System for controlling the cyclic setting of blades

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.