Providing supermaneuverability for electrically-actuated aircraft

Abstract

The problem of providing supermaneuverability of aircraft is considered taking into account the possibilities that are opened in a electrically-actuated aircraft. The concept of creating a electrically-actuated aircraft provides for the replacement of hydraulic drives to electric drives powered by electric energy sources. It is noted that modern electromechanical actuators are already superior to hydraulic actuators in a number of indicators. This is especially important for a flight control system that needs fast and powerful drives for aerodynamic control of the aircraft. The flight control system provides stability and controllability of the aircraft at all stages and flight modes. In this regard, when solving the problem of ensuring supermaneuverability of the aircraft, it is necessary to take into account the permissible limits of changing the parameters of its movement. This problem is solved using logic devices that implement algorithms of channel selection. A method of synthesis of coordinated control of the roll angle control loop and the roll angular velocity limitation loop is proposed.