Abstract: An electrically heatable layer stack is disclosed. The electrically heatable layer stack includes at least two substrate layers, and at least one carbon nanotubes-, CNT-, layer, which is arranged between the substrate layers and which is configured to conduct an electric current. The substrate layers and the at least one CNT-layer are configured to produce heating of at least one of the substrate layers when an electric current is applied to the at least one CNT-layer. A vehicle assembly group, an aircraft, a method and a system for manufacturing an electrically heatable layer stack are also disclosed.

Abstract: A linkage mechanism for a flaperon includes a support structure linkage, a droop panel linkage, and a flaperon linkage. The support structure linkage is pivotally attached to a support structure of a wing of an aircraft. The droop panel linkage is pivotally attached a droop panel. The flaperon linkage is pivotally attached to a flaperon. A second end of the droop panel linkage and a second end of the flaperon linkage are pivotally attached to a connecting section of the support structure linkage. The connecting section is spaced apart from the pivot end of the support structure linkage such that the linkage mechanism transfers a pivoting motion from the flaperon into a pivoting motion of the droop panel.

Abstract: A cargo hold component system for a cargo hold of an aircraft, the cargo hold component system including floor elements and fixing elements. The floor elements can at least partially be fixed releasably by the fixing elements to fixing sites provided on or in the hold floor, such that in a state fixed to the fixing sites, the floor elements support a loading of the hold with cargo containers, and that in a state in which a first group of the floor elements has been removed from the fixing sites by release of the fixing elements and a second group of the floor elements has been partially removed from the fixing sites by release of the fixing elements, the hold is sealed gas-tightly.

Abstract: A temperature regulating system for at least one galley compartment for an in-flight kitchen which is intended for installing in a transport apparatus or vehicle, especially in an aircraft, includes a controllable cooling and heating element, which is designed for selectively cooling or heating a specified section of the cooling and heating element, and a heat-insulating partitioning wall, which at least partially adjoins an encompassing side edge of the cooling and heating element and encloses the specified section of the cooling and heating element. The heat-insulating partitioning wall is designed for separating an interior space of the galley compartment from an interior of a section of a fluid duct which extends in the in-flight kitchen.

Abstract: A wing (5) for an aircraft (1) and include a fixed wing (7), a high lift system (9) including a high lift surface (27) movably mounted to the fixed wing (7), and a high lift actuation system (29) for moving the high lift surface (27) relative to the fixed wing (7) between a retracted position and at least one deployed position, a foldable wing tip portion (11) mounted to the fixed wing (7) pivotally about an axis of rotation (35) between an extended position and a folded position, a tip actuation unit (13) for moving the foldable wing tip portion (11) between the extended position and the folded position.

Abstract: A system for representing a vehicle cabin layout on an original scale comprising a plurality of projectors, a planar projection surface and a control system. The layout is loaded as digital cabin layout data into the control system and the layout comprises a first cabin aisle section extending along a first aisle axis. The projectors comprise vertical projectors spaced along a first projector axis. The control system drives the vertical projectors and processes cabin layout data loaded into the control system to project at least one section of the cabin layout on the planar projection surface on the original scale. That section of the layout which is projected by the vertical projectors comprises the first aisle section, such that the first aisle axis runs with the first projector axis in a first aisle plane extending perpendicular to the planar projection surface.

Abstract: A system and method for minimizing buffeting in the case of an aircraft. Buffeting load control elements are provided in airfoils of the aircraft are arranged to be at least partly moved out of the airfoils by a control to reduce buffeting loads acting on the aircraft.

Abstract: A cabin monument arrangement for a passenger cabin of an aircraft, has at least two cabin monuments arranged next to each other, aligned substantially parallel and forming a gap. The gap includes a gap covering in the fastening region of the first lateral monument part and of the second lateral monument part in the region of the front edge portion of the respective cabin monument. In each case, a first contour-adapted rigid fastening strip is on the fastening region and a second contour-adapted, rigid fastening strip is on the second fastening region. A covering element is between the first and second fastening strips for covering the gap between the first monument part and the second monument part, the covering element formed from a flexible covering material of thin design. A corresponding covering of the gap between the cabin monuments can therefore be achieved with sufficient flexibility and material width.

Abstract: A panel structure for a vehicle, and especially for an aircraft or spacecraft, includes an area member, especially a skin member, that defines an areal expanse with a first surface and an opposite second surface and having a thickness between the first and second surfaces; and a plurality of elongate stiffener members which are attached to the area member and extend over at least one of the first and second surfaces; wherein at least one of the stiffener members is bifurcated at a bifurcation point into two or more branch stiffener members.

Abstract: A flap system driving a leading-edge flap between retracted and extended positions comprises a leading-edge flap having first and second flap joints, first and second scissor links, a first connecting link, and an actuator. The actuator couples with either the first scissor link or first connecting link. The first scissor link is rotatable supported on a first fixed point by a first support joint. An end of the first scissor link opposite the first support joint couples with the first flap joint. The first connecting link is rotatably supported on a second fixed point by a second support joint. An end of the first connecting link opposite the second support joint rotatably couples with an end of the second scissor link. An opposite end of the second scissor link couples with the second flap joint. The first and second scissor links are rotatably coupled to form a scissor arrangement.

