System for controlling the cyclic setting of blades

1. A system for controlling a cyclic pitch of blades of a propeller of a turbomachine, the propeller comprising a set of blades movable in rotation around an axis of rotation relative to a stator frame of reference of the turbomachine, the blades being arranged in a plane normal to the axis of rotation of the propeller, called normal plane, wherein the system comprises:

a plate assembly that can be inclined relative to the normal plane (P),

an articulation system articulating the plate assembly relative to the blades so that an inclination of the plate assembly causes a cyclic modification of the pitch of the blades,

a force sensor, mounted fixed in the stator frame of reference, the force sensor being suitable for measuring a force exerted in the normal plane by an air flow at an inlet of the propeller blades, and

a cylinder suitable for inclining the plate assembly, the cylinder being suitable to be actuated in response to a force measured by the force sensor,

wherein the plate assembly comprises an inner plate mounted fixed in the stator frame of reference and an outer plate mounted movable in rotation around the axis of rotation of the propeller, the inner plate and the outer plate being separated from one another by an antifriction bearing so that the inner plate and the outer plate are independent in rotation around the axis of rotation and are integral in inclination relative to the normal plane,

wherein the cylinder is actuated so as to modify an inclination of the inner plate, and

wherein the articulation system articulates the outer plate relative to the blades.

2. The system for controlling cyclic pitch of blades according to claim 1 , wherein the force sensor comprises a strain gauge and is suitable for being positioned at a bearing support of an intermediate casing of the turbomachine.

3. The system for controlling cyclic pitch of blades according to claim 1 , comprising a first set of force sensors suitable for measuring a force in a first direction of the normal plane and a second set of force sensors suitable for measuring a force in a second direction of the normal plane, the second direction being perpendicular to the first direction, the system further comprising a first cylinder suitable for being actuated in response to a force measured by the first set of force sensors, and a second cylinder suitable for being actuated in response to a force measured by the second set of force sensors.

4. The system for controlling cyclic pitch of blades according to claim 1 , further comprising a ball comprising a domed outer surface, wherein the plate assembly comprises an inner surface with a shape complementary to the outer surface of the ball and positioned in contact with the outer surface of the ball, so that the outer surface of the ball guides a displacement in inclination of the plate assembly.

5. The system for controlling the cyclic pitch of blades according to claim 1 , wherein the articulation system includes a set of connecting rods, each connecting rod being articulated at a first end on an associated blade by means of a pivoting link, and at a second end on the plate assembly, the connecting rods being mounted movable in rotation around the axis of rotation of the propeller, so that an inclination of the plate assembly causes a corresponding displacement of the connecting rods capable of cyclically modifying the pitch of the blades.

6. The system for controlling the cyclic pitch of blades according to claim 1 , further comprising a control unit suitable for generating a blade pitch control signal based on a comparison between a measurement signal originating in the force sensor and a predetermined set point signal, the control signal being suitable for actuating the cylinder when the measurement signal differs from the set point signal by a predetermined difference for a predetermined period.

7. The system for controlling the cyclic pitch of blades according to claim 1 , further comprising a system for controlling the collective pitch of blades configured to displace the plate assembly in translation in a longitudinal direction while retaining a same inclination of the plate assembly, so as to modify the pitch of each of the blades identically, the collective pitch of the blades being independent of a cyclic pitch of the blades.

8. A turbomachine comprising the system for controlling the cyclic pitch of blades of a propeller according to claim 1 .

9. An aircraft comprising the system for controlling cyclic pitch of blades of a propeller according to claim 1 .