Electrical actuator for controlling hydraulic control valve in aircraft e.g. helicopter, has energizing unit that produces relative movement of two portions of rotor stator arrangement and energizes armature of rotor stator arrangement

摘要

The electrical actuator comprises a rotor stator arrangement that is provided for performing the positioning movement. A first portion (10) of the rotor stator arrangement is equipped with a magnet ring segment (12) while a second portion is equipped with an armature extended around the magnet ring segment. An energizing unit is provided along a circular arc surface (16) of the ring segment, for producing a relative movement of the two portions of the rotor stator arrangement and for energizing the armature.