Abstract: A system is proposed, using which a material is dispensed in a web shape to additively produce a component. An in situ material check is performed, wherein if a geometric deviation lying outside a tolerance is established, material dispensing is interrupted to carry out finish compacting of a dispensed material web by way of a compacting unit.

Abstract: A method is proposed for installing system components in a portion of an aircraft fuselage. The method provides at least one planar structural arrangement to be secured on or in the aircraft fuselage, secures system components on the structural arrangement, couples system lines to the system components and arranges the system lines on the structural arrangement. The method includes positioning of the structural arrangement with the system components and system lines arranged thereon at a designated installation location of the structural arrangement, and mechanical coupling of the structural arrangement to the aircraft fuselage.

Abstract: A floor fixing assembly for releasable fixing of a leg of a frame to a vehicle floor comprises at least one retaining peg which can be fixed to the vehicle floor. The floor fixing assembly furthermore comprises a frame fixing element, which is configured to be connected to the leg of the frame and comprises at least one receiving space for receiving the retaining peg. A clamping device is configured to be introduced into the receiving space of the frame fixing element in order to connect the frame fixing element to the retaining peg by form fit.

Abstract: In order to provide a new and improved bonding arrangement, especially for use in an aircraft or spacecraft, which is designed to overcome problems of bonding arrangements under Mode I loading stress and which is designed or configured particularly to create a bond design which is incapable of locally loading the adhesive bond above the peel strength, a bonding arrangement is disclosed with a coating structure, which is split into a plurality of neighboring structural elements spatially separated from each other, and at least one supporting member is provided, which comprises a plurality of recesses receiving the structural elements in operating position.

Abstract: A vertical stabilizer for an aircraft, including a fin, pivotable rudder, rudder adjustment arrangement, and vortex generator arrangement having on each side of the fin a turbulence generation element, each turbulence generation element disposed in a surface section of the fin and mounted moveably between a first, retracted position, where it is retracted into an interior space of the fin, and a second, extended position, where it projects at least partially outwardly from the fin transversely with respect to the surface section, and a turbulence generation element adjustment arrangement which is coupled to the rudder. The turbulence generation element adjustment arrangement engages the turbulence generation elements to move them. In a range of angular positions of the rudder, the turbulence generation element adjustment arrangement is inoperative for causing a movement of the turbulence generation elements out of the first position.

Abstract: A heatable water pipe for an aircraft, having a heat-generating ply which extends in the pipe circumferential direction and the pipe longitudinal direction, at least in some section or sections. The heat-generating ply comprises a fiber composite layer containing fibers and a matrix surrounding the fibers, wherein at least some of the fibers are formed as conducting fibers. In this context, the conducting fibers are formed as carbon fibers with an electrically insulating coating. By virtue of the electrically insulating coating, leakage currents can be avoided. The carbon fibers serve both as heating elements and as reinforcing fibers in the fiber composite layer.

Abstract: This relates to a method for manufacturing a shell-like structural component for a vehicle using additive layer manufacturing. In a step of the method, a first material is applied to a region of the shell-like structural component. In another step of the method, the region of the shell-like structural component is heated by a laser beam such that the first material is added to the shell-like structural component. The shell-like structural component comprising the first material is cooled in another step such that an internal stress is generated within the shell-like structural component resulting in a bending of the shell-like structural component. This further relates to a shell-like structural component which is manufactured by a method using additive layer manufacturing.

Abstract: A heatable floor panel for an aircraft, with a supporting level, a heat-generating level and a heat-conducting level. The heat-generating level comprises a fiber composite layer with fibers and with a matrix surrounding the fibers. The fibers are at least partially formed as conducting fiber, and the conducting fibers are formed as carbon fibers with an electrically insulating coating. The conducting fibers integrated in the floor panel in order to conduct a heating current through them. Due to the electrically insulating coating of the conducting fibers, leakage currents are avoided. The carbon fibers serve not only as heating elements, but, at the same time, also as reinforcing fibers of the fiber composite layer or of the floor panel.

Abstract: A magnetically levitated arrangement for contactless movement over a surface comprising a magnetizable reaction surface and a magnetically levitated unit arranged to interact with the reaction surface. The levitated unit has at least one pair of rotatable rotary magnet units, each unit rotatable about a rotation axis and having magnetic elements arranged with alternating poles and respectively substantially parallel to the rotation axis in a pole connection direction. Each rotary unit pair is formed to interact, due to rotation of the two rotary units in opposite directions relative to one another and relative to the reaction surface, in such a way with the reaction surface, that forces are generated holding the levitated unit at a distance from the reaction surface, and due to the opposite rotation directions of the rotary units of each pair, a directed drive force moving the levitated unit relative to the reaction surface is generated.

