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    Optimal speed management for reaction wheel control system and method
    1.
    发明授权
    Optimal speed management for reaction wheel control system and method 有权
    反馈轮控制系统和方法的最佳速度管理

    公开(公告)号：US07198232B1

    公开(公告)日：2007-04-03

    申请号：US10926092

    申请日：2004-08-26

    申请人： Santosh Ratan ,  Xipu Li

    发明人： Santosh Ratan ,  Xipu Li

    IPC分类号： B64G1/28

    CPC分类号： B64G1/283 ,  B64G1/285 ,  B64G2001/245

    摘要： A spacecraft attitude control system and method in which an attitude controller is configured for sensing three-dimensional attitude of the spacecraft, and producing torque signals for stabilizing the spacecraft in a prescribed attitude in space. At least four mutually skew reaction wheels are rotated in response to the torque control signals for storing three-dimensional angular momentum, and speeds of rotation of the wheels are measured. A reaction wheel speed control processor, responsive to reaction wheel torque and speed for producing reaction wheel spin control signals, implements an infinity-norm algorithm for causing the nullspace components of wheel speed to re-distribute a desired three-dimensional stabilizing momentum of the spacecraft in such a manner that the maximum speeds of rotation of all the reaction wheels is minimized. As a result, periods between successive momentum dumping maneuvers are prolonged to the maximum possible.

    摘要翻译： 一种航天器姿态控制系统和方法，其中姿态控制器被配置用于感测航天器的三维姿态，并产生用于在空间中以规定姿态稳定航天器的扭矩信号。 响应于用于存储三维角动量的转矩控制信号，旋转至少四个相互偏斜的反作用轮，并且测量车轮的旋转速度。 反应轮速度控制处理器响应于反作用力矩和转速来产生反作用轮自旋控制信号，实现了无穷大范数的算法，用于使车轮速度的零空间分量重新分配航天器所需的三维稳定动量 使得所有反作用轮的最大旋转速度最小化。 因此，连续的动力倾倒机动之间的时间长短到最大可能。

    Gyroless control system for zero-momentum three-axis stabilized spacecraft
    2.
    发明授权
    Gyroless control system for zero-momentum three-axis stabilized spacecraft 失效
    无动力三轴稳定航天器的无陀螺控制系统

    公开(公告)号：US06600976B1

    公开(公告)日：2003-07-29

    申请号：US10108626

    申请日：2002-03-29

    申请人： Neil Evan Goodzeit ,  Xipu Li ,  Santosh Ratan ,  Harald Weigl

    发明人： Neil Evan Goodzeit ,  Xipu Li ,  Santosh Ratan ,  Harald Weigl

    IPC分类号： B64G124

    CPC分类号： G05D1/0883 ,  B64G1/283 ,  B64G1/363 ,  B64G1/365

    摘要： A method for maintaining three axis control of a geosynchronous spacecraft without body rate measurements using reaction wheel assemblies. Earth sensor assembly angle measurements are utilized for high-bandwidth roll and pitch control. A positive pitch momentum bias is stored in the reaction wheel assemblies. A gyroscopic feedforward torque is applied to rotate reaction wheel assembly momentum in a yaw/roll plane of the spacecraft at orbit rate. A dynamic mode that couples yaw and roll axes and that results from applying the gyroscopic feedforward torque and the high-bandwidth roll control is damped based on earth sensor assembly roll measurements.

    摘要翻译： 一种使用反作用轮组件保持地球同步航天器的三轴控制的方法，而不使用体速率测量。 地面传感器组件角度测量用于高带宽滚动和俯仰控制。 反馈轮组件中存储正间距动量偏压。 应用陀螺前馈扭矩以在轨道速率的旋转/滚动平面中旋转反作用轮组件的动量。 基于地球传感器组件辊测量，阻尼偏航和滚动轴的动态模式以及由应用陀螺前馈扭矩和高带宽滚动控制产生的动态模式。

    Sun sensor alignment compensation system
    5.
    发明授权
    Sun sensor alignment compensation system 有权
    太阳传感器对准补偿系统

    公开(公告)号：US06629672B1

    公开(公告)日：2003-10-07

    申请号：US10092636

    申请日：2002-03-08

    申请人： Neil Evan Goodzeit ,  Xipu Li

    发明人： Neil Evan Goodzeit ,  Xipu Li

    IPC分类号： B64G136

    CPC分类号： B64G1/363 ,  B64G1/365 ,  G05D1/0883

    摘要： A method for correcting differences in measurements between sensors. Misalignment of a roll error of a sun sensor alignment is estimated with respect to a reference roll value measured by an earth sensor. Sun sensor assembly elevation angle residual is calculated utilizing the estimated sun sensor assembly roll misalignment. A yaw attitude of the spacecraft is updated based upon the calculated sun sensor assembly elevation residual.

    摘要翻译： 一种用于校正传感器之间的测量差异的方法。 相对于由地球传感器测量的参考滚动值估计太阳传感器对准的滚动误差的未对准。 使用估计的太阳传感器组件辊未对准来计算太阳传感器组件仰角残差。 基于计算出的太阳传感器组件仰角残差来更新航天器的偏航姿态。