Abstract: A system comprising a discharge valve that allows some of the fluid generated by a fluid generating source and intended for a drive torque generating member for a rotary element of a mechanical device to be removed so as to limit the corresponding rotational speed, this being done for a length of time that allows a thermal gradient to be reduced sufficiently that a phenomenon of deformation of said rotary element can be prevented.

Abstract: A method for manufacturing a fiber composite component includes providing a semi-finished textile product; injecting a matrix material into the semi-finished textile product so as to form an infiltrated semi-finished product, wherein the matrix material includes a thermoplastic film having particles dispersed therein; and curing the infiltrated semi-finished product.

Abstract: The device according to the invention consists of associating a laser inspection head including a source emitting a laser beam swept along a defined axis and a handling robot seeing to the movement and spatial orientation of parts whose structure requires inspection. The inspection head and the handling robot are configured and arranged across from one another such that the inspection head occupying a stationary position, the handling robot can move the part to be inspected across from the inspection head, such that the sweep of the laser beam combined with the movement of the part in a direction perpendicular to the sweeping direction makes it possible to inspect the entire surface of the part. In one particular configuration, the handling robot makes it possible to vary the orientation of the part relative to the direction of the laser beam so as to have optimal lighting of the part.

Abstract: A joining part with a wing comprises a through bore defining a fastening direction perpendicular to the wing. The wing comprises at least one non-through pocket configured to reduce the stress gradient in a peripheral zone of the through bore and/or at least one relief configured to reduce the stress gradient in a peripheral zone of the through bore, the non-through pocket forming a cavity in the thickness of the wing and comprising a curved side at a distance from the peripheral edge of the through bore. The joining part may be part of a lug, such as, for an aircraft fitting.

Abstract: The invention consists of a system allowing remote wireless transfer of energy from a base station to a moving object, in particular a drone, moving in a given zone around the base station. The system includes means for tracking the moving object so as to determine the position of the moving object relative to the base station at any time, means for transmitting a synthetic acoustic wave focused in the direction of the moving object, these two means being located at the base station and powered by the base station, and acoustic reception means, located on the moving object, for receiving the acoustic wave transmitted by the base station and converting the received acoustic wave into an electrical signal and then into a power supply voltage for a battery.

Abstract: An air input structure includes an air input lip and a front reinforcement frame placed inside the air input lip. The front part of the air input lip has a plurality of segments distributed angularly along the leading edge of the air input lip, two adjacent segments being separated by an intermediate part having an excess thickness. Each segment has four edges, each having an excess thickness relative to the rest of the segment. Thus, the air input lip has a lighter structure.

Abstract: A machine tool for carrying out operations on a part includes a longitudinal rail, a transverse arm, a module for connection between the transverse arm and the longitudinal rail, the module being fitted in translation on the longitudinal rail, a tool which is supported by the transverse arm, and a retention unit which is arranged at one end of the transverse arm, and includes at least one sucker. The machine tool has an assembly configuration—in which the retention unit and the tool are positioned respectively on both sides of the longitudinal rail, such that the tool is fitted cantilevered relative to the longitudinal rail. This provides the machine tool with great polyvalence, in that it makes it possible to carry out operations in areas which in particular have significant curvatures, which are difficult to access, or which are unsuitable for securing of the sucker(s) of the retention unit.

Abstract: Awing box of an aircraft with a stiffened shell structure, consisting of fiber reinforced material includes a skin for absorbing shear loads, and several stringers arranged on the inner side of the wing box for absorbing axial loads, in which at least 60% of the mass of the stiffened shell structure is concentrated in the stringers, wherein the stringers provide at least 80% of the axial stiffness of the stiffened shell structure. In the specific case of wing structure, this embodiment allows the use of unbalanced laminates for the skin to induce higher nose-down twist of the wing box without any loss in bending stiffness and so envisaging higher weight saving capability.

Abstract: An electrical energy distribution network in a transport vehicle, such as an aircraft, includes nodes to which at least one power supply source and at least one equipment can be connected by external links. The nodes are interconnected by internode links forming at least one mesh in a meshed network, each mesh being polygonal of order higher than or equal to three, at least one node of each mesh being an active node controlled by a management unit. The active nodes include switches and transmit physical operating characteristics measurements to the management unit, which configures the active nodes according to said measurements so as to enable each equipment to receive power supply via the meshed network. Flexibility in configuration of the electrical energy distribution network is thus achieved.

Abstract: A monitoring system comprising ultrasound sensors to monitor the structure of a composite material part during production is automatically calibrated using reference sensors mounted on reference blocks and placed in the production environment of the part. The automatic calibration comprises actuating a reference sensor to transmit an ultrasonic wave and measuring the amplitude of a reference echo constituted by the transmitted ultrasonic wave after it has passed through the reference block. The measured amplitude is compared to a set point value and the gain is applied to the reference sensor to obtain an amplitude value of the reference echo substantially equal to the set point value. The gain applied to the reference sensor is applied to the ultrasound sensors of the same type as the reference sensor. The operation is performed for each reference sensor, and successively for all of the stages of production of the part.

