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 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 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: 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: 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 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: 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: 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: A cellular sound insulation structure and associated aircraft, a cell of which is provided with a diaphragm which includes a membrane having at least one orifice passing through a thickness of the membrane, and at least one tube surmounting the orifice and extending from a face of the membrane into one compartment of the cell, the tube comprising a free end, forming an acoustic outlet, which is positioned at a distance (p) from the base cross section of the cell. Also, a method for manufacturing such a cellular sound insulation structure, as well as to a tool for inserting a diaphragm into a cell. Such a cellular structure makes it possible to treat a wider acoustic frequency spectrum, and its acoustic dimensioning as well as its manufacture are simplified.

Abstract: A method and a device for manufacturing a part starting from a cushion made of deformable material, in particular for an edge of an element of an aircraft. The device includes a preparation unit to create a cushion with two plates and, between the plates, an internal space with an opening, and a molding unit comprising a mold in which the cushion is positioned, the mold comprising two shells and an imprint corresponding to the shape of the part to be manufactured, the molding unit configured to inject a pressurized fluid into the internal space of the cushion through the opening to deform the cushion such that it matches the imprint and forms the part, the device being capable of manufacturing one-piece parts of various sizes, and in particular parts having complex shapes, in particular non-developable shapes.

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.

Abstract: A device for manufacturing a stiffened panel with reinforcements which each have a final thickness and a final height. The manufacturing device includes tools configured to each support a preform of fibers having a U-shaped or C-shaped cross section with a base and two wings. Each tool comprises, at at least one of its first and second lateral faces, a set-back portion which, when two tools are juxtaposed, delimits a recess configured to form a reinforcement during a consolidation or polymerization step. The tools are dimensioned such that each recess has a width, at the consolidation or polymerization temperature, that is substantially equal to the thickness of the reinforcements. This solution makes it possible to more effectively control the geometry of the stiffened panel by avoiding the formation of beads. A method for manufacturing a stiffened panel using the device is also disclosed.

Abstract: A manufacturing method of a control surface of an aircraft, the control surface including an upper skin, a lower skin, ribs joining the upper skin and the lower skin and located along a chordwise direction of the control surface. The manufacturing method includes the steps of providing a single composite preform comprising the upper skin, the lower skin and the ribs, and curing the single composite preform such that an integrated box comprising the upper skin, the lower skin and the ribs is formed.

Abstract: A structure and equipment system installed in an aircraft includes vertical supports, a rail device, a connector, guiding elements, pivot joints, and locking devices. The rail device is arranged on the aircraft to guide the guiding elements along a rail device extension axis. Via the connector, the vertical supports are arranged in parallel and connect to form a grid arrangement with the guiding elements arranged thereon. The pivot joints are attached to upper ends of the vertical supports to pivot them. The locking devices each have a first and a second locking element. The grid arrangement is inserted into the aircraft as far as an installation position via the guiding elements on the rail device with vertical supports pivoted upwards from the vertical, by pivoting down into a vertical orientation, the first locking elements can interlock with correspondingly arranged second locking elements to form a load-bearing support structure.

Abstract: An aircraft empennage, comprising a rear fuselage section, a trimmable horizontal tail plane comprising a first and a second lateral torsion box), each comprising a front spar and a rear spar, a front fitting and a rear fitting, an actuator acting on the front fitting for a rotation of the trimmable horizontal tail plane around a hinge axis passing through the rear fitting, the front fitting comprising a first and a second front fitting units being joined to the front spars of the lateral torsion boxes, and the actuator comprising first and a second actuator units, each acting on the first front fitting unit and the second front fitting unit respectively.

Abstract: A mounting rail arrangement for an aircraft floor, floor structure and aircraft having the same. To allow full floor structural decoupling for monuments and/or cabin attendant seats, a mounting rail arrangement includes two mounting rails having mounting holes distributed along their longitudinal direction. A mounting bolt is inserted into the mounting holes and an attachment bolt for fixing a cabin monument and/or a cabin attendant seat is inserted into the mounting bolt. As a result, the cabin monument and/or cabin attendant seat may be installed on at different locations and/or with different orientations using all kinds of configurations enabled by the mounting holes.

Abstract: For sealing at the transition between high-lift devices and fairings, a shutter assembly can be installed in a high-lift system, thereby forming the shutter arrangement. The shutter assembly includes the shutter panel and possibly the driving member. The shutter assembly can be installed in the high-lift system, to form any embodiment of the shutter arrangement. The shutter arrangement covers the trunnion opening and is moveable in correspondence with the movement of the high-lift device in a continuous and strictly monotone manner.

Abstract: A method of securing a lower trailing edge panel of an aircraft wing. The wing includes a wingbox with an upper cover, a lower cover, and a rear spar. A leading edge of the lower trailing edge panel is attached to the wingbox. A support structure is also attached to the wingbox and a connector is mounted to the trailing edge panel. A link is provided, with a first end and a second end. The second end of the link is pivotally attached to the support structure at a pivot joint. A biasing arrangement biases the link towards an upright orientation in which the first end of the link is higher than the pivot joint. The link is held in its upright orientation with the biasing arrangement; and then the first end of the link is attached to the connector.

Abstract: A method for testing an avionic computer having internal parameters of which only a subset of internal parameters is accessible to a test bench. The method includes connecting the avionic computer to the test bench, equipping the test bench with a test computer having software similar to software of the avionic computer, all of the internal parameters of which are accessible to the test bench, executing the software of the avionic computer in interaction with the test bench and executing the software of the test computer at the same time as the software of the avionic computer, and visualizing internal parameters belonging to the subset of internal parameters of the avionic computer and visualizing internal parameters of the test computer, corresponding to internal parameters of the avionic computer not belonging to the subset of internal parameters of the avionic computer, to check the conformity of operation of the software.

Abstract: A multimedia distribution network, useful on board a passenger aircraft, includes a first network node configured as a head controller, a plurality of second network nodes configured as intermediate controllers connected to the first network node, and a plurality of third network nodes configured as end device controllers, each connected to one of the second network nodes. The head controller is configured to transmit a multicast stream of multimedia control signal packets to control the end device controllers to the intermediate controllers. The intermediate controllers are configured to periodically transmit unicast delay queries to the head controller, to process the received multimedia control signal packets to the end device controllers and to distribute processed multimedia control signal packets with a controllable delay based on the content of unicast delay indicator signals sent by the head controller to the intermediate controllers in response to the unicast delay queries.