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31. 发明授权

US06298288B1 Autonomous gyro scale factor and misalignment calibration 有权
标题翻译：自主陀螺仪比例因子和不对准校准
公开(公告)号：US06298288B1
公开(公告)日：2001-10-02
申请号：US09212454
申请日：1998-12-16
申请人： Rongsheng Li , Yeong-Wei A. Wu , Garry Didinsky
发明人： Rongsheng Li , Yeong-Wei A. Wu , Garry Didinsky
IPC分类号： G06F770
CPC分类号： G05D1/0883 , B64G1/288 , B64G1/36 , B64G1/361 , B64G1/363 , B64G1/365 , B64G2001/245
摘要： A system and method of estimating the attitude of a spacecraft is disclosed. A three-axis inertial-based estimate of spacecraft attitude is produced and is compared to a stellar-based estimate of spacecraft attitude. A Kalman filter having states associated with gyro scale factor and/or misalignment errors compares the stellar-based attitude estimate to the inertial-based estimate of attitude and apportions the total error into three time varying matrices. A first time varying matrix is associated with gyro scale factor and misalignment errors, a second time varying matrix is associated with gyro bias errors, and a third time varying matrix is associated with attitude errors. The time varying matrices are applied as corrective feedbacks to the inertial-based estimate of spacecraft attitude and are adaptively adjusted to minimize the error therein.
摘要翻译：公开了一种估计航天器姿态的系统和方法。产生了基于三轴惯性的航天器姿态估计，并将其与航天器态度的恒星估计进行了比较。具有与陀螺仪比例因子和/或未对准误差相关联的状态的卡尔曼滤波器将基于恒星的姿态估计与基于惯性的姿态估计进行比较，并将总误差分配给三个时变矩阵。第一时变矩阵与陀螺仪比例因子和未对准误差相关联，第二时变矩阵与陀螺仪偏置误差相关联，并且第三时变矩阵与姿态误差相关联。时变矩阵作为校正反馈应用于基于惯性的航天器姿态估计，并进行自适应调整以最小化其中的误差。

32. 发明授权

US5535593A Apparatus and method for temperature control of a cryocooler by adjusting the compressor piston stroke amplitude 失效
标题翻译：通过调节压缩机活塞冲程振幅来控制制冷机的温度的装置和方法
公开(公告)号：US5535593A
公开(公告)日：1996-07-16
申请号：US293621
申请日：1994-08-22
申请人： Yeong-Wei A. Wu , Michael H. Kieffer
发明人： Yeong-Wei A. Wu , Michael H. Kieffer
IPC分类号： F25B9/14 , G05B11/42 , F25B9/00 , F25B1/00
CPC分类号： F25B9/14 , G05B11/42 , F25B2309/001
摘要： A temperature control apparatus and method for active control of a Stirling-cycle cryocooler cold finger tip temperature, by adjusting the cryocooler compressor piston stroke amplitude. In a control loop of the Stirling cryocooler, having a compressor in which the pistons are reciprocated by linear motors at fundamental frequency and the length of a stroke of the piston is varied as a direct function of cryocooler temperature, temperature is sensed at the cryocooler cold finger tip and the temperature signal is compared with a set temperature signal to produce a temperature error signal. This signal is input in a PID control law module which uses proportional, derivative, and integrated temperature error information to generate the required compressor piston stroke amplitude change for achieving the precision temperature control. The resulting signal is further processed in a distribution law module that distributes the desired piston stoke amplitude change to each compressor motor so that the force balance at the fundamental frequency is maintained.
摘要翻译：一种用于主动控制斯特林循环冷冻机冷指尖温度的温度控制装置和方法，通过调节低温冷冻机的压缩机活塞冲程振幅。在斯特林低温制冷机的控制回路中，具有压缩机，其中活塞通过线性电动机在基本频率下往复运动，并且活塞的行程长度随着低温冷却器温度的直接函数而变化，在低温冷却器感测温度指尖和温度信号与设定温度信号进行比较，产生温度误差信号。该信号输入到PID控制定律模块中，该模块使用比例，微分和积分温度误差信息来产生所需的压缩机活塞行程幅度变化，以实现精密温度控制。所得到的信号在分配规则模块中进一步处理，该分配规则模块将期望的活塞行程振幅变化分配给每个压缩机电动机，使得维持基频处的力平衡。

