空间站柔性太阳电池翼对日跟踪控制

Solar Tracking Control of Flexible Solar Cell Wings of Space Station

空间站柔性太阳电池翼高稳定对日跟踪驱动控制,对于保障空间站长期在轨能源安全和平稳运行具有重要意义。在推导柔性太阳电池翼动力学模型、柔性体模态分析和截断、Alpha对日定向装置机电系统模型、非线性传动系统模型的基础上,对空间站柔性太阳电池翼对日跟踪控制系统进行设计。采用Heaviside五次样条变速规划、位置和速度两级闭环、速度环陷阱滤波器柔性振动抑制的组合方案,实现空间站柔性太阳电池翼高稳定驱动控制。通过对典型工况的仿真校核,验证所设计的控制方案可实现跟踪精度优于0.3°、速度偏差±0.005(°)/s、稳定度优于7%@0.065(°)/s的性能指标。同时,Alpha对日定向装置的启动和变速过程中驱动力矩不大于30N·m,稳速运行期间驱动力矩不大于5N·m。各项性能指标要好于国际空间站Alpha对日定向装置,满足使用要求。

The highly stable tracking drive control of the flexible solar cell wings of Chinese Space Station(CSS)is of great significance to ensure the long-term energy safety and stable operation.In this paper,based on the derivation of the dynamic model of flexible solar cell wings,the normal mode analysis(NMA)of flexible body,the model of the electromechanical system for the solar Alpha rotary joint(SARJ),and the model of the nonlinear transmission system,a control system is designed for the SARJ.The combination scheme of Heaviside quintic spline variable speed planning,position and speed two-stage closed-loop,and speed loop flexible vibration suppression is used to achieve the highly stable drive control of the SARJ.Through simulation verification of typical cases,it is verified that the designed control scheme can achieve the tracking accuracy better than 0.3°,the speed deviation of±0.005(°)/s,and the stability superior to 7%@0.065(°)/s.Meanwhile,the driving torque during the starting and shifting of the SARJ is not greater than 30 N·m,and the driving torque during steady-speed operation is not greater than 5 N·m.In summary,all performance indicators are better than those obtained by the SARJ of International Space Station(ISS),and meet the application requirements.