公开(公告)号：US06288671B1

公开(公告)日：2001-09-11

申请号：US09557378

申请日：2000-04-25

申请人： Yeong-Wei Andy Wu ,  Umesh S. Ketkar ,  Rongsheng Li ,  Richard Y. Chiang

发明人： Yeong-Wei Andy Wu ,  Umesh S. Ketkar ,  Rongsheng Li ,  Richard Y. Chiang

IPC分类号： H04B7185

CPC分类号： G01S3/30 ,  G01S5/0247 ,  G01S19/38

摘要： Control systems and methods are provided which enhance acquisition range, transient response and offset pointing accuracy in beacon-assisted orientation of a spacecraft to a desired spacecraft attitude Adsrd. The methods receive a beacon signal with antennas that are arranged in a fixed angular relationship to thereby form an attitude error signal Serr whose magnitude is a measure of the attitude difference between a current spacecraft attitude Acrnt and the desired spacecraft attitude Adsrd. A sum power P&Sgr; that is the sum of the signal powers from the antennas is sensed and a signal modifier Smod is generated that increases with decreases in the sum power P&Sgr;. The attitude error signal Serr is then modified with a term (1+Smod) to form an enhanced attitude error signal Serrenhd. In one embodiment, the signal modifier Smod is n|Pmax−P&Sgr;|m wherein n and m are positive numbers and Pmax is the sum power P&Sgr; when the attitude error is zero.

摘要翻译： 提供了控制系统和方法，其增强了航天器信标辅助定向到期望的航天器姿态的采集范围，瞬态响应和偏移指向精度Adsrd。 该方法接收具有以固定角度关系布置的天线的信标信号，从而形成姿态误差信号Serr，其大小是当前航天器姿态Acrnt与期望的航天器姿态Adsrd之间的姿态差的度量。 检测作为来自天线的信号功率的总和的总功率PSIGMA，并且产生信号修正器Smod，其随和功率PSIGMA的减小而增加。 然后用项（1 + Smod）修改姿态误差信号Serr，以形成增强的姿态误差信号Serrenhd。 在一个实施例中，信号修正器Smod是n | Pmax-PSIGMA | m，其中n和m是正数，Pmax是姿态误差为零时的和功率PSIGMA。

公开(公告)号：US07337021B2

公开(公告)日：2008-02-26

申请号：US10397495

申请日：2003-03-26

申请人： Richard Y. Chiang ,  Che-Hang Charles Ih ,  Yeong-Wei Andy Wu

发明人： Richard Y. Chiang ,  Che-Hang Charles Ih ,  Yeong-Wei Andy Wu

IPC分类号： G05B13/02

CPC分类号： G05B9/03

摘要： A method, apparatus, article of manufacture, and a memory structure for designing a robust controller. The method comprises the steps of determining a plant model G of the system dynamics; bounding system dynamics unmodeled by the plant model G of the system dynamics by a weighting function W; applying a transform to an augmented plant model T having the plant model G and the weighting function W; defining a controller {tilde over (F)} from the transformed plant model T; and applying an inverse of the transform to the controller {tilde over (F)} defined from the transformed plant model and the weighting function W to generate the robust controller F.

摘要翻译： 用于设计鲁棒控制器的方法，装置，制品和存储器结构。 该方法包括确定系统动力学的植物模型G的步骤; 未通过加权函数W由系统动力学的工厂模型G建模的边界系统动力学; 对具有植物模型G和加权函数W的增强植物模型T应用变换; 从变换的植物模型T中定义控制器F; 以及将变换的反相应用于从变换的植物模型和加权函数W定义的控制器F，以生成鲁棒控制器F.

公开(公告)号：US06988051B2

公开(公告)日：2006-01-17

申请号：US10713340

申请日：2003-11-14

申请人： Richard Y. Chiang

发明人： Richard Y. Chiang

IPC分类号： G06F101/14

CPC分类号： G05D1/0883

摘要： A method of analysis to process jitter information by using a window average statistic model to determine a pointing accuracy. The pointing accuracy ultimately determines whether or not a mission can proceed. The process includes the following: collect a signal, process the signal to produce data, insert the data from the signal into a statistical model to produce statistics, compile the statistics using the statistics model to produce a probability density function, integrate the probability density function to produce a probability distribution function, determine a pointing accuracy from the probability distribution function.

