Finite-time attitude control of spacecraft

Dai Gao; Siming Meng; Wei Yao; Jianting Lv

doi:10.1109/CCDC.2012.6244224

Finite-time attitude control of spacecraft

Dai Gao^*
, Siming Meng
, Wei Yao
, Jianting Lv

^*Corresponding author for this work

School of Astronautics, Harbin Institute of Technology
Heilongjiang University

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution › peer-review

2 Scopus citations

Abstract

In this paper, we propose two finite-time control laws for rigid spacecraft. We use quaternion for attitude representation and employ the Lagrange-like model for convenience of system design. First, by using the finite-time control method, a full-state feedback control scheme is presented. Then, considering no angular velocity measurement can be obtained, we propose a finite-time control law. Under the proposed control laws, the attitude of spacecraft converge to desired attitude in finite time.

Original language	English
Title of host publication	Proceedings of the 2012 24th Chinese Control and Decision Conference, CCDC 2012
Pages	1397-1401
Number of pages	5
DOIs	https://doi.org/10.1109/CCDC.2012.6244224
State	Published - 2012
Externally published	Yes
Event	2012 24th Chinese Control and Decision Conference, CCDC 2012 - Taiyuan, China Duration: 23 May 2012 → 25 May 2012

Publication series

Name	Proceedings of the 2012 24th Chinese Control and Decision Conference, CCDC 2012

Conference

Conference	2012 24th Chinese Control and Decision Conference, CCDC 2012
Country/Territory	China
City	Taiyuan
Period	23/05/12 → 25/05/12

Keywords

Attitude Control
Finite Time Converge
Output Feedback
State Feedback

Access to Document

10.1109/CCDC.2012.6244224

Cite this

@inproceedings{87910997b6e0402a826fa56d99245608,

title = "Finite-time attitude control of spacecraft",

abstract = "In this paper, we propose two finite-time control laws for rigid spacecraft. We use quaternion for attitude representation and employ the Lagrange-like model for convenience of system design. First, by using the finite-time control method, a full-state feedback control scheme is presented. Then, considering no angular velocity measurement can be obtained, we propose a finite-time control law. Under the proposed control laws, the attitude of spacecraft converge to desired attitude in finite time.",

keywords = "Attitude Control, Finite Time Converge, Output Feedback, State Feedback",

author = "Dai Gao and Siming Meng and Wei Yao and Jianting Lv",

year = "2012",

doi = "10.1109/CCDC.2012.6244224",

language = "英语",

isbn = "9781457720727",

series = "Proceedings of the 2012 24th Chinese Control and Decision Conference, CCDC 2012",

pages = "1397--1401",

booktitle = "Proceedings of the 2012 24th Chinese Control and Decision Conference, CCDC 2012",

note = "2012 24th Chinese Control and Decision Conference, CCDC 2012 ; Conference date: 23-05-2012 Through 25-05-2012",

}

Gao, D, Meng, S, Yao, W & Lv, J 2012, Finite-time attitude control of spacecraft. in Proceedings of the 2012 24th Chinese Control and Decision Conference, CCDC 2012., 6244224, Proceedings of the 2012 24th Chinese Control and Decision Conference, CCDC 2012, pp. 1397-1401, 2012 24th Chinese Control and Decision Conference, CCDC 2012, Taiyuan, China, 23/05/12. https://doi.org/10.1109/CCDC.2012.6244224

Finite-time attitude control of spacecraft. / Gao, Dai; Meng, Siming; Yao, Wei et al.
Proceedings of the 2012 24th Chinese Control and Decision Conference, CCDC 2012. 2012. p. 1397-1401 6244224 (Proceedings of the 2012 24th Chinese Control and Decision Conference, CCDC 2012).

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution › peer-review

TY - GEN

T1 - Finite-time attitude control of spacecraft

AU - Gao, Dai

AU - Meng, Siming

AU - Yao, Wei

AU - Lv, Jianting

PY - 2012

Y1 - 2012

N2 - In this paper, we propose two finite-time control laws for rigid spacecraft. We use quaternion for attitude representation and employ the Lagrange-like model for convenience of system design. First, by using the finite-time control method, a full-state feedback control scheme is presented. Then, considering no angular velocity measurement can be obtained, we propose a finite-time control law. Under the proposed control laws, the attitude of spacecraft converge to desired attitude in finite time.

AB - In this paper, we propose two finite-time control laws for rigid spacecraft. We use quaternion for attitude representation and employ the Lagrange-like model for convenience of system design. First, by using the finite-time control method, a full-state feedback control scheme is presented. Then, considering no angular velocity measurement can be obtained, we propose a finite-time control law. Under the proposed control laws, the attitude of spacecraft converge to desired attitude in finite time.

KW - Attitude Control

KW - Finite Time Converge

KW - Output Feedback

KW - State Feedback

UR - https://www.scopus.com/pages/publications/84866702729

U2 - 10.1109/CCDC.2012.6244224

DO - 10.1109/CCDC.2012.6244224

M3 - 会议稿件

AN - SCOPUS:84866702729

SN - 9781457720727

T3 - Proceedings of the 2012 24th Chinese Control and Decision Conference, CCDC 2012

SP - 1397

EP - 1401

BT - Proceedings of the 2012 24th Chinese Control and Decision Conference, CCDC 2012

T2 - 2012 24th Chinese Control and Decision Conference, CCDC 2012

Y2 - 23 May 2012 through 25 May 2012

ER -

Finite-time attitude control of spacecraft

Abstract

Publication series

Conference

Keywords

Access to Document

Other files and links

Fingerprint

Cite this