Aerospatiale Societe Nationale Industrielle

Eurocopter

Eurocopter France

Societe Nationale Industrielle Et Aerospatiale

Aerospatiale Nationale Insustrielle

Bruno Robert Guimbal

Jean-Pierre Jalaguier

Rene L Mouille

Elio Zoppitelli

Jean-Luc M Leman

Marc Anglade

Michel A Hancart

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

Variable pitch rotor blade for shrouded rotors, in particular helicopter rotors

The annular cushion,interposed between the fixed housing,and a swiveling exterior surface,in the shape of a spherical sector with relatively large radius of curvature of the bearing block,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,and the swiveling exterior surface of the bearing block,this annular cushion consisting of two rings,spaced apart and arranged on each side of the transverse median plane of the swiveling exterior surface. The fixed housing also comprises adjustment means,of the axial engagement amplitude of the cover,on the body,of said fixed housing, and tightening adjustment means of the fixing screws, enabling in this way the radial compression of said relatively rigid annular cushion,to be adjusted on said swiveling exterior surface of the bearing block

Device for coaxially coupling two shafts, especially for a helicopter

The bidirectional suspension comprises, in order to connect the transmission gearbox to the fuselage, two parallel connecting rods which are articulated to lateral supports on opposite sides of the base of this gearbox and on the same side of the latter as far as their articulations to two transverse levers, each articulated to the fuselage about an axis perpendicular to the connecting rods and substantially parallel to the axis of the rotor. Each of the two levers lie substantially in the extension of the other and are connected to each other via their adjacent ends. Means providing elastic linkages in the direction of the connecting rods and in the direction perpendicular to the latter connect the fuselage to the gearbox and may consist of a single elastic pad.

Bidirectional antivibration suspension device for helicopter rotor

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.

Vibration damping apparatus for helicopter rotor

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.

Plastics multi-blade variable-pitch rotor

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.

Tail rotor anti-torque system for a helicopter

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.

Variable-pitch multi-blade rotor, in particular for the rear anti-torque

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).

Landing gear for an aerodyne, with arches in composite material

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

Device for the adjustment of the maneuver forces of movable members of

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.

Device of retractable stops for rotor blades of giroplanes, and rotor

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.

Rotary-wing aircraft rotor head having resilient-return interblade ties

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).

Flapping stop device for a gyroplane rotor

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.

Growing community of inventors

Les Milles, France

Bruno Robert Guimbal