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1. 发明授权

US08213803B2 Method and system for laser based communication 有权
标题翻译：基于激光的通信方法与系统
公开(公告)号：US08213803B2
公开(公告)日：2012-07-03
申请号：US12128857
申请日：2008-05-29
申请人： Yeong-wei A. Wu , Ketao Liu
发明人： Yeong-wei A. Wu , Ketao Liu
IPC分类号： H04B10/00
CPC分类号： H04B10/118
摘要： Method and system for determining a point-ahead angle from a first spacecraft to a second spacecraft, each spacecraft having a laser communication (“lasercom”) terminal is provided If ephemeris data regarding the second spacecraft is unavailable to the first spacecraft while the second spacecraft is mobile, (a) obtaining attitude information regarding the first spacecraft; and (b) obtaining gimbal offload commands from a fast steering mirror and a first spacecraft telescope subsystem of the first spacecraft; wherein a point-ahead determination module receives the attitude information and the gimbal offload commands; and determining an estimate of the point-ahead angle from the first spacecraft to the second spacecraft based on the attitude information and the gimbal offload commands.
摘要翻译：用于确定从第一航天器到第二航天器的点前进角度的方法和系统，提供具有激光通信（“激光通信”）终端的每个航天器如果关于第二航天器的星历数据对于第一航天器是不可用的，而第二航天器是移动的，（a）获得关于第一航天器的态度信息; 和（b）从第一航天器的快速转向镜和第一航天器望远镜子系统获得万向节卸载命令; 其中，提前确定模块接收姿态信息和万向节卸载命令; 以及基于姿态信息和万向节卸载命令确定从第一航天器到第二航天器的点前进角度的估计。

2. 发明授权

US08000896B2 Scale factor calibration and compensation for angular position resolver 有权
标题翻译：角度位移解算器的比例因子校准和补偿
公开(公告)号：US08000896B2
公开(公告)日：2011-08-16
申请号：US12019513
申请日：2008-01-24
申请人： Ketao Liu , Yeong-Wei A. Wu , Jeffrey L. Lee
发明人： Ketao Liu , Yeong-Wei A. Wu , Jeffrey L. Lee
IPC分类号： G01C21/00
CPC分类号： G01D5/208 , G01D3/02
摘要： In accordance with an embodiment of the present invention, a resolver system has at least one resolver and at least one amplifier in electrical communication with each resolver. A reference circuit is in electrical communication with the amplifiers. The reference circuit provides reference signals to the amplifiers. A non-linearity calibration and compensation circuit in communication with each amplifier uses the amplified reference signals to provide scale factors, so as to enhance a precision of the resolver system.
摘要翻译：根据本发明的实施例，旋转变压器系统具有至少一个分解器和至少一个与每个旋转变压器电连通的放大器。参考电路与放大器电连通。参考电路为放大器提供参考信号。与每个放大器通信的非线性校准和补偿电路使用放大的参考信号来提供比例因子，以提高旋转变压器系统的精度。

3. 发明申请

US20090324236A1 METHOD AND SYSTEM FOR LASER BASED COMMUNICATION 有权
标题翻译：用于激光通信的方法和系统
公开(公告)号：US20090324236A1
公开(公告)日：2009-12-31
申请号：US12128857
申请日：2008-05-29
申请人： Yeong-wei A. Wu , Ketao Liu
发明人： Yeong-wei A. Wu , Ketao Liu
IPC分类号： H04B10/00
CPC分类号： H04B10/118
摘要： Method and system for determining a point-ahead angle from a first spacecraft to a second spacecraft, each spacecraft having a laser communication (“lasercom”) terminal is provided If ephemeris data regarding the second spacecraft is unavailable to the first spacecraft while the second spacecraft is mobile, (a) obtaining attitude information regarding the first spacecraft; and (b) obtaining gimbal offload commands from a fast steering mirror and a first spacecraft telescope subsystem of the first spacecraft; wherein a point-ahead determination module receives the attitude information and the gimbal offload commands; and determining an estimate of the point-ahead angle from the first spacecraft to the second spacecraft based on the attitude information and the gimbal offload commands.
摘要翻译：用于确定从第一航天器到第二航天器的点前进角度的方法和系统，提供具有激光通信（“激光通信”）终端的每个航天器如果关于第二航天器的星历数据对于第一航天器是不可用的，而第二航天器是移动的，（a）获得关于第一航天器的态度信息; 和（b）从第一航天器的快速转向镜和第一航天器望远镜子系统获得万向节卸载命令; 其中，提前确定模块接收姿态信息和万向节卸载命令; 以及基于姿态信息和万向节卸载命令确定从第一航天器到第二航天器的点前进角度的估计。

