Abstract: A mobile application device for dispensing a formed fibre composite strand has: a coupling unit for detachably fastening the application device to the handling device for moving the application device; a preforming unit for continuously forming an unprocessed fibre strand into a formed fibre strand with a formed fibre cross section settable by the preforming unit; an impregnating unit for continuously developing the formed fibre strand into a fibre composite strand by impregnation with a matrix material; and a postforming unit for continuously pressing the fibre composite strand to and through the dispensing unit and having a drive unit and an adjustable dispensing unit for continuously forming a fibre composite strand into a formed fibre composite strand with a dispensing cross section settable by the dispensing unit and for dispensing the same such that the formed fibre cross section is at least 70% congruent with the dispensing cross section.

Abstract: A method of producing a fibre composite component having an elastomer seal disposed on a top side at the edge in annular manner around an opening, includes: providing a first, laminar semifinished product having fibres preimpregnated with a first thermoset, incompletely crosslinked matrix material; applying a sealing compound to a particular deposition region at a top side of the first semifinished product so as to form a semifinished composite product including the first semifinished product and the sealing compound applied, the sealing compound being formed by an elastomeric semifinished product; and extrusion-forming the semifinished composite product to give the fully crosslinked fibre composite component having the elastomer seal. The fibre composite component results from crosslinking of the first semifinished product, and the elastomer seal from crosslinking of the sealing compound.

Abstract: A sleeping box for installation in an aircraft includes a casing which is suitable for accommodating a person located in a reclining position parallel to a longitudinal axis of the casing and which has an access aperture in the area of a front side which extends perpendicularly to the longitudinal axis of the casing. The sleeping box also includes a fastening apparatus which is configured to fasten the sleeping box within a passenger cabin of the aircraft in such a way that the longitudinal axis of the casing extends perpendicularly to a longitudinal axis of the passenger cabin and the access aperture of the casing borders on an aisle which is present within the passenger cabin.

Abstract: An aircraft galley including a trolley stowage provided in a main body of the aircraft galley. A wall of the main body includes a first section delimiting the trolley stowage and a second section. The trolley stowage is convertible between a first operational state, wherein the trolley stowage is adapted to accommodate a first number of trolleys, and a second operational state, wherein the trolley stowage is adapted to accommodate a second number of trolleys. The second number of trolleys is greater than the first number of trolleys.

Abstract: Disclosed is an infusion method for the manufacture of a fiber-reinforced composite component with semi-finished textile products in an open molding tool, in which at least one local gas reception space is designed for the reception of volatile substances, such as resin gases and residual air contained in the matrix material and/or in the system, which gas reception space is blocked off from the matrix material by a local semi-permeable membrane; also disclosed is a system for the execution of such a method.

Abstract: A method of installing a fixture, such as a bracket, in a fuselage structure of an aircraft includes the steps of: providing or generating a three-dimensional digital model of the fixture; arranging a head of an additive manufacturing apparatus in the fuselage structure; and forming the fixture in situ in the fuselage structure with the head of the additive manufacturing apparatus based upon the digital model of the fixture. The fixture is installed in the fuselage structure by bonding or fusing the fixture to the fuselage structure as the fixture is formed. A fixture, such as a bracket, which is generated in situ in a fuselage structure of an aircraft based upon a three-dimensional digital model, wherein the fixture is bonded or fused to the fuselage structure as the fixture is formed.

Abstract: A cooling system suitable for cooling food on board an aircraft is provided which includes a chiller device and a first cooling circuit which is adapted to feed cooling energy generated by the chiller device to at least one cooling station, the chiller device includes a second cooling circuit formed separately from the first cooling circuit and is thermally coupled to the first cooling circuit.

Abstract: In a pultrusion method for manufacturing a fiber-reinforced composite product comprising reinforcing fibers embedded in a thermoplastic matrix material, the following is performed along a path of pultrusion: providing a preform; further downstream, inductively heating the preform to a processing temperature of the thermoplastic matrix material; and, further downstream, introducing the preform into a die and consolidating the preform by means of the die while the preform passes through the die.

Abstract: This relates to wireless communication on-board aircraft. More particularly, the present disclosure relates to a method for controlling an on-board aircraft network cell to be used in an on-board aircraft wireless communication network, to such an on-board aircraft network cell configured to be used in an on-board aircraft wireless communication network, to an on-board aircraft wireless communication network comprising at least one such on-board aircraft network cell, and to an aircraft comprising such on-board aircraft wireless communication network. An embodiment of the on-board aircraft network cell comprises at least one Wireless Module unit, at least two Wireless Data Concentrator units, and at least two independent wireless links, each wireless link being established between the at least one Wireless Module unit and one of the at least two Wireless Data Concentrator units.

Abstract: The invention relates to a method and a molding core for producing a fiber composite component (34), in particular in aerospace, comprising the following method steps: introducing a core sleeve (9) into a molding tool (2) for establishing an outer geometry of a molding core (27) to be formed; filling the core sleeve (9) that is introduced with a vacuum-fixable filling material (21); applying a vacuum to the core sleeve (9) and consequently vacuum-fixing the filling material (21) for forming the molding core (27); and at least partly laying at least one semifinished fiber product (33a, 33b) on the molding core (27) that is formed, for the shaping of the fiber composite component (34) to be produced.

