Abstract: The present invention provides a method for the localized working of a structural component that comprises a foam material reinforced by at least one strut at a working location. Firstly, the foam material is selectively removed, while leaving the at least one strut, within a strut connecting zone in the region of the working location. Subsequently, the strut connecting zone is filled with a filling material and the at least one strut is connected to the filling material in the strut connecting zone. From a further aspect, a sandwich component which comprises a foam core is provided. An embedding part is at least partially embedded in the foam core and at least partially surrounded by a layer of filling material. At least one strut is incorporated in the foam material, fastened at one end to the surface of the foam core and integrated at another end in the layer of filling material.

Abstract: Producing a local reinforcement in a core structure of a composite sandwich structure involves forming a hole in a cover layer and the core of the sandwich structure, forming a hollow space in the core with a diameter the same as or preferably larger than that of the hole, introducing a spatial bounding device through the hole into the hollow space, seating the spatial bounding device in the hollow space to contact outwardly against parts of the core preferably by outwardly expanding the device, and introducing a filler material into the spatial bounding device. A sandwich structure includes a core between cover layers, and a local reinforcement including a hole in at least one of the cover layers, a space in the core with a larger diameter than the hole, a spiral sleeve in the space, and a filler material inside the spiral sleeve.

Abstract: The present disclosure relates to a wall component for an aircraft for forming an outer wall comprising at least one first wall element, at least one second wall element and at least one connecting device for connecting the first wall element to the second wall element. On wall regions that are to be directed towards each other, the first and the second wall element comprise connecting regions. Furthermore, a joint element is provided, which comprises a joint region with a joint region surface that is to be arranged towards the outside of the aircraft, wherein the joint region is designed to be received with a matching fit into a recess formed by the connecting regions of the wall elements, and wherein the joint region surface, when the joint element is inserted, is flush with the outer surfaces of the wall elements.

Abstract: The present invention relates to a method for producing a core structure. Firstly, a first core structure and a second core structure are fastened. The first core structure and the second core structure are positioned at a defined distance. A reinforcement element is introduced into a cavity between the first core structure layer and the second core structure layer. The reinforcement element, the first core structure layer, and the second core structure layer form a self-supporting core structure.

Abstract: The invention relates to a structural component for an aircraft or spacecraft, comprising a component core extended across a component area, a first and second cover layer, which are formed on two opposite bounding surfaces of the component core and extend across the component area, a plurality of braces, which are distributed across the component area and connect the first and second cover layers to each other through the component core, and a stiffening belt, which extends between the cover layers along a stiffening line that extends substantially parallel to the component area.

Abstract: The present invention relates to a device and a method for providing cut-to-length rovings having a defined length from an endless roving, in particular in the aviation and aerospace sector, and also to a machine with a device of this type. The device comprises a loop shape setting arrangement, a loop bracing arrangement and a cutting arrangement. An endless roving can be braced by means of the loop bracing arrangement onto the loop shape setting arrangement, thus forming a loop which can be cut to length by means of the cutting arrangement in order to produce the cut-to-length roving.

Abstract: A method is provided for manufacturing a three dimensional frame structure that can be used as a core structure in a sandwich construction. Furthermore, a frame structure is provided for a sandwich construction, which frame structure has been manufactured in accordance with the method. In the method, a two dimensional lattice structure is made from bar-shaped linear semi finished products, in which structure the semi finished products intersect at defined points of intersection; the bar-shaped linear semi finished products are connected at the points of intersection and are softened by locally applying heat to the lattice structure in each case along three non-intersecting (imaginary) straight lines.

Abstract: The present invention provides a method for the localized working of a structural component that comprises a foam material reinforced by at least one strut at a working location. Firstly, the foam material is selectively removed, while leaving the at least one strut, within a strut connecting zone in the region of the working location. Subsequently, the strut connecting zone is filled with a filling material and the at least one strut is connected to the filling material in the strut connecting zone. From a further aspect, a sandwich component which comprises a foam core is provided. An embedding part is at least partially embedded in the foam core and at least partially surrounded by a layer of filling material. At least one strut is incorporated in the foam material, fastened at one end to the surface of the foam core and integrated at another end in the layer of filling material.

Abstract: The invention relates to a structural component for an aircraft or spacecraft, comprising a component core extended across a component area, a first and second cover layer, which are formed on two opposite bounding surfaces of the component core and extend across the component area, a plurality of braces, which are distributed across the component area and connect the first and second cover layers to each other through the component core, and a stiffening belt, which extends between the cover layers along a stiffening line that extends substantially parallel to the component area.

Abstract: The present invention provides a device for producing a composite fiber component. The device comprises a shaping tool having a shaping surface for shaping a resin-soaked fiber material, a filter panel that is arranged at the shaping surface and comprises a porous material, and a means for generating a negative pressure at the shaping surface at a side of the filter panel that faces away from the fiber material. In another aspect, the invention provides a method for producing a composite fiber component. First, a filter panel comprising a porous material is provided. In subsequent steps, a resin-soaked fiber material is arranged on the filter panel, the fiber material on the filter panel is covered and a negative pressure is generated at a side of the filter panel that faces away from the fiber material.

