Abstract: A DC switching device has at least one switching unit which is arranged between two terminals. Further, the DC switching device has a control unit for controlling the at least one switching unit. The switching unit has a first and a second semiconductor switching element, which are arranged in parallel with one another, the first switching element being a high-voltage switching element and the second switching element being a low-power-loss switching element. The switching unit is controllable by the control unit in such a way that, when the switching unit is switched off, initially the second switching element is switched to be non-conductive, and subsequently the first switching unit is switched to be non-conductive, and when the switching unit is switched on, initially the first switching element is switched to be conductive and subsequently the second switching element is switched to be conductive.

Abstract: A DC switching device has at least one switching unit which is arranged between two terminals. Further, the DC switching device has a control unit for controlling the at least one switching unit. The switching unit has a first and a second semiconductor switching element, which are arranged in parallel with one another, the first switching element being a high-voltage switching element and the second switching element being a low-power-loss switching element. The switching unit is controllable by the control unit in such a way that, when the switching unit is switched off, initially the second switching element is switched to be non-conductive, and subsequently the first switching unit is switched to be non-conductive, and when the switching unit is switched on, initially the first switching element is switched to be conductive and subsequently the second switching element is switched to be conductive.

Abstract: A drive system for a helicopter includes a main drive for driving a rotor the helicopter, a flywheel mass battery including at least one flywheel, a first transmission coupling the flywheel mass battery with the main drive such that, during operation of the main drive, output can be transferred from the main drive to the flywheel mass battery, and a second, variable transmission connecting the flywheel mass battery to the rotor of the helicopter such that a predetermined output can be transferred to the rotor through adjustment of a transmission ratio of the variable transmission.

Abstract: An electrical energy storage device has a plurality of electrochemical energy storage cells for collecting, supplying and storing electrical energy, each of which has a first electrical terminal and a second electrical terminal, and a contacting device for contacting the first and second electrical terminals of the energy storage cells, wherein the contacting device has a multi-layered structure and has at least one insulation layer and a conductor layer. A vehicle with such an electrical energy storage device is also described.

Abstract: A hybrid drive system for aircraft, in particular helicopters, with at least one energy generating module having an internal combustion engine and a generator that can be powered by the latter to generate electrical energy, and at least one electric motor for powering a drive means of the aircraft.

Abstract: A drive system for a helicopter includes a main drive for driving a rotor the helicopter, a flywheel mass battery including at least one flywheel, a first transmission coupling the flywheel mass battery with the main drive such that, during operation of the main drive, output can be transferred from the main drive to the flywheel mass battery, and a second, variable transmission connecting the flywheel mass battery to the rotor of the helicopter such that a predetermined output can be transferred to the rotor through adjustment of a transmission ratio of the variable transmission.

Abstract: The rotors of a helicopter are directly connected with electric high-torque motors, and are powered by the latter. Energy generation and rotor drive are separate from each other. The high-torque motor of the main rotor is pivoted to the cabin canopy, so that it can be tilted together with the main rotor.

Abstract: The rotors of a helicopter are powered by electric motors. The electrical energy required for this purpose is produced by a motor-generator unit, which comprises one or more internal combustion engines. The motor-generator unit can be secured under the cabin floor. This yields a hybrid helicopter that can set the rotational frequency of the rotors within a large interval.

Abstract: The invention relates to a method for controlling a rotary wing aircraft with at least one main rotor, comprising a rotor head and rotor blades (12), arranged such that each rotor blade (12) is supported to be able to pivot or twist around the lengthwise axis of its blade on the rotor head and has at least one control flap (14) that can be deflected. According to the invention, the rotary wing aircraft is controlled solely by changing the respective blade pitch angle (X) by means of changing the flap control angle (Y) of the assigned control flaps (14) by the resulting blade pitch angle (X3) being set by applying the resulting flap angle (Y4) to the control flap (14), and the flap angle (Y4) being computed using an algorithm, the input quantities comprising the flap control angle (Y1) depending on the pilot primary control and the flap correction angle (Y2) depending on the secondary control.

Abstract: A motorized spindle drive for an actuator, particularly for an aerodynamically effective surface of an aircraft, may have a spindle and a motor that comprises a mechanical transmission element engaging the spindle in order to drive said spindle and causing a relative movement in the axial direction between the spindle and the motor and that is connected to an element that is fixed in place relative to the motion of the spindle, said element absorbing the torque of the motor. According to the invention, the bearing absorbing the torque of the motor comprises a detachable coupling that detaches upon a predetermined torque being exceeded and releases the motor in the sense of a free movement in the axial direction of the spindle relative to the fixed element.

