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.
Attitude control of spacecrafts based on small-gain theorem
2014-07-01
166024 byte
Conference paper
Electronic Resource
English
ATTITUDE STABILITY OF DISSIPATIVE DUAL-SPIN SPACECRAFTS
NTIS | 1971
|Attitude stability of dissipative dual-spin spacecrafts
NTRS | 1971
|Distributed Adaptive Attitude Consensus Control for Multiple Rigid Spacecrafts
British Library Conference Proceedings | 2022
|A Quaternion-Based Nonlinear Attitude Controller for Spacecrafts
British Library Online Contents | 2012
|