Review on Input Saturation in the Spacecraft Attitude Control

被引：0
|
作者：
Wang L.-Y. [1 ]
Guo Y.-N. [1 ]
Ma G.-F. [1 ]
Liu W.-L. [1 ]
机构：
[1] Dept. of Control Engineering and Science, Harbin Institute of Technology, Harbin
来源：
Yuhang Xuebao/Journal of Astronautics | 2021年 / 42卷 / 01期
关键词：
Input saturation; Optimization; PD type control; Saturation function; Spacecraft attitude control;
D O I：
10.3873/j.issn.1000-1328.2021.01.002
中图分类号：
学科分类号：
摘要：
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. © 2021, Editorial Dept. of JA. All right reserved.
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页码：11 / 21
页数：10
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