利索-全球专利检索

  1. 登录
  2. 注册

搜索结果

57 条记录 (耗时 0.03 秒)

    Spacecraft attitude determination system and method
    41.
    发明授权
    Spacecraft attitude determination system and method 有权
    航天器姿态测定系统及方法

    公开(公告)号：US06285927B1

    公开(公告)日：2001-09-04

    申请号：US09318565

    申请日：1999-05-26

    申请人： Rongsheng Li ,  Yeong-Wei Andy Wu

    发明人： Rongsheng Li ,  Yeong-Wei Andy Wu

    IPC分类号： B64G124

    CPC分类号： G05D1/0883 ,  B64G1/24 ,  B64G1/288 ,  B64G1/36 ,  B64G1/361 ,  B64G1/363 ,  B64G1/365 ,  B64G2001/245 ,  G01C21/025

    摘要： A method and system for minimizing attitude errors resulting from dynamic spacecraft maneuvers or time-varying mismatched attitude sensor measurements. The method includes time-tagging a primary attitude value from a primary attitude sensor and storing the value and associated time stamp in a buffer. A secondary attitude value, generated by a secondary attitude sensor, having a different associated time-stamp is then time-matched to the primary attitude valve. The corrected spacecraft attitude is then calculated as a function of the time-matched primary and secondary attitude values. In one aspect of the invention, the primary attitude sensor generates attitude data at a faster rate than the secondary attitude sensor. This primary attitude data is stored in a buffer such that, when the secondary attitude data becomes available, several nearest-in-time primary attitude data points are retrieved from the buffer. These data points are then used to interpolate a higher time-matched resolution data point. This, in turn, is used along with the secondary attitude data point in updating the spacecraft attitude.

    摘要翻译： 一种用于最小化由动态航天器操纵或时变不对称姿态传感器测量引起的姿态误差的方法和系统。 该方法包括从主姿态传感器对主要姿态值进行时间标记，并将该值和相关联的时间戳存储在缓冲器中。 然后，由二次姿态传感器产生的具有不同相关联的时间戳的二次姿态值与主姿势阀进行时间匹配。 然后根据时间匹配的主要和次要姿态值来计算校正的航天器姿态。 在本发明的一个方面，主姿态传感器以比二次姿态传感器更快的速度生成姿态数据。 该主要态度数据被存储在缓冲器中，使得当二级姿态数据变得可用时，从缓冲器检索几个最接近时间的主姿势数据点。 然后将这些数据点用于内插较高时间匹配的分辨率数据点。 这反过来又与二级姿态数据点一起用于更新航天器的态度。

    Autonomous attitude acquisition for a stellar inertial attitude determination system
    42.
    发明授权
    Autonomous attitude acquisition for a stellar inertial attitude determination system 失效
    一种恒星惯性姿态测定系统的自主态度采集

    公开(公告)号：US6108594A

    公开(公告)日：2000-08-22

    申请号：US87409

    申请日：1998-05-29

    申请人： Garry Didinsky ,  Yeong-Wei Wu ,  Rongsheng Li ,  Arunkumar Nayak ,  Douglas Hein

    发明人： Garry Didinsky ,  Yeong-Wei Wu ,  Rongsheng Li ,  Arunkumar Nayak ,  Douglas Hein

    IPC分类号： B64G1/28 ,  B64G1/36 ,  G01C21/02 ,  G01S3/781 ,  G01S5/16 ,  G05D1/08 ,  G06F165/00

    CPC分类号： G01C21/025 ,  B64G1/361 ,  G01S3/781 ,  G01S5/163 ,  G05D1/0883 ,  B64G1/288

    摘要： A method and apparatus for autonomous acquisition of attitude in a stellar inertial spacecraft attitude system is disclosed. The present invention uses star trackers, an on-board star catalog, spacecraft steering and inertial sensors to determine spacecraft attitude. The present invention utilizes pattern match and pattern rejection methods and uses multiple stellar snap-shots in conjunction with spacecraft steering and spacecraft inertial measurements to acquire spacecraft attitude. Spacecraft inertial measurements are used to connect multiple stellar snap-shots to provide adequate star information that can be used to acquire spacecraft attitude. In an attitude determination system using star trackers, the star trackers may have a narrow field-of-view or few stars may be available for viewing. The present invention uses pattern matching and pattern rejection on different sets of stars, thereby allowing attitude acquisition when the number of stars in view is small.

