Abstract: A leading edge structure (1) for a flow control system of an aircraft (101) including a double-walled leading edge panel (3) with a first side portion (11) extending to a first attachment end (17), a second side portion (13) extending to a second attachment end (19), an inner wall element (21) facing a plenum (7), an outer wall element (23) facing ambient flow (25), and a core assembly (97). The outer wall element (23) includes micro pores (31) and the inner wall element (21) includes openings (33) which form a fluid connection from ambient flow, through the core assembly (97) and to the plenum (7). The thickness of the outer wall element is reduced due to the first attachment end (17) and/or at the second attachment end (19) attached to the inner wall element (21) by both bonding and fasteners (85, 87, 89, 91).

Abstract: A time-delay latch for securing a structure in a specified position includes a housing, a fluid chamber contained within the housing for holding fluid, a pin that extends through the fluid chamber and is axially movable within and through the fluid chamber, and a release frame movably secured within the housing. When the pin is in a latched position, the release frame engages with the pin to prevent axial movement of the pin. When the pin is in an unlatched position, the release frame disengages from the pin to allow axial movement of the pin. The axial movement of the pin between the latched position and the unlatched position requires a prescribed duration of time to elapse. During operation, the axial movement of the pin between the unlatched position and the latched position can occur faster than the prescribed duration of time.

Abstract: A multipurpose connector for connecting a multiplicity of lines of an aircraft monument. The multipurpose connector comprises a base bracket, a system connector plate configured to receive a multiplicity of first line adapters, a monument connector plate configured to receive at least one second line adapter, and a movement device configured to move the system connector plate relative to the base bracket and the monument connector plate between an open position and a closed position. The system connector plate is, in the closed position, arranged relative to the monument connector plate such that the at least one second line adapter of the monument connector plate is operatively connected to an associated first line adapter of the system connector plate, and, in the open position of the system connector plate, the multiplicity of first line adapters and the at least one second line adapter are detached from one another.

Abstract: A hatch locking device for an aircraft hatch includes an eccentric bush which can be connected to a hatch bulkhead of the aircraft hatch panel, an inner lining which is introduced into the eccentric bush and has a bolt receptacle which is oriented centrally along a bolt receptacle axis for receiving a locking bolt, a conical pressing sleeve in the inner lining, a conical clamping sleeve, the outer conical shell face of which is in displaceable engagement with an inner conical shell face of the conical pressing sleeve, and the inner cylindrical shell face of which is flush with the outer wall of the bolt receptacle, and linear actuators which are mounted on in each case two opposite sides of the conical pressing sleeve in the inner lining and are designed to displace the conical pressing sleeve along the bolt receptacle axis with respect to the conical clamping sleeve.

Abstract: A cabin module for an aircraft comprises a section which has an upward-facing surface in an installed state of the cabin module, wherein the upward-facing surface of the section comprises an integrated drainage channel. An aircraft furthermore comprises at least one such cabin module.

Abstract: An aircraft-floor element comprising a first cladding element configure to be swung from a first position to a second position. In the first position, the first cladding element is arranged parallel to a main plane of the aircraft-floor element and on a side of the aircraft-floor element which is directed towards a passenger cabin. In the second position, the first cladding is arranged at an angle to the main plane of the aircraft-floor element, wherein it forms a cladding for a cargo space. An aircraft zone having an aircraft-floor element and an aircraft having such an aircraft zone are also disclosed.

Abstract: A panel for covering a supply channel in a passenger cabin of a vehicle including a mounting surface facing the passenger cabin while the panel covers the supply channel. The panel is elongated in a longitudinal direction and adapted for mounting passenger supply units. The mounting surface includes spaced openings arranged along a longitudinal direction of the panel, wherein each opening includes a connector assembly for a passenger supply unit. The panel includes a mount securing passenger supply units. The mounting surface comprises extended areas for providing support in opposing lateral directions to passenger supply units mounted to the panel.

