Abstract: A cladding element having a heating layer in a sandwich construction. In the case of a cladding element in a sandwich construction for an interior space of an aircraft, the cladding element includes a core layer and a first cover layer. The first cover layer forms a visible side of the cladding element. An electrically heating layer extends at least across a sub-face of the first cover layer and serves for generating heat for emission through the first cover layer is disposed between the core layer and the first cover layer.

Abstract: A system and method for welding two thermoplastic workpieces. The system has an ultrasonic tool, a support and a cooling unit. The ultrasonic tool is configured to generate mechanical vibrations. The system is configured to clamp together workpieces in the receiving region by the ultrasonic tool and the support if at least one fastening portion of the workpieces opposite one another is arranged in the receiving region. The ultrasonic tool is configured to introduce the mechanical vibrations into the fastening portion of the workpieces to weld the workpieces in a joining zone. The cooling unit is configured to cool, with cooling fluid, at least a part of the fastening portion of the workpieces and/or a cooling portion of the workpieces directly adjacent to the fastening portion.

Abstract: A brake control system 200 and method 300 for controlling a park brake of an aircraft including a controller 201 configured to cause an increase in a brake torque of the park brake based of an indication to the controller. The indication is generated in response to touchdown of the aircraft.

Abstract: A tank configured to store a liquid and that includes at least one capture device which includes at least a first portion of a line situated at the bottom of the tank, close to its first end, and at least a second portion of the line situated at the bottom of the tank, close to its second end, each of the first and second portions including at least one orifice situated on the upper face thereof, a floating shut-off device for each orifice, the floating shut-off device being movable between an open position in which the floating shut-off device is spaced apart from the orifice and a closed position in which the floating shut-off device shuts off the orifice, the floating shut-off device having a density lower than that of the liquid stored in the tank.

Abstract: An auxiliary power unit system of an aircraft includes an auxiliary power unit (APU), a cooling unit for the APU including a heat exchanger, an air inlet in communication with the APU and/or with the cooling unit, an air inlet door unit located at the air inlet, a first duct configured to draw air into the APU and having an entrance in communication with the air inlet, a second duct having an entrance in communication with the air inlet, the heat exchanger being at least partially located within the second duct, an air turbine located within the second duct downstream of the heat exchanger, and an electrical generator coupled to the air turbine.

Abstract: A structural element for a passenger cabin of an aircraft is built using biomimicry methods. The structural element includes a generative structure, and a functional component. The generative structure includes at least one accommodating space. The functional component is arranged within the at least one accommodating space. The generative structure includes a load topology optimized structure based on a bioinspired generative design that is configured to enable the structural integrity of the structural element while simultaneously providing integrated functionalities via the functional component. Further, an interior component for an aircraft is disclosed that includes at least one such structural element, and an aircraft including at least one structural element. For example, an aircraft galley may include a structural component that may therefore, for example, include integrated wiring, plumbing or other functionalities.

Abstract: A movable aerodynamic surface for an aircraft is disclosed including a skin having a first skin portion and a second skin portion both extending from the leading edge to the trailing edge and together surrounding an interior from opposite sides, and a stiffener arrangement arranged in the interior and including at least an inboard stiffener in the area of the inboard end and/or an outboard stiffener in the area of the outboard end. At the inboard end between the first skin portion, the second skin portion and the inboard stiffener an inboard cavity is formed, and/or at the outboard end between the first skin portion, the second skin portion and the outboard stiffener an outboard cavity is formed. An acoustic filler arrangement including multiple filler elements is arranged within the inboard cavity and/or the outboard cavity for reducing noise.

Abstract: A module ensuring an acoustic attenuation of a flow of a first fluid and a heat exchange between the first fluid and a second fluid. The module comprises a perforated first wall with a cutout, a second wall, a cellular structure extending from the second wall to the first wall, a recess provided in the cellular structure between a perforated bottom and a perforated top, and a heat exchanger which is fixed inside the recess between the bottom and the top and in which the second fluid circulates. Such a module ensures an attenuation of sound waves and a heat exchange without limiting the attenuation surface.

Abstract: A tank including at least first and second portions connected by a connection ring and weld seams obtained by means of a friction welding method. The connection ring includes at least a first cylindrical portion fitted in the end of the first portion, at least a first shoulder protruding toward the outer zone of the tank relative to the first cylindrical portion and at least a first transverse web positioned approximately in the same transverse plane as the first shoulder. According to this configuration, the first cylindrical portion and the transverse web ensure that the forces generated by a friction welding head during the production of the weld seam which enables the tank to be closed are absorbed.

Abstract: A resin film configured to hold a conductive metallic track against a panel. The resin film partially covers the conductive metallic track, such that the conductive metallic track has at least one region which does not have the resin film, so as to allow an electrical connection by contact. Thus, in the context of assembly on a panel, the metallic track incorporated between the panel and the resin film is protected, thus rendering this technical solution particularly robust. Furthermore, the resin film electrically insulates the metallic track from surrounding elements, and the regions which do not have resin film allow an electrical connection by contact.

