Nonlinear Attitude Control of Flexible Spacecraft with Scissored Pairs of Control Moment Gyros

Author

Fan, Jixiang ; Zhou, Di

Author_Institution

Dept. of Control Sci. & Eng., Harbin Inst. of Technol., Harbin, China

fYear

2010

fDate

17-19 Sept. 2010

Firstpage

719

Lastpage

722

Abstract

Dynamic equations describing the attitude motion of flexible spacecraft with scissored pairs of control moment gyroscopes are established. A nonlinear controller is designed to drive the flexible spacecraft to implement three-axis large-angle attitude maneuvers with the vibration suppression. Singularity of three orthogonally mounted scissored pairs of control moment gyros is analyzed. A new moore-penrose steering law is designed based on the synchronization constraint of gimbal angles. To improve the synchronization performance, an adaptive nonlinear controller is designed for each pairs of control moment gyros. Simulation results show the validity of the controllers and the steering law.

Keywords

adaptive control; attitude control; control system synthesis; gyroscopes; nonlinear control systems; space vehicles; steering systems; vibration control; adaptive nonlinear controller; attitude motion; control moment gyros; flexible spacecraft; gimbal angle; moore-penrose steering law; nonlinear attitude control; synchronization constraint; vibration suppression; Attitude control; Equations; Mathematical model; Space vehicles; Symmetric matrices; Synchronization; Torque; attitude control; flexible spacecraft; nonlinear control;

fLanguage

English

Publisher

ieee

Conference_Titel

Pervasive Computing Signal Processing and Applications (PCSPA), 2010 First International Conference on

Conference_Location

Harbin

Print_ISBN

978-1-4244-8043-2

Electronic_ISBN

978-0-7695-4180-8

Type

conf

DOI

10.1109/PCSPA.2010.179

Filename

5635604