Abstract: An aircraft includes a passenger cabin having a floor, a cargo compartment below the floor, a first access unit for accessing the cargo compartment from the passenger cabin, the first access unit being located on the floor and a utility space module arranged in the cargo. At least one part of the cargo compartment includes a first lateral half and a second lateral half in relation to a longitudinal axis of the aircraft; the lateral halves form the part of the cargo compartment. The utility space module includes a utility space cross-section in a direction normal to the longitudinal axis, which is dimensioned such that it conforms to a cross-section of one of the lateral halves of the cargo compartment. Further, the utility space module is placed exclusively in the first lateral half or the second lateral half of the cargo compartment directly below the first access unit.

Abstract: A slat track device (7) for an aircraft wing (1) including a beam-shaped main load bearing track structure (9) connected to a slat (5) and movably connected to a main wing (3), a guidance surface (11) at the track structure (9) and guided along a corresponding guidance device (19) at the main wing, a connection device (13) at the track structure (9) connecting the track structure (9) to the slat (5), and an engagement device (15) at the track structure (9) and configured to engage a drive member (33) of a drive unit (37) provided at a main wing (3). The slat track device has redundant main load paths achieved by the track structure (9) having a first track member (41) and a separate second track member (43) both connected to the connection device (13) and the engagement device (15).

Abstract: An aircraft airflow modification device, comprising: at least one resiliently deformable base member; and at least one resiliently deformable flap member that extends from the resiliently deformable base member. Deformation of the resiliently deformable base member from a first state to a second state results in corresponding deformation of the resiliently deformable flap member from a first state to a second state.

Abstract: A wing arrangement for an aircraft including a latching arrangement (29, 29?, 29?) having a latching member (31, 31?, 31?) and an engagement device (33), wherein the latching member (31, 31?, 31?) is fixed to a wing tip section (13), and the engagement device (33) has a base member (35) on a wing base section (7) and has an abutment surface (43), and an engagement member (45, 45?, 63) supported on the base section (7) and moves between a release position and a latching position by an actuator (49, 49?) coupled to the engagement member (45, 45?, 63) and the base section (7), wherein when the tip section (13) is in the deployed position, the latching member (31, 31?, 31?) abuts the abutment surface (43) and the engagement member (45, 45?, 63) can move between the release position and the latching position, wherein when the latching member (31, 31?, 31?) abuts the abutment surface (43) and the engagement member (45, 45?, 63) is in the latching position, the engagement member (45, 45?, 63) abuts on a surface sect

Abstract: A vehicle passenger cabin has a holding structure having multiple load introduction points, a multiplicity of support structure parts to be attached to the load introduction points, a lower base for delimiting a lower passenger deck, and a multiplicity of furnishing components to be fastened to the support structure parts. The holding structure has laterally on both sides one floor overhang as a lower delimitation of an upper passenger deck, extending from a laterally outer region of the holding structure radially inwards and at a distance vertically from the lower base. The structure parts are at least regionally curved or bent and are connected at an upper end and at a lower end to an upper and a lower load introduction points, respectively. The structure parts have a first receiving surface for receiving one of the furnishing components, which first receiving surface adjoins the floor overhang radially on the inside.

Abstract: A passenger cabin for a vehicle has an upper passenger deck with an upper arrangement of seats, a lower passenger deck with a lower arrangement of seats, an upper floor for the upper passenger deck arranged between the upper passenger deck and the lower passenger deck, and a lower floor for the lower passenger deck delimiting the lower passenger deck. The upper floor has a central hump region extending along a longitudinal axis of the passenger cabin at least in regions and above which the upper arrangement of seats is arranged, and two side regions adjacent to the hump region. The central hump region is raised relative to the side regions. The lower floor has a lower gangway, wherein the at least one lower arrangement of seats is arranged below the side regions of the upper floor, and the lower gangway is arranged below the central hump region.

Abstract: A system for handling a first component includes: a main-device and a module-device, the module-device having a pressing section arranged to form an outer surface of the module-device, the module-device configured to releasably receive the first component, such that a connection section of the first component is attachable to the pressing section of the module-device. The module-device is releasably connected to a second component, wherein the main-device includes a grabbing unit adapted for releasably connecting the module-device, such that the pressing section is arranged to form a first outer surface section of the main-device, and wherein the main-device includes a connector for connecting to a handling-unit for arranging the main-device at the second component, such that the connection section of the first component, if attached to the pressing section of the module-device, is at least indirectly attachable to a front surface of the second component.

Abstract: The disclosure relates to a component device, in particular for a primary supporting component of an aircraft, which comprises a first component element, a second component element, a bonding providing a connection between the first component element and the second component element, a marker substance device configured to dispense a volatile marker gas to the environment when in contact with the surrounding air and being hermetically sealed from the surrounding air by the first component element, the second component element, and/or the bonding if the bonding is not damaged, and a detector device configured to detect the marker gas dispensed by the marker substance device.

Abstract: A plastics material component for an aircraft includes (i) a substrate, which comprises one or more thermosetting plastics materials, and (ii) one or more layers which are applied to the substrate, at least one layer S1 comprising mica. A method for producing the plastics material component includes providing a substrate including at least one thermosetting plastics material or one polymer which is crosslinked to form a thermosetting plastics material, and applying one or more layers to the substrate, wherein at least one layer includes mica. The mica-containing layer is applied directly to the substrate and the application is carried out before and/or during the curing of the thermosetting plastics material.

