A Novel Method for Controlling the Roll Angle of Aircraft using Sliding Mode Control Methodology

摘要

The automatic flight control system of an aircraft is very complicated in nature with lot of logics and operational constraints. The study of the detailed automatic flight control and thrust control involves complicated logics for the control functions with closed loop control systems which can be realized in the software. The work is focussed on the redesign of automatic flight control system using robust control methods in MATLAB/Simulink environment. This paper aims at a complete study, analysis, design and performance monitoring of new generation autopilot system using sliding mode control (SMC)?method and the results of simulation of the above analysis shows an optimal performance of the autopilot system.