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 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: To make an aircraft assembly installation modulable, the latter includes a floor, assembly stations distributed on the floor, and structures for accessing the aircraft during their assembly, each structure being mobile on the ground. The access structures include at least one access structure at an orbital junction between two fuselage sections, at least one access structure at the two junctions between a fuselage section and each of the two aircraft wings, and at least one access structure at the junctions between a rear fuselage section and tail units. In addition, the installation is designed to be able to adopt several distinct configurations, each having a different distribution of the access structures between the assembly stations.

Abstract: A system includes at least one reception unit installed in an aircraft and configured for tracking satellites of the satellite navigation system of the GNSS type. The system includes a generation unit for generating an expected number corresponding to the number of satellites that the reception unit is expected to track, a detection unit including a comparison part for comparing the expected number with a tracked number corresponding to the number of satellites that the reception unit is actually tracking and a decision part for detecting a jamming, as a function of the result of the comparison made by the comparison part and transmitting detection data in the event of detection, and a transmission unit configured to transmit jamming detection data to at least one user device, the system making it possible to detect a jamming of a GNSS system in an automatic and reliable manner.

Abstract: A support for a busbar including two parts each having two surfaces substantially planar and perpendicular to one another and arranged to form, together with the two surfaces of the other part from the two parts, a through-cavity or a passage, a base including a hole or a fastener, and, a shape complementary to a shape of the other of the two parts, the shape being arranged to form, together with the shape of the other of the two parts, an attachment between the two parts. Advantageously, it is possible to obtain a support for a busbar, the support being robust, reliable, and inexpensive and able to be mounted in an easy and rapid manner.

Abstract: An anchor rail for an aircraft floor includes an upper flange with a guideway and two flange wings. The rail is formed of a beam and of an anti-corrosion protection. The beam is formed at least of a body made from a first material and defining the lower stiffening structure and an upper platform. The anti-corrosion protection wholly covers an upper face of the upper platform and therewith constitutes the upper flange of the rail, thus layered. The anti-corrosion protection is at least formed of a protective sheet made of a second material more resistant to corrosion than the first material and selected from a metal and a fiber-reinforced plastic composite material. Such a rail exhibits good corrosion resistance for modest cost.

Abstract: A retractable fuselage mounted landing gear assembly is disclosed. The landing gear assembly includes a main strut, a drag stay and a landing gear main fitting. A first end of the drag stay is attached to the main strut and a second end of the drag stay is connected to the fuselage. A first end of the landing main fitting is attached to the main strut and a second end of the main fitting is connected to the fuselage. When the landing gear is extended, substantially all the landing gear loads are transferred from the landing gear to the fuselage via one or more of the drag stay and the main fitting.

Abstract: A method for fabricating a central caisson of an aircraft wing including a frame formed from U-section crossmembers. Formation of at least one crossmember includes forming a stack comprising at least one layer of resin film applied to a layer of dry fibers, pressing this stack to confer on it a U-section form and such as to compress the layers thereof, and pre-polymerization and/or polymerization of the resin of the stack. The manipulated fiber layers are layers of dry fibers, such that manipulation thereof by an automated machine may be effected for a reasonable cost and at a high throughput. Deposition of resin films carried by removable leaves, i.e., of which one of the faces is not adhesive, likewise facilitates manipulation by an automated installation.

Abstract: An engine pylon of an aircraft having a rear portion, two rear cowls around the rear portion, each rear cowl having an upper fixed cowl and a lower movable cowl mounted articulated on the rear portion, wherein in the closed position the two lower movable cowls are moved close to one another, such that their lower edges are contiguous, wherein in the open position the two lower movable cowls are tilted such that their lower edges are moved away from one another, for each lower movable cowl, a hinge system fixed between the lower movable cowl and the rear portion, and at least one locking system which locks the two lower movable cowls to one another in the closed position. The presence of the lower movable cowls ensures, among other things, easy access to the interior of the engine pylon.

Abstract: A system and method for controlling an actuator for a control surface of an aircraft includes a processing unit configured for acquiring a set of N values of the same parameter, N being equal to 2×p or to 2×p+1, p being an integer greater than or equal to 2, and determining a voted value of the parameter by a voter (15) with N inputs. The voter with N inputs includes a module for determining two intermediate values from among the values of a subset of 2×p values of the set of N values of the parameter, this module including at least p+1 voters with 2×p?1 inputs, receiving as input distinct subsets of 2×p?1 inputs of the subset of 2×p inputs, two sub-modules for determining a maximum value and a minimum value, respectively, each receiving as input the outputs of the various voters with 2×p?1 inputs and delivering as output the two intermediate values.

Abstract: A fluidic connector to connect two ducts of a system such as an air conditioning system. The connector includes at least one elastic material, and includes a duct surrounded by an adjustable clamping collar which, when tightened, serves to deform it to reduce the internal space of the duct. The clamping of the collar makes it possible to easily and quickly regulate the rate of flow in the ducts.

