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1. 发明授权

US5124925A Method for controlling east/west motion of a geostationary satellite 失效
标题翻译：控制地球卫星东/西运动的方法
公开(公告)号：US5124925A
公开(公告)日：1992-06-23
申请号：US464799
申请日：1990-01-16
申请人： Donald W. Gamble , Lisa K. White , Thomas J. Kelly , Ronald H. Bingaman
发明人： Donald W. Gamble , Lisa K. White , Thomas J. Kelly , Ronald H. Bingaman
IPC分类号： B64G1/24 , B64G1/34 , G05D1/08
CPC分类号： B64G1/24 , G05D1/0883 , B64G1/34
摘要： A method for East/West stationkeeping of a geostationary satellite maintains the osculating value of longitude from exceeding a specified deadband for a specified drift period between maneuvers. In the planning, the mean longitude, the mean drift rate and the mean eccentricity vector are calculated and then maneuvers are executed to maintain the values below a magnitude such that the osculating longitude will be within the specified deadband over a specified drift period. The target conditions are achieved through a plurality of maneuvers which initiate a period of free drift which lasts for a specified number of days. During the free-drift period, longitude remains within its deadband, and no additional maneuvers are needed or are performed. The method has the advantage that it can take into account limitations on thruster on-time by allowing for a generalized number of stationkeeping maneuvers.

2. 发明授权

US5787368A Spacecraft yaw control using only wheel speed measurements processed through a simple filter bank 失效
标题翻译：航天器的偏航控制只能通过一个简单的滤波器组进行轮速测量
公开(公告)号：US5787368A
公开(公告)日：1998-07-28
申请号：US552613
申请日：1995-11-03
申请人： Donald W. Gamble , Xenophon H. Price , Kam Kin Chan
发明人： Donald W. Gamble , Xenophon H. Price , Kam Kin Chan
IPC分类号： B64G1/24 , B64G1/28 , B64G1/32 , G05D1/08
CPC分类号： B64G1/285 , B64G1/24 , B64G1/32 , G05D1/0883
摘要： An attitude or orientation control system for spacecraft that provides for yaw axis error reduction and momentum dumping using a simple calculation involving only the momentum wheel speeds as input and which outputs two axis (roll and yaw) torque commands. The system utilizes the spacecraft 1) momentum wheels that store spacecraft momentum, 2) processing means for the calculation of control torques, and 3) torque actuators, e.g., magnetic torquers, that can provide a torque axis anywhere in the spacecraft roll/yaw plane, and involves three fundamental steps, 1) the input of the momentum wheel speed mearsurements, and 2) the calculation of the required torques, using the wheel speed measurements, and and 3) the outputting of the required torques in a form appropriate for controlling the available actuators.
摘要翻译：一种用于航天器的姿态或姿态控制系统，其使用仅涉及动量轮速度作为输入并且输出两轴（侧倾和偏航）转矩指令的简单计算来提供偏航轴误差减小和动量倾倒。该系统利用航天器1）存储航天器动量的动量轮，2）用于计算控制扭矩的处理装置，以及3）可在航天器侧倾/偏航平面上任何地方提供扭矩轴的扭矩致动器，例如磁力扳机，并涉及三个基本步骤：1）动量轮速度测量的输入，以及2）使用车轮速度测量计算所需扭矩，以及3）以适合于控制的形式输出所需扭矩可用的执行器。

3. 发明授权

US5992799A Earth based spacecraft orbit and attitude control using a look-ahead thruster selection logic and magnetic torquers 失效
标题翻译：基于地球的航天器轨道和姿态控制采用先进的推进器选择逻辑和磁力计
公开(公告)号：US5992799A
公开(公告)日：1999-11-30
申请号：US801842
申请日：1997-02-18
申请人： Donald W. Gamble , Mark D. McLaren , Marc Takahashi
发明人： Donald W. Gamble , Mark D. McLaren , Marc Takahashi
IPC分类号： B64G1/24 , B64G1/26 , B64G1/28 , B64G1/32 , B64G1/36 , G05D1/08
CPC分类号： B64G1/26 , B64G1/24 , B64G1/283 , B64G1/285 , B64G1/288 , B64G1/32 , B64G1/36 , G05D1/0883
摘要： A spacecraft ground loop controller (GLC), located on the Earth, interfaces with a satellite ground station receiving spacecraft telemetry from the downlink baseband equipment and automatically sending spacecraft commands through the command uplink baseband equipment to control the attitude of an orbiting spacecraft and achieve partial orbit control using commanded thruster firings and magnetic torquer polarity and magnitude. A cooperative approach of using all available thrusters, of both the primary and redundant strings, provides greater fuel savings.
摘要翻译：位于地球上的航天器接地回路控制器（GLC）与下行基带设备接收航天器遥测的卫星地面站接口，通过上行基带设备自动发送航天器命令，以控制轨道航天器的姿态，并实现部分轨道控制使用指令式推进器启动和磁极化极性和大小。使用所有可用的推进器，主要和冗余的字符串的合作方法提供更大的燃料节省。