Abstract: A passenger cabin area includes at least one aisle extending along a longitudinal axis of the passenger cabin area, a seating area next to the aisle in the direction of a transverse axis, perpendicular to the longitudinal axis, of the passenger cabin area and in which at least one passenger seat is provided, and a plurality of sleeping berths arranged above the seating area in the direction of a vertical axis, perpendicular to the longitudinal axis and the transverse axis, of the passenger cabin area. Each sleeping berth is accessible from the aisle of the passenger cabin area via a stairway element assigned individually to the sleeping berth.

Abstract: A system for producing a component or semifinished product with a fibre-reinforced foam core, includes a substrate on which the foam core having a first main surface and an opposite second main surface is to be laid; a sewing device having a needle configured to be moved at least linearly; a fibre supply device for three-dimensional supply of a fibre; and a coating device. The sewing device is configured to position the needle at the first main surface and to pierce the foam core, such that a needle tip penetrates through the first main surface and then through the second main surface. The fibre supply device is configured to position a reinforcing fibre such that the reinforcing fibre is hooked into the needle tip. The coating device is configured to coat a reinforcing fibre hooked into the needle tip with resin immediately before the reinforcing fibre enters the foam core.

Abstract: A wing for an aircraft is disclosed including a fixed wing, a high-lift device and a hold-down arrangement arranged between two supports of the high lift device having a first hold-down element attached to the high-lift device and a second hold-down element attached to the fixed wing. The first hold-down element contacts the second hold-down element when the high-lift device is in a retracted position in which it prevents a trailing edge of the high-lift device from detaching from an upper surface of the fixed wing when the fixed wing bends in the spanwise direction. One of the hold-down elements is a load-limited hold-down element which comprises a biasing means. When the load transmitted through the hold-down arrangement exceeds an operational threshold, elastic deformation of the biasing element results in the hold-down arrangement no longer preventing the trailing edge high-lift device from detaching from the upper surface of the fixed wing.

Abstract: An aircraft usable as a passenger aircraft and a fire fighter aircraft. The passenger aircraft includes a passenger area with passenger seats and a permanently installed fire extinguishing medium tank for storing fire extinguishing medium such as water, as well as a fire extinguishing medium nozzle for discharging the fire extinguishing medium. The passenger aircraft may be a type from an aircraft series also including a long-haul aircraft having a center tank for range extension. In the passenger aircraft, a center tank may be used as an extinguishing medium tank.

Abstract: A wing for an aircraft, comprising a main wing and a slat assembly with a slat and a connection assembly with a slat track. The front end of the slat track is mounted to the slat, and the rear end and/or the intermediate portion of the slat track are mounted to the main wing by a roller or slide bearing. The slat track is movable along the track longitudinal axis. The connection assembly includes a drive unit. The drive unit includes a rotary actuator mounted to the main wing and having at least one drive arm rotatably driven about a rotation axis and drivingly engaging the slat track, and one of the drive arm and the slat track has at least one groove and the other one of the drive arm and the slat track comprises at least one spigot drivingly engaging the groove.

Abstract: A drilling method is provided allowing drilling in confined spaces with less effort. Two independent data sources are used for reducing tolerances between the component to be joined to the workpiece. The component is measured at the supplier using photogrammetry or laser scanning. First geometric data of the component obtained by this measurement are put in a data storage, such as a barcode tag or database. At the manufacturer, the first geometric data are used to position the component relative to the workpiece. Subsequently, the component is measured to obtain second geometric data indicative of the positions and diameters of the component joining holes. After determining a deviation between the first and second geometric data to be smaller than a predetermined threshold, the automatic drill is positioned at the correct drilling location and joining holes are drilled into the workpiece. Finally, the component and the workpiece are joined by fasteners.

Abstract: A table arrangement has a mounting element to be fastened to a fastening structure element. A first table element is connected to the mounting element, pivotally relative to the mounting element about a first pivot axis between a stowage position, in which the first table element extends substantially parallel to a mounting plane defined by the mounting element, and a position of use, in which the first table element extends substantially perpendicular to the mounting plane. A second table element is connected to the first table element substantially parallel to the first table element and rotatable relative to the first table element about a rotation axis that is parallel to the mounting plane in the position of use.

