太阳翼驱动机构扰振力矩的建模与仿真

摘要

Taking the SADA of a satellite as the research object,firstly,the vibration equation of SADA driving no load was established by simplifying and linearizing the electromagnetic torque;secondly,the coupling vibration equation of SADA driving solar array was modeled by using the free-interface modal synthesis method based on the vibration equation of SADA driving free of load;thirdly,on the basis of the coupling vibration equation modeled,the disturbance torque emitted by the SADA driving solar array was obtained via force analysis and the simplified force system.Finally,the disturbance torque produced by SADA driving a flexible load,designed to simulate solar array,was simulated and analyzed.The results show that:in the case of considering load damping,the disturbance frequency of the disturbance torque aroused by SADA driving a flexible load is mainly consisting of two parts:① the low order torsional natural frequency of the coupling structure;② the input frequency of the digital pulse signal and its harmonics.%以某型号卫星的太阳翼驱动机构(Solar Array Drive Assembly,SADA)为研究对象,首先,通过线性化电磁力矩建立了SADA空载运行振动方程;其次,在SADA空载运行振动方程的基础上,利用自由界面模态综合法建立了SADA驱动太阳翼耦合系统的振动方程;再次,在耦合系统振动方程的基础上,通过受力分析和空间力系简化建立了SADA驱动太阳翼运行过程中所产生的扰振力矩模型;最后,设计了一个模拟真实太阳翼的柔性负载,并对SADA驱动该柔性负载运行过程中所产生的扰振力矩进行了仿真与分析.结果表明:在考虑负载阻尼的情况下,SADA驱动柔性负载运行过程中所产生扰振力矩的扰振频率主要由两部分组成,即:①SADA与柔性负载耦合系统的低阶扭转固有频率;②SADA电脉冲信号的输入频率及其倍频.