Abstract: An aircraft wing having a fixed wing with a wing tip device. The wing tip device is movable between a flight configuration for use during flight, and a ground configuration for use during ground-based operations. The wing has a master flight control surface associated with the fixed wing and a slave flight control surface associated with the wing tip device. An interface between the master flight control surface and the slave flight control surface is arranged to provide a rigid connection between the master flight control surface and slave flight control surface when the wing tip device is in the flight configuration. Moving the master control surface about a control axis causes the slave control surface to be moved about the control axis. The interface is arranged to de-couple the slave and master control surfaces when the wing tip device is moved from the flight configuration into the ground configuration.

Abstract: A battery has an integrated flame retardant device, wherein the battery has: a cathode layer, a separating layer, and an anode layer, wherein the separating layer is arranged between the cathode layer and the anode layer, wherein the separating layer is impermeable to electrons and permeable to at least one positive type of ion, wherein the separating layer has a flame retardant device having at least one glass fibre, which includes a closed cavity, and wherein a flame retardant is arranged in the cavity. The battery has increased fire resistance.

Abstract: A first aspect of the invention provides a method of joining a part to a composite component, the composite component comprising fibres impregnated with a matrix material, and the part comprising a plurality of projections, the method comprising: inserting the projections into the composite component; and pre-heating the projections before they are inserted into the composite component, so that the projections are at a higher temperature than the composite component as they are inserted into the composite component. The projections locally heat the matrix material of the composite component as they are pushed into the composite component. Increased temperature during insertion is advantageous as the reduced matrix viscosity, due to the increased temperature of the matrix, results in better consolidation of the fibres around the projections and minimises the distortion of the fibres.

Abstract: A heat exchange device to be positioned in an aircraft pylon and including a heat exchanger and an obturator to adopt a closed state where it prevents flow of air from flowing through the heat exchanger, and more- or less-permissive states where it allows flow of air to flow with a higher or lower flow rate. The obturator includes slats each including a pivot axis, the pivot axes of the various slats being mutually parallel and intersecting the direction of the flow of air, the slats being simultaneously mobile in rotation about their pivot axis between a closed position in which the slats are contiguous, which corresponds to the closed state of the obturator, and an open position in which the slats are spread apart, which corresponds to the permissive state of the obturator.

Abstract: A cooling system for a galley installed in a transportation device, in particular an aircraft, has a cooling device with a coolant circuit configured to have a coolant flow therethrough. A fluid line is configured to have a fluid to be cooled flow therethrough and is thermally coupled with the coolant circuit to transfer heat from the fluid to be cooled to the coolant circulating in the coolant circuit, and an air line configured to be flowed through with air and thermally coupled to the coolant circuit of the cooling device to transfer heat from the coolant to the air line. The air line, downstream of the thermal coupling of the air line with the coolant circuit, is connectable to a cabin region of the transportation device accommodating the galley to supply the cabin region with air warmed by heat transfer from the coolant circulating in the coolant circuit.

Abstract: A method of assembling a wing tip device to a wing of a powered aircraft including: providing a wing tip, providing a wing tip device, pivotably attaching the wing tip device to the wing at a first position, pivoting the wing tip device about the first position, and attaching the wing tip device to the wing at a second position spaced from the first position.

Abstract: Disclosed here is a cargo drive unit for a cargo hold of an aircraft. The cargo drive unit includes at least one driven power transmission element, which is configured to transmit drive forces to a load arranged in the cargo hold, in order to move the load inside the cargo hold. The cargo drive unit also includes a sensor unit configured to acquire at least one movement parameter of the load. The cargo drive unit also includes a control unit configured to control the power transmission element according to the acquired movement parameter. Also disclosed here is a cargo hold that includes such a cargo drive unit, and a related method for operating such a cargo hold.

