Abstract: A method for assembling an aircraft pylon having a primary structure and at least one internal system at least partially positioned within the primary structure, wherein the internal system is positioned inside the primary structure before the last lateral panel of the primary structure is attached. The absence of one of the lateral panels facilitates the installation of the internal systems.

Abstract: A method for producing an acoustically resistive structure includes the steps of creating, consolidating and cutting a first layer of reinforcing fibres embedded in a first thermoplastic resin having a first melting point so as to obtain an interlayer, a step of laying a second layer of reinforcing fibres against a first face of the interlayer, a second consolidation step of consolidating the second layer of reinforcing fibres embedded in a second thermoplastic resin having a second consolidation temperature lower than the first melting point of the first resin so as to obtain a non-perforated external layer bound to the interlayer, a step of perforating the external layer and a step of laying an internal layer on a second face of the interlayer. An acoustically resistive structure obtained from the method as well as a sound-absorption panel including such an acoustically resistive structure are also described.

Abstract: An aircraft interior lining component is formed at least partially of a thermoplastic foam material and includes a first surface which faces an interior of an aircraft cabin when the aircraft interior lining component is mounted in an aircraft, and a second surface which faces away from the interior of the aircraft cabin when the aircraft interior lining component is mounted in an aircraft. The second surface of the aircraft interior lining component includes at least one supporting section and at least one surface section adjacent to the supporting section and recessed relative to the supporting section. The supporting section is dimensioned and arranged so that it is supported, when the aircraft interior lining component is mounted in an aircraft, on an element of a primary structure of the aircraft at least when a predetermined load acts on the first surface of the aircraft interior lining component.

Abstract: The method for producing bindings includes: positioning at least one binding bobbin on a machine having: a winding bobbin including a device for supporting and a notch, an electric motor which is coupled to the winding bobbin; and at least one shaft capable of receiving a binding bobbin, supporting a free end of the binding of the binding bobbin on the winding bobbin, by the device for supporting; supplying electricity to the electric motor of the machine to drive the winding bobbin in rotation, so as to wind the binding of the binding bobbin over a plurality of turns around the winding bobbin; stopping the supply of electricity to the electric motor of the machine; and in the region of the notch of the winding bobbin, cutting the plurality of turns of bindings wound onto the winding bobbin.

Abstract: A device for controlling an opening forming an air inlet or air outlet in an outer skin of a vehicle. The device comprises a multiple-member inlet ramp, which is configured to vary at least one of a degree of opening of the opening and a cross section of an air duct connected to the opening; an actuator, which is coupled to the multiple-member inlet ramp and is configured to move the multiple-member inlet ramp into a shape related to at least one of a certain degree of opening and a certain cross section; and a movement control device, which is configured to control a movement of the multiple-member inlet ramp.

Abstract: An internal structure of a primary exhaust duct of a turbomachine. The internal structure comprises a primary wall comprising a surface of revolution, allowing air to pass through the orifices and forming an internal surface of the primary exhaust duct, an interior skin, comprising a surface of revolution, arranged inside the primary wall and extending between an upstream flank for facing toward the front of the turbomachine and a downstream flank for facing toward the rear of the turbomachine, and a plurality of spacers angularly distributed around a periphery of the interior skin and fixed between the primary wall and the interior skin. The particular way in which the interior wall is fixed makes the internal structure easier to construct and allows attenuation of noise at chosen frequencies.

Abstract: An aircraft fuel tank system including a fuel tank compartment for containing liquid fuel and having a float-activated valve arranged to become positively buoyant when immersed in liquid fuel so that the float moves up to a raised position which causes the valve to close and prevent liquid fuel from flowing out of the fuel tank compartment through the valve. The float is also arranged to move down to a lowered position in response to a level of the liquid fuel in the fuel tank compartment dropping, the movement of the float to the lowered position causing the valve to open and permit liquid fuel to flow out of the fuel tank compartment through the valve. A pressure-activated valve may be used as an alternative to the float-activated valve.

Abstract: A three-dimensional printing device includes a movable unit with a superconductor and a printing head arrangement for printing a printing material, a magnetic field generator adapted to generate a magnetic field, and a control device. The magnetic field generator and the movable unit are adapted for coupling in a force-locking manner by means of frozen magnetic flux, and the controlling device is adapted to control a magnetic field strength of the magnetic field generator.

Abstract: A seat system for a cabin of a transportation system includes a first seat unit, a second seat unit, and a rail system attachable to a floor of the cabin, having two rails that run parallel to each other, for receiving the seat units on selective positions. A line-up of a plurality of first seat units and at least one second seat unit on the rail system constitutes a seat arrangement. The first seat unit includes a seat frame having a seat cushion and a back cushion. The second seat unit includes a seat frame having a foldable seat cushion and a back cushion. The second seat frame includes two forward seat legs supported on two auxiliary rail segments that are arranged between the rails in a region. The forward seat legs are guidable underneath the seat cushion of a first seat unit arranged in front of it.

