Abstract: A high lift system for an aircraft includes: a main wing, a flap disposed on the main wing of the aircraft that can be adjusted between a retracted position and several extended positions relative to the main wing by means of flap actuating means and a drive device, said system further comprising a carrier part disposed on the main wing to which the flap actuating means are coupled and relative to which the flap actuating means for adjusting the flap can be moved, wherein the carrier part is disposed on the main wing by means of a bearing device comprising an adjusting device with which the orientation of the carrier part relative to the orientation of the main wing can be adjusted.

Abstract: The invention relates to a method for producing a component for connecting a fuselage cell skin to an annular rib of an aircraft, wherein the component is formed by bending of a flat blank along at last two edge lines and wherein the blank is formed by a CFRP. According to the invention the interlaminar sliding of the fiber layers is largely completed in a first forming step, while in a second forming step a consolidation of the component takes place by the use of pressure from the press on all sides by means of an upper tool and a lower tool. This enables complex components with at least two edge lines to be produced, which edge lines run at angles of approximately, preferably at angles of 309° to 90°, to each other, and which edge lines also lie in at least two different planes.

Abstract: Disclosed is a method for producing a releasable seal with a sealing compound between two fairing parts, in particular between two fairing parts for the wing-fuselage fillet of aircraft, including the steps of applying adhesive strips to respectively opposite edges, of the fairing parts and outer surfaces adjacent to them of the fairing parts; filling a sealing joint extending between the opposite edges with the sealing compound; and removing the adhesive strips after the curing of the sealing compound. This makes it possible to provide a re-releasable seal with a sealing compound which is curable or cures on its own in air between two fairing parts without the use of release agents. Also disclosed is the use of adhesive strips for carrying out this method.

Abstract: The invention relates to an improved aircraft electronics cooling system for an aircraft having a liquid cooling system (2), the aircraft electronics cooling system providing a thermal coupling between an electronic device (40a, 40b, 40c, 40d, 42, 44) to be cooled and the liquid cooling system (2) of the aircraft. A coolant delivered by the liquid cooling system (2) may flow through a board of the electronic device (40a, 40b, 40c, 40d), through a heat sink on which the electronic device (42) is arranged and/or through a housing in which the electronic device (44) is arranged. The coolant may be permanently in the liquid state in a cooling circuit. The coolant may vaporize at least partially while cooling the electronic device.

Abstract: Disclosed is a method for producing single- or multi-layered fiber performs by the TFP process with fiber strands which are aligned substantially such that they are oriented with the flux of force, are laid on at least one backing layer and are attached by at least one fixing thread. After completion of the TFP process, at least one fiber preform is introduced into a fixing device to secure the position of the fiber strands and the fixing threads and/or the backing layers are at least partially removed. As a result of the preferably complete removal of the fixing threads and/or the backing layer from the fiber preform, the latter has virtually ideal mechanical, quasi isotropic properties. In a preferred variant, the fixing threads and/or the backing layers are formed by a water-soluble material, so that they can be completely dissolved by water as the solvent and flushed out.

Abstract: The invention concerns a method of dimensioning and producing stiffened structural components (4) comprising at least one shell component (6) and at least one stiffening component (8) which can be connected thereto, in which the shell component (6) and the at least one stiffening component (8) is dimensioned on the assumption of intactness of the at least one stiffening component and having regard to a predetermined safety factor and/or a predetermined structural inspection interval in which a predetermined maximum crack progression in the shell component is not to be exceeded and/or the strength of the structural component is not to fall below a predetermined minimum residual strength, and in which the at least one stiffening element (8) of the structural component dimensioned by this method is equipped with at least one structural condition sensor (30) for detecting intactness; as well as the use of structural condition sensors in an aircraft, in particular a passenger aircraft.

Abstract: Pultrusion methods and apparatus for manufacturing a profiled preform or FRP-component with cross-sectional segments that extend angularly to one another from a plurality of semifinished products in a quasi-continuous process, where: at least one multilayer semifinished product arrangement [of a multilayer semifinished product arrangement] is dispensed from a dispenser unit in order to manufacture the preform, with the multilayer semifinished product arrangement dispensed from the dispenser unit being fed to the forming device and including a combination of several webs of semifinished reinforcement fiber layers and at least one resin film; the semifinished product arrangement is guided through a forming device and at least one cross-sectional segment of the semifinished product arrangement is angled in order to form an angle profile, with the semifinished product arrangement being compressed in a pressing device, optionally after a hardening process, and with a longitudinal section of the preform or the comp

Abstract: An aircraft featuring: a fuselage with a fuselage section, an energy supply device, at least two supporting devices that are arranged on the fuselage section and serve for fastening the energy supply device, a mounting device for mounting an energy supply device on a structural component of an aircraft and an aircraft with a mounting device, as well as to a mounting device for mounting an energy supply device on a structural component of an aircraft and to an aircraft with a mounting device.

Abstract: The invention concerns a method for manufacturing a shell, in particular a fuselage shell, a wing shell, a horizontal stabilizer shell or a vertical stabilizer shell, that is reinforced with a plurality of stiffening elements, for forming component parts for aircraft with high dimensional stability, wherein the stiffening elements and a shell skin are made with epoxy resin from at least partially cured carbon fiber reinforced semi-finished parts, the method comprising the following steps: positioning the stiffening elements on the shell skin, abutting connecting elements against the shell skin and the stiffening elements, and curing the connecting elements to form the shell. The invention also concerns a shell, in particular a fuselage shell, a wing shell, a horizontal stabilizer shell or a vertical stabilizer shell, manufactured in accordance with the inventive method.

