ELECTROMECHANICAL ACTUATOR DEVICE FOR AN AERODYNAMIC SURFACE OF AN AIRCRAFT

摘要

The invention relates to systems for controlling the aerodynamic surfaces (rudder, aileron, etc.) of an aircraft. The electromechanical actuator device for an aerodynamic surface of an aircraft has: a controllable aerodynamic surface that is rotatably connected to an aerodynamic surface which is stationary relative to the fuselage; first and second electromechanical actuators mounted coaxially between the aerodynamic surface that is stationary relative to the fuselage and the controllable aerodynamic surface, each of said actuators consisting of a housing with an electric motor disposed therein and a reduction gear which is arranged coaxially with the electric motor and has a rotating output member that is connected to the controllable aerodynamic surface; and means for the emergency disengagement of the controllable aerodynamic surface and the aerodynamic surface that is stationary relative to the fuselage in order to provide for the rotation of the controllable aerodynamic surface, wherein each electromechanical actuator has a stationary housing which is attached to the aerodynamic surface that is stationary relative to the fuselage, the reduction gear used in the electromechanical actuator is a two-stage harmonic drive, the rotating member of which is in the form of a hollow output shaft with a flange that is attached to the controllable aerodynamic surface in such a way that the axis of rotation of the controllable aerodynamic surface coincides with the axes of rotation of the first and second electromechanical actuators, and the means for the emergency disengagement of the controllable aerodynamic surface and the aerodynamic surface that is stationary relative to the fuselage are arranged in an axially symmetric manner in the hollow output shaft of the electromechanical actuator and comprise an explosive cartridge.