Airbus Operations Gmbh

Airbus Defence and Space Gmbh

Airbus (sas)

Airbus Operations Sl

Airbus India Operations Private Limited

Peter Linde

Matthias Hegenbart

Hermann Benthien

Norbert Heltsch

Pierre C Zahlen

Brian Lee Wardle

Alois Friedberger

Dan Zenkert

Tamara Blanco Varela

Paul Jörn

Blanka Lenczowski

Christian Karch

Andreas Helwig

Leif Asp

Maciej Wysocki

Markus Müller

Christian Metzner

Wolfgang Machunze

Michael Telkamp

Ingo Krohne

Florian Schmidt

Rainer Rauh

Detlev Konigorski

Alexander Horn

Shubham Shukla

Johannes Stuhlberger

Gunnar Haase

Yoshiyasu Hirano

Awista Nasiri

Dennis Hahn

Guido Kaiser

Albrecht Kluge

Fredrik Ohlsson

Elmar Bonaccurso

Thorsten Steinlicht

Josefina Menendez-Alberquilla

Sean Dempsey

Santosh Thukaram

Pedro Nehter

Claus Gosch

Markus Feiler

Maximilian Schutzeichel

Göran Lindbergh

Benedikt Kriegesmann

Peter Rostek

Thorsten Schüppstuhl

Camilla Brodale

Dirk Herzog

Maria Tamara Blanco-varela

Paulo Lage

Gülcan Graevendieck

Lisa Tölle

John Cole

Brian Wardle

Jan SCHÖNKE

Josefina Menendez Alberquilla

Leakage detection for pressurized fuel tanks. To provide facilitated leakage detection, a leakage detection device for pressurized fuel tanks for storing a pressurized fuel includes a fuel-sensing tracer and a light-wave conducting component. The fuel sensing tracer is configured to alter its optical properties in the presence of a predetermined fuel. The light-wave conducting component is in optical contact with the fuel sensing tracer. Light travelling within the light-wave conducting component is modifiable by altered optical properties of the fuel sensing tracer such that modified light is indicative of the presence of fuel at the location of the fuel sensing tracer.

Leakage detection for pressurized fuel tanks

A cryogenic storage tank including a first metallic end piece having a first structured connection area on its outer surface, a second metallic end piece having a second structured connection area on its outer surface, a hollow body extending between the first structured connection area and the second structured area. The hollow body is formed of a fiber reinforced polymer-based composite, a first metallic clamp having a third structured connection area and a second metallic clamp having a fourth structured connection area. The hollow body is arranged between and in intimate contact with the first structured connection area of the first metallic end piece and with the third structured connection area of the first metallic clamp and is arranged between and in intimate contact with the second structured connection area of the second metallic end piece and with the fourth structured connection area of the second metallic clamp.

Cryogenic storage tank, aircraft with a cryogenic storage tank and method for forming a hybrid metal polymer joint

An indicator apparatus for guiding interior aircraft occupants has a mounting device fastenable to a wall portion of the interior and having an indicator conveying an item of visual information to occupants. An indicator can be or is operated electrically, and the indicator can be or is connected to a power supply for operation. To create an indicator apparatus which helps improve orientation of cabin passengers, can be produced, installed and serviced easily, and which can be operated in a fail-safe manner in an emergency situation of the aircraft, the indicator has an at least one-piece layer, on which circuitry necessary for operation is provided in an integrated fashion, and the power supply is formed by a composite structure battery built up layer by layer and can be or is connected to the layer. A method for producing an indicator apparatus of this kind is disclosed.

Indicator apparatus and method for producing same

Methods for fastening two fiber composite parts to each other with a fastener that includes electroactive polymer material. The parts have an opening within an inner circumferential surface. Fibers protrude from the inner circumferential surface into the opening and interlock with chains of micrograins of the electroactive polymer material. The fastener may switch between an activated state and a deactivated state and in the deactivated state, the fastener engages the exposed fibers.

Method for fastening a part to another part using electrically deformable rivets

A lightweight structure for a vehicle or aircraft includes a longitudinal member with a base bridge, having a first collective conductor and a transversal member with a central bridge and transversal bridge with a first connection conductor extending on a first surface of the transversal bridge and on a second surface of the transversal bridge oriented opposite the first surface, and a second connection conductor extending separately from the first connection conductor. The transversal member is connected to the base bridge at the first end section, so the first connection conductor contacts the first collective conductor of the base bridge. The lightweight structure includes a carbon fiber structural battery (CFSB) connected with the central bridge of the transversal member, a first collector of the CFSB electrically connected to the first or second connection conductor and a second collector of the CFSB electrically connected to the other connection conductor.

Lightweight structure for a vehicle and aircraft

A bipolar plate for a fuel cell for generation of electrical power has a bipolar plate body having a first surface. The bipolar plate body has at least one gas flow channel on the first surface, the gas flow channel defining a first gas flow channel side wall and an opposite second gas flow channel side wall, and the gas flow channel running in a first direction to expose the electrode to the reactant. The bipolar plate also has at least one electrical conductor to run at least partly parallel to the first direction within the bipolar plate body behind the first gas flow channel side wall and/or the second gas flow channel side wall, such that, when a voltage is applied to the electrical conductor, the electrical conductor forms an electromagnetic field, the electromagnetic field to accelerate the reactant at least partly in the direction of the electrode.

