Abstract: A method of producing a panel for lining or cladding an aircraft interior, such as an aircraft cargo hold includes arranging at least one resin layer of a thermo-plastic polymer and at least one reinforcement layer of reinforcement fibres upon one another in a stack, wherein each resin layer extends adjacent and/or substantially parallel to each reinforcement layer; and consolidating the stack to form a panel by applying heat and pressure to the stack. The pressure is applied to the stack in a direction substantially perpendicular to a primary plane of the layers. The pressure is applied to the stack in a non-constant distribution over the primary plane. A corresponding panel for lining or cladding an aircraft interior, such as a cargo hold is also described.

Abstract: A method of transmitting speech and digital data via an analog speech channel within a single frequency band, wherein an analog speech signal is transmitted via the speech channel and a stream of digital data is encoded by an encoding device to a sequence of blocks of symbols taken from a predetermined set of symbols. The transmission of the analog speech signal is periodically blanked during predetermined spaced time intervals, and the blocks of symbols are transmitted during the time intervals. In each time interval a plurality of signals are transmitted via a corresponding plurality of spaced predetermined carrier frequencies. A receiver receives the analog speech signal and the signals transmitted during the time intervals. The signals are demodulated to recover the individual symbols and the respective block of symbols transmitted during the time interval groups, and the digital data is recovered by decoding recovered blocks of symbols.

Abstract: The invention relates to a movable fastening unit for a seat frame in an aircraft. In said fastening unit, a connecting element can be movably mounted on both a seat structure and a floor fixture by means of bearings, thus allowing the seat frame to be moved relative to the floor fixture without having to detach the fixture from the floor.

Abstract: The invention relates to a cabin system for an aircraft fuselage, having one or more lining components for interior lining, and optionally one or more cabin equipment components, wherein the lining component can be installed either separately or in combination with a further lining component and/or a cabin equipment component under tension in the aircraft fuselage such that a cabin that is under tension in the circumferential direction and attaches to the aircraft fuselage is defined. In this manner a passenger cabin configured as a closed safety cell is created in a fuselage, which is of particular advantage in an aircraft fuselage made of a fiber composite material because no splinters or the like can penetrate the self-supporting passenger cabin in case of damage to the same.

Abstract: A method for displaying information by means of a dual-view-display in a passenger-cabin of an air-/spacecraft, comprising the following steps: providing the dual-view-display on a predetermined portion of the passenger-cabin; providing first information by means of the dual-view-display, in such a way that said information can be perceived from a gangway between rows of seats of the passenger cabin; and simultaneously providing second information, different from the first information, by means of the dual-view-display, in such a way that said information can be perceived from one of the rows of seats. A display device for displaying information in a passenger-cabin of an air-/spacecraft, comprising a dual-view-display which is arranged on a predetermined portion of the passenger-cabin, the dual-view-display being configured to provide first and second information in the above described ways. A passenger-cabin for an air-/spacecraft comprising said display-device.

Abstract: A method for mounting an aircraft component, which in the mounted state is movable between a first and a second operating position and is taken up in its first operating position in a mounting area, comprises the measuring of the mounting area, in order to obtain data characteristic of the shape and/or the dimensions of the mounting area. The data characteristic of the shape and/or the dimensions of the mounting area are projected onto the aircraft component arranged in its second operating position. Finally, the aircraft component arranged in its second operating position is adjusted with reference to the projection of the data characteristic of the shape and/or the dimensions of the mounting area.

Abstract: A display module for displaying passenger-specific display information in an aircraft, comprising: a display, a control unit, a storage device, and a first interface, wherein the first interface is connected to the control unit, and wherein the control unit is designed, on the basis of a signal that is present at the first interface, to read out a storage device content stored in the storage device and associated with the signal in relation to display information, and on the basis of the read-out storage device content and of the signal present at the interface to control the display.

Abstract: An aircraft with a daylight input system may provide improved illumination with a reduced energy demand. The aircraft has a fuselage construction and at least one interior area arranged within the fuselage construction and includes the daylight input system. The daylight input system includes at least one light receiving device arranged in an outer wall, at least one light guiding device and at least one light emitting device arranged on the inner side. In this case, the light receiving device serves for receiving daylight present in the surrounding outside the outer wall and transmitting the same into the light guiding device. The light guiding device optically couples the light receiving device to the light emitting device. This light emitting device in turn emits the received daylight into an interior space on the inner side of a wall construction, wherein at least a partial deflection of the daylight is provided.

Abstract: An aerofoil wing with a main aerofoil, a high-lift flap movably arranged on the aerofoil wing by adjustment mechanisms. Each of the adjustment mechanisms including a first adjustment lever hinged to the main aerofoil via a first rotary linkage, with the formation of a first axis of rotation, a second adjustment lever hinged to the high-lift flap via a second rotary linkage, with the formation of a second axis of rotation, and a central linkage, with the formation of a third axis of rotation, such that the first, second and third axes of rotation pass through a common pole. The aerofoil wing further includes a drive device with a drive module mounted on the main aerofoil, and movable with respect to the drive module a drive lever coupled to the high-lift flap, and a stop device to limit the maximum extended setting of the high-lift flap.

