Abstract: A method for connecting two components is proposed where a pressure acting on an adhesive between two join partners is supported by an auxiliary body which rests on a cutout of one of the components. Both components to be connected together and the auxiliary body are covered by a vacuum film and once the air has been sucked out, the compressive force is generated below the vacuum film.

Abstract: A structural component of a primary structure for a vehicle, the structural component including a fiber composite laminate with a plurality of fiber composite sublayers. The plurality of fiber composite sublayers includes an electric energy store which is configured as a multilayer electrochemical fiber composite battery to store electric energy in a rechargeable manner; and an electrothermal temperature regulation sublayer which is configured to supply thermal energy to the electric energy store and conducting thermal energy away from the electric energy store as required to regulate a temperature. A control device, which is connected to the electric energy store and the electrothermal temperature regulation sublayer, is configured to control a temperature regulation of the electric energy store by means of the electrothermal temperature regulation sublayer.

Abstract: A support stay is provided to improve failsafe configurations for movable parts of an aircraft. The support stay supports the movable part with a primary body and a separate secondary body. The primary body and the secondary body provide separate load paths. The secondary body is attached to the primary body by a mechanical connection, e.g., rivets. If one of the bodies becomes structurally compromised, for example by a crack, this configuration does not transfer shear load between the primary and secondary body, so that the other body does not become structurally compromised.

Abstract: A device for manufacturing a composite component including a tool with a first and second sections forming first and second confinement surfaces, the sections movable relative to each other into and out of a fastening configuration. The device includes a closing mechanism with a closing section. In the fastening configuration, the first confinement surface and the second confinement surface face one another, and the sections and the closing mechanism are arranged such that a cavity is formed between the sections and the closing mechanism. The closing section is transferable from an open configuration into a closed configuration. In the closed configuration, the third confinement surface extends along a plane perpendicular to the first and second confinement surfaces, wherein, when the closing mechanism is heated from a first temperature to a second temperature, the closing section transfers from the open configuration into the closed configuration at a predefined temperature.

Abstract: A device and method for producing a component. The device is composed of two mold elements, wherein one of the mold elements has a cavity which communicates with the position of one side of a component to be produced. An inflatable tube which is fluidically linked to the surrounding atmosphere is provided in the cavity. A cover covers the first and the second mold element and seals the first and said second mold element in relation to the surrounding atmosphere. The tube is expanded by applying a vacuum within the sealed regions and the tube can shape or facilitate shaping the side of the component to be produced.

Abstract: A method is disclosed for determining mechanical robustness of an overhead stowage bin for an aircraft includes repeatedly effecting an impact of a test body against an impact surface of the overhead stowage bin with a predefined impact force by a robotic arm of a manipulator, and investigating damage parameters of the overhead stowage bin.

Abstract: An aircraft door lock having a bolt and a closure block, wherein the bolt is fastened in a movable manner to a door leaf structure and the closure block can at least partially receive the bolt. The closure block prevents any movement of the bolt in at least one direction, wherein the closure block is arranged on a portion of a hinge arm that overlaps the door leaf structure when the door leaf structure is in a closed position. Furthermore, an aircraft door having such an aircraft door lock, and an aircraft having such an aircraft door are described.

Abstract: A sensor network for use in an aircraft, including a plurality of wireless nodes. A first wireless node of the plurality of wireless nodes is arranged to communicate with at least one other wireless node of the plurality of wireless nodes. The communication is via a secure communications channel and is on the basis of a control message received at the first wireless node. The at least one other wireless node is arranged to perform an operation on the basis of the control message.

Abstract: A floor panel for an aircraft or spacecraft. The floor panel has a panel-like portion and an additional structure. A first side of the panel-like portion forms part of a floor surface in the aircraft or spacecraft. The additional structure is connected to the panel-like portion on a second side of the panel-like portion that is opposite the first side. The panel-like portion and the additional structure each comprise a matrix material formed by a thermoplastic material. Endless reinforcing fibers are embedded in the matrix material of the panel-like portion. Discontinuous reinforcing fibers are embedded in the matrix material of the additional structure. An aircraft or spacecraft may have a floor area which is formed by a planar arrangement of floor panels of this type. The method for producing a floor panel for an aircraft or spacecraft is provided.

Abstract: A method is provided for producing a common connecting opening in two components, at least one of which is made from a plastically deformable material. In the method, at least the edge region of a first prefabricated opening of the first component is softened in order subsequently to introduce a mandrel which displaces the material softened by the heating so that a common connecting opening having a predetermined diameter is obtained.

Abstract: A cooling circuit operable with fuel of a fuel cell system includes a fuel tank storing fuel for the fuel cell system, a fuel compressor configured to increase a pressure of the fuel, a first heat exchanger configured to cool the pressurized fuel, a first conduit coupled to an outlet of the first heat exchanger, a first turbine coupled to the first conduit and configured to expand the pressurized and cooled fuel, and a second conduit coupled to an outlet of the first turbine and configured to direct the expanded fuel to the fuel cell system. Further disclosed is a vehicle including at least one cooling circuit or a cooling system having a cooling circuit.

