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The invention relates to a flight control device for an aircraft, the device comprising a mount, a lever pivotally mounted on the mount, and mechanical means for generating a return force for the lever, said means including a spring and a first motor member that are arranged so that a first end of t

The invention relates to a flight control device for an aircraft, the device comprising a mount, a lever pivotally mounted on the mount, and mechanical means for generating a return force for the lever, said means including a spring and a first motor member that are arranged so that a first end of the spring is constrained to move in rotation with the lever and a second end of the spring is constrained to move in rotation with an outlet shaft of the first motor member. According to the invention, the flight control device includes an electrical assistance system for assisting said mechanical means for generating a return force.

대표청구항 ▼

1. A flight control device for an aircraft, the device comprising: a mount;a lever pivotally mounted on the mount to pivot about at least one axis of rotation and designed to be secured to a control stick of the aircraft; andmechanical means for generating a return force for the lever about the axis

1. A flight control device for an aircraft, the device comprising: a mount;a lever pivotally mounted on the mount to pivot about at least one axis of rotation and designed to be secured to a control stick of the aircraft; andmechanical means for generating a return force for the lever about the axis of rotation, said mechanical means comprising a spring and a first motor member that are arranged in such a manner that a first end of the spring is constrained to move in rotation with the lever and a second end of the spring is constrained to move in rotation with an outlet shaft of the first motor member;the device being characterized in that it includes an electrical assistance system for assisting said mechanical means for generating a return force, the system comprising a second motor member that is distinct from the first motor member and that is arranged in such a manner that its outlet shaft is constrained to move in rotation with the first end of the spring, the system including control means for controlling the second motor member in order to modify the apparent stiffness of the spring in operation by means of the second motor member. 2. The flight control device according to claim 1, including first control means for the first motor member and said control means being second control means for the second motor member, which second control means are distinct from the first control means. 3. The flight control device according to claim 2, wherein the second control means include a first electronic control module and a second electronic control module, each module controlling a respective pole of the second motor member. 4. The flight control device according to claim 1, wherein the second motor member is a direct current motor having brushes. 5. The flight control device according to claim 1, wherein the electrical assistance system includes a stepdown assembly arranged between an outlet shaft of the second motor member and a toothed segment fastened to the lever in such a manner that the outlet shaft of the second motor member is constrained to move in rotation with the first end of the spring via the stepdown assembly, the toothed segment, and the lever. 6. The flight control device according to claim 5, wherein the stepdown assembly further includes a friction torque limiter. 7. The flight control device according to claim 5, wherein the toothed segment is fastened to the lever via a disconnectable device. 8. The flight control device according to claim 1, wherein the electrical assistance system is constrained to move in rotation with the first end of the spring by a disconnectable device. 9. The flight control device according to claim 8, wherein the second end of the spring moves in rotation with the outlet shaft of the first motor member via another disconnectable device. 10. The device according to claim 9, wherein the another disconnectable device presents a breaking threshold that is bigger than that of the disconnectable device connecting the electrical assistance system to the spring. 11. The device according to claim 8, wherein the disconnectable device is a shear pin. 12. The device according to claim 9, wherein the disconnectable device is a shear pin. 13. The device according to claim 10, wherein the disconnectable device is a shear pin.