33. 发明授权

US08019544B2 Real-time refinement method of spacecraft star tracker alignment estimates 有权
标题翻译：航天器星形跟踪器对准估计的实时优化方法
公开(公告)号：US08019544B2
公开(公告)日：2011-09-13
申请号：US11028094
申请日：2005-01-03
申请人： David D. Needelman , Rongsheng Li , Yeong-Wei A. Wu
发明人： David D. Needelman , Rongsheng Li , Yeong-Wei A. Wu
IPC分类号： G01C21/00
CPC分类号： B64G1/361 , G01C21/025 , G01S3/7867
摘要： A method of estimating the alignment of a star sensor (20) for a vehicle (12) includes generating star tracker data. A vehicle attitude and a star sensor attitude are determined in response to the star tracker data. A current alignment sample is generated in response to the vehicle attitude and the star sensor attitude. A current refined estimate alignment signal is generated in response to the current alignment sample and a previously refined estimate alignment signal via a vehicle on-board filter (38).
摘要翻译：估计用于车辆（12）的星形传感器（20）的对准的方法包括产生星形跟踪器数据。响应于星形跟踪器数据确定车辆姿态和星形传感器姿态。响应于车辆姿态和星形传感器姿态产生当前的对准样品。响应于当前对准样本和经由车载过滤器（38）的先前精确的估计对准信号，产生当前精细估计对准信号。

34. 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。

35. 发明授权

US07260456B2 Pixel-frequency slews and filters for star data measurements 有权
标题翻译：用于星形数据测量的像素频率转换和滤波器
公开(公告)号：US07260456B2
公开(公告)日：2007-08-21
申请号：US11064375
申请日：2005-02-23
申请人： Richard A. Fowell , Yeong-Wei A. Wu
发明人： Richard A. Fowell , Yeong-Wei A. Wu
IPC分类号： B64G1/36 , B64G1/24
CPC分类号： G01S3/7867 , B64G1/361 , B64G2001/245 , G01C21/025 , G05D1/0883
摘要： A method and apparatus for reducing centroiding error of a star sensor having a plurality of pixels is disclosed. The method comprises the steps of computing a star sensor angular slew rate of ω pixels per star sensor integration period τ, collecting star sensor data while slewing the star sensor according to the selected star sensor angular slew rate ω, and filtering the collected star sensor data according to a frequency determined by the selected star sensor angular slew rate.
摘要翻译：公开了一种用于降低具有多个像素的恒星传感器的重心误差的方法和装置。该方法包括以下步骤：计算每个星形传感器积分周期τ的ω像素的星形传感器角度转换速率，在根据所选择的星形传感器角度转换速率ω旋转星形传感器时采集星形传感器数据，并对收集的星形传感器数据进行滤波根据选定的星形传感器角度转换速率确定的频率。

36. 发明授权

US06362464B1 System for stellar inertial attitude determination 有权
标题翻译：恒星惯性姿态测定系统
公开(公告)号：US06362464B1
公开(公告)日：2002-03-26
申请号：US09504543
申请日：2000-02-15
申请人： Yong Liu , Yeong-Wei A. Wu , Rongsheng Li , Christopher L. Rice
发明人： Yong Liu , Yeong-Wei A. Wu , Rongsheng Li , Christopher L. Rice
IPC分类号： G01C2102
CPC分类号： B64G1/361 , G01C21/025 , G01S3/7867 , G05D1/0883
摘要： An apparatus for determining stellar inertial attitude based upon a plurality of stars includes a star tracker and a controller. The star tracker is used to sense the positions of stars and generate signals corresponding to the positions of the stars as seen in its field of view. The controller checks a star catalog and actively determines which stars to track. The controller does this determination in terms of each star's relative geometry. The controller then commands the star tracker to track these stars and uses them to determine the spacecraft attitude.
摘要翻译：一种用于根据多个恒星确定恒星惯性姿态的装置包括星形跟踪器和控制器。星形跟踪器用于感测恒星的位置，并产生与其视场中所见的恒星位置相对应的信号。控制器检查星号目录，并主动确定要跟踪的星星。控制器根据每颗星的相对几何来做出这一决定。然后，控制器命令星形跟踪器跟踪这些恒星并使用它们来确定航天器的姿态。

