Abstract: A hinge assembly 8a for an aircraft component comprises first and second hinge plates 9, 10, each hinge plate including a plurality of fingers 13 to 17. The fingers of the first and second hinge plates are interleaved. A seal assembly 28 to 32 is provided between at least some of the fingers. The provision of a hinge including interposed fingers allows for a hinge assembly having a complex aerodynamic profile to be made, while the sealing function is performed by the seals filling the gaps between the fingers.

Abstract: A device for electrically connecting cables where a change of direction occurs. The device includes at least two busbars as well as a plate having independent internal ducts in which the busbars are located, each duct being electrically insulated from the other ducts, the busbars ensuring electrical conduction from one open end of a duct to the other end. The cables are fastened at these open ends and thus do not undergo any deformation, the change of direction taking place inside the plate with the aid of the busbars.

Abstract: A fuel system for an aircraft including a fuel tank for storing fuel during operation of the aircraft and a diffuser disposed inside the fuel tank. The diffuser is configured such that it forms part of a flow path configured to connect a fuel source to the inside of the fuel tank. The diffuser includes a wall which at least partially defines an internal space of the diffuser; an opening in the wall, which provides access to the internal space; and a blocking component configured to block the opening.

Abstract: A method for initialising a tyre monitoring device including a wireless communication interface and tyre monitoring devices and systems using the method are disclosed. The method includes operating the tyre monitoring device in a first mode, in the first mode the tyre monitoring device is only responsive to an initialisation instruction received over the wireless communication interface from the second device; receiving an initialisation instruction over the wireless communication interface while operating in the first mode; and, responsive to the initialisation instruction, operating the tyre monitoring device in a second mode in which the tyre monitoring device is responsive to instructions received over the wireless communication interface. The first mode draws lower power than the second mode so power draw prior to initialisation, for example while storage awaiting use, is reduced.

Abstract: A component system for an aircraft, having at least one furnishing component, a plurality of component rails, a plurality of guide elements engageable with and movable relative to the component rails, a plurality of retaining elements connected to the guide elements and configured to be coupled to a hull structure of the aircraft or the at least one furnishing component, and a plurality of locking units arranged on the component rails and/or on the guide elements and configured to lock the guide elements to a particular rail. At least two component rails are arranged on the at least one furnishing component or the hull structure at a distance and parallel to each other such that the furnishing component is retractable via the component rails on guide elements or component rails that are spatially fixed in the aircraft and can be locked in a retracted position by the locking units.

Abstract: An electric generator including a number of electric accumulators and at least one heat-sink device using a phase-change material configured to pick up the excessive thermal energy produced by one of the electric accumulators and change phase in order to absorb a large quantity of thermal energy in the form of latent heat.

Abstract: An apparatus for threading a tool unit onto an elongate structural element. The apparatus has a holding arrangement for holding it on a feed device, a tool unit to be threaded onto the elongate structural element. The tool unit has a tool axis and a vibration unit connected to the tool unit and configured to generate a periodic force in at least one first spatial direction that runs transversely with respect to the tool axis. First and second coupling components, held elastically on one another, are provided. The first coupling component is connected to the holding arrangement, the second coupling component is connected to the tool unit. The vibration unit is operated, during a feed movement of the holding arrangement for threading the tool unit onto the elongate structural element, to add an additional, periodically varying transverse component to a feed force acting on the tool unit.

Abstract: Devices and methods for producing a T-shaped semifinished product from a multiply non-crimp fabric with reinforcing fibers for a composite material. The product has a web and a flange. The device includes a web forming tool, with which a web portion of the non-crimp fabric is clamped in place, a forming tool, with which plies of a flange portion of the non-crimp fabric are split into two parts, a depositing device, with which a tube body is deposited on the flange portion formed into the flange, a holding tool, with which a clearance between the holding tool and the flange is formed, and a filling device, with which the tube body is filled with a gas such that the tube body fills the clearance and firmly holds the flange portion formed into the flange, and alternatively, a magnetic force can be generated between a sheet and the web forming tool.

Abstract: A method for manufacturing deicing acoustic skin for an aircraft acoustic panel, using a fiber spacing device. The manufacturing method includes at least one step for manufacturing a layer assembly having a deicing layer supplied with electrically conductive fibers embedded in a resin and two insulating layers arranged on either side of the deicing layer, and a baking step. The method provides for fitting, during baking, a spacing device on the layer assembly, the spacing device having pins passing through said layer assembly, perforations being produced at the locations of the pins after the withdrawal of the spacing device, the fitting of the spacing device making it possible to produce perforations with desired sizes and shapes, in a simple and effective manner, and with a reduced manufacturing duration.

Abstract: An electric power supply system for an aircraft includes: a first electric source and a second electric source coupled together to supply electric power to a set of electrical loads, and a controller configured to acquire a piece of information on the current electric consumption consumed by the set of electrical loads; acquire a piece of information corresponding to a target ratio of the distribution, between the first and second electric sources, of the current electric consumption consumed by the set of electrical loads; perform frequency filtering of the current electric consumption to determine a transient consumption portion of the current electric consumption; determine control setpoints for the first electric source and for the second electric source in accordance with the target distribution ratio and with the transient consumption portion; and apply the control setpoints to the first and second electric sources.

