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1. 发明授权

US08186626B1 GPS based orbit determination of a spacecraft in the presence of thruster maneuvers 有权
标题翻译：在推进器机动的情况下，基于GPS的轨道确定航天器
公开(公告)号：US08186626B1
公开(公告)日：2012-05-29
申请号：US12486989
申请日：2009-06-18
申请人： Ketao Liu , Qinghong W. Wang , Douglas H. Hein
发明人： Ketao Liu , Qinghong W. Wang , Douglas H. Hein
IPC分类号： B64G1/10
CPC分类号： B64G1/24 , B64G1/242 , B64G1/26 , B64G1/283 , B64G1/286 , B64G1/36
摘要： A system for determining and controlling an orbit of a spacecraft may include a GPS receiver mounted to the spacecraft to receive GPS information from a plurality of GPS satellites visible to the GPS receiver for determining a position of the spacecraft relative to a reference coordinate system. The system may also include a filter configuration control module to sense a thruster maneuver operation to adjust the orbit of the spacecraft. The system may also include an orbit determination filter to determine at least one of a spacecraft position, velocity, and residue acceleration based on the GPS information and information from the filter configuration control module related to the thruster maneuver operation.
摘要翻译：用于确定和控制航天器的轨道的系统可以包括安装到航天器的GPS接收器，以从GPS接收器可见的多个GPS卫星接收GPS信息，以确定航天器相对于参考坐标系的位置。该系统还可以包括用于感测推进器操纵操作以调整航天器的轨道的过滤器配置控制模块。该系统还可以包括轨道确定滤波器，用于基于GPS信息和来自与推进器机动操作相关的过滤器配置控制模块的信息来确定航天器位置，速度和残余加速度中的至少一个。

2. 发明授权

US08355635B1 Gyro-aided pointing control for laser communications 有权
标题翻译：用于激光通信的陀螺辅助指向控制
公开(公告)号：US08355635B1
公开(公告)日：2013-01-15
申请号：US12551787
申请日：2009-09-01
申请人： Ketao Liu , Qinghong W. Wang
发明人： Ketao Liu , Qinghong W. Wang
IPC分类号： H04B10/00 , G06F19/00 , G01S5/14
CPC分类号： H04B10/118
摘要： A method for pointing control of a laser communication terminal on a spacecraft may include measuring a line-of-sight (LOS) error of the laser communication terminal. The method may also include estimating a LOS error of the laser communication terminal based on measurements from a spacecraft gyro and a gimbal gyro onboard the spacecraft. The method may further include switching from a LOS error measurement feedback to a LOS error estimate feedback to control pointing of the laser communication terminal during a power fade condition.
摘要翻译：用于将激光通信终端指向控制的方法可以包括测量激光通信终端的视线（LOS）误差。该方法还可以包括基于航天器陀螺仪和航天器上的万向陀螺仪的测量来估计激光通信终端的LOS误差。该方法还可以包括从LOS误差测量反馈切换到LOS误差估计反馈以控制在衰落状态期间激光通信终端的指向。

3. 发明授权

US08620496B2 Systems and method of controlling a spacecraft using attitude sensors 有权
标题翻译：使用姿态传感器控制航天器的系统和方法
公开(公告)号：US08620496B2
公开(公告)日：2013-12-31
申请号：US12178440
申请日：2008-07-23
申请人： Dan Y. Liu , Qinghong W. Wang , Richard Y. Chiang
发明人： Dan Y. Liu , Qinghong W. Wang , Richard Y. Chiang
IPC分类号： B64G1/38 , B64G1/28
CPC分类号： B64G1/281 , B64G1/283 , B64G1/285 , B64G1/286 , B64G1/361 , B64G1/363 , B64G1/365 , B64G1/366 , B64G1/38 , G05D1/0883
摘要： A system for damping nutation and removing wobble of a spacecraft spinning about a given axis is provided. The system includes a sensor configured to determine three dimensional attitude measurements of the spacecraft, a processor operatively coupled to the sensor and configured to execute a process that facilitates aligning the spin axis with a spacecraft momentum vector. The processor, when executing the process, is programmed to receive spacecraft attitude data from the sensor, determine a torque command using the received attitude data, and control a momentum storage actuator on the spacecraft using the determined torque command such that an angular deviation about the given axis is reduced.
摘要翻译：提供了一种用于阻尼章动和消除围绕给定轴线旋转的航天器摆动的系统。该系统包括被配置为确定航天器的三维姿态测量的传感器，可操作地耦合到传感器并被配置为执行有利于使旋转轴与航天器动量向量对准的过程的处理器。处理器在执行该过程时被编程为从传感器接收航天器姿态数据，使用接收的姿态数据确定扭矩指令，并且使用所确定的扭矩命令来控制航天器上的动量存储致动器，使得围绕给定轴减少。