4. 发明授权

US07561968B2 Scale factor calibration and compensation for angular position resolver 有权
标题翻译：角度位移解算器的比例因子校准和补偿
公开(公告)号：US07561968B2
公开(公告)日：2009-07-14
申请号：US10965441
申请日：2004-10-13
申请人： Ketao Liu , Yeong-Wei A. Wu , Jeffrey L. Lee
发明人： Ketao Liu , Yeong-Wei A. Wu , Jeffrey L. Lee
IPC分类号： G01C21/00
CPC分类号： G01D5/208 , G01D3/02
摘要： In accordance with an embodiment of the present invention, a resolver system has at least one resolver and at least one amplifier in electrical communication with each resolver. A reference circuit is in electrical communication with the amplifiers. The reference circuit provides reference signals to the amplifiers. A non-linearity calibration and compensation circuit in communication with each amplifier uses the amplified reference signals to provide scale factors, so as to enhance a precision of the resolver system.
摘要翻译：根据本发明的实施例，旋转变压器系统具有至少一个分解器和至少一个与每个旋转变压器电连通的放大器。参考电路与放大器电连通。参考电路为放大器提供参考信号。与每个放大器通信的非线性校准和补偿电路使用放大的参考信号来提供比例因子，以提高旋转变压器系统的精度。

5. 发明授权

US06825806B2 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：US06825806B2
公开(公告)日：2004-11-30
申请号：US10162465
申请日：2002-06-03
申请人： Ketao Liu , Richard Fowell , Yeong-Wei A. Wu , Rongsheng Li
发明人： Ketao Liu , Richard Fowell , Yeong-Wei A. Wu , Rongsheng Li
IPC分类号： H01Q300
CPC分类号： H01Q3/005
摘要： Methods and structures are provided for reducing pointing errors &zgr; 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 &bgr; and are transmitted to overlap on a ground-based receiving terminal which has a known terminal location &lgr; and which measures received signal strengths &agr;. Pointing errors &zgr; of the transmit beams are then determined from the estimated pointing attitudes &bgr;, the terminal location &lgr; and the signal strengths &agr; and the pointing errors &zgr; are subsequently reduced by revising the pointing attitudes &bgr;. 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。

6. 发明授权

US07877173B2 Method and apparatus for determining a satellite attitude using crosslink reference signals 有权
标题翻译：使用交联参考信号确定卫星姿态的方法和装置
公开(公告)号：US07877173B2
公开(公告)日：2011-01-25
申请号：US11825207
申请日：2007-07-05
申请人： Ketao Liu , Yeong-Wei A. Wu
发明人： Ketao Liu , Yeong-Wei A. Wu
IPC分类号： G05D1/00
CPC分类号： G01S5/0247 , B64G1/1085 , B64G1/24 , B64G1/285 , B64G1/32 , B64G1/361 , B64G1/363 , B64G1/365 , B64G1/366 , B64G1/407 , B64G1/44 , B64G1/66 , B64G2001/245
摘要： A method and apparatus for determining the attitude of a satellite using crosslink information is disclosed. The method and apparatus integrates data from the crosslinks with data available from other sources including, for example, star sensors, inertial sensors, and earth limb sensors to derive an accurate estimate of the satellite attitude, even in harsh nuclear environments.
摘要翻译：公开了一种使用交联信息确定卫星姿态的方法和装置。该方法和装置将来自交联的数据与来自其他来源的数据（例如，星形传感器，惯性传感器和地球肢体传感器）集成，以得到卫星姿态的准确估计，即使在恶劣的核环境中。

7. 发明申请

US20090012662A1 Method and apparatus for determining a satellite attitude using crosslink reference signals 有权
标题翻译：使用交联参考信号确定卫星姿态的方法和装置
公开(公告)号：US20090012662A1
公开(公告)日：2009-01-08
申请号：US11825207
申请日：2007-07-05
申请人： Ketao Liu , Yeong-Wei A. Wu
发明人： Ketao Liu , Yeong-Wei A. Wu
IPC分类号： G01C21/24
CPC分类号： G01S5/0247 , B64G1/1085 , B64G1/24 , B64G1/285 , B64G1/32 , B64G1/361 , B64G1/363 , B64G1/365 , B64G1/366 , B64G1/407 , B64G1/44 , B64G1/66 , B64G2001/245
摘要： A method and apparatus for determining the attitude of a satellite using crosslink information is disclosed. The method and apparatus integrates data from the crosslinks with data available from other sources including, for example, star sensors, inertial sensors, and earth limb sensors to derive an accurate estimate of the satellite attitude, even in harsh nuclear environments.
摘要翻译：公开了一种使用交联信息确定卫星姿态的方法和装置。该方法和装置将来自交联的数据与来自其他来源的数据（例如，星形传感器，惯性传感器和地球肢体传感器）集成，以得到卫星姿态的准确估计，即使在恶劣的核环境中。