Abstract: Method and device for manufacturing a component from a plate made of deformable material, in particular for an edge of an element of an aircraft. The device includes a tool with two tool parts configured to be able to move closer to one another and are able to round a plate made of deformable material fixed to the two tool parts, a mold at the periphery of the tool and including a molding cavity of a shape corresponding to the shape of the component that is to be manufactured, and a displacement system configured to press the rounded plate firmly against the molding cavity of the mold, the mold being able to shape the rounded plate when it is pressed firmly against the molding cavity to give it its definitive shape, the device allowing the manufacture of single-piece components of varying sizes and notably large-sized components and/or deep components.

Abstract: A simple and lightweight system for discharging water that can flow out through an orifice in an insulation blanket lining the walls of a fuselage of a transport vehicle such as an aircraft. The blanket has an impermeable collection plate having at least partially the shape of a channel, container or the like for collecting and discharging condensation water under the effect of gravity through an orifice.

Abstract: A braking system and a method for applying one or more aircraft wheel brakes according to at least one of a plurality of wheel brake control functions are disclosed. The method includes receiving an indication of an aircraft speed from an aircraft speed indicator, controlling a wheel braking operation of the aircraft according to at least a first wheel brake control function if the aircraft speed indicated by the aircraft speed indicator exceeds a speed threshold, and controlling the wheel braking operation of the aircraft according to at least a second wheel brake control function if the aircraft speed does not exceed the speed threshold. Also disclosed is an aircraft including one or more aircraft wheel brakes and the disclosed braking system.

Abstract: A propulsion assembly includes an engine below a pylon by engine attachments, including a thrust force uptake device, the engine having a longitudinal axis and a vertical median plane parallel to the longitudinal axis, the thrust force uptake device having a main fitting fixed below the pylon and two links disposed on either side of the vertical median plane and which each have a rear end articulated to the main fitting by a spreader mounted to pivot on the main fitting about an axis of rotation which, on the one hand, is orthogonal to a mean plane for transmitting thrust forces parallel to the longitudinal axis of each of the links, and which is disposed in the vertical median plane, each link being articulated to the spreader by a connecting pin extending parallel to the mean plane for transmitting thrust forces and perpendicular to the longitudinal axis of the link.

Abstract: A turbofan with a sliding element, rotary blades that can rotate between stowed and deployed positions, and a maneuvering system which moves each blade when the sliding element moves and which includes, for each blade, a rotary main shaft, for each main shaft, a transmission lever rigidly secured to the main shaft, at least two connecting strips articulated to one another, wherein each connecting strip is associated with at least three main shafts, the transmission levers of which are articulated to the connecting strip, and a drive system which rotates the first connecting strip when the sliding element moves. The use of rotary blades on the sliding element and the simplified maneuvering system makes the assembly more lightweight compared to the use of conventional reverser doors.

Abstract: A method for detecting potential dents in a surface includes providing a flying drone with an image acquisition device and a light source, the shape of which is elongate, and a data processing device. At least one series of images is acquired of portions of the surface by the image acquisition device by moving the flying drone past the surface along a trajectory so that, for each image of the series, the light source is illuminating the corresponding portion of the surface. The data processing device is operated to analyze the shape of a specular reflection of the light source in images of the series of images to estimate the position of any dents in the surface.

Abstract: A flying drone for inspecting surfaces able to reflect light has a lighting device formed of two light sources each having a shape that is elongate in a longitudinal direction of each of the light sources, two first image acquisition devices, and a second image acquisition device between the two first image acquisition devices. The two light sources are respectively between the second image acquisition device and each of the first image acquisition devices. The flying drone allows effective detection of dents in surfaces by analyzing specular reflections, by the lighting device and of the first image acquisition devices, and effective detection of superficial defects on surfaces by the second image acquisition device, with the lighting device switched off.

Abstract: To simplify architecture of a measurement device for affixing to a wall of a moving object or stationary object located in a flow, a device includes a support having compartments with an opening that opens to the exterior of the support at the free face in which sensors are housed, the support having a free face and a face to come into contact with the wall, the free face being opposite the face. The device includes a cavity with a printed circuit board, the compartments including an opening that opens to the exterior of the support in the cavity. The cavity is made in the free face opening into it. The circuit board is upside down in the cavity with the printed face towards the interior of the support. The sensors attached to the circuit board are suspended in the compartments. The unprinted face affords an aerodynamic smooth and planar surface.

Abstract: An assembly includes a structure with 6 o'clock and 12 o'clock beams and front and rear curved beams, in which the 12 o'clock beam is mounted to be able to rotate on a pylon of an aircraft between a closed position and a raised position, a fan cowl fixed to the structure, a thrust reverser with a rear cowl and that is able to move in translation along the 6 o'clock and 12 o'clock beams between a forward position and a backward position, cascades fixed to the thrust reverser, and a mover for moving the thrust reverser. With such an arrangement, the fan cowl and the thrust reverser are fixed to the same structure, and it is this structure that is hinged to the pylon.