Airbus Helicopters

Eurocopter

Eurocopter France

Jacques Joseph Gaffiero

Andre Amari

Laurent Bianchi

Jean-Romain Bihel

Daniel Brunner

Jean-Luc Christian Besse

Michel Morant

François Lorin De La Grandmaison

Olivier Ardesi

Benedicte Rinaldi

Jean-Francois Piccone

Christophe Serr

Guillaume Dulac

Francois Marchand

Nicolas Isidore

Bernard Michel

Didier Trallero

David Broucke

Jean-François Hirsch

Francois Lorin De La Grandmaison

Jean-Patrick Boderlique

Alain Charreyre

Claude Laloi

Philippe Tardieu

Cédric Lanouette

André Amari

Bénédicte Rinaldi

Jean-François Piccone

François Marchand

A method of fabricating a filler body for a blade of a rotor. In addition, such a method comprises a succession of steps of adding material layer by layer, each step consisting in making a new layer of material on a preceding layer of material made in the preceding step, at least one of the steps consisting in making an openwork layer of material presenting a plurality of openings, the succession of steps of adding material layer by layer generating openwork layers of material, each having a closed outline, the respective closed outlines of the openwork layers of material touching mutually in pairs and forming a closed envelope of the filler body for the blade.

Method of fabricating a rotor blade filler body, and a rotor blade filler body comprising at least one cellular assembly having closed cells

A rotorcraft comprising a fuselage, a single main rotor, and a first propeller and a second propeller. The rotorcraft has an adjustment system configured, at least during a stage of hovering flight, to position the first propeller in a first low speed configuration in order to exert a first thrust including a first horizontal component and a first vertical component, the adjustment system being configured, at least during the stage of hovering flight, to position the second propeller in a second low speed configuration so as to exert a second thrust comprising a second horizontal component and a second vertical component.

Rotorcraft having a rotary wing and at least two propellers, and a method applied by the rotorcraft

A method of fabricating a blade spar that includes transversely at least one arrangement. A pressure-side mold and a suction-side mold are defined for each arrangement that is to be fabricated. Each mold includes at least one removable slide and a base. Each slide is then removed from a mold and the tape segments of a hank are laid by a fiber-placement method on each mold. Each mold is closed by putting the slides into place on the mold. During a finalizing step, the molds are juxtaposed and the spar is heated.

Method of fabricating a spar for a blade, a method of fabricating a blade, and a blade

The present invention relates to a deposition head provided with an assemblage comprising a of impregnated fibers arranged against a backing tape. The deposition head includes a slide and a movement actuator connected to the slide to move the slide in translation from a high position to a low position, said slide carrying a peeling roller, said backing tape extending over a circular arc against the peeling roller, said low position being configured so that said peeling roller presses said tape of impregnated fibers against a deposition surface only in the low position of the slide, said circular arc occupying a first angle in the low position of the slide and a second angle in the high position of the slide, said first angle being greater than said second angle.

Deposition head for depositing an impregnated fiber tape, and a device for placing such a tape

A monolithic blade of a rotorcraft rotor, the blade comprising at least locally an airfoil zone having a pressure side face and a suction side face. The invention is remarkable in that the blade has a root zone including a finger with a spherical bearing surface arranged at a root end of the blade, a recess suitable for receiving a laminated spherical bearing, and a flexible portion having a preferred direction of deformation in bending about a flapping axis of the blade, the flexible portion being arranged between the finger and the recess.

Monolithic blade, a rotorcraft rotor fitted with such a monolithic blade, and an associated rotorcraft

A method of fabricating a spar for a blade, which spar includes transversely at least one arrangement. A male former is defined for each arrangement that is to be fabricated and each arrangement is subdivided into a pressure-side subassembly and a suction-side subassembly, each comprising a plurality of hanks, each hank comprising a plurality of U-shaped tape segments stacked on one another. Each subassembly of an arrangement is fabricated outside a mold for fabricating the blade on a single former adapted to that particular arrangement, fabrication being by stacking tape segments on the former using a fiber placement method implemented by a placement head.

Method of fabricating a spar for a blade, and a method of fabricating a blade

A device () for folding a blade (), the device comprising a fitting () and a cuff () connected to said fitting (). The fitting () has at least one horizontal pin axis () perpendicular to a radial direction (AX) and a clevis () axially offset relative to the horizontal pin axis () in the radial direction (AX). The cuff () has an insert () inserted in said clevis (), a vertical pin () passing through said clevis () and said insert (). The cuff () includes at least one horizontal fastener pin axis () axially offset relative to said insert () along the radial direction (AX), at least one lateral arm () connects said horizontal pin axis () to said fastener pin axis ().