Abstract: A busbar for an aircraft with at least two conductive layers and at least three insulating layers. The conductive layers and the insulating layers are stacked together alternatingly and extend in a longitudinal direction. The conductive layers and the insulating layers include different coefficients of thermal expansion. Each of the conductive layers includes spatial structures. Each spatial structure is connected to an adjacent one by an interconnecting segment. Each conductive layer is embedded between two insulating layers, resulting in a deforming of the side walls of the spatial structures under heat, thereby compensating a longitudinal expansion of the conductive layers. Further, an aircraft with a disclosed busbar and a method of producing such busbar is provided.

Abstract: An exhaust muffler for an APU of an aircraft, including an exhaust gases inlet, an exhaust gases outlet, a peripheral wall configured to guide a flow of exhaust gases between the inlet and the outlet. The peripheral wall includes at least one vacuum chamber to provide thermal insulation.

Abstract: A structural assembly for an aircraft having pairs of main gantries distributed in the longitudinal direction, two transverse panels fixed to the front and the rear of the pairs of main gantries to together define a compartment for a landing gear of the aircraft, at least one pair of secondary gantries between the main gantries, at least one crossmember parallel to the transverse panels and that straddles at least one secondary gantry, and, for each secondary gantry and each crossmember straddling the secondary gantry, a connecting rod mounted to be able to freely rotate, via a first end, on a lower part of the crossmember and, via a second end, on an outer lateral part of the secondary gantry. Such an arrangement reduces the vertical bulk of the structural assembly.

Abstract: A supply system for an aircraft arranged between two dihydrogen tanks and an engine. The supply system includes a supply module that assures the flow of dihydrogen between the tanks and an outlet pipe and two heaters mounted in series on a main pipe connected to the engine. The supply system also includes a network of pipes and solenoid valves that, in the event of a problem in one of the components of the supply system, enable dihydrogen to be redirected so as to reach the engine. Also an aircraft with such a supply system.

Abstract: A method of operating a landing gear controller for an aircraft, including: the landing gear controller receiving one or more signals from at least one position sensor. The one or more signals indicate a position of one of a landing gear bay door and a landing gear when the landing gear bay door or the landing gear, respectively, is part way through a range of travel between two limits of travel. The method may also include the landing gear controller controlling movement of the other of the landing gear bay door and the landing gear on the basis of the one or more signals.

Abstract: A method and system for assisting a pilot of an aircraft when the aircraft is taxiing on a traffic lane of an airport are described. The system includes a unit for receiving at least a part of a path (TR) to be followed by the aircraft (AC) on the airport, a unit for surveying the airport so as to be able to detect a characteristic element of a traffic lane taken by the aircraft (AC), to determine a current relative position of the aircraft (AC) with respect to the characteristic element detected and to deduce therefrom at least one assistance information item, and a unit for assisting the pilot of the aircraft (AC) when taxiing on the airport by taking into account at least this assistance information item, this assistance being able to be implemented according to a plurality of different, more or less automated, assistance modes.

Abstract: The system includes a unit for monitoring the aerodrome so as to be able to detect at least one obstacle to determine a current relative position and a current relative speed of the aircraft (AC) with respect to the detected obstacle, and to detect a future or potential collision of the aircraft (AC) with the obstacle according to at least this current relative position and this current relative speed. The system also includes a unit for, in the event of detection of a future collision, implementing at least one action intended to help to avoid this future collision. The system is configured to provide assistance to the pilot of the aircraft by improving his awareness of the future collision, by means of warning messages and/or ground navigation aids, and by providing protection of last resort in the form of an automatic avoidance maneuver.

Abstract: The system for assisting the avoidance of an excursion by an aircraft from a runway or taxiway of an aerodrome includes a unit for monitoring the aerodrome so as to allow the detection, by optical detection, of a characteristic element of a pathway, for determining a current relative position of a landing gear of the aircraft (AC) with respect to the detected characteristic element, and for detecting a future excursion from the pathway of the aerodrome by the aircraft (AC) on the basis of at least this current relative position, and a unit for assisting the implementation of an action for assisting the avoidance of said future excursion. The system is configured for providing assistance to the pilot of the aircraft by improving his awareness of a potential excursion, by warning and/or ground navigation aid messages, and by providing protection of last resort via automatic braking.

Abstract: The system includes a unit for surveying the airfield to detect, by an optical detection, one or more characteristic elements corresponding to a mandatory characteristic element corresponding to a stop marking on the ground, a taxi-holding position of a runway of the airfield, to determine a current relative position of the aircraft with respect to a taxi-holding position for which at least the mandatory characteristic element has been detected and to detect a future entry onto the runway of the airfield by the aircraft, a unit for deducing a future incursion if this future entry is not cleared and a unit for implementing an action intended to assist in avoiding, the future incursion, the system being configured to provide assistance to the aircraft pilot by improving awareness concerning a possible incursion onto a runway, by alert or ground navigation assistance messages and by providing protection via automatic braking.

Abstract: A rear pressure bulkhead comprising a dome shaped structure, and a set of built-in extension components (“petals”) homogeneously distributed along the periphery of the dome-shaped structure. This results in the dome-shaped structure being secured to a frame of the aircraft, while the extension components are secured to longitudinal structures of the aircraft. An aircraft rear fuselage is provided including such a rear pressure bulkhead so that the available cabin space, i.e., pressurized space, is extended without enlarging the fuselage.