Abstract: The present invention relates to a method for detecting a defective sandwich component, particularly in aircraft construction, the method comprising the following steps: forming at least one measuring chamber in a core arrangement of a sandwich component, said at least one measuring chamber having an outwardly open end; subjecting the at least one measuring chamber to a predetermined pressure; and detecting and evaluating the pressure forming in the at least one measuring chamber.

Abstract: An aerodynamic body with an outside with a top and bottom in relation to the direction of airflow, with lateral end parts that form the lateral ends of the aerodynamic body when viewed across the direction of airflow, where in the interior of the aerodynamic body a duct with an airflow drive with a drive motor and a compressor means that is driven by the aforesaid and that is arranged in the duct is arranged, with at least one inlet at the bottom and/or at at least one of the lateral end parts of the aerodynamic body and with at least one outlet at the top of the aerodynamic body for influencing the airflow at the aerodynamic body is arranged, where in the duct a sleeve is arranged which is rotatable by means of a drive motor, which sleeve includes at least one recess which at a particular rotational position of the sleeve can be made to at least in part coincide with the outlet at the top of the aerodynamic body so that the air that has been compressed by the compressor flows through the recess in the sleeve

Abstract: The invention provides a continuous pultrusion process for producing structural profiles wherein a) one or more textile sheets are impregnated with a resin composition comprising a combination of (i) at least one epoxy resin which is a tri- or tetrafunctional epoxy resin and (ii) a curing agent system comprising at least two types of reactive groups of different reactivity b) the impregnated textile sheets are subjected to heat to cause a partial reaction between the at least one epoxy resin and the curing agent system, so that the viscosity of the resin composition is increased, and c) the partially reacted impregnated resin composition is gelled using heat and/or pressure.

Abstract: An air outlet has at least one air supply line and at least one baffle plate, wherein the opening cross section of the air supply line is arranged in a plane running parallel to the baffle plate, the baffle plate has a circumferential contour, and is spaced apart from the air supply line, and the opening cross section of one end of the air supply line is directed toward the baffle plate. Such air outlets are particularly suited for small-volume rest rooms, such as in a vehicle, which require a sufficiently high ventilation quality at the lowest possible draught.

Abstract: An aircraft door includes an outer skin configured as a panel structure; and a rear body structure configured as an integral cast structure and operatively connected to the panel structure so as to provide rigidity.

Abstract: A high-lift system for an aircraft with a main wing and a slat that by means of an adjustment device is adjustable relative to said main wing to various adjustment states, with a gap resulting between the rear of the slat, which rear faces the main wing, and the main wing, wherein the size of the gap results from the adjustment state of the slat relative to the main wing, wherein in the interior of the slat an air guidance channel with at least one inlet and an outlet is formed, wherein the inlet is arranged at the rear, which faces the main wing, in order to influence the airflow in the gap.

Abstract: A conjunction for mounting a cross beam to a structure part of an aircraft fuselage by means of at least one conjunction device wherein the conjunction device defines a circular path on which loads acting on the cross beam are applied in the structure element.

Abstract: A method for tolerance compensation in an overlap joint between a first and a second body section of adjacent fuselage rings includes introducing a plurality of holes into a first body section corresponding to a pattern of rivets; arranging the first and second body section in an overlapping configuration so as to form an overlap; injecting a filler mass through the plurality of holes into a gap formed in the overlap; and hardening the filler mass.

Abstract: The present invention provides a structural component for an aircraft or a space craft having an outer skin and a first reinforcing element which runs on the outer skin along a first spatial direction. A second reinforcing element runs over the first reinforcing element in a second spatial direction. A foot element supports the second reinforcing element on the outer skin, the foot element having a feed-through opening in which the first reinforcing element is held in a positive manner. From another point of view, a method is provided for reinforcing an outer skin of an aircraft or space craft, in which a first reinforcing element is attached to the outer skin along a first spatial direction. A foot element having a feed-through opening is attached over the first reinforcing element such that the first reinforcing element is held positively in the feed-through opening. A second reinforcing element is attached to the foot element in a second spatial direction over the first reinforcing element.

Abstract: The invention relates to a connection 1 between a first component and a second component, the first component being formed from an aluminium alloy in particular and the second component being formed from a carbon-fibre-reinforced plastics material in particular. The first component is a rib 6 in particular and the second component is preferably an angle bracket 7, with which the rib 6 is connected to an aircraft fuselage skin 2 within a fuselage reinforcement structure. The connection 1 between the components comprises, according to the invention, a ceramic coating 16 which is applied for protection against corrosion at least in the region of a contact area 9 between the components, the components being riveted and/or adhesively bonded. The ceramic coating 16 is less than 0.1 mm thick and may be formed from a mixture of aluminium oxide (Al2O3) and TiO2 for example.

Abstract: A method for plasma treatment and painting of a surface, the surface including a plurality of different materials includes blasting the surface with a carbon dioxide snow so as to activate the surface to improve an adhesive strength; and treating the surface with a plasma treatment using at least one plasma nozzle following the blasting step, the treating including guiding the at least one plasma nozzle at a distance of not more than 15 mm from the surface at a feed rate of not more than 50 m/min.