太阳翼驱动机构机电耦合建模及微振动控制稳定性分析  

Electromechanical Coupling Modeling and Micro Vibration Control Stability Analysis of Solar Array Drive Assembly

作　　者：郑照明月 程伟[1] Zheng Zhaomingyue;Cheng Wei(School of Aeronautic Science and Engineering,Beihang University,Beijing 100191,China)

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100191

出　　处：《航天控制》2021年第6期60-66,73,共8页Aerospace Control

摘　　要：针对永磁同步电机太阳翼驱动机构(SADA)与柔性太阳翼的耦合现象,通过建模、仿真及实验的方法研究了耦合结构微振动影响SADA控制稳定性的问题。给出了采用微步驱动方法的永磁同步电机模型,通过线性化方法简化了上述模型的动力学方程。采用固定界面模态综合法建立了一种面向控制系统的SADA驱动柔性太阳翼模型。根据经典控制理论给出了一种控制参数的确定方法。仿真和实验结果表明:SADA驱动柔性太阳模型预测的微振动频率准确,幅值误差小于9.7%;当不满足控制参数的稳定条件时,微振动将提高一个量级,控制参数的确定方法有效。Aiming at the coupling phenomenon between Solar Array Drive Assembly(SADA) driving by permanent magnet synchronous motor(PMSM) and flexible solar array, the influence of micro vibration caused by the coupling structure on control stability of SADA is studied by modeling, simulation and experiment. A PMSM model driving by using micro-step driving method is presented, and the dynamic equation of the PMSM model is simplified by applying linearization method. A model of SADA in driving flexible solar array is established by using the fixed interface mode synthesis method. According to the classical control theory, a method of determining the control parameters is introduced. The simulation and experimental results show that the micro vibration frequency predicted by the model is accurate, and the amplitude error is less than 9.7%, and when the stability condition of control parameters is not satisfied, the micro vibration can be increased by one order of magnitude which verifies that the determination method of control parameters is effective.

关 键 词：太阳翼驱动机构(SADA) 永磁同步电机 机电耦合 微步驱动方法 控制稳定性 微振动 

分 类 号：V448.22[航空宇航科学与技术—飞行器设计]