Abstract: A heated floor panel system for an aircraft, the floor panel system comprising a floor panel element including a panel structure and a panel heater device, a temperature sensor device for detecting the temperature at the floor panel element, and a connector device connected to the floor panel element, wherein the connector device comprises a power link for providing an electric power connection between the panel heater device and an electric power supply, and a data link for providing a data connection between the temperature sensor device and a control unit. An object of the present disclosure, to provide a floor panel system including a floor panel element which has a possibly simple construction and which can be used independently from the connector device, is achieved in that the temperature sensor device is located in the connector device and connected to the floor panel element via a thermal conductor element.

Abstract: A tip structure for an aircraft airfoil, such as a control surface (ailerons, flaps, elevators, rudders, etc) and/or a lifting surface (wings, HTP's, VTP's) is a unitary body and includes a tip shell and a metallic material on the outer surface of the tip shell suitable to withstand a lighting strike. The tip shell has been obtained by a single-stage injection molding process using a thermoplastic composite material having fibers dispersed therein, and the metallic material has been integrally formed with the tip shell.

Abstract: An aircraft airflow modification device, comprising: at least one resiliently deformable base member; and at least one resiliently deformable flap member that extends from the resiliently deformable base member. Deformation of the resiliently deformable base member from a first state to a second state results in corresponding deformation of the resiliently deformable flap member from a first state to a second state.

Abstract: A wing arrangement for an aircraft including a latching arrangement (29, 29?, 29?) having a latching member (31, 31?, 31?) and an engagement device (33), wherein the latching member (31, 31?, 31?) is fixed to a wing tip section (13), and the engagement device (33) has a base member (35) on a wing base section (7) and has an abutment surface (43), and an engagement member (45, 45?, 63) supported on the base section (7) and moves between a release position and a latching position by an actuator (49, 49?) coupled to the engagement member (45, 45?, 63) and the base section (7), wherein when the tip section (13) is in the deployed position, the latching member (31, 31?, 31?) abuts the abutment surface (43) and the engagement member (45, 45?, 63) can move between the release position and the latching position, wherein when the latching member (31, 31?, 31?) abuts the abutment surface (43) and the engagement member (45, 45?, 63) is in the latching position, the engagement member (45, 45?, 63) abuts on a surface sect

Abstract: A method of producing a sealed structural joint between two components (23, 24) and such a sealed joint are provided. The method includes the steps of applying a layer of sealant (27) to the first component (23), applying liquid shim (28) to the second component (24), inserting an intermediate layer (29) between the sealant (27) and the liquid shim (28), the intermediate layer (29) having a series of raised structural features (31) to engage the first component (23). The features (31) are positioned to allow the sealant (27) to extend across the joint between the raised features (31) to form a continuous seal. The joint is then closed and cure of the liquid shim (28) and sealant (27) takes place to solidify the shim (28) to the desired thickness within the joint.

Abstract: A fire seals system positioned in a corner of a region of attachment between a rear engine mount and a pylon and comprising a metal shoe comprising a fitting comprising two first vanes forming an L fixed in the corner and a lower second vane between the lower edges of the two first vanes and an upper second vane between the upper edges of the two first vanes, and a flexible tongue having a fixed upstream end and a free downstream end in which an intermediate part of the tongue is arranged between the lower second vane and the upper second vane, and a longilinear seal attached to a thrust reverser cowl with one end of the longilinear seal bearing against the tongue. Such a fire seals system makes it possible to limit the spread of flames and to absorb movements of the nacelle.

Abstract: A suspended rudder bar for aircraft and aircraft having a suspended rudder bar, which includes a set of primary hinges, a set of secondary hinges including control and synchronization devices, and a set of linkages generating functional and structural links between the set of primary hinges and the set of secondary hinges, wherein the primary hinges are configured to be suspended at least on a structure supporting the instrument panel of the flight deck of the aircraft, and the secondary hinges configured to be suspended at least on a structural component of an area situated forward of the flight deck.

