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Adaptive back-stepping sliding mode attitude control of missile systems.
- Source :
-
International Journal of Robust & Nonlinear Control . Oct2013, Vol. 23 Issue 15, p1699-1717. 19p. - Publication Year :
- 2013
-
Abstract
- SUMMARY 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. Copyright © 2013 John Wiley & Sons, Ltd. [ABSTRACT FROM AUTHOR]
- Subjects :
- *GUIDED missiles
*AERODYNAMICS
*INERTIA (Mechanics)
*UNCERTAINTY
*ACTUATORS
Subjects
Details
- Language :
- English
- ISSN :
- 10498923
- Volume :
- 23
- Issue :
- 15
- Database :
- Academic Search Index
- Journal :
- International Journal of Robust & Nonlinear Control
- Publication Type :
- Academic Journal
- Accession number :
- 90469504
- Full Text :
- https://doi.org/10.1002/rnc.2952