spacecraft's attitude control system does not drive its absolute-attitude sensors out of their capture ranges. In a method embodiment, an operational process-noise covariance Q of a Kalman filter is temporarily replaced with a substantially greater interim process-noise covariance Q. This replacement increases the weight given to the most recent attitude measurements and hastens the reduction of attitude errors and gyroscope bias errors. The error effect of the substituted gyroscopes is reduced and the absolute-attitude sensors are not driven out of their capture range. In another method embodiment, this replacement is preceded by the temporary replacement of an operational measurement-noise variance R with a substantially larger interim measurement-noise variance R to reduce transients during the gyroscope substitutions.
摘要翻译：提供了通过确保航天器的姿态控制系统不将其绝对姿态传感器驱动到其捕获范围之外来增强陀螺仪替换期间的姿态控制的方法和结构。在方法实施例中，卡尔曼滤波器的操作过程 - 噪声协方差Q被临时过程噪声协方差Q临时替换。该替换增加了给予最近姿态测量的重量并加速了姿态误差的降低，并且陀螺偏置误差。取代陀螺仪的误差效应降低，绝对姿态传感器不会被驱赶出其捕获范围。在另一方法实施例中，该替换之前是临时替换具有相当大的临时测量噪声方差R的操作测量噪声方差R，以减少在陀螺仪替换期间的瞬变。

5. 发明申请

US20030093194A1 Attitude determination system and method with outer-loop gyro scale-factor non-linearity calibration 失效
公开(公告)号：US20030093194A1
公开(公告)日：2003-05-15
申请号：US09993022
申请日：2001-11-13
申请人： THE BOEING COMPANY
发明人： Rongsheng Li , Yeong-Wei Wu , David L. Augenstein
IPC分类号： B64G001/24
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.

6. 发明申请

US20030080255A1 ATTITUDE CONTROL METHODS AND SYSTEMS FOR MULTIPLE-PAYLOAD SPACECRAFT 有权
标题翻译：多种载荷空间的姿态控制方法和系统
公开(公告)号：US20030080255A1
公开(公告)日：2003-05-01
申请号：US10039474
申请日：2001-10-28
申请人： THE BOEING COMPANY
发明人： Rongsheng Li , Yeong-Wei A. Wu , Hanching Grant Wang
IPC分类号： B64G001/22 , B64G001/62
CPC分类号： G05D1/0883 , B64G1/24 , B64G1/26 , B64G1/285 , B64G1/288 , B64G1/36 , B64G1/361 , B64G1/363 , B64G1/365 , B64G1/66 , Y10S343/02
摘要： Attitude determination and control systems are provided that combine attitude measurements from all spacecraft payloads to determine a master attitude estimate for a master payload and relative slave attitude estimates for the remaining slave payloads. These estimates are then used to control the attitudes of spacecraft elements that correct the absolute and relative attitude errors. These systems significantly enhance attitude accuracy when compared to systems that realize independent payload estimates. determine payload attitudes. These systems also provide significant processing advantages (e.g., simpler algorithms, reduced data throughput and slower processing rate).
摘要翻译：提供了姿态确定和控制系统，其结合来自所有航天器有效载荷的姿态测量，以确定主载荷的主姿态估计以及剩余从动载荷的相对从属姿态估计。然后将这些估计值用于控制航天器元件的态度，以纠正绝对和相对姿态误差。与实现独立有效载荷估计的系统相比，这些系统显着提高了姿态精度。确定有效载荷态度。这些系统还提供显着的处理优点（例如，更简单的算法，减少的数据吞吐量和较慢的处理速率）。

7. 发明申请

US20020125375A1 SPACECRAFT METHODS AND SYSTEMS FOR AUTONOMOUS CORRECTION OF STAR TRACKER CHARGE-TRANSFER-EFFICIENCY ERRORS 有权
标题翻译：用于自动校正星形跟踪器充电传输效率错误的方法和系统
公开(公告)号：US20020125375A1
公开(公告)日：2002-09-12
申请号：US09769637
申请日：2001-01-25
申请人： THE BOEING COMPANY
发明人： Yeong-Wei Wu , Rongsheng Li , James H. Green
IPC分类号： B64G001/24 , B64G001/36
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 null 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 null* of the star-coordinate error factor null with conventional estimation processes. The measured star coordinates Cms are then corrected with the error factor estimate null* 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。

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