Abstract: In the method of loading data on board an aircraft), a data set is loaded into on-board equipment of the aircraft, the data set comprising at least: a first version of a database that is identical to a version already in use in the aircraft; and a second version of the database. The database preferably relates to an aircraft warning system.

Abstract: Embodiments relate to a locking and unlocking system of a separation door separating a cockpit from a cabin of an aircraft. In one embodiment, a system comprises a set of electrically controlled bolts configured to lock the door, a control unit configured to electrically control the set of bolts, a first manual control connected to the control unit, installed in the cockpit and configured to unlock the door, a second manual control connected to the control unit, installed in the cabin and configured to unlock the door, an accelerometer to detect a crash, and a switching relay to control automatic unlocking of the door when a crash of the aircraft is detected, the relay connected to the accelerometer, the control unit and the set of bolts.

Abstract: An aircraft nacelle includes an air inlet (110) with a lip (114) extended to the back by a passage (116) to channel an air flow to a drive (112), the passage having at least one acoustic treatment panel (120) that includes, from the outside to the inside: an acoustically resistant porous layer (122); at least one cell-like structure (124), whose cells are sized for acoustic treatment; and a reflective or sealed layer (126). The reflective layer includes, near the end thereof that is oriented toward the lip, a surface (130) that is angled so as to be connected to the lip. A cell-like structure (136) is in contact with the angled surface, which forms an angle less than 30° with the tangent on the acoustically resistant layer. The cell-like structure is inserted between the angled surface of the reflective layer and an acoustically resistant porous layer.

Abstract: An aircraft wingtip device comprises illumination means arranged to project light onto interior and exterior surfaces of the wingtip device.

Abstract: The invention relates to a method for producing a fiber composite component, comprising the steps: introduction of a first body (12), consisting of fibers and a matrix material, into a mold (10), said first body (12) having a continuous first body edge (18); the first body (12) is irradiated with microwaves (28) to produce a fiber-composite component. According to the invention, the first body (12) is introduced into the mold (10) in such a way that at least parts of the first body edge (18) are brought into contact with the mold (10).

Abstract: To create a metal section (P3) of complex shape, a three-dimensional drawing is made of the final size, then plane drawings are developed and made of each of the elements that form a distinct part of the section. These elements are then cut out (A3, B3) in at least one metal plate. Cutting operations are preferably executed flat in the flat plate. If necessary, at least one of the elements (A3, B3) is then formed. Lastly, the elements (A3, B3) are assembled together by welding for example, to form the section (P3).

Abstract: A frame switching device for an AFDX network, the device including a first port, configured to be connected to a frame switch of the network or else to a terminal, for example a computer, and a plurality of second ports configured to be respectively connected to on-board pieces of equipment. Each frame incident on the first port is replicated on each of the second ports. The second ports are periodically polled in turn, each frame present on a second polled port being transferred onto the first port.

Abstract: Methods and systems for optimizing the design of aerodynamic surfaces are provided. They include in the design process of an aerodynamic surface of a body which moves through a flow field, the following: preparation of a CFD simulation of said body; resolution of the CFD calculation for specific conditions of the flow field and for obtaining flow lines of the flow on said surface; calculation of at least one geometrical variable of the surface, such as, for example, the normal curvature, according to the direction of said flow lines; and simultaneous visualization of the surface of said body and of at least one geometric variable. Additionally, at least one variable of the aerodynamic flow, such as, for example, a pressure gradient, may be calculated and visualized.

Abstract: A method is disclosed of identifying or fixing the value of the parameters (aerodynamic data) of a pre-determined set of equations forming the aerodynamic models of an aircraft in various configurations, so as to minimize the variance between the values anticipated by using these aerodynamic data, and reference data in cases of known configurations, includes the use of learning or optimization methods to determine at least one portion of the parameters' values. The method includes storing database data, choosing an optimization method or a neural network method, breaking the identification down into several partial identifications, carrying out successive partial identifications, validating the values found for the aerodynamic model's parameters or iterating the method according to a threshold criterion determined on the value of variances between the reference data and the values measured by the identified model.

Abstract: A joint construction for an aeronautical structure made from composite material having an internal structural element and an adjoining skin element which define the aeronautical structure, which includes a coupling element disposed between and contiguous with the internal structural element and the adjoining skin element, wherein the coupling element has opposing adjoining diagonally configured end portions which form a wedge shaped diagonal joint therebetween which terminates at the internal structural element at one end and the skin element at the other end, and a plurality of rivets extending from the internal structured element to the adjoining skin, across the coupling element and across the diagonal joint.