摘要翻译： 一种通过使用窗口平均统计模型来确定指向精度来处理抖动信息的分析方法。 指点精度最终决定了任务是否能够进行。 该过程包括：收集信号，处理信号以产生数据，将信号中的数据插入统计模型进行统计，使用统计模型编制统计量，产生概率密度函数，整合概率密度函数 产生概率分布函数，从概率分布函数确定指向精度。

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。

公开(公告)号：US08131409B2

公开(公告)日：2012-03-06

申请号：US12635426

申请日：2009-12-10

申请人： Tung-Ching Tsao ,  Richard Y. Chiang

发明人： Tung-Ching Tsao ,  Richard Y. Chiang

IPC分类号： G05D1/08 ,  B64G1/10

CPC分类号： B64G1/242 ,  B64G1/24 ,  B64G1/281 ,  B64G1/283 ,  B64G1/44 ,  G05D1/0883

摘要： A system and method for gyroless transfer orbit sun acquisition using only wing current measurement feedback is disclosed. With this system and method, a spacecraft is able to maneuver itself to orient its solar panel to its maximum solar exposure spinning attitude. The disclosed system and method involve controlling a spacecraft maneuver using only the solar wing current feedback as the sole closed-loop feedback sensor for attitude control. A spin controller is used for controlling the spacecraft spin axis orientation and spin rate. The spin controller commands the spacecraft spin axis orientation to align with an inertial fixed-direction and to rotate at a specified spin rate by using a momentum vector. In addition, a method for estimating spacecraft body angular rate and spacecraft attitude is disclosed. This method uses a combination of solar array current and spacecraft momentum as the cost function with solar wing current feedback as the only closed-loop feedback sensor.

摘要翻译： 公开了仅使用翼电流测量反馈的无陀螺转移轨道太阳采集的系统和方法。 利用这种系统和方法，航天器能够自动地将其太阳能电池板定向到其最大的太阳能曝光旋转姿态。 所公开的系统和方法包括仅使用太阳能翼电流反馈来控制航天器操纵作为姿态控制的唯一闭环反馈传感器。 旋转控制器用于控制航天器旋转轴取向和旋转速率。 旋转控制器命令航天器旋转轴取向与惯性固定方向对准，并通过使用动量向量以指定的旋转速度旋转。 另外，公开了一种用于估计航天器身体角速度和航天器姿态的方法。 该方法采用太阳能阵列电流和航天器动量的组合作为唯一的闭环反馈传感器的太阳能翼电流反馈的成本函数。

公开(公告)号：US08380370B2

公开(公告)日：2013-02-19

申请号：US12487187

申请日：2009-06-18

申请人： Dan Y. Liu ,  Richard Y. Chiang

发明人： Dan Y. Liu ,  Richard Y. Chiang

IPC分类号： B64G1/24

CPC分类号： B64G1/26 ,  B64G1/283 ,  B64G1/36 ,  B64G1/361 ,  B64G2001/245 ,  G05D1/0883

摘要： A system and a method for commanding a spacecraft to perform a three-axis maneuver purely based on “position” (i.e., attitude) measurements. Using an “inertial gimbal concept”, a set of formulae are derived that can map a set of “inertial” motion to the spacecraft body frame based on position information so that the spacecraft can perform/follow according to the desired inertial position maneuvers commands. Also, the system and method disclosed herein employ an intrusion steering law to protect the spacecraft from acquisition failure when a long sensor intrusion occurs.

摘要翻译： 一种用于命令航天器完全基于位置（即姿态）测量进行三轴机动的系统和方法。 使用惯性万向节概念，导出一组公式，其可以基于位置信息将一组惯性运动映射到航天器身体框架，使得航天器可以根据期望的惯性姿态操纵命令执行/跟随。 此外，本文公开的系统和方法采用入侵转向规律来保护航天器在发生长传感器入侵时不会获取故障。