Abstract: An aircraft with an electric propulsion arrangement which includes a fuselage, a wing system attached to the fuselage, and a tail unit attached to a rear part of the fuselage. The electric propulsion arrangement is arranged on each side of the fuselage, an electrical energy generator and electricity storage and supply devices are arranged substantially along a longitudinal axis of symmetry of the fuselage. The aircraft thus incorporates a hybrid motorization.

Abstract: A lightning protection device for an antenna receiver includes a shield for a coaxial cable connected to the antenna, and a high-pass filter mounted in series relative to the shield and capable of limiting the low-frequency power flowing in the coaxial cable, including a capacitor and an inductor lower than 1 ohm at the lowest frequency used by the receiver, the capacitor including at least one layer of a conductive material embedded in a printed circuit. The capacitor may be made of a printed circuit including at least two floor plans, each of which is connected to the ground of a connector of the coaxial cable. The printed circuit may include at least one layer of a highly pervious material sandwiched between two layers of a conductive material.

Abstract: A device for moving aircraft along the ground includes at least one runway and at least one aircraft. The aircraft is secured to a tractor element having a magnetic mass formed mainly of type II superconductor material and the runway includes stator coils arranged in the runway with at least one line of coils parallel to an axis of the runway. A command/control system supplies power to the stator coils to generate a magnetic field that levitates the tractor element, magnetized beforehand into a phase II superconducting state, above the runway.

Abstract: An aircraft comprising at least two engines and an electronic management arrangement comprising a control computer for each engine, each computer being configured for monitoring the operation of its associated engine and for activating an engine protection mode when the engine operation exceeds predetermined operational limits. The electronic management arrangement furthermore comprises an engine interface device to which the control computers are connected, the device prohibiting the activation of a protection mode by a control computer when a protection mode is activated by another control computer. A monitoring device is connected to the control computers and receives an information signal from each control computer to indicate if a protection mode is activated and transmits, in the case where a protection mode is activated on at least two engines, a control signal to the control computer having last activated a protection mode to cancel the activation of the protection mode.

Abstract: In an aircraft having a central maintenance computer, an ACMS system and a communications unit allowing communications with a ground station, a maintenance aid device comprises a processing unit configured to: store a trigger condition dependent on at least one aircraft maintenance data item and/or at least one aircraft flight data item; acquire first data emanating from the central maintenance computer and/or second data emanating from the ACMS system; verify whether the trigger condition is met, on the basis of the first data and/or of the second data; and if the trigger condition is met, send the communications unit, a dataset comprising maintenance data emanating from the central maintenance computer and aircraft flight data emanating from the ACMS system.

Abstract: A combination comprises an aircraft wing trailing edge section and an adjustment body. The adjustment body comprises a tapered cross section in a local chord axis direction of the wing trailing edge section, a lower adjustment body surface connected to a top surface of the aircraft wing trailing edge section and a back-end surface having a height. The adjustment body is positioned such that the back-end surface is flush with the trailing edge of the aircraft wing trailing edge section. Attaching the adjustment body onto a top surface of the wing trailing edge section leads to compensation of an offset rolling moment due to unavoidable structural shape deviations of the aircraft and eliminates additional structural reinforcement requirements on the trailing edge compared to edge wedges mounted on the bottom surface of trailing edges. The trailing edge section may comprise a flap.

Abstract: In an aircraft duct formed with pipes connected in pairs via connectors in which the pipes are mounted with the possibility of axial displacement, there exists a risk that a pipe of the duct, with a dimension greater that the dimension of the nominal pipe, is mounted instead and in place of the latter. In this case, the wrongly mounted pipe would risk not having sufficient clearance in axial translation. In order to solve this problem, it is disclosed to equip one of the relevant connectors with an obstacle limiting the travel of the nominal pipe and preventing the mounting of a pipe with a greater dimension belonging to the duct. A method for assembling an aircraft portion is also proposed, in order to benefit from the particularities of the duct.

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 and a system for the detection and passivation of an electric arc on at least one connecting element of an electrical device. The system comprises an acoustic acquisition channel configured for the acquisition of acoustic signals emitted by the connecting element, an electric acquisition channel configured for the acquisition of electric signals which are representative of the electric current intensities supplying the connecting element, and a correlator coupled to the acoustic and electric acquisition channels, configured for the evaluation of a correlation between the acoustic and electric signals and for the tripping of an appropriate cut-off signal for the interruption of an electric circuit relative to the connecting element, where the correlation is representative of the initiation of an electric arc.

Abstract: A taxiing system for an aircraft including an undercarriage having a wheel, includes an electric motor associated with the wheel, an electric controller of the electric motor, connected to an output of an electrical power supply, and a taxiing control computer configured to determine control instructions for the electric motor and to transmit these instructions to the electric controller. The taxiing control computer is configured to receive braking of the aircraft commands during the taxiing of the aircraft and to determine control instructions for the electric motor corresponding to operation of the motor in generator mode when it receives a braking command. The electric controller is connected to an energy absorber making it possible to absorb the electric energy produced by the electric motor when the latter is operating in generator mode.