Abstract: The present invention provides a method of producing a construction, in particular a sandwich construction for the aeronautical and aerospace fields, comprising the following steps. A heating material is initially applied on one side of a core construction material. In a further step a reinforcing element is introduced into the core construction material and the heating material in such a way that the reinforcing element extends through the core construction material and the heating material and has a portion which projects beyond the heating material. The heating material is then heated to soften the projecting portion at least in regions and said projecting portion is subsequently deformed using the softened region as a pivot point to engage the core construction material from behind and to form the construction. This method is distinguished in particular by the fact that it allows the portions to be heated substantially simultaneously, and not sequentially as in the state of the art.

Abstract: A method for reinforcing a substrate or textile of a core structure of a component with the following method steps: a continuous semi-finished product is fed, via a feed means, into a cartridge of a conveying means which comprises a plurality of cartridges; the continuous semi-finished product is cut to length using a cutting means in order to produce a cut, reinforcing semi-finished product which is received in the cartridge; the cartridge is conveyed to a machining means; the cut, reinforcing semi-finished product is sharpened using the machining means; the cartridge is conveyed to a textile or substrate to be reinforced of a core structure; and the sharpened semi-finished product is shot into the textile or substrate of a core structure by a stud-shooting means.

Abstract: To form a cutout reinforcement according to the invention for a sandwich construction, according to the invention two methods are combined to improve the strength characteristics of a braid core which preferably consists of foamed material. For this purpose, a braiding is combined with fibre bundles which are pulled through holes in the braid core. As a result, the cutout reinforcement according to the invention for a sandwich construction has particularly outstanding strength characteristics, while the component has only a low weight.

Abstract: Provided is a method for reinforcing a foam material in which a working region is first prescribed. A gap that at least partially encloses the prescribed working region in a two-dimensional manner is created in the foam material. A strut is introduced into the foam material, extending from an entry surface of the foam material from outside the working region to at least the fibrous sheet-like material. From a further aspect, a sandwich component with a core which comprises a foam material is provided. A fibrous sheet-like material arranged in the foam material at least partially encloses a working region of the sandwich component in a sheet-like manner. At least one strut is incorporated in the foam material and extends from an entry surface of the foam material from outside the working region to at least the fibrous sheet-like material.

Abstract: In a method of producing a folded honeycomb structure for a sandwich component a sheet-like material is provided. The sheet-like material comprises a softening temperature and is heated to at least the softening temperature in a region about predetermined folding lines. Then, the sheet-like material is folded along the heated region of the folding lines into the folded honeycomb structure.

Abstract: The invention relates to a device for producing a reinforced foam material and for receiving a textile semifinished product in a hook. To this end, the device has a first subunit having a transport device and a second subunit having a receiving device. The transport device is designed to convey the textile semifinished product into the receiving device, and the first subunit and the second subunit are designed such that the textile semifinished product can be presented in defined length by a relative movement of the first subunit relative to the second subunit. Furthermore, the receiving device of the second subunit is set up such that the textile semifinished product can be placed in the hooks by a relative movement of the receiving device relative to the hook.

Abstract: The present invention relates to a device and a method for providing cut-to-length rovings having a defined length from an endless roving, in particular in the aviation and aerospace sector, and also to a machine with a device of this type. The device comprises a loop shape setting arrangement, a loop bracing arrangement and a cutting arrangement. An endless roving can be braced by means of the loop bracing arrangement onto the loop shape setting arrangement, thus forming a loop which can be cut to length by means of the cutting arrangement in order to produce the cut-to-length roving.

Abstract: Provided is a sandwich component with a core which comprises a foam material. A fibrous sheet-like material arranged in the foam material at least partially encloses a working region of the sandwich component in a sheet-like manner. At least one strut is incorporated in the foam material and extends from an entry surface of the foam material from outside the working region to at least the fibrous sheet-like material.

Abstract: A method and an apparatus facilitate the processing of a core structure for a composite sandwich structure. The core has an open three-dimensional structure and is not self-supporting due to an insufficient strength or stiffness. The method involves temporarily providing a support arrangement on the core structure to mechanically support and stabilize it, then subjecting the supported core structure to the desired processing, and then separating and removing the core structure and the support arrangement from one another. The processing can involve immersion into a processing liquid such as a curable resin, or mechanical machining operations. The support arrangement preferably includes a core impression that is surfacially form-fitting on a structured surface of the core structure. The apparatus includes a support arrangement including a core impression to be disposed on a surface of the core structure. The core impression may be formed of a polymer, a metal, or a casting material.

Abstract: The present invention relates to a method for producing a core structure. Firstly, a first core structure and a second core structure are fastened. The first core structure and the second core structure are positioned at a defined distance. A reinforcement element is introduced into a cavity between the first core structure layer and the second core structure layer. The reinforcement element, the first core structure layer, and the second core structure layer form a self-supporting core structure.