Abstract: A system for producing a component or semifinished product with a fibre-reinforced foam core, includes a substrate on which the foam core having a first main surface and an opposite second main surface is to be laid; a sewing device having a needle configured to be moved at least linearly; a fibre supply device for three-dimensional supply of a fibre; and a coating device. The sewing device is configured to position the needle at the first main surface and to pierce the foam core, such that a needle tip penetrates through the first main surface and then through the second main surface. The fibre supply device is configured to position a reinforcing fibre such that the reinforcing fibre is hooked into the needle tip. The coating device is configured to coat a reinforcing fibre hooked into the needle tip with resin immediately before the reinforcing fibre enters the foam core.

Abstract: A method for producing a component with a fibre-reinforced foam core has the steps of supplying a foam core having a first main surface and an opposite, second main surface, positioning at least one needle at the first main surface of the foam core, piercing the foam core with the needle, with the result that a needle tip penetrates through the first main surface into the foam core and then through the second main surface, hooking a reinforcing fibre into the needle tip, pulling the needle back, with the result that the reinforcing fibre is pulled through the foam core, and coating the reinforcing fibre with a resin while the needle is being pulled back.

Abstract: A composite panel assembly including a first panel with a first skin, a second skin, a core, and an assembly flange. A second panel includes a first skin, a second skin, a core, and an assembly flange. A fastening device is adapted to fasten the assembly flange of the first panel to the assembly flange of the second panel, wherein the core of one of the first panel or the second panel includes reinforcing pins and a high-density portion placed along the assembly flange.

Abstract: A composite panel includes a first skin, a second skin, a core arranged between the first skin and the second skin, reinforcing pins connected by a first end to the first skin and connected by a second end to the second skin, in which inclined reinforcing pins form an angle of from 25 degrees to 40 degrees with the first skin and/or the second skin.

Abstract: A composite construction, such as, in particular, a composite plate having a sandwich-type construction, has two outer layers which are mutually opposed in parallel and a foam material completely filling the space between the outer layers at least in some regions. The outer layers are interconnected by means of spacers, and the spacers are connected to the outer layers via a cured plastics material.

Abstract: A battery housing for the structural integration of batteries in a vehicle, in particular an aircraft or spacecraft, includes an inner housing for receiving a battery, and an outer housing which surrounds the inner housing such that a cavity is formed between the inner housing and the outer housing, wherein pins are formed in the cavity and connect the inner housing to the outer housing. A battery arrangement includes at least one battery housing of this type and at least one battery which is arranged in the inner housing of the at least one battery housing.

Abstract: A method for producing a component with a fibre-reinforced foam core has the steps of supplying a foam core having a first main surface and an opposite, second main surface, positioning at least one needle at the first main surface of the foam core, piercing the foam core with the needle, with the result that a needle tip penetrates through the first main surface into the foam core and then through the second main surface, hooking a reinforcing fibre into the needle tip, pulling the needle back, with the result that the reinforcing fibre is pulled through the foam core, and coating the reinforcing fibre with a resin while the needle is being pulled back.

Abstract: A composite panel includes a first skin, a second skin, a core arranged between the first skin and the second skin, reinforcing pins connected by a first end to the first skin and connected by a second end to the second skin, in which inclined reinforcing pins form an angle of from 25 degrees to 40 degrees with the first skin and/or the second skin.

Abstract: A composite panel assembly including a first panel with a first skin, a second skin, a core, and an assembly flange. A second panel includes a first skin, a second skin, a core, and an assembly flange. A fastening device is adapted to fasten the assembly flange of the first panel to the assembly flange of the second panel, wherein the core of one of the first panel or the second panel includes reinforcing pins and a high-density portion placed along the assembly flange.

Abstract: A battery housing for the structural integration of batteries in a vehicle, in particular an aircraft or spacecraft, includes an inner housing for receiving a battery, and an outer housing which surrounds the inner housing such that a cavity is formed between the inner housing and the outer housing, wherein pins are formed in the cavity and connect the inner housing to the outer housing. A battery arrangement includes at least one battery housing of this type and at least one battery which is arranged in the inner housing of the at least one battery housing.

Abstract: The embodiment relates to the production of reinforced materials, for example reinforced foam materials or reinforced textiles. A multi-needle machine is provided with a plurality of serially arranged repeating units, which are able to move sliders and pins toward and past each other along a circular path so as to create the semi-finished textile products. In this way, it is possible to reinforce components with curved surfaces.

Abstract: This relates to the manufacturing of reinforced materials, such as reinforced cellular materials or reinforced textiles, for example. Reinforcement is achieved by including a textile semi-finished product into the material to be reinforced, by providing the semi-finished product at the rear side of the material in a zigzag or wave-like manner and then pulling the semi-finished product through the material by a plurality of needles. Thus, the manufacturing process may be performed in a time saving manner.

Abstract: A composite construction, such as, in particular, a composite plate having a sandwich-type construction, has two outer layers which are mutually opposed in parallel and a foam material completely filling the space between the outer layers at least in some regions. The outer layers are interconnected by means of spacers, and the spacers are connected to the outer layers via a cured plastics material.

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: 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: This relates to the manufacturing of reinforced materials, such as reinforced cellular materials or reinforced textiles, for example. Reinforcement is achieved by including a textile semi-finished product into the material to be reinforced, by providing the semi-finished product at the rear side of the material in a zigzag or wave-like manner and then pulling the semi-finished product through the material by a plurality of needles. Thus, the manufacturing process may be performed in a time saving manner.

Abstract: This relates to measures for protection against striking and penetrating objects. To provide ballistic protection measures that are as light and efficient as possible while having a compact design, a ballistic protective component for protection against penetrating foreign objects comprises a first layer and a second layer, which are mutually spaced by an intermediate layer, that together with a plurality of reinforcement elements, form a sandwich component. Further, an intermediate sheet made of core material is arranged in the intermediate layer. At least one sheet is arranged in the intermediate layer. The ballistic protective material is a fibrous sheet material. In another example, the ballistic protective material comprises dilatant material. The reinforcement elements are tensile and compressive resistant and extend from the first to the second layer through the at least one sheet of ballistic protective material, and, in one example, through the at least one intermediate sheet.

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 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: 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.