This paper is concerned with robust fuzzy attitude control of spacecraft with aperiodically sampled measurements, actuator saturation, and persistent disturbance. Takagi-Sugeno (T-S) fuzzy model is employed to describe the kinematics and dynamics of spacecraft. Under the constraint of actuator saturation, a digital fuzzy controller consisting of discrete-time states and an exponentially decaying term is newly proposed to carry out exponential attitude stabilization of the considered spacecraft. Moreover, compared with ${\mathcal{H}}_{\infty }$ performance most often encountered when considering robust attitude control of spacecraft, ${\mathcal{L}}_{\infty }$-gain performance is designed to deal with persistent bounded disturbance in this study. Based on time-dependent Lyapunov functional and invariant set, the stability of closed-loop system is strictly proved. With the aid of convex optimization techniques, the desired sampled-data controller can be obtained by solving a set of linear matrix inequalities (LMIs). Finally, illustrative simulation results are presented to validate the effectiveness of the theoretical developments shown in this paper.

本文涉及具有不定期采样的测量值，执行器饱和度和持续扰动的航天器鲁棒模糊姿态控制。Takagi-Sugeno（TS）模糊模型用于描述航天器的运动学和动力学。在执行器饱和的约束下，提出了一种由离散时间状态和指数衰减项组成的数字模糊控制器，用于对所考虑的航天器进行指数姿态稳定。而且，与${\mathcal{H}}_{\infty }$ 在考虑航天器的稳健姿态控制时最常遇到的性能， ${\mathcal{大号}}_{\infty }$增益性能旨在处理本研究中的持续有限扰动。基于时间相关的Lyapunov函数和不变集，严格证明了闭环系统的稳定性。借助凸优化技术，可以通过求解一组线性矩阵不等式（LMI）获得所需的采样数据控制器。最后，给出了说明性的仿真结果，以验证本文显示的理论发展的有效性。