Abstract: A pressure fuselage of an aircraft, which fuselage in longitudinal direction comprises several fuselage sections, wherein at least one rear dome-shaped pressure bulkhead is provided to form an aircraft-internal pressurized region, with a ring-shaped frame element profile being provided for radially outward attachment of said dome-shaped pressure bulkhead to at least one fuselage section, wherein the frame element profile on the side of the dome-shaped pressure bulkhead comprises a U-shaped profile section whose first end-side limb is attached towards the back on the dome-shaped pressure bulkhead by way of connecting means, and whose elongated radially outward extending second limb establishes a connection to the at least one fuselage section in such a manner that it is possible for the connecting means to be installed solely from the aircraft-internal pressurized region.

Abstract: An interface device for a cabin monument, in particular for assembly in an aircraft or spacecraft, including a routing device, a first plurality of interface connection sockets, which are connected to the routing device via a first plurality of connection lines and to which a vehicle interface of the aircraft or spacecraft can be connected. A second plurality of interface connection sockets are provided which are connected to the routing device via a second plurality of connection lines and to which a cabin monument can be connected. The routing device is constructed so as to selectively electrically connect interface connection sockets of the first plurality of interface connection sockets to interface connection sockets of the second plurality of interface connection sockets.

Abstract: A device for modifying audio signals to be output within a room is introduced. The device exhibits an input for supplying audio information and a processor unit for modifying the audio information. The device further exhibits at least two outputs for distributing respectively modified audio information. The processor unit is here adapted to modify the audio information in such a way that respective sound sources to be connected to the outputs simulate a linear sound source for outputting the audio information according to the audio signals. The linear sound source is here achieved via the coherent coupling of a plurality of point sound sources, for example loudspeakers.

Abstract: An auxiliary cooling device is configured to be operated outside of an aircraft. The auxiliary cooling device is configured to be connected to an aircraft liquid cooling system which includes a refrigerating device, a coolant supply connection, a coolant discharge connection, and a control device. The auxiliary cooling device includes a cold source that is adapted to cool a coolant down to a desired low temperature, an auxiliary cooling device outlet which is connected to the cold source and connectable to the coolant supply connection. The auxiliary cooling device also includes an auxiliary cooling device inlet which is connected to the cold source and connectable to the coolant discharge connection of the aircraft liquid cooling system.

Abstract: An end stop device for restraining an ULD from movement across a cargo deck surface of an aircraft includes a main body; and a mounting interface connected to the main body which is configured and arranged to attach the end stop device to the cargo deck by means of a corresponding tie down ring. Each mounting interface includes a tongue-like support plate which is partially protruding below a bottom side of the main body, at least one recess arranged in an area above the support plate, wherein side walls of the recess form a frame-like structure. and a bolt portion extending from the support plate into the recess and partially surrounded by the frame-like structure. The bolt portion is configured to engage the tie down ring in an operation mode where the end stop device is fixed to a tie down ring.

Abstract: The invention relates to a method of producing an overlapping hybrid connection between two or more components. A hybrid connection in the meaning of the invention is characterized by adhesively bonding and producing mechanical spot joint connections between two joining parts, the adhesive layer being arranged in the region of the mechanical joint connections. The method according to the invention is carried out in the following method steps: purposefully removing material from one or more of the components or purposefully applying material to one or more of the components in the region of the lap joint to be produced to form one or more projections, applying adhesive to one or more of the components in the region of the lap joint to be produced, overlapping the components, pressing the components together in the region of the lap joint to press the projections against the overlapping component(s) and producing one or more mechanical spot joint connections on the projections in the overlap region.

Abstract: An aerodynamic body that can be adjusted relative to a main wing of an aircraft by an adjusting device is provided. A gap between the aerodynamic body and another aerodynamic body or a component of the fuselage or the main wing is formed on one lateral end and said and the gap is variable due to the adjustability of the aerodynamic body. The body features a gap bridge-over device with a shell part that extends along the gap and overlaps the outer shell of the aerodynamic body in the wingspread direction on the front side thereof so that the shell part can be telescopically moved relative to this aerodynamic body in the wingspread direction. An airfoil for an aircraft with a main wing and a plurality of aerodynamic bodies that are arranged adjacent to one another transverse to the chord direction is also provided.

Abstract: A pressure bulkhead of an aircraft with a fuselage shell and a pressure bulkhead disposed therein preferably in the rear region for forming a fuselage-internal pressure region, which pressure bulkhead is attached on the edge in the interior of the fuselage shell, wherein the pressure bulkhead has a lenticular cross-section and a sandwich construction that comprises a foam core sandwiched between two opposing exterior shells.

Abstract: A device for securing a mobile device in an aircraft cabin includes a first connection element having a bar receiving member. The device further has a second connection element which includes a bar which is suitable for co-operating with the bar receiving member of the first connection element, the bar being moveable between an unlocking position and a locking position, in which the bar of the second connection element is able to be brought into engagement with the bar receiving member of the first connection element.

Abstract: A power distribution device has a number N1 of conversion devices comprising a respective cascade generator for converting a first part of a mechanical power into a first electrical power with an alternating voltage of constant amplitude and constant frequency, and comprising a respective frequency converter for supplying a second electrical power with the alternating voltage of constant amplitude and constant frequency as a function of a second part of the mechanical power; a number N2 of constant frequency buses for the respective transfer of the electrical power of constant frequency supplied by the at least one conversion device to a number N3 of loads which comprises at least a number N4 of loads to be controlled in terms of their power consumption; and a number N4 of control devices, wherein the respective control device is coupled between the respective load to be controlled and the constant frequency bus and is designed to control the power consumption of the load to be controlled.

Abstract: A component for building a fuselage section of an aircraft includes a border area connectable to a corresponding further border area of a further component so as to form an electrically conductive joint, wherein the component includes a composite structure.