Abstract: In controlling pressure in an aircraft cabin, during flight operation, an effective flow cross-sectional area of at least one outflow valve is controlled to adjust air flow exiting the cabin through the outflow valve so pressure within the cabin is controlled according to a predetermined cabin pressure control strategy. During flight operation of the aircraft, an effective flow cross-sectional area of at least one negative relief valve is controlled to adjust air flow entering the cabin through the negative relief valve so a negative differential pressure between the pressure within the aircraft cabin and an ambient pressure prevailing outside of the aircraft cabin is prevented from exceeding a predetermined threshold value. During ground operation of the aircraft, the effective flow cross-sectional area of the at least one negative relief valve is controlled to allow an equalization between pressure within the cabin and ambient pressure prevailing outside of the aircraft.

Abstract: A rigging tool for a control surface of an aircraft, including a laser for outputting a low energy laser beam, a target assembly including a plate including a target point, and a support to sustain the target assembly on a surface of a control surface, and a laser platform provided with structure to rest on a surface of a control surface, having backward and forward extremes, the backward extreme being configured to hold the laser, and the forward extreme including a pair of holes at opposite positions aligned with the output of the laser, such that, in operation, when the laser beam passes through the holes and incises in the target point, a neutral position of a control surface is indicated.

Abstract: A visual output assembly for an aircraft cabin includes at least one electronic display device, a projection screen, an image projector configured to project images onto the projection screen, and at least one illumination device.

Abstract: A wearable manufacturing assistance device (1) for supporting a manufacturing tool (3), the manufacturing assistance device (1) includes a body unit (7) including a fastener (11) for fastening the body unit (7) to the back (13) of a technician (5) in a wearing position (15), and an arm member (9) which has an attachment end (19) attached to the body unit (7) and a tool end (21) opposite to the attachment end (19), wherein at the tool end (21) a mounting device (23) for mounting the manufacturing tool (3) to the arm member (9) is provided. While the wearable manufacturing assistance device (1) is fastened to the back (13) of the technician (5) and is in a wearing position (15), the arm member (9) extends from the attachment end (19) at the body unit (7) over a shoulder (17) and laterally past a head (27) of the technician (5).

Abstract: An aircraft (1) including a wing (5), the wing having an inner region (5a) and an outer region (5b), the inner and outer regions (5a, 5b) being connected by a hinge (11) defining a hinge line about which the outer region (5b) is foldable to reduce the span of the wing. The aircraft (1) includes an actuator (13) arranged to actuate the folding of the outer region (5b) of the wing with an actuation force. The wing (5) is braced by an external strut structure (9) for transferring some of the wing loadings in the outer region (5b) of the wing away from the inner region of the wing (5a). The actuator (13) is arranged to exert the actuation force via the strut structure (9).

Abstract: The disclosure herein relates to a quality control method and system in aeronautical manufacturing. The system comprises a tablet connected to a concession management server, the server being itself linked to an aircraft configuration database, a three-dimensional digital model of the aircraft and a fault database. The element to be inspected is identified using the digital model and the fault is characterized by browsing a predetermined decision tree associated with the element.

Abstract: A shaping tool for forming a semi-finished product which contains reinforcing fibers and is fed to the shaping tool in a continuous process comprises a first shaping-tool element and a second shaping-tool element which is located opposite the first shaping-tool element. The shaping-tool elements have shaping faces which face towards the semi-finished product, at least in certain operating phases of the shaping tool, and which are curved and/or inclined, at least in certain sections, in a direction of conveyance of the semi-finished product through the shaping tool, and/or curved and/or inclined, at least in certain sections, in a direction perpendicular to the direction of conveyance of the semi-finished product.

Abstract: A fuselage rear end of an aircraft, comprising a structural part comprising a skin and longitudinal and transversal reinforcing members and a fairing. The structural part longitudinally spans over the whole rear end and comprises a first portion in which the transversal reinforcing members occupy the whole perimeter of the corresponding fuselage section and at least a second portion in which the transversal reinforcing members occupy only a portion of the perimeter of the corresponding fuselage section. The fairing is located below the second portion of the structural part.

Abstract: A turbine engine ignition system comprising a spark plug having excitation and return terminals, and a spark plug exciter connected to the excitation terminal. The return terminal is connected to an equipotential reference-forming structure, the exciter device is connected to a command line for a signal to supply an excitation signal to the spark plug. The ignition system comprises a control device comprising current and voltage sensors, a first voltage comparator, a second current comparator, and a microcontroller receiving output from the two comparators. The first comparator compares the voltage sensor signal to a first reference value and the second comparator compares the current sensor signal to a second reference value. The microcontroller generates a signal indicating a malfunction of the ignition system if the current sensor signal is lower than the second reference value while the voltage sensor signal is higher than the first reference value.

Abstract: A fault detection system for an aircraft braking system including: a controller configured to receive braking demand information; torque information; wear information; wheel speed information; and brake temperature information. The controller is to calculate an expected maximum temperature of the brake based on the torque information, the wear information and the wheel speed information; to determine whether a significant temperature discrepancy exists between the expected maximum temperature and the brake temperature information; to determine whether a significant torque-related discrepancy exists based on the braking demand information and the torque information.

Abstract: A fiber composite component includes an integrated structural health sensor arrangement, wherein the component includes a plurality of layers of fibers embedded in a matrix material, wherein the layers include at least two strain sensing fibers arranged parallel and at a distance to each other, wherein the strain sensing fibers are lithiated carbon fibers having piezoelectric characteristics.