Longitudinal directional flight control design using robust dynamic contraction method

In the paper the design of an aircraft flight controller based on the Dynamic Contraction Method is presented. The control task is formulated as a tracking problem of aerodynamic state variables: velocity of flight and flight path angle, which are responsible for aircraft flight conditions in the longitudinal movement. The applied DCM method allows to create the expected outputs for non-linear and non-stationary objects in spite of incomplete information about varying parameters of the system and external disturbances. The proposed technique is tested by simulations of a few maneuvers under wind gust for a F-16 aircraft model.