Abstract: A device and a method for manufacturing a fiber-reinforced fuselage shell for an aircraft, which fuselage shell for the purpose of reinforcement comprises several stringers that are spaced apart from each other, wherein the device includes a base frame comprising several supporting walls of different lengths for forming a curved mounting surface for the fuselage shell to be manufactured, wherein several actuators that extend radially outwards and that are longitudinally adjustable are affixed to the mounting surface, at the distal ends of which actuators in each case mold channels for receiving the stringers are attached, which mold channels are interconnected by means of flexible intermediate elements and/or further mold channels for forming a vacuum-tight closed mold surface.

Abstract: A vacuum set-up to pressurize a component part during its production is provided. The set-up includes a base with a contact surface for component part, and a casing that is airtight to contact surface that can be sealed to cover component part to effect pressurization of component part by evacuating an internal space of casing. To also effect a defined pressurization of component part on at least one component part edge in lateral direction, on at least this component part edge together with component part, a pressure strip system that can be mounted in the interior space is provided that is formed by at least two pressure strips extending along the component part edge and over inclined planes, that work together in such a way that pressure exerted on pressure strip system by the evacuation of the interior space, generates pressure acting laterally on component part edge.

Abstract: A non-destructive determination of material characteristics of an aircraft component is provided. To provide a simple determination of material characteristics, which can be implemented economically, it is provided to make available image data of a layer, which can be detected from outside using electromagnetic radiation, of a workpiece to be examined; to detect first areas having a first pixel characteristic using the image data; and to detect second areas having a second pixel characteristic using the image data; the first pixel characteristic being associated with a fiber inlay of a fiber composite layer; and the second pixel characteristic being associated with an at least part-crystalline thermoplastic polymer of the fiber composite layer, which thermoplastic polymer is in a crystalline state; and to determine a relationship of the first areas to the second areas.

Abstract: A method for stabilising a honeycomb core for a sandwich-type structural component includes configuring the honeycomb core. A hardenable adhesive layer is applied to at least one exterior surface of the honeycomb core. A semi-permeable membrane is positioned on the at least one exterior surface. The membrane is gas-permeable and liquid-impermeable. Air in the honeycomb core is drawn off through the semi-permeable membrane. The adhesive layer is hardened.

Abstract: A draping device for draping a two-dimensional textile semi-finished product includes a first rotationally symmetrical body having a first axis of rotation and a peripheral surface which varies along the axis of rotation. A first drive is configured to rotate the first body about the first axis of rotation so as to deform, via the first body, the semi-finished product.

Abstract: A connecting element includes a first leg, a second leg and a third leg that are connected to each other and are each disposed at an angle to each other. The first leg includes a first fastening section and the second leg includes a second fastening section. A bending edge is disposed between the first leg and the second leg. The first leg includes at least one supporting section adjacent to the first section in a direction parallel to the bending edge, with the supporting section being connected to the second leg. The second leg forms an extension part in the first direction that is adjacent to the second fastening section, has a free end and is longer than the first fastening section of the first leg. The third leg is connected to the first leg and to the second leg.

Abstract: A supporting profiled demerit is configured to support a reinforcing profiled element that is formed from a fiber composite semi-finished product during a curing process of a method for producing a vehicle fuselage component, during which the reinforcing profiled element is bonded to a surface of a fuselage shell that is also formed from a fiber composite semi-finished product. The supporting profiled element includes an air-impermeable profiled hose having two ends and a first end piece that is detachably inserted at a first of the two ends of the profiled hose so as to form an insertion connection. The first end piece is sealed against the profiled hose by the insertion connection.

Abstract: An aircraft fuselage has an integrated energy-absorbing deformation structure. The fuselage includes annular frames, longitudinal fuselage beams interconnecting the annular frames, and a covering forming a fuselage skin. A lower floor structure is disposed in an interior of the fuselage. The lower floor structure includes a plurality of transverse beams connected to an assigned frame and longitudinal floor beams which interconnect said transverse beams. The deformation structure is formed in a lower fuselage region disposed below the lower floor structure. The deformation structure includes a first inelastically deformable central region and, on a left-hand side and a right-hand side, respective second inelastically deformable regions of greater stiffness in the vertical direction than the central region.

Abstract: A method for producing a composite molded part from fiber-reinforced plastics material includes providing a prepreg semi-finished product including fibers that are pre-impregnated with a matrix material and encasing the semi-finished product with a flexible sheet material to form an inner arrangement. The flexible sheet material includes a gas-permeable membrane and an inner planar gas-conducting element. The inner arrangement is encased with a first gas-tight casing and positioned on a molding surface of a mold. The inner arrangement and molding surface is encased with a second gas-tight casing. A first negative pressure is applied to the inner planar gas-conducting element and the inside of the first gas-tight casing, and the entire arrangement is heated for a first time at a first temperature. A second negative pressure is applied to an inside of the second gas-tight casing and the entire arrangement is heated for a second time at a second temperature.

Abstract: An aircraft comprising includes a fuselage shell with fuselage frames, a floor structure with transverse and longitudinal beams, and a fastening arrangement for supporting the floor structure on the fuselage shell. The fastening arrangement includes first bars each connecting an end of a transverse beam to a fuselage frame so as to transfer forces extending in a transverse direction between the floor structure and the shell. Second bars each connect an end of a transverse beam to a fuselage frame so as to transfer forces in a longitudinal direction between the floor structure and the fuselage shell. Third bars disposed beneath the floor structure transfer forces extending in a. vertical direction between the floor structure and the fuselage shell. Fourth bars each connect an end of a transverse beam to a fuselage frame so as to transfer forces extending in the vertical direction between the floor structure and the shell.

