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    Spacecraft acquisition of orientation by scan of earth sensor field of view
    1.
    发明公开
    Spacecraft acquisition of orientation by scan of earth sensor field of view 失效
    Erfassung der Orientierung eines Raumfahrzeuges durch Abtastung des Sichtfeldes eines Endsensors

    公开(公告)号：EP1104896A1

    公开(公告)日：2001-06-06

    申请号：EP01200730.8

    申请日：1996-03-05

    申请人： Space Systems/Loral, Inc.

    发明人： Leung, Yat Fei ,  Tilley, Scott W.

    IPC分类号： G05D1/08 ,  B64G1/24 ,  B64G1/36

    CPC分类号： G05D1/0883 ,  B64G1/24 ,  B64G1/26 ,  B64G1/288 ,  B64G1/32 ,  B64G1/363 ,  B64G1/365 ,  B64G2001/245

    摘要： A spacecraft orientation procedure, in accordance with a first embodiment of the invention, is practiced with a sun sensor to bring the x (roll) axis of the spacecraft parallel to a ray of the sun, and with a gyro sensor and an earth sensor of the spacecraft in conjunction with one instruction provided either autonomously or by a ground tracking station regarding an orientation of a spacecraft reference plane to enable locating the earth by the earth sensor. Furthermore, in accordance with a second embodiment of the invention, the orientation is established without aid from the ground tracking station by use of at least one telemetry and command antenna having a continuous field of view, as measured in one plane, which is greater than a semicircle.' In the second embodiment, the orientation procedure provides for rotation of the spacecraft about the x axis for a scanning of the antenna to intercept command signals broadcast from the earth, thereby to locate the earth in a first reference plane. Rotation about the y (pitch) axis enables measurement of command signal strength for location of the earth in a second reference plane perpendicular to the first reference plane. Gyrocompassing establishes yaw in both embodiments of the invention.

    摘要翻译： 根据本发明的第一实施例的太空船取向程序用太阳传感器来实现，以使航天器的x（滚动）轴平行于太阳的光线，并且使用陀螺仪传感器和地球传感器 航天器结合一个指令自动提供或由地面跟踪站提供有关航天器参考平面的方位以使地球传感器能够定位地球的指令。 此外，根据本发明的第二实施例，通过使用至少一个具有在一个平面中测量的连续视场的遥测和命令天线，来自地面跟踪站的辅助建立方向，其大于 半圆形“。 在第二实施例中，定向过程提供了航天器围绕x轴的旋转，用于扫描天线以截取从地球广播的命令信号，从而将地球定位在第一参考平面中。 围绕y（俯仰）轴的旋转使得能够测量在与第一参考平面垂直的第二参考平面中地球的位置的命令信号强度。 陀螺仪在本发明的两个实施例中建立偏航。

    Onboard attitude control system using reaction wheels
    3.
    发明公开
    Onboard attitude control system using reaction wheels 审中-公开
    Bordlageregelungssystem mitReaktionsrädern

    公开(公告)号：EP1114774A2

    公开(公告)日：2001-07-11

    申请号：EP00311287.7

    申请日：2000-12-15

    申请人： Space Systems/Loral, Inc.

    发明人： Tilley, Scott W. ,  Holmes, Thomas J. ,  Reckdahl, Keith J.

    IPC分类号： B64G1/28

    CPC分类号： B64G1/285 ,  B64G1/283 ,  B64G1/288 ,  B64G1/32 ,  B64G1/36 ,  B64G1/363 ,  B64G1/365 ,  G05D1/0883

    摘要： An onboard attitude control system is constructed to utilize a four reaction wheel system (10-13) having a reference axis, wherein at least three of the reaction wheel spin axes are oriented obliquely to the reference axis. Current attitude is estimated based on uploaded orbital data, onboard sensed earth and sun position data, and attitude data sensed by a three axes gyroscope system (9). Current attitude is compared to mission attitude to calculate an error which is transformed to a trihedral axes adjustment command to actuate the reaction wheel system.

