Abstract
This paper is devoted to the attitude control of a quaternion missile model, which is nonlinear in aerodynamics with atmospheric moment uncertainties, inertia uncertainties, bounded disturbances and actuator failures. By employing the back-stepping technique, the corresponding sliding mode controller is designed to guarantee the state variables of the closed loop system to converge to a small region of the reference states with the help of the adaptive law by estimating the total uncertainties, and be chatter-free. Also, simulation results are presented to illustrate the effectiveness of the control strategy.
| Original language | English |
|---|---|
| Pages (from-to) | 1699-1717 |
| Number of pages | 19 |
| Journal | International Journal of Robust and Nonlinear Control |
| Volume | 23 |
| Issue number | 15 |
| DOIs | |
| Publication status | Published - Oct 2013 |
Keywords
- adaptive control
- back-stepping
- missile attitude control
- sliding mode control
Fingerprint
Dive into the research topics of 'Adaptive back-stepping sliding mode attitude control of missile systems'. Together they form a unique fingerprint.Cite this
Xia, Y., Lu, K., Zhu, Z., & Fu, M. (2013). Adaptive back-stepping sliding mode attitude control of missile systems. International Journal of Robust and Nonlinear Control, 23(15), 1699-1717. https://doi.org/10.1002/rnc.2952