Airbus Deutschland Gmbh

Daimlerchrysler Aerospace Airbus Gmbh

Peter May

Detlev Schwetzler

Susanne Wyrembek

Klaus Muthreich

A system and a method according to the invention reduce wake turbulence of an aircraft in that a component affixed to the extremity of the wing of an aircraft disturbs the rolling action of the air in the region of the outer wing by periodic hingeing movements.

System and method for reducing airfoil vortices

To control and particularly steepen the landing glide path of an aircraft, a respective aerodynamic component mounted on each wingtip includes a fixed plane member and a pivotable control element pivotally connected to the fixed plane member. The pivot axis is perpendicular to the major plane of the wing. The pivotable control element can be selectively pivotally deflected about the pivot axis relative to the fixed plane member, so as to thereby increase the overall drag without influencing the overall lift of the aircraft. This achieves a fine adjustment that is superimposed on the basic landing configuration established by the setting of the flaps, spoilers, engine thrust, etc. By increasing the drag without influencing the lift, this steepens the landing glide path slope.

Method and device for steepening a landing approach of an aircraft

A method for improving the precision of wind tunnel measurements provides a correction to reduce the influence of a suspension device. A model, such as an aircraft model, is held by the suspension device in a wind tunnel and has multiple suspension wires. By attaching one or more sleeves to each suspension wire, a plurality of measurements with identical model configuration are capable of providing data for extrapolating corrected measurement values for a plurality of aerodynamic characteristic variables measurable in a wind tunnel. Examples of sleeves include a slit along the sleeve length and an inner diameter of the sleeves selected such that the sleeve is capable of being pressed onto and removed from a suspension wire or a sleeve of lesser outer diameter.

Method and device for improving accuracy of wind tunnel measurements, particularly for correcting the influence of a mounting device

An aerodynamic including a main body and a control member. The main body is configured to be connected to a wing of an aircraft. The control member is connected to the main body, the control member including a fixed member secured to the main body and a pivotable member configured to increase a drag of the aircraft without substantially changing a lift of the aircraft.

Aerodynamic component for controlling a landing guide path of an aircraft

An auxiliary flap is movably arranged on a planar trailing edge of an aerodynamic element such as a wing, rudder, stabilizer, or flap. The auxiliary flap is rotatable and/or slidable relative to the aerodynamic element, to move selectively into three positions. In a first position, a free edge of the auxiliary flap protrudes into an airflow boundary layer on one side of the aerodynamic element, to decrease lift. In a second position, a free edge of the aerodynamic element protrudes into an airflow boundary layer on the other side of the aerodynamic element, to increase lift. In a third neutral position, the auxiliary element does not protrude into either boundary layer, so as not to influence lift. The auxiliary flap is simple and rapidly acting. The flap protrudes substantially perpendicularly into the boundary layer flow. The auxiliary flap has a planar plate shape.

Flap arrangement for varying the aerodynamic lift generated by an aerodynamic element of an aircraft

An arrangement of an airfoil, such as a main wing of an aircraft, includes a close-mounted engine on a short pylon connected to the airfoil, an inboard slat arranged inboard from the engine pylon along the leading edge of the airfoil, and an auxiliary high lift device. An open cut-out space is formed between the outboard edge of the inboard slat, the engine pylon, and the leading edge of the airfoil when the inboard slat is extended. The auxiliary high lift device is configured and arranged to be extendable into an extended position in which it aerodynamically covers or closes the cut-out space. The auxiliary high lift device is a movable high lift component that can be retracted into a retracted position in which it is recessed and integrated into the outer contour of the engine nacelle and/or the pylon. Thereby, the structural arrangement and mechanisms necessary for extending and retracting the auxiliary high lift device are simplified, and the weight and costs are reduced.

Growing community of inventors

Bremen, Germany

Peter May