Title :
Attitude control of spacecrafts based on small-gain theorem
Author_Institution :
Sci. & Technol. on Space Intell. Control Lab., Beijing Inst. of Control Eng., Beijing, China
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;
Conference_Titel :
Control Conference (CCC), 2014 33rd Chinese
Conference_Location :
Nanjing
DOI :
10.1109/ChiCC.2014.6895519
