Abstract: A method for assembling a fuselage section which comprises producing a lower part of the section from at least two panels and an upper part of the section from at least two panels, then assembling the lower and upper parts so as to obtain the fuselage section. A lower or upper mounting support, a gear and a production unit are used in the method.

Abstract: A device for lacquer transfer includes a frame, a transfer roller with a circumferential lateral wall, a drive unit and a lacquer application unit. The lacquer application unit is mounted on the frame and applies lacquer to a work surface of a work piece while the device is moved in an application direction across the work surface. The drive unit drives the transfer roller in a rotation direction about an axis of rotation. An outside contact surface of the lateral wall comprises a plurality of depressions forming a predetermined structure. The transfer roller rolls with the outside contact surface on the work surface of the work piece for transferring the predetermined structure defined by the depressions in the outside contact surface to lacquer previously applied to the work surface by the lacquer application unit.

Abstract: An apparatus for setting a dimension parameter relating to a value of a shock absorber dimension of an extension of a shock absorber of an aircraft landing gear. The apparatus includes a processor configured to identify a respective range of values relating to each of a plurality of operating characteristics under which the shock absorber may operate, and identify a respective probability distribution of values for each of the operating characteristics within the identified ranges. The processor is also configured to perform a generation process for generating a plurality of values of the shock absorber dimension by repeatedly selecting, as input into a computer-implemented model for determining a value of the shock absorber dimension, a value of each of the operating characteristics based on the respective probability distributions, and determining a given value of the shock absorber dimension using the selected values and the computer-implemented model.

Abstract: A firing simulation scope, for installation on a rifle, includes an inertial measurement unit, a windage correction adjustment device, an electronic system, a microphone, a display and an interface for connection to a control station.

Abstract: A method for manufacturing a composite assembly of an empennage and rear-fuselage having a continuous skin solution. The method obtains parts of the sub-structure. For each part, it is obtained a plurality of stringers performs and frames preforms by composite tooling. The frames are transferred to curing frames molds and a sub-structure skin is obtained. Furthermore, the method includes integrating the parts over an integration tool having cavities for locating the curing frames molds and the stringer performs. Furthermore, the method includes co-curing the integration tool in one shot on an autoclave, demolding the sub-structure skin sections and disassembling the curing frame molds to obtain the composite assembly of the rear section.

Abstract: A combined seat/stair arrangement for a multi-deck vehicle, in particular a multi-deck aircraft or spacecraft, include a foldable passenger seat; a stair which is designed to connect an upper deck to a lower deck via a stair hatch and at least one floor flap which movable between a use position of the stair with the stair hatch open and a use position of the foldable passenger seat with the stair hatch closed, wherein, in the use position of the foldable passenger seat, the at least one floor flap closes at least a partial region of the stair hatch, and wherein the floor flap is designed with a seat attachment, to which the foldable passenger seat is attached.

Abstract: A device for lacquer transfer is disclosed having a frame, a transfer roller with a circumferential lateral wall, and a nozzle for dispensing lacquer. The nozzle is arranged contactless to or in direct contact with the outside contact surface of the lateral wall for dispensing lacquer into respective depressions in the lateral wall while the transfer roller is rotated about the axis of rotation. The transfer roller is configured to roll with the outside contact surface on a work surface of a work piece for transferring the lacquer from the depressions to the work surface of the work piece. The transfer roller includes a rim and a tire, wherein the rim is mounted to the frame rotatably about the axis of rotation by the first end and extends between a first end and a second end along the axis of rotation, wherein the tire is mounted on the rim and includes the lateral wall.

Abstract: A locking pin associated with one of a fixed wing and a wing tip device, and a bush associated with the other of the fixed wing and wing tip device, the bush configured to receive the locking pin. The bush is located within a bush housing arranged to allow relative movement of the bush in the direction of a longitudinal axis of the locking pin when the locking pin is received within the bush.

Abstract: A hydraulic system 300 for an aircraft including a backup hydraulic pressure source 216 to provide hydraulic pressure to a brake 222 in the event of a failure condition of a primary hydraulic brake pressure source. The hydraulic system 300 also includes a landing gear backup system to provide hydraulic pressure to enable extension and/or retraction of landing gear 100. The backup hydraulic pressure source 216 is arranged to provide hydraulic pressure to the landing gear backup system in the event of a failure condition of a primary landing gear hydraulic pressure source.

Abstract: An assembly including a support tower and at least two support systems, each bearing a panel of a section of an aircraft fuselage and including four fixing points. The support tower includes a tower extending along an axis X, a seat on which the tower is mounted and which is rotationally mobile about the axis X, and, for each fixing point, a fixing base mounted on a three-dimensional adjustment system mounted on the tower and motorized to displace the fixing base in two horizontal directions and one vertical direction, where each fixing point and the associated fixing base can be locked with one another to ensure the fixing of one with the other, and that can be unlocked to allow them to be separated. Such an assembly makes it possible to keep the various elements of the section vertical during assembly and allows for a space saving on the ground and a saving on transfer utilities.

