Synthesis and analysis of the controller of the parameters of the longitudinal motion of an unmanned aircraft during the takeoff phase

This paper develops a robust controller for the longitudinal motion parameters of a lightweight unmanned airplane for automatic control during the takeoff phase. The regulator was synthesized using the method of linear matrix inequalities from H∞-theory at three points along the trajectory. The properties of a system containing regulators with three sets of coefficients are compared to a system using a single stationary regulator. The transient characteristics of trajectory angle control are examined. The analysis includes the effects of inaccurately specified aerodynamic characteristics. The performance of a dynamic stationary robust regulator, obtained at one point along the trajectory, is demonstrated throughout the flight from takeoff to the aircraft's transition height.