Sliding mode observer based variable-structure control in attitude control system of small satellite

Author

Xian, Zhang ; Yuehua, Cheng ; Bin, Jiang

Author_Institution

Coll. of Autom. Eng., Nanjing Univ. of Aeronaut. & Astronaut., Nanjing

fYear

2008

fDate

16-18 July 2008

Firstpage

141

Lastpage

144

Abstract

In view of the small satellite attitude system where no gyro is available or gyro fails, the quaternion estimating angle rate of satellite is proposed by means of sliding mode observer. Based on the attitude rate estimator, the decoupling variable structure controller is designed for attitude control system. The simulation results show that the accuracy of estimating is rather high, and the variable structure control method has advantages of being easily designed and realized.

Keywords

artificial satellites; attitude control; control system synthesis; observers; variable structure systems; angle rate estimation; attitude control system; attitude rate estimator; decoupling variable structure controller design; quaternion; sliding mode observer; small satellite attitude system; Aerodynamics; Attitude control; Automatic control; Automation; Control systems; Educational institutions; Kinematics; Quaternions; Satellites; Sliding mode control; Attitude rate estimator; Sliding mode observer; Small satellite; Variable structure control;

fLanguage

English

Publisher

ieee

Conference_Titel

Control Conference, 2008. CCC 2008. 27th Chinese

Conference_Location

Kunming

Print_ISBN

978-7-900719-70-6

Electronic_ISBN

978-7-900719-70-6

Type

conf

DOI

10.1109/CHICC.2008.4605185

Filename

4605185