Saturated output feedback control for finite-time attitude stabilization of spacecraft

被引：2
|
作者：
Xia, Yuquan [1 ]
Su, Yuxin [1 ]
机构：
[1] Xidian Univ, Sch Electromech Engn, Xian 710071, Peoples R China
来源：
PROCEEDINGS OF THE INSTITUTION OF MECHANICAL ENGINEERS PART C-JOURNAL OF MECHANICAL ENGINEERING SCIENCE | 2020年 / 234卷 / 23期
关键词：
Actuator saturation; finite-time stabilization; homogeneity; output feedback; RIGID-BODY ATTITUDE; ANGULAR VELOCITY OBSERVERS; TRACKING;
D O I：
10.1177/0954406220928107
中图分类号：
TH [机械、仪表工业];
学科分类号：
0802 ;
摘要：
The finite-time attitude stabilization of spacecraft subject to actuator constraints and attitude measurements only is investigated. A saturated output feedback finite-time proportional-derivative control is proposed. Lyapunov stability theory and homogeneous method are employed to show the finite-time stabilization. Advantages of the proposed control include the finite-time stabilization featuring faster transient and higher precision and the absence of the modelling information and the velocity measurements in the control law formulation, and thus, it offers an easy-going solution for high-quality motion control of spacecraft. An additive feature is that the actuator saturation will not be reached by selecting the control gains a priori. Simulations are presented to illustrate the effectiveness of the proposed control.
引用
收藏
页码：4557 / 4571
页数：15
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