Abstract: A storage compartment arrangement for a cabin of a vehicle has a storage compartment, housing, storage compartment opening, lower compartment, and upper compartment. The compartments are directly above each other and separated by an intermediate base pivotable at least in sections into the upper compartment. Items of luggage can be placed onto a lower horizontal pivoting edge and pushed into the lower compartment. Adjacent to a lower delimitation of the upper compartment, when the intermediate base is not pivoted, an upper horizontal pivoting edge is formed, onto which items of luggage can be placed and pushed into the upper compartment. The upper compartment has an upper opening edge adjoined by an auxiliary surface extending over the upper compartment, is at an angle in a range of 10° to 50° to the intermediate base and, as the distance from the upper delimitation increases, encloses an increasing distance from the intermediate base.

Abstract: A wing for an aircraft is disclosed having a fixed wing, a foldable wing tip portion and a flight latch device for latching the foldable wing tip portion in the extended position, wherein the flight latch device includes a housing, a latch bolt, and a motor for driving the latch bolt between the latched and unlatched positions. A flight latch device includes a threaded shaft rotationally driven by the motor, a nut engaging the shaft, so that the nut can rotate relative to the shaft, the nut is connected to the housing via a linear guide and is connected to the latch bolt for common linear movement with the latch bolt, and the flight latch device includes an offset compensation, providing that the shaft is supported pivotable relative to the housing and the latch bolt is coupled to the nut via a compensational bearing allowing angular play between the nut and the latch bolt.

Abstract: A line assembly for installation in an aircraft fuselage includes a first line section having a first diameter, a second line section having a second diameter, a set of first line brackets, and a set of second line brackets. The first line brackets include a first receiving space configured to hold the first line section and a first support portion for attaching the first line brackets to a fuselage structural part. The second line brackets include a second receiving space configured to hold the second line section and a second support portion for attaching the second line brackets to the first line section. The second line section includes a higher flexibility than the first line section. The second line section is attached to the first line section through a plurality of second line brackets arranged at a distance to and independent from the first line brackets.

Abstract: A device for latching a door of an oxygen mask container in an aircraft cabin includes a door for an oxygen mask container having an inner side, outer side and hinge, a first latching device attached to the inner side, and a second latching device movable relative to the first latching device to selectively engage or disengage the second latching device. A retaining element is attachable to a structural part inside the oxygen mask container. A test control device on the inner side of the door includes a movable hook element and can move the hook element to a first or second position. The hook element can engage the retaining element in the first position to restrict an opening degree of the door. The hook element is placed in the second position such that when the door is opened, the hook element is moved past the retaining element.

Abstract: An expansion tank system for a liquid cooling system includes a first chamber for receiving a coolant, a second chamber for pressurized gas, a first gas conveying device for conveying gas from the first to the second chamber, a second gas conveying device for conveying gas from the second to the first chamber, a first pressure sensor in fluid communication with the first chamber, and a control unit connected to the first gas conveying device, the second gas conveying device and the first pressure sensor for controlling the second conveying device to selectively convey gas from the second to the first chamber if a pressure measured through the first pressure sensor is below a predefined first threshold value, and for controlling the first conveying device to convey gas from the first to the second chamber if a pressure measured through the first pressure sensor is above a second threshold value.

Abstract: A piccolo tube for de-icing an airfoil structure of an aircraft is disclosed having a shape extending in a longitudinal direction and is configured for installation in an airfoil structure of an aircraft in the longitudinal direction of the airfoil structure. The piccolo tube includes a connector element for receiving heated air from a supply source, and a longitudinally extending air duct having a plurality of outlet openings arranged along the air duct, for supplying and distributing the heated air along the inner side of the airfoil structure. The piccolo tube is curved and its curvature is adapted to a curvature of the airfoil structure in its longitudinal direction. A de-icing system includes the piccolo tube and a supply source for supplying heated air to the piccolo tube. An airfoil structure includes the piccolo tube and/or the de-icing system.