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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

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）。

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