“…While the elevator deflection ( δ e ) and throttle setting ( η c ) are selected as control inputs ( U ), the airplane model with the state variables X = [ V , γ , q , α , h ] is given as follows [10]:where m and I y denote the mass and moment of inertia of the airplane, respectively. Besides that, the lift L , the drag D , the thrust T , and the pitching moment M y are determined by …”