Observer-Based Output Feedback Attitude Stabilization for Spacecraft With Finite-Time Convergence

被引：105

作者：

Hu, Qinglei ^{[1
]}

Jiang, Boyan ^{[2
]}

Zhang, Youmin ^{[3
]}

机构：

[1] Beihang Univ, Sch Automat Sci & Elect Engn, Beijing 100191, Peoples R China

[2] Harbin Inst Technol, Dept Control Sci & Engn, Harbin 150001, Heilongjiang, Peoples R China

[3] Concordia Univ, Dept Mech Ind & Aerosp Engn, Montreal, PQ H3G 1M8, Canada

来源：

IEEE TRANSACTIONS ON CONTROL SYSTEMS TECHNOLOGY | 2019年 / 27卷 / 02期

基金：

中国国家自然科学基金;

关键词：

Attitude stabilization; finite-time control; finite-time observer; output feedback; SLIDING-MODE CONTROL; TOLERANT TRACKING CONTROL; RIGID SPACECRAFT; CONTROL DESIGN; SYSTEMS;

D O I：

10.1109/TCST.2017.2780061

中图分类号：

TP [自动化技术、计算机技术];

学科分类号：

0812 ;

摘要：

This brief investigates the problem of finite-time output feedback control for spacecraft attitude stabilization without angular velocity measurement. First, two new sufficient conditions for finite-time ultimate boundedness and local finite-time stability are derived, which reduce the conservativeness of the traditional conditions. Then, based on the two new sufficient conditions of the finite-time stability, a finite-time observer is proposed to estimate the unknown angular velocity by using the quadratic Lyapunov function method. Next, a finite-time attitude controller is designed based on the estimate of the angular velocity. The finite-time stability of the entire closed-loop system is analyzed through the Lyapunov approach. The rigorous proof shows that the observation errors and the spacecraft attitude will converge to a residual set of zero in finite time. Numerical simulation results illustrate the effectiveness of the proposed strategy.

引用

页码：781 / 789

页数：9

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