关键词: 航天器姿态控制, 输入饱和, 限幅函数, 类PD控制, 最优化

Abstract: The existing methods to solve the control input saturation problem are summarized and divided into three main technical approaches. Then systematically analyze and compare the design ideas, mathematical forms and working characteristics of each methods. Summarize and analyze the effectiveness and area of application of the three technical approaches mainly including as follow in order to provide effective support for practical tasks. 1) Control law considering saturation as a whole: including saturation function, limiting function, switching function, anti saturation control, etc. Due to the high efficiency of actuator and complex form, it is suitable for the fast attitude maneuver missions of spacecraft with high computing power and adjusting time. 2) Control law considering saturation every item separately, including PD type control, backstepping control, etc. This technical approach has simple design and insufficiently utilization of the actuator which is suitable for attitude regulation with no time requirement or low cost small satellites. 3) Optimization considering saturation constraints: including time/energy/fuel optimal control and hybrid index optimal control, etc. This approach, which has high computation and dependence on accurate mathematical model, is suitable for the optimal attitude maneuvers of large spacecraft because of solving multiple constraints optimal problem.

Key words: font-size:10.5pt, ">Spacecraft attitude controlfont-size:10.5pt, ">；Input saturation；Saturation function；PD type control；optimization