Abstract: The invention describes a system for controlling the cyclic setting of blades (1) of a turbine engine propeller, the blades (1) being arranged in a plane normal to the axis of rotation (r) of the propeller, the system comprising: —a plate assembly (40) that can be tilted relative to the normal plane (P), —an articulation system (50) articulating the plate assembly (40) relative to the blades (1) such that tilting the plate assembly (40) modifies the setting of the blades (1), —a force sensor (5) designed to measure a force applied in the normal plane (P) by an air flow at the inlet of the propeller blades (1), —a cylinder (60) suitable for tilting the plate assembly (40) in response to a force measured by the force sensor (5).

Abstract: The invention describes a system for controlling the cyclic setting of blades (1) of a turbine engine propeller, the blades (1) being arranged in a plane normal to the axis of rotation (r) of the propeller, the system comprising: —a plate assembly (40) that can be tilted relative to the normal plane (P), —an articulation system (50) articulating the plate assembly (40) relative to the blades (1) such that tilting the plate assembly (40) modifies the setting of the blades (1), —a force sensor (5) designed to measure a force applied in the normal plane (P) by an air flow at the inlet of the propeller blades (1), —a cylinder (60) suitable for tilting the plate assembly (40) in response to a force measured by the force sensor (5).

Abstract: An epicyclic gear device for driving rotation of a first blade set of a turbine engine, the device: including a sunwheel centered on a longitudinal axis of the turbine engine and connected to a rotor of the engine in order to be driven in rotation; at least one planet meshing with the sunwheel; a planet carrier rotatably carrying the planet and connected to a first blade set in order to drive it in rotation; and a ring meshing with the planet; the sunwheel being connected to the rotor via a first constant velocity ball transmission joint.

Abstract: The invention provides a suspension structure for suspending a turboprop (10) having two unducted propellers on a structural element of an aircraft, the suspension structure comprising a cradle (18) for fastening to a structural element of the aircraft and having two lateral beams (22) connected to a main beam (20) extending parallel to a longitudinal axis (14) of the turboprop so as to form a V-shaped cradle structure, the cradle being fastened to the turboprop via two angle members (24) connecting each free end of the lateral beams of the cradle to the turboprop, via an axial link (28) connecting one end of the main beam of the cradle of the turboprop, and via at least one transverse link (30) situated in a plane extending transversely relative to the longitudinal axis of the turboprop and connecting the cradle to the turboprop.

Abstract: A rotor of an aircraft turbomachine having a main axis A, which includes modifying the critical speed of the rotor, depending on whether the rotational speed of the rotor is lower or higher than a predefined rotational speed, including a component that is capable of occupying a first state or a second state depending on whether the rotational speed of the rotor is lower or higher than the predefined rotational speed, each state of the component corresponding to a critical speed of the rotor, and driving the component to one or the other of the two states thereof, depending on the rotational speed of the rotor, wherein modifying the critical speed of the rotor further includes a component that engages with the drive means and is capable of being deformed elastically between one or the other of two stable forms, each of which corresponds to a state of the component.

Abstract: The invention provides a suspension structure for suspending a turboprop (10) having two unducted propellers on a structural element of an aircraft, the suspension structure comprising a cradle (18) for fastening to a structural element of the aircraft and having two lateral beams (22) connected to a main beam (20) extending parallel to a longitudinal axis (14) of the turboprop so as to form a V-shaped cradle structure, the cradle being fastened to the turboprop via two angle members (24) connecting each free end of the lateral beams of the cradle to the turboprop, via an axial link (28) connecting one end of the main beam of the cradle of the turboprop, and via at least one transverse link (30) situated in a plane extending transversely relative to the longitudinal axis of the turboprop and connecting the cradle to the turboprop.