Spacecraft Attitude Control Using a Double-Gimbal Control Moment Gyro
Spacecraft Attitude Control Using a Double-Gimbal Control Moment Gyro
复制标题
使用双万向节控制力矩陀螺仪控制航天器姿态
DOI：
10.2322/tastj.8.pd_45
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发表时间：
2010
期刊：
影响因子：
--
通讯作者：
I. Jikuya
中科院分区：
文献类型：
--
作者：
N. Takatsuka;Katsuhiko Yamada;I. Jikuya
提出了一种新的航天器姿态控制方案。它包括使用双框架控制力矩陀螺(CMG)，其中动量轮的转速保持恒定。使动量轮的旋转轴绕内框架轴或外框架轴倾斜可以在一个旋转方向上产生姿态控制力矩。为了补偿在另一个旋转方向上没有控制力矩的情况，设计了内外轴旋转的组合，以产生围绕动量轮自旋轴的循环运动，从而实现三轴姿态控制。发展了解析和数值算法来计算控制输入，即内外框架轴的倾斜角，这是导致期望的姿态变化的原因。通过数值仿真验证了该控制方案的有效性。
This paper presents a novel attitude control scheme for a spacecraft. It involves the use of a double-gimbal control moment gyro (CMG), wherein the rotational speed of the momentum wheel is kept constant. Tilting the spin axis of the momentum wheel around either an inner or an outer gimbal axis can generate attitude control torques in one rotational direction. In order to compensate for the absence of control torque in the other rotational direction, a combination of rotations of the inner and outer axes is designed to generate a cyclic motion about the spin axis of the momentum wheel resulting in three-axis attitude control. Analytical and numerical algorithms are developed to compute the control inputs, i.e., the tilt angles of the inner and outer gimbal axes, which are responsible for the desired change in attitude. The effectiveness of the proposed control scheme is verified by numerical simulations.