Abstract: The invention relates to a structural component (1) of a flow body, comprising at least one lining shell (B) that carries a main load, said lining shell having a core layer (33) that absorbs shear load and that comprises a plurality of core-layer sections (33a) arranged next to each other in the longitudinal extension of the foam layer, wherein said core-layer sections are connected to each other at the sides lying against each other by a core-layer reinforcement area (37), which extends through the core layer perpendicularly to the longitudinal extension of the core layer (33).

Abstract: An aircraft having an aircraft fuselage that has an outer skin includes an air sucking fuselage component with an outer surface that is perforated at least in some regions, and a suction profile body. The suction profile body is arranged on the outer skin, forms a local bulge in the outer skin, and further includes a suction opening that is arranged at a location at which there is the lowest pressure, for example at a position furthest away from the outer skin. The suction opening is connected to a suction connection of the air sucking fuselage component. In this way laminarization of the flow at the air sucking fuselage component may take place without the use of active air conveying devices.

Abstract: A locking system is disclosed for locking and unlocking a door such as a cockpit door between the cockpit and cabin of an aircraft. The locking system has a door held by hinges on a door frame and movable between an open position and closed position, and at least one closing means that can lock the door when it is in the closed position. The locking system includes a compressed air source that can be coupled to the closing means to move the closing means from an unlocking position to a locking position by supplying compressed air, and at least one venting valve coupled to each of the closing means in order to conduct compressed air away from each closing means when in the open state, in order to move the at least one closing means from the unlocking position to the locking position.

Abstract: A device and a method for exchanging information between at least one operator and a machine which comprises the following components: a display means, which is set up so as to display information from the machine to the at least one operator visually and three-dimensionally; an input means, which is set up so as to detect the position of objects, preferably the position of the fingers of at least one operator, in three-dimensional space in relation to the display means, in a time-resolved manner by optical and/or acoustic and/or electromagnetic measurement methods, and to detect at least one operator input from the detected progression over time in accordance with at least one predetermined criterion and to pass said operator input on to the machine.

Abstract: The invention concerns a reinforcement device for the purpose of reinforcing a main load-bearing covering panel, also a corresponding main load-bearing covering panel, a structural component of a flow body, and also a corresponding flow body. Here the reinforcement device serves the purpose of accommodating and transferring forces and/or stresses in the interior of the covering panel. In accordance with the present invention, in addition to forces and/or stress in the normal direction, forces and/or stresses in a crosswise direction, that is to say, for example, transverse stresses and/or shear stresses, can also be accommodated and transferred.

Abstract: A device for manually painting a large surface using a spray gun connected to a paint feed line for the supply of an enamel paint and to a pressure line for the provision of compressed air. After the manual actuation of an operating switch arranged on a handle piece, the spray gun sprays the enamel paint by compressed air via a spray head to apply the enamel paint onto the surface. The spray gun includes means such that it can be moved manually along the surface. The means include an extension rod, at one end of which the spray gun is attached by the handle piece and which is configured such that, when held by an operator on an arm holder configured at the opposite end, it extends from the elbow along the forearm of the operator and beyond the distal end of the forearm.

Abstract: A structural component for an aircraft or spacecraft having an outer skin, comprising at least one former element for reinforcing the outer skin. The former element is arcuately curved in accordance with an inner contour of the outer skin 10, wherein the former element has a plurality of first cutouts for receiving longitudinal reinforcements and at least one second cutout, which is configured between adjacent first cutouts of one or more former elements. The invention furthermore relates to an aircraft or spacecraft with the structural component according to the invention.

Abstract: An aerodynamic body with at least one ancillary flap on the aerodynamic body so it can be moved with a guide mechanism, and with a drive device for actuating the ancillary flap. The guide mechanism has a connecting lever, which at its first end is articulated on the aerodynamic body by a first pivotal articulation, and which at its second end is articulated on the ancillary flap by a second pivotal articulation. The second pivotal articulation is located at some distance from a trailing edge of the ancillary flap, and from a leading edge of the ancillary flap. The guide mechanism has an actuation element, which is coupled with the drive device. The actuation element is articulated on the ancillary flap by a third pivotal articulation. The third pivotal articulation is arranged such that it can be moved in the chordwise direction of the aerodynamic body.

Abstract: A compound engine for a means of transportation, includes a diesel engine and a gas turbine with at least one compressor and with at least one turbine. The diesel engine and the gas turbine are interconnected in such a manner that during continuous duty operation the compound engine is configured to be operated only by way of the diesel engine, and the diesel engine is optionally operated on its own or together with a compressor and a turbine of the gas turbine as a turbocharger for the diesel engine. The compound engine is configured to be operated by way of the diesel engine or the gas turbine.

Abstract: An earth connection for electrically and mechanically connecting a plurality of earth wires to a structure, in particular to an aircraft structure, comprising an angled element which element is formed in one piece and is made of electrically conductive material, which comprises a first and a second fastening portion. The first fastening portion is fastened to the structure and the second fastening portion comprises a plurality of electrical connections for connecting the earth wires. The electrical connections comprise socket contact elements which are formed so as to receive pin contact elements of the earth wires.

