Abstract: A front structure of an aircraft fuselage comprising landing gear pivoting about a main shaft and a stay shaft. The front structure also comprises a first reinforcing frame and a second reinforcing frame, the main shaft and the stay shaft being respectively connected to the first and second frames, and a device for the mechanical connection and transfer of forces connecting the stay shaft and the main shaft and transferring to the main shaft a portion of the forces induced by the wheels of the landing gear onto the stay shaft, the second frame and said device being perpendicular to one another.

Abstract: The invention relates to a fish joint device intended to attach securely first and second structural elements of an aircraft to one another, having two fishplates positioned either side of the structural elements, and attached to them by a set of fishplate through fastenings. According to the invention, the fish joint device includes at least one intermediate fish joint plate which is positioned between one of said fishplates and said structural elements which said intermediate plate partly covers, and which is attached to these elements by a set of intermediate plate through fastenings which includes the set of fishplate through fastenings.

Abstract: A component for connecting structures to intersection regions of said component is disclosed, particularly for an aircraft or spacecraft, including a coupling element, including a first fiber which wraps around the coupling element so that the first fiber extends in a first plane in front of the coupling element and in a second plane behind the coupling element, the first and second planes intersecting, and including a second fiber which wraps around the coupling element so that the second fiber extends in a third plane in front of the coupling element and in a fourth plane behind the coupling element, the third and fourth planes intersecting, and with the first fiber portions of the first and second fibers crossing over in a first region and the second fiber portions of the first and second fibers crossing over in a second region.

Abstract: The present invention provides a network, in particular for an aircraft and spacecraft, comprising a network line and at least two network access devices which are interconnected by the network line and between which data of different levels of priority can be transmitted, the network access devices being formed so as allocate data with a level of priority allocated to the respective data, at least two different levels of priority being provided for the data depending on the relevance of the respective data, and the data being transmitted on the network line in fixed time slots depending on the level of priority assigned in each case. The present invention further provides a method and an aircraft and spacecraft.

Abstract: A device for processing faults, that detects and identifies faults, including, for at least part of the identified faults: a mechanism storing a log of occurrences of faults having a same identification, in a course of a plurality of flights; a mechanism determining an impact of each identified fault, on availability of aircraft in a predetermined duration, a mechanism associating a hierarchical attribute with each fault detected in a course of a flight, the hierarchical attribute being dependent on the log and on the impact; and a mechanism displaying identified faults associated with part of the hierarchical attributes. The device enables, in particular, maintenance operations or operations preparatory to maintenance to be better scheduled by virtue of hierarchization of faults displayed.

Abstract: An energy protection device includes a plurality of sensors that detect a triggering situation requiring an energy protection and a control unit that actuates an energy protection function when the triggering situation is detected and also activates an autothrottle. When the control unit begins the energy protection function, an original engagement state of the autothrottle before the triggering is stored. Thus, when the aircraft returns to an operational flight domain not requiring the energy protection function, the control unit stops the energy protection function and sets an engagement state of the autothrottle based on the stored original engagement state.

Abstract: Protection of elements (1) of composite material protected at its points of complex geometry, such as various edges and corners, against electric discharges to which they are potentially exposed, said elements (1) being obtained by applying a cycle of temperature and pressure to a composite material arranged in a mold (2) designed in such a way that, once the geometry of the element (1) is known, the mold (2) includes free spaces (6) intended for the accumulation of resin from the process of manufacture of said element (1), and said resin will form the dielectric protection of the various edges or corners of the element (1) as it builds up, forming layers (3) that are disposed around the free edges of the element (1), thus endowing these surfaces of various edges or corners with dielectric protection of electrical insulation that prevents possible discharges and expulsion of hot particles in the case of electric discharge on said element (1).

Abstract: The present invention provides a cover plate for covering at least portions of a door gap formed between a door covering and a fuselage cell of an aircraft or spacecraft, comprising: a fastening portion by which the cover plate can be mounted on an outer surface of the door covering; a contact portion which rests in a contacting manner against an outer skin of the fuselage cell when the door covering is closed; at least one corner portion associated with a corner of the door covering; and a side portion associated with a side of the door covering, the at least one corner portion and the side portion being configured to press the contact portion with a constant contact pressure against the outer skin of the fuselage cell when the door covering is closed.

Abstract: A method for producing a part made of a composite material, including a skin and at least one stiffener made of strips, which are in turn made of one or more plies of fibers impregnated with a non-polymerized resin. The method includes the steps of: producing a preform of the part by pulling the strips through a die for shaping and positioning the skin and the stiffeners, a polymerization core being provided between a first strip and a second strip prior to the passage thereof through the die; and pressing the resulting preform in a hot press for a duration dt while applying a pressure P and at a temperature T for polymerizing the resin of the strips in the hot press over a pressing length L that is shorter than the length of the panel.

Abstract: A method of design optimization, the method comprising producing a first computer model of a first geometry, producing a CFD mesh from the first computer model, using the CFD mesh from the first computer to produce a measure of the fluid dynamic performance of the first geometry, producing a new computer model of a new geometry, producing a CFD mesh from the new computer model, using the CFD mesh to produce a measure of the fluid dynamic performance of the new geometry, and “identifying an optimal geometry using the fluid dynamic performance measurements of the first and new geometries previously produced.

