Airbus Operations Gmbh

Navasto Gmbh

Airbus Defence and Space Gmbh

Matthias Bauer

Wolfgang Nitsche

Burkhard Gölling

Jakob Lohse

Frank Haucke

Bruno Stefes

Burkhard Goelling

Inken Peltzer

Burkhard GÖLLING

A flow guide body for an aircraft includes a main body having an outer aerodynamic surface having a plurality of outlet openings, and flow control devices, each having an inlet, an interaction chamber, a first outlet and a second outlet. A first control inlet is connected to the interaction chamber at the first side of the chamber axis. The outlets are each connected to outlet openings in the aerodynamic surface. Each outlet has a control outlet. A second flow control device is arranged such that one outlet is connected with the inlet of the first flow control device. One of the control outlets of the first flow control device is connected to the first control inlet of the first flow control device, and the other of the control outlets of the first flow control device is connected to the first control inlet of the second flow control device.

Flow guide body for an aircraft

A method for generating fluid pulses is provided. The device comprises a first channel with a first fluid inlet and a second channel with a second fluid inlet, in which the first fluid inlet and second fluid inlet are substantially situated opposite each other. The first channel comprises a first control outlet at the height of the first fluid inlet, and the second channel comprises a second control outlet at the height of the second fluid inlet, in which the respective control outlet is located in front of the respective fluid inlet in relation to the inflowing direction of the fluid inlet.

Device for generating fluid pulses

The invention relates to fluid actuator for influencing the flow along a flow surface through ejection of a fluid. By means of a like fluid actuator, a continuous flow is distributed to at least two outlet openings in order to generate fluid pulses out of these outlet openings. Control of this distribution takes place inside an interaction chamber which is supplied with fluid flow via a feed line. Into this interaction chamber there merge at least two control lines via control openings to which a respective different pressure may be applied. Depending on the pressure difference at the control openings, the flow in the interaction chamber is distributed to the individual outlet openings.

Fluid actuator for influencing the flow along a flow surface, as well as blow-out device and flow body comprising a like fluid actuator

A flow body having a surface, a leading edge has an active flow control system. The active flow control system includes a plurality of openings, at least one control pressure varying device and at least one fluidic actuator with an interaction chamber having an inlet connectable to an air source, at least two outlets and at least two control pressure ports. The openings are distributed along or parallel to the leading edge in a side-by-side relationship and extend through the surface. The control pressure varying device is connected to the at least two control pressure ports in a fluidic manner, wherein the control pressure varying device is adapted to bring about the flow of the fluid at least majoritarily into a respective one of the outlets. Each of the outlets is connected to one individual opening of the plurality of openings.

Flow body having a leading edge, a surface and an active flow control system and vehicle comprising at least one such flow body and an air source

An aircraft with aerofoils including a main wing and a control flap that includes an adjustment flap. The aircraft includes an actuator for the control flap, as well as a sensor device for acquiring the position of the control flap, an arrangement of flow-influencing devices for influencing the fluid that flows over a segment of the main wing, and flow-state sensor devices for measuring the flow state. The aircraft includes a flight control device connected to the sensor device for acquiring the position of the control flap and to the flow-state sensor devices, and connected to the actuator and flow-influencing devices for transmitting actuating commands, and a flight-state sensor device connected to the flight control device for transmitting flight states. The flight control device includes a function that selects the flow-influencing devices that are operated for optimizing local lift coefficients on the aerofoil, depending on the flight state.

Aircraft with a control device

A fluid actuator for influencing the flow along a flow surface by ejecting a fluid flowing through the fluid actuator is described. The fluid actuator has at least two outlet lines with outlet openings at the respective ends thereof, and a feed line connected to the outlet lines for feeding fluid at a supply pressure, a flow direction diverting device into which the feed line opens and out of which the outlet lines open, and an adjusting device coupled to the flow direction diverting device to control the latter. The adjusting device is configured so the fluid is conducted successively in a cyclic sequence into each of the outlet lines. A discharge device for discharging a fluid out of a flow body, and a flow body having a multiplicity of discharge openings and a discharge device of said type are also described.

Growing community of inventors

Berlin, Germany

Matthias Bauer