Abstract: An aircraft fuselage element being a one-piece component, and including a closed wall defining an internal volume, an external surface of the wall forming the external skin of the fuselage. The wall has a cross section that includes on a side facing the internal volume a planar central part, a male connecting element at a first edge, and a female connecting element at its other edge, which connecting elements project, each connecting element configured to engage with the corresponding connecting element of another fuselage element placed side by side with the fuselage element to connect these fuselage elements longitudinally to each other, and one of the connecting elements includes a step forming a frame for the fuselage.

Abstract: The invention relates to an engine assembly for aircraft in which the coupling device comprises a fore aerodynamic structure having a cradle equipped with an aerodynamic cowling, the cradle being hinge mounted on the air intake of the engine, and the fan cowls being mounted to move on the cradle so as to be able to occupy an open position as well as a closed position in which they are supported by the air intake and by a thrust reverser. According to the invention, when the cowls are in open position, the cradle adopts a first configuration in which its aft end rests on a span of the engine mounting structure, and when the cowls are in closed position, the cradle, borne by said cowls, adopts a second configuration in which it is lacking any direct mechanical link with the other elements of the engine mounting structure.

Abstract: Embodiments of the disclosure include methods in which locations within an aircraft fuselage are automatically pointed to and marked so that a part may be fastened at each marked location. A mobile assembly includes a video camera that may capture images of the aircraft fuselage. A plurality of predetermined locations may be visualized and verified by a successive implementation of a first image recognition process and a second image recognition process. The mobile assembly may then automatically point to the predetermined locations after each has been identified and mark each predetermined location.

Abstract: A method for the production of a stiffener on a surface of an element that is to be made rigid, whereby at least one of the two is made of a composite material that is not completely polymerized, whereby the stiffener includes—in a transverse direction—two contact zones with the surface between which the stiffener and the element to be made rigid form a cavity that empties out at least one of the ends of the stiffener, includes using a core that is placed in the cavity and removed from the cavity after polymerization. The core has a first part that has a low expansion coefficient to ensure the geometric precision required and at least one second part that has a significant elongation coefficient to make possible the extraction of the part by traction on one of the ends of the second part so as to cause a contraction of its cross-section.

Abstract: A reduction of the multiple costs of manufacture, assembly use, and upkeep connected with the assembly of window frames on aircraft fuselages. To this end, the invention provides a particular shape for the frames connected to the fuselage skin according to a specific assembly method. The shape enables, among other things, the window frames to be fitted onto the skin by means of adhesion and also frames to be dispensed with between the fuselage and the window. In one embodiment, composite material window frame has a wall totally in the shape of a crown that is connected, through co-adhesion, to the inner surface of the fuselage skin, also made of composite material. The skin is cut into a window-receiving opening, and the frame has a T-shaped cross section, wherein the bar of the “T” that forms the crown includes two portions having substantially equal lengths “T.

Abstract: An interface device for a cabin monument, in particular for assembly in an aircraft or spacecraft, including a routing device, a first plurality of interface connection sockets, which are connected to the routing device via a first plurality of connection lines and to which a vehicle interface of the aircraft or spacecraft can be connected. A second plurality of interface connection sockets are provided which are connected to the routing device via a second plurality of connection lines and to which a cabin monument can be connected. The routing device is constructed so as to selectively electrically connect interface connection sockets of the first plurality of interface connection sockets to interface connection sockets of the second plurality of interface connection sockets.

Abstract: An aircraft including: at least one floor cross-member; at least one support carrying the cross-member; and at least one bearing including at least one flexible material and connecting the cross-member to the support.

Abstract: An aircraft having a dihedral wing configuration with a wing fuel tank and a vent system for ventilating the fuel tank, the vent system including a combined vent-surge tank disposed inboard of at least part of the wing fuel tank, a vent fluidically connecting the vent-surge tank to ambient, and a vent line fluidically connecting the upper part of the fuel tank to the combined vent-surge tank, wherein the vent line has its lowest point at the combined vent-surge tank.

Abstract: The invention relates to a method for manufacturing an engine pylon (7) to be mounted between an engine (1) and an aircraft wing (6), said method comprising: mounting a pylon box (8) around a main structure (9), the box having a substantially oblong shape along which an air boundary layer (C) is formed while in flight; mounting at least one vortex generator (2) onto the pylon box such that a thickness (e) of the boundary layer is changed; and previously determining the shape of the pylon on the basis of the changed thickness of the boundary layer and the position of the vortex generators.

Abstract: A device for modifying audio signals to be output within a room is introduced. The device exhibits an input for supplying audio information and a processor unit for modifying the audio information. The device further exhibits at least two outputs for distributing respectively modified audio information. The processor unit is here adapted to modify the audio information in such a way that respective sound sources to be connected to the outputs simulate a linear sound source for outputting the audio information according to the audio signals. The linear sound source is here achieved via the coherent coupling of a plurality of point sound sources, for example loudspeakers.