Abstract: An aircraft includes a passenger cabin having a floor, a cargo compartment below the floor, a first access unit for accessing the cargo compartment from the passenger cabin, the first access unit being located on the floor and a utility space module arranged in the cargo. At least one part of the cargo compartment includes a first lateral half and a second lateral half in relation to a longitudinal axis of the aircraft; the lateral halves form the part of the cargo compartment. The utility space module includes a utility space cross-section in a direction normal to the longitudinal axis, which is dimensioned such that it conforms to a cross-section of one of the lateral halves of the cargo compartment. Further, the utility space module is placed exclusively in the first lateral half or the second lateral half of the cargo compartment directly below the first access unit.

Abstract: A port expansion device is connected to a user interface terminal in an aircraft. The user interface terminal displays a first selection page designed to make it possible to select a peripheral system from among a first set of peripheral systems connected to the user interface terminal, so as to transfer graphical interface control to the selected peripheral system. A second set of peripheral systems are connected to the user interface terminal via control circuitry of the port expansion device, which emulates peripheral system behaviour. The control circuitry exports a name representative of a menu navigation action on the user interface terminal, and emulates a second selection page in the style of the first selection page generated by the user interface terminal, making it possible to select a peripheral system from among the second set of peripheral systems. The port expansion is thus performed transparently.

Abstract: A slat track device (7) for an aircraft wing (1) including a beam-shaped main load bearing track structure (9) connected to a slat (5) and movably connected to a main wing (3), a guidance surface (11) at the track structure (9) and guided along a corresponding guidance device (19) at the main wing, a connection device (13) at the track structure (9) connecting the track structure (9) to the slat (5), and an engagement device (15) at the track structure (9) and configured to engage a drive member (33) of a drive unit (37) provided at a main wing (3). The slat track device has redundant main load paths achieved by the track structure (9) having a first track member (41) and a separate second track member (43) both connected to the connection device (13) and the engagement device (15).

Abstract: A passenger cabin for a vehicle has an upper passenger deck with an upper arrangement of seats, a lower passenger deck with a lower arrangement of seats, an upper floor for the upper passenger deck arranged between the upper passenger deck and the lower passenger deck, and a lower floor for the lower passenger deck delimiting the lower passenger deck. The upper floor has a central hump region extending along a longitudinal axis of the passenger cabin at least in regions and above which the upper arrangement of seats is arranged, and two side regions adjacent to the hump region. The central hump region is raised relative to the side regions. The lower floor has a lower gangway, wherein the at least one lower arrangement of seats is arranged below the side regions of the upper floor, and the lower gangway is arranged below the central hump region.

Abstract: A vehicle passenger cabin has a holding structure having multiple load introduction points, a multiplicity of support structure parts to be attached to the load introduction points, a lower base for delimiting a lower passenger deck, and a multiplicity of furnishing components to be fastened to the support structure parts. The holding structure has laterally on both sides one floor overhang as a lower delimitation of an upper passenger deck, extending from a laterally outer region of the holding structure radially inwards and at a distance vertically from the lower base. The structure parts are at least regionally curved or bent and are connected at an upper end and at a lower end to an upper and a lower load introduction points, respectively. The structure parts have a first receiving surface for receiving one of the furnishing components, which first receiving surface adjoins the floor overhang radially on the inside.

Abstract: A nacelle for a turbofan including a mobile cowl mobile in translation between a closing position and an opening position, a window on the upstream side by a fixed cowl and on the downstream side by the mobile cowl, and a reverser flap in rotation between a closed position and an open position. The nacelle includes a locking system with a groove fixed to the mobile cowl and extending between a first end and a second end, and a guided element mounted guided in the slide and fixed to the reverser flap, the guided element moving from the second end towards the first end with cowl movement and leaving the groove when the reverser flap begins rotation, and the guided element moving outside the groove while the reverser flap pivots from the positions and entering the groove at the end of rotation of the reverser flap.