Abstract: A process for connecting two aircraft fuselage segments and a reinforcing profile arranged in the joint region of the two aircraft fuselage segments by friction twist welding using a rotating tool, wherein a cover plate is brought onto the aircraft fuselage segments to be connected above the joint regions and after the friction twist welding the remainder of the cover plate is milled off. This makes it possible to overcome significantly greater gap tolerances in the edges to be connected so that the dimension tolerance requirements for the aircraft fuselage segments can be reduced. Furthermore, a smooth surface can be achieved in the welding region.

Abstract: An emergency supply system for a transportation means is provided. The system includes at least one fuel cell, a hydrogen tank, an oxygen tank, an extinguishing agent container, an oxidant supply unit and an extinguishing-agent supply unit. The oxidant supply unit includes an oxygen inlet connectable to the oxygen tank, an air inlet connectable to an air source, and an oxidant outlet connected to an oxidant inlet of the fuel cell. The oxidant supply unit either conveys oxygen from the oxygen inlet or air from the air inlet to the oxidant outlet. The extinguishing-agent supply unit includes a first extinguishing agent inlet connected to an exhaust air outlet of the fuel cell, a second extinguishing agent inlet connected to the extinguishing agent container, and an extinguishing agent outlet that is connectable to an extinguishing-agent inlet unit of at least one space of the transportation means.

Abstract: The invention relates to an auxiliary flap arrangement for modifying the profile of an aerodynamic body, in particular the trailing edge of the aerodynamic body. The auxiliary flap arrangement here exhibits at least two auxiliary flaps that can be adjusted by an adjustment device while coupled to each other.

Abstract: A method for the joining of moulded components with a punching, stamping rivet, wherein a punched hole is radially widened in at least certain sections of the moulded components that are to be punched. A punching, stamping rivet is provided which has a deforming section that has a greater external diameter than a punching section.

Abstract: An icing protection system comprises a fuel cell, an evaporative cooling system, a thermal deicing device, a control unit and a device for measuring the pressure in the evaporative cooling system. The evaporative cooling system is in thermal contact with the fuel cell and with the thermal deicing device in order to conduct heat from the fuel cell to the thermal deicing device. The control unit controls the electrical power demanded from the evaporatively cooled fuel cell in dependence on a deviation of the pressure measured by the pressure measuring device from a predetermined NOMINAL pressure. In this way, an energetically very efficient and very well controllable icing protection system is made available that can be operated without bleed air supplied by engines or electrical energy provided by engine generators.

Abstract: An interior component carrier system for use in assembly of aircraft interior components in an aircraft includes a retaining system with at least one retaining element. A first connection device for connecting the retaining element to a first aircraft interior component and a second connection device are provided on the retaining element. On the retaining element a structural retainer is provided for fastening the retaining element to an aircraft structure. The interior component carrier system includes a hinge connectable to a second and a third aircraft interior component such that the third aircraft interior component is pivotable about a longitudinal axis of the hinge relative to the second aircraft interior component. The second connection device mounted on the retaining element is configured to be connected to the hinge and/or to a region of the second or third aircraft interior component, that is adjacent to the hinge.

Abstract: A method and computer program product for planning a landing approach of an aircraft based on an actual position or first nominal position of the aircraft during its approach for landing on a runway, including providing a stabilization flight path section and stabilization region and/or stabilization point defined by an altitude profile by at least one configuration change point in the stabilization flight path section with a change of the overall profile configuration of the airfoils and with a predetermined final approach flight status of the aircraft, and checking or changing position of the at least one configuration change measure in a change and/or the addition of an additional configuration change measure to the stabilization flight path section and by changing a speed profile along the stabilization flight path section so that the aircraft reaches the predetermined final approach flight status in the stabilization region or at the stabilization point.

Abstract: An air conditioning system in an aircraft is provided. The system comprises at least one air cycle air-conditioning pack with a compressor comprising a bleed air outlet and with a compressed-air line connected to the bleed air connection, which compressed-air line is connectable to a starter turbine for a main engine. With the use of air from a compressor of an air conditioning pack it is not necessary to switch off the air conditioning pack; bleed air removal from the auxiliary power units becomes obsolete; and, since there is no unnecessary discharge of compressed air from a bleed air system, noise pollution on the ground is reduced.

Abstract: The invention relates to a method for producing a fiber composite workpiece. In the method according to the invention, cross-linking silicone is used with the aid of a volatile diluent for infiltrating individual mats of a mat composite. A further object of the present invention is a device for performing the method according to the invention.

Abstract: The invention relates to a device for producing an inert gas that comprises a fuel tank for a fuel, at least one fuel cell with a cathode, an anode, a reactor for reforming fuel from the fuel tank into a hydrogenous fuel gas and an inert gas outlet. The reactor comprises a fuel gas outlet that is connected to a fuel gas inlet arranged on the anode of the fuel cell. The inert gas outlet is arranged downstream of the reactor and forms a fluid sink for non-hydrogenous reaction products of the reactor.