Airbus Defence and Space Gmbh

Airbus Operations Gmbh

Airbus (Sas)

Airbus Defence and Air Space Gmbh

Chemetall Gmbh

Airbus Corporation

Airbus Group Limited

Christian Karch

Johannes Wolfrum

Juergen Steinwandel

Blanka Lenczowski

Kay Dittrich

Yehoshua Yeshurun

Peter Linde

Jonathan Meyer

Jürgen Steinwandel

Matthias Bleckmann

Christian Metzner

Karin Bauer

Paulin Fideu

Ilya Ostrovsky

Bernard Duprieu

Ralf Caspari

Heiko Fietzek

Michael Pilawa

Alexander Ohnesorge

Markus Blechschmidt

Emanuel Ermann

Robert Weichwald

Claudio Dalle Donne

Thomas Schuster

Alexander Heilmann

Heinrich Dinnebier

Kay W Dittrich

A structural part for lightning strike protection, preferably of an aircraft includes a first structure element, wherein the first structure element includes a conducting material and is adapted to conduct electric currents into a grounded conducting airframe structure, and a second structure element, wherein the second structure element includes an outer layer with a first surface, wherein the outer layer includes a composite, preferably carbon-fibre reinforced plastic, CFRP or glass-fibre reinforced plastic GFRP. The structural part further includes a first elongated, preferably wedge-shaped, electrical conductor, with a first end and a second end, wherein the first end of the first elongated electrical conductor is connected to the first structure element and extends through the second structure element to the first surface, so that the second end of the first elongated electrical conductor serves as a lightning receptor without impairing the radar cross section of the aircraft.

Structural part for lightning strike protection

A structural component for an aircraft, spacecraft or rocket has a ply of fiber reinforced polymer, a first carbon nanotube mat; and a metallic layer, wherein the carbon nanotube mat and the metallic layer are arranged on the ply of fiber reinforced polymer to form a hybrid lightning strike protection layer. A component for manufacturing such a structural component, a method for manufacturing a component of this type, a method for manufacturing a structural component and an aircraft or spacecraft with such a structural component are described.

Structural component

An asymmetrically constructed radome for an aircraft and an aircraft having an antenna and a corresponding radome are described. The radome has a first layer with a first dielectric constant and a first layer thickness, and a second layer with a second dielectric constant and a second layer thickness. The first layer thickness and the second layer thickness are different from each other. The first layer includes a thermosetting material and the second layer includes a thermoplastic material. Such an asymmetrical radome structure improves the mechanical stability and electromagnetic transparency of the radome.

Asymmetrically constructed radome

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

A structural component, in particular for an aircraft, spacecraft or rocket, has a ply of fiber reinforced polymer; a first carbon nanotube mat; and a metallic layer, wherein the carbon nanotube mat and the metallic layer are arranged on the ply of fiber reinforced polymer to form a hybrid lightning strike protection layer. A component for manufacturing such a structural component, a method for manufacturing a component of this type, a method for manufacturing a structural component and an aircraft or spacecraft with such a structural component are described.

A structural component for a vehicle has a battery construction having a solid-electrolyte matrix material, a first layer of carbon fibres having a cathode-active coating, embedded in said solid-electrolyte matrix material, a second layer of carbon fibres without a cathode-active coating, embedded in said solid-electrolyte matrix material, and at least one electrically isolating barrier layer disposed between said first layer and said second layer. The structural component has a first collector layer and a second collector layer disposed on the first layer and the second layer, respectively, on a side that faces away from the barrier layer. The first collector layer and the second collector layer are configured from a flexible, moldable and porous layer of carbon allotropes.

Structural component having an integrated battery construction

The invention provides a method and apparatus for forming a freeform metal structure by wire feed additive manufacturing. In accordance with the method, a holding structure is moved in at least one moving direction, the holding structure holding the metal structure. A metal wire end is fed along an area of deposition on the metal structure in the at least one moving direction. The metal wire end is heated to a melting temperature using a heat source, with the metal wire end as melted being deposited on the metal structure as a metallic build-up material. The metallic build-up material after heating and during the cooling is subjected in the at least one moving direction behind the area of deposition to at least one pulsed magnetic field using a magnetic coil arranged after the heat source, the at least one pulsed magnetic field effecting plastic deformation of the build-up material.

Method and apparatus for distortion control on additively manufactured parts using wire feed and magnetic pulses

A structural element, in particular for an aircraft, such as an airplane, contains a laminate having a plurality of layers made of a fiber composite plastics material with carbon fibers, a lightning protection layer and optionally an electrically insulating dielectric protection layer. The laminate contains at least one hybrid layer, which comprises a carbon fiber-absorption fiber composite, the elongation at break of the absorption fiber being greater than the elongation at break of the carbon fibers.

Structural element

An actuator assembly is capable of manipulating a fluid flowing around a flow body, the fluid being received or able to be received in a volume of at least one cavity arranged in the flow body, and the fluid passing through at least one opening in the at least one cavity during manipulation of the fluid. In this process, the volume of the at least one cavity can be changed by moving a wall portion delimiting or defining the cavity. The actuator assembly has a drive unit with at least one actuator, which executes a periodic movement over time when actuated, causing a translational movement of the wall portion delimiting or defining the cavity and the wall portion being shaped in terms the topology thereof in such a way that it is adapted to the shape of the at least one cavity with the at least one opening thereof.

Actuator assembly

A microelectronic module for altering the electromagnetic signature of a surface. The microelectronic module includes at least one voltage converter for converting a first voltage provided into a higher, lower or identical second voltage. Furthermore, the microelectronic module includes at least one actuator. The actuator includes at least one generator for generating an electrical plasma from the second voltage provided by the voltage converter. At least the voltage converter and the actuator are arranged on a thin-layered planar substrate. The electrical plasma generated by the actuator interacts with an electromagnetic radiation impinging on the surface, as a result of which the electromagnetic signature is altered.

Microelectronic module for altering the electromagnetic signature of a surface, module array and method for altering the electromagnetic signature of a surface

An induction heating system and a method for controlling a process temperature for induction heating of a workpiece. The induction heating system comprises an inductor configured to generate an alternating magnetic field in response to an alternating current supplied thereto, a magnetic load comprising a magnetic material, the magnetic material having a Curie temperature and being configured to generate heat in response to the alternating magnetic field being applied thereto, the magnetic load being connectable to the workpiece in a heat-conducting manner so as to transfer the generated heat to the workpiece, and a control unit configured to control the process temperature for manufacturing the workpiece by adjusting the alternating magnetic field when the temperature of the magnetic material is in a temperature control range around or below the Curie temperature of the magnetic material, the temperature control range being dependent on the magnetic material of the magnetic load.

Active temperature control for induction heating

Specified is a lightning protection layer for an aircraft. The lightning protection layer has a first stratum and a second stratum. The second stratum is coupled to the first stratum along a connecting surface. The first stratum has a metal foil and the second stratum has carbon allotropes. It is thus made possible that damage to a structure of the aircraft by lightning strike is reduced.

Growing community of inventors

Neubiberg, Germany

Christian Karch