设计了单框架控制力矩陀螺中的角动量飞轮分系统以提高卫星姿态控制精度。首先，从理论上分析了角动量飞轮的角速度波动对单框架控制力矩陀螺输出力矩的影响，得到当期望转速为5 000 r/min且力矩波动<0.002 Nm时，角速度波动应小于5 r/min的结论。然后，采用无刷直流电机驱动角动量飞轮，利用FPGA实现控制驱动电路，并设计自适应PI控制律以跟踪期望角速度。实验结果显示：从静止状态跟踪5 000 r/min期望转速，达到稳定状态耗时25 s, 超调量<15 r/min，稳态精度为2 r/min。通过对上位机实时采集转速数据进行分析，验证了动量飞轮分系统设计的合理性，表明其能够满足单框架控制力矩陀螺对角动量飞轮分系统的设计要求，降低了角速度波动对输出力矩的影响，进而能够提高卫星对地观测时的平台控制精度。

The angular momentum flywheel subsystem of a Single Gimbal Control Moment Gyro(SGCMG) was designed to improve the attitude control accuray of satellites. Firstly, the impact of angular velocity fluctuations on the output torque of SGCMG was analyzed in theory. The conclusion suggests that when the expected speed is 5 000 r/min and the torque fluctuation is less than 0.002 Nm, the angular velocity fluctuations should be less than 5 r/min. Then, the angular momentum flywheel was driven by a Brushless Direct Current Motor(BLDCM), the control driver circuit was designed by a Field Programming Gate Array(FPGA),and an adaptive compensation PI control strategy was established to track the expected angular velocity. Test and experiments show that it takes 25 s to reach a steady-state from stillness to 5 000 r/min,the overshoot is less than 15 r/min and the steady-state accuracy is 2 r/min. Analysis of the data collected real-time by PC shows the rationality of the subsystem and indicates the angular moment wheel designed satisfies the requirement of the SGCMG, reduces the impact of angular velocity fluctuations on the output torque of SGCMG,and improves the platform control accuracy of satellites.