针对基于磁悬浮万向飞轮的高轨卫星姿态机动控制问题，建立磁悬浮万向飞轮和卫星的姿态动力学方程，通过磁悬浮万向飞轮转子的偏转控制实现卫星滚动和偏航轴的姿态机动。由两个磁悬浮万向飞轮反向安装，组成双轮控制构型，实现整星零动量控制。仿真结果表明，在双磁悬浮万向飞轮系统控制下，卫星在20 s 内可实现5°的姿态机动，所需要的框架角为3°；当磁悬浮万向飞轮达到最大框架角6°时，卫星可实现12°的姿态机动。分析磁悬浮万向飞轮在低轨卫星中应用的前景，为实现卫星的快速机动和快速稳定控制提供新的思路。

Attitude maneuver control of high-earth-orbit satellite at roll and yaw axes with magnetically suspended gimbaling flywheel(MSGFW) is presented. The dynamic equations of satellite with MSGFW as actuator are developed. The control torque generates in roll and yaw axis when the gamble angles of flywheel change. Double MSGFWs mounted on the satellite with opposite rotation direction comprise the double MSGFWs attitude control system. The attitude control system works at zero momentum mode. Simulation results show that the satellite achieves attitude angle maneuver of 5° in 20 s with the gimbal angle of 3°. When the gimbal angle is 6° the satellite can achieve attitude angle maneuver of 12°. The future application of MSGFW on low-orbiting satellite is analyzed and the new concept in rapid maneuver and stabilization of satellite attitude control is proposed.