Abstract: A method of encrypting data, in particular encrypting data in dependence on a user verification confidence level. An encryption algorithm is provided, data is input into the encryption algorithm, along with a public key and an access structure comprising the user verification confidence level. The encryption algorithm is run to output a cypher text of encrypted data, whereby the access structure is embedded into the cypher text such that only an entity satisfying the access structure can decrypt the cypher text.

Abstract: A hydrogen tank for aircraft, including an inner vessel configured to contain hydrogen, first and second outer jacket domes having a semi-spherical shape and first L-shaped ends, a first semi-cylindrical outer jacket established on top of the first and second outer jacket domes, a second semi-cylindrical outer jacket established in the bottom of the first and second outer jacket domes. The first and second semi-cylindrical outer jackets include second L-shaped ends. The first and second L-shaped ends form L-shaped junctions to attach the first and second outer jacket domes to the first and second semi-cylindrical outer jackets.

Abstract: A joining method and assembly for an aircraft. To improve the characteristics or permit hitherto impossible connections between thermoplastic and thermoset components, a multi-material joining method is disclosed in which a thermoplastic connecting region is formed on the thermoplastic component. The connecting region is connected to the thermoset component by interdiffusion. For this purpose, the uncured second component is brought into contact with the connecting region and heat is supplied. An interdiffusion layer is formed which fixedly connects the second component and the connecting region to one another and thus joins the first component to the second component.

Abstract: A multibeam antenna is provided comprising a direct radiating array, DRA, and a reflector arranged to reflect signals radiated from the DRA in a transmission mode and to reflect signals to the DRA in a reception mode. The antenna is a very high throughput satellite (VHTS) antenna providing global coverage with narrow, high gain beams.

Abstract: A handling system for a receptacle space in a vehicle for storage for containers. A linear guide is on an inner wall of the receptacle space. The linear guide guides at least one carrier element in the movement direction of the container, wherein the storage position of the container is provided having the rear wall thereof in the region of the rear wall of the receptacle space. The removal position is provided in the region of an insertion opening, arranged opposite the rear wall. The at least one carrier element is operatively connected to at least one spindle nut of a spindle drive. The container is thus moved linearly from a stowage and storage position to a removal position and vice versa.

Abstract: A measuring device able to be closely attached to an outer wall of a movable or fixed object located in an air flow. The measuring device comprises a flexible envelope having a cavity provided with an opening orifice. At least one optical fiber is provided in the cavity, the opening orifice of which is closed by the wall on which the envelope is applied. In this way, the fiber is positioned as closely as possible to the wall for which measurements are desired.

Abstract: An enclosure containing an inerting gas and at least one liquid to be discharged. This enclosure comprises at least one orifice positioned in its lower part and a liquid discharging system positioned at the orifice. This liquid discharging system is configured to take up a closed state and an open state in which the system allows the liquid to flow towards the outside of the enclosure and includes at least one element that is elastically deformable depending on the pressure inside the enclosure and, depending on its deformation, controls the open or closed state of the liquid discharging system. This solution makes it possible to achieve simple and automatic regulation of the volume of the liquid in the enclosure, without a sensor. An aircraft including at least one such enclosure is also provided.

Abstract: A reinforcing element for a structural profile, in particular for a round, oval or elliptical structural tube, includes a composite structure, which has a hollow-cylindrical, helically wound mesh of fiber strands which form an inner shell surface configured to receive the structural profile, wherein the fiber strands are respectively embedded in a matrix material, which has an electroactive polymer which can be stretched along a longitudinal extent of the fiber strands by application of an electrical voltage, such that the composite structure can be expanded by application of the electrical voltage to introduce the structural profile into the composite structure and can be shrunk by switching off the electrical voltage to fix the structural profile on the shell surface in the composite structure.

Abstract: An aircraft has a first antenna arrangement, a payload and a processing unit. The first antenna arrangement is designed to wirelessly receive electromagnetic signals. The processing unit is coupled to the first antenna arrangement, on the one hand, and to the payload, on the other hand. The processing unit is designed to modulate an electromagnetic signal received by the first antenna arrangement and thereby to generate a first modulated signal and to forward it to the payload. The payload is designed to use the first modulated signal as working signal. A radiofrequency power signal on an uplink is thus remodulated into a payload working signal, such that the payload working signal is able to be used directly by the payload without rectification into a DC voltage.

Abstract: An aircraft includes an active drag control system such as a Laminar Flow Control (LFC) system having a port LFC apparatus and a starboard LFC apparatus. The aircraft has a control system to test how efficiently the LFC system is working by differentially operating the port LFC apparatus and the starboard LFC apparatus, for example by deactivating either LFC apparatus, and measuring the effect on the direction of flight of the aircraft. The control system also can change the direction of the aircraft, and trim the aircraft, by differentially operating the port LFC apparatus and the starboard LFC apparatus.

Abstract: A cabin lining element for an aircraft cabin which is arranged in the interior of an aircraft fuselage structure, having a fuselage structure side and a cabin side. The cabin lining element comprises an electrically contactable heating lacquer layer at least in regions on its fuselage structure side. A rib is provided for an aircraft fuselage structure, having at least one foot portion on the outer skin facing side and a cabin facing side head portion. The rib comprises an electrically contactable heating lacquer layer at least in regions on a side of the head portion facing the cabin. As a result of the heating lacquer layer, it is possible to omit insulation which otherwise surrounds the rib heads and, as a consequence, to enlarge the width of the cabin.