Abstract: A system for the additive manufacturing of components includes a powder receptacle, which is designed to receive a powdered material in the form of a starting material for a component to be manufactured, a construction platform that is mounted within the powder receptacle and is mounted so as to rotate relative to the powder receptacle about a rotational shaft, a lowering drive, which is designed to incrementally or continuously lower the construction platform within the powder receptacle, and an energy input apparatus, which is arranged above an opening in the powder receptacle and is designed to carry out locally selective melting or hardening of a powdered material introduced into the powder receptacle on a surface of the material. The construction platform can be tilted by an angle of inclination relative to a rotational shaft of the rotatable mount.

Abstract: An overhead bin for an aircraft comprises a base unit that is designed to fasten the overhead bin to a retaining structure of the aircraft, and a mounting unit that is connected to the base unit. By way of the mounting unit, a stowage space of the overhead bin can be accessed. The base unit provides a first stowage space region, and the mounting unit provides a second stowage space region that together with the first stowage space region forms the stowage space of the overhead bin.

Abstract: An embodiment of the invention relates to a system for receiving cargo or passengers in a vehicle. The system includes a bottom beam and several functional units, wherein each functional unit includes a floor segment and a seat row with several passenger seats being attached to the floor segment. Each functional unit is assigned to a pivoting device for pivoting the functional unit relatively to bottom beam. Another embodiment of the invention relates to a vehicle having such a system.

Abstract: An expandable cargo storage for a transportation means, comprising a first storage wall and a second storage wall opposite of the first storage wall, and a plurality of foldable walls arranged between the first and the second storage wall, each of the plurality of foldable walls being foldable between a first position in which the respective foldable wall is arranged essentially in parallel with the second storage wall, and a second position in which the foldable wall is arranged essentially perpendicularly to the second storage wall, wherein, when each of the foldable walls is arranged in its first position, the cargo storage is in a first operational state enclosing a first volume, and when each of the foldable walls is in its second position, the cargo storage is in a second operational state enclosing a second volume which is larger than the first volume.

Abstract: A boundary-layer-influencing aerodynamic part comprises a carrier element provided with at least one air passage aperture for guiding an air flow through the carrier element, an air guiding layer disposed on the carrier element and a cover layer constituting at least a part of a flow surface and being configured to have air flow there through at least in sections. The air guiding layer is configured to have air flow there through with an air flow supplied to the part, at least in certain operating phases of the part, through the cover layer and flowing in the direction of the carrier element or through the air passage aperture of the carrier element and flowing in the direction of the cover layer. The cover layer is applied directly to the air guiding layer via an additive manufacturing method.

Abstract: A composite sandwich panel comprises a top layer, a bottom layer, and a honeycomb core layer sandwiched between the top layer and the bottom layer. The honeycomb core layer includes an array of hollow cells formed between vertical walls. This array of hollow cells is recessed in the form of a channel network running from a first side face of the sandwich panel through the honeycomb core layer to a second side face, opposite to the first side face of the sandwich panel.

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: In controlling pressure in an aircraft cabin, during flight operation, an effective flow cross-sectional area of at least one outflow valve is controlled to adjust air flow exiting the cabin through the outflow valve so pressure within the cabin is controlled according to a predetermined cabin pressure control strategy. During flight operation of the aircraft, an effective flow cross-sectional area of at least one negative relief valve is controlled to adjust air flow entering the cabin through the negative relief valve so a negative differential pressure between the pressure within the aircraft cabin and an ambient pressure prevailing outside of the aircraft cabin is prevented from exceeding a predetermined threshold value. During ground operation of the aircraft, the effective flow cross-sectional area of the at least one negative relief valve is controlled to allow an equalization between pressure within the cabin and ambient pressure prevailing outside of the aircraft.

Abstract: A visual output assembly for an aircraft cabin includes at least one electronic display device, a projection screen, an image projector configured to project images onto the projection screen, and at least one illumination device.

Abstract: An aircraft interior lining component is formed at least partially of a thermoplastic foam material and includes a first surface which faces an interior of an aircraft cabin when the aircraft interior lining component is mounted in an aircraft, and a second surface which faces away from the interior of the aircraft cabin when the aircraft interior lining component is mounted in an aircraft. The second surface of the aircraft interior lining component includes at least one supporting section and at least one surface section adjacent to the supporting section and recessed relative to the supporting section. The supporting section is dimensioned and arranged so that it is supported, when the aircraft interior lining component is mounted in an aircraft, on an element of a primary structure of the aircraft at least when a predetermined load acts on the first surface of the aircraft interior lining component.

Abstract: A device for controlling an opening forming an air inlet or air outlet in an outer skin of a vehicle. The device comprises a multiple-member inlet ramp, which is configured to vary at least one of a degree of opening of the opening and a cross section of an air duct connected to the opening; an actuator, which is coupled to the multiple-member inlet ramp and is configured to move the multiple-member inlet ramp into a shape related to at least one of a certain degree of opening and a certain cross section; and a movement control device, which is configured to control a movement of the multiple-member inlet ramp.