Abstract: A rotor blade comprises an inner rotor blade root area, a rotor blade main area disposed adjacent to the inner rotor blade root area along a length of the rotor blade and having an aerodynamically effective rotor blade profile, the profile including a nose area and a rear edge area, and a rotor blade tip disposed adjacent to the rotor blade main area along the length of the rotor blade. The rotor blade tip is configured to be deformable relative to the rotor blade main area and is operatively connected to a first actuator device. The first actuator device is configured to initiate a vertical movement of the rotor blade tip upwards or downwards relative to the lift direction. The vertical movement starts from a neutral position relative to the rotor blade main area.

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: 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.

Abstract: An apparatus for producing a holding or transmission frame (12, 20) for an electrostrictive actuator, in particular, a stacked piezoactuator (5) includes the following steps: a) a winding spindle (52), corresponding to the shape of the inner periphery of the frame (12, 20), is wound with several layers of a unidirectional prepreg for forming a laminate body; b) the laminate body is hardened; c) the hardened laminate body in the frame is cut by sections parallel to the direction of winding. An electrostrictive drive (100) includes an electrostrictive actuator (5) in which the length varies during actuation, and a transmission frame (12) that surrounds the actuator, is connected to the actuator for initiating the variation in length of the actuator and for amplifying the actuator, the transmission frame (12) being made of a prepreg that is wound in the laminate body and hardened.

Abstract: The invention relates to a motorized spindle drive for an actuator, particularly for an aerodynamically effective surface of an aircraft, having a spindle and a motor that comprises a mechanical transmission element engaging the spindle in order to drive said spindle and causing a relative movement in the axial direction between the spindle and the motor and that is connected to an element that is fixed in place relative to the motion of the spindle, said element absorbing the torque of the motor. According to the invention, the bearing absorbing the torque of the motor comprises a detachable coupling that detaches upon a predetermined torque being exceeded and releases the motor in the sense of a free movement in the axial direction of the spindle relative to the fixed element.

Abstract: The invention relates to a method for controlling a rotary wing aircraft with at least one main rotor, comprising a rotor head and rotor blades (12), arranged such that each rotor blade (12) is supported to be able to pivot or twist around the lengthwise axis of its blade on the rotor head and has at least one control flap (14) that can be deflected. According to the invention, the rotary wing aircraft is controlled solely by changing the respective blade pitch angle (X) by means of changing the flap control angle (Y) of the assigned control flaps (14) by the resulting blade pitch angle (X3) being set by applying the resulting flap angle (Y4) to the control flap (14), and the flap angle (Y4) being computed using an algorithm, the input quantities comprising the flap control angle (Y1) depending on the pilot primary control and the flap correction angle (Y2) depending on the secondary control.

Abstract: A deformable aerodynamic profiled member has a front profile area and a rear profile area in the outflow area. It is bounded by shells on the pressure side and/or on the suction side, converging in a rear profile edge (6). D33 piezo actuators are provided in at least some locations for deformation of the profiled member. The piezo actuators are aligned such that their length changes essentially in the direction of the planes of the shells when acted upon by electricity.

Abstract: A device for generation of hydrogen gas by dehydrogenation of hydrocarbon fuels. The device includes a fuel reservoir connected to a reactor by a fuel line to supply said reactor with fuel. The reactor has a first discharge for recycling of residual hydrocarbons generated during dehydrogenation to the fuel reservoir and optionally cooperates with a catalyst. The fuel reservoir may contact a heat exchanger by the fuel line and the first discharge. The fuel may be preheated by the heat exchanger which may be introduced to the reactor by the fuel line and the reactor may have a heating device for heating the introduced fuel to reaction temperature. The residual fuel generated by dehydrogenation in the reactor may be cooled by the heat exchanger and may be returned to the fuel reservoir. The reactor may have a second discharge for the extraction of the hydrogen gas generated on dehydrogenation.

Abstract: A rotor blade comprises an inner rotor blade root area, a rotor blade main area disposed adjacent to the inner rotor blade root area along a length of the rotor blade and having an aerodynamically effective rotor blade profile, the profile including a nose area and a rear edge area, and a rotor blade tip disposed adjacent to the rotor blade main area along the length of the rotor blade. The rotor blade tip is configured to be deformable relative to the rotor blade main area and is operatively connected to a first actuator device. The first actuator device is configured to initiate a vertical movement of the rotor blade tip upwards or downwards relative to the lift direction. The vertical movement starts from a neutral position relative to the rotor blade main area.

Abstract: A piezoelectric expansion actuator for d33 piezoelements, which allows vibrations in structures to be suppressed. An expansion actuator (1) includes a piezoelectric stack (2), which consists of d33 piezoelectric elements and is arranged between output elements (4), which are attached to the surface of the structure (7). The invention applies to a piezoelectric extension actuator, which is used to control vibrations in structures. Alternatively, in order to damp vibrations between the main gearbox of a helicopter rotor and the cellular structure of the cockpit, a power application point of the output element (18, 19, 180, 190; 35, 36) is arranged at a distance from the corresponding end plate of the piezoelectric stack (22, 220; 31, 32, 33) in the axial direction (X).