Preliminary design of sliding mode controller for angular positional tracking of an aircraft

摘要: Sliding mode controllers are known to be robust parameter changes and capable of rejecting disturbances. Most sliding were implemented on aircraft models that derived based the aircraft's body axes. The model in this paper from an energybased modeling technique where dynamics can defined by Euler-Lagrangian equations makes decoupling simple straightforward. It is possible do so since these inertial axes instead nature it easy implement controller all angular positions for purpose tracking a reference trajectory. Parameter disturbances also introduced as part evaluation procedure few sets simulations prove how well tracked. designed achieve positional includes nominal feedback compensator. performance presented measured using root-mean-square error values maximum errors roll, pitch yaw. Results shows good performances throughout entire flight trajectory one-sided engine failure, 90 degree turn rotations angle.