Abstract: The invention relates to a seat assembly for a cabin of a means of transportation, having an aisle which is arranged in the longitudinal direction of the cabin, two mutually spaced cabin walls which are oriented parallel to the aisle at least in some regions and laterally delimit the cabin, two outer passenger seat regions which are separated from one another by the aisle and each of which adjoins one of the two cabin walls, wherein the outer passenger seat regions have at least one row of seats with a respective inner first seat module which faces the aisle, a central second seat module adjoining the first module, and an outer third seat module adjoining the respective cabin wall.

Abstract: A mold core for producing a component of fiber composite material with a cavity makes a particularly simple and efficient demolding process possible by the mold core extending along a longitudinal axis and in the form of a hybrid core and which includes, viewed in a cross section perpendicular to the longitudinal axis, a first core portion and a second core portion, wherein the first core portion has a thickness that is substantially greater than a thickness of the second core portion. The first core portion is formed from a first material with high stiffness and low coefficient of thermal expansion, and the second core portion is formed from a second material that differs from the first material, and is configured such that, under predetermined conditions, its form changes in a predetermined manner such that removal of the mold core from a cavity in the cured component is made easier.

Abstract: A mount for a double-walled vessel includes a first support to support the mount against an outer wall of the double-walled vessel, a second support to support the mount against an inner wall of the double-walled vessel, and a flexible member connecting the first support and the second support. The first support and can be arranged at a first end of the flexible member and the second support can be arranged at a second end of the flexible member opposite to the first end. Further described are a vessel including at least one such mount as well as a vehicle including such vessel.

Abstract: A wing for an aircraft, including a main wing, a slat, and a connecting assembly movably connecting the slat to the main wing, the slat being movable between retracted and extended positions. The connecting assembly includes a slat track and a roller bearing. A front section of the slat track is mounted to the slat. A rear section and an intermediate section of the slat track are mounted to the main wing via the roller bearing. The roller bearing includes a guide rail mounted to the main wing and a first roller which is rotatably mounted to the rear section of the slat track. The first roller engages a first engagement surface formed by the guide rail. The roller bearing includes a second roller which is rotatably mounted to the main wing. The second roller engages a second engagement surface formed by the intermediate section of the slat track.

Abstract: A method of providing a deformable shim 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: An induction heated tool system for receiving and heating polymer-fiber components from a starting temperature to a target temperature includes a tool part having a receiving cutout, the tool part formed from a thermally dimensionally stable material so it has a coefficient of thermal longitudinal expansion less than 10×10?6 K?1, or less than 5×10?6 K?1, or less than 4×10?6 K?1 in the plane of the largest dimension of the receiving cutout, at temperatures between the starting and target temperatures. A receiving cutout for receiving a polymer-fiber component is in the tool part, the receiving cutout delimited by a receiving surface portion so a polymer-fiber component received in the receiving cutout can lie against the receiving surface portion. A susceptor element includes a ferromagnetic material with a first Curie temperature. The susceptor element is on a surface portion of the tool part outside the receiving cutout and the receiving surface portion.

Abstract: An inflatable suspended ceiling for a vehicle compartment, in particular for a passenger cabin of an aircraft, includes a flat fabric cover sheet configured to roof over at least a longitudinal section of an interior space along an extending direction of the vehicle compartment underneath a structural ceiling of the vehicle compartment, and a tensioning structure attached to the cover sheet to carry the cover sheet from above and having a flexible envelope enclosing at least one inflatable chamber configured to tension the cover sheet when inflated. Mounting members are attached to the tensioning structure to mount the tensioning structure to counter-mounting members on the structural ceiling in a hanged configuration.

Abstract: An auxiliary power unit for an aircraft. It includes an air compressor coupled to an air-drawing device for drawing in air from outside the aircraft, the compressor supplying compressed air to a manifold. The manifold is configured to supply air to an environmental control system and a start-up module of at least one propulsion system of the aircraft running on hydrogen. The manifold is also configured to supply air to a fuel cell stack arranged to provide an electric generation function configured to power non-propulsive systems of the aircraft, the fuel cell stack also being supplied with hydrogen from a tank supplying hydrogen to the at least one propulsion system of the aircraft.

Abstract: To improve the complicated painting process of large three-dimensionally shaped components, preferably aircraft components, the masking step is automated. This is achieved by printing a masking medium onto the component with an inkjet method, the masking medium forming a masking film. The masking film masks the desired surface area and can be pulled off following the end of the painting. Preferably, spray films, functional printing inks or mold release agents are used as the masking medium.

Abstract: In an aircraft, latches are used to secure cargo within the cargo hold of the aircraft. Such latches include a base plate configured for rigid attachment to a surface of the cargo hold, a latch head attached to the base plate and configured to prevent a movement of at least one cargo unit in a Y-direction and a Z-direction and to allow a movement of the at least one cargo unit in an X-direction, and a roller assembly attached to the base plate, opposite the latch head, and comprising at least one roller, the roller being configured to provide a vertical support to the at least one cargo unit in the Z-direction while allowing the movement of the at least one cargo unit in the X-direction.

Abstract: A multipurpose tool for flight attendants includes a telescopic arm on which two handle elements are articulated at opposite ends, which handle elements can be folded in so as to lie adjacent to one another. By folding the handle elements apart and extending the telescopic arm, the multipurpose tool can be used in a variety of ways. In addition, fold-out tools may likewise be arranged on the multipurpose tool.

