Abstract: Producing a composite structure involves providing a core structure having a folded configuration with fold valleys forming open channels extending along the valleys, and then forming a local reinforcement zone in the core structure itself, before applying any cover layer onto the core structure. The method may further involve applying two cover layers on two opposite sides of the core structure to form a composite sandwich structure, after the local reinforcement zone has been formed in the core structure. A core structure preferably has a local reinforcement zone formed by two molded bodies, e.g. of cured synthetic resin or foam, arranged form-fittingly on the opposite sides of the core.

Abstract: A composite sandwich structure is produced by providing a core structure, applying cover layers on opposite sides of the core structure, and forming an edge seal. The core structure has a folded cell structure with fold valleys forming continuous open channels with open ends and/or open channel sides at edges of the core structure. The channels extend along and are bounded between the fold valleys and the cover layers. The edge seal is formed to have a limited spatial volume in an edge region at an edge of the core structure, to close and seal open ends and/or open channel sides of the channels of the core, without an uncontrolled penetration of the seal material from the edge region to a greater depth into the open channels.

Abstract: The invention pertains to a method for reinforcing cellular materials (1), a reinforced sandwich construction (5) as well as a correspondingly equipped aircraft. In the method, a cellular material (1) is provided with fiber bundles (3) that are introduced into the cellular material (1) with a needle (8). In this case, the needle (8) initially pierces a through-hole (2) into the cellular material (1) from one side in order to subsequently take hold of a fiber bundle (3) situated on the other side with the needle (8) and pull said fiber bundle into the cellular material (1).

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: 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: 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 relates to a method for producing a folded core structure, particularly in the aerospace field, comprising the following steps: Initially a low-cross-linked, pre-impregnated semi-finished fibre component is provided. Subsequently heat is brought into predetermined regions of the pre-impregnated semi-finished fibre component, particularly using a laser, so as to highly cross-link the resin matrix in predetermined regions and so as to consequently generate a pattern of low-cross-linked and high-cross-linked regions in the semi-finished pre-impregnated fibre component. In a further step, of the method the pre-impregnated semi-finished fibre component is folded along the low-cross-linked regions that serve as hinges. Hereupon, the folded, pre-impregnated semi-finished fibre component is cured to the folded core structure.

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.