This paper is devoted to the attitude control of a quaternion described missile model, which is nonlinear in aerodynamics with atmospheric moment uncertainties, inertia uncertainties, bounded disturbances and actuator failures. One backstepping 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. The variable structure control including sliding mode control has the valuable features of anti-interference and resisting parameter distortion, providing a useful solution for designing control law. Also, simulation results are presented to illustrate the effectiveness of the control strategy.
Backstepping Sliding Mode Control for Missile Attitude System
2018-08-01
223131 byte
Conference paper
Electronic Resource
English
Backstepping based adaptive sliding mode control for spacecraft attitude maneuvers
Online Contents | 2013
|Backstepping sliding mode control for flight attitude of quadrotor UAVs
British Library Conference Proceedings | 2023
|Design of missile attitude controller based on backstepping method
Tema Archive | 2008
|