Airbus Defence and Space Gmbh

Airbus (Sas)

Airbus Operations Gmbh

Fundacio Eurecat

Airbus Helicopters Deutschland Gmbh

Airbus Corporation

Christian Metzner

Uwe Beier

Thomas Meer

Wolfgang Machunze

Peter Linde

Christian Karch

Kristian Zimmermann

Jorge Alejandro Carretero Benignos

Heinz Hansen

Markus Joerg Weber

Stephan Friedl

Andreas Gessler

Leif Asp

Dan Zenkert

Johannes Kirn

Fredrik Ohlsson

Matthias Bleckmann

Maciej Wysocki

Jürgen Silvanus

Hermann Seefried

Bettina Arold

Heinrich Dinnebier

Stefan Mittmann

Marc Crescenti

Christoph Breu

To achieve a composite material part with a fully load adapted 3D fiber reinforcement with low costs for tools and process, a method is provided for manufacturing a part made of composite material with a continuous fiber reinforcement. The method comprises the steps of providing a body with tubular cavities and having at least one first portion made from a first polymer material and at least one second portion made from a second polymer material, introducing resin and continuous fibers into the tubular cavities, and removing at least a part of the second polymer material.

Manufacturing method and system for manufacturing a continuous fiber reinforced composite part

A component for an aircraft and an aircraft with such component. The component includes a heat source enclosed by a housing, heat exchanger, heat sink, at least one structural suspension element, and an air duct. Each structural suspension element is attached to an inner surface of the housing and supports one or more of the heat source within the housing. The heat sink is part of the housing and configured to guide air from an inside of the housing an outside of the housing. Each heat exchanger is thermally coupled to the heat source. Each heat exchanger is fluidly connected to the heat sink via an inlet line and a return line for a coolant. The air duct is configured to guide ambient air from the outside through the housing, past each of the at least one structural suspension element, and through the heat sink out of the housing.

Structural cooling system for an aircraft

A joining method and assembly for an aircraft. To improve the characteristics or permit hitherto impossible connections between thermoplastic and thermoset components, a multi-material joining method is disclosed in which a thermoplastic connecting region is formed on the thermoplastic component. The connecting region is connected to the thermoset component by interdiffusion. For this purpose, the uncured second component is brought into contact with the connecting region and heat is supplied. An interdiffusion layer is formed which fixedly connects the second component and the connecting region to one another and thus joins the first component to the second component.

Joining method and assembly for an aircraft

In order to improve usability of hybrid or fully electric aircraft, a fuel cell having improved efficiency and increased volume/weight specific energy density is provided. The fuel cell has a self-supporting membrane structure that is formed as a triply periodic level surface, which separates a first cavity supplied with gaseous fuel from a second cavity supplied with gaseous oxidizer in a gas-sealed manner while connecting the cavities in an ion-conductive manner.

Fuel cell and fuel cell system for an aircraft

A method for producing a layer of a device for electromagnetic radiation absorption, includes: providing a ply of powder material in the layer to be produced of the device; providing a predefined concentration distribution of particles for electromagnetic radiation absorption in the layer; providing a first binder and a second binder for the powder materials, wherein the first binder includes particles for the absorption of electromagnetic radiation, wherein the second binder includes a lower concentration of identical and/or different particles than the first binder; determining a mixing ratio between the first binder and the second binder for every position in the layer; selecting a position of the layer; mixing the first and second binder according to the mixing ratio for the selected position; wetting the powder material at the selected position using the mixed first and second binders; and repeating selecting, mixing, and wetting to produce the layer.

Method for producing a layer of a device for the absorption of electromagnetic radiation

To improve the range of application of manufacturing methods for fiber-reinforced polymer or metal hybrid composite components, and preferably to enable the introduction of fiber bundles into a larger number of geometries, such as branches, merging points and intersections, a production method for producing a component including a composite material with a fiber reinforcement which is formed from fiber bundles and resin is disclosed. A component body with tube-like cavities is initially provided. Curable resin is introduced into the cavities. A pulling apparatus for the fiber bundles is also inserted into at least one of the cavities. The pulling apparatus includes at least one pulling member suitable for pulling the fiber bundles and transmitting compressive force. As a result of pulling of the pulling member, the fiber bundles are pulled into the cavities.

Production method and production system for producing a continuous-fiber-reinforced component

A battery cell includes an anode, a cathode, and a separator between the anode and the cathode, wherein at least one of the anode or the cathode includes at least a carbon fiber ply comprising carbon fibers, the carbon fiber ply having a thickness of less than 90 micrometers. Also disclosed are a battery and an aircraft including such battery cell, and a method for manufacturing such battery cell.

Battery cell comprising an ultra thin layer of carbon fibers

An aircraft wing has an upper surface element and a first actuator powered mechanism for varying the shape of the surface element which includes: an upstream segment SEG, a downstream segment SEG, an interconnecting segment SEGinterconnecting a downstream edge of SEGwith an upstream edge of SEG, wherein the interconnecting segment SEGextends along the whole or at least a major part of the downstream edge of SEGand the whole or at least a major part of the upstream edge of SEG, and a link element LNK interconnecting an upstream edge of SEGwith an upper surface of the aircraft wing, and the first mechanism interconnecting a contact Con a lower side of the upper surface element with a contact Con an inner structure of the airfoil. The first mechanism controls the shape of the upper surface element by controlling the distance between Cand C

Aircraft wing with an adaptive shock control bump

A module element for driving and retaining braiding bobbin carriers on a predetermined bobbin path has at least one base element that can rotate about an axis of rotation, and at least one retaining element that is formed integrally with the base element. The retaining element is configured to releasably hold at least one braiding bobbin carrier offset from the rotary axis.

Module element for driving and retaining braiding bobbin carriers and a braiding device

Growing community of inventors

Gmund, Germany

Christian Metzner