公开(公告)号：US20110024571A1

公开(公告)日：2011-02-03

申请号：US12635426

申请日：2009-12-10

申请人： Tung-Ching Tsao ,  Richard Y. Chiang

发明人： Tung-Ching Tsao ,  Richard Y. Chiang

IPC分类号： B64G1/36

CPC分类号： B64G1/242 ,  B64G1/24 ,  B64G1/281 ,  B64G1/283 ,  B64G1/44 ,  G05D1/0883

摘要： A system and method for gyroless transfer orbit sun acquisition using only wing current measurement feedback is disclosed. With this system and method, a spacecraft is able to maneuver itself to orient its solar panel to its maximum solar exposure spinning attitude. The disclosed system and method involve controlling a spacecraft maneuver using only the solar wing current feedback as the sole closed-loop feedback sensor for attitude control. A spin controller is used for controlling the spacecraft spin axis orientation and spin rate. The spin controller commands the spacecraft spin axis orientation to align with an inertial fixed-direction and to rotate at a specified spin rate by using a momentum vector. In addition, a method for estimating spacecraft body angular rate and spacecraft attitude is disclosed. This method uses a combination of solar array current and spacecraft momentum as the cost function with solar wing current feedback as the only closed-loop feedback sensor.

摘要翻译： 公开了仅使用翼电流测量反馈的无陀螺转移轨道太阳采集的系统和方法。 利用这种系统和方法，航天器能够自动地将其太阳能电池板定向到其最大的太阳能曝光旋转姿态。 所公开的系统和方法包括仅使用太阳能翼电流反馈来控制航天器操纵作为姿态控制的唯一闭环反馈传感器。 旋转控制器用于控制航天器旋转轴取向和旋转速率。 旋转控制器命令航天器旋转轴取向与惯性固定方向对准，并通过使用动量向量以指定的旋转速度旋转。 另外，公开了一种用于估计航天器身体角速度和航天器姿态的方法。 该方法采用太阳能阵列电流和航天器动量的组合作为唯一的闭环反馈传感器的太阳能翼电流反馈的成本函数。

公开(公告)号：US20100193641A1

公开(公告)日：2010-08-05

申请号：US12487187

申请日：2009-06-18

申请人： Dan Y. Liu ,  Richard Y. Chiang

发明人： Dan Y. Liu ,  Richard Y. Chiang

IPC分类号： B64G1/36 ,  B64G1/26 ,  B64G1/24

CPC分类号： B64G1/26 ,  B64G1/283 ,  B64G1/36 ,  B64G1/361 ,  B64G2001/245 ,  G05D1/0883

摘要： A system and a method for commanding a spacecraft to perform a three-axis maneuver purely based on “position” (i.e., attitude) measurements. Using an “inertial gimbal concept”, a set of formulae are derived that can map a set of “inertial” motion to the spacecraft body frame based on position information so that the spacecraft can perform/follow according to the desired inertial position maneuvers commands. Also, the system and method disclosed herein employ an intrusion steering law to protect the spacecraft from acquisition failure when a long sensor intrusion occurs.

摘要翻译： 用于命令航天器完全基于“位置”（即姿态）测量执行三轴机动的系统和方法。 使用“惯性万向节概念”，导出一组公式，其可以基于位置信息将一组“惯性”运动映射到航天器身体框架，使得航天器可以根据期望的惯性姿态操纵命令执行/跟随。 此外，本文公开的系统和方法采用入侵转向规律来保护航天器在发生长传感器入侵时不会获取故障。

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。

公开(公告)号：US06980893B2

公开(公告)日：2005-12-27

申请号：US10719628

申请日：2003-11-21

申请人： Richard Y. Chiang

发明人： Richard Y. Chiang

IPC分类号： B64G1/24 ,  G06F7/00 ,  G06F19/00

CPC分类号： B64G1/24

摘要： This invention introduces innovative filtering techniques to recover the instability phase margin loss due to time delay induced from a throughput shortage problem of a spacecraft central processor (SCP). This invention relates to digital control systems and, more particularly, to a phase recovery filtering technique to alleviate spacecraft central computer processor or (SCP) throughput shortages. This filtering technique recovers the unstable phase margin loss due to the time delay caused by the SCP throughput problem. The filtering techniques may be accomplished without schedule slip or extra cost to the project.

摘要翻译： 本发明引入创新的过滤技术，以恢复由于航天器中央处理器（SCP）的吞吐量不足问题而引起的时间延迟的不稳定相位裕度损失。 本发明涉及数字控制系统，更具体地说，涉及一种用于减轻航天器中央计算机处理器或（SCP）吞吐量短缺的相位恢复滤波技术。 该过滤技术由于SCP吞吐量问题引起的时间延迟，恢复了不稳定的相位裕度损失。 过滤技术可以在没有计划滑移或项目额外成本的情况下完成。