Device for folding a blade, a blade, and an aircraft

The invention provides a rotary-wing aircraft rotor fitted with a connector device for connecting electrical power between a hub () and blades () of said rotor. For each of the blades (), a wired connection () provides an electrical connection between the hub () and the blade (). A guide path () holds the wired connection () in shape and guides it under tension to move over itself, accompanying the pivoting movement of the blade root ().

Aircraft rotor fitted with a connector device for connecting electrical power between a hub and blades of the rotor

A blade () provided with a fitting () for fastening to a hub and with an airfoil element () having a spar () extending spanwise from an attachment zone () towards a distal zone (), said attachment zone () surrounding a centrifugal force transmission bushing () that is connected to said fitting () by a through pin (). The blade comprises a twisting force transmission member () provided with a first half-shell () and with a second half-shell () that together surround said attachment zone (), each half-shell () having a perforated first portion (&#x2033;) giving visual access to said bushing () when said airfoil element is removed from the fitting, and a second portion (&#x2033;) co-operating with a torsion box () surrounding said distal zone (), said transmission member () being secured to said fitting in rotation about a torsion axis (AX) of the blade ().

Blade and method of fabricating said blade

A rotorcraft rotor fitted with a device for damping lead-lag oscillations of the blades () of the rotor. The blades () are hinge-mounted on a rotary hub () of the rotor via respective sleeves (). The damper device comprises a set of dampers (), each individually housed in a respective one of said sleeves () and deformable between two fastening points (), one with the sleeve and the other with an engagement member () for engaging the hub () via a linkage (). For each of the sleeve (), the damper () housed by a given sleeve () is in hinged engagement with the linkage () via a lever arm () hinged to the sleeve ().

Rotorcraft rotor fitted with lead-lag dampers housed in sleeves connecting blades to a hub of the rotor

A rotor blade () provided with an outer covering () and with at least one load take-up spar () associated with at least one pin-receiving bushing (). Each spar () is a compartmentalized spar comprising centrifugal force take-up means () incorporated within a twisting stress take-up casing (), said centrifugal force take-up means () comprising at least two boxes (), each having said pin-receiving bushing () of the spar () passing therethrough, each box () including a closed retention belt () extending in the spanwise direction of the blade, the retention belt () of one box () surrounding the retention belt () of another box (), each retention belt () being provided with unidirectional fibers () wound around said pin-receiving bushing (), said casing () being provided with inclined fibers () presenting an angle relative to said unidirectional fibers ().

Rotor blade and an aircraft

Method for fabricating a reinforcing coating for a part made of composite material. Pre-impregnated reinforcing fibers are used in the form of slivers and said slivers are laid on the part in two layers of longitudinal slivers by being placed thereon. This fabrication makes provision for using an angular orientation for the slivers of each layer respectively of 0&#xb0; and of some other angle relative to said determined direction of the solid body for covering using an interlaced pattern type that gives layer crossing lines parallel to a longitudinal axis of the solid body for covering, which pattern type is selected to form interlacing patterns that limit the number of layer crossing lines along the longitudinal axis of the solid body for covering to a single line.

Fabricating parts with composite material reinforcement having a single crossing line

The present invention relates to a rotorcraft rotor blade () that comprises at least one tiltable trailing-edge flap (), said flap () being suitable for pivoting about a virtual hinge axis (Y') extending substantially in the span direction of said blade () and of said flap (). The blade () is remarkable in that the flap () is provided with at least two fastener ball joints (), each provided with an inner cage () together with an outer cage () and a first pin () that is also secured to said flap (), the first pins () of the fastener ball joints () being perpendicular to the virtual pivot axis (Y&#x2032;) of the flap (). In addition, the blade () is provided at its trailing edge (BF) with a fastener tongue () provided with ball-receiving sockets (), the outer cages () of the fastener ball joints () being secured to the ball-receiving sockets ().

Rotorcraft blade provided with a tiltable flap and a fastener tongue

The present invention relates to a rotorcraft rotor blade () having at least one trailing edge flap () that is tiltable, the flap () being suitable for pivoting about a virtual hinge axis (Y') extending substantially along the span of the blade () and of the flap (). The blade () is remarkable in that the flap () is provided with at least one main ball joint () having an inner cage () and an outer cage (), and a first shaft () secured to the flap (), the front portion (&#x2032;) of the outer cage () of the main ball joint () being connected to a linear actuator () which is arranged in the blade () and which enables the flap () to be pivoted, the first shaft () of the main ball joint () extending substantially perpendicularly to the virtual hinge axis (Y&#x2032;) about which the flap () pivots.

Growing community of inventors

Paris, France

Jacques Joseph Gaffiero