This study develops a dynamic event-triggered anti-disturbance (DETAD) controller to solve attitude control problem for flexible spacecraft systems with multiple disturbances. The disturbances involve two aspects: one belongs to $L_{2}$ space, and the other is described by an exogenous nonlinear system. Two sets of Takagi–Sugeno (T–S) fuzzy models are employed to model the flexible spacecraft systems and an exogenous nonlinear system, respectively. Moreover, a flexible vibration observer (FVO) is introduced to estimate the flexible modes. And a fuzzy disturbance observer (FDO) is designed to estimate the T–S fuzzy modeling disturbance in the case of the unmeasurable premise variables. By utilizing the estimations of two observers, a DETAD controller is constructed, where a dynamic event-triggered mechanism is implemented to reduce communication transmission. Additionally, new sufficient conditions for the closed-loop system to be asymptotically stable with strict dissipative performance are formed using linear matrix inequality techniques. Simulations are also provided to verify the advantages of the proposed scheme for flexible spacecraft systems subject to different types of disturbances.

中文翻译：

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柔性航天器系统的动态事件触发抗扰控制

本研究开发了一种动态事件触发抗扰动（DETAD）控制器，以解决具有多扰动的柔性航天器系统的姿态控制问题。干扰涉及两个方面：一是属于$L_{2}$空间，另一个由外生非线性系统描述。两组 Takagi–Sugeno (T–S) 模糊模型分别用于对柔性航天器系统和外生非线性系统进行建模。此外，引入了柔性振动观测器（FVO）来估计柔性模式。并设计了一个模糊扰动观测器（FDO）来估计前提变量不可测情况下的T-S模糊建模扰动。通过利用两个观察者的估计，构造了一个 DETAD 控制器，其中实现了动态事件触发机制以减少通信传输。此外，使用线性矩阵不等式技术形成闭环系统渐近稳定且具有严格耗散性能的新充分条件。