Airbus Operations (s.a.s.)

Airbus Operations Gmbh

Fabien Raison

Stephane Romani

Stephane Machado

Herve Marche

Jacques Herve Marche

Laurent Bel

Emmanuelle Dumont

Laurent Bell

Stéphane Romani

A propulsion system for an aircraft, including a dual-flow turbojet and a mounting structure for mounting this turbojet on the wing surface or on the fuselage of an aircraft. The mounting structure includes an aft aerodynamic fairing including a thermal protection floor to protect the mounting structure from the heat of a primary airstream channelled by an exhaust nozzle of the turbojet, as well as an air inlet provided in a longitudinal aerodynamic wall washed by a secondary airstream of the turbojet and delimiting together with an other similar wall a cavity isolated from the secondary airstream for extracting a cooling airstream from the secondary airstream, and air circulation means fed by the air inlet and having at least one outlet aperture emerging in a space between the thermal protection floor and the exhaust nozzle.

Method for cooling a thermal protection floor of an aft aerodynamic fairing of a structure for mounting an aircraft propulsion system

An aft aerodynamic fairing for a pylon for attaching an aircraft propelling assembly, including a caisson structure, a heat-shield floor, as well as a support structure for this floor comprising linking parts arranged to link two side edges of this floor to the caisson structure. The linking parts of each side edge of the floor are configured so as to allow travelling motion of the side edge relative to the caisson structure in a corresponding direction included in a plane orthogonal to a longitudinal direction of the fairing. The linking parts form a sliding link between the floor and the caisson structure, reducing the stresses induced by the deformations of these elements in use.

Aft aerodynamic fairing with improved thermal resistance for a pylon for attaching an aircraft propelling assembly

An aircraft engine pylon aft aerodynamic fairing includes upper spars, transverse stiffening ribs, lower spars and a trailing edge where the upper spars and lower spars join together. In this fairing, a profiled structure is formed according to a profile open to the outside of the fairing. In a first end portion, the profiled structure comes to be enclosed between an end portion of the lower spars and the ends of at least one transverse stiffening ribs flush with the lower spars. This structure extends between the lower spars and the upper spars over a straight central portion inclined relative to the first end portion, and comes in a second end portion flush against a portion of the upper spars, parallel to the first end.

Aircraft engine pylon AFT aerodynamic fairing

The present invention relates to a method of manufacture of a group of transverse internal stiffening ribs () for an aerodynamic fairing of an engine mounting device, including:

Method of manufacture by superplastic forming and by fishplating of a rib for an aerodynamic fairing of an aircraft engine mounting pylon

The present invention relates to a method of manufacture of a stiffening transverse internal rib () for an aerodynamic fairing of an engine mounting device, including:

An engine attachment pylon for an aircraft, including a rigid structure including a box formed by one or plural hollow segments. The section of at least one hollow segment is circular or elliptical in shape.

Aircraft engine attachment pylon comprising a box with a circular or elliptical shaped section

An engine attachment pylon for an aircraft including a rigid structure including a box including an upper spar and a lower spar, connected to each other through two lateral panels. At least one of the upper and lower ends of the web of at least one of the two lateral panels includes at least one assembly cleat projecting sideways from the web towards the outside of the box, and assembled to the spar on which it bears through an attachment mechanism located outside the inner space in the box.

Engine attachment pylon comprising means of fastening spars and panels located outside the inner space in the box

Sail wing aircraft which includes a wing () and at least one propulsion engine (). It includes an upper beam () which is firmly fixed at its front end to a first frame () located on an air inlet () of the propulsion engine and which is in addition firmly fixed at its median part to a second frame () located to the rear of the first frame. The sail wing aircraft includes in addition a pylon () for attachment of the engine onto the fuselage, where the engine is fixed to the pylon ().

Sail wing aircraft which includes an engine mounted on a pylon

A system for attaching an engine to the structure of an aircraft, such as a sail wing aircraft is disclosed. The system includes an upper beam which is firmly fixed at its front end to a first frame mounted on the aircraft structure, and firmly fixed at its median part to a second frame located to the rear of the first frame. The engine is hooked beneath the upper beam. The system is orientated in relation to a longitudinal axis X, a transverse axis Y and a vertical axis Z. Two front engine attachment points are arranged symmetrically on either side of the vertical median plane of the engine. The front attachment points include a shaft which is inclined relative to the Y-direction and to the Z-direction so that they bear the forces along the longitudinal direction and forces which are inclined relative to the Z-direction and Y-direction.

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Plaisance du Touch, France

Fabien Raison