Spacecraft attitude control with double-gimbaled control moment gyroscopes

Author

Zhou, Jingyang ; Zhou, Di

Author_Institution

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

fYear

2007

fDate

15-18 Dec. 2007

Firstpage

1557

Lastpage

1562

Abstract

An exact mathematical description of spacecraft attitude motion driven by double-gimbaled control moment gyroscopes(DGCMGs) is proposed. With this mathematical description, a nonlinear control law is designed based on the second method of Lyapunov for spacecraft large angle attitude maneuvers. In the design process, stability of the attitude control system is proved. The singularity robustness (SR) plus null motion steering law is designed to realize the control law by gyroscopes´ precession. Principle of DGCMGs´ singularity is proposed, and singularity analyses of the orthogonally mounted three DGCMGs system and that of the parallel mounted four DGCMGs system are presented. Analysis and simulation results are provided to show the capabilities of large angle and fast attitude maneuver of the orthogonally mounted three DGCMGs system.

Keywords

Lyapunov methods; attitude control; control system synthesis; nonlinear control systems; Lyapunov method; attitude control system stability; double-gimbaled control moment gyroscopes; nonlinear control law; null motion steering law; singularity robustness; spacecraft attitude control; spacecraft attitude motion; Actuators; Attitude control; Control systems; Equations; Feedback control; Gyroscopes; Motion control; Space vehicles; Torque; Wheels; DGCMG; attitude control; nonlinear control; spacecraft; steering law;

fLanguage

English

Publisher

ieee

Conference_Titel

Robotics and Biomimetics, 2007. ROBIO 2007. IEEE International Conference on

Conference_Location

Sanya

Print_ISBN

978-1-4244-1761-2

Electronic_ISBN

978-1-4244-1758-2

Type

conf

DOI

10.1109/ROBIO.2007.4522396

Filename

4522396