Abstract: A method and device for inspecting the structural damage on the skin of an aircraft after a lightning strike, the skin has marks derived from the lightning strike, wherein the marks represent a Visual Damage (VD) and a Structural Damage (SD). The method includes for every mark: measuring the area of paint that has been removed by the lightning strike, and comparing the measured area with an area threshold value, wherein the threshold value is related to the Structural Damage (SD) of every mark.

Abstract: A turbofan with a secondary duct and including a fixed structure and a mobile assembly including a frame with openwork regions. The mobile assembly is translatable between advanced and extended positions. The openwork regions are positioned across the window in the extended position. A plurality of blocking doors is provided, each being mobile between stowed and deployed positions. An array of rams move the mobile assembly. A cascade grille mounts on the frame across the openwork region. The grille slides on the frame parallel to the translational direction. For each grille, a rear stop limits rearward movement, and a compression spring pushes the grille to the rear for abutment against a rear stop. For each grille, the fixed structure comprises a stop element against which the grille abuts upon movement from the advanced position to the extended position.

Abstract: A monitoring system for an aircraft has sensors that are used to sense the presence of objects around the aircraft for collision avoidance, navigation, or other purposes. At least one of the sensors may be configured to sense objects around the aircraft and provide data indicative of the sensed objects. The monitoring system may use information from the sensor and information about the aircraft to determine an escape envelope including possible routes that the aircraft can follow to avoid colliding with the object. The monitoring system may select an escape path based on the escape envelope and control the aircraft to follow the escape path to avoid collision with one or more objects.

Abstract: A flight control system for an aircraft comprises a set of actuators for controlling the aircraft and a set of flight control computers only made up of a set of duplex type main computers and of at least one backup computer. All the main computers are configured to implement auto-pilot laws for the aircraft. The set of main computers comprises two computers from a first hardware type, configured to control actuators of the set of actuators as per a first tolerance level and two computers from a second hardware type, different from the first hardware type, configured to control actuators of the set of actuators as per a second tolerance level, less stringent than the first tolerance level.

Abstract: A control mechanism includes an existing aerodynamic device, such as a slat 5, that moves between at least one deployed position and a retracted position; and a load-alleviation mechanism 10 arranged to move the aerodynamic device into a load-alleviation position in response to a load 18, such as a gust of wind acting over a predetermined threshold. During flight, an aircraft can experience gusts of wind that cause strain on the wings 4. The addition of a load-alleviation mechanism to a pre-existing aircraft component allows for gust loading to be alleviated without adding significantly to the weight or complexity of the aircraft. The control mechanism may be retro-fitted to existing aircraft.

Abstract: A 3D printed drilling template (20, 30a, 30b, 30c) including: a rigid framework able to be manipulated by an operator or an automaton, and a set of traversing (22, 32a, 32b, 32c, 33c) orifices in the framework and arranged to guide the drilling of holes into a structure on which the drilling template is mounted, wherein the drilling template (20, 30a, 30b, 30c) is designed or revised on an ad-hoc basis and manufactured by 3D printing and using a 3D printing material based on a polymer material mixed with powdered graphene.

Abstract: A device for lacquer transfer includes a frame, transfer roller with circumferential lateral wall, nozzle for dispensing lacquer, and hardening unit, the hardening unit formed as a UV-light unit for hardening the lacquer in a contactless way by emitting UV-light, and is within an interior space defined by the transfer roller. The lateral wall of the transfer roller is transparent for UV-light, and the hardening unit is arranged such that UV-light is emitted towards the work surface upon which the lateral wall of the transfer roller rolls, to harden the lacquer after it being transferred to the work surface. Using the device, lacquer transfer can occur from the transfer roller to the work surface more reliably. The device includes a light shield between the hardening unit and outside contact surface with at least a portion of the outside contact surface provided with lacquer is shielded from UV-light emitted from the hardening unit.

Abstract: An indication device for monitoring the structural integrity of a repair location on a laminate structure, produced from a composite material, of a part of an aircraft outer skin is specified. The indication device has at least one elongate, thin indicator strip. The indicator strip is detachably applied to the outer layer of the laminate structure in the immediate vicinity of the repair location. The indicator strip is designed to indicate a predefined residual strength of an adhesive joint of a repair patch to the surrounding composite material.

Abstract: A rail for an aircraft floor includes an upper plate for supporting a set of floor panels covering the plate, and a lower stiffening structure. The rail is formed by a beam and by an anticorrosion protection. The beam is at least formed by a body made of a first material and defining the lower stiffening structure and an upper platform. The anticorrosion protection fully covers an upper face of the upper platform and forms therewith the upper plate of the rail, thus layered. The anticorrosion protection is at least formed by a protective sheet made of a second material that is more corrosion resistant than the first material and is selected from a metal and a fiber-reinforced plastic composite material. Such a rail exhibits good corrosion resistance at a moderate cost.

Abstract: An improved procedure and associated hardware to allow a satellite to switch antenna coverages according to predefined repetitive sequences and to align switching of the antenna sequence with ground data sequence switching. The principle of synchronisation of the sequence switching is based on the anticipation of the exact time at which change in beam hopping sequence occurs at the satellite, such that a change to a beam hopping sequence can be reflected in ground data sequence switching without losing connectivity between the satellite and ground segment.