Bounded finite-time attitude tracking control for rigid spacecraft via output feedback

Jian Zhang; Qinglei Hu; Danwei Wang

doi:10.1016/j.ast.2017.01.020

Bounded finite-time attitude tracking control for rigid spacecraft via output feedback

Jian Zhang
, Qinglei Hu^*
, Danwei Wang

^*Corresponding author for this work

School of Automation Science and Electrical Engineering

Harbin Institute of Technology
Nanyang Technological University

Research output: Contribution to journal › Article › peer-review

53 Scopus citations

Abstract

This paper investigates a velocity-free finite-time attitude control scheme for a rigid spacecraft with actuator saturation and external disturbances. Initially, a finite-time observer is designed to compensate the unknown angular velocity information. With the estimated values, a finite-time controller is further developed under which the time-varying reference attitude trajectory can be tracked precisely. Moreover, input saturation problem is solved by adaptive method. Rigorous Lyapunov-based analysis shows that the states of the closed-loop system converge to a small neighborhood of the origin in finite time. Finally, the dynamic performance of attitude control system is presented by numerical simulation examples and the superiority of the finite-time control scheme is verified.

Original language	English
Pages (from-to)	75-84
Number of pages	10
Journal	Aerospace Science and Technology
Volume	64
DOIs	https://doi.org/10.1016/j.ast.2017.01.020
State	Published - 1 May 2017

Keywords

Actuator saturation
Attitude tracking
Finite-time control
Finite-time observer
Rigid spacecraft

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10.1016/j.ast.2017.01.020

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title = "Bounded finite-time attitude tracking control for rigid spacecraft via output feedback",

abstract = "This paper investigates a velocity-free finite-time attitude control scheme for a rigid spacecraft with actuator saturation and external disturbances. Initially, a finite-time observer is designed to compensate the unknown angular velocity information. With the estimated values, a finite-time controller is further developed under which the time-varying reference attitude trajectory can be tracked precisely. Moreover, input saturation problem is solved by adaptive method. Rigorous Lyapunov-based analysis shows that the states of the closed-loop system converge to a small neighborhood of the origin in finite time. Finally, the dynamic performance of attitude control system is presented by numerical simulation examples and the superiority of the finite-time control scheme is verified.",

keywords = "Actuator saturation, Attitude tracking, Finite-time control, Finite-time observer, Rigid spacecraft",

author = "Jian Zhang and Qinglei Hu and Danwei Wang",

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year = "2017",

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doi = "10.1016/j.ast.2017.01.020",

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T1 - Bounded finite-time attitude tracking control for rigid spacecraft via output feedback

AU - Zhang, Jian

AU - Hu, Qinglei

AU - Wang, Danwei

PY - 2017/5/1

Y1 - 2017/5/1

N2 - This paper investigates a velocity-free finite-time attitude control scheme for a rigid spacecraft with actuator saturation and external disturbances. Initially, a finite-time observer is designed to compensate the unknown angular velocity information. With the estimated values, a finite-time controller is further developed under which the time-varying reference attitude trajectory can be tracked precisely. Moreover, input saturation problem is solved by adaptive method. Rigorous Lyapunov-based analysis shows that the states of the closed-loop system converge to a small neighborhood of the origin in finite time. Finally, the dynamic performance of attitude control system is presented by numerical simulation examples and the superiority of the finite-time control scheme is verified.

AB - This paper investigates a velocity-free finite-time attitude control scheme for a rigid spacecraft with actuator saturation and external disturbances. Initially, a finite-time observer is designed to compensate the unknown angular velocity information. With the estimated values, a finite-time controller is further developed under which the time-varying reference attitude trajectory can be tracked precisely. Moreover, input saturation problem is solved by adaptive method. Rigorous Lyapunov-based analysis shows that the states of the closed-loop system converge to a small neighborhood of the origin in finite time. Finally, the dynamic performance of attitude control system is presented by numerical simulation examples and the superiority of the finite-time control scheme is verified.

KW - Actuator saturation

KW - Attitude tracking

KW - Finite-time control

KW - Finite-time observer

KW - Rigid spacecraft

UR - https://www.scopus.com/pages/publications/85012248752

U2 - 10.1016/j.ast.2017.01.020

DO - 10.1016/j.ast.2017.01.020

M3 - 文章

AN - SCOPUS:85012248752

SN - 1270-9638

VL - 64

SP - 75

EP - 84

JO - Aerospace Science and Technology

JF - Aerospace Science and Technology

ER -

Bounded finite-time attitude tracking control for rigid spacecraft via output feedback

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Keywords

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