Airbus Operations Gmbh

Christian Heck

Bernhard Schlipf

Dort Daandels

Geza Schrauf

Shekhar Inamdar

A slat arrangement for a wing of an aircraft. The arrangement has a movable leading-edge slat and a connection section. The leading-edge slat includes a slat leading edge and a slat trailing edge. The connection section includes a receiving opening for receiving the slat trailing edge. The connection section includes an overhang having a free end. The slat trailing edge is configured to be translated under the overhang. A trailing region of the slat is configured to be elastically deformed by the overhang when the slat trailing edge is moved into the receiving opening.

Slat arrangement for a wing of an aircraft

A flow body for an aircraft includes a torsion box with spars and/or ribs and at least two skin portions for enveloping the spars and/or ribs, wherein at least one inner cell is formed in the torsion box. It is provided that a gas tank with a gas tank shell is arranged in the at least one inner cell, and that the gas tank includes fastening elements coupled to retaining elements in the relevant inner cell in order to hold the gas tank such that the gas tank shell is supported at a distance from the spars and/or ribs and the skin portions and is supported in three spatial directions.

Flow body for an aircraft with integrated gas tank

An aircraft structure () for flow control including a perforated panel () having an inner surface () directed to a structure interior (), an outer surface () in contact with an ambient flow (), and a plurality of micro pores () connecting the inner and outer surfaces (). Elongate crack stopper elements () are attached to the inner surface () of the perforated panel (). The crack stopper elements () are configured to inhibit crack propagation within the perforated panel ().

Aircraft structure for flow control

A leading edge structure () for a flow control system of an aircraft (), including a double-walled leading edge panel having an inner wall element () and an outer wall element (). Between the inner and outer wall elements () are elongate stiffeners () spaced apart from one another. And, between adjacent stiffeners () are a hollow chamber (). The outer wall element () includes micro pores (). The inner wall element () includes passages () forming a fluid connection between the hollow chambers () and a vacuum system (). An ice protection system in the stiffeners () includes hot air ducts () configured for connection to a hot air system (), and the stiffeners () include hot air openings () forming a fluid connection between the hot air ducts () and the hollow chambers ().

Leading edge structure for a flow control system of an aircraft

A leading edge structure () for a flow control system of an aircraft, including a double-walled leading edge panel () that surrounds a plenum (), wherein the leading edge panel () includes an inner wall element () facing the plenum () and an outer wall element () in contact with the ambient flow (), wherein between the inner and outer wall elements () the leading edge panel () includes elongate stiffeners () spaced apart from one another, so that between each pair of adjacent stiffeners () a hollow chamber () is formed between the inner and outer wall elements (), wherein the outer wall element () includes micro pores () forming a fluid connection between the hollow chambers () and an ambient flow (), and wherein the inner wall element () includes openings () forming a fluid connection between the hollow chambers () and the plenum ().

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Hamburg, Germany

Christian Heck