Abstract Attitude and vibration control of a general form of flexible satellites is addressed in this paper. Partial differential dynamic equations are derived considering new details such as multi sectioned solar panels and elastic connections between main hub and solar panels. Boundary control approach is adopted to eliminate simplification errors of discrete models, using just one actuator in the hub. Asymptotic stability of attitude dynamics is proved for a group of boundary controllers and necessary conditions for asymptotic stability of vibrations are discussed. Being independent of modeling accuracy and using easily measurable feedbacks are among advantages of the proposed class of controllers. Through simulations using FEM technique and a controller with the least number of boundary feedback parameters, good performance of the introduced method is illustrated.

中文翻译：

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多段附件柔性卫星振动抑制与姿态控制边界控制设计

摘要 本文研究了一种通用型柔性卫星的姿态和振动控制。偏微分动力学方程是考虑到新的细节，如多节太阳能电池板和主枢纽和太阳能电池板之间的弹性连接而推导出来的。采用边界控制方法消除离散模型的简化误差，仅在集线器中使用一个执行器。证明了一组边界控制器的姿态动力学渐近稳定性，讨论了振动渐近稳定性的必要条件。独立于建模精度和使用易于测量的反馈是所提出的控制器类别的优点之一。通过使用 FEM 技术和具有最少边界反馈参数的控制器进行模拟，