Abstract: A wing tip device for fixing to the outboard end of a wing, the wing defining a wing plane, the wing tip device comprising: an upper wing-like element projecting upwardly with respect to the wing plane and having a trailing edge; and a lower wing-like element fixed with respect to the upper wing-like element and having a root chord and a trailing edge, the lower wing-like element root chord intersecting with the upper wing-like element, and the lower wing-like element projecting downwardly from the intersection, wherein the upper wing-like element is larger than the lower wing-like element and the trailing edge of the lower wing-like element is adjacent the trailing edge of the upper wing-like element at the intersection, and wherein an included angle between the upper and lower wing-like elements at the intersection is less than, or equal to, 160 degrees.

Abstract: A sealing assembly is provided in an airframe of aircraft. The sealing assembly includes, but is not limited to a resilient and yet stiff enough bellows body that is attachable to the fuselage of the aircraft and is further attachable to a center wing box of the aircraft. The sealing assembly seals off a gap between the fuselage and the center wing box so as to allow maintaining pressure in the fuselage if the fuselage is pressurized. The bellows body is a composite and is designed to sustain exposure to tear and wear and exposure to a high and low temperatures as well as exposure to chemicals used during operation of the aircraft.

Abstract: A door system for an aircraft or spacecraft having a door and an actuator for actuating the door. The actuator includes an actuator drive which moves the door in relation to the aircraft or spacecraft, a detection device which determines movement information of the door and/or of the actuator, an actuator control unit which controls the actuator based on the movement information, and an actuator housing which surrounds the actuator drive and the actuator control unit.

Abstract: An installation assembly for bridging a cable harness between two aircraft structure elements of an aircraft is provided. The installation assembly includes an elongated connecting rod having two end sections for attaching the connecting rod onto two adjacent aircraft structure elements, at least one cable guidance element having at least one receiving section for receiving a cable harness and an attachment section for circumferentially surrounding the connecting rod. Locking means are provided to form a connection between the attachment section and the connecting rod, wherein a polygonal cross section of the connecting rod corresponds to a recess of the attachment section in order to form a positive locking engagement between the cable guidance element and the connecting rod.

Abstract: A cabin attendant seat for an aircraft, a seat system comprising such a cabin attendant seat, an aircraft monument comprising such a cabin attendant seat and an aircraft comprising such an aircraft monument. The cabin attendant seat comprises a backrest element and a seat element. The cabin attendant seat is movable from a starting position into at least one end position. The cabin attendant seat further comprises an adapter element, the adapter element being arranged in the cabin attendant seat and configured to connect the cabin attendant seat, in the at least one end position, to an aircraft seat provided in the aircraft.

Abstract: A mounting system (10) for attaching a box (14) in a compartment (12) of an aircraft galley comprises a first guide device set up for engaging with a complementary second guide device designed on the box (14) when the box (14) is inserted into the compartment (12) of the aircraft galley, and further set up for securing the box (14) against movement in the compartment (12) of the aircraft galley in a direction (P) perpendicular to a longitudinal axis (L) of the compartment (12) of the aircraft galley when the device is engaged with the complementary second guide device designed on the box (14). The mounting system (10) further comprises a locking mechanism set up for securing the box (14) against movement in the compartment (12) of the aircraft galley in a direction parallel to the longitudinal axis (L) of the compartment (12) of the aircraft galley.

Abstract: A tank system for the cryogenic storage of hydrogen includes a tank structure with at least one hollow body for accommodating liquid hydrogen and at least one insulating means, which encloses the tank structure, for insulating the at least one hollow body. The tank structure has an exterior shape that is integrateable in a load-bearing primary structure of an aircraft. The tank structure is load bearing and is designed to at least partially absorb a load introduced into the primary structure. This makes it possible to achieve a particularly efficient design of an aircraft in which the fuselage of the aircraft is not divided into two parts by the hydrogen tank integrated therein, can be arranged near the center of gravity, and essentially does not increase the additional weight of the aircraft.

Abstract: The present disclosure relates to a flight recorder, having a memory, a control device, which is coupled to the memory and which is configured to record flight data during the flight of an aircraft and to store said flight data in the memory, a transceiver device, which is coupled to the control device and which is configured to accept stored flight data signals from the control device and to convert them into acoustic signals, and an acoustic transducer, which is coupled to the transceiver device and which is configured to emit the acoustic signals of the transceiver device into a body of water, the control device being configured to receive control signals via the transceiver device and, depending on the control signals, to retrieve partial data areas of the stored flight data from the memory and to transfer them to the transceiver device.

Abstract: A wing tip device for fixing to the outboard end of a wing, the wing defining a wing plane, the wing tip device comprising: an upper wing-like element projecting upwardly with respect to the wing plane and having a trailing edge; and a lower wing-like element fixed with respect to the upper wing-like element and having a root chord and a trailing edge, the lower wing-like element root chord intersecting with the upper wing-like element, and the lower wing-like element projecting downwardly from the intersection, wherein the upper wing-like element is larger than the lower wing-like element and the trailing edge of the lower wing-like element is adjacent the trailing edge of the upper wing-like element at the intersection, and wherein an included angle between the upper and lower wing-like elements at the intersection is less than, or equal to, 160 degrees.

Abstract: An insulation arrangement for thermally and acoustically insulating an aircraft fuselage, which comprises at least one insulation packet arranged on an exterior skin of the aircraft. The insulation packet includes dimensionally rigid foam, and comprises a shape corresponding at least with a structural component on the exterior skin, as the result of which the insulation packet is retained on the structural component even without any additional attachment elements. As a result, ventilation openings need not be provided, thereby reducing condensation water accumulating in aircraft insulation.

