Abstract: A method for installing an item of equipment in a cabin, includes: determining the actual position of each anchoring location provided for the equipment in a first reference system and of each fixing location of the equipment in a second reference system, positioning the second reference system relative to the first reference system, prior to the installation of the equipment in the cabin, adjusting each adjustable connection in accordance with at least one characteristic determined from the actual position determined for each anchoring location and for each fixing location, positioning the adjusted adjustable connections which connect the equipment to the cabin.

Abstract: A trolley for collecting waste includes a housing having a main waste chamber for receiving waste, and wheels attached to a bottom wall of the housing. The housing has at least one module seating, each configured to receive a waste module for collecting waste. Each module seating includes fasteners configured to releasably couple to a waste module. The waste module includes a module housing having at its top surface a top opening for inserting waste, and having a module waste chamber for receiving waste inserted through the top opening. The module housing includes second connection means at its outside surface, which are configured to releasably interact with first connection means of a trolley for collecting waste. Also disclosed herein is a system that includes the trolley and at least one waste module inserted into the at least one module seating.

Abstract: An aircraft fuselage includes: at least one lower part, at least one upper part, structural connections connecting the lower part and the upper part in joining zones, in each joining zone, at least one space between the lower and upper parts and the structural connections, and a transparent wall for closing off each space.

Abstract: A device for protecting an airfoil element made of a complex comprising a polymer film, a metal strip deposited on a part of the polymer film and an adhesive element to attach the polymer film on the airfoil element. The polymer film forms a protection against sand abrasion. The metal strip forms a protection against water abrasion of the airfoil element on which the complex is attached.

Abstract: A method for structural component crack testing comprising: a) identifying a structural component hole and inserting a probe thereinto; b) for different emission directions, automatically performing the following: b1) controlling a probe ultrasound beam emission; b2) measuring a probe signal; b3) if the measured signal amplitude is above a predetermined threshold: determining a distance between the probe and a structural component discontinuity point; recording a data set comprising at least the distance between the probe and the discontinuity point, together with a data element corresponding to the probe emission angular direction, c) automatically searching for data sets corresponding to characteristic discontinuity points, and consequently establishing a correspondence between the probe emission angular directions and an angular reference frame linked to the component; d) based on the recorded data sets, automatically determining the discontinuity point positions; e) determining a dimensional characteristi

Abstract: A method for the non-destructive ultrasonic testing of a part by the analysis of echoes returned by the part in response to the emission of an ultrasonic wave via an ultrasonic transducer, includes a step of determining a variable gain curve and a step of correcting the amplitude of the echoes returned by the part according to the variable gain curve and the moments of reception of the echoes. The method further includes steps of: producing a wave function representative of an ultrasonic transducer; producing transfer functions Fm representative of the frequency responses of reference samples Rm of the material forming the part; and calculating reference attenuation values between the wave function and the results of calculations of filtering of the wave function by the respective transfer functions Fm of the reference samples Rm.

Abstract: A device for weighing aircraft includes a weighing platform configured to receive a undercarriage leg of the aircraft and to generate weighing signals, a first calculation unit configured to calculate weighing information from the weighing signals generated by the weighing platform, a communication unit configured to transmit to a central device and to receive signals including at least one signal representing the weighing information calculated by the calculation unit, and a ground rolling unit configured to move the weighing platform over a surface.

Abstract: A method for manufacturing an aircraft leading edge panel, includes a step of overmoulding a coating onto a sheet positioned in a cavity of a mould, which cavity is delimited by a shaping surface which exhibits an optimized surface finish. The coating includes, after the overmoulding step, an exterior face which corresponds to the exterior face of the panel that is to be obtained and which exhibits an optimized surface finish conferred by the shaping surface of the mould. A panel may be obtained using this method and a leading edge includes at least one such panel. Because of the optimized surface finish of the exterior surface thereof, the panel contributes to extending the regions of laminar flow.

Abstract: In order to reduce the mass of a primary structure of a mounting pylon for an engine of an aircraft, the mounting pylon includes a box and a rear sub-structure fastened to the box which includes two lateral panels, each equipped at its rear end with a first linking portion through which passes a first connection orifice that is designed to receive a connection pin of a lateral front wing attachment. The rear sub-structure is made in one piece and includes two opposite lateral flanks that are respectively fastened to the two lateral panels of the box by fastening elements. Each lateral flank has a second linking portion through which passes a second connection orifice that is aligned with the first connection orifice, and is also designed to receive the connection pin of the lateral front wing attachment.

Abstract: A method and a tool for repairing a composite-material panel of an aircraft with at least one repair part made of composite material without using an autoclave. The repair method includes the steps of preparing the panel, placing at least one repair part made of composite material on the second face to cover a damaged zone, positioning a vacuum bag configured to sealingly cover the repair part, polymerizing or consolidating the repair part, compressing the vacuum bag against the repair part using a compression plate concomitantly with the step in which the repair part is polymerized or consolidated.

