Airbus Operations Gmbh

Volker Robrecht

Bernd Ruppert

Gilles Debril

Till Raguse

Daniel Stoevesand

Markus Kerber

Matthias Siercke

Joakim Holmgren

Urs Pachale

Sergej Naumann

Thomas Holder

Uwe Wurr

A flow body for a vehicle having a flow surface, as well as a skin system attached to the flow surface is proposed. The skin system has a top layer and a foam arrangement positioned between the flow surface and the top layer, wherein the top layer includes an elastic, surface-like material, wherein the foam arrangement includes a first layer of an elastic, compressible open cell foam, wherein the foam arrangement is bonded to the top layer. The skin system has a static shape in an unloaded state, in which the shape defines an outer surface geometry that directly follows the geometry of the respective flow surface, and the skin system has a deflected shape when the flow body is subjected to turbulent air flow. The deflected shape at least temporarily compresses the foam arrangement.

Flow body for a vehicle with a compressible skin

A method for manufacture of a complex component includes construction of the component from a metal material in an additive manufacturing method with at least one cavity segment that has a cavity open on at least one side and defined by an interior surface of the component, formation of an auxiliary electrode during construction of the component, formation of one or a plurality of supporting structures that connect the auxiliary electrode to the interior surface of the component during the construction of the component, electrical insulation of the auxiliary electrode from the interior surface by separating the supporting structures from the interior surface or from the auxiliary electrode, and performance of an electro-polishing of the interior surface in an electrolyte bath by connecting the component and the auxiliary electrode to different poles of an electric voltage source.

Method for the manufacture of a complex component and separating tool

A process for producing a sandwich component. A first covering layer is formed on a molding surface of a molding tool; a core is produced by building up a cell structure having a multiplicity of cells in a thickness direction on the first covering layer via an additive production process; and a second covering layer is formed on a deposition surface of the core, the surface being situated on the opposite side from the first covering layer. A core for a sandwich component is furthermore described, as is a sandwich component.

Process for producing a sandwich component, core for a sandwich component, and sandwich component

A boundary-layer-influencing aerodynamic part comprises a carrier element provided with at least one air passage aperture for guiding an air flow through the carrier element, an air guiding layer disposed on the carrier element and a cover layer constituting at least a part of a flow surface and being configured to have air flow there through at least in sections. The air guiding layer is configured to have air flow there through with an air flow supplied to the part, at least in certain operating phases of the part, through the cover layer and flowing in the direction of the carrier element or through the air passage aperture of the carrier element and flowing in the direction of the cover layer. The cover layer is applied directly to the air guiding layer via an additive manufacturing method.

Boundary-layer-influencing aerodynamic part and method for producing the same

An air conduction part for conducting a compressible medium, which part has a cross section through which the medium passes in a flow direction of the medium when the air conduction part is used, which flow direction approximately corresponds to a longitudinal axis of the air conduction part, the air conduction part including at least one wall arrangement that laterally defines the cross section of the air conduction part and conducts the medium. The wall arrangement are provided with at least one shell and with at least one damping device that removes sound energy from the medium, and the shell and the damping device are integrally interconnected so that, with a justifiable amount of outlay, the resulting air conduction parts effectively damp sound and the transport direction of the medium and/or the cross section of the air conduction part may change.

Sound-damping air conduction part

An installation assembly for bridging a cable harness between two aircraft structure elements of an aircraft is provided. The installation assembly includes an elongated connecting rod having two end sections for attaching the connecting rod onto two adjacent aircraft structure elements, at least one cable guidance element having at least one receiving section for receiving a cable harness and an attachment section for circumferentially surrounding the connecting rod. Locking means are provided to form a connection between the attachment section and the connecting rod, wherein a polygonal cross section of the connecting rod corresponds to a recess of the attachment section in order to form a positive locking engagement between the cable guidance element and the connecting rod.

Installation assembly for bridging a cable harness or the like between two aircraft structure elements

A device for mounting at least one connector in an aircraft fuselage includes a first and a second traverse configured to connect the device to a structural section of the aircraft fuselage at end sections of the first and second traverses. A frame element extends transversely between the first and the second traverses and is configured to accommodate the at least one connector. A first and a second connecting profile respectively connect the frame element to the first and second traverse.

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Hamburg, Germany

Volker Robrecht