Abstract: A device for reducing structural vibrations of airfoils in an aircraft comprises, in the region of the airfoil tips, at least one force generator acting substantially in the direction of movement of the vibrations. This arrangement has the advantage that such a force generator is considerably less susceptible to wear than conventional aerodynamic flaps and therefore effective vibration damping is possible with a reduced outlay on maintenance and greater efficiency.

Abstract: A force generator for introducing vibrational forces into a structure for vibration control of the structure includes an inertial mass, at least one actuator for generating a vibratory movement of the inertial mass relative to the structure, and a drive circuit constructed from components for driving the at least one actuator. At least part of the inertial mass is formed by one component of the drive circuit.

Abstract: A noise reduction system for connecting a noise source with a body, having at least one piezoactuator for suppressing a noise transmission from the noise source to the body. The noise reduction system has a first carrying structure to be connected with the noise source and a second carrying structure to be connected with the body. The at least one piezoactuator is positioned in series with the carrying structures and connects them with each other, such that the at least one piezoactuator forms a structural loaded part.

Abstract: A device for reducing structural vibrations of aerofoils in an aircraft comprises, in the region of the aerfoil tips, at least one force generator (24a) acting substantially in the direction of movement of the vibrations. This arrangement has the advantage that such a force generator (24a) is considerably less susceptible to wear than conventional aerodynamic flaps and therefore effective vibration damping is possible with a reduced outlay on maintenance and greater efficiency.

Abstract: The present invention relates to an acoustic absorber that is particularly suitable for aircraft engines and has a honeycomb-shaped 3-dimensional structure, which absorbs engine noise when used in an engine. The structure has a plurality of folded honeycomb structures formed by folding a flat semi-finished product.

Abstract: Minimizing dynamic structural loads of an aircraft, introduced by an external excitation, which, includes generating a signal (x) indicative of the external excitation; deriving signals (y) of pre-controlling for actuating control elements of the aircraft from the excitation indicating signal (x) in accordance with a pre-controlling rule, so as to reduce the dynamic structural loads introduced to the aircraft; generating an error signal (e, e*) representing performance of said pre-controlling; optimizing the pre-controlling rule by the error signal (e, e*) and/or the excitation indicating signal (x) so as to minimize the dynamic structural loads.

Abstract: Device and process for oscillation insulation in a transmission path. The device includes a first body structured and arranged to undergo an oscillation movement, at least one rigid connection element, a second body connected to the first body via the at least one rigid connection element, and an actuator device attached to the at least one connection element. A sensor unit is arranged in an interface area of the at least one connection element, and a regulator unit, connected to the sensor unit, is arranged to control the actuator device to perform an elastic deformation equivalent to an oscillation movement of the first body. The instant abstract is neither intended to define the invention disclosed in this specification nor intended to limit the scope of the invention in any way.

Abstract: Device and process for oscillation insulation in a transmission path. The device includes a first body structured and arranged to undergo an oscillation movement, at least one rigid connection element, a second body connected to the first body via the at least one rigid connection element, and an actuator device attached to the at least one connection element. A sensor unit is arranged in an interface area of the at least one connection element, and a regulator unit, connected to the sensor unit, is arranged to control the actuator device to perform an elastic deformation equivalent to an oscillation movement of the first body. The instant abstract is neither intended to define the invention disclosed in this specification nor intended to limit the scope of the invention in any way.

Abstract: Minimizing dynamic structural loads of an aircraft (2), introduced by an external excitation (1), which, comprises generating a signal (x) indicative of the external excitation (1); deriving signals (y) of pre-controlling for actuating control elements of the aircraft (2) from said excitation indicating signal (x) in accordance with a pre-controlling rule, so as to reduce the dynamic structural loads introduced to the aircraft (2); generating an error signal (e, e*) representing performance of said pre-controlling; optimizing the pre-controlling rule by said error signal (e, e*) and/or said excitation indicating signal (x) so as to minimize the dynamic structural loads.

Abstract: The present invention relates to an acoustic absorber that is particularly suitable for aircraft engines and has a honeycomb-shaped 3-dimensional structure, which absorbs engine noise when used in an engine. The structure has a plurality of folded honeycomb structures formed by folding a flat semi-finished product.

Abstract: A capacitor includes an anode body, a dielectric layer adjacent to the anode body, a cathode layer adjacent to the dielectric layer, and an enclosure that substantially encloses the anode body, the dielectric layer, and the cathode body. The enclosure has an upper side and an underside and is made of a castable material. The capacitor includes an anode contact having a contact section on the underside of the enclosure, an anode conductor that connects the anode body to the anode contact, and a cathode conductor that contacts the cathode layer and that exits the enclosure. The cathode conductor is a plate having holes at a portion of the cathode conductor inside the enclosure. The holes are at least partially filled with castable material.

Abstract: The invention relates to a capacitor with a capacitance (1), comprising an anode body (2) with a dielectric layer (3) and a cathode layer (4), which is enclosed by an enclosure (5) with an upper side (6) and a underside (7). Further, the capacitor comprises an anode conductor (8) that contacts the anode body (2) and is connected to an anode contact (9), which feature a contact section (10) arranged on the underside (7) of the enclosure (5). Further, the capacitor comprises a cathode conductor (11) that contacts the cathode layer (4), which is fixed to the upper side of the capacitance (1), which exits the enclosure (5) in a straight line, and which is connectively connected to a cathode contact (12) arranged on the underside of the enclosure (5). By dispensing with bending the cathode plate, volume utilization can be improved.

Abstract: A molding system has a slide displaceable parallel to an axis through a relatively long stroke relative to a stationary overhead extruder head, a center support fixed on the slide, and a pair of end supports displaceable axially through relatively short strokes on the slide between inner and outer end positions. A pair of inner mold halves carried on the center support are directed axially oppositely therefrom toward the end supports. Respective outer mold halves carried on the end supports are axially engageable with the respective inner mold halves in the inner positions of the end supports. An end-support drive connected between the slide and the end supports moves the end supports between their end positions and a slide drive connected to the slide moves the slide axially relative to the head. Each of the end-support drives includes a respective motor mounted on the slide.

Abstract: Body or structural noise transmitted through a connector such as a strut, that connects a noise source, such as an engine, to an enclosure, such as a passenger cabin or cell of a helicopter, is suppressed by at least one piezoactuator which is excited to counteract any vibrations of the strut caused by body noise so that body noise vibrations are cancelled or at least substantially suppressed. The excitation of the piezoactuator is controlled in closed loop fashion in response to feedback signals from a sensor secured to the connector.