Zhang Chao, Ma Guangfu, Sun Yanchao, Li Chuanjiang
Department of Control Science and Engineering, Harbin Institute of Technology, 150001 Harbin, People's Republic of China.
Department of Control Science and Engineering, Harbin Institute of Technology, 150001 Harbin, People's Republic of China; Science and Technology on Underwater Vehicle Laboratory, Harbin Engineering University, 150001 Harbin, People's Republic of China.
ISA Trans. 2019 Jun;89:84-95. doi: 10.1016/j.isatra.2018.12.027. Epub 2019 Jan 25.
This paper investigates the prescribed performance attitude control problem for flexible spacecraft subject to external disturbances and actuator constraints. By using a new performance function and an error transformation, the attitude control system is transformed into an error system which will be kept bounded to ensure expected dynamic and steady-state responses. Compared with the commonly used performance function, the modified one has an explicit prespecified terminal time which determines the maximum convergence time of the attitude control system. A modal observer and a disturbance observer are designed to deal with the flexible vibration and disturbances, respectively. Furthermore, when considering actuator saturation, an improved control strategy is developed with an auxiliary system utilized to compensate the saturation. The stability of the closed-loop system is analyzed by Lyapunov theory. Simulation results show the effectiveness and performance of the proposed methods.
本文研究了受外部干扰和执行器约束的挠性航天器的规定性能姿态控制问题。通过使用一种新的性能函数和误差变换，将姿态控制系统转换为一个误差系统，该误差系统将保持有界，以确保预期的动态和稳态响应。与常用的性能函数相比，改进后的性能函数具有明确的预先指定的终端时间，该时间确定了姿态控制系统的最大收敛时间。设计了一个模态观测器和一个干扰观测器，分别用于处理挠性振动和干扰。此外，在考虑执行器饱和时，开发了一种改进的控制策略，利用一个辅助系统来补偿饱和。通过李雅普诺夫理论分析了闭环系统的稳定性。仿真结果表明了所提方法的有效性和性能。