    摘要翻译： 公开了一种用于在恒星惯性航天器姿态系统中自动获取姿态的方法和装置。 本发明使用星形跟踪器，一个车载星形目录，航天器转向和惯性传感器来确定航天器的姿态。 本发明利用模式匹配和模式排斥方法，并结合航天器转向和航天器惯性测量使用多个恒星卡扣，以获得航天器的姿态。 航天器惯性测量用于连接多个恒星快照，以提供可用于获取航天器姿态的足够的星级信息。 在使用星形跟踪器的态度确定系统中，星形跟踪器可以具有窄的视场或几颗恒星可用于观看。 本发明在不同的星星集合上使用模式匹配和模式抑制，从而当观看的星星数量小时允许姿态采集。

    Spacecraft gyro calibration system
    45.
    发明申请
    Spacecraft gyro calibration system 有权
    航天器陀螺校准系统

    公开(公告)号：US20050108884A1

    公开(公告)日：2005-05-26

    申请号：US10723782

    申请日：2003-11-26

    申请人： Hangching Wang ,  Rongsheng Li

    发明人： Hangching Wang ,  Rongsheng Li

    IPC分类号： G01C19/00 ,  G01C25/00

    CPC分类号： G01C25/005

    摘要： A method of calibrating a gyro (42) of a spacecraft (14) may include determining a yaw attitude residual of the spacecraft. Roll gyro bias residual is determined in response to the yaw attitude residual. The gyro (42) is calibrated in response to the roll gyro bias residual. A method of calibrating a gyro (42) of a spacecraft (14) may alternatively include disabling gyro calibration, gain scheduling, or resetting attitude and gyro bias covariance, for selective axes, for a yaw transient period. The gyro (42) is calibrated in a nominal fashion after completion of the yaw transient period.

    摘要翻译： 校准航天器（14）的陀螺仪（42）的方法可以包括确定航天器的偏航姿态残差。 响应于偏航姿态残差来确定滚动陀螺仪偏差残差。 陀螺仪（42）响应于滚动陀螺仪偏置残差进行校准。 对于偏航过渡时段，校准宇宙飞船（14）的陀螺仪（42）的方法可替代地包括用于选择轴的禁用陀螺仪校准，增益调节或复位姿态和陀螺仪偏置协方差。 陀螺仪（42）在完成偏航过渡期后以标称方式进行校准。

    Refinement of spacecraft angular velocity and attitude estimates using star data
    46.
    发明申请
    Refinement of spacecraft angular velocity and attitude estimates using star data 有权
    使用星级数据对航天器角速度和姿态估计进行细化

    公开(公告)号：US20050071055A1

    公开(公告)日：2005-03-31

    申请号：US10945671

    申请日：2004-09-21

    申请人： David Needelman ,  Rongsheng Li ,  Yeong-Wei Wu

    发明人： David Needelman ,  Rongsheng Li ,  Yeong-Wei Wu

    IPC分类号： B64G1/36 ,  G01C21/02 ,  G01S3/786 ,  G06F17/00

    CPC分类号： G01C21/025 ,  B64G1/361 ,  G01S3/7867

    摘要： A method and apparatus for refining a spacecraft state estimate, such as an attitude estimate or an angular velocity estimate, is disclosed. The method computes a plurality equations using residuals describing the difference between observed star positions and predicted positions based on inertial measurements, and solves those equations to generate refined estimates of the spacecraft state estimates.

