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: A door arrangement for an aircraft comprising a door designed to close an aperture in an outer skin of the aircraft, and a articulated arm which is fixed by a first end to the door and which is designed to move the door in at least two translational directions and at least two rotational directions. An aircraft area with this door arrangement and an aircraft having such an aircraft area are furthermore provided. The aircraft area comprises a door aperture arranged in an outer skin of an aircraft, and a door arrangement. Here the door of the door arrangement may be designed to close the door aperture from an inside of the outer skin, and the articulated arm of the door arrangement may be fixed to the aircraft area.

Abstract: An installation system for a cabin of a vehicle includes at least one built-in component for installation in the cabin, multiple base elements for arrangement on a structurally fixed component of the vehicle and multiple holding devices that can be connected to the at least one built-in component. The holding devices each include a clamping unit with receiving space defined by at least two clamping members, wherein the receiving space can be moved between an open and a closed state through movement of at least one of the clamping members in the direction of the other clamping member in each case and wherein the clamping unit is configured to move the at least one clamping member by pressing the clamping unit onto a base element when the receiving space is in the open state and thereby closing the receiving space including the base element.

Abstract: A tolerance compensation subassembly in the form of a tolerance compensation element or a tolerance compensation region to improve the production, maintenance and repair of aircraft. The tolerance compensation subassembly contains an actuator which is formed from an electro-active polymer so that the tolerance compensation subassembly is electrically switchable between a fixed state and a non-fixed state. As a result, automation of the assembly of aircraft components on each other can be enabled or facilitated.

Abstract: A structural component for a vehicle, in particular an aircraft or spacecraft, includes a fiber composite laminate comprising an electric energy store which is configured as a multilayer electrochemical fiber composite battery for storing electric energy in a rechargeable manner; and an electrothermal temperature regulation sublayer which is configured for supplying thermal energy to the electric energy store and conducting thermal energy away from the electric energy store when required in order to regulate the temperature. The structural component further comprises a control device which is configured for controlling the temperature regulation of the electric energy store by means of the electrothermal temperature regulation sublayer.

Abstract: With the measures described herein, a structural composite laminate is provided that includes a structural fuel cell, a structural supercondensator and a structural battery. Each of these components is configured in a self-supporting manner, such that aircraft parts, like exterior panels, may be manufactured from the laminate. The aircraft parts are capable of generating electrical energy by means of the structural fuel cell and distribute the electrical energy over the whole aircraft without cabling. Furthermore, short power demand peaks can be absorbed by the structural supercondensator, whereas the basic load is supplied by the structural battery.

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: 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: A vortex generator apparatus for an aircraft includes a surface section having a receiving recess, a vortex generator having a first edge, an opposite second edge and a vortex generator surface component extending from the first edge to the second edge, wherein the first edge is fixedly arranged in or adjacent to the receiving recess. The vortex generator surface component includes at least one electroactive polymer assembly, wherein the at least one electroactive polymer is switchable into an extended state by applying an electrical voltage and into a neutral state by removing the electrical voltage. The electroactive polymer assembly and the vortex generator surface component are configured to retract the vortex generator surface component completely into the receiving recess in the neutral state of the electroactive polymer assembly and to extend the vortex generator surface component from the receiving recess in the extended state.

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 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: 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 skin panel with an energy-storing layer for an aircraft or spacecraft comprises structural layers for providing structural stability to the skin panel, at least one of the structural layers forming an exterior supporting layer of the skin panel and at least one of the structural layers forming an interior supporting layer of the skin panel. Primary functional layers are embedded between the exterior supporting layer and the interior supporting layer for providing functional capabilities to the skin panel. The structural layers and the primary functional layers are formed together as a composite laminate and the functional layers comprise an energy-storing layer configured as a structural electro-chemical battery. The present disclosure further pertains to a method for manufacturing such an energy-storing layer for a skin panel of an aircraft or spacecraft.

Abstract: An aircraft seat fastening assembly, due to the use of electroactive polymers, facilitates the compensation of tolerances and the fastening of aircraft seats in the passenger cabin of the aircraft. A fixing actuator contains the electroactive polymer and can be switched electrically between a fixed state, in which a movement of a fastening region is not possible, and a non-fixed state, in which a movement of the fastening region is possible in a vertical direction. The aircraft seats can thereby be displaced in a continuously variable manner along the aircraft seat fastening rail. The aircraft seats can also be locked in a fully automated manner, and possibly from a central location. It is also conceivable to individually control the aircraft seats and/or the group(s) of seats.

Abstract: A tolerance compensation subassembly in the form of a tolerance compensation element or a tolerance compensation region to improve the production, maintenance and repair of aircraft. The tolerance compensation subassembly contains an actuator which is formed from an electro-active polymer so that the tolerance compensation subassembly is electrically switchable between a fixed state and a non-fixed state. As a result, automation of the assembly of aircraft components on each other can be enabled or facilitated.

Abstract: An installation system for a cabin of a vehicle includes at least one built-in component for installation in the cabin, multiple base elements for arrangement on a structurally fixed component of the vehicle and multiple holding devices that can be connected to the at least one built-in component. The holding devices each include a clamping unit with receiving space defined by at least two clamping members, wherein the receiving space can be moved between an open and a closed state through movement of at least one of the clamping members in the direction of the other clamping member in each case and wherein the clamping unit is configured to move the at least one clamping member by pressing the clamping unit onto a base element when the receiving space is in the open state and thereby closing the receiving space including the base element.

Abstract: A method for manufacturing a lining panel with integrated electric lines for a lining of a passenger cabin of an aircraft or spacecraft includes using an additive manufacturing (AM) or 3D printing technique to form the electric lines on or into a panel body of the lining panel. A lining panel with integrated electric lines for a lining of a passenger cabin of an aircraft or spacecraft includes a panel body and electric lines being formed on or into the panel body using an AM or 3D printing technique.

Abstract: A three-dimensional printing device includes a movable unit with a superconductor and a printing head arrangement for printing a printing material, a magnetic field generator adapted to generate a magnetic field, and a control device. The magnetic field generator and the movable unit are adapted for coupling in a force-locking manner by means of frozen magnetic flux, and the controlling device is adapted to control a magnetic field strength of the magnetic field generator.

Abstract: A door arrangement for an aircraft comprising a door designed to close an aperture in an outer skin of the aircraft, and a articulated arm which is fixed by a first end to the door and which is designed to move the door in at least two translational directions and at least two rotational directions. An aircraft area with this door arrangement and an aircraft having such an aircraft area are furthermore provided. The aircraft area comprises a door aperture arranged in an outer skin of an aircraft, and a door arrangement. Here the door of the door arrangement may be designed to close the door aperture from an inside of the outer skin, and the articulated arm of the door arrangement may be fixed to the aircraft area.