Abstract: A method for producing a component with at least one hollow profile from a fiber composite material includes producing a component blank from the fiber composite material. The component blank includes a hollow profile with open ends. The component blank is thermally treated. Each open end of the hollow profile is closed with a stopper that includes at least an outer circumference of a closed-pore foam. The thermally treated component blank is tested using ultrasound in accordance with a non-destructive material-testing method. The component blank is then mechanically treated so as to obtain a finished component and the stoppers are removed. Alternatively, the component blank is mechanically treated to obtain the finished product before the ultrasound testing.

Abstract: A method of heating a thermoplastic board by heat conduction in a heating system which has at least a first surface contacting tool and a second surface containing tool spaced from the first tool, at least one of which is heatable. The thermoplastic board is placed into the heating system between the two surface contacting tools, with an auxiliary sheet being placed between the contact surface of the respective heatable surface contacting tool and the surface of the thermoplastic board facing it. The space between the two surface contacting tools is then reduced to a predefined gap measurement, and the heatable surface contacting tool or tools is heated.

Abstract: A device and a method for manufacturing a fiber-reinforced fuselage shell for an aircraft, which fuselage shell for the purpose of reinforcement comprises several stringers that are spaced apart from each other, wherein the device includes a base frame comprising several supporting walls of different lengths for forming a curved mounting surface for the fuselage shell to be manufactured, wherein several actuators that extend radially outwards and that are longitudinally adjustable are affixed to the mounting surface, at the distal ends of which actuators in each case mold channels for receiving the stringers are attached, which mold channels are interconnected by means of flexible intermediate elements and/or further mold channels for forming a vacuum-tight closed mold surface.

Abstract: A non-destructive determination of material characteristics of an aircraft component is provided. To provide a simple determination of material characteristics, which can be implemented economically, it is provided to make available image data of a layer, which can be detected from outside using electromagnetic radiation, of a workpiece to be examined; to detect first areas having a first pixel characteristic using the image data; and to detect second areas having a second pixel characteristic using the image data; the first pixel characteristic being associated with a fiber inlay of a fiber composite layer; and the second pixel characteristic being associated with an at least part-crystalline thermoplastic polymer of the fiber composite layer, which thermoplastic polymer is in a crystalline state; and to determine a relationship of the first areas to the second areas.

Abstract: A draping device for draping a two-dimensional textile semi-finished product includes a first rotationally symmetrical body having a first axis of rotation and a peripheral surface which varies along the axis of rotation. A first drive is configured to rotate the first body about the first axis of rotation so as to deform, via the first body, the semi-finished product.

Abstract: A semi-finished textile for producing a fiber composite component part has a textile structure and a fixation structure so as to provide a semi-finished textile that can be easily handled and that is suitable for use in complex component part shapes. The textile structure includes a first multitude of reinforcement-fiber bundles of high-performance fibers. Displacement sections are formed between adjacent reinforcement-fiber bundles and adjacent reinforcement-fiber bundles can be displaced against each other. The fixation structure fixates the reinforcement-fiber bundles, depending on the textile structure, with a fixation pattern in such a way that the reinforcement-fiber bundles are fixated at least partially and the displacement sections remain at least partially free.

Abstract: A method for creating a vacuum setup for processing a semi-finished fiber composite into a cured fiber composite component is provided. The semi-finished fiber composite is positioned on a molding surface of a tool so that a non-planar surface of the semi-finished fiber composite faces away from the molding surface, covering the non-planar surface of the semi-finished fiber composite by applying an air-tight film and sealing the film with respect to the molding surface of the tool. Application of the film is performed using a plunger formed from a flexible material and having a plunger surface on which the film is retained.

Abstract: A vacuum set-up to pressurize a component part during its production is provided. The set-up includes a base with a contact surface for component part, and a casing that is airtight to contact surface that can be sealed to cover component part to effect pressurization of component part by evacuating an internal space of casing. To also effect a defined pressurization of component part on at least one component part edge in lateral direction, on at least this component part edge together with component part, a pressure strip system that can be mounted in the interior space is provided that is formed by at least two pressure strips extending along the component part edge and over inclined planes, that work together in such a way that pressure exerted on pressure strip system by the evacuation of the interior space, generates pressure acting laterally on component part edge.

Abstract: A process for producing a hollow profiled component formed by joining at least two laminated component elements, includes the steps of laminating a first of the component elements with at least one indentation, arranging a preformed hollow body in the indentation, applying an adhesive agent to a surface area of the first component element next to the indentation, placing the first component element together with the hollow body on the second component element with the indentation facing the second component element and the surface area provided with the adhesive agent contacting the second component element, covering the two component elements with a non-rigid fluid-tight covering, the interior of the hollow body being sealed off from the interior of the covering and being fluidically connected with the ambient exterior environment, placing the covered component elements in a pressure chamber, and applying a vacuum to the interior of the covering.

Abstract: A method of heating a thermoplastic board by heat conduction in a heating system which has at least a first surface contacting tool and a second surface containing tool spaced from the first tool, at least one of which is heatable. The thermoplastic board is placed into the heating system between the two surface contacting tools, with an auxiliary sheet being placed between the contact surface of the respective heatable surface contacting tool and the surface of the thermoplastic board facing it. The space between the two surface contacting tools is then reduced to a predefined gap measurement, and the heatable surface contacting tool or tools is heated.