Airbus Operations Gmbh

Airbus Deutschland Gmbh

Airbus Defence and Space Gmbh

Eads Deutschland Gmbh

Heinz Hansen

Burkhard Goelling

Klaus-Peter Neitzke

Florent Laporte

Tamas Havar

Christian Metzner

Wolfgang Machunze

Markus Joerg Weber

Andreas Gessler

Ross Salisbury

Alexander Horoschenkoff

Christopher Payne

Kai-Christoph Pfingsten

Johannes Kirn

Llifon Williams

Rolf Radespiel

Robert McCormick

Christoph Jensch

Timothy Evans

Juergen Frey

Veit Hildebrand

Hugh Theobald

Marcus Rafla

Robert Mccormick

Burkhard GÖLLING

Jürgen Frey

A leading edge structure for providing an aerodynamic surface of an aircraft is disclosed having a skin structure, the skin structure providing an outer aerodynamic surface and an inner surface, both surfaces extending in a chordwise and spanwise direction of the structure, and a plurality of structural members, each structural member being connected to the inner surface of the skin structure and extending in the chordwise direction along the inner surface, wherein the structural members are integrally formed with the inner surface of the skin structure. The disclosure is also related to an aircraft wing, aircraft tailplane, wing box structure, wing or wing structure and an aircraft including the leading edge structure.

Leading edge structure

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 aerodynamic body of an aircraft with an air outlet opening and an air intake opening that communicates with the air outlet opening via an air conduit is described. A flow delivery driver device for influencing the flow within the air conduit is integrated into the air conduit. The surfaces of the aerodynamic body in the body chord direction include at least one air outlet opening in the front region of the aerodynamic body, and at least one air intake opening on the upper surface of the aerodynamic body and in the rear region of the aerodynamic body and/or on the upper surface of the aerodynamic body in the trailing edge region and/or on the lower surface of the aerodynamic body in the trailing edge region. Arrangements of a main wing and an adjustable flap, and an aircraft with such an aerodynamic body are also described.

High-lift flap, arrangement of a high-lift flap together with a device for influencing the flow on the same and aircraft comprising said arrangement

A wing of an aircraft is described, having: a main wing, at least one high lift flap which can be moved between a retracted and an extended position, and a spoiler. The main wing has ejection openings, arranged side-by-side along the main wing spanwise direction, and in the main wing chordwise direction, and which are connected via an air conduit with the outlet device of a flow delivery driver device on the main wing or on the spoiler. The spoiler has inlet openings for the intake of air, which are connected via an air conduit with the inlet device of the flow delivery driver device. The flow delivery driver device has a receiver device for the reception of command signals for purposes of adjustment of the flow delivery driver device. An arrangement of a wing with a device for purposes of flow control with such a wing is also described.

Wing of an aircraft and assembly of a wing comprising a device for influencing a flow

The flight of an aircraft is controlled by controlling the aircraft propulsion thrust and adjusting aerodynamic control elements so that the aircraft flies along a specified flight path. In order to reduce wake vortices generated by and trailing behind the aircraft, a wake vortex parameter is determined as a function of a spoiler deflection, and a spoiler element is adjusted to a spoiler deflection value in an optimum range in which the spoiler influence on the wake vortex parameter is maximized and the spoiler influence on the aircraft performance is at its lowest level for achieving that maximum spoiler influence on the wake vortex parameter.

Method of controlling an aircraft in flight, especially to reduce wake vortices

An aerodynamic profile has an adjustable flap, which has a forward profile area as well as a rearward profile area situated in the downward current, bounded by a pressure-side covering skin as well as a suction-side covering skin. The pressure-side and suction-side covering skins converge in the rearward profile area at a trailing profile edge. In the rearward profile area on the underside of the pressure-side covering skin, a flap is swivellably disposed such that, in the inoperative condition, the flap, pointing in the flow direction, rests against the contour of the pressure-side covering skin and, in the deflected condition, the flap encloses an angle with the pressure-side covering skin. An airtight hinge connection is integrated in the flap so that, on the side of the flap protected from the wind, a turbulence system which improves the flow conditions is formed.

Aerodynamic profile with an adjustable flap

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Weyhe, Germany

Heinz Hansen