Abstract: A clamping system for positioning a first component and a second component relatively to each other includes a clamping device, a separating foil and an electrical contacting device. The clamping device is adapted to fix the first and second components in a desired joining position under creation of a gap therebetween with a characteristic measure of tolerance relative to each other in a first position of the clamping device and to release this fixation in a second position of the clamping device. The separating foil includes an anti-stick layer and a heating layer connected with electrically conducting contact zones for heating a compensation compound arranged in the gap. The electrical contacting device is mechanically couplable with the clamping device or a supporting device holding the clamping device and is adapted for creating an electrical contact with the contact zones at least in the first position of the clamping device.

Abstract: A system for moving loads, in particular within an aircraft, comprising: a cargo hold floor, at least one row of rollers including a plurality of rollers integrated into the floor one behind another, at least one guide rail in the floor extending substantially parallel to the row of rollers, and at least one transport vehicle removably received in and movable along the guide rail. At least one coupling arrangement selectively couples the vehicle with a load arranged on the row of rollers, the load being movable with the vehicle. At least one locking arrangement, in an active state, locking the load relative to the floor and, in a non-active state, allowing a relative movement between the load and the floor. The vehicle operates the locking arrangement according to at least one of the following: so that it assumes the active state; and, so that it assumes the non-active state.

Abstract: A vortex generator arrangement for an aircraft including a surface section, a flap element pivotable between a first position and a second position, a biasing arrangement biasing the flap element towards the second position, retaining devices retaining the flap element in the first or second position, and a release device releasing the flap element from the first retaining device. The biasing arrangement, the first retaining device and the second retaining device are configured such that the second retaining device automatically retains the flap element in the second position after the flap element has been pivoted by the biasing arrangement from the first position into the second position. As soon as the torque exceeds a predetermined value, the second retaining device automatically releases the flap element, which pivots against the force of the biasing arrangement into the first position and is automatically retained therein by the first retaining device.

Abstract: An insert for an aircraft galley for storing and charging personal electronic devices (PEDs), wherein the insert includes at least one physical interface and at least one data and power interface in accordance with the ARINC standard. In an open state, the insert is suitable for introducing the PEDs into the insert, and in the closed state, it is suitable for storing and charging the PEDs. The insert includes: a module for providing the respective electric power to the PEDs required by the PEDs for charging, wherein electric power is provided to the module via the data and power interface; standardized electric plugs for connecting the PEDs to the module; one or multiple temperature sensors for measuring the temperature in the interior of the insert; and a heat dissipation arrangement.

Abstract: Fuel cell systems aboard means of transport can be used for generating energy and for producing water. In order to reduce the overall weight of the system, the fuel cell is controlled or regulated in dependence on a current fill level or a limit level of the water tank, as well as a predicted future water consumption. In this way, it may be possible to minimize the water quantity to be stored in the water tank.

Abstract: An aircraft air conditioning system comprising an ambient air supply line with a first end connected to an ambient air inlet and a second end connected to a mixing chamber. A first electrically driven ambient air compressor in the ambient air supply line compresses the ambient air flowing therethrough. A first ambient air branch line branches off from the ambient air supply line upstream of the first ambient air compressor and rejoins the supply line downstream of the air compressor. A second ambient air compressor in the first ambient air branch line compresses the ambient air flowing therethrough. A cabin exhaust air line has a first end connected to an air conditioned aircraft area. A cabin exhaust air turbine in the exhaust air line is driven by the exhaust air flowing through the cabin exhaust air line and is coupled to drive the second ambient air compressor.

Abstract: A passenger cabin area, which is suitable for installation in an aircraft cabin, includes passenger seats arranged one behind another along a longitudinal axis of the passenger cabin area. The passenger cabin area also includes luggage compartments which are arranged, at least in certain sections, in an area between an inner face, which faces towards an interior space of the passenger cabin area, of a fuselage sidewall and the passenger seats, and have an access aperture which faces towards the passenger seats.

Abstract: An aircraft ram air channel assembly having: a first ram air inlet with a deflector protruding from the aircraft outer skin, the deflector guiding an air flow into a first ram air inlet channel; a second ram air inlet having a cross-sectional area flush with the outer skin, the second inlet being coupled to a second ram air inlet channel and arranged proximate to the first inlet upstream of the first inlet; and a flap pivotable about an axis between first and second operating positions. The axis is upstream of the first and second inlets and extends perpendicular to the air flow. The flap in its first position projects into the second inlet channel to control air flow through the second inlet into the second inlet channel, and in its second position projects into the air flow to prevent foreign objects from entering the first and second inlets.

Abstract: A stowage and removal system has a receiving frame with an insertion opening for insertion and removal of a container and with a first wall lying opposite the insertion opening; at least one first locking device for releasably locking a container arranged in the receiving frame at the first wall; a first control element for actuating the at least one first locking device; a removal device with a first engagement body which can be brought into engagement with a side of a container directed towards the first wall, wherein the removal device is configured to move the first engagement body from a region near the wall in the direction of the insertion opening, and a removal control element which is coupled to the removal device for selectively moving the first engagement body. The first control element and the removal control element are arranged in a region of the insertion opening.

Abstract: A device for reducing a stress concentration at an edge of a laminated composite material has an optical element, an actuator element, and a receptacle space for a first component of a laminated composite material which can be or is connected to a second component via a contact face and has an edge element above the contact face. The optical element defines a focus face for laser radiation for vaporizing laminated composite material. The actuator element is designed to move the optical element around a first component arranged in the receptacle space. and orients the optical element in such a way that an angle, including the first component, between the contact face and the focus face is smaller than 90°. The angle is selected such that after vaporization of the laminated composite material at the focus face the stress concentration at the edge element is reduced under load.