Abstract: Method and system for merging measurements of flight parameters of an aircraft. The system is for merging measurements of flight parameters of an aircraft, linked to one another by at least one equation, and includes at least one acquisition module for acquiring at least one measurement of flight parameters, a scoring module for attributing a first validity score to the equations by checking whether the measurement or measurements of flight parameters are a solution or solutions of the equation or equations, a scoring module for attributing a second validity score to failure scenarios involving one or more acquisition modules from the first validity scores, a determination module for determining the validity of the measurements of flight parameters from the second validity scores, consolidation module for consolidating the measurements of flight parameters, a transmission module for transmitting the consolidated measurements of flight parameters to a user device.

Abstract: An assembly constituting an acoustically absorbent material and including a first panel, a second panel pierced with holes, an intermediate panel pierced with through-holes and arranged between the first panel and the second panel, a first structure between the first panel and the intermediate panel and including first cages, a second structure between the second panel and the intermediate panel and including second cages, and for each through-hole of the intermediate panel, a tube opening out at the two ends thereof, where one of the ends of the tube is fixed to the intermediate panel at the through-hole, and where the other end of the tube is accommodated inside a first cage. Such an assembly makes it possible to obtain broad-band attenuation and is easy to manufacture.

Abstract: An air intake structure for an aircraft nacelle is disclosed. The air intake structure delimits a channel and includes a lip having a U-shaped cross section oriented towards the rear, a first sound-absorbing panel fixed behind the lip and delimiting the channel, and a second sound-absorbing panel fixed behind the first sound-absorbing panel and delimiting the channel. Each sound-absorbing panel includes a cellular core which is fixed between an inner skin pierced with holes and oriented towards the channel, and an outer skin oriented in the opposite direction, where the inner skin of the first sound-absorbing panel has a thickness greater than the thickness of the inner skin of the second sound-absorbing panel, and where each of the inner skins includes a heat source which is embedded in the mass of the inner skin.

Abstract: A method and device for optimizing tests of systems, in particular of an aircraft, including a first display module displaying a list of tests that can be executed by systems, a selection module allowing an operator to select a set of tests to be executed and communicate it to an optimization module which determines a sequence of tests representing an optimized execution of the set of tests to be executed, the sequence of tests being displayed by a second display module for an operator, a decision module generating either a first signal if the operator validates the sequence of tests, or a second signal if the operator cancels the sequence of tests, and a control module which, if the first signal is generated, commands the execution of the sequence of tests by each of the systems, and generates results of the execution thereof.

Abstract: To facilitate the assembly of the wing unit of an aircraft, this wing unit includes two wings each having a lateral wing box extended toward the interior by a center wing box half having an interior end, the two wings being attached to one another using attachment bolts linking the two interior ends of the two center wing box halves, and passing through an intermediate wall connecting two fuselage frame walls.

Abstract: To facilitate assembly of an aircraft cockpit, a cockpit module includes an instrument panel to support at least one screen and an air conditioning distribution block bordering the instrument panel and integral with a rear face of it. The air conditioning distribution block includes an air distributor, an excess air collector, and air distribution channels each including a first end communicating with the air distributor and a second end communicating with the excess air collector, each distribution channel being equipped with an air outlet arranged between its first and second ends.

Abstract: An aircraft pylon including a heat exchange device having a heat exchanger which includes a first circuit portion ducting a flow of hot air tapped off an engine of the aircraft and a second circuit portion ducting a flow of cold air, the first and second circuit portions of the heat exchanger being coaxial, separated by at least one partition forming an exchange surface, and positioned, at least partially, in the primary structure of the pylon.

Abstract: A method of manufacturing stiffened structural panel for an aircraft including a main sheet made of composite material with unidirectional fibers, and a stiffening structure secured to the main sheet and made of a composite material comprising a resin and chopped fibers, the stiffening structure including on the one hand a base adhering to one of the two lateral faces of the main sheet, and a network of stiffeners in the form of a grid projecting from the base. The method includes a step of compression molding the stiffening structure from a block formed of a prepolymer reinforced with chopped fibers.

Abstract: An acoustic reflector for a microphone to measure flyover noise generated by an aircraft. The microphone is configured to measure flyover noise generated by an aircraft flying on a preset path. The acoustic reflector includes at least a central portion having the shape of an ellipse having a major axis and a plurality of peripheral portions distributed around the central portion. The acoustic reflector allows edge effects to be attenuated at the low frequencies of the noise to be measured.

Abstract: An air intake structure for a nacelle of an aircraft is disclosed having an air intake lip with a U-shaped section open towards the rear, an acoustic panel that extends the air intake lip towards the rear and on an inner side, an outer panel extending the air intake lip towards the rear and on an outer side, and a rear strengthening frame fixed between the outer panel and the acoustic panel, where the rear strengthening frame partly defines an inner volume that is immediately in front of the rear strengthening frame. The air intake structure comprises an impact absorber element positioned in the inner volume and the impact absorber element assumes the form of a structure that is deformable during an impact and that is at least partially filled with a fluid. The impact absorber element is a flexible shroud filled with a pressurized gas.