8. 发明申请

US20080129242A1 SCALE FACTOR CALIBRATION AND COMPENSATION FOR ANGULAR POSITION RESOLVER 有权
标题翻译：标准因子校准和补偿用于角位置分辨率
公开(公告)号：US20080129242A1
公开(公告)日：2008-06-05
申请号：US12019513
申请日：2008-01-24
申请人： Ketao Liu , Yeong-Wei A. Wu , Jeffrey L. Lee
发明人： Ketao Liu , Yeong-Wei A. Wu , Jeffrey L. Lee
IPC分类号： G05B19/31
CPC分类号： G01D5/208 , G01D3/02
摘要： In accordance with an embodiment of the present invention, a resolver system has at least one resolver and at least one amplifier in electrical communication with each resolver. A reference circuit is in electrical communication with the amplifiers. The reference circuit provides reference signals to the amplifiers. A non-linearity calibration and compensation circuit in communication with each amplifier uses the amplified reference signals to provide scale factors, so as to enhance a precision of the resolver system.
摘要翻译：根据本发明的实施例，旋转变压器系统具有至少一个分解器和至少一个与每个旋转变压器电连通的放大器。参考电路与放大器电连通。参考电路为放大器提供参考信号。与每个放大器通信的非线性校准和补偿电路使用放大的参考信号来提供比例因子，以提高旋转变压器系统的精度。

9. 发明授权

US07547870B2 Precision spacecraft payload platforms 有权
标题翻译：精密航天器有效负载平台
公开(公告)号：US07547870B2
公开(公告)日：2009-06-16
申请号：US11400874
申请日：2006-04-10
申请人： Ketao Liu , Gregory S. Becker , Peter J. Sedivec , Douglas Bender
发明人： Ketao Liu , Gregory S. Becker , Peter J. Sedivec , Douglas Bender
IPC分类号： G01C21/02 , G01N21/86 , G01B11/26 , B64G1/36
CPC分类号： G01S5/163 , G01B11/272
摘要： One or more fixed-orientation fanned laser beams and one or more displacement measurement devices to precisely measure the orientation of a payload platform are disclosed in a metrology system and method. The measurement devices may be distributed at locations across a payload platform such that displacement changes of these devices can be used to accurately determine platform pointing. Laser beam transmitters may be fixed in the same reference block to which a spacecraft attitude sensor is mounted. Fanned laser beams are transmitted from these sources to the measurement devices so that their displacements can be determined with respect to the plane of the fanned beams and thereby with respect to the spacecraft attitude sensor. Only a small number of fixed laser beams are needed to achieve precision measurements at a reduced cost, weight and power, and with increased system reliability and simplified system integration.
摘要翻译：计量系统和方法中公开了一种或多种固定方向的扇形激光束和一个或多个位移测量装置来精确地测量有效负载平台的取向。测量设备可以分布在有效负载平台上的位置，使得这些设备的位移变化可以用于准确地确定平台指向。激光束发射器可以固定在安装有航天器姿态传感器的相同参考块中。扇形激光束从这些源传输到测量装置，使得它们的位移可以相对于扇形光束的平面，从而相对于航天器姿态传感器确定。只需要少量的固定激光束，以降低成本，重量和功率，以及更高的系统可靠性和简化的系统集成来实现精密测量。

10. 发明申请

US20060054745A1 Thermal deformation determination for payload pointing using space-based beacon 有权
标题翻译：使用基于空间的信标的有效载荷指向的热变形确定
公开(公告)号：US20060054745A1
公开(公告)日：2006-03-16
申请号：US10929844
申请日：2004-08-30
申请人： Leonard Plotke , Ketao Liu
发明人： Leonard Plotke , Ketao Liu
IPC分类号： B64G1/36
CPC分类号： B64G1/24 , B64G1/36
摘要： A system and associated method for compensating for thermal deformation of a spaced-based structure having a spacecraft payload. The system including a beacon source coupled to a first spacecraft for transmitting a first signal and a beacon sensor coupled to a second spacecraft for receiving the first signal and providing measurement data derived from the first signal. At least one attitude sensing device is coupled to the second spacecraft for determining estimated spacecraft attitude data for the second spacecraft. A processor on the second spacecraft is configured to process ephemeris data of the first and second spacecraft, beacon measurement data, estimated spacecraft attitude data, and gimbal angular position data to estimate spacecraft structural deformation.
摘要翻译：一种用于补偿具有航天器有效载荷的基于间隔的结构的热变形的系统和相关方法。该系统包括耦合到第一航天器的用于发射第一信号的信标源和耦合到第二航天器的信标传感器，用于接收第一信号并提供从第一信号导出的测量数据。至少一个姿态感测装置耦合到第二航天器，用于确定第二航天器的估计的航天器姿态数据。第二航天器上的处理器被配置为处理第一和第二航天器的星历数据，信标测量数据，估计的航天器姿态数据和万向角位置数据以估计航天器结构变形。

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