Flight control device for an aircraft
The invention concerns a flight control device ( 1 ) for an aircraft, comprising: —a housing ( 2 ), —a handle ( 4 ) mounted rotating relative to the housing ( 2 ) about a center of rotation (O), —a first drive shaft ( 31 ), a second drive shaft ( 32 ) and a third drive shaft ( 33 ), the drive shafts ( 31 - 33 ) being mounted rotating relative to the housing ( 2 ) about a same axis of rotation (X), —a first connecting part ( 34 ) mounted pivoting on the first shaft ( 31 ) about a first axis of rotation (A 1 ), and on the handle ( 4 ) about a fourth axis of rotation (B 1 ), —a second connecting part ( 35 ) mounted pivoting on the second shaft ( 32 ) about a second axis of rotation (A 2 ), and on the handle ( 4 ) about a fifth axis of rotation (B 2 ), —a third connecting part ( 36 ) mounted pivoting on the third shaft ( 33 ) about a third axis of rotation (A 3 ), and on the handle ( 4 ) about a sixth axis of rotation (B 3 ), the first axis of rotation (A 1 ), the second axis of rotation (A 2 ) and the third axis of rotation (A 3 ) intersecting at the center of rotation (O) of the handle ( 4 ).
1. A flight control device for an aircraft, comprising:
a casing,
a handle rotatably mounted with respect to the casing around a center of rotation,
a first drive shaft, a second drive shaft and a third drive shaft, the drive shafts being rotatably mounted with respect to the casing along the same axis of rotation,
a first connecting part pivotally mounted on the first drive shaft around a first axis of rotation, and on the handle around a fourth axis of rotation,
a second connecting part pivotally mounted on the second drive shaft around a second axis of rotation, and on the handle around a fifth axis of rotation,
a third connecting part pivotally mounted on the third drive shaft around a third axis of rotation, and on the handle around a sixth axis of rotation,
wherein the first axis, the second axis and the third axis of rotation intersect at the center of rotation of the handle.
2. The flight control device according to claim 1 , wherein the first axis, the second axis and the third axis of rotation define a conical surface of revolution having an apex angle comprised between 15 and 30 degrees.
3. The flight control device according to claim 2 , wherein, when the handle is in a neutral position in which the fourth, fifth and sixth axes of rotation are orthogonal to the axis of rotation of the drive shafts, the first axis, the second axis and the third axis of rotation are arranged with an identical angular spacing between two axes.
4. The flight control device according to claim 1 , wherein the fourth, the fifth and the sixth axes of rotation intersect at the center of rotation of the handle.
5. The flight control device according to claim 4 , wherein the fourth, the fifth and the sixth axes of rotation extend in a same plane.
6. The flight control device according to claim 4 , wherein the fourth, the fifth and the sixth axes of rotation are arranged with an angular spacing of 120 degrees with respect to one another.
7. The flight control device according to claim 1 , wherein the first drive shaft, the second drive shaft and the third drive shaft are coaxial.
8. The flight control device according to claim 1 , comprising a first motor for generating a first resisting torque on the first drive shaft against a drive torque generated on the first drive shaft by a pilot activating the handle, a second motor for generating a second resisting torque on the second drive shaft against a drive torque generated on the second drive shaft by the pilot, and a third motor for generating a third resisting torque on the third drive shaft against a drive torque generated on the third drive shaft by the pilot.
9. The flight control device according to claim 8 , wherein the motors are aligned along the axis of rotation of the first drive shaft, of the second drive shaft and of the third drive shaft.