Abstract: A system for manufacturing a kitchen arrangement for a cabin of a vehicle includes a primary module with an electrical energy supply device, a cooling device, and at least one supply connection for supplying the primary module with a requisite. The system also includes at least one auxiliary module that is couplable with the primary module. The cooling device is set up to provide a stream of cooled fluid to a fluid outlet. At least one outer boundary surface of the primary module comprises an electrical connection coupled with the electrical energy supply device and a fluid connection coupled with the fluid outlet. The at least one outer boundary surface is adjusted for coupling with an auxiliary module having a correspondingly shaped boundary surface.

Abstract: An aircraft (1) including a fixed wing (7) and a wing tip device (9) moveably mounted thereon. The wing tip device (9) is movable from a load-alleviating configuration to a flight configuration. The wing tip device includes an airflow channel (88) extending between respective apertures (83, 84) on the upper surface and lower surface of the wing tip device. The channel (88) is configurable between an open state in which air can flow through the channel and a closed state in which the airflow through the channel (88), via the apertures (83, 84), is blocked. The channel (88) is configured such that when the wing tip device (9) is in the load-alleviating configuration and the channel (88) is in the open state, the aerodynamic loading on the wing tip device in flight urges the wing tip device towards the flight configuration.

Abstract: A wing system (2) for an aircraft includes a movable flow body (6) and a cover panel (8), wherein the flow body (6) and the cover panel (8) both are movably supported on a main wing body (4). While the flow body (6) is actively driven into upwards or downwards deflected positions, the cover panel (8) is coupled with the flow body (6) to follow its motion. The cover panel covers a part of the flow body (6) and the main wing body (4) in order to provide a substantially continuous, closed outer contour.

Abstract: A payload module of a stratospheric drone including a casing (10), and payload equipment contained in the casing (10), wherein the casing includes a support structure (12) and a cover (15), the support structure being suitable for attachment to the drone at the front end thereof, relative to the direction of movement of the drone, and for extending forward from said front end, and in that the cover (15) and the payload equipment are supported by the support structure (12).

Abstract: A fastening system for passenger seats in a vehicle cabin has two or more guide rails to be integrated into or onto a cabin floor, and a plurality of slides, to be brought into engagement with the guide rails and having a flange for connection to a passenger seat in order to retain the passenger seat on a guide rail. Each guide rail has a profile cross section, perpendicularly to a main axis of extent, having a base region and a supporting region. Each slide has a cavity of complementary design with the profile cross section. The guide rails have a plurality of transverse openings spaced apart from one another between the base region and the supporting region. At least one slide has a displaceably mounted retaining body which, when the slide is in engagement with the guide rail, can be brought into engagement with one of the transverse openings.

Abstract: A method for determining a distance between components has the steps of providing a first conductive section in or on the first component in a region directed toward the second component, providing a second conductive section in or on the second component in a region directed toward the first conductive section, feeding a first voltage pulse into a first connection of the first conductive section, capturing a reflection voltage pulse in response to the first voltage pulse at the first connection, determining an impedance profile along the first conductive section by evaluating the reflection voltage pulse, and determining a distance between the components along the first conductive section by calculating a corresponding local distance, associated with the determined impedance profile, between the first conductive section and the second conductive section.

Abstract: An aircraft wing subassembly including: a wing skin defining a first outer surface, and, a structural reinforcement member, the structural reinforcement member defining a second outer surface, wherein the structural reinforcement member is arranged within the wing such that the first outer surface and the second outer surface form part of an outer wing surface.

Abstract: A method for testing an arresting unit (15) for locking a foldable wing tip portion (11) to a wing (5) that includes a fixed wing (9), a foldable wing tip portion (11), and a folded position, an actuation unit (13) for actuating movement of the foldable wing tip portion (11), and an arresting unit (15) for locking the foldable wing tip portion (11). The method includes: locking the foldable wing tip portion (11) in the extended position by the arresting unit (15), controlling the actuation unit (13) to move the foldable wing tip portion (11) in the direction towards the folded position, such that the foldable wing tip portion (11) urges against the arresting unit (15) with a predefined test load, detecting deformation of the arresting unit (15) during or after application of the test load, and comparing the detected deformation to a predefined threshold deformation.

Abstract: A wing tip device for attaching to an aircraft wing comprising a first wing tip device element having a root end and a tip end; a second wing tip device element coupled to the tip end of the first wing tip device element; wherein the second wing tip device element has an inboard portion extending inboard from the tip end of the first wing tip device element and/or an outboard portion extending outboard from the tip end of the first wing tip device element, when viewed in the wing planform direction.

Abstract: A processor system comprises a memory having at least two interleaved memory banks, at least two multiplexers which are respectively coupled to one of the at least two interleaved memory banks via a respective memory bank bus, a first processor or processor core which is coupled to first multiplexer inputs of the at least two multiplexers via a first data bus, a second processor or processor core which is coupled to second multiplexer inputs of the at least two multiplexers via a second data bus, and at least two queue buffers which are arranged in the second data bus between the second processor or processor core and the second multiplexer inputs of the at least two multiplexers. The first processor or processor core is configured to have read access or write access only to one of the at least two interleaved memory banks within one clock cycle.

Abstract: A landing gear controller (120) to control extension and retraction of a landing gear for an aircraft, the landing gear controller (120) configured to cause, during an aircraft take-off or landing procedure, a landing gear extension and retraction system (110) to perform only a first portion of a landing gear extension or retraction process, on the basis of a status of the aircraft and prior to receiving a command for the landing gear to be extended or retracted.