Abstract: A lift arrangement for an aircraft includes an aircraft fuselage section with an outside, an aerodynamic lift body attached to the aircraft fuselage section and extending from the aircraft fuselage section outwardly, and a pair of movably held add-on bodies arranged upstream of a leading edge of the aerodynamic lift body. The add-on bodies include an aerodynamically effective surface and are equipped with incoming airflow to generate vortices that impinge on the aerodynamic lift body, thus leading to an increase in lift on the aerodynamic lift body. Thus the lift generation on a lift body is effectively influenced, in particular to compensate for loss of lift as a result of icing. The add-on bodies are moveable, and, can be moved to a neutral position in which they do not project into the flow around the aircraft, and are thus not effective from the point of view of fluid dynamics.

Abstract: An air-sucking vehicle tail section component or wing section component includes an outer delimitation part having microperforation including boreholes, and inner delimitation part having a plurality of suction boreholes including fluid connections to the microperforation boreholes, and connecting elements. The inner delimitation part is connected via the connecting elements to the outer delimitation part. The outer delimitation part includes a continuously curved shape. The inner delimitation part includes two or more planar inner delimitation part components, which are each connected to one another at one edge to form a connection edge, and the connection edge is configured to be attached to the outer delimitation part. A type of framework structure is thus provided, which causes increased stability and can split impacting objects in particular if two inner delimitation part components are used on the vehicle tail section component or wing section component.

Abstract: A flow body for an aircraft with a leading edge and a trailing edge includes a first spar, a second spar, and an external skin that spans from the leading edge to the trailing edge and on both sides rests on the spars. At least one of the first spar and the second spar includes a web and two spaced-apart flanges that enclose the web, on which flanges the skin that spans the respective spar is arranged. At least one of the first spar and the second spar includes at least one load introduction fin that forms an integral component with the web and extends outwards by way of one of the flanges and the skin that rests on the spars.

Abstract: A contact sealing ring includes an electrically conductive annular disc which has a central through-opening, a first electrically conductive contact formation which protrudes from a first side of the annular disc, and a second electrically conductive contact formation which protrudes from a second side, opposite the first side, of the annular disc.

Abstract: An elongated supporting pillar for a high-strength structural component is designed to absorb bending forces that act transversely to a longitudinal direction of extension of the supporting pillar. The supporting pillar comprises a wall which at least partially encloses an elongated cavity of the supporting pillar. A reinforcement structure is arranged within the cavity and transversely to the direction of longitudinal extension in such a manner that the reinforcement structure can absorb at least some of the bending forces. The reinforcement structure is designed integrally with the wall, wherein both the wall and the reinforcement structure comprise a meltable material. The supporting pillar has a conical shape, and wherein a first end of the supporting pillar is wider than a second end of the supporting pillar.

Abstract: A cooling system for cooling food on board an aircraft includes a cooling circuit adapted to supply cooling energy to at least one cooling station, a refrigerant circulating in the cooling circuit selected such that it is convertible at least partially from the liquid to the gaseous state of aggregation on releasing its cooling energy to the at least one cooling station and subsequently convertible back at least partially to the liquid state of aggregation again by an appropriate pressure and temperature control in the cooling circuit, and a refrigerant container including a receiving space arranged in an interior space of the refrigerant container which receives the refrigerant circulating in the cooling circuit, the receiving space of the refrigerant container connected to the cooling circuit by a flow line for discharging the refrigerant from the receiving space and by a return line for returning the refrigerant into the receiving space.

Abstract: In order to provide additional safety measurements for protection on-board a vehicle, a mobile on-board passive protection device for use on-board of a vehicle is provided. The mobile passive protection device comprises side panels and a top and a bottom panel, which panels are enclosing at least one stowage compartment, a plurality of castors for providing movability on-board a vehicle, and a support structure for connecting the castors and the panels. At least one of the side panels is provided with a bullet-protection layer.

Abstract: Method for manufacturing a dry textile preform, including: pulling a textile fabric sheet; grabbing a first side portion of the sheet between rollers, the rollers forming a first flange of the first side portion of the sheet inclined at a predeterminable angle to the plane of extension of the sheet; grabbing a second side portion of the sheet opposite to the first side portion between other rollers, the other rollers forming a second flange of the second side portion of the sheet inclined at a predeterminable angle to the plane of extension of the sheet; adjusting a difference between the rolling speed of the pair of first rollers and the rolling speed of the pair of second rollers to form a curvature radius of the sheet; and adjusting distance between the rollers perpendicular to the movement direction of the sheet to form a web portion between the first flange.

Abstract: The invention relates to a method of connecting two fuselage sections (1, 2, 21, 22) formed by a fiber-reinforced plastics material, in particular wound fuselage sections (1, 2, 21, 22) for aircraft fuselage cells, having a multiplicity of stringers (10, 11, 35, 36) arranged with a uniform distribution at a distance from and parallel to one another on the inner side of an outer skin (3, 4, 25, 26), with the formation of a transverse joint (5, 30).

Abstract: A method for manufacturing a load bearing structure involves providing a panel; providing a first set of split stiffening elements on a surface of the panel, wherein the split stiffening elements of the first set have bottom surfaces and central portions with open top clearances, respectively, spaced apart from each other; providing a second set of stiffening elements having bottom surfaces and top surfaces and central portions, respectively; inserting the stiffening elements of the second set into respective open top clearances of the split stiffening elements of the first set and providing the second set of stiffening elements on the surface of the panel for forming a grate structure; and attaching top surfaces to the split stiffening elements of the first set for forming complete profiles.