Patent ID: 8197212

Claim:
An assisted control system for controlling the attitude of a rotorcraft comprising: a flight control device; at least one control member configured to act on an aerodynamic element of the rotorcraft; a mechanical connection connecting the flight control device to the at least one control member, the mechanical connection including at least one connecting rod moveable in translation, a crank device pivotably disposed about a stationary support shaft passing through the crank device, and a motor including a drive rotor and a stator configured to facilitate a pivoting movement of the crank device about the stationary support; a motor control device configured to control a rotation of the drive rotor relative to the stator; and at least one sensor configured to measure information representative of an operation performed by the flight control device under pilot control and to deliver a signal relating to the information to the motor control device, wherein the at least one connecting rod includes a first and second connecting rod, wherein the crank device includes a transition zone and first and second branches secured to the transition zone, wherein the motor is disposed in the transition zone, and wherein the first branch is connected to the flight control device using the first connecting rod and the second branch is connected to the at least one control member using the second connecting rod, and wherein the transition zone is cylindrical and hollow so as to receive at least the stator.