Attitude control of spacecrafts based on small-gain theorem

Author

Yan Han

Author_Institution

Sci. & Technol. on Space Intell. Control Lab., Beijing Inst. of Control Eng., Beijing, China

fYear

2014

fDate

28-30 July 2014

Firstpage

3494

Lastpage

3499

Abstract

A nonlinear attitude control law for spacecrafts is proposed based on small-gain theorem considering the effects of the control loop dynamics. The attitude angular rate commands, which are aimed at driving the attitude angles to the desired ones, are designed according to input-to-state stability (ISS) theory. Then, the small-gain theorem is iteratively used to propose the final torque input. It is shown that the attitude angles under the control law can robustly track the desired values, and the tracking errors are ISS with respect to disturbances. Simulation results have confirmed the effectiveness of the proposed scheme.

Keywords

aircraft control; attitude control; nonlinear control systems; space vehicles; stability; torque control; ISS theory; attitude angular rate commands; control loop dynamics; input-to-state stability theory; nonlinear attitude control law; small-gain theorem; spacecraft; torque input; Actuators; Attitude control; Backstepping; Robustness; Space vehicles; Stability analysis; Vehicle dynamics; Attitude control; generalized small-gain theorem; input-to-state stability; robustness;

fLanguage

English

Publisher

ieee

Conference_Titel

Control Conference (CCC), 2014 33rd Chinese

Conference_Location

Nanjing

Type

conf

DOI

10.1109/ChiCC.2014.6895519

Filename

6895519