Airbus Deutschland Gmbh

Eads Deutschland Gmbh

Airbus Operations Gmbh

Daimler Chrysler Ag

Thomas Lorkowski

Boris Grohmann

Frank Hermle

Peter Jaenker

Burkhard Gölling

Johann Reichenberger

Ulf Breuer

A high lift system with a main wing and regulating flaps, also bearing devices for the mounting of the regulating flaps, and positioning devices for the positioning of the regulating flaps, wherein the respective bearing device and/or positioning device is at least partially provided with a fairing, having a flow control device for purposes of controlling the flow around the high lift system with at least one inlet duct with at least one inlet, which device is located on or underneath the lower face of the high lift system, wherein at least one outlet duct for air is furthermore provided, which is connected with the inlet duct in a fluid-communicating manner, and has at least one outlet, which is located on the upper face in the region of at least one regulating flap of the high lift system.

High lift system for an aircraft

An aerodynamic body with an outside with a top and bottom in relation to the direction of airflow, with lateral end parts that form the lateral ends of the aerodynamic body when viewed across the direction of airflow, where in the interior of the aerodynamic body a duct with an airflow drive with a drive motor and a compressor means that is driven by the aforesaid and that is arranged in the duct is arranged, with at least one inlet at the bottom and/or at at least one of the lateral end parts of the aerodynamic body and with at least one outlet at the top of the aerodynamic body for influencing the airflow at the aerodynamic body is arranged, where in the duct a sleeve is arranged which is rotatable by means of a drive motor, which sleeve includes at least one recess which at a particular rotational position of the sleeve can be made to at least in part coincide with the outlet at the top of the aerodynamic body so that the air that has been compressed by the compressor flows through the recess in the sleeve and through the outlet, as well as a high-lift system comprising such an aerodynamic body.

Aerodynamic body and high-lift system comprising such an aerodynamic body

A wing of an aircraft has a mainplane, which has an upper face, a lower face and an aerodynamically shaped area. The wing has an additional airfoil which is articulated on the mainplane and can be extended from a retracted state with a slot area being opened between the mainplane and the additional airfoil. The wing also has a variable-position slot-varying apparatus which is arranged on the lower face, forms a part of the aerodynamic profile of the additional airfoil or mainplane when the additional airfoil is extended, and at least partially covers the slot area between the mainplane and the additional airfoil on the lower face when the additional airfoil is in the retracted state. The slot-varying apparatus can be varied between a curved configuration, in which it forms a part of an aerodynamic profile, and an extended configuration, in which it at least partially covers the slot area.

Wing of an aircraft

A system for reducing aerodynamic noise of a supplementary wing of an aircraft is provided. The supplementary wing is hinged to a main wing and is extendable when a gap region between the main wing and the supplementary wing is opened. The system includes a separating surface which can be moved into the gap region when the supplementary wing is extended and which extends at least partially along a separation flow line between a vortex flow region and a gap flow for the air flowing in the gap region. The separating surface is an n-stable surface which through an actuator device can be moved between at least one of the stable states and at least one additional state.

System for reducing aerodynamic noise at a supplementary wing of an aircraft

The invention relates to a linear, hydraulic pivot drive, especially for the flap control system of aerodynamic structures. Said pivot drive comprises a housing provided with ports for introducing a hydraulic medium, a piston which is arranged inside the housing and can be axially displaced by the effect of the hydraulic medium, and an output shaft which is provided with coarse threads and interacts with the piston in order to cover the axial displacement of the piston into a rotational movement. The invention is characterized in that the output shaft is integrated into the piston, the coarse threads running in the same direction and engaging in the piston, and the cross-section of the piston has a spline profile for effectively preventing a rotational movement of the piston.

Linear, hydraulic pivot drive

Rotor blade for a helicopter having an aerodynamic control flap, particularly a camber flap, is integrated essentially in the contour of the blade profile. The camber flap is swivellably arranged on an axis of rotation and is linked to a control rod of a control device outside the axis of rotation, for converting a linear movement into a swivelling movement of the control flap. The control device is disposed by way of roller bearings and bolts aligned in the span direction. Devices are provided which absorb by way of the control flap centrifugal forces of the control device resulting from the rotation of the rotor blade.

Rotor blade with control flaps

A rotor blade for a helicopter has a blade root for a fastening in the area of the rotor mast and a radially exterior blade tip. An aerodynamic control flap is integrated essentially in the contour of the blade profile is swivellably disposed in the rotor blade between the blade root and the blade tip. The control flap is disposed at its two ends in each case by way of roller bearings on bearing bolts aligned in the span direction of the rotor blade. The bearing of the control flap which is radially on the outside has devices which provide a support with respect to the centrifugal forces of the control flap upon the rotor blade resulting from the rotation of the rotor blade.

Rotor blade having a control flap

An aerodynamic component such as a helicopter rotor blade has an aerodynamic flow profile, a free end and a mounting end forming a blade root for attachment to a rotor mast. A blade section between the root and the free end has a leading edge and a trailing edge as viewed in the flow or chord direction. The blade is enclosed on its suction side and its pressure side with a respective skin. A nose flap or leading edge flap is secured to the leading edge by a bearing or hinge. The blade tilting angle is adjustable by piezo-drive elements arranged in at least one pair forming an actuator for each nose flap. The piezo-elements of a pair are arranged in the chord direction one behind the other and the pair is secured to the body of the blade by a fixed point positioned between the elements of a pair. The expansion and contraction from the piezo-element closer to the trailing edge is transmitted to the flap by a push rod. The expansion and contraction of the piezo-element closer to the leading edge is transmitted to the flap by a pronged pull-fork. The push rod and the pull-fork drive a free end of a lever secured to the flap, whereby a displacement of the push rod or of the pull fork causes the tilting adjustment of the flap by a push-pull action.

Growing community of inventors

Taufkirchen, Germany

Thomas Lorkowski