Abstract: An aircraft including at least one pressure-relief device having: at least one fixed part, at least one deformable mobile wall configured to occupy a closed position in which it blocks an opening, at least one retaining system configured to retain the mobile wall in the closed position as long as the wall is not in a given deformed state, the retaining system including: at least one first slot through the mobile wall opening at the level of one of its edges, for each slot, a first retaining element fastened to the fixed part and configured to cooperate with the slot as long as the mobile part is not in the given deformed state.

Abstract: A connecting rod with a body, first and second fastening heads provided at each end of the body and connected by first and second connection systems to first and second elements, the first fastening head comprising an extension which is screwed into a housing of the body to adjust the length of the connecting rod. The connecting rod includes an anti-rotation system with a key, positioned astride the first fastening head and the body, which has a first part cooperating with the body so as to be rotationally immobilized with respect to the body and also a second part cooperating with the first fastening head and the first connection system so as to be immobilized with respect to the first fastening head.

Abstract: A passenger aircraft includes a plurality of passenger seats arranged in seat rows, and a disembarkation guidance system. The disembarkation guidance system includes a plurality of electronically operable visual indicators, each of the plurality of electronically operable visual indicators being assigned to a respective seat row. The disembarkation guidance system further includes an indicator control device coupled to each of the electronically operable visual indicators. The indicator control device is configured to individually control electronically operable visual indicators to indicate passengers in the assigned seat row whether they are permitted to disembark the passenger aircraft.

Abstract: A device for handling a shaft forming a pivoting link between two parts, including a body configured to be inserted into the shaft, and blocked in translation with respect to the shaft along a longitudinal axis in a first direction, a compression nut screwed onto a threaded outer portion of the body along the axis in a second direction opposite the first direction, a bearing member positioned against one of the parts, and a return member configured to be compressed between the compression nut and the bearing member by the screwing of the compression nut and to be decompressed in the second direction under the action of the compression nut. This device allows the shaft of the pivoting link to be handled rapidly, and makes it possible to control the load applied onto the shaft during the handling thereof.

Abstract: An aerodynamic system includes a support structure and an aerodynamic component movably coupled to the support structure via first and second coupling units such that the aerodynamic component can be moved relative to the support structure. The first and second coupling units can transfer a load from the aerodynamic component to the support structure. The system further includes an auxiliary coupling unit coupled between the aerodynamic component and the support structure, and configured to switch from a decoupling state to a coupling state, wherein, in the decoupling state, a load transfer via the at least one auxiliary coupling unit is prevented, and wherein, in the coupling state, a load transfer via the at least one auxiliary coupling unit is enabled.

Abstract: A tank, in particular for a liquid hydrogen reservoir, provided with at least one dome fixed by way of an outer welded joint and having a central portion provided with at least one free end including a first connecting element and at least one dome provided with an open end including a second connecting element, the dome and the central portion being able to be joined together, the first connecting element and the second connecting element being configured to form, when the central portion and the dome are joined together, a protruding tab extending toward the outside of the tank and able to be welded to a protruding end, such a protruding tab making it possible in particular to join together the tank, this being done entirely from the outside of said tank, and to easily mount and dismount the dome, in particular without accessibility issues.

Abstract: An aircraft with a unit to transmit information on ability/inability of pilots to fly the aircraft. Guidance avionics include guidance architecture and a flight controller to fly the aircraft. The guidance architecture has two dissimilar guidance chains and a selection unit connected thereto, to the flight controller and to the unit for measuring physical ability/inability, a first guidance chain to compute a main path for the aircraft towards a destination airport based on a current state of the aircraft by following a flight plan and to compute main guidance instructions for following the main path, a second guidance chain to compute an emergency path for the aircraft towards a diversion airport based on an initial portion of the common path with the main path and to compute emergency guidance instructions for following the emergency path. The selection unit receives the main and emergency guidance instructions and transmits either one to the flight controller.

Abstract: A blade seal for sealing a gap between a first aircraft component and a second aircraft component, including a flexible seal member having a first end for attaching to the first aircraft component and a second end for extending towards the second aircraft component, a sensor and an actuator directly coupled to the flexible seal member. The sensor is configured to detect deformation of the flexible seal member and send a signal to the actuator in response to the deformation, and the actuator is configured to impart a load on the flexible seal member and to activate only in response to the signal received directly from the sensor by the actuator to counter the detected deformation of the flexible seal member.

Abstract: A method for producing a supporting element for a transportation device or vehicle, having steps of providing a flat base chord made of a first material having a first surface and a second surface, applying at least one layer of at least one second material to the first surface using a friction-based application or welding method, and machining the at least one layer of the second material to produce a desired profile cross section of the supporting element, wherein the first material and the second material are different metallic materials.

Abstract: Method for producing composite components having an undevelopable surface. To be able to maintain the tolerances when manufacturing especially large components in the case of composite components with undevelopable surfaces, it is proposed according to the invention to drape a cut-to-size blank on a molding tool and to determine the deviation of the cut-to-size blank edge from the setpoint cut-to-size edge. Then, on the basis of the deviation, a new cut-to-size blank edge is calculated, and a new cut-to-size blank is created and re-draped for examination purposes. The method is repeated until the deviations are below a tolerable threshold value. The method is furthermore carried out for each textile ply of the composite component.