4. 发明授权

US6062512A Wobble and nutation control, and spin stabilization for a spacecraft using momentum conserving devices 失效
标题翻译：摇摆和章动控制，以及使用动量守恒装置的航天器的自旋稳定
公开(公告)号：US6062512A
公开(公告)日：2000-05-16
申请号：US921752
申请日：1997-08-27
申请人： Qinghong W. Wang , Michael F. Barsky
发明人： Qinghong W. Wang , Michael F. Barsky
IPC分类号： B64G1/28 , B64G1/36 , B64G1/38
CPC分类号： B64G1/283 , B64G1/281 , B64G1/285 , B64G1/36 , B64G1/38
摘要： A method of damping nutation and removing wobble of a spacecraft provided with first and second momentum sources having linearly independent momentum components in the plane transverse to the given axis. The method includes sensing angular velocities of the spacecraft along orthogonal first and second axes in the transverse plane, and generating velocity signals representative of the angular velocities. The velocity signals are processed to form control signals representative of desired torques for driving the momentum sources. The desired torques have a first additive component proportional to the angular velocities for removing the wobble and a second additive component proportional to the first derivatives of the angular velocities for damping the nutation.
摘要翻译：一种阻尼章动和去除摆放在具有在垂直于给定轴线的平面中的具有线性独立的动量分量的第一和第二动量源的航天器的摆动的方法。该方法包括：沿横向平面中的正交第一和第二轴检测航天器的角速度，以及产生代表角速度的速度信号。处理速度信号以形成表示用于驱动动量源的期望转矩的控制信号。期望的扭矩具有与用于移除摆动的角速度成比例的第一添加剂组分和与用于阻尼章动的角速度的一阶导数成比例的第二添加剂组分。

5. 发明授权

US08321076B2 On-line inertia estimation for use in controlling an aerospace vehicle 有权
标题翻译：用于控制航空航天车辆的在线惯性估计
公开(公告)号：US08321076B2
公开(公告)日：2012-11-27
申请号：US12641718
申请日：2009-12-18
申请人： Manu Sharma , Qinghong W. Wang
发明人： Manu Sharma , Qinghong W. Wang
IPC分类号： B64G1/28 , B64G1/36 , B64G1/38
CPC分类号： B64G1/28 , B64G1/283 , B64G1/285 , B64G1/36
摘要： A system for controlling an aerospace vehicle using on-line inertia estimation may include an attitude sensor to measure an attitude of the aerospace vehicle. The system may also include a processor on board the aerospace vehicle. An inertia estimator operable on the processor may generate an on-line inertia estimate of the aerospace vehicle. A rate and attitude estimator operable on the processor may determine an angular position and angular velocity of the aerospace vehicle using the attitude measurement of the aerospace vehicle and the on-line inertia estimate for controlling movement and orientation of the aerospace vehicle without any rates of rotation of the aerospace vehicle being required.
摘要翻译：使用在线惯性估计来控制航空航天车辆的系统可以包括用于测量航空航天器的姿态的姿态传感器。该系统还可以包括航空航天车辆上的处理器。可在处理器上操作的惯性估计器可以产生航空航天车辆的在线惯性估计。在处理器上可操作的速率和姿态估计器可以使用航空航天车辆的姿态测量值确定航空航天车辆的角度位置和角速度，以及用于控制航空航天车辆的运动和取向的在线惯性估计，而没有任何转速的航空航天车辆。