    摘要翻译： 构造车载姿态控制系统以利用具有参考轴线的四个反作用轮系统（10-13），其中至少三个反作用轮旋转轴线相对于参考轴线倾斜定向。 目前的态度是根据上传的轨道数据，车载感测地面和太阳位置数据以及由三轴陀螺仪系统（9）感测到的姿态数据来估计的。 将当前姿态与任务姿态进行比较，以计算转换为三角轴调整命令以致动反作用轮系统的误差。

    Spacecraft acquisition of orientation by scan of earth sensor field of view
    5.
    发明公开
    Spacecraft acquisition of orientation by scan of earth sensor field of view 失效
    Erfassung der Orientierung eines Raumfahrzeuges durch Abtastung des Sichtfeldes eines Endsensors

    公开(公告)号：EP0731401A2

    公开(公告)日：1996-09-11

    申请号：EP96301465.9

    申请日：1996-03-05

    申请人： SPACE SYSTEMS / LORAL INC.

    发明人： Leung, Yat Fei ,  Tilley, Scott W.

    IPC分类号： G05D1/08

    CPC分类号： G05D1/0883 ,  B64G1/24 ,  B64G1/26 ,  B64G1/288 ,  B64G1/32 ,  B64G1/363 ,  B64G1/365 ,  B64G2001/245

    摘要： A spacecraft orientation procedure, in accordance with a first embodiment of the invention, is practiced with a sun sensor to bring the x (roll) axis of the spacecraft parallel to a ray of the sun, and with a gyro sensor and an earth sensor of the spacecraft in conjunction with one instruction provided either autonomously or by a ground tracking station regarding an orientation of a spacecraft reference plane to enable locating the earth by the earth sensor. Furthermore, in accordance with a second embodiment of the invention, the orientation is established without aid from the ground tracking station by use of at least one telemetry and command antenna having a continuous field of view, as measured in one plane, which is greater than a semicircle. In the second embodiment, the orientation procedure provides for rotation of the spacecraft about the x axis for a scanning of the antenna to intercept command signals broadcast from the earth, thereby to locate the earth in a first reference plane. Rotation about the y (pitch) axis enables measurement of command signal strength for location of the earth in a second reference plane perpendicular to the first reference plane. Gyrocompassing establishes yaw in both embodiments of the invention.

    摘要翻译： 根据本发明的第一实施例的太空船取向程序用太阳传感器来实现，以使航天器的x（滚动）轴平行于太阳的光线，并且使用陀螺仪传感器和地球传感器 航天器结合一个指令自动提供或由地面跟踪站提供有关航天器参考平面的方位以使地球传感器能够定位地球的指令。 此外，根据本发明的第二实施例，通过使用至少一个具有在一个平面中测量的连续视场的遥测和命令天线，来自地面跟踪站的辅助建立方向，其大于 半圆形 在第二实施例中，定向过程提供了航天器围绕x轴的旋转，用于扫描天线以截取从地球广播的命令信号，从而将地球定位在第一参考平面中。 围绕y（俯仰）轴的旋转使得能够测量在与第一参考平面垂直的第二参考平面中地球的位置的命令信号强度。 陀螺仪在本发明的两个实施例中建立偏航。

    Combined stationkeeping and momentum management
    6.
    发明公开
    Combined stationkeeping and momentum management 审中-公开
    合并的储存和脉冲控制

    公开(公告)号：EP1024082A3

    公开(公告)日：2001-01-17

    申请号：EP00300508.9

    申请日：2000-01-24

    申请人： Space Systems / Loral, Inc.

    发明人： Tilley, Scott W. ,  Stratemeier, Darren R.

    IPC分类号： B64G1/26 ,  B64G1/28 ,  G05D1/08

    CPC分类号： B64G1/242 ,  B64G1/26 ,  B64G1/285 ,  G05D1/0883

    摘要： There is provided a method and system for simultaneous north-south stationkeeping and 3-axis momentum management for a geosynchronous orbiting spacecraft (1). The spacecraft (1) has a first thruster (4), a second thruster (5), and at least three momentum wheels (6) mounted on-board the spacecraft (1). The first (4) and second (5) thrusters are mounted adjacent to a north face (7) and a south face (8) of the spacecraft, respectively, on an anti-earth side of the spacecraft and are aligned to produce thrust vectors slightly off from the spacecraft's center of mass. The first (4) and second (5) thrusters are independently fired at predetermined positions along the geosynchronous orbital path of the spacecraft. The thrust vectors provide attitude and orbital adjustment needed to correct north-south orbital position deviation and provide torque needed to desaturate the stored angular momentum of the momentum wheels (6).

