Sliding mode attitude control for flexible spacecraft
Qi Wang, Qin Wei
Available Online March 2014.
- https://doi.org/10.2991/mce-14.2014.122How to use a DOI?
- flexible spacecraft; error quaternion; sliding mode control; Chattering reduction
- Aiming at the attitude control problem of flexible spacecraft, an improved sliding mode controller is presented. First of all, the dynamics equation and the kinematics equation described by error quaternion and error angular velocity are studied, which avoid the non-single question of the end attitude. What’s more, according to the mathematical model of flexible spacecraft attitude system, the sliding mode controller is designed by the Lyapunov approach. Finally, in order to reduce the chattering of variable structure control for flexible spacecraft attitude, the smoother “arc tan function” is used to replace the sign function to reduce the chattering. And optimization to reduce the maximum control torque required by the system, which can avoid the vibration of flexible appendages. Simulation results show that the proposed control scheme can effectively achieve the spacecraft attitude control. Besides, On account of this, we can find that it can eliminate the chattering of traditional sliding mode control and keep good robustness.
- Open Access
- This is an open access article distributed under the CC BY-NC license.
Cite this article
TY - CONF AU - Qi Wang AU - Qin Wei PY - 2014/03 DA - 2014/03 TI - Sliding mode attitude control for flexible spacecraft BT - 2014 International Conference on Mechatronics, Control and Electronic Engineering (MCE-14) PB - Atlantis Press SP - 545 EP - 549 SN - 1951-6851 UR - https://doi.org/10.2991/mce-14.2014.122 DO - https://doi.org/10.2991/mce-14.2014.122 ID - Wang2014/03 ER -