Abstract: A method for joining, by adhesive bonding, at least two large joining partners in vehicle construction, in particular in aircraft construction, comprises the following steps: detecting the geometric data of the joining partners in an automated manner, detecting the joint gap dimensions of the joining partners from the geometric data, applying adhesive to one or both joint faces of the two joining partners to be joined as a function of the joint gap dimensions, joining the joining partners in the joining position, and sequentially applying joining pressure to the joint faces along the joint gap to bring the joining partners into the final joining position.

Abstract: According to an exemplary embodiment of the present invention, a diagnosis system for detecting a state of emergency during assembly of a fuselage (101) of an airplane is provided, which is adapted for detecting an emergency event and outputting information relating to the actual position of the emergency event. This may provide for a fast error identification during airplane assembly.

Abstract: A drop test device includes a suspension frame, a delay roller which is placed and mounted on the suspension frame, and at least one suspension cable, a first end of which is connected in a stationary manner to an attachment point on the outer surface of the delay roller and a second end of which includes a mounting which can be releasably or fixedly connected to a drop object.

Abstract: A method for operating a control panel of an aircraft includes: sending display data from a control panel to a central controller of the aircraft, the display data including values to be displayed on a display screen of the control panel; loading, in the central controller, a display template from a central data storage, the display template including information for layouting the display data; generating a display page for the control panel in the central controller by merging the display data and the display template; sending the display page to the control panel; and displaying the display page on a display screen of the control panel.

Abstract: A mounting system for objects in a transportation means includes a profile rail, at least one locking device with a base body that is bringable in surface contact with a supporting surface of the profile rail and at least one locking body which is interlockable with the profile rail, as well as an actuating device with an actuating element that extends parallel to the profile rail and a clamping body that is connected to the actuating element. The clamping body is realized in such a way that it exerts a compressive force, which results in the locking body being interlocked, upon a component of the locking device during a motion of the actuating element in a first direction parallel to the profile rail and releases the interlock during a motion of the actuating element in a second, opposite direction.

Abstract: A method for manufacturing a fluid-leading component includes positioning a base element machined by a material-removing method with a planar upper face in a mounting support. The method at least includes the initial application of a layer section with predetermined dimensions of a particulate material in a predetermined region on the planar upper face of the base element; the heating of the layer section by a heat source in such a manner that the particles of the material within predetermined dimensions bond; and the application thereto and heating of at least one further layer section with predetermined dimensions of a particulate material in a predetermined region. In this way it is possible, in the generative manufacturing method, to obviate the need to provide support structures that subsequently have to be removed, and the base element is a functional part of the component to be manufactured.

Abstract: The invention is based on a partition wall in an aircraft, wherein the partition wall comprises a support element and a tension-mounted material. According to the invention, the support element is composed of individually formed system components, and the tension-mounted material is supported by the support element such that an area-shaped partition wall is created in the aircraft.

Abstract: In a method for operating a cooling system for cooling food on board an aircraft, a partial amount of refrigerant, which, in the rest state, is stored in a receiving space of a refrigerant container in the gaseous state of aggregation, is discharged from the receiving space of the refrigerant container into a cooling circuit of the cooling system. The partial amount of the refrigerant is directed into a liquefier arranged in the cooling circuit and converted to the liquid state of aggregation. The partial amount of the refrigerant liquefied by the liquefier is directed through a heat exchanger arranged in the receiving space of the refrigerant container. The remaining refrigerant, stored in the receiving space of the refrigerant container in the gaseous state of aggregation, is converted to the liquid state of aggregation by heat energy transfer to the partial amount of the refrigerant flowing through the heat exchanger.

Abstract: The present invention provides a method and a device for providing a three-phase electrical system alternating voltage for an electrical system of an aircraft, a plurality of voltage sources being provided which comprise at least one engine generator and a further voltage source, in particular a fuel cell, comprising one or more frequency converters for converting an alternating voltage of variable frequency provided by the respective engine generator into a first output alternating voltage and comprising at least one cyclo-inverter for cyclo-inverting a voltage provided by the respective further voltage source into a second output alternating voltage which is synchronous with the first output alternating voltage and constitutes the electrical system alternating voltage.

Abstract: The invention relates to a method for producing a fiber composite workpiece. In the method according to the invention, cross-linking silicone is used with the aid of a volatile diluent for infiltrating individual mats of a mat composite. A further object of the present invention is a device for performing the method according to the invention.

