Spacecraft Pointing Control Using a Variable-Speed Control Moment Gyro
Spacecraft Pointing Control Using a Variable-Speed Control Moment Gyro
复制标题
使用变速控制力矩陀螺仪进行航天器指向控制
DOI：
10.2322/tstj.7.pd_1
复制
发表时间：
2009
期刊：
影响因子：
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通讯作者：
T. Shima
中科院分区：
文献类型：
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作者：
Katsuhiko Yamada;N. Takatsuka;T. Shima
本文研究的目的是利用变速单框架控制力矩陀螺实现航天器某轴的任意方向对准。由于航天器的总角动量在惯性空间中守恒，航天器的最终姿态受到限制，有可能实现与框架轴正交的轴的指向控制。使用新的参数来表示指向误差，我们提出了一个简单的指向控制律，可以用来对准指向轴在惯性空间中的任意方向。数值仿真结果验证了所提出控制律的有效性。
The objective of this study is to align a certain axis of a spacecraft in an arbitrary direction by using a variable-speed single-gimbal CMG. Because the total angular momentum of the spacecraft is conserved in inertial space, the final attitude of the spacecraft is restricted, and it is possible to achieve pointing control of the axis that is orthogonal to the gimbal axis. Using new parameters to express pointing errors, we have proposed a simple pointing control law that can be used to align the pointing axis in an arbitrary direction in inertial space. The validity of the proposed control law is verified by numerical simulations.