Airbus Operations Gmbh

Airbus Defence and Space Gmbh

Gerd Heller

Frank Theurich

Ralf Caspari

Emanuel Ermann

Alexander Buescher

Michael Karwin

Robert Weichwald

Tom Gibson

Stephen Powell

Christopher Wright

Ben Commis

Nicole Jordan

Detlev Konigorski

Kasidit Leoviriyakit

Stefan Schnäubelt

An assembly for arrangement to the surface of an aerodynamic profile comprises an array of actuators, which are designed as piezo actuators and plasma actuators.

Actuators for flow control at surfaces of aerodynamic profiles

An aircraft () including a wing () and a winglet () at the end of the wing, the winglet including: a root (); a tip (); a transition region () extending away from the root; and a wing-like region () extending from the distal end of the transition region to the tip. When the aircraft wing () is under the worst-case static loading, the tip of the winglet is located at the maximum spanwise extent of the winglet (), but when the aircraft wing () is under the no-load condition, the wing-like region () is canted inboard such that the tip () of the winglet () is located inboard of the maximum spanwise extent of the winglet.

Winglet and method of designing a winglet

A microelectronic module for cleaning a surface is described. The microelectronic module comprises at least one voltage converter for converting a provided first voltage into a higher, lower, or identical second voltage. The module also comprises at least one actuator. The actuator comprises at least one generator for generating an ionic current, an electrical plasma, harmonic components and/or an electrostatic field from the second voltage which is provided by the voltage converter. At least the voltage converter and the actuator are disposed on a thin-film, planar substrate. At least most of at least one object adhering to the surface is removed by the actuator.

Microelectronic module for cleaning a surface, module array, and method for cleaning a surface

An aircraft flow body includes a flow surface exposed to an airstream during flight, at least one structural component attached to an interior of the flow surface, at least one perforated area having a plurality of openings extending through the flow surface, a manifold positioned interior to the flow surface in fluid communication with the openings and upstream of the at least one structural component, and at least one suction duct having a first end in communication with the manifold and a second end placed exterior to the flow surface downstream of the structural component. The at least one suction duct includes a suction opening facing away from the first end and adapted for inducing a suction force into the at least one suction duct when the flow surface is exposed to the airstream during flight, thereby inducing a flow of air from through the openings to the suction opening.

Flow body for an aircraft for passive boundary layer suction

A wing for an aircraft, including a main wing and a wing tip device, a front blade and a rear blade of the wing tip device extending from an attachment end, a front blade leading edge extending in front of a rear blade leading edge and a front blade trailing edge extending in front of a rear blade trailing edge, in a chord direction, and at a front blade tip the front blade extending under a different dihedral angle than the rear blade at a rear blade tip. The front blade leading and trailing edges, as well as the rear blade leading and trailing edges have a tangent-continuous developing. The front blade leading edge extends tangent-continuously with the wing leading edge. The rear blade trailing edge extends tangent-continuously with the wing trailing edge. The front blade trailing edge extends behind the rear blade leading edge, in the chord direction.

Wing for an aircraft, and an aircraft comprising such a wing

A fixed wing of an aircraft, having a main wing extending over a half-span with a wing box including spars extending along the spanwise direction of the main wing, ribs arranged one in back of the other viewed in the spanwise direction, and an outer skin. The wing box includes a wing box base section (K) and a wing box adapter section, that forms the outer end area of the wing box, as viewed from the wing root, and is designed to secure a wing tip device. In its nominal state of construction, the dihedral angle of the wing box adapter section referring to the respective local spanwise direction continuously increases by at most 60 degrees from the outer rib of the wing box base section (K) up to the outermost rib of the wing box adapter section.

Fixed wing of an aircraft

A high-lift system on a wing with a curved nose and a leading-edge flap mounted via levers for movement between retracted and extended positions while expanding the airfoil profile, increasing its curvature and exposing a gap for guiding air from under the flap to above the wing. The levers form a four bar mechanism including first and second levers respectively pivotably connected at one end to spaced first and second points on the wing. The other ends of the levers are connected to opposite ends of a third lever forming part of the flap. The length and positions of the levers and the curvature of the wing nose are matched such that during initial extension from retracted position to an intermediate position the trailing edge of the flap blocks the gap between the flap and wing, and during further extension beyond the intermediate position the gap is exposed.

Growing community of inventors

Hamburg, Germany

Gerd Heller