Airbus Operations Gmbh

Matthias Hegenbart

Peter Linde

Hermann Benthien

Pierre C Zahlen

Wolfgang Eilken

Mika Bots

Ingo Roth

Memis Tiryaki

Alexander Horn

Michael Sauer

Detlev Konigorski

Andreas Poppe

Markus Piesker

Oliver Seack

Andreas Wietzke

Bruno Stefes

Torsten Noebel

Thorsten Otto

Dirk Elbracht

Ingo Krohne

Bastian Schaefer

Florian Schmidt

Thomas Lerche

Marcus Hinrichs

Nabankele-Martial Somda

Yoshiyasu Hirano

Erich Paul

Tobias-Valentin Mayer

Jens Rohde

Thorsten Steinlicht

Sebastian Palm

Joern Clausen

Matthias Radny

Claus Gosch

Ulrich Knapp

Liu Wang

Camilla Brodale

Dirk Herzog

Lena Duken

Lisa Tölle

Martin M Johannsen

Jan SCHÖNKE

Peter Dr- Ing Linde

A fastening element for fastening a first component to a second component. The fastening element includes an elastically deformable body and an elongated actuating member. The actuating member is movably guided relative to the body to be selectively movable further into or further out of the body. The body is configured to be elongated by moving the actuating member further into the body and applying a corresponding load onto the body and to elastically deform back by moving the actuating member further out of the body and releasing the load applied thereto. Further, the body is configured to have a smaller outer diameter when correspondingly elongated than when non-elongated and/or deformed back.

Fastening element with selectively elongatable body

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 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 connecting system for connecting components in a vehicle includes a first elongate element with a first connecting face at a first end, and a second elongate element with a second connecting face at a second end. The first and second elements each comprise holding devices distributed along an annular connecting line. The connecting faces are congruent. The connecting faces and holding devices are configured to be brought into a flush superficial contact when the orientations of the elongate elements coincide, and the mutually opposing holding devices then connect with one another. One of the elements has a length adjustment component configured to change a position of the respective connecting face in a longitudinal direction of the respective element. The connecting faces comprise at least one pair of connectable interfaces which correlate with one another in pairs for transfer of a fluid, electrical or optical signals or electrical current.

Connecting system for connecting components in an aircraft

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

An apparatus for fastening a component to an aircraft cabin attachment structure, the attachment structure having a fastening tube with a longitudinal axis. The apparatus has an internally bored sleeve rotatably positionable on the fastening tube and an external thread. A holding body connects to the component and has two spaced-apart limbs and a bearing surface enclosed by the limbs, and on which, an internal thread configured to the sleeve external thread, is arranged. A device fixes the holding body to the threaded sleeve and the fastening tube, the external and internal threads being non-self-locking. When the holding body internal thread presses against the threaded sleeve external thread, the threaded sleeve rotates until the external and internal threads align. The fixing device connects the threaded sleeve to the holding body in a rotationally fixed manner and fixes the holding body transversely with respect to the longitudinal axis.

Fastening apparatus for fastening a furnishing component to an attachment structure of an aircraft cabin

A reinforcing element for a structural profile, in particular for a round, oval or elliptical structural tube, includes a composite structure, which has a hollow-cylindrical, helically wound mesh of fiber strands which form an inner shell surface configured to receive the structural profile, wherein the fiber strands are respectively embedded in a matrix material, which has an electroactive polymer which can be stretched along a longitudinal extent of the fiber strands by application of an electrical voltage, such that the composite structure can be expanded by application of the electrical voltage to introduce the structural profile into the composite structure and can be shrunk by switching off the electrical voltage to fix the structural profile on the shell surface in the composite structure.

Reinforcing element for a structural profile, structural arrangement, aircraft or spacecraft, and method for producing a structural arrangement

A method of providing a deformable shim that comprises a main structure of an at least partly cellular region. The main structure is compressible by plastic deformation from an initial volume to a deformed volume, wherein the deformed volume is smaller than the initial volume. In a deformed state, the main structure maintains the deformed volume without further or continuing compression force. Further, the main structure is arrangeable between a first aircraft component and a second aircraft component to create a predefined distance between the first and the second aircraft component.

Deformable shim and mounting arrangement

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 structure and equipment system installed in an aircraft includes vertical supports, a rail device, a connector, guiding elements, pivot joints, and locking devices. The rail device is arranged on the aircraft to guide the guiding elements along a rail device extension axis. Via the connector, the vertical supports are arranged in parallel and connect to form a grid arrangement with the guiding elements arranged thereon. The pivot joints are attached to upper ends of the vertical supports to pivot them. The locking devices each have a first and a second locking element. The grid arrangement is inserted into the aircraft as far as an installation position via the guiding elements on the rail device with vertical supports pivoted upwards from the vertical, by pivoting down into a vertical orientation, the first locking elements can interlock with correspondingly arranged second locking elements to form a load-bearing support structure.

Structure and equipment system for installation in an aircraft

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 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

A system is proposed, using which a material is dispensed in a web shape to additively produce a component. An in situ material check is performed, wherein if a geometric deviation lying outside a tolerance is established, material dispensing is interrupted to carry out finish compacting of a dispensed material web by way of a compacting unit.

System and a method for producing a component

A structural member for an aircraft or spacecraft has at least one fiber plastic composite, the fiber plastic composite having at least one or a plurality of plies. The structural member also has at least one pre-stressing means providing internal stresses to the fiber plastic composite. The fiber plastic composite and the pre-stressing means are configured and arranged to form a balanced system the internal stresses of which are essentially balanced to zero in a cured state of the said system. The balanced system of the structural member is able to counteract loading stresses exerted to the airframe in service such, that a damage caused by the loading stress is easily detectable visually.

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Hamburg, Germany

Matthias Hegenbart