4. 发明授权

US4687161A Pointing compensation system for spacecraft instruments 失效
标题翻译：飞船仪器指点补偿系统
公开(公告)号：US4687161A
公开(公告)日：1987-08-18
申请号：US802121
申请日：1985-09-30
申请人： Carl T. Plescia , Donald W. Gamble
发明人： Carl T. Plescia , Donald W. Gamble
IPC分类号： G05D1/08 , B64G1/36
CPC分类号： G05D1/0883
摘要： A closed loop system reduces pointing errors in one or more spacecraft instruments. Associated with each instrument is a electronics package (3) for commanding motion in that instrument and a pointing control system (5) for imparting motion in that instrument in response to a command (4) from the commanding package (3). Spacecraft motion compensation logic (25) compensates for instrument pointing errors caused by instrument-motion-induced spacecraft motion. Any finite number of instruments can be so compensated, by providing each pointing control system (5) and each commanding package (3), for the instruments desired to be compensated, with a link to the spacecraft motion compensation logic (25). The spacecraft motion compensation logic (25) is an electronic manifestation of the algebraic negative of a model of the dynamics of motion of the spacecraft. An example of a suitable model, and computer-simulated results, are presented.
摘要翻译：闭环系统减少了一个或多个航天器仪器中的指示误差。与每个仪器相关联的是用于在该仪器中指令运动的电子组件（3）和用于响应于来自命令包（3）的命令（4））在该仪器中传递运动的指点控制系统（5）。航天器运动补偿逻辑（25）补偿由仪器运动引起的航天器运动引起的仪器指向误差。通过提供每个指向控制系统（5）和每个命令包（3），对于希望被补偿的仪器，通过与航天器运动补偿逻辑（25）的链接，可以对任何有限数量的仪器进行补偿。航天器运动补偿逻辑（25）是航天器运动动力学模型的代数负的电子表现。提出了一个合适的模型和计算机模拟结果的例子。

5. 发明授权

US4688091A Spacecraft camera image registration 失效
标题翻译：航天器相机图像注册
公开(公告)号：US4688091A
公开(公告)日：1987-08-18
申请号：US860373
申请日：1986-05-06
申请人： Ahmed A. Kamel , Donald W. Graul , Fred N. T. Chan , Donald W. Gamble
发明人： Ahmed A. Kamel , Donald W. Graul , Fred N. T. Chan , Donald W. Gamble
IPC分类号： B64G1/66 , B64G1/22 , G01C21/20 , G01C21/24 , G01J1/42 , G03B15/00 , G03B17/00 , H04N5/232 , H04N7/01
CPC分类号： G01C21/20 , H04N5/232
摘要： A system for achieving spacecraft camera (1, 2) image registration comprises a portion external to the spacecraft and an image motion compensation system (IMCS) portion onboard the spacecraft. Within the IMCS, a computer (38) calculates an image registration compensation signal (60) which is sent to the scan control loops (84, 88, 94, 98) of the onboard cameras (1, 2). At the location external to the spacecraft, the long-term orbital and attitude perturbations on the spacecraft are modeled. Coefficients (K, A) from this model are periodically sent to the onboard computer (38) by means of a command unit (39). The coefficients (K, A) take into account observations of stars and landmarks made by the spacecraft cameras (1, 2) themselves. The computer (38) takes as inputs the updated coefficients (K, A) plus synchronization information indicating the mirror position (AZ, EL) of each of the spacecraft cameras (1, 2), operating mode, and starting and stopping status of the scan lines generated by these cameras (1, 2), and generates in response thereto the image registration compensation signal (60). The sources of periodic thermal errors on the spacecraft are discussed. The system is checked by calculating "measurement residuals", the difference between the landmark and star locations predicted at the external location and the landmark and star locations as measured by the spacecraft cameras (1, 2).
摘要翻译：用于实现航天器相机（1,2）图像配准的系统包括航天器外部的部分和飞船上的图像运动补偿系统（IMCS）部分。在IMCS内，计算机（38）计算发送到车载摄像机（1,2）的扫描控制回路（84,88,94,98）的图像配准补偿信号（60）。在航天器外部的位置，对航天器的长期轨道和姿态扰动进行了建模。来自该模型的系数（K，A）通过命令单元（39）周期性地发送到车载计算机（38）。系数（K，A）考虑到由航天器相机（1,2）自身制成的星星和地标的观测。计算机（38）将更新的系数（K，A）加上指示每个航天器相机（1,2）的镜像位置（AZ，EL）的同步信息，操作模式和起始和停止状态作为输入由这些摄像机（1,2）生成的扫描线，并且响应于此生成图像配准补偿信号（60）。讨论了航天器周期性热误差的来源。通过计算“测量残差”来检查系统，由外部位置预测的地标和星形位置之间的差异以及由航天器相机（1,2）测量的地标和星形位置。

6. 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。

7. 发明授权

US5100084A Method and apparatus for inclined orbit attitude control for momentum bias spacecraft 失效
标题翻译：用于母体偏移量的嵌入式姿态控制的方法和装置
公开(公告)号：US5100084A
公开(公告)日：1992-03-31
申请号：US579117
申请日：1990-09-07
申请人： Christopher D. Rahn , John A. Lehner , Donald W. Gamble
发明人： Christopher D. Rahn , John A. Lehner , Donald W. Gamble
IPC分类号： B64G1/24 , B64G1/26 , B64G1/28 , B64G1/36 , B64G1/38 , G05D1/08
CPC分类号： B64G1/38 , B64G1/24 , B64G1/28 , B64G1/36 , G05D1/0883 , B64G1/26 , B64G1/283 , B64G1/285
摘要： The present invention is a method and apparatus to control a pointing trajectory of an aim point with respect to one or more targets for a momentum bias spacecraft in an orbit inclined relative to an equatorial geosynchronous orbit wherein the spacecraft is provided with an onboard computer capable of using orbit information available to the spacecraft and spacecraft hardware to move the aim point according to a predetermined tracking model which may be either time-varying or invariant. The tracking model allows the controller to remove short-term nutational and long-term orbit rate dynamical disturbances, beyond simple-order sinusoidal functions having a single frequency.

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