37. 发明授权

US06236939B1 Method and apparatus for controlling spacecraft attitude with rotational star trackers 有权
标题翻译：用旋转星形跟踪器控制航天器姿态的方法和装置
公开(公告)号：US06236939B1
公开(公告)日：2001-05-22
申请号：US09261727
申请日：1999-03-03
申请人： Yeong-Wei A. Wu , Douglas H. Hein , Garry Didinsky , David L. Augenstein
发明人： Yeong-Wei A. Wu , Douglas H. Hein , Garry Didinsky , David L. Augenstein
IPC分类号： G01C2102
CPC分类号： B64G1/361 , B64G2001/245 , G01C21/025 , G01S3/7867 , G01S5/163
摘要： High precision spacecraft attitude determination is produced by specially positioning the spacecraft's star trackers and then filtering out measurement errors produced from star tracker electronics. In addition to the conventional azimuth and elevation controls used for star tracker pointing, the star tracker detector array is rotationally positioned about its boresight so that its pixels are traversed by the imaged star path at an angle within 20° of diagonal. This forces both vertical and horizontal spatial error components in the detector plane to a high frequency range at which they can easily be filtered out in common.
摘要翻译：通过专门定位航天器的星形跟踪器，然后滤除由星形跟踪器电子产生的测量误差，产生高精度航天器姿态测定。除了用于星形跟踪器指向的常规方位和仰角控制之外，星形跟踪器检测器阵列围绕其视轴旋转地定位，使得其像素以对角线的20°内的角度被成像的星形路径穿过。这迫使检测器平面中的垂直和水平空间误差分量都到高频范围，在这个高频范围内，它们可以容易地被共同滤除。

38. 发明授权

US5392607A Stirling-cycle cyrogenic cooler using adaptive feedforward vibration control 失效
标题翻译：使用自适应前馈振动控制的斯特林循环系统冷却器
公开(公告)号：US5392607A
公开(公告)日：1995-02-28
申请号：US91541
申请日：1993-07-08
申请人： Yeong-Wei A. Wu
发明人： Yeong-Wei A. Wu
IPC分类号： F16F15/02 , F25B9/14 , G05D19/02 , F25B9/00
CPC分类号： F16F15/02 , F25B9/14 , G05D19/02 , F25B2309/1428 , F25B2500/13
摘要： A Stirling-cycle cryogenic cooler that employs a vibration control procedure based on adaptive feedforward principles. The vibration control procedure is particularly adapted for use as a spacecraft cryogenic cooler, and may be used to cool a detector array or other sensor located on the spacecraft. The vibration control procedure suppresses vibrational forces that occur during operation of the cooler. The cooler comprises an expander module and a compressor module. The expander and compressor modules employ separate motors that respectively drive an expander piston and a compressor piston, and a balancer piston is employed to dynamically balance the respective expander and compressor pistons. In the control procedure, current command signals are injected into a selected motor drive of either the compressor or expander module. The injected current command signals comprise higher-order harmonics with adaptively determined phases and amplitudes that provide for complete force cancellation in the cooler. The desired phases and amplitudes of the injected current command signals are estimated in real time using outputs of force sensors, such as load cells, coupled to the cooler housing that measure higher-order harmonic forces. In operation, when operational parameters of the cryogenic cooler have reached equilibrium, the harmonic content of its vibration force is very stable in time. Because of this unique characteristic, the phases and amplitudes of injected current command signal do not have to be determined quickly. Thus, the computation throughput required for the present control procedure are significantly reduced.
摘要翻译：采用基于自适应前馈原理的振动控制程序的斯特林循环低温冷却器。振动控制程序特别适合用作航天器低温冷却器，并且可用于冷却位于航天器上的检测器阵列或其它传感器。振动控制程序抑制在冷却器运行期间发生的振动。冷却器包括膨胀器模块和压缩机模块。膨胀机和压缩机模块采用分别驱动膨胀机活塞和压缩机活塞的单独的马达，并且使用平衡器活塞来动态平衡相应的膨胀机和压缩机活塞。在控制过程中，电流指令信号被注入到压缩机或扩展器模块的选定的电机驱动器中。注入的电流指令信号包括具有自适应确定的相位和幅度的高次谐波，其在冷却器中提供完全的力消除。注射电流指令信号的期望相位和幅度使用耦合到测量高次谐波力的较冷外壳的力传感器（例如称重传感器）的输出实时估计。在运行中，当低温冷却器的运行参数达到平衡时，其振动力的谐波含量在时间上非常稳定。由于这种独特的特性，注入电流指令信号的相位和幅度不必快速确定。因此，本控制程序所需的计算吞吐量显着降低。

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