Abstract: The device comprises anti-cone stops projecting outwards from a common ring that can rotate about the rotor axis on the top face of the hub and flyweights are each individually joined to the ring for driving the latter in rotation from the "ground" position, in which each anti-cone stop is facing an upper bearing shoe of the corresponding blade, to the "flight" position, in which the anti-cone stops are retracted, returning them to the "ground" position.

Abstract: An individual pitch control device for the blades (7) of a rotor of a rotor craft employing respective rotating linear jacks (29) for controlling the pitch of the rotor blades. The linear jacks are implanted in a rotating support (25) which is driven in rotation with the rotor. The jacks (29) include rods (31) which are connected via additional rods (33) to drive pitch control levers (24) for each respective blade. The jacks (29) are linear, electrohydraulic, dual-action jacks having at least one body, and are supplied by control servovalves (36) which are also mounted in a rotating reference system. The servovalves (36) are supplied from a hydraulic circuit in a fixed reference system positioned on the rotor craft, having at least one hydraulic collector (27) which is at least partially rotating.

Abstract: The resilient return strut is of the elastic-hydraulic type with incorporated linear damping by throttling a high-viscosity fluid, and comprises a damper (1) mounted between two return springs (2, 3) in elastomer-based sleeves (17, 18), undergoing a shearing action and sealing the chambers (34, 35) set off within the body of the damper (12) by a transverse wall (10) which marks off a permanent throttling passage around a central brace (23). Limiting valves equipped with spring-leaves (45) sealing the holes (40) bored in the wall (10) increase the throttling section. A compressed-air system (52), mounted in a spring (2), compensates for thermal expansion of the fluid. The device is used with helicopter rotors.

Abstract: The invention relates to a control device for monocyclic pitch in a fixed reference system and multicyclic pitch in a rotating reference system, for the blades (7) of a rotor craft.In addition to conventional swashplates (27, 38), one (38) of which rotates (39) on the other (27) held in rotation by a nonrotating compass (28), but which slides axially (4) and oscillates (25) about the rotor mast (1), through the action of pilot control (30), it comprises multicyclic jacks (45) in a number equal to the blades (7), and each of which is implanted in the rotating plate (38) and directly drives a pitch control rod (44) of a corresponding blade (7). Each multicyclic jack (45) is a dual-action, hydraulic linear jack controlled by a servovalve (49) also implanted on the rotating plate (38).

Abstract: The invention relates to a combined bearing device for a rotorcraft rotor or a rotor equipped with such a bearing device. In the rotor, each blade is held on the hub by a flexible arm surrounded without contact by a rigid stub sleeve by a combined bearing device including a cylindrical plain angle of attach bearing, a spherical ball joint with visco-elastic element for resiliently returning the blade under flapping and drag conditions, and with an integrated damper for damping the angular oscillations of the blade under drag conditions, of the hydraulic rotation damper type with vanes for laminating the hydraulic fluid and compensation chambers for the expansion of this latter, the hydraulic damper being integrated in the spherical thrust bearing and its compensation chambers belonging to a hydraulic automatic play take-up device for the plain bearing.