Airbus Operations Gmbh

Airbus Deutschland Gmbh

Klaus-Peter Neitzke

Burkhard Gölling

Karin Bauer

Heinz Hansen

Burkhard Goelling

Winfried Kupke

Christian Bolzmacher

Kai-Christoph Pfingsten

Rolf Radespiel

Andreas Schroeder

Christoph Jensch

Juergen Frey

Veit Hildebrand

Winfried Kuehn

Eric Wilhelmus Maria Roosenboom

Andreas Ulrich

Burkhard GÖLLING

Jürgen Frey

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 vortex generator is useable in a model in a fluid-dynamic channel. In order to save time during the development of vehicles, in particular, aircraft, to save wind tunnel time, it is suggested to configure the vortex generator to be switchable. A switchable vortex generator can be used, in particular, on models in fluid-dynamic channels and in fluid-dynamic channel tests.

Switchable vortex generator and array formed therewith, and uses of the same

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 present invention provides a method and a system for determining forces which act on a body with a controlled volume which is provided inside the flow tunnel and in which the body is arranged. A first measuring means is used to measure a pressure distribution for each surface defining the controlled volume. A second measuring means measures a velocity field for each defining surface of the controlled volume. Furthermore, a calculation unit is provided for calculating the forces acting on the body as a function of the pressure distributions and velocity fields measured for the defining surfaces of the controlled volume.

Method and system for determining a force acting on a body

The invention relates to a vortex generator (), in particular for a model () in a fluid-dynamic channel. In order to save time during the development of vehicles, in particular aircraft, in particular to save wind tunnel time, it is suggested to configure the vortex generator () switchable. Further, the invention relates to various uses of such a switchable vortex generator (), in particular on models in fluid-dynamic channels and in fluid-dynamic channel tests.

Apparatus for adjusting pitch angle of propeller blades of a variable-pitch propeller. The blades being adjustable in a first blade pitch-angle range with positive pitch angles, in a second blade pitch-angle range, and in a third blade pitch-angle range with negative pitch angles. The second blade pitch-angle range is an intermediate range located between the first and the third blade pitch-angle range, which includes the pitch-angle range where blade drag is a minimum, and ranges of positive pitch angles with low thrust and of negative pitch angles with low reverse thrust. The apparatus provides adjustment of the propeller blades from the first to the third blade pitch-angle range and vice versa, and is designed to be operated so that at least a first group of propeller blades can be rotated through the second blade pitch-angle range, while propeller blades in another group are in a positive blade pitch-angle range.

Adjusting apparatus for adjusting the pitch angle of propeller blades, variable-pitch propeller, control function which can be implemented in a computer, and method for adjusting the pitch angle of propeller blades

Growing community of inventors

Bremen, Germany

Klaus-Peter Neitzke