Abstract: The blade includes a current part (1) having an aerodynamic profile enclosing a spar (7) and extending from blade tip (4) to a blade root (3) provided with a pitch sleeve (21), through which twisting arm (6) passes and protrudes beyond blade root (3), and having a first part of a bundle (5) of superimposed and elongated metal strips, current part (1) including a block (13) based on synthetic material molded in form in a single piece around spar (7), and a second part of bundle (5) extending in line with the first part forming the twisting arm (6) and cooperating with the anchoring devices (14, 17) of the block (13) based on synthetic material around the spar (7).

Abstract: The blade includes a current part (1) having an aerodynamic profile enclosing a spar (7) and extending from blade tip (4) to a blade root (3) provided with a pitch sleeve (21), through which twisting arm (6) passes and protrudes beyond blade root (3), and comprising a first part of a bundle (5) of superimposed and elongated metal strips, current part (1) including a block (13) based on synthetic material molded in form in a single piece around spar (7), comprising a second part of bundle (5) extending in line with the first part forming the twisting arm (6) and cooperating with the anchoring devices (14, 17) of the block (13) based on synthetic material around the spar (7).

Abstract: The annular cushion 25 interposed between the fixed housing 22, 23 and a swiveling exterior surface 27 in the shape of a spherical sector with relatively large radius of curvature of the bearing block 12, 15, 16, is in a relatively rigid and incompressible material, with low coefficient of friction surface, and has a transverse section wholly adapted to the section of the annular space arranged between the inner surface of the fixed housing 22, 23 and the swiveling exterior surface of the bearing block 12, 15, 16, this annular cushion consisting of two rings 25 spaced apart and arranged on each side of the transverse median plane of the swiveling exterior surface.

Abstract: An apparatus has at least one pendulous member mounted on a rotor so as to be able to swing about an axis of pendular motion spaced at a distance from the center of inertia of the pendulous member. The pendulous member is pivotably mounted on its own axis of rotation parallel to the axis of pendular motion and situated substantially closer to the center of inertia of the pendulous member than to the axis of pendular motion.

Abstract: A multi-blade rotor (1), especially for a helicopter rear anti-couple propeller, includes a hub body (3) to which are connected twistable straps (11 to 17) each formed by two bundles (20) of fibers with a flattened cross section arranged radially around the hub (3), each of the bundles (20) forming at least two halves of different blades (11 to 17) and being twisted and curved in the region of its passage near the center of the hub body (2) in such a way that it forms a tangent to the circumference of the center of the hub body (3) along the greater dimension of its cross section.

Abstract: An anti-torque system for a helicopter with a rearwards-elongated fuselage where an engine drives a main gearbox. The engine and the main gearbox are arranged in the central part of the fuselage. The anti-torque system includes an anti-torque tail rotor whose axis is transversal with respect to the fuselage and which is situated at the rear end of the fuselage. A fairing defines an aerodynamic tunnel in which the tail rotor is housed coaxially. The tunnel has a trailing edge on the downstream side of the airflow blown by the tail rotor. A tail gearbox is arranged in the tunnel and is able to rotationally drive the tail rotor. A rotating transmission shaft connects the main gearbox to the tail gearbox. The transmission shaft passes in the vicinity of the trailing edge of the tunnel.

Abstract: A variable-pitch multi-blade rotor for use as the anti-torque rear rotor of a rotating wing aircraft has a rotor with a central shaft rotated about a central axis, a hub constrained to rotate with the central shaft about the central axis, blades distributed around the central axis with each blade being connected to the central shaft by a twistable element, a pitch control disk for the blades which is constrained to rotate with the central shaft but free to slide axially relative to the central shaft, and a member for controlling the sliding of the pitch control disk along the central shaft. Each blade root is secured to a transverse thrust and pitch control lever forming a yoke having one end hinged to the hub and another end hinged to the pitch control disk.

Abstract: The landing gear for an aerodyne, and especially for a helicopter (H), is of the type including lateral members (4) for contact with the ground, such as skids, skis, floats or similar members. The members (4) are linked to the fuselage of the aerodyne (H) by at least two crosspieces (2, 3) of composite material. The crosspieces are produced in a laminated material having high elastic absorption capacity. They have a sharply curved shape in the area of their central parts by which they are linked to the fuselage of the aerodyne (H), the link (5) between each of the crosspieces (2, 3) and the fuselage being a link with longitudinal embedding with respect to the aerodyne. The lateral members (4) for contact with the ground are linked to the crosspieces (2, 3) by means of articulation (17, 18) which allow large deformations of the crosspieces (2, 3) without torsion of the lateral members (4).

Abstract: A device for the adjustment of the maneuver forces of movable members of an aircraft.

Abstract: A device of retractable stops for the blades of articulated rotors for giroplanes, which includes a stationary stop 20 with a finger 22 radially converging towards the exterior and externally radially protruding on the external spar 9 of the articulation means 7 of each blade on the hub 3, as well as a movable stop 21 with a receptacle 36 resiliently returned by a return device 45 in a position fit around the finger, but disengaged from the finger by centrifugal force when the rotation speed of the blades is higher than a set value. The invention therefore provides absolute stops in flapping and drag in the "ground" position and sharp stops in the flight position. One advantageous application is for helicopter rotors.

Abstract: The invention relates to a rotor head having interblade ties with resilient return in lag and with built-in damping, wherein each tie is connected, to each of the two rotor blades joined by it, by articulation means comprising a main ball retained on a member connecting a blade to the hub and centered on or in immediate proximity to the pitch change axis of the corresponding blade.A single main ball may be connected to the adjacent ends of two neighboring ties by a connection member having the shape of a V open towards the hub, or else each tie is connected to a connection member by a respective one of two main balls offset transversely in relation to the pitch change axis of the blade and/or radially along said axis.Application to the main and/or auxiliary rotors of helicopters.

Abstract: The flapping stop device of the invention is intended for a gyroplane rotor comprising a hub (3) to which each blade (22) is connected by retaining and pivoting members (16) having two frames, one (17) of which is fixed to the hub (3) and the other (19) of which, in an internal radial position with respect to the first one, is locked for movement with the root (23) of the blade (22). The internal frame (19) has, projecting radially inwardly, at least one nose piece (29) having a stop surface and defining a convex cylindrical sliding surface (28) on the internal radial face of the frame (19). The nose piece or pieces (29) and the convex surface (28) cooperate respectively with one or more bearing surfaces (34) and a complementary concave surface (33) of a central stop (30) integral with the hub (3) or with the rotor mast (2).

Abstract: The integrated hub-mast (1) of the invention is composed of a tubular single piece body whose hub body forming part (3) is integral, on the side of its end end opposite the mast (2), with a reinforcing ring (5) and in which openings (6) are pierced. For each blade of the rotor, a stratified spherical stop (16) is fixed against the ring (5) and is retained in the hub body (3) and this stop (16) is also fixed to the ends integral to the hub body (3) of the lower (24) and upper (25) branches of a forked fastening part (23) connecting the blade (22) to the stop (16), the lower branch (24) passing through an opening (6) in the hub (3). A central flapping stop (30) is mounted on a support (31), in the hub-mast (1), which carries external fastenings for coupling to the resilient drag return and damping members of the blade.