Abstract: Production methods for producing a fiber-reinforced metal component having a metal matrix which is penetrated by a plurality of reinforcing fibers are provided. One method includes depositing in layers reinforcing fibers in fiber layers, depositing in layers and liquefying a metal modelling material in matrix material layers, and consolidating in layers the metal modelling material in adjacently deposited matrix material layers to form the metal matrix of the fiber-reinforced metal component. Here, the metal component is formed integrally from alternately deposited matrix material layers and fiber layers. An alternative method includes introducing an open three-dimensional fiberwoven fabric consisting of reinforcing fibers into a casting mold, pouring a liquid metal modelling material into the casting mold and consolidating the metal modelling material to form the metal matrix of the fiber-reinforced metal component.

Abstract: A connection system has a first adhesion segment, on which a first connection region is formed, a second adhesion segment, on which a second connection region is formed, and a solidifiable liquid connection substance for connecting the two adhesion segments in a material fit, wherein at least one of the two connection regions is formed flexibly, such that, when the liquid connection substance is introduced between the two connection regions which are opposite one another in an assembly arrangement of the two adhesion segments, a material connection is formed between the two connection regions automatically as a result of the elastocapillary effect via the liquid connection substance.

Abstract: Disclosed here is a transfer system for transferring luggage into a vehicle having a freight hold opening and a passenger compartment opening arranged at the same level outside the vehicle. The system has a luggage transfer element and a passenger bridge, wherein the passenger bridge has a transition zone that can be simultaneously connected to the freight hold opening and the passenger compartment opening. The luggage transfer element has a housing module for receiving luggage, and a movement module for transferring the luggage transfer element. The luggage transfer element can be transferred through the transition zone and the freight hold opening by way of the movement module. The system avoids delays as the passengers are boarding and simplifies the transfer of luggage into a freight hold.

Abstract: A method for laser shock peening of a component, in particular at points that are difficult to access, includes the steps of: supplying a first end of a flexible optical waveguide, which end is designed in the form of an optical waveguide brush having a plurality of divergent optical waveguide fibres, to a point of the component to be treated by laser shock peening; generating laser shock pulses, which are coupled in at a second end of the optical waveguide, by a laser beam source; and discharging the laser shock pulses by the optical waveguide brush into a process zone at the point of the component to be treated. A use of an optical waveguide brush, a system for laser shock peening of a component, and a mobile laser shock treatment station are also described.

Abstract: A riblet film for reducing the air resistance of aircraft, comprising a suspension with magnetic particles enclosed therein. Depending on the pattern of a magnetic field acting on the riblet film, the magnetic field that is acting can be made visible, at least in certain regions, by changing the orientation of the magnetic particles. The riblet film allows an inspection of the aircraft structure located under the riblet film through the riblet film.

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: A load bearing element for attachment of a heat generating unit to a heat sensitive supporting structure, wherein said load bearing element includes at least one body integrally formed by additive layer manufacturing, ALM. The body is adapted to provide a controlled heat transfer from said heat generating unit to said heat sensitive supporting structure.

Abstract: In order to improve and facilitate shimming between two parts, a deformable shim is provided that comprises a main structure of an at least partly cellular region. The main structure is compressible by plastic deformation from an initial volume to a deformed volume, wherein the deformed volume is smaller than the initial volume. In a deformed state, the main structure maintains the deformed volume without further or continuing compression force. Further, the main structure is arrangeable between a first aircraft component and a second aircraft component to create a predefined distance between the first and the second aircraft component.

Abstract: This relates to a holding apparatus for holding a component during mounting. The holding apparatus comprises at least a first holding unit including at least one magnetic field generating device for generating a magnetic field, and at least a second magnetic holding unit spaced apart from the first holding unit in a predetermined distance for receiving the component. A holding force for holding the component between the first holding unit and the second holding unit is generated in the second magnetic holding unit as a result of induction and by means of a magnetic field generated by the magnetic field generating device. The embodiment also comprises a mounting system and a method for holding components by means of such holding apparatuses.

Abstract: Validating additively manufactured components is carried out by transmitting to a distributed validation network printing specification data for a component that is to be additively manufactured, validating the printing specification data, and adding the printing specification data, together with a cryptographically encoded checksum, to a print history log, transmitting the printing specification to a 3D printing device, and implementing a generative manufacturing process for the component that is to be additively manufactured in accordance with the transmitted printing specification data. While the generative manufacturing process is being carried out, in each case following specified manufacturing stages, a plurality of manufacturing parameters prevailing in the preceding manufacturing stage are transmitted to the distributed validation network.

Abstract: A rotary joint includes a socket rod having a socket rod flange with a basically spheroid con-cave bearing surface at a first end, a housing nut encircling the socket rod and having a threaded wrenching head, a ball rod having a basically spheroid convex bearing surface and threaded side walls around the convex bearing surface, and a joint actuator configured to actuate relative movement of the socket rod flange and the ball rod. A diameter of the threaded side walls of the ball rod corresponds to a diameter of the threaded wrenching head of the housing nut.