Airbus Operations (s.a.s.)

Rolls-Royce Corporation

Airbus Operations Gmbh

Stéphane Dida

Alain Porte

Laurent Lafont

Matthieu Fargues

Jacques Lalane

Jérôme Colmagro

Frédéric Chelin

Julian Mark Reed

Martial Marro

Olivier Dubois

Jacky Puech

Arnaud Hormiere

Julien Moulis

Emeric Chancerelle

Jérome Colmagro

Julien Allain

Caroline Halliday

David Wattam

Colin Woodward

The pylon, intended to support a flying vehicle engine, includes a primary structure formed by at least one longeron and one panel, the panel including at least one end part provided with a notch, the longeron being provided with an end adapted to be positioned in the notch, the panel and the longeron being assembled by welding a part of the end to a part of the notch. A welded primary structure enables minimization of the blanks of parts associated with the longerons and with the panels by avoiding having recourse to the production of edges.

Pylon including a primary structure formed of at least one longeron and one panel assembled by welding

An assembly for an aircraft and comprising a wing comprising an airfoil box partly produced using a front spar, a mounting pylon arranged under the wing and comprising a primary structure formed as a primary box having a top spar extending at least partly under the airfoil box and having a slit, a bottom spar, lateral panels and a transverse reinforcing fixing rib, of which a bottom part is housed and fixed inside the primary structure and of which a top part passes through the slit. A fixing arrangement fixes the top part to the front spar. The fixing arrangement comprises a plurality of fixing bolts, where each fixing bolt fixes the top part to the front spar and has its axis at right angles to the fixing rib. Such an assembly allows the mounting pylon primary structure to be as close as possible to the wing.

Assembly for aircraft comprising a primary mounting pylon structure fixed to an airfoil box using a bolted link

The invention relates to a wall made from a composite material comprising at least two layers of fibers (') embedded in a resin matrix, a crack being able to spread in said wall in a direction of propagation, characterized in that it comprises at least one longilineal metal reinforcement (), oriented in a direction secant to the direction of propagation, inserted between two layers of fibers (&#x2032;) of the wall.

Wall made from a composite material reinforced so as to limit the spread of a crack in a direction

An aircraft nacelle with a connecting device between a first conduit of an air intake and a second conduit of a motor, both conduits being arranged end-to-end, the connecting device including an annular flange connected to the air intake, an annular flange connected to the motor pressed against annular flange of the air intake, the flanges extending in a plane perpendicular to the longitudinal axis of the nacelle; bolt holes formed in annular flanges and disposed plumb to one another; and connecting elements located in bolt holes, for connecting the annular flanges, wherein at least one flange includes at least one opening interposed between a bolt hole and junction zone of the flange and/or between a bolt hole and outer edge of the flange.

Fastening device particularly suitable for the fastening between an air intake and an engine of an aircraft nacelle

A fastening device includes a first annular flange connected to an air intake, a second annular flange connected to a powerplant pressed against the second annular flange and fastening elements that allow the annular flanges to be linked. For at least a first fastening element, a blade is fitted between the first fastening element and the first annular flange, the blade including at least a central part linked to the first fastening element, radially mobile relative to the first annular flange, and at least one offset part for which at least radial centripetal displacement is limited relative to the first annular flange, the central part and the offset part being offset relative to one another along the direction of the circumference.

An acoustic treatment panel includes an acoustically resistive layer that defines a surface of an aircraft that is in contact with an aerodynamic stream, a reflective layer () between which are arranged at least one alveolar structure () with a number of cells dedicated to the acoustic treatment, and de-icing cavities () in which hot air circulates in contact with the acoustically resistive layer to ensure a frost treatment, characterized in that it includes holes for supplying de-icing cavities () with hot air and in that the capacity to treat the frost is adjusted along the zones by modifying the open surface ratio that results from the holes.

Panel for an air intake of an aircraft nacelle that ensures optimized acoustic treatment and frost treatment

Growing community of inventors

Fontenilles, France

Stéphane Dida