Abstract: A forward engine attachment system for an engine of an aircraft, the forward engine attachment system including a jet engine pylon including, in the region of the forward part thereof, a front part having an attachment wall, and a forward engine attachment with a connecting rod system on either side of a median plane, wherein each connecting rod system is fixed in articulated manner by at least one first link point to the attachment wall and is designed to be fixed in an articulated manner by at least one second link point to a forward part of the engine. Such a forward engine attachment system thus includes a direct coupling between the jet engine pylon and the engine, allowing the production of an assembly that is less heavy and is easier to produce.

Abstract: A monitoring system for an aircraft has sensors configured to sense objects around the aircraft and provide data indicative of the sensed objects. The system contains a first type of computing module that processes data obtained from all the sensors and a second type of computing module dedicated to processing data from a particular sensor. The second module may characterize and locate a detected object within the processed image data. Both the first and second modules generate a likelihood of detection of an object within their processed image data. A scheduler module calculates a percentage of computing resources that should be assigned to processing data from a respective image sensor in view of this likelihood and assigns a dedicated compute module to an image sensor requiring a higher percentage of attention. Processing resources may therefore be focused on geospatial areas with a high likelihood of object detection.

Abstract: A primary structure of a strut for bearing an aircraft power plant including a front part intended to be joined to an aircraft power plant and a rear part intended to be joined to a structure of the aircraft, the front part being formed from a box including an upper longitudinal member, a lower longitudinal member, and lateral panels. A main rib is located at an interface between the front part and the rear part. The rear part is formed from a set of four connecting rods. The first end of each connecting rod is joined to the front part of the primary structure and the second end of each connecting rod is joined to a separate interface for fastening to the structure of the aircraft. This allows a substantial simplification of the primary structure of a strut for bearing an aircraft power plant, which can have advantages in particular in terms of cost, mass, and simplicity of implementation and integration.

Abstract: A device for a lacquer transfer includes a transfer roller mounted at and rotatable relative to a frame. The roller includes a cylindrical support-body, first ring-element, second ring-element, and a tire including a middle-section forming a circumferential outer contact surface with depressions, the roller configured to roll with the outer contract surface on a work surface of a workpiece for transferring lacquer from the outer contact surface and the depressions to the work surface. The tire includes two annular end-sections attached to a cylindrical outer shell of the support-body resulting in two axially separated and circumferentially extending connections, the tire, connections, and outer shell of the support-body being fluid-tight. The first and second ring-elements are in the first cavity seated on the support-body at a distance in an axial direction of the roller from one another and the middle-section of the tire between the first and second ring-elements is prestrained in the axial direction.

Abstract: A fastener for holding together two or more structures. The fastener includes a first bush and a second bush. The first bush includes a hollow shaft having a first end and a second end opposite to the first end. The first end of the first bush has a first radially-extending protrusion. The second bush includes a hollow shaft having a first end and a second end opposite to the first end. The first end of the second bush has a second radially-extending protrusion. The second end of the second bush is configured to connect to the second end of the first bush so as to resist separation of the first and second bushes and so as to define an axial hole through the fastener defined by the shaft of the first bush and the shaft of the second bush.

Abstract: A device is specified for producing a flight plan for lightweight aircraft. The device includes a first interface, a second interface, and a processing unit. The first interface is configured to receive aircraft data relating to the lightweight aircraft, wherein the aircraft data at least contain flight properties and functions of the lightweight aircraft. The second interface is configured to receive weather data from a weather information source, wherein the weather data contain at least weather data from the past and contain at least air movements in an altitude profile between a maximum altitude of the lightweight aircraft and the Earth's surface. The processing unit is configured to compare the aircraft data to the weather data and to ascertain whether the lightweight aircraft is manoeuvrable in the case of the received weather data and on the basis of the aircraft data.

Abstract: A tooling device for producing a planar structural component for an aircraft has a moulding tool part with a contour surface for receiving a planar semi-finished product, a heating device for heating the semi-finished product, a film produced from an elastically deformable material and a clamping system with a first clamping device arranged on a first longitudinal side of the contour surface , and a second clamping device arranged on a second longitudinal side of the contour surface located opposite the first longitudinal side. The film is couplable to the clamping devices by the edge regions thereof and, when it is coupled to the clamping devices, covers the contour surface of the moulding tool part. The film is elastically deformable relative to the contour surface by the first and/or the second clamping device to press the semi-finished product in a planar manner against the contour surface for deforming purposes.

Abstract: An actuation unit (15) for actuating a foldable wing tip portion (9) includes a first housing part (19) including a first attachment device (23) configured for attachment to a fixed wing (5), and a second housing part (21) including a second attachment device (25) configured for attachment to a foldable wing tip portion (9). The second housing part (21) is rotatable about a main axis of rotation (35). The second housing part (21) includes a toothed rack (37) having a concave shape and facing the main axis of rotation (35). A drive pinion (39) is supported at the first housing part (19) and engaging the toothed rack (37) for driving the second housing part (21) rotatingly relative to the first housing part (19). The drive pinion (39) is driven by a coupling arrangement (43) that is configured to be coupled to an output (45) of a motor unit (47).

Abstract: A device is specified for ascertaining a movement corridor for lightweight aircraft. The device includes a first interface, a second interface, and a processing unit. The first interface is configured to receive aircraft data relating to the lightweight aircraft, wherein the aircraft data at least contain flight properties and functions of the lightweight aircraft. The second interface is configured to receive weather data from a weather information source, wherein the weather data contain weather predictions and also current weather data and contain at least air movements in an altitude profile between a maximum altitude of the lightweight aircraft and the Earth's surface. The processing unit is configured to compare the aircraft data to the weather data and to ascertain a probable movement corridor of the aircraft.