Abstract: The invention relates to an elongated supporting pillar for a high-strength structural component, wherein the supporting pillar is designed to absorb bending forces that act transversely to a longitudinal direction of extension of the supporting pillar. The supporting pillar comprises a wall which at least partially encloses an elongated cavity of the supporting pillar. A reinforcement structure is arranged within the cavity and transversely to the direction of longitudinal extension in such a manner that the reinforcement structure can absorb at least some of the bending forces. The reinforcement structure is designed integrally with the wall, wherein both the wall and the reinforcement structure comprise a meltable material.

Abstract: An aircraft structure is provided with load-bearing hollow structural elements that form an aircraft fuselage. The cavities in the structural elements are designed as air ducts for an air conditioning system of the aircraft. An aircraft is also provided with such an aircraft structure.

Abstract: A decompression assembly (10; 10?) for an aircraft comprises a first cabin lining element (12; 12?) having a boundary area (14; 14?) and a second cabin lining element (20; 20?) having a boundary area (22; 22?), wherein the boundary area (22; 22?) of the second cabin lining element (20; 20?) is disposed at a smaller distance from an aircraft outer skin (24; 24?) than the boundary area (14; 14?) of the first cabin lining element (12; 12?). An air discharge opening (28; 28?) is disposed between the boundary area (14; 14?) of the first cabin lining element (12; 12?) and the boundary area (22; 22?) of the second cabin lining element (20; 20?) for discharging air from a cabin (18; 18?) of the aircraft into an area (30; 30?) of the aircraft located between the cabin lining elements (12, 20; 12?, 20?) and the aircraft outer skin (24; 24?).

Abstract: A wingtip device for a wing is provided. The wingtip device has an inner end and an outer end, and in which the local dihedral of the wingtip device increases or reduces from the inner end to the outer end, with a pressure-side flow surface and a suction-side flow surface. At least two ancillary wing sections are arranged on the wingtip device, projecting in each case from the flow surface of the wingtip device. The ancillary wing sections in each case form an interface with the surface of the wingtip device; which interfaces are located spaced apart from one another. A wing with such a wingtip device is also provided.

Abstract: The present invention is concerned with a system for the oxygen supply of persons in an aircraft. In order to provide the simplest possible system, which is suitable in particular for a reconfiguration of the seat devices (12), the system has at least one oxygen line, one oxygen feed, and multiple attachment points for oxygen masks (24), the oxygen line extending in the longitudinal direction and the attachment points being connected to the oxygen line. The attachment points are preferably situated linearly and are spaced apart from one another in the longitudinal direction.

Abstract: A force introduction fitting for lightweight constructional components comprises at least one radial force introduction surface, at least one axial force introduction surface, and at least one receiving means for holding the force introduction fitting and for introducing loads into the force introduction fitting. The radial force introduction surface and the axial force introduction surface enclose a hollow space. The radial force introduction surface and the axial force introduction surface form a single-piece component. Such a force introduction fitting can be produced with the use of a selective laser melting method. The force introduction fitting can thus be adjusted in a particularly flexible manner to the load conditions, comprises particularly advantageous materials characteristics and features a lightweight construction.

Abstract: The invention relates to a system (10) for configuring an aircraft passenger cabin, said system comprising a first database (12) that stores cabin equipment component data pertaining to cabin equipment components selected for and included in a configuration of the aircraft passenger cabin. In addition, said system (10) comprises a second database (14) that stores configuration rules pertaining to the configuration of the aircraft passenger cabin. Finally, the system (10) comprises a unit (16) for generating a documentation, configured in such a way that documentation of the configured aircraft passenger cabin is generated on the basis of at least one user-defined configuration parameter, on the basis of the cabin equipment component data stored in the first database (12), and on the basis of the configuration rules stored in the second database (14).

Abstract: A connection arrangement for at least two abutting components to be firmly connected to one another, includes a self-piercing rivet having a rivet head for punching of a hole and subsequent riveting of the components, wherein a washer is allocated to the self-piercing rivet at the distal end region opposite to the rivet head, with the washer including a frontal area for the insertion of a circular indentation to create a firm compression connection between a hole in the washer and the distal end region of the self-piercing rivet.

Abstract: A system for evacuating persons from a vehicle includes a light signal generating device, which is adapted to emit at least one visual light signal that indicates at least one preset escape route for at least one person to be evacuated.

Abstract: The invention pertains to a composite panel with a first cover layer, a second cover layer and a first core layer that is arranged between the first cover layer and the second cover layer and features a plurality of cells that are separated from one another by walls at least in certain areas, wherein the first cover layer features a draining layer. The inventive composite panel may be distinguished from a composite panel according to the state of the art in that a second core layer with a plurality of cells that are separated from one another by walls at least in certain areas is arranged between the first cover layer and the first core layer.