6. 发明申请

US20100019092A1 SYSTEMS AND METHOD OF CONTROLLING A SPACECRAFT USING ATTITUDE SENSORS 有权
标题翻译：使用姿态传感器控制空间的系统和方法
公开(公告)号：US20100019092A1
公开(公告)日：2010-01-28
申请号：US12178440
申请日：2008-07-23
申请人： Dan Y. Liu , Qinghong W. Wang , Richard Y. Chiang
发明人： Dan Y. Liu , Qinghong W. Wang , Richard Y. Chiang
IPC分类号： B64G1/38
CPC分类号： B64G1/281 , B64G1/283 , B64G1/285 , B64G1/286 , B64G1/361 , B64G1/363 , B64G1/365 , B64G1/366 , B64G1/38 , G05D1/0883
摘要： A system for damping nutation and removing wobble of a spacecraft spinning about a given axis is provided. She system includes a sensor configured to determine three dimensional attitude measurements of the spacecraft, a processor operatively coupled to the sensor and configured to execute a process that facilitates aligning the spin axis with a spacecraft momentum vector. The processor, when executing the process, is programmed to receive spacecraft attitude data from the sensor, determine a torque command using the received attitude data, and control a momentum storage actuator on the spacecraft using the determined torque command such that an angular deviation about the given axis is reduced.
摘要翻译：提供了一种用于阻尼章动和消除围绕给定轴线旋转的航天器摆动的系统。她的系统包括被配置为确定航天器的三维姿态测量的传感器，可操作地耦合到传感器并被配置为执行便于将旋转轴与航天器动量向量对准的过程的处理器。处理器在执行该过程时被编程为从传感器接收航天器姿态数据，使用接收的姿态数据确定扭矩指令，并且使用所确定的扭矩命令来控制航天器上的动量存储致动器，使得围绕给定轴减少。

7. 发明授权

US06860451B1 Spacecraft spin axis reorientation method 有权
标题翻译：航天器旋转轴重新定向方法
公开(公告)号：US06860451B1
公开(公告)日：2005-03-01
申请号：US10719329
申请日：2003-11-21
申请人： Qinghong W. Wang
发明人： Qinghong W. Wang
IPC分类号： B64G1/24 , B64G1/26 , B64G1/28
CPC分类号： B64G1/281 , B64G1/24 , B64G1/26 , B64G1/283
摘要： A reorientation controller for a satellite includes a slew rate command generator that generates a slew rate command signal ({right arrow over (ω)}r—cmd) in response to an attitude error signal. The attitude error signal corresponds to the difference between an initial attitude and a target attitude. The slew rate command generator may introduce a phase lead (θL) into the slew rate command signal ({right arrow over (ω)}r—cmd). The controller may perform a spin phase synchronization when the target attitude is unsynchronized in spin phase with the initial attitude. The satellite may perform a reorientation maneuver in response to the slew rate command signal ({right arrow over (ω)}r—cmd).
摘要翻译：用于卫星的重新定向控制器包括：压摆率命令发生器，其响应于姿态误差信号产生转换速率命令信号（{右箭头（ω）} r-cmd）。姿态误差信号对应于初始姿态与目标姿态之间的差异。转换速率命令发生器可以将相位引线（thetaL）引入转换速率命令信号（{右箭头（omega）} r-cmd）。当目标态度与初始姿态的自旋阶段不同步时，控制器可以执行自旋相位同步。卫星可以响应于转换速率命令信号（{right arrow over（omega）} r-cmd）执行重新定向机动。

8. 发明授权

US6032903A Cooperative control structures and methods for satellite spin axis control 失效
标题翻译：卫星旋转轴控制的协同控制结构和方法
公开(公告)号：US6032903A
公开(公告)日：2000-03-07
申请号：US22991
申请日：1998-02-12
申请人： Richard A. Fowell , Qinghong W. Wang
发明人： Richard A. Fowell , Qinghong W. Wang
IPC分类号： B64G1/24 , B64G1/26 , B64G1/28
CPC分类号： B64G1/28 , B64G1/24 , B64G1/26 , B64G1/281 , B64G1/283 , B64G1/285 , B64G1/288 , B64G2001/245
摘要： Structures and methods are provided to effect satellite maneuvers in the presence of disturbance torques with enhanced fuel efficiency. A thruster control loop is combined with a wheel control loop in which the wheels respond to an estimate of the disturbance torques (e.g., an angular acceleration estimate, a thruster torque command or a filtered thruster torque command) to create a counteracting gyroscopic torque. Simulations of the invention's methods have shown they have the authority of all-thruster control systems and fuel efficiency that rivals that that of all-wheel control systems.
摘要翻译：提供了结构和方法，以在存在具有提高的燃料效率的干扰转矩的情况下实现卫星操纵。推进器控制回路与车轮控制回路相结合，其中车轮对干扰转矩（例如，角加速度估计，推进器转矩指令或滤波推进器转矩指令）的估计作出响应，以产生抵消的陀螺转矩。本发明方法的仿真表明，它们具有全推进器控制系统和燃油效率的权威，与全轮控制系统相当。

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