Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: The invention relates to a device for the attachment of an object to another object comprising an interface insert (1) intended to be positioned between said objects and comprising a chamber (3). One of the two objects is attached to the insert (1), and the other object is attached to a mobile connecting element (2) inserted into said chamber (3). A liquid that is capable of solidifying is injected into the chamber (3) of the insert (1). As long as the liquid (4) 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 (4) will permit the two objects to be set one in relation to the other.

Abstract: 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.

Abstract: 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.

Abstract: The invention relates to a method for the remote inspection of a structure, comprising the following operations: producing a 3D image of an area of the structure to be inspected, superimposing said 3D image with a previously stored digital model of the structure, geographically locating the area of the structure to be inspected on the structure model, and inspecting the area of the structure to be inspected on the 3D image superimposed with the digital model. The invention also relates to a system for implementing the method, comprising an imaging device (10) that can be installed in the vicinity of the area of the structure to be inspected (2), and an image-processing device (6) located remotely from the imaging device (10) in order to generate a 3D image from the images captured by the camera (11).

Abstract: 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.

Abstract: The invention relates to a mounting (1) for holding an elongate object (13) such as an electric cable in position relative to a structure (12). According to the invention, said mounting comprises: two parts for connecting the mounting to the structure (2, 3, 21, 22) each of which has a bearing surface (2a, 3a, 21a, 22a) suitable for resting each side of the structure against a bearing surface (12a, 12b) of the structure, said two connecting parts being assembled together by a clamping means (7, 8, 10), at least one supporting part (4, 23, 24) suitable for maintaining said elongate object (13) via a holding means (50, 31, 37, 69), characterized in that said mounting part is provided in the form of a substantially cylindrical railing (23, 24), secured to a connecting part.

Abstract: The invention relates to a device for the attachment of an object to another object comprising an interface insert (1) intended to be positioned between said objects and comprising a chamber (3). One of the two objects is attached to the insert (1), and the other object is attached to a mobile connecting element (2) inserted into said chamber (3). A liquid that is capable of solidifying is injected into the chamber (3) of the insert (1). As long as the liquid (4) 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 (4) will permit the two objects to be set one in relation to the other.

Abstract: An insulation blanket to be connected at the inside surface (16) of an aircraft fuselage, includes at least one opening that allows a through element (20) to pass, at which is connected a sealing device, characterized in that this sealing device includes a core (28) that is combined with a body (30) that extends over a closed contour delimiting the opening (26), with the core (28) having a spring action that tends to flatten the body (30) against the through element (20) over at least a part of the circumference of the opening (26).

Abstract: 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 (58, 95).

Abstract: According to one embodiment, a modular aircraft includes a propulsion module dedicated to flight, combining avionic equipment—wing structures assembly, flight deck, engines, tail unit—and a module dedicated to the carriage of passengers and/or goods. These modules include external cells extending longitudinally along a main axis and having tubular end parts of the same outline in the region of two disconnectable-coupling structures, one axial-coupling structure for keeping an end face of the propulsion module against an end face of the carriage module, and one radial-coupling structure for keeping an end face of the propulsion module against an end face of the carriage module. The wing structures assembly of the propulsion module includes two wing structures having opposite sweeps which are connected at the end and by a longitudinal connecting spar.

Abstract: 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.

Abstract: A device according to the present invention comprises: a central unit (8) having access to a database (18) in which there are stored not only information on the aircraft fleet to be managed but also an aircraft repair manual, this central unit (8) having means of communicating with the outside, and in particular with a technical center (16) of at least one aircraft manufacturer, at least one portable device equipped with visual display means as well as with means of wireless communication between the said portable device and the central unit (8). Application to the analysis of damage observed in an aircraft during inspection thereof.

Abstract: The invention relates to a mounting (1) for holding an elongate object (13) such as an electric cable in position relative to a structure (12). According to the invention, said mounting comprises: two parts for connecting the mounting to the structure (2, 3, 21, 22) each of which has a bearing surface (2a, 3a, 21a, 22a) suitable for resting each side of the structure against a bearing surface (12a, 12b) of the structure, said two connecting parts being assembled together by a clamping means (7, 8, 10), at least one supporting part (4, 23, 24) suitable for maintaining said elongate object (13) via a holding means (50, 31, 37, 69), characterised in that said mounting part is provided in the form of a substantially cylindrical railing (23, 24), secured to a connecting part.

Abstract: The invention relates to a method for the remote inspection of a structure, comprising the following operations: producing a 3D image of an area of the structure to be inspected, superimposing said 3D image with a previously stored digital model of the structure, geographically locating the area of the structure to be inspected on the structure model, and inspecting the area of the structure to be inspected on the 3D image superimposed with the digital model. The invention also relates to a system for implementing the method, comprising an imaging device (10) that can be installed in the vicinity of the area of the structure to be inspected (2), and an image-processing device (6) located remotely from the imaging device (10) in order to generate a 3D image from the images captured by the camera (11).

Abstract: An insulation blanket to be connected at the inside surface (16) of an aircraft fuselage, includes at least one opening that allows a through element (20) to pass, at which is connected a sealing device, characterized in that this sealing device includes a core (28) that is combined with a body (30) that extends over a closed contour delimiting the opening (26), with the core (28) having a spring action that tends to flatten the body (30) against the through element (20) over at least a part of the circumference of the opening (26).

Abstract: The invention concerns a wall (10) of vertical partitioning for a ventral cowling of an aircraft including a plurality of vertical panels (11, 12, 12?, 13, 13?), each panel being linked to an adjacent panel by a vertical post (14, 15, 16). At least one exterior panel (13, 13?) is mounted in a fixed manner on at least one associated vertical post (14, 16). The upper end of said vertical post is fitted with a means of fastening in transverse rotation intended to be fixed to the structure (8) 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 (12, 12?) to be mounted floating on at least one associated vertical post (15, 16), in such a way as to have a deflection parallel and perpendicular to the adjacent panels.

Abstract: 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 (58, 95).