Abstract: A method for modifying a current sound-volume value assigned by an on-board system to an acoustic alert signal emitted on board an aircraft is provided. The method includes furnishing, on board the aircraft, the on-board system with at least one information item defining a modification of the current sound-volume value to a new sound-volume value in accordance with a predetermined rule.

Abstract: A fuel system comprising a fuel tank, a catalytic inerting device for producing oxygen depleted air (ODA) by reaction of fuel vapor from the fuel tank with air, and a separator device for separating carbon dioxide from the ODA gas before feeding the carbon dioxide depleted ODA gas to the fuel tank so as to render the fuel tank ullage atmosphere inert. Also, a method of reducing the carbon dioxide content of oxygen depleted air (ODA) produced by a catalytic inerting device for inerting a fuel tank ullage atmosphere, the method comprising separating carbon dioxide from the ODA gas before feeding the carbon dioxide depleted ODA gas to the fuel tank. The system may be installed in an aircraft.

Abstract: A sealing unit for sealing a gap between a pair of surfaces includes a nozzle for injecting sealant into the gap, rollers, an endless track round the rollers, and a curing device. The sealing unit is moved along the length of the gap. A sealant is injected into the gap from the nozzle and the track is rotated around the rollers as they are moved along the length of the gap. The track is pressed onto first and second surfaces so the sealant in the gap is constrained by the track to lie substantially flush with the first and second surfaces. The sealing unit is moved along the length of the gap at a rate such that the sealant becomes sufficiently cured when it is in contact with the track so that the track can be peeled away from the sealant as the track rotates round the second roller.

Abstract: The structural integrity of a safe-life aircraft component on an aircraft is measured and assessed by a processing unit. The component includes a load-bearing metal element that is free from cracks. In the method, acoustic emissions generated in the metal element are converted into electronic signals. The acoustic emissions converted include relevant acoustic emissions resulting from changes in the structure of the element that make the element more susceptible to the formation of cracks. The electronic signals are set to a processing unit. The processing unit processes over time the signals in conjunction with stored reference data that allows a measure of the structural integrity to be made. Information providing a measure of the structural integrity of the aircraft component is outputted. Thus, deterioration of the structure of the component can be detected and monitored before a crack occurs.

Abstract: The invention belongs to the field of single-effect hydraulic cylinders. It relates to a device that makes it possible to limit the pressure in the pressurization chamber of a single-effect cylinder when the rod thereof is in a particular range of longitudinal positions of safety, while respecting the operating safety of the device, that is, in the case that the power supply of the pilot valves of the distributors and of the hydraulic pump is cut, the rod of the cylinder remains in its position if this position does not lie within the safety position range.

Abstract: A method for making a rib for an aerofoil structure, the aerofoil structure including a skin component, the method including the steps of scanning the inner surface of the skin component to determine the surface profile thereof, providing a rib having a rib body and a rib foot protruding from the body, machining a foot surface profile into the rib foot, the foot surface profile being arranged to complement the skin inner surface profile where the rib foot is intended to abut the skin component.

Abstract: An aircraft slat assembly comprises a first slat and a second slat positioned adjacent thereto. The first and second slats are moveable between extended and retracted positions. The slats are connected by a joint, the joint being arranged to transfer a shear load from one slat to the other slat when the slats are urged into a configurations in which there would be differential extension/retraction of the slats, such as a skewed position.

Abstract: The invention relates to a locking mechanism for a cargo door (1, 27) in a fuselage cell (3) of an aircraft. The cargo door (1, 27) is attached by a hinge (5) in the area of a recess (2) to open outwards. The locking mechanism comprises inter alia a number of fuselage cell fitments (9, 41) which are disposed in the area of a loading edge (8) of the cargo door (1, 27), and a corresponding number of cargo door fitments (7, 28, 61) which are fixed in the area of a lower edge (6) of the cargo door (1, 27).

Abstract: An engine nacelle of an aircraft, which engine nacelle on one side comprises several fin-shaped vortex generators so that with an increase in the angle of attack, to improve maximum lift, the field of vorticity generated by said vortex generators overall extends over an increasing region of the wing in the direction of the wingspan, with the first vortex generator being located within a positioning corridor situated between two boundary lines, wherein: the starting point of the first boundary line is the circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi=35 degrees and the engine-nacelle longitudinal coordinate X=L/4; the end point of the first boundary line is the circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi=25 degrees and the engine-nacelle longitudinal coordinate X=L·?; the starting point of the second boundary line is the circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi=

Abstract: An aircraft includes a hose that makes it possible to channel the pressurized air that is used in a sleeve (52) that delimits an annular chamber with the hose, with the sleeve (52) including at least one opening (54) that is delimited by an edge (58) that makes it possible to link the annular chamber and the outside of the sleeve (52), and a leak detection system that includes at least one loop (A) in the form of a threadlike element (56), characterized in that it includes a connecting device that includes a ring (60) that is connected at at least one connecting point (64) with a loop (A), and a flexible wall that delimits a hose (68) for channeling the air that extends from the edge (58) of the opening (54) up to the ring (60).