Airbus Operations (s.a.s.)

Airbus France

Airbus Operations Gmbh

François Rouyre

Samuel Burgunder

Olivier Piuzzi

Pascal Chaumel

Alain Depeige

Francis Dazet

Jacques Roux

Jérome Antypas

Christian Cros

Daniela Simon

Gerard Peyssi

Sebastien Menard

Sébastien Menard

Loic Le Lay

Gérard Peyssi

Method and system of simple, precise, rapid and automatic control to verify fit between a manufactured device and its digital mock-up modelling it beforehand. The system includes a scanner configured to produce a three-dimensional cloud of points representative of the device, as well as a processor and a memory configured to superpose the cloud of points on the digital mock-up, coordinate the cloud of points with polychrome images captured during the scanning of the device and stored in a memory, disperse the cloud of points into several sets of points, each set of points corresponding to an object identified in the polychrome images, establish a correspondence between the sets of points and nodes of a treelike structure identifying the digital mock-up, and evaluate a fit between the cloud of points and the digital mock-up by analyzing the correspondence between the sets of points and the nodes of the treelike structure.

Control of a device with respect to its numerical model

A joint assembly in an aircraft connecting a belly fairing to the fuselage of the aircraft. The belly fairing has a sewing angle connected to a main belly fairing section, while the fuselage has a fuselage skin with an exterior and an interior. The joint assembly includes a sewing angle with a flange connected to the fuselage skin exterior at a fixation zone of the fuselage skin, with the fixation zone being overlapped by the flange where it is connected thereto. The joint assembly further includes a stringer connected to the fuselage skin interior and overlapping the fixation zone. This joint assembly is less susceptible to vibrations. The disclosure herein also pertains to a method of providing such a joint assembly.

Joint assembly and method connecting an aircraft belly fairing to the fuselage provided with a particularly positioned stringer

The invention relates to a device for the attachment of an object to another object comprising an interface insert () intended to be positioned between said objects and comprising a chamber (). One of the two objects is attached to the insert (), and the other object is attached to a mobile connecting element () inserted into said chamber (). A liquid that is capable of solidifying is injected into the chamber () of the insert (). As long as the liquid () has not solidified, the relative position between the two objects may be adjusted. Once this position is considered to be satisfactory, the solidification of the liquid () will permit the two objects to be set one in relation to the other.

Device for the attachment of an object by injection of liquid

An aircraft nacelle comprising an air intake configured to channel an air flow in the direction of an engine assembly which comprises a fan with an axis of rotation, said air intake comprising, according to a flow direction of the air flow, a lip with a leading edge and an internal conduit which extends said lip towards the fan, wherein the air intake comprises a plurality of protrusions distributed over the circumference of the air intake and following each protrusion, a concave form configured in order to achieve compression of the air flow.

Aircraft nacelle comprising an improved air intake

The invention relates to a method for the remote inspection of a structure, comprising the following operations: The invention also relates to a system for implementing the method, comprising an imaging device () that can be installed in the vicinity of the area of the structure to be inspected (), and an image-processing device () located remotely from the imaging device () in order to generate a 3D image from the images captured by the camera ().

Method and system for the remote inspection of a structure

The invention relates to a mounting () for holding an elongate object () such as an electric cable in position relative to a structure (). According to the invention, said mounting comprises: two parts for connecting the mounting to the structure () each of which has a bearing surface () suitable for resting each side of the structure against a bearing surface () of the structure, said two connecting parts being assembled together by a clamping means (), at least one supporting part () suitable for maintaining said elongate object () via a holding means (), characterized in that said mounting part is provided in the form of a substantially cylindrical railing (), secured to a connecting part.

Mounting for holding elongate objects in position relative to a structure

An insulation blanket to be connected at the inside surface () of an aircraft fuselage, includes at least one opening that allows a through element () to pass, at which is connected a sealing device, characterized in that this sealing device includes a core () that is combined with a body () that extends over a closed contour delimiting the opening (), with the core () having a spring action that tends to flatten the body () against the through element () over at least a part of the circumference of the opening ().