Abstract: A device for cooling at least one autonomous electric power source of an aircraft, includes: an inlet for air cooling a cooling fluid; the cooling fluid being fed towards at least one autonomous electric power source of the aircraft; a convergent hot air outlet, including moving elements for controlling the air flowrate; and supervision elements of the aircraft, which control the moving elements for controlling the air flowrate depending on the need for cooling of the autonomous electric power source. A method for cooling at least one autonomous electric power source of an aircraft and an aircraft including such a device are also described.

Abstract: An electric propulsion assembly for an aircraft includes a nacelle having a nacelle cowl which defines an inner space for arranging an electric propulsion unit, which includes a blower, of the aircraft. An electric motor assembly is placed in the inner space and connected to the propulsion unit to supply power to the propulsion unit. An airflow generated by the blower flows in a space between the motor assembly and the nacelle cowl defining a duct to supply thrust to the aircraft. A power electronics system has at least one heat exchanger to transfer thermal energy from the system to a work fluid to cool the system. The heat exchanger is placed to project at least partially into the duct, so that the work fluid consists of the air flow generated by the blower.

Abstract: A device for maneuvering ground support equipment on an airport stand. Included in the device are a moving apparatus having a system for coupling with the ground support equipment, configured for maneuvering the ground support equipment according to a predetermined trajectory; and a remote control configured for remotely controlling the movements of the moving apparatus according to the predetermined trajectory. The device also relates to an item of ground support equipment on an airport stand which includes a connecting plate configured for being coupled to a moving apparatus of the device.

Abstract: This relates to a System and a method for determining weight of freight units and baggage. Such a system comprises a Unit Load Device (ULD), an internal system of the Unit Load Device (ULD) and a digital memory unit, wherein the internal system is configured for retrieving individual identification and weight data of items within the Unit Load Device (ULD), for calculating a gross weight of the Unit Load Device (ULD) by summing the individual weight data of the items together with empty weight data of the Unit Load Device (ULD) and for storing a list of all identified items based on the identification data as well as the calculated gross weight of the Unit Load Device (ULD) in the digital memory unit.

Abstract: An aircraft including a fuselage and at least one wing comprising, on the aerodynamic plane, a plurality of distributed airfoils separated from one another, numbering more than 10, and arranged inside an enclosing space bearing on the airfoils. The shape and dimensions of the enclosing space correspond to the shape and dimensions of a simple wing of conventional structure, which is adapted to the aircraft taking account of the weight and flight speed of the aircraft. Advantageously, the airfoils are arranged such that the cross-section of the enclosing space in a vertical plane XZ of the aircraft matches the shape of the aerodynamic profile of the simple wing of conventional structure. The airfoils are arranged, for example, to produce a V formation in plan view, with the tip pointing forwards.

Abstract: A drill bit having an interior canal for liquid nitrogen to pass longitudinally through the body of the drill bit. The canal has, on the side of a cutting edge of the drill bit, at least one liquid nitrogen ejection duct that opens near the cutting edge which is formed by an insert made with polycrystalline diamond fixed to the body of the drill bit. A device for drilling a metal-composite stack includes the drill bit, a liquid nitrogen production unit and a distribution network to distribute the liquid nitrogen. The device drills through a metal-composite stack in a single pass of the drill bit. The liquid nitrogen at cryogenic temperature is conveyed close to the cutting edge, at least while the cutting edge is in contact with the metallic material.

Abstract: An induction heating system and a method for controlling a process temperature for induction heating of a workpiece. The induction heating system comprises an inductor configured to generate an alternating magnetic field in response to an alternating current supplied thereto, a magnetic load comprising a magnetic material, the magnetic material having a Curie temperature and being configured to generate heat in response to the alternating magnetic field being applied thereto, the magnetic load being connectable to the workpiece in a heat-conducting manner so as to transfer the generated heat to the workpiece, and a control unit configured to control the process temperature for manufacturing the workpiece by adjusting the alternating magnetic field when the temperature of the magnetic material is in a temperature control range around or below the Curie temperature of the magnetic material, the temperature control range being dependent on the magnetic material of the magnetic load.

Abstract: A retractable chair for an aircraft cabin which is connected in use to a wall of the cabin, and includes an articulated frame having a back and a seat; a support which is connected to the frame, and fitted such as to be mobile on the wall around an axis of rotation; and at least one covering stretched on the frame. The fact of pivoting the support relative to the wall makes it possible to be able to incline the back, which contributes towards improving the comfort of the chair.

Abstract: An ultrasound probe for inspecting a bore opening onto a peripheral surface, includes a coupling support which has: a through-orifice to allow the ultrasound probe to pass through, a contact face, which has an external diameter greater than the diameter of the bore to be inspected and is configured to be pressed against the peripheral surface of the bore in order to close the bore.

Abstract: An ultrasound probe for inspecting a bore opening onto a peripheral surface includes an offcentring device which includes at least two strips which are elastically deformable, connected to the ultrasound probe and configured to keep the emission head of the ultrasound probe pressed firmly against the wall of the bore that is to be inspected.