Abstract: A gas dehumidification device having two heat exchangers, each including a first and second fluid line. Each second fluid line at least partially surrounds the respective first fluid line. Each heat exchanger thermally couples a fluid in the respective heat exchanger second fluid line with a first coolant on an outside surface of the respective heat exchanger second fluid line. The gas dehumidification device further comprises a two-position valve. In a first position, a fluid comprising a higher temperature than the first and/or second coolant is conducted into the first heat exchanger first fluid line and in the second position, the fluid is conducted into the second heat exchanger first fluid line. A controller is configured to place the valve selectively into the first or second position.

Abstract: An actuator assembly for moving an aircraft wing tip device is disclosed. The wing tip device is rotatable about a hinge axis relative to a fixed wing of the aircraft. The hinge axis is orientated non-parallel to a line-of-flight direction of the aircraft. The actuator assembly includes a primary shaft having an axis of rotation orientated substantially parallel to the line-of-flight direction, a motor to cause rotation of the primary shaft, and a secondary shaft orientated substantially parallel to the hinge axis. The secondary shaft is couplable to the primary shaft and is arranged to rotate the wing tip device in response to the rotation of the primary shaft.

Abstract: An aircraft cooling system and an aircraft having an aircraft cooling system of this type. The aircraft cooling system comprises a ram air duct, a nozzle arranged in the ram air duct and connected to a first water-conducting line, and a refrigeration device. The refrigeration device comprises a heat exchanger thermally coupled to the refrigeration device and configured to release waste heat generated by the refrigeration device to cooling air present in the ram air duct, a first water separator configured to separate off water from the air cooled by the refrigeration device, and a water outlet configured to conduct water obtained in the first water separator into the first water-conducting line. Furthermore, the water outlet has an inlet configured to be connected to a second water-conducting line, wherein the water outlet is furthermore configured to generate a negative pressure at the inlet.

Abstract: A device for inserting the blind fastener in the fastening site, a pulling and extracting device for swaging the blind fastener in the fastening site and a passive compliance device that binds the inserting device to the pulling and extracting device. The passive compliance device allows the installation of the bind fastener without sensors.

Abstract: A turbofan having a nacelle comprising a slider mobile in translation between advanced position and retracted positions to open a window between a duct and the exterior, a plurality of blades, each one being rotatably mobile on the slider between stowed and deployed positions, and a maneuvering system moving each blade and comprising for each blade, a shaft rotatably mobile on the slider and onto which the blade is fixed, for each shaft, a balance beam fixed to the shaft and having first and second ends, for three consecutive balance beams, two connecting rods where the first connecting rod is mounted articulated between the first balance beam and the second balance beam, and where the second connecting rod is mounted articulated between the second balance beam and the third balance beam, and an actuation system rotating one of the connecting rods in one direction and in the other.

Abstract: A cargo loading platform for an aircraft, with a plate-like supporting structure, which is configured to support or to receive cargo, and a lifting device. The lifting device is arranged asymmetrically on the plate-like supporting structure and can be moved from a stowage position to a lifting position. In the stowage position, the lifting device is arranged here above a lower side of the plate-like supporting structure and, in the lifting position, is at least partially arranged below the lower side of the plate-like supporting structure. This permits asymmetrical raising of the plate-like supporting structure by the lifting device, as a result of which steps during the transportation of the cargo loading platform can be easily and rapidly overcome. Furthermore, a cargo loading apparatus and a cargo container each with such a cargo loading platform, and also an aircraft with such a cargo loading apparatus are described.

Abstract: A multifunctional seat arrangement for a passenger cabin of a vehicle includes at least one first seat and one second seat which is laterally arranged directly adjacent to the at least one first seat. The second seat is narrower than the first seat, and the second seat has a pivotable seat surface extension which is pivotable into different positions relative to the seat surface of the second seat. Support functions and a child seat function or baby carrier function may be achieved thereby.

Abstract: A curable composite bush for an aircraft joint comprising a generally hollow cylindrical body formed from a matrix material impregnated with a reinforcement material substantially composed of fibers, the fibers being oriented in a generally circumferential direction about a longitudinal axis of the bush. The body may define a plurality of corrugations extending between an inner and an outer diameter of the bush to improve the compressibility of the bush in a direction substantially collinear to a longitudinal axis of the bush.

Abstract: A planar pressure bulkhead for an air- or spacecraft, including a first planar wall designed as a pressure seal for a fuselage structure, a second planar wall arranged opposite the first wall, and a reinforcing structure which is arranged between the first and the second wall and which includes at least one circumferential monolithic reinforcing element. Furthermore, the present disclosure provides an air- or spacecraft, including a fuselage structure and a planar pressure bulkhead that is coupled to the fuselage structure in a circumferentially continuous manner.

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 sound-proofing covering comprising a cellular structure, each cell of which comprises a duct extending at least between the first face and the second face of the covering. The duct is formed between an outer wall and an inner wall of the cell and has a restriction of its cross section. The outer and inner walls have rounded forms, without sharp edges. The cell comprises a cavity in which the duct emerges. Thus, each cell forms a resonator comprising a neck formed by the duct and the cavity. Each cell is conformed such that the duct and the cavity are formed on either side of the inner wall. Such a covering is particularly suitable for reducing acoustic waves in aircraft engine plant nacelles, particularly in the low frequencies.

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 kit of parts for forming an aerofoil structure including a torsion box for use in attaching a fixed leading or trailing edge structure to the torsion box, and a fixed leading or trailing edge structure attachable to the torsion box. The torsion box includes a first mounting feature. The fixed leading or trailing edge structure includes a second mounting feature configured to engage with the first mounting feature. The first mounting feature and the second mounting feature are mutually configured to permit the first and second mounting features to be moved into engagement with each other along a first direction, and to prevent relative movement of the first and second mounting features along a second direction when the first and second mounting features are engaged with each other.

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 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: 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 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: 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 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.