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    Stationkeeping maneuvering of a spacecraft
    1.
    发明公开
    Stationkeeping maneuvering of a spacecraft 审中-公开
    机动航天器到其存储

    公开(公告)号：EP1074470A3

    公开(公告)日：2001-09-19

    申请号：EP00305806.2

    申请日：2000-07-10

    申请人： Space Systems / Loral, Inc.

    发明人： Barker, Lee A. ,  Lange, Benjamin

    IPC分类号： B64G1/24 ,  B64G1/40 ,  G05D1/10

    CPC分类号： B64G1/24 ,  B64G1/242 ,  B64G1/407

    摘要： A spacecraft (10) having a solar array (11) is launched into orbit at a desired orbital location. Once the spacecraft is in orbit at the desired orbital location, a reflected component of solar radiation pressure is used to selectively apply a force to the spacecraft that moves the spacecraft to perform stationkeeping maneuvers. The reflected component of the solar radiation pressure may be caused to selectively apply a force to the spacecraft in one of two ways. In one example, the spacecraft is yaw steered to follow a yaw steering profile so that the axis of the solar array is substantially normal to a plane containing the sun vector and nadir vector. The orbit of the spacecraft is then controlled to provide stationkeeping by applying an additional bias to the yaw steering profile. In another example, the orbit is controlled to provide stationkeeping by tilting (or rotating) the solar array so that the solar array is at a predetermined angle relative to the sun vector. The additional bias or tilting may be applied as a command from a control station that is remotely located from the spacecraft (on the Earth), or applied as a command in a command and control system on the spacecraft.

    Method for inhibiting the automatic scan of a satellite sensor
    2.
    发明公开
    Method for inhibiting the automatic scan of a satellite sensor 审中-公开
    一种用于防止卫星传感器的自动检测方法

    公开(公告)号：EP1160542A3

    公开(公告)日：2003-05-21

    申请号：EP01303657.9

    申请日：2001-04-20

    申请人： Space Systems / Loral, Inc.

    发明人： Barker, Lee A. ,  Price, Xenophon

    IPC分类号： G01C21/02 ,  B64G1/36 ,  G05D1/08

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

    摘要： A method for use on a satellite that automatically inhibits scanning of an Earth sensor to handle sensor intrusions by the sun, moon, or other celestial bodies. In implementing the method, a predicted state vector for the satellite, derived from an orbit propagator, is generated. An attitude profile for the satellite is generated. Then, the satellite state (predicted state vector) and attitude profile are processed to determine Earth, sun, and moon vectors in a satellite body frame of reference at any instant. The Earth, sun, and moon vector are compared to the Earth sensor field of view and sensor field of view limit boxes to determine if scan inhibiting or Earth sensor switching should occur. The affected Earth sensor is inhibited or switched if an intrusion of the sun and/or moon into the field of view of the Earth sensor is predicted.

    Stationkeeping maneuvering of a spacecraft
    4.
    发明公开
    Stationkeeping maneuvering of a spacecraft 审中-公开
    航天器的保管操作

    公开(公告)号：EP1074470A2

    公开(公告)日：2001-02-07

    申请号：EP00305806.2

    申请日：2000-07-10

    申请人： Space Systems / Loral, Inc.

    发明人： Barker, Lee A. ,  Lange, Benjamin

    IPC分类号： B64G1/24 ,  B64G1/40

    CPC分类号： B64G1/24 ,  B64G1/242 ,  B64G1/407

    摘要： A spacecraft (10) having a solar array (11) is launched into orbit at a desired orbital location. Once the spacecraft is in orbit at the desired orbital location, a reflected component of solar radiation pressure is used to selectively apply a force to the spacecraft that moves the spacecraft to perform stationkeeping maneuvers. The reflected component of the solar radiation pressure may be caused to selectively apply a force to the spacecraft in one of two ways. In one example, the spacecraft is yaw steered to follow a yaw steering profile so that the axis of the solar array is substantially normal to a plane containing the sun vector and nadir vector. The orbit of the spacecraft is then controlled to provide stationkeeping by applying an additional bias to the yaw steering profile. In another example, the orbit is controlled to provide stationkeeping by tilting (or rotating) the solar array so that the solar array is at a predetermined angle relative to the sun vector. The additional bias or tilting may be applied as a command from a control station that is remotely located from the spacecraft (on the Earth), or applied as a command in a command and control system on the spacecraft.

    摘要翻译： 具有太阳能阵列（11）的航天器（10）在期望的轨道位置处发射到轨道上。 一旦航天器在轨道上处于期望的轨道位置，太阳辐射压力的反射分量就被用来选择性地向航天器施加一个力，以移动航天器来执行定位机动。 可以使太阳辐射压力的反射分量以两种方式之一选择性地施加到航天器上的力。 在一个示例中，航天器偏航转向以遵循偏航转向轮廓，使得太阳能阵列的轴线基本上垂直于包含太阳向量和最低点向量的平面。 然后通过对偏航转向轮廓施加额外的偏置来控制航天器的轨道以提供站点保持。 在另一个示例中，通过倾斜（或旋转）太阳能电池阵列来控制轨道以提供电台保持，使得太阳能电池阵列相对于太阳向量处于预定角度。 附加的偏差或倾斜可以作为来自远程位于航天器（在地球上）的控制站的命令应用，或者作为命令应用于航天器上的命令和控制系统。