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反作用轮系统是影响航天器姿控系统精度的主要扰动源之一．建立反作用轮扰动模型的目的是预测扰动对航天器产生的影响,并采取相应的控制方法和隔离系统．基于反作用轮的扰动实验模型,通过对反作用轮扰动实验数据的分析,确定出反作用轮扰动实验模型中的参数:谐波数和幅值系数,并在此基础上提出了能量补偿法,最后进行了数值仿真．结果表明,谐波数的辨识精度不超过0．04％,当采用振幅谱法计算幅值系数时,误差高达15．5％;而用能量补偿法,其幅值系数的精度不超过1．1％．可见能量补偿法提高了幅值系数的辨识精度．本文研究为改善航天器姿态控制精度和稳定度奠定了一定的基础．
The reaction wheel system is one of the main disturbance sources that affects the accuracy of the spacecraft attitude control system. The purpose of establishing the reaction wheel perturbation model is to predict the impact of disturbance on the spacecraft and to adopt corresponding control methods and isolation systems. Based on the experimental model of the reaction wheel disturbance, through the analysis of the experimental data of the reaction wheel disturbance, the parameters of the reaction wheel perturbation experimental model are determined: the number of harmonics and the amplitude coefficient, and on this basis, the energy compensation method is proposed and finally Numerical simulation. The results show that the identification accuracy of harmonic number does not exceed 0.04%, and the error is as high as 15.5% when using amplitude spectrum method to calculate the amplitude coefficient. The accuracy of amplitude coefficient does not exceed 1 by energy compensation method. 1%. Visible energy compensation method to improve the identification accuracy of the amplitude coefficient. This study lays a solid foundation for improving the attitude control accuracy and stability of spacecraft.