Eurocopter

Eurocopter France

Airbus Helicopters

Artus

Jean Joseph Mondet

Jean-Luc M Leman

Charles Louis

Patrick Quesne

Vincent Scala

Sylvie Jacqueline Garcin

Stephane Mazet

Philippe Maurice Antomarchi

Philippe Almeras

Gilbert Jean Mestre

Serge Louis Roux

St&euml;phane Mazet

Jean-Marc Latorre

Sylvie J Commelin

St&eacute;phane Mazet

Charles Marcel Louis

An abutment mechanism for limiting the flapping of the blades of a rotor (). High abutment members () can be moved into an engagement position by return means () exerting an intrinsic return force (R), and into a disengagement position by a flyweight () exerting a centrifugal force (C) under the effect of the rotor () rotating. At least one magnetic type bistable latch () is in selective engagement with the high abutment members (). When the rotor () is stationary and while it is starting to rotate, an engagement latch () engages with the high abutment member () to prevent it passing from the engagement position towards the disengagement position. At a predetermined centrifugal force threshold, the engagement of the engagement latch () with the high abutment member () is broken, and the high abutment member () quickly passes into the disengagement position.

Rotocraft rotor including a flapping abutment mechanism for blades hinged on a hub of the rotor

The present invention relates to an electromechanical motor (M) provided with an actuator (A) having an outer casing (--) surrounding a stator (-) possessing a coil (). The rotor () is also disposed inside the stator (-). The invention is remarkable in that the actuator has two distinct and independent outlets (S, S) capable respectively of actuating, one after the other, first and second transmissions (C, C).

Two-outlet electromechanical motor

A rotorcraft rotor with hinged blades, includes: a hub; a plurality of blades hinged to flap relative to the hub; bottom abutments of the hub, and bottom abutments of the blades suitable for co-operating with the bottom abutments of the hub; and top abutments of the hub, and top abutments of the blades suitable for co-operating with the top abutments of the hub; the top abutments of the hub being movable between a deployed position in which they extend facing the top abutments of the blades, and a retracted position in which they are offset angularly away from the top abutments of the blades. The rotor also includes elements for locking the top abutments of the hub in the deployed position, and inertial means for releasing the top abutments of the hub and for deactivating the locking means.

Rotocraft rotor with hinged blades and lockable retractable flapping abutments

The invention relates to a system for suspending an engine of a rotary wing aircraft. The technical field of the invention is that of manufacturing suspension devices for helicopter engines. The invention consists in a device for suspending an engine () to a rotary aircraft airframe (), which device includes a deformable structure () interconnecting two attachment zones () of the device.

Suspension system for a rotary wing aircraft engine

On the rotor, between each blade and the member for linking with the hub, an electrical connecting cable comprises a first section of which one part is held above that one of the two blade pins which is the pivot pin about which the blade can be folded by pivoting, once the other blade pin has been removed. This holding is provided by a cradle formed in a cable support connected to the pivot pin, and by a collar articulated to one edge of the cradle and which can be folded down into the closed position onto the opposite edge of the cradle, to which this collar can be connected detachably by at least one detachable retaining element. The section of cable is manually released from the collar and from the cradle before the removal of the removable pin, which precedes folding, so that this section of cable deforms naturally, following the pivoting of the blade. Whilst the blade has been deployed, the releasable part of this section is once again retained in the cradle above the pivot pin by the closing of the collar.

Rotary-wing aircraft rotors with manually folding blades and electrical connection installation

On the rotor, between each blade integral with its folding mount and the member for linking with the hub, an electrical connecting cable comprises a first section of which one part is held, in any position of the blade about the folding axis, above the mount and the radially outer end of the link member on which the mount pivots, in an off-centered position with respect to the folding axis and on the side towards which the blade is designed to be folded. This holding is provided by a cable support tied to the folding pivot and on which an arm, receiving the held part of this section of cable, is mounted in cantilever manner on the folding side.

Rotary-wing aircraft rotors with automatically folding blades and electrical connection installation for the blades

The present invention relates to a device for locking the pitch of the blades of a main rotor of a rotary-wing aircraft in which each blade is firstly rotated about an axis of rotation of the rotor by a rotor mast and is secondly constrained to pivot about a longitudinal pitch axis of the blade together with a pitch lever which is controlled by a pitch link connected to a rotary plate rotating with the rotor mast and belonging to a cyclic swash plate mechanism in which the rotary plate is rotatably mounted on a non-rotary plate capable of sliding axially along said rotor mast and of tilting in any direction relative to the rotor mast under the drive of at least three servo-controls each comprising a body fixed on a support secured to the aircraft and a rod having a free end secured to the non-rotary plate. The device includes immobilization means for holding the rod of each of the servo-controls relative to the corresponding body so as to lock the blades in a predetermined pitch position.

Blade pitch locking device for a main rotor of a rotary-wing aircraft

The locking device comprises, for each blade, at least one first subassembly with a fork for locking a finger, one of the fork and finger pivoting on a chassis attached laterally to the hub between the linking members of two neighboring blades, the other element being fixed to the linking member and projecting laterally towards the other linking member so that the pivoting element can be moved between a position in which it is engaged over the finger for locking the blade at least in terms of pitch, and a disengaged position for unlocking.

Device for locking the blades of a rotor, at least in terms of pitch

The device includes anti-cone stops projecting outward from at least two coaxial rings that can rotate about the rotor axis on the top face of the hub. Flyweights are each mechanically joined to one of the rings by a mechanism 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 against elastic mechanisms returning them to the 'ground' position.

Device with retractable double anti-cone stops ring, and rotor head

The folding device comprises a fitting pivoting on a cuff about a folding axis which is offset laterally thanks to two lateral bearings of the fitting journal-mounted about bushings retained in lateral devises of the cuff and which are coaxial about the axis by pegs for centering a maneuvering actuator for maneuvering the fitting and the blade about the folding axis.

Device for folding a rotorcraft rotor blade

The installation links a supply conductor to an electrical device for de-icing a blade using at least one cable with a first stretch linked to the supply conductor by a connector and to a second stretch with an overhead hook in the form of flattened half loop, itself linked to the device for de-icing the blade by a second connector fitted on the blade, possibly via a straight and flat third stretch and a second overhead hook. The first hook is of nonscreened structure, with an elongate part of substantially flattened rectangular transverse section and with a concavity pointing towards a device for retaining and articulating the blade on a hub.

De-icing connection installation for rotorcraft rotor

The installation for removing electrostatic charge and passing lightning current between a conductor of each blade of the rotor and a metallic part of the hub comprises at least one conductive member integral with the member for linking the blade to the hub in its angular deflections, and in electrical continuity with the conductor of the blade and held elastically in permanent contact with a conductive terminal integral with the hub and in electrical continuity therewith.

Installation for affording electrical continuity for rotorcraft rotor

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.

Growing community of inventors

Pelissanne, France

Jean Joseph Mondet