Bipolar plate for a fuel cell for generation of electrical power

A bipolar plate for a proton exchange membrane fuel cell includes a laminate of carbon fiber reinforced plastic (CFRP) with a first outer ply. The CFRP includes a resin and carbon fibers. The first outer ply is arranged at a first lateral surface of the laminate, wherein the laminate includes a first plurality of carbon nanotubes (CNTs). The first outer ply includes a first groove, wherein the first groove is configured to define a first gas diffusion channel. At least some of the first plurality of CNTs extend through the first outer ply in a direction transversely to the first lateral surface of the laminate.

Carbon nanotubes reinforced bipolar plate

In order to improve liquid hydrogen storage on aircraft, a liquid hydrogen tank is integrated into the fuselage of the aircraft. At least one portion of the tank wall is formed by specially adapted tank skin panels and/or a pressure bulkhead. The parts forming the tank wall are strengthened to contain a tank pressure of about 3 bar.

Fuselage section of an aircraft, aircraft fuselage, and aircraft

A method for resistance welding of two fiber-composite components to give a fiber-composite structure includes arranging conductive fibers within a jointing region of the two fiber-composite components, where each conductive fiber includes a carbon fiber with an electrically insulating coating. An electric current is passed through the conductive fibers to heat the jointing region to a welding temperature and melt the fiber-composite components in the jointing region. The jointing region is hardened in a manner that bonds the two fiber-composite components by way of the jointing region to give the fiber-composite structure.

Method for the resistance welding of fiber-composite components to give a fiber-composite structure, fiber-composite structure and fiber-composite component

A busbar for an aircraft with at least two conductive layers and at least three insulating layers. The conductive layers and the insulating layers are stacked together alternatingly and extend in a longitudinal direction. The conductive layers and the insulating layers include different coefficients of thermal expansion. Each of the conductive layers includes spatial structures. Each spatial structure is connected to an adjacent one by an interconnecting segment. Each conductive layer is embedded between two insulating layers, resulting in a deforming of the side walls of the spatial structures under heat, thereby compensating a longitudinal expansion of the conductive layers. Further, an aircraft with a disclosed busbar and a method of producing such busbar is provided.

Busbar for an aircraft, method of manufacturing such busbar, and aircraft comprising such busbar

A component system for an aircraft, having at least one furnishing component, a plurality of component rails, a plurality of guide elements engageable with and movable relative to the component rails, a plurality of retaining elements connected to the guide elements and configured to be coupled to a hull structure of the aircraft or the at least one furnishing component, and a plurality of locking units arranged on the component rails and/or on the guide elements and configured to lock the guide elements to a particular rail. At least two component rails are arranged on the at least one furnishing component or the hull structure at a distance and parallel to each other such that the furnishing component is retractable via the component rails on guide elements or component rails that are spatially fixed in the aircraft and can be locked in a retracted position by the locking units.

Component system for interior furnishing of an aircraft

A structural component for an aircraft including at least one heatable component section having a layer structure including an inner base structure, at least one heating layer having carbon allotropes embedded in a matrix material, at least one first group of consecutive layers including at least one anode layer, at least one first insulating layer, and at least one cathode layer having an electroactive coating. The first group of layers are arranged between the inner base structure and the at least one heating layer, and at least one protective layer is arranged outside the heating layer. The first group of layers constitute a structural battery. The at least one anode layer and the at least one cathode layer are electrically connectable with the heating layer.

Structural component for an aircraft with integrated heating layer and structural battery

A heatable floor panel for an aircraft, with a supporting level, a heat-generating level and a heat-conducting level. The heat-generating level comprises a fiber composite layer with fibers and with a matrix surrounding the fibers. The fibers are at least partially formed as conducting fiber, and the conducting fibers are formed as carbon fibers with an electrically insulating coating. The conducting fibers integrated in the floor panel in order to conduct a heating current through them. Due to the electrically insulating coating of the conducting fibers, leakage currents are avoided. The carbon fibers serve not only as heating elements, but, at the same time, also as reinforcing fibers of the fiber composite layer or of the floor panel.

Heatable floor panel and floor heating system for an aircraft

A flow body for an aircraft includes a skin having a first flow surface, having a flow influencing section with at least one first layer, at least one separator layer, at least one third layer, and at least one base layer. The first layer includes lithiated carbon fibers embedded into a matrix to form a negative electrode. The third layer includes carbon fibers with an electrode active material coating to form a positive electrode. The separator layer includes a non-conductive material for electrically isolating the first layer and the third layer from each other. The flow influencing section is configured for selectively raising a region of the arrangement of first layer, separator layer and third layer from the base layer upon application of a voltage between the first and third layers to form a bump on the flow body.

Flow body for an aircraft with a selectively activatable shock bump

A structural component of a primary structure for a vehicle, the structural component including a fiber composite laminate with a plurality of fiber composite sublayers. The plurality of fiber composite sublayers includes an electric energy store which is configured as a multilayer electrochemical fiber composite battery to store electric energy in a rechargeable manner; and an electrothermal temperature regulation sublayer which is configured to supply thermal energy to the electric energy store and conducting thermal energy away from the electric energy store as required to regulate a temperature. A control device, which is connected to the electric energy store and the electrothermal temperature regulation sublayer, is configured to control a temperature regulation of the electric energy store by means of the electrothermal temperature regulation sublayer.

Structural component of a primary structure for a vehicle with an electric energy store and electrothermal temperature regulation sublayer

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Hamburg, Germany

Peter Linde