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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 000r/min且力矩波动<0.002Nm时,角速度波动应小于5r/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 000r/min期望转速,达到稳定状态耗时25s,超调量<15r/min,稳态精度为2r/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 in single-frame control moment gyroscope is designed to improve the satellite attitude control accuracy. First of all, the influence of the angular velocity fluctuation of the angular momentum flywheel on the output moment of single-frame control moment gyroscope is theoretically analyzed. The conclusion is obtained that the angular velocity fluctuation should be less than 5r / min when the expected rotation speed is 5 000r / min and the torque fluctuation <0.002Nm . Then, a brushless DC motor is used to drive the angular momentum flywheel. The FPGA is used to control the driving circuit and an adaptive PI control law is designed to track the desired angular velocity. The experimental results show that the steady state is 25s, the overshoot is less than 15r / min and the steady state precision is 2r / min. Through the analysis of real-time data collected from the host computer, the rationality of the design of the momentum flywheel subsystem is verified, which shows that it can meet the design requirements of the diagonal momentum flywheel subsystem of the single-frame control moment gyroscope and reduce the influence of the angular velocity fluctuation on the output torque , Which in turn can improve the platform control precision when the satellite observes the earth.