    摘要翻译： 公开了一种用于精制航天器状态估计的方法和装置，例如姿态估计或角速度估计。 该方法使用基于惯性测量描述观察到的星座位置和预测位置之间的差的残差来计算多个方程，并且求解这些等式以产生航天器状态估计的精确估计。

    Method and apparatus for spacecraft payload pointing registration
    47.
    发明授权
    Method and apparatus for spacecraft payload pointing registration 有权
    航天器有效载荷指向注册的方法和装置

    公开(公告)号：US06441776B1

    公开(公告)日：2002-08-27

    申请号：US09479701

    申请日：2000-01-07

    申请人： Douglas H. Hein ,  Rongsheng Li

    发明人： Douglas H. Hein ,  Rongsheng Li

    IPC分类号： G01S502

    CPC分类号： B64G1/242 ,  B64G1/24 ,  B64G1/26 ,  B64G1/288 ,  B64G1/36 ,  B64G1/361 ,  B64G1/363 ,  B64G1/365 ,  B64G2001/245 ,  G01S19/53

    摘要： A method, apparatus, and article of manufacture for directing a payload coupled to a spacecraft substantially at a target location is disclosed. The method comprises the steps of determining spacecraft orbital parameters and spacecraft payload attitude parameters; and directing the payload at the target location by applying a spacecraft bus steering law determined at least in part from the orbit and attitude parameters. The apparatus comprises a navigation system for determining spacecraft orbit parameters and spacecraft attitude parameters, and for applying a spacecraft bus steering law to direct the payload substantially at the target location. The spacecraft bus steering law is determined at least in part from the determined spacecraft orbital parameters, the determined spacecraft attitude, and determined payload attitude parameters. In one embodiment, the apparatus includes a payload attitude control system for directing the payload relative to the spacecraft bus. The article of manufacture comprises a program storage device tangibly embodying a series of instruction for performing the above method steps.

    摘要翻译： 公开了一种用于引导耦合到航天器的有效载荷基本上在目标位置处的方法，装置和制品。 该方法包括确定航天器轨道参数和航天器有效载荷姿态参数的步骤; 以及通过应用至少部分地从轨道和姿态参数确定的航天器总线导向法，将有效载荷指向目标位置。 该装置包括用于确定航天器轨道参数和航天器姿态参数的导航系统，以及用于应用航天器总线指导规则以将有效载荷基本上引导到目标位置。 至少部分地根据确定的航天器轨道参数，确定的航天器姿态和确定的有效载荷姿态参数来确定航天器总线导向规律。 在一个实施例中，该装置包括用于将有效载荷相对于航天器总线引导的载荷姿态控制系统。 该制品包括有形地体现用于执行上述方法步骤的一系列指令的程序存储装置。

    Stable and verifiable state estimation methods and systems with spacecraft applications
    48.
    发明授权
    Stable and verifiable state estimation methods and systems with spacecraft applications 有权
    具有航天器应用的稳定和可验证的状态估计方法和系统

    公开(公告)号：US06317662B1

    公开(公告)日：2001-11-13

    申请号：US09624270

    申请日：2000-07-24

    申请人： Rongsheng Li ,  Yeong-Wei Andy Wu

    发明人： Rongsheng Li ,  Yeong-Wei Andy Wu

    IPC分类号： G06F1700

    CPC分类号： G05B13/04

    摘要： The stability of a recursive estimator process (e.g., a Kalman filter is assured for long time periods by periodically resetting an error covariance P(tn) of the system to a predetermined reset value Pr. The recursive process is thus repetitively forced to start from a selected covariance and continue for a time period that is short compared to the system's total operational time period. The time period in which the process must maintain its numerical stability is significantly reduced as is the demand on the system's numerical stability. The process stability for an extended operational time period To is verified by performing the resetting step at the end of at least one reset time period Tr whose duration is less than the operational time period To and then confirming stability of the process over the reset time period Tr. Because the recursive process starts from a selected covariance at the beginning of each reset time period Tr, confirming stability of the process over at least one reset time period substantially confirms stability over the longer operational time period To.

    摘要翻译： 递归估计器过程的稳定性（例如，卡尔曼滤波器通过周期性地将系统的误差协方差P（tn）重置为预定的复位值Pr来确保长时间周期。因此递归过程被重复地从一个 选择的协方差，并持续一段与系统总运行时间相比较短的时间段，过程必须保持其数值稳定性的时间段显着减少，对系统的数值稳定性的要求， 延长的工作时间段To通过在至少一个持续时间小于操作时间段的至少一个复位时间段Tr的结束执行复位步骤来验证，然后确认过程在复位时间段Tr上的稳定性由于递归 过程从每个复位时间段Tr的开始处的选择的协方差开始，确认过程至少在o上的稳定性 复位时间段在较长的操作时间段To基本上确认了稳定性。