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1. 发明授权

US5978716A Satellite imaging control system for non-repeatable error 失效
标题翻译：卫星成像控制系统不可重复的错误
公开(公告)号：US5978716A
公开(公告)日：1999-11-02
申请号：US864263
申请日：1997-05-28
申请人： Ahmed Kamel , Sun Hur-Diaz , Thomas Joseph Holmes , Donald W. Gamble
发明人： Ahmed Kamel , Sun Hur-Diaz , Thomas Joseph Holmes , Donald W. Gamble
IPC分类号： B64G1/10 , B64G1/24 , B64G1/26 , B64G1/28 , B64G1/36 , G01C21/02 , G01S19/48 , G05D1/08 , G06T1/00 , G06F17/00
CPC分类号： B64G1/361 , B64G1/365 , G01C21/025 , G05D1/0883 , B64G1/1021 , B64G1/242 , B64G1/26 , B64G1/285 , B64G1/36 , B64G1/366
摘要： An onboard star tracking system is used to provide continuous attitude and orbital position data independent of the image generating instruments. Such data is instantaneously and continually supplied to the onboard computer which translates such information into mirror position coordinates which is added to the mirror position set based on estimated data from the ground control. An error signal is generated which is used to further adjust the position of the mirror.
摘要翻译：使用车载星形跟踪系统来提供独立于图像产生装置的连续姿态和轨道位置数据。这样的数据被瞬时地且连续地提供给车载计算机，其将这些信息转换成根据来自地面控制的估计数据而被添加到设置的镜像位置的镜像位置坐标。产生用于进一步调整反射镜位置的误差信号。

2. 发明授权

US07113851B1 Practical orbit raising system and method for geosynchronous satellites 有权
标题翻译：地球同步卫星的实际轨道提升系统和方法
公开(公告)号：US07113851B1
公开(公告)日：2006-09-26
申请号：US09328911
申请日：1999-06-09
申请人： Walter Gelon , Ahmed Kamel , Darren Stratemeier , Sun Hur-Diaz
发明人： Walter Gelon , Ahmed Kamel , Darren Stratemeier , Sun Hur-Diaz
IPC分类号： G06F19/00 , G06F169/00 , G01N15/08 , B64G1/00
CPC分类号： G05D1/0883 , B64G1/007 , B64G1/242 , B64G1/26 , B64G1/405 , B64G1/406
摘要： A practical orbit raising method and system wherein a satellite quickly escapes the Van Allen radiation belts and payload mass and mission life are maximized. A satellite is launched that contains high thrust chemical propulsion thrusters, high specific impulse electric propulsion thrusters and a solar array. The satellite quickly escapes the Van Allen radiation belts by firing the high thrust chemical propulsion thrusters at apogees of intermediate orbits, starting from the transfer orbit initiated by a launch vehicle, to successively raise the perigees until the perigee clears the Van Allen radiation belts. The payload mass and mission life are maximized by firing high specific impulse electric propulsion thrusters to raise the satellite to near synchronous orbit, while steering the thrust vector and solar array to maintain the sun's illumination on the solar array. The chemical and/or electric propulsion thrusters are then fired to achieve geosynchronous orbit.
摘要翻译：一种实用的轨道提升方法和系统，其中卫星快速逃离范艾伦辐射带，有效载荷质量和使命寿命最大化。发射的卫星包含高推力化学推进推进器，高比冲量电推进推进器和太阳能阵列。卫星通过从运载火箭发射的转移轨道开始的中等轨道远地点发射高推力化学推进推进器，迅速逃离范艾伦辐射带，连续提升近地点，直到近地点清除了范艾伦辐射带。通过发射高比冲击电推进推进器将载体质量和使命寿命最大化，以将卫星提升到接近同步轨道，同时控制推力矢量和太阳能阵列以保持太阳照射在太阳能阵列上。然后对化学和/或电力推进推进器进行射击以实现地球同步轨道。

3. 发明授权

US06266584B1 Robust autonomous GPS time reference for space application 有权
标题翻译：强大的自主GPS时间参考空间应用
公开(公告)号：US06266584B1
公开(公告)日：2001-07-24
申请号：US09256712
申请日：1999-02-24
申请人： Sun Hur-Diaz , Jack Rodden , Richard A. Fuller
发明人： Sun Hur-Diaz , Jack Rodden , Richard A. Fuller
IPC分类号： G06F700
CPC分类号： G01S19/42 , G01C21/00 , G04G7/02
摘要： A receiver clock bias signal for a spacecraft in motion is is used to obtain a real-time navigation Kalman filter solution of the clock bias and provide a robust autonomous GPS time reference, even when there are less than 4 GPS satellites within the view of the receiver in the spacecraft. The Kalman filter of the spacecraft provides an accurate solution of the clock bias, with less than 4 GPS satellite signals, by means of a system which uses the knowledge of the dynamic motion of the satellite in conjunction with GPS signals for a robust estimation of time. The system provides an accurate GPS time reference by transferring timing information from an atomic reference standard (GPS) to a spacecraft in motion by directly measuring the GPS signal and without depending upon the tracking of multiple GPS satellites or a static receiver. Implementation in current aerospace qualified GPS receivers, e.g., the “GPS TENSOR™”, and known orbital dynamics are used to predict receiver position which aids in the transfer of the GPS time.
摘要翻译：用于运动中的航天器的接收机时钟偏置信号被用于获得时钟偏差的实时导航卡尔曼滤波器解，并且提供鲁棒的自主GPS时间参考，即使在视野内存在少于4个GPS卫星接收器在航天器。航天器的卡尔曼滤波器通过使用卫星的动态运动知识结合GPS信号的系统来提供具有小于4个GPS卫星信号的时钟偏差的精确解决方案，用于鲁棒的时间估计。通过直接测量GPS信号并且不依赖于多个GPS卫星或静态接收机的跟踪，将定时信息从原子参考标准（GPS）传送到运动中的航天器来提供精确的GPS时间参考。当前的航空航天合格GPS接收机（例如“GPS TENSOR TM”）和已知的轨道动力学的实施用于预测有助于GPS时间传送的接收机位置。

4. 发明授权

US6012000A Simplified onboard attitude control based on star sensing 失效
标题翻译：基于星形感测的简化车载姿态控制
公开(公告)号：US6012000A
公开(公告)日：2000-01-04
申请号：US6740
申请日：1998-01-14
申请人： Thomas Joseph Holmes , Sun Hur-Diaz , Donald Gamble , John Higham
发明人： Thomas Joseph Holmes , Sun Hur-Diaz , Donald Gamble , John Higham
IPC分类号： B64G1/26 , B64G1/28 , B64G1/32 , B64G1/36 , G05B17/02 , G05D1/08 , G05D1/00
CPC分类号： G05D1/0883 , B64G1/361 , B64G1/26 , B64G1/285 , B64G1/32 , B64G1/365 , B64G2001/245
摘要： An onboard star tracking system is used to provide continuous attitude data based on a fixed star catalog. An orbital position reference for the sensed star data is estimated from uploaded data. The attitude is calculated based solely on the star sensor data referenced to the estimated orbital position and compared to mission attitude to generate an attitude adjustment.
摘要翻译：使用车载星形跟踪系统提供基于固定星形目录的连续姿态数据。根据上传的数据估计所感测的星形数据的轨道位置参考。该姿态仅基于参考估计轨道位置的星传感器数据计算，并与任务态度进行比较以产生姿态调整。

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