Eads Deutschland Gmbh

Daimler Chrysler Ag

Daimler-benz Ag

Mtu Aero Engines Gmbh

Frank Hermle

Peter Jaenker

Thomas Lorkowski

Erwin Bayer

Boris Grohmann

Peter J&auml;nker

Peter Janker

A friction-welding device for the integral joining of components, having an oscillator, which generates a periodic movement of a component and a welding surface provided thereon relative to another, static component and a welding surface provided thereon, with directions of movement parallel to the welding surfaces, having a compression device which presses the welding surfaces together, and a cartridge which accommodates the moved component. The oscillator includes two or a greater, even number of piezoactuators, which are arranged in pairs on a line of application and are able to be prestressed with respect to the cartridge from opposite sides under pressure generation and are able to be moved in a synchronous, oscillating manner together therewith and the component.

Friction-welding device

A form-adaptable electrode structure in layer construction includes at least two conductor layers, between which an insulating layer is disposed, the conductor layers having first and second electrode strips arranged in each case in parallel, and the electrode strips of the first conductor layer being arranged at an angle with respect to the electrode strips of the second conductor layer, so that a net-like structure is formed, and the first electrode strips of the first conductor layer being conductively interconnected with the first electrode strips of the second conductor layer, and the second electrode strips of the first conductor layer being conductively interconnected with the second electrode strips of the second conductor layer via the insulating layer at intersections of the net-like structure.

Form-adaptable electrode structure in layer construction

A piezoelectric actuating device for controlling a flap on a rotor blade of a helicopter includes a piezo element arrangement including at least one piezoelectric stack actuator. A power transmission frame is coupled to the piezo element arrangement, the power transmission frame including an abutment and a driven element and generating a force therebetween from a change in length of the piezo element arrangement upon an excitation thereof, the force acting transversely to a direction of a centrifugal force of the rotor blade. A first holding device is provided including a pair of first flexible straps configured to fix the power transmission frame relative to the rotor blade in the direction of the centrifugal force and to allow the power transmission frame to move relative to the rotor blade transversely to the direction of the centrifugal force within a limited range. A second holding device is provided including a pair of second flexible straps configured to fix the abutment relative to the rotor blade transversely to the direction of the centrifugal force and to allow the abutment to move relative to the rotor blade in the direction of the centrifugal force within a limited range.

Piezoelectric actuating device for controlling the flaps on the rotor blade of a helicopter

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.

Aerodynamic component with a leading edge flap

The piezoelectric actuator consists of at least two disk-shaped congruent bending elements which each have a carrier plate made of a hard-elastic material with a layer of a piezoelectric material applied to one or both sides. Two bending elements respectively are connected with one another by way of at least two bending joints arranged on the circumference of the carrier plates.

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Munich, Germany

Frank Hermle