Airbus Defence and Space Gmbh

Airbus Operations Gmbh

Markus Joerg Weber

Gregor Christian Endres

Paul Joern

Norbert Heltsch

Markus Mueller

Wolf-Dietrich Dolzinski

Arne Hartwig

Jens-Ulrich Prowe

Christian Metzner

Kristian Zimmermann

Wolfgang Machunze

Heinz Hansen

Johannes Kirn

Ulf Henning Neumann

Christian Schumacher

Andreas Wieltsch

A composite panel assembly including a first panel with a first skin, a second skin, a core, and an assembly flange. A second panel includes a first skin, a second skin, a core, and an assembly flange. A fastening device is adapted to fasten the assembly flange of the first panel to the assembly flange of the second panel, wherein the core of one of the first panel or the second panel includes reinforcing pins and a high-density portion placed along the assembly flange.

Composite panels assembly, furniture comprising such assembly and aircraft comprising such assembly

A composite panel includes a first skin, a second skin, a core arranged between the first skin and the second skin, reinforcing pins connected by a first end to the first skin and connected by a second end to the second skin, in which inclined reinforcing pins form an angle of from 25 degrees to 40 degrees with the first skin and/or the second skin.

Composite panel with reinforcing pins

A battery housing for the structural integration of batteries in a vehicle, in particular an aircraft or spacecraft, includes an inner housing for receiving a battery, and an outer housing which surrounds the inner housing such that a cavity is formed between the inner housing and the outer housing, wherein pins are formed in the cavity and connect the inner housing to the outer housing. A battery arrangement includes at least one battery housing of this type and at least one battery which is arranged in the inner housing of the at least one battery housing.

Battery housing, battery arrangement and method for producing a battery housing

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 fuselage cell structure for an aircraft includes at least two skin panels including at least one double shell skin panel and at least one monolithic skin panel. At least one longitudinal brace or a transverse brace is disposed so as to form at least one of longitudinal seam or a transverse seam between the double shell skin panel and the monolithic skin panel. The fuselage cell structure includes at least one of a longitudinal bracket and a load transfer point. The longitudinal bracket is disposed in a region of the longitudinal seam and includes a first and a second longitudinal flanges disposed offset with respect to one another and connected by a web. The load transfer point is disposed in a region of the transverse seam so as to connect the longitudinal brace disposed on the monolithic skin panel to the double shell skin panel.

Fuselage cell structure for an aircraft in hybrid design

A window element for a double-shell skin field of an aircraft fuselage cell includes a window frame having a window module disposed in the frame, wherein the frame is disposed in an opening of the double-shell skin field, and wherein the frame is connected to the double-shell skin field by a surrounding embrasure profile positioned against a core structure of the skin field at least in some regions, wherein the core structure includes an inner and an outer covering layer.

Window element for a double-shell skin field of an aircraft fuselage cell

Growing community of inventors

Hamburg, Germany

Markus Joerg Weber