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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:(1)SADA与柔性负载耦合系统的低阶扭转固有频率;(2)SADA电脉冲信号的输入频率及其倍频。
Taking the Solar Array Drive Assembly (SADA) of a certain type of satellite as the research object, firstly, the vibrational equation of no-load operation of SADA is established by linearized electromagnetic torque. Secondly, based on the vibration equation of SADA in no-load operation, The vibration equation of SADA-driven solar-wing coupling system is established by the modal synthesis method of free interface. Thirdly, based on the vibration equation of the coupled system, the generation of SADA-driven solar wing is simplified by the force analysis and space force system Finally, a flexible load simulating the real solar wing was designed and the disturbing torque generated during the operation of SADA driving the flexible load was simulated and analyzed. The results show that the disturbing frequency of the disturbance torque generated by the SADA driving flexible load mainly consists of two parts when considering load damping: (1) the low-order torsional natural frequency of SADA and flexible load-coupled system ; (2) SADA electrical pulse signal input frequency and multiplier.