Abstract: A method and a system for estimating the state of wear of a cutting tool mounted on a machine tool. The system includes an acquisition module configured to acquire, for a determined duration of machining, values of an operating signal specific to the cutting tool mounted on the machine tool, and a microprocessor configured for calculating current values of a set of wear indicators from the values of the operating signal, and determining the state of wear of the cutting tool as a function of the current values of the set of indicators using a predetermined wear model modeling the state of wear of the cutting tool in function of learning values of the set of wear indicators.

Abstract: A linking part for an aircraft is disclosed having an elongated section including an internal longitudinal seat and a tenon mounted in the seat. The tenon includes a linking element at a free longitudinal end thereof and configured in a retracted position in which the tenon is fully inserted in the seat and does not create an obstruction, enabling the linking part to be easily moved towards the support element, or a deployed position (P2) in which the free longitudinal end of the tenon is outside the seat and is able to be linked using the linking element to the support element, thereby enabling a link to be made simply and quickly.

Abstract: A forward engine attachment system for an engine of an aircraft, the forward engine attachment system including a jet engine pylon including, in the region of the forward part thereof, a front part having an attachment wall, and a forward engine attachment with a connecting rod system on either side of a median plane, wherein each connecting rod system is fixed in articulated manner by at least one first link point to the attachment wall and is designed to be fixed in an articulated manner by at least one second link point to a forward part of the engine. Such a forward engine attachment system thus includes a direct coupling between the jet engine pylon and the engine, allowing the production of an assembly that is less heavy and is easier to produce.

Abstract: A primary structure of a strut for bearing an aircraft power plant including a front part intended to be joined to an aircraft power plant and a rear part intended to be joined to a structure of the aircraft, the front part being formed from a box including an upper longitudinal member, a lower longitudinal member, and lateral panels. A main rib is located at an interface between the front part and the rear part. The rear part is formed from a set of four connecting rods. The first end of each connecting rod is joined to the front part of the primary structure and the second end of each connecting rod is joined to a separate interface for fastening to the structure of the aircraft. This allows a substantial simplification of the primary structure of a strut for bearing an aircraft power plant, which can have advantages in particular in terms of cost, mass, and simplicity of implementation and integration.

Abstract: A front landing gear module for an aircraft is disclosed including an open box provided with at least one door and containing a deployable front landing gear. The module may be a one-piece module and also including an attachment system intended to attach it on the aircraft, which allows the module to be manufactured in advance, before it is integrated as an individual assembly into the structure of the fuselage of the aircraft.

Abstract: A module includes two main landing gears and a landing gear bay containing the landing gears. The bay has two lateral walls, a roof wall, a front wall and a rear wall. The roof wall, the front wall and the rear wall together form a pressurization barrier between the bay and a pressurized compartment. By virtue of the landing gear module, it is now possible to assemble and test the main landing gears and the one or more doors and the fairing before they are installed on the aircraft.

Abstract: An anterior part of a nacelle of an aircraft propulsion unit. A rigidifying frame annular about a longitudinal axis of extension of the nacelle is at the rear end of the anterior part. An annular shield is in front of the rigidifying frame and connects an internal peripheral edge of the rigidifying frame to an internal structure. The shield has a portion extending towards the external panel beyond the internal peripheral edge of the rigidifying frame, the portion forming a non-zero angle with respect to the rigidifying frame to form a free space with respect to the rigidifying frame behind the portion. The shield can thus deform in the event of an impact of a foreign object entering through the air inlet lip, without the rigidifying frame itself being deformed, thereby absorbing all or some of the impact energy. A nacelle can have such an anterior part, and an aircraft can have such a nacelle.

Abstract: To reduce the footprint of an installation for assembling a fuselage section, a support structure includes a chassis and a core mounted so that it can rotate relative to the chassis about an axis of rotation of the core. The core includes a fastener(s) for holding the longitudinal fuselage portions around the core, with a view to assembling them to form the fuselage section. The support structure includes one or more rolling elements provided on the chassis, in order to allow the movement of this support structure within the installation.

Abstract: A seal includes a barrel extending between a base and a top, in which the barrel has a cylindrical cavity passing through it between its base and its top, and a skirt indissociable from the barrel and extending around said barrel, in which the skirt adopts the shape of a dome of which the exterior edges extend out beyond the base starting from the top. The seal is able to divert the fluid and keep the space under the skirt fluid tight.

Abstract: An anterior part of a nacelle of an aircraft propulsion unit having an air inlet lip at the front end, an internal structure and an external panel extending the air inlet lip, and an annular rigidifying frame having an external peripheral edge connected to the external panel is disclosed. The anterior part of the nacelle includes a shock-absorbing element connected rigidly on the one hand to an internal peripheral edge of the rigidifying frame and on the other hand to the internal structure.