Abstract: A battery cell includes an anode, a cathode, and a separator between the anode and the cathode, wherein at least one of the anode or the cathode includes at least a carbon fiber ply comprising carbon fibers, the carbon fiber ply having a thickness of less than 90 micrometers. Also disclosed are a battery and an aircraft including such battery cell, and a method for manufacturing such battery cell.

Abstract: A fastening system has a fastening element and at least one fastening device having a flanged housing, a closure element, a hollow-sphere element and a spherical insert. The hollow-sphere element pivots about a first pivoting axis relative to the flanged housing, while the spherical insert pivots about a second pivoting axis in the hollow-sphere element. First engagement means in an opening of the spherical insert are of complementary design to second engagement means of the fastening element. The first and second engagement means are designed such that, in a first rotational position, the fastening element can be inserted freely into the opening and, in a second rotational position, the first and second engagement means engage in one another.

Abstract: A system for producing a component from a fibre composite material includes a moulding tool, a control unit and a plurality of mutually independent material application units, each of which includes a material store for providing fibres, a material delivery apparatus for delivering fibres from the material store and a drive device, and is configured, with the aid of the drive device, to follow a predetermined path on the moulding tool, while delivering fibres as required. The control unit controls the material application units by specifying a plurality of individual paths, so that they move autonomously along the paths. The control may, in particular, be carried out by optical projection onto the moulding tool.

Abstract: A fastening system for securing a component includes a first securing element having an engagement end and external toothing, a second securing element having elastic clamp members arranged about a common axis and having internal toothing facing the axis, and a fixing member. The clamps members assume a radial position relative to the axis that is variable due to their elasticity. The clamps are designed such that the second securing element can be pushed onto the engagement end such that the teeth of the engagement end and the clamps snap into each other. The clamps move from a first radial position to an external second radial position to engage or disengage a snapped-in state when shifting the external toothing and the first internal toothing to each other.

Abstract: A fastening system for fastening fitments to a floor of a cabin of a vehicle has a receiving frame, a cantilever mounted on the receiving frame so as to be pivotable on a pivoting plane defined by the receiving frame, and having a mounting end and a fastening end, a first fastening element, and a multiplicity of second fastening elements. The first fastening element is arranged at the fastening end of the cantilever. The second fastening elements are positionable on the floor. The first fastening element is configured in a manner corresponding to the second fastening elements such that the first fastening element is mechanically connectable selectively to a second fastening element. A pivoting position of the cantilever is lockable relative to the receiving frame.

Abstract: An electrical supply system for an aircraft includes a generator having a neutral point, an AC network, a bipolar DC network, and a neutral point clamped converter. The neutral point is connected to ground, in at least one operating mode. The converter has an AC side with AC connectors couplable with at least one phase of the generator. The converter also has a DC side with a first DC connector, a second DC connector and a neutral DC connector. The AC side of the converter is coupled with the generator, the DC side is coupled with the bipolar DC network, and the neutral DC connector is connected to ground. The convertor provides a DC voltage on the DC side upon receiving an AC voltage on the AC side, and provides an AC voltage on the AC side upon receiving a DC voltage on the DC side.

Abstract: A method for manufacturing a multilayer fiber structure includes providing a receiving surface being formed by a first surface region of a contoured tool surface of a forming tool component and a support surface of a support component. Further, at least one fiber layer is formed on the receiving surface by laying down a plurality of fiber tapes onto the receiving surface. A roller device is positioned so as to press the at least one fiber layer against the tool surface and the support component and the roller device are synchronously moved along a curved transition region connects the first surface region to a second surface region of the tool surface. Thereby the at least one fiber layer is abutted against the transition region and the second surface region of the tool surface. Further, a tool system for manufacturing a multilayer fiber structure is disclosed.

Abstract: A fairing for an aircraft is disclosed in which the fairing comprises a first fairing portion configured to be fixedly attached to a first structural component and having a first edge; a second fairing portion configured to be fixedly attached to a second structural component and having a second edge, wherein the first edge and the second edge define an interface configured to enable relative movement between the first fairing portion and the second fairing portion.

Abstract: A leading-edge component for an aircraft includes at least a part of a flow body having a front skin and at least one rib, wherein the front skin includes a top section, a bottom section and a leading edge arranged therebetween, wherein the rib extends from the bottom section to the top section, wherein the rib includes at least one kink separating the rib into a first section and at least one second section, and wherein main extension planes of the first section and the at least one second section enclose an angle of at least 10°.

Abstract: A seat frame fastening assembly for laterally fastening a seat frame in a vehicle, wherein the seat frame fastening assembly comprises a holding rail arranged in a longitudinal direction of the vehicle, and a lateral element laterally fastened to a seat frame and coupled to the holding rail. The holding rail comprises a first power- and/or data-transfer interface and the lateral holding element comprises a second power- and/or data-transfer interface. The second power- and/or data-transfer interface is furthermore arranged in the lateral holding element such that a position of the second power- and/or data-transfer interface corresponds to a position of the first power- and/or data-transfer interface when the lateral holding element is coupled to the holding rail. Furthermore, a seat frame has such a seat frame fastening assembly, a vehicle portion has a corresponding seat frame and a vehicle has such a vehicle portion.