Abstract: An auxiliary cooling device is configured to be operated outside of an aircraft. The auxiliary cooling device is configured to be connected to an aircraft liquid cooling system which includes a refrigerating device, a coolant supply connection, a coolant discharge connection, and a control device. The auxiliary cooling device includes a cold source that is adapted to cool a coolant down to a desired low temperature, an auxiliary cooling device outlet which is connected to the cold source and connectable to the coolant supply connection. The auxiliary cooling device also includes an auxiliary cooling device inlet which is connected to the cold source and connectable to the coolant discharge connection of the aircraft liquid cooling system.

Abstract: It comprises applying a mould release agent on a compaction tool (1), carrying out its curing and applying a layer with adhesive properties (2) on the mould release agent. It is characterized in that it also comprises extending an aerator blanket (4) along the layer (2) with dimensions larger than the adhesive layer (2), extending a membrane with resilient properties (5) on the entire surface of the tool (1) by applying vacuum to the membrane (5) for compacting the adhesive layer. This method reduces the number of stages required to perform the compaction and avoids the generation of waste materials thus reducing the cost of the process.

Abstract: An end stop device for restraining an ULD from movement across a cargo deck surface of an aircraft includes a main body; and a mounting interface connected to the main body which is configured and arranged to attach the end stop device to the cargo deck by means of a corresponding tie down ring. Each mounting interface includes a tongue-like support plate which is partially protruding below a bottom side of the main body, at least one recess arranged in an area above the support plate, wherein side walls of the recess form a frame-like structure. and a bolt portion extending from the support plate into the recess and partially surrounded by the frame-like structure. The bolt portion is configured to engage the tie down ring in an operation mode where the end stop device is fixed to a tie down ring.

Abstract: The invention relates to a method of producing an overlapping hybrid connection between two or more components. A hybrid connection in the meaning of the invention is characterized by adhesively bonding and producing mechanical spot joint connections between two joining parts, the adhesive layer being arranged in the region of the mechanical joint connections. The method according to the invention is carried out in the following method steps: purposefully removing material from one or more of the components or purposefully applying material to one or more of the components in the region of the lap joint to be produced to form one or more projections, applying adhesive to one or more of the components in the region of the lap joint to be produced, overlapping the components, pressing the components together in the region of the lap joint to press the projections against the overlapping component(s) and producing one or more mechanical spot joint connections on the projections in the overlap region.

Abstract: A method for running a computer application for interfacing with a crew of a vehicle, for example an aircraft, to a corresponding system and to an aircraft including the system. The method reads a removable medium, including the application to be run, by a removable-medium reader with which an on-board running system in the vehicle is equipped, and runs the application by a running mechanism with which the running system is equipped and connected to the removable-medium reader. The running of the application requires permanent recording of data necessary for execution thereof only on the removable medium. As an example, a portable application is used or the running system is booted from an installed operating system provided on the removable medium.

Abstract: An inspection device (300) has an ultrasonic transducer (304) encased in a couplant block (302) mounted in a housing (328). The housing (328) has a pair of encoders (340, 342) mounted thereto. The transducer (304) is mounted to scan perpendicular to the contact surface (306) of the block (302). A coupling block with a PTFE layer on the contact surface is also provided.

Abstract: A deicing device for propfan-type aircraft propulsion unit blades, wherein the propulsion unit includes a turbomachine that drives in rotation at least one rotor including a plurality of blades arranged around an annular crown moving with the blades, which forms with its outer wall part of an outer envelope of the propulsion unit, the outer envelope being subjected to atmospheric conditions outside the propulsion unit, the turbomachine generating a flow of hot gases that exit via an annular vein, which is concentric with the moving annular crown, and defined for part of its surface by the inner wall of the moving annular crown. The deicing device includes: a mechanism capturing thermal energy from the annular vein, within the moving annular part; a mechanism transferring thermal energy towards the rotor blades; and a mechanism distributing the thermal energy onto at least a part of the surface of the blades.

Abstract: An aerodynamic body that can be adjusted relative to a main wing of an aircraft by an adjusting device is provided. A gap between the aerodynamic body and another aerodynamic body or a component of the fuselage or the main wing is formed on one lateral end and said and the gap is variable due to the adjustability of the aerodynamic body. The body features a gap bridge-over device with a shell part that extends along the gap and overlaps the outer shell of the aerodynamic body in the wingspread direction on the front side thereof so that the shell part can be telescopically moved relative to this aerodynamic body in the wingspread direction. An airfoil for an aircraft with a main wing and a plurality of aerodynamic bodies that are arranged adjacent to one another transverse to the chord direction is also provided.

Abstract: The system (1) comprises means for determining the distance at the current time of the target aircraft (B) with respect to the merge waypoint (P0) along its path (TB), this distance being transmitted to calculation means in order to determine the speed control commands which are subsequently applied to the reference aircraft (A) in order for it to carry out the acquisition of the spacing at said merge waypoint (P0).

Abstract: A pressure bulkhead of an aircraft with a fuselage shell and a pressure bulkhead disposed therein preferably in the rear region for forming a fuselage-internal pressure region, which pressure bulkhead is attached on the edge in the interior of the fuselage shell, wherein the pressure bulkhead has a lenticular cross-section and a sandwich construction that comprises a foam core sandwiched between two opposing exterior shells.