Abstract: An aircraft wing, including a main wing, a leading edge high lift assembly including a high lift body, and an assembly connecting the high lift body to the main wing. The high lift body is movable relative to the main wing between stowed and deployed positions. The connection assembly includes at least one rotation element mounted to the high lift body and rotatably mounted to the main wing. The main wing comprises an upper panel with a leading edge portion and a lower skin panel. The high lift body has a leading and a trailing edge. The high lift body trailing edge moves along the main wing upper skin panel leading edge portion when the high lift body is moved between the stowed and deployed positions. The upper skin panel leading edge portion is elastically deformed when the high lift body is moved from the stowed to the deployed position.

Abstract: An arrangement comprising an airfoil body, a junction mechanism for attaching the airfoil body to a support element of an aircraft, and a fairing for aerodynamically covering the junction mechanism. The fairing has a cover element covering a trailing end portion of the fairing. The cover element is attached to the trailing edge of the airfoil body by a form fit connection.

Abstract: A high-lift device connection assembly (24) for movably connecting a high lift device (16) to a wing (14) of an aircraft (10) wherein a track (30) is movably guided between main rollers (38, 40, 42, 44). In order to provide an enhanced fall back safety feature in case of a failure of a roller the invention proposes a track catcher (92) to be attached to a structure (26) of the wing (14) and configured to bear a load imposed by the track (30) in case of a main roller failure, wherein the track catcher (92) has at least one first hook element (94, 94-1-94-4) engaged within a first recession (72) at a first side of the track (30) and at least one second hook element (96, 96-1-96-4) engaged with a second recession (74) at the second side of the track (30). Further, the invention relates to a wing and an aircraft equipped with such high-lift device connection assembly (24).

Abstract: A drive system for driving a movable flow body having a drive unit, a shaft, a torque sensing device, a no-back friction unit, and an axial bearing. The drive unit is coupled with the shaft to rotate the shaft, the torque sensing device is coupled with at least one of the drive unit and the shaft to detect a torque transferred from the drive unit into the shaft, the no-back friction unit is arranged between the axial bearing and an axial support means of the shaft, such that an axial load of the shaft is supported by the axial bearing, and the no-back friction unit is configured to substantially not counteract a rotation of the shaft in a first direction of rotation of the shaft and to apply a friction-induced additional torque to the shaft in an opposite second direction of rotation.

Abstract: A method for resistance welding of two fiber-composite components to give a fiber-composite structure includes arranging conductive fibers within a jointing region of the two fiber-composite components, where each conductive fiber includes a carbon fiber with an electrically insulating coating. An electric current is passed through the conductive fibers to heat the jointing region to a welding temperature and melt the fiber-composite components in the jointing region. The jointing region is hardened in a manner that bonds the two fiber-composite components by way of the jointing region to give the fiber-composite structure.

Abstract: An information processing architecture for implementation in a vehicle includes a software segregation unit which is configured to provide a first security domain and a second security domain which are assigned in each case to different operational areas of the vehicle and have their own data processing environments which are segregated from one another to run a multiplicity of computer applications. The software segregation unit is further configured to provide a synchronization instance, wherein the synchronization instance has a central dataset which is synchronized with data generated in the respective security domains independently from one another via data exchange and is selectively readable by both security domains.

Abstract: An apparatus for threading a tool unit onto an elongate structural element. The apparatus has a holding arrangement for holding it on a feed device, a tool unit to be threaded onto the elongate structural element. The tool unit has a tool axis and a vibration unit connected to the tool unit and configured to generate a periodic force in at least one first spatial direction that runs transversely with respect to the tool axis. First and second coupling components, held elastically on one another, are provided. The first coupling component is connected to the holding arrangement, the second coupling component is connected to the tool unit. The vibration unit is operated, during a feed movement of the holding arrangement for threading the tool unit onto the elongate structural element, to add an additional, periodically varying transverse component to a feed force acting on the tool unit.

Abstract: A busbar for an aircraft with at least two conductive layers and at least three insulating layers. The conductive layers and the insulating layers are stacked together alternatingly and extend in a longitudinal direction. The conductive layers and the insulating layers include different coefficients of thermal expansion. Each of the conductive layers includes spatial structures. Each spatial structure is connected to an adjacent one by an interconnecting segment. Each conductive layer is embedded between two insulating layers, resulting in a deforming of the side walls of the spatial structures under heat, thereby compensating a longitudinal expansion of the conductive layers. Further, an aircraft with a disclosed busbar and a method of producing such busbar is provided.

Abstract: Devices and methods for producing a T-shaped semifinished product from a multiply non-crimp fabric with reinforcing fibers for a composite material. The product has a web and a flange. The device includes a web forming tool, with which a web portion of the non-crimp fabric is clamped in place, a forming tool, with which plies of a flange portion of the non-crimp fabric are split into two parts, a depositing device, with which a tube body is deposited on the flange portion formed into the flange, a holding tool, with which a clearance between the holding tool and the flange is formed, and a filling device, with which the tube body is filled with a gas such that the tube body fills the clearance and firmly holds the flange portion formed into the flange, and alternatively, a magnetic force can be generated between a sheet and the web forming tool.