Finite-time attitude control of spacecraft

Author

Gao, Dai ; Meng, Siming ; Yao, Wei ; Lv, Jianting

Author_Institution

Sch. of Astronaut., Harbin Inst. of Technol., Harbin, China

fYear

2012

fDate

23-25 May 2012

Firstpage

1397

Lastpage

1401

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

angular velocity measurement; attitude control; space vehicles; state feedback; Lagrange-like model; angular velocity measurement; attitude representation; finite-time attitude control; finite-time control law; finite-time control laws; finite-time control method; full-state feedback control scheme; rigid spacecraft; spacecraft converge attitude; system design; Angular velocity; Asymptotic stability; Attitude control; Output feedback; Space vehicles; Stability analysis; Velocity measurement; Attitude Control; Finite Time Converge; Output Feedback; State Feedback;

fLanguage

English

Publisher

ieee

Conference_Titel

Control and Decision Conference (CCDC), 2012 24th Chinese

Conference_Location

Taiyuan

Print_ISBN

978-1-4577-2073-4

Type

conf

DOI

10.1109/CCDC.2012.6244224

Filename

6244224