Abstract: Method for manufacturing a composite fiber component (1) the method comprising the following method steps: forming a moulding core (4) comprising a hollow profile (15) made of segments (16a . . . d) in order to establish an external geometry of the moulding core (4), wherein the segments (16a . . . d) of the moulding core (4) each extend in the direction of the longitudinal axis of the moulding core (4) and are each constructed so as to be pivotable about an axis running in the longitudinal direction of the moulding core (4), between a folded position (A), and an unfolded position (B) of the hollow profile (15) of the moulding core (4), wherein the segments (16a . . . d) are constructed so as to be coupled to one another via connections (18a . . . d, 19a . . .

Abstract: The invention pertains to an inerting system for an aircraft featuring at least one air separation module with at least one air inlet, a first air outlet and a second air outlet. The air separation module is designed for splitting an input air flow into a first air flow and a second air flow, wherein the first air flow is enriched with oxygen in comparison with the input air flow and discharged at the first air outlet and the second air flow is enriched with nitrogen in comparison with the input air flow and discharged at the second air outlet. In comparison with known inerting systems, the inerting system according to the invention is characterized in that the air inlet can be connected to an air extraction point in an air processing system and the inerting system is designed for routing the first air flow into a cabin to be air-conditioned.

Abstract: A device for adjusting the pitch angle of propeller blades for a model engine including at least one rotor, the blades extending radially on the surface of the rotor to form a propeller. It includes a tool-holder including a base designed to be fixed to a part of the outside of the engine housing and an upper part, the aforementioned upper part being fitted with means of support movable horizontally along a longitudinal axis (XX?), the aforementioned axis being parallel to the main axis of the model engine, contactless means of optical measurement, the aforementioned means of measurement being mounted on the movable means of support by using means of travel in rotation around an axis of rotation, the aforementioned axis of rotation being the blade's axis of rotation.

Abstract: An apparatus for pressurizing an aircraft cabin structure and measuring the amount of leakage of the aircraft cabin structure comprises an air supply line which at a first end is connectable to a pressurized air source and which at a second end is connectable to the aircraft cabin structure so as to supply pressurized air from the pressurized air source into the aircraft cabin structure, an air supply valve disposed in the air supply fine, a pressure sensor for sensing the pressure inside the aircraft cabin structure and for providing signals indicative of the pressure inside the aircraft cabin structure, an air discharge line which at a first end is connectable to the aircraft cabin structure and which at a second end is connectable to an air discharge opening so as to discharge air from the inside of the cabin structure to the air discharge opening and an air discharge valve disposed in the air discharge line.

Abstract: A system is provided for water purification for a recirculation shower in a transport with a filtration unit, a first backwash line and a second backwash line. The filtration unit is designed to filter used shower water. The first backwash line and the second backwash line are designed to clean the filtration unit with a backwashing. The first backwash line is designed to convey backwash water to the filtration unit. The second backwash line is designed to discharge backwash water from the filtration unit.

Abstract: A system for cooling and adjusting the temperature of apparatuses in the propulsion assembly of an aircraft, that includes first means for heat exchange between lubrication circuits of at least two of the aforementioned apparatuses and a heat-carrier fluid contained in a closed circuit, a second means for heat exchange between the heat-carrier fluid and at least one coolant, the first heat exchange means being arranged locally at each of the aforementioned apparatuses, the second heat exchange means being remote from the aforementioned first means, the closed circuit extending between at least two of the aforementioned apparatuses and the aforementioned second means.

Abstract: The invention relates to a device for moving objects, particularly luggage, in an aircraft hold, said device including a moving wall (10) and at least one belt. One end of the belt (20) is connected to a roller (24) around which the belt (20) is wound. The other end of the belt (20) is attached to the moving wall (10). A lower section of the belt (20) extends from the moving wall (10) to a threshold element (22) and an upper section of the belt (20) extends from the threshold element (22) to the moving wall (10).

Abstract: A drainage mast (13) for draining liquids from an APU compartment (11) of an aircraft with a first end (15) connected to the APU compartment (11) and a second end (17) for discharging said liquids to the atmosphere. The drainage mast (13) is configured with at least a sector having decreasing cross section areas towards the second end (17). The area of the initial cross section of said sector is lesser than the area of any cross section of the drainage mast (13) closer to the first end (15). The invention also refers to an aircraft comprising the drainage mast (13).

Abstract: An aircraft includes an overpressure valve with a sealing member which is moveable, in response to a first pressure differential across the valve, between a closed position and an open position. The overpressure valve further has a frangible portion, for example, a carbon or sheet metal disc. The frangible portion is arranged to fail in response to a second pressure differential across the valve, the second pressure differential being more than the first pressure differential. Thus the valve is still able to relieve pressure when the sealing member is jammed (due to ice, for example). The valve may be in the surge tank of a fuel tank system.