Airbus Operations Gmbh

Airbus Defence and Space Gmbh

Airbus (Sas)

Fundacio Eurecat

Wolfgang Machunze

Alois Friedberger

Peter Linde

Tassilo Witte

Christian Metzner

Michael Meyer

Tamas Havar

Andreas Helwig

Markus Gibbert

Heinz Hansen

Christian Thomas

Matthias Lengers

Markus Joerg Weber

Marc Hencke

Heiko Fietzek

Johannes Kirn

Mirko Missbach

Benjamin Ehring

Elmar Bonaccurso

Martin Wandel

Marc Crescenti

Mirko Mißbach

A semi-active noise control system includes a layer configured to be part of an interior panel of an aircraft The layer includes conductive tracks, a driver arrangement, tuned mass dampers, and sensors. Each tuned mass damper has an eigenfrequency that depends on a control signal applied to the tuned mass damper and is connected to the driver arrangement via a conductive track and configured to receive control signals from the driver arrangement. Each sensor is connected to the driver arrangement via a conductive track and is configured to sense vibrations and/or acoustic sounds and send measurement signals to the driver arrangement. The driver arrangement is configured to analyze the measurement signals and to generate and send control signals to the tuned mass dampers such that the eigenfrequency of the tuned mass dampers is matched with the frequency of the vibrations and/or acoustic sounds sensed by the sensors.

Semi-active noise control system for an aircraft

To achieve a composite material part with a fully load adapted 3D fiber reinforcement with low costs for tools and process, a method is provided for manufacturing a part made of composite material with a continuous fiber reinforcement. The method comprises the steps of providing a body with tubular cavities and having at least one first portion made from a first polymer material and at least one second portion made from a second polymer material, introducing resin and continuous fibers into the tubular cavities, and removing at least a part of the second polymer material.

Manufacturing method and system for manufacturing a continuous fiber reinforced composite part

A method for producing a panel with integrated conductor tracks and electronic components. The panel includes a panel body, wherein the panel body is in particular a sandwich structure, and a membrane. The membrane is connected to the panel body and has integrated conductor tracks and electronic components. At the beginning of the method, an operation for attaching the conductor tracks and the electronic components to the membrane is provided. The subsequent step includes an operation for connecting the membrane, fitted with the conductor tracks and the electronic components, to the panel body.

Method for producing a panel with integrated electronics

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 flap support for supporting a flap of a wing for an aircraft is disclosed and includes a load bearing fairing shell and a reinforcement structure at least partially received in the interior space of the fairing structure and mounted to the first and second side wall portions of the fairing shell. The fairing shell includes a front attachment device configured for attachment to a main wing, and the reinforcement structure includes an aft attachment device configured for attachment to the main wing. The flap support further includes a hinge device configured for forming an articulated connection to the flap.

Flap support for supporting a flap of a wing for an aircraft

An end rib assembly for a high-lift device of an aircraft to reduce the noise caused by the transition between the wing and a high-lift device as well as the noise caused by the lateral side edge of the end rib assembly. An end rib assembly includes a noise-reducing portion configured to reduce noise caused by an airflow around the end rib assembly, and a guiding portion configured for guiding the end rib assembly along a pre-determined path when the high-lift device is moved between a retracted position and an extended position, wherein the guiding portion is formed such that an airflow impinging on the guiding portion is partly guided towards the noise-reducing portion.

Noise reduced end rib assembly for a high-lift device of an aircraft

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

An airfoil portion includes an outer skin member and an inner stiffening member. Either the outer skin member or the inner stiffening member or both are arranged to delimit a chamber. The chamber is configured to contain an inner pressure, wherein the inner pressure differs from a pressure external to the chamber. In an embodiment, an aircraft includes such an airfoil portion. A method for providing such an airfoil portion with a chamber is also described.

Airfoil portion with a chamber

A load-bearing fairing element for a flap adjustment mechanism of an aircraft comprises a shell-shaped fairing housing with an at least partly U-shaped profile with an open side, a closed side, and a direction of main extension, at least one first cover panel that along the direction of main extension covers part of the open side, and a load-bearing bridge element. The bridge element is arranged in the fairing housing and with a base area conforms so as to be flush against an internal surface of the fairing housing and extends towards the open side. The bridge element comprises an essentially planar cover area that covers the base area on the open side in order to produce a closed profile contour that is circumferential on the direction of main extension. The bridge element comprises means for holding a shaft feed-in of a central flap drive and means for holding an adjustment mechanism that is couplable to the shaft feed-in. Consequently there is no need to provide complex stiffening structures within the fairing element.

Growing community of inventors

Oberhaching, Germany

Wolfgang Machunze