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31. 发明授权

US07665695B2 Unified attitude control for spacecraft transfer orbit operations 有权
标题翻译：航天器转移轨道作战统一态度控制
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。

32. 发明申请

US20060186274A1 Spacecraft power acquisition method for wing-stowed configuration 有权
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.

33. 发明授权

US06691033B1 System and method for calibrating inter-star-tracker misalignments in a stellar inertial attitude determination system 有权
标题翻译：用于校正恒星惯性姿态测定系统中的星际跟踪器未对准的系统和方法
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。

34. 发明授权

US06460809B1 Spacecraft methods and systems for autonomous correction of star tracker charge-transfer-efficiency errors 有权
标题翻译：航天器方法和系统，用于自动校正星形跟踪器电荷转移效率误差
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。

35. 发明授权

US06285927B1 Spacecraft attitude determination system and method 有权
标题翻译：航天器姿态测定系统及方法
公开(公告)号：US06285927B1
公开(公告)日：2001-09-04
申请号：US09318565
申请日：1999-05-26
申请人： Rongsheng Li , Yeong-Wei Andy Wu
发明人： Rongsheng Li , Yeong-Wei Andy Wu
IPC分类号： B64G124
CPC分类号： G05D1/0883 , B64G1/24 , B64G1/288 , B64G1/36 , B64G1/361 , B64G1/363 , B64G1/365 , B64G2001/245 , G01C21/025
摘要： A method and system for minimizing attitude errors resulting from dynamic spacecraft maneuvers or time-varying mismatched attitude sensor measurements. The method includes time-tagging a primary attitude value from a primary attitude sensor and storing the value and associated time stamp in a buffer. A secondary attitude value, generated by a secondary attitude sensor, having a different associated time-stamp is then time-matched to the primary attitude valve. The corrected spacecraft attitude is then calculated as a function of the time-matched primary and secondary attitude values. In one aspect of the invention, the primary attitude sensor generates attitude data at a faster rate than the secondary attitude sensor. This primary attitude data is stored in a buffer such that, when the secondary attitude data becomes available, several nearest-in-time primary attitude data points are retrieved from the buffer. These data points are then used to interpolate a higher time-matched resolution data point. This, in turn, is used along with the secondary attitude data point in updating the spacecraft attitude.
摘要翻译：一种用于最小化由动态航天器操纵或时变不对称姿态传感器测量引起的姿态误差的方法和系统。该方法包括从主姿态传感器对主要姿态值进行时间标记，并将该值和相关联的时间戳存储在缓冲器中。然后，由二次姿态传感器产生的具有不同相关联的时间戳的二次姿态值与主姿势阀进行时间匹配。然后根据时间匹配的主要和次要姿态值来计算校正的航天器姿态。在本发明的一个方面，主姿态传感器以比二次姿态传感器更快的速度生成姿态数据。该主要态度数据被存储在缓冲器中，使得当二级姿态数据变得可用时，从缓冲器检索几个最接近时间的主姿势数据点。然后将这些数据点用于内插较高时间匹配的分辨率数据点。这反过来又与二级姿态数据点一起用于更新航天器的态度。

