Patent ID: 8682506

Claim:
A flight control device outputting actuator steering commands in the yaw, pitch and roll domain from an angular velocity rate control input (wi) controlling a rotary wing aircraft comprising at least one rotor and one fuselage, the flight control device comprising: a rate controller deriving requested angular velocity (w) and angular acceleration (wdot) from wi and a measured velocity rate (wg); an actuator controller deriving actuator steering commands by an aerodynamic function (F 2 ) being modeled by at least the aerodynamics of the rotary wing aircraft; and a torque controller device deriving required torque (T) corresponding to w and wdot by a torque function F 1 being dependent of w, wdot, the inertia of the fuselage (If) and the inertia of the rotor (Ir), the torque function device being coupled between the rate controller and the actuator controller, having the outputs w and wdot from the rate controller as inputs and providing T as input to the actuator controller.