    Combined stationkeeping and momentum management
    7.
    发明公开
    Combined stationkeeping and momentum management 审中-公开
    Kombinierte Lagerhaltung und Impulsregelung

    公开(公告)号：EP1024082A2

    公开(公告)日：2000-08-02

    申请号：EP00300508.9

    申请日：2000-01-24

    申请人： SPACE SYSTEMS / LORAL, INC.

    发明人： Tilley, Scott W. ,  Stratemeier, Darren R.

    IPC分类号： B64G1/26 ,  B64G1/28

    CPC分类号： B64G1/242 ,  B64G1/26 ,  B64G1/285 ,  G05D1/0883

    摘要： There is provided a method and system for simultaneous north-south stationkeeping and 3-axis momentum management for a geosynchronous orbiting spacecraft (1). The spacecraft (1) has a first thruster (4), a second thruster (5), and at least three momentum wheels (6) mounted on-board the spacecraft (1). The first (4) and second (5) thrusters are mounted adjacent to a north face (7) and a south face (8) of the spacecraft, respectively, on an anti-earth side of the spacecraft and are aligned to produce thrust vectors slightly off from the spacecraft's center of mass. The first (4) and second (5) thrusters are independently fired at predetermined positions along the geosynchronous orbital path of the spacecraft. The thrust vectors provide attitude and orbital adjustment needed to correct north-south orbital position deviation and provide torque needed to desaturate the stored angular momentum of the momentum wheels (6).

    摘要翻译： 提供了一种用于地球同步轨道航天器同时进行南北保持和三轴动量管理的方法和系统（1）。 航天器（1）具有安装在飞船（1）上的第一推进器（4），第二推进器（5）和至少三个动量轮（6）。 第一（4）和第二（5）推进器分别安装在航天器的反面一侧的北面（7）和南面（8）附近，并对齐以产生推力矢量 稍微偏离了航天器的质心。 第一（4）和第二（5）推进器在沿着航天器的地球同步轨道路径的预定位置独立地发射。 推力向量提供校正南北轨道位置偏差所需的姿态和轨道调整，并提供使动量轮（6）的存储的角动量去饱和所需的扭矩。

    Spacecraft attitude control and momentum unloading using gimballed and throttled thrusters
    8.
    发明公开
    Spacecraft attitude control and momentum unloading using gimballed and throttled thrusters 失效
    由万向节的装置位置控制和转矩补偿航天器安装和连续节流发动机。

    公开(公告)号：EP0568209A1

    公开(公告)日：1993-11-03

    申请号：EP93302764.1

    申请日：1993-04-08

    申请人： SPACE SYSTEMS / LORAL INC.

    发明人： Tilley, Scott W. ,  Liu, Tung Yuan ,  Higham, John S.

    IPC分类号： B64G1/26

    CPC分类号： B64G1/26

    摘要： A spacecraft (201) maintains its north-south positioning by using one of two pairs of single-gimballed throttled thrusters (221-224) on a face of the spacecraft (201). The throttles (118) and gimbals (116) of the thrusters (221-224) are controlled to produce torques on the spacecraft (201) that will maintain a desired attitude for the spacecraft (201) while simultaneously desaturating the momentum stabilizing wheels (120, 121) of the spacecraft (201).

    摘要翻译： 的航天器（201）通过使用两对的面上的航天器（201）的单万向支架推进器节流（221-224）中的一个维持其南北定位。 推进器的节流阀（118）和万向节（116）（221到224）被控制以产生对航天器（201）thatwill保持航天器（201）所期望的姿势，同时去饱和动量稳定轮扭矩（120 ，121）的航天器（201）。