Abstract: An electric propulsion system of an aircraft includes an electrical generator and a cooling device of the electrical generator. It further includes at least one thermoacoustic engine and a heat transfer circuit configured to transport heat dissipated by the electrical generator to the thermoacoustic engine. The cooling device of the electrical generator is at least partially powered by energy from the thermoacoustic engine.

Abstract: A liner segment for a frame bay of a fuel tank structure includes a liner segment base body adapted to float on fuel in the fuel tank structure, a liner segment side wall extending from the liner segment base body, a multitude of drainage holes arranged in the liner segment base body, and adapted to provide a bidirectional fluid connection from an upper side to a bottom side of the liner segment facing the fuel tank structure, a valve, arranged in a cut out of the liner segment and adapted to provide an unidirectional fluid connection from the bottom side of the liner segment to the upper side of the liner segment, such that the unidirectional fluid connection is blocked in the opposite direction, such that a remaining portion of fuel within the fuel tank structure is reduced.

Abstract: An aircraft system includes a support structure, an aerodynamic component, a first coupling unit and a second coupling unit. The first coupling unit includes a first coupling mechanism movably coupling the aerodynamic component to a first coupling point at the support structure, and a second coupling mechanism coupling the aerodynamic component to a second coupling point at the support structure. The first and second coupling points are spatially separated from each other, wherein the first coupling mechanism and the second coupling mechanism interact with each other to enable a rotational movement of the aerodynamic component with respect to the support structure such that, during the rotational movement of the aerodynamic component, a center of rotation of the aerodynamic component is translated from a neutral position to an adjusted position. The second coupling unit pivotably moves the aerodynamic component about a pivot axis at the support structure.

Abstract: An aircraft including a floor positioned above a central wing box and in a front fuselage portion positioned in front of the central wing box. The floor includes at least one rail which has at least first and second rail portions and at least one articulation connecting the first and second rail portions and configured to allow a pivoting movement, about a transverse and horizontal pivot pin, between the connected first and second rail portions. By virtue of this articulation, it is possible to integrate the rails into the floor and not to position them on the floor.

Abstract: An aerial device for a vehicle, particularly an aircraft, includes an aerial arrangement and a lens, which includes a first lens area, made of a first material with a first dielectric constant, overlapping the aerial arrangement and a second lens area, made of a second material with a second dielectric constant, overlapping the first lens area, with the second dielectric constant being smaller than the first dielectric constant, and wherein the second lens area extends in a longitudinal direction and in a curve in respect of a vertical direction oriented transverse to the longitudinal direction.

Abstract: An aircraft propulsion assembly having an engine, a nacelle positioned around the engine, an annular duct delimited by the engine and the nacelle for a bypass flow of cold air, at least one bifurcation passing through the annular duct for connecting the engine and the nacelle and having a leading edge and a primary structure of a pylon housed in the bifurcation and configured to connect the engine to an aircraft wing. The propulsion assembly has at least one heat exchange device including a plate heat exchanger, having a hexagonal longitudinal section and positioned in the bifurcation. According to one configuration, the heat exchanger is a countercurrent heat exchanger.

Abstract: An aircraft barrier system separating, within an aircraft, a secure area from a passenger cabin of the aircraft, comprises a barrier installed inside the passenger cabin and configured to move between an open position and a closed position, a latch mounted to the barrier, and a locking device comprising a latching clamp configured to lock the latch when the barrier is in the closed position. The aircraft barrier system further comprises a release mechanism configured to move the latching clamp from a locking state locking the latch to an unlocking state releasing the latch, wherein the release mechanism is further configured to delay the moving of the latching clamp from the locking state to the unlocking state. Also, an aircraft area and an aircraft having such aircraft barrier system.

Abstract: A device for accommodating and for releasing a payload on an aerial vehicle having a mounting frame for accommodating the payload, a linear mover for positioning in a cavity of the aerial vehicle, the mover having a base and at least one holding element, and a release device on the mounting frame. The mounting frame has a largely planar opening area surrounded by an opening edge, wherein the mover is coupled with the mounting frame on a side of the mounting frame facing away from the opening area by the at least one holding element. The mover can move the mounting frame linearly and vertically to the opening area at a variable distance from the base, and the release device can hold the payload in the mounting frame and release it selectively from the mounting frame, where necessary, via the opening edge and in a direction away from the base.

Abstract: A method for generating a labeled set of images for use in machine learning based stray light characterization for space-related optical systems. The method includes (a) obtaining a set of images simulated for a space-related optical system, wherein the images of the set of images contain stray light simulated for the space-related optical system, (b) for each image of the set of images, identifying one or more clusters of light contained in the respective image and labeling the respective image by the one or more clusters of light, wherein the one or more clusters of light include at least one cluster of stray light, and (c) creating, based on the labeled images of the set of images, a plurality of new labeled images by applying transformations to the labeled images to generate an augmented set of labeled images.