36. 发明授权

US6108594A Autonomous attitude acquisition for a stellar inertial attitude determination system 失效
标题翻译：一种恒星惯性姿态测定系统的自主态度采集
公开(公告)号：US6108594A
公开(公告)日：2000-08-22
申请号：US87409
申请日：1998-05-29
申请人： Garry Didinsky , Yeong-Wei Wu , Rongsheng Li , Arunkumar Nayak , Douglas Hein
发明人： Garry Didinsky , Yeong-Wei Wu , Rongsheng Li , Arunkumar Nayak , Douglas Hein
IPC分类号： B64G1/28 , B64G1/36 , G01C21/02 , G01S3/781 , G01S5/16 , G05D1/08 , G06F165/00
CPC分类号： G01C21/025 , B64G1/361 , G01S3/781 , G01S5/163 , G05D1/0883 , B64G1/288
摘要： A method and apparatus for autonomous acquisition of attitude in a stellar inertial spacecraft attitude system is disclosed. The present invention uses star trackers, an on-board star catalog, spacecraft steering and inertial sensors to determine spacecraft attitude. The present invention utilizes pattern match and pattern rejection methods and uses multiple stellar snap-shots in conjunction with spacecraft steering and spacecraft inertial measurements to acquire spacecraft attitude. Spacecraft inertial measurements are used to connect multiple stellar snap-shots to provide adequate star information that can be used to acquire spacecraft attitude. In an attitude determination system using star trackers, the star trackers may have a narrow field-of-view or few stars may be available for viewing. The present invention uses pattern matching and pattern rejection on different sets of stars, thereby allowing attitude acquisition when the number of stars in view is small.
摘要翻译：公开了一种用于在恒星惯性航天器姿态系统中自动获取姿态的方法和装置。本发明使用星形跟踪器，一个车载星形目录，航天器转向和惯性传感器来确定航天器的姿态。本发明利用模式匹配和模式排斥方法，并结合航天器转向和航天器惯性测量使用多个恒星卡扣，以获得航天器的姿态。航天器惯性测量用于连接多个恒星快照，以提供可用于获取航天器姿态的足够的星级信息。在使用星形跟踪器的态度确定系统中，星形跟踪器可以具有窄的视场或几颗恒星可用于观看。本发明在不同的星星集合上使用模式匹配和模式抑制，从而当观看的星星数量小时允许姿态采集。

37. 发明授权

US08543266B2 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：US08543266B2
公开(公告)日：2013-09-24
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
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。

38. 发明授权

US07546983B2 Spacecraft power acquisition method for wing-stowed configuration 有权
标题翻译：用于机翼收起配置的航天器功率采集方法
公开(公告)号：US07546983B2
公开(公告)日：2009-06-16
申请号：US11200215
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： B64G1/40
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.
摘要翻译：用于使来自使未知航天器的姿态出现的异常的太阳能飞船的系统和方法包括通过使用太阳能电池板电流传感器在两个正交轴之间切换来维持功率安全姿态。该系统和方法还可以包括使用星形传感器同时确定航天器姿态。该系统适用于以太阳能机翼存放配置运行的航天器。

39. 发明申请

US20050246072A1 METHOD AND APPARATUS FOR REAL-TIME STAR EXCLUSION FROM A DATABASE 有权
标题翻译：从数据库中实时排除星号的方法和设备
公开(公告)号：US20050246072A1
公开(公告)日：2005-11-03
申请号：US10709346
申请日：2004-04-29
申请人： David Needelman , Rongsheng Li , Richard Fowell , Peter Lai , Yeong-Wei Wu , Bruce Eyerly , Jonathan French
发明人： David Needelman , Rongsheng Li , Richard Fowell , Peter Lai , Yeong-Wei Wu , Bruce Eyerly , Jonathan French
IPC分类号： B64C1/00 , B64G1/36 , G01C21/26 , G01C22/00
CPC分类号： B64G1/361 , G01C22/00
摘要： A vehicle (12) including a control system (18) is used for controlling vehicle attitude or angular velocity (38). The processor (24) is coupled to a star sensor or tracker (22) and a memory (30) that may include a star catalog (32), and an exclusion list (36). The exclusion list (36), a list of stars to be temporarily excluded from consideration when determining attitude or angular velocity or relative alignment of star sensors or trackers, is calculated on-board. Such a calculation prevents the necessity for a costly, periodic, ground calculation and upload of such data. By manipulating the star catalog, or sub-catalogs derived from said catalog, based upon the exclusion list (36), measurements of such excluded stars are prevented from corrupting the attitude or angular velocity or alignment estimates formulated on board.
摘要翻译：包括控制系统（18）的车辆（12）用于控制车辆姿态或角速度（38）。处理器（24）耦合到星形传感器或跟踪器（22）和可包括星形目录（32）的存储器（30）和排除列表（36）。排除列表（36），在确定姿态或角速度或星形传感器或跟踪器的相对对齐时暂时排除考虑的恒星列表。这样的计算可以防止对这些数据进行昂贵，周期性，地面计算和上传的必要性。通过根据排除列表（36）操纵从所述目录导出的星号目录或子目录，防止这些排除的星星的测量破坏了在船上制定的姿态或角速度或对准估计。

40. 发明申请

US20050049764A1 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：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。

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