Sealing device between a cross member and insulation blanket provided at an aircraft fuselage

Devices associated with an interface that is advantageous for the customized attachment of pieces of furniture to the floor of an aircraft. The interface includes rails extending longitudinally in the aircraft cabin, able to receive anchoring devices for connecting the furniture elements to these rails. The anchoring devices include axial and radial claw clamping devices which are associated together in pairs and operated together in pairs by a single and same lever ().

Device for attaching a piece of furniture to the floor of an aircraft

A block including at least one glass ply at least partially covering an outer surface of a core made from composite material. A method for reinforcing a block made from a composite material, including a glass ply placed in a mold, such as to cover the base of the mold; the block is positioned in the mold; the edges of the glass ply are folded such that the glass ply is molded to the outer edge of the block; the mold is closed with a cover; the block housed inside the mold is cured in an oven such as to polymerize the glass ply; and the glass-ply-covered block is recovered.

Reinforced block made from composite material and method for reinforcing a composite block

A device according to the present invention comprises: Application to the analysis of damage observed in an aircraft during inspection thereof.

Diagnostic tool for repairing aircraft and method of using such a tool

The invention concerns a wall () of vertical partitioning for a ventral cowling of an aircraft including a plurality of vertical panels (), each panel being linked to an adjacent panel by a vertical post (). At least one exterior panel () is mounted in a fixed manner on at least one associated vertical post (). The upper end of said vertical post is fitted with a means of fastening in transverse rotation intended to be fixed to the structure () of an aircraft, the means of fastening in transverse rotation being capable of allowing the displacement (Dy) of the structure of the aircraft with respect to the fixed partitioning wall. It is also possible for at least one intermediary panel () to be mounted floating on at least one associated vertical post (), in such a way as to have a deflection parallel and perpendicular to the adjacent panels.

Aircraft ventral fairing partition wall and aircraft equipped with a ventral fairing

A shim adapted for positioning on the upper surface of at least one wing of an aircraft. The shim restores an aerodynamic profile of the wing at the position of a zone of transition between structure fastening the wing to the fuselage of the aircraft and the upper surface of the aircraft. The shim enables a seal to run from the fastening structure to the upper surface of the wing, in eliminating the zones at which the seal may break open. An aircraft provided with such a shim is also disclosed.

Transition shim between structure for fastening a wing to a fuselage of an aircraft, and aircraft having such a shim

In an aircraft comprising a fuselage and a belly fairing, the fairing is made of two independent parts. For example, a first part of the fairing comprises a front section, a central section and a first portion of a rear section. A second part of the fairing comprises a second portion of the rear section. The second part can shift relative to the first part of the fairing. Also disclosed is a belly fairing for aircraft comprising two independent parts.

Aircraft provided with a belly fairing, and corresponding belly fairing

An aircraft landing gear door comprises a rigid one-piece panel (), hinged onto the aircraft structure by arms (). The panel () is installed such that it pivots on the arms () in order to prevent any risk of contact between the panel () and the wheels () as the door opens and closes when the landing gear is extended, and a jack () automatically varies the angle &#x3a6; formed between these two parts, according to a predetermined kinematic law. A control system () automatically controls the jack () as a function of the jack () being actuated to control opening and closing of the door.

Landing gear door with controlled kinematic control

The door comprises a panel () formed from two rigid parts () hinged to each other edge to edge. A first part () of these two parts is connected to the aircraft structure through a pivot pin () and a control means () is inserted between this first part () and the structure. A kinematic control mechanism () connects the two parts () to the aircraft structure, so as to enable progressive and controlled folding of these parts when opening the door. Thus the landing gear door can be opened and closed without any risk of it coming into contact with the wheels when the landing gear is extended.

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Cornebarrieu, France

François Rouyre