Abstract: A wing for an aircraft, including a main wing, a slat, and a connection assembly movably connecting the slat to the main wing. The connection assembly includes an elongate slat track with a front end mounted to the slat and a rear end and an intermediate portion mounted to the main wing by a roller bearing, and includes a guide rail mounted to the main wing and a first roller unit mounted to the slat track rear end and engaging the guide rail. The roller bearing includes a second roller unit mounted to the main wing and engaging a slat track intermediate portion engagement surface. The slat track has an upper and lower flange and at least one web. The second roller unit is arranged in a recess between the upper and lower flanges and engages the engagement surface provided at the upper and/or lower flange.

Abstract: In order to improve linear drives on aircraft with regards to backlash, gear reduction, self-lock capability, load transfer and wear, a linear drive device is provided that has a first member with engaging teeth, such as a tooth rack and a second member which functions as a drive unit. The second member includes a plurality of movable teeth that are actuated by a cam shaft. The cam shaft has a control cam portion that is shaped such that the movable teeth perform a wave-like motion that forces the first member along its longitudinal direction relative to the second member.

Abstract: An aircraft comprising a skin, a multiplicity of antenna arrangements, each of which is arranged in a different region of a corresponding multiplicity of mutually spaced regions of the skin and comprises an antenna element that is arranged and configured to emit radio waves into a surrounding area of the aircraft, and a multiplicity of visual indicators, each of which is assigned to a different antenna arrangement of the antenna arrangements. Each of the visual indicators is arranged on the skin or on the antenna arrangement in the region of the skin in which the assigned antenna arrangement is situated in such a manner that it is visible from outside the aircraft and emits light during operation in an on state.

Abstract: A control system for an aircraft includes a hydraulic pump, first hydraulic line, second hydraulic line, a first actuator coupled with a first control surface, a second actuator coupled with a second control surface, and a third actuator coupled with a third control surface. The first control surface and the second control surface are at a distance to each other and symmetrically relative to a symmetry axis. The third control surface is substantially on the symmetry axis, and the first hydraulic line and the second hydraulic line are connected to the hydraulic pump. The first actuator is connected to the first hydraulic line, and the second actuator is connected to the second hydraulic line. The third actuator is connected to the first hydraulic line downstream of the first actuator at a junction point, and the first hydraulic line at least partially includes a larger diameter than the second hydraulic line.

Abstract: A wing for an aircraft, including a main wing, a slat, and a connection assembly movably connecting the slat to the main wing, such that the slat is movable between a retracted position and at least one extended position. The connection assembly includes a first connection station and a second connection station spaced apart from the first connection station in a wing span direction. The object, to prevent the slat from skewing, is achieved in that the connection assembly includes a sync shaft coupling the first connection station to the second connection station for sync movement of the first and second connection stations.

Abstract: A method for producing an aircraft fuselage for simplifying and accelerating the production of the aircraft fuselage. The method includes providing a fuselage structure which surrounds an interior space and has an inner side facing the interior space, providing an insulating panel for insulating the fuselage structure, wherein the insulating panel has an inner surface and an outer surface, providing a film which is provided with electric strip conductors, fastening the film to the inner surface of the insulating panel, and attaching the insulating panel to the inner side of the fuselage structure.

Abstract: An aircraft includes a fuselage, a wing attached thereto, a wing tip device attached to a wing end of the wing (2), a wing-like element having a wing root, a wing leading edge and a wing trailing edge, and a torque control device having a rotatable interface means. The torque control device is adapted for rotatably supporting the wing root of the wing-like element on the interface means about a rotational axis extending from the interface means into the wing-like element and to limit the degree of rotation depending on a torque introduced into the interface means by the wing-like element. The wing-like element is adapted to induce a rotation around the rotational axis in an air flow. The wing root is coupled with the wing tip device, the wing or the fuselage through the torque control device such that the leading edge extends into an airflow surrounding the aircraft.

Abstract: A method for joining two components of a meltable material comprises the steps of providing a first component having a first border region and a second component having a second border region, placing the second component relative to the first component so as to form an overlap between the first border region and the second border region under a gap between the first border region and the second border region, continuously heating opposed sections of the first border region and the second border region at the same time through at least one energy source arranged in the gap at least partially, continuously providing a relative motion of the at least one energy source along the first border region and the second border region in the gap, and continuously pressing already heated sections of the first border region and the second border region onto each other.

Abstract: An assembly-ready joint for an aircraft assembly is disclosed. The joint includes a first joint part having a spigot. The joint also has a second joint part with a housing. A floating socket is in an interior of the housing. The second joint part receives the spigot in the floating socket. The joint is arranged to receive a curable medium, such as curable resin, in the interior to contract between the housing and the floating socket.