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.
Type:
Grant
Filed:
May 25, 2012
Date of Patent:
May 3, 2016
Assignee:
Airbus Defence and Space GmbH
Inventors:
Stefan Storm, Rudolf Maier, Andreas Wildschek
Abstract: A device for producing a three dimensional object from a powdery material by solidifying the powdery material through the application of energy includes a working surface, an application device for applying the powdery material onto the working surface, and a solidifying device for solidifying the powdery material applied onto the working surface. The application device can apply predefined, locally different amounts of powdery material and includes a transfer device, which can be magnetized and/or electrostatically charged and discharged, as well as a magnetizing and/or charging device.
Abstract: A sound absorber comprising a base body and a tongue (24). The base body has a bottom plate, a wall enclosing the bottom plate and an opening enabling the entry of air into the base body. The tongue has a fixed end, a free end and a central portion disposed between the fixed and the free end. The free end of the tongue is spaced from the wall and the bottom plate, and the central portion of the tongue is disposed to extend at least partially straight along a width direction. Furthermore, a sound absorber assembly can include at least two sound absorbers, and an engine, in particular, for an aircraft, comprising such a sound absorber and/or such a sound absorber assembly.
Type:
Grant
Filed:
August 28, 2014
Date of Patent:
April 5, 2016
Assignees:
Airbus Defence and Space GmbH, Rolls-Royce Deutschland Ltd & Co KG
Inventors:
Reinhard Pongratz, Christoph Richter, Max Kern, Daniel Redmann
Abstract: An emergency power supply system for providing hydraulic power and electric power in an aircraft includes a fuel cell having an electric outlet for providing electric power, a conversion unit couplable with at least one of an AC bus and a DC bus and the electric outlet, and at least one hydraulic pump having a reconfigurable electric motor and a motor control unit and being couplable with a hydraulic system for providing hydraulic power. The conversion unit is adapted for converting a supply voltage of the electrical outlet to at least one of an AC voltage matching a predetermined voltage at the AC bus and a DC voltage matching a predetermined voltage at the DC bus. The reconfigurable electric motor is couplable with the fuel cell and the AC bus and is adapted for being operated by the supply of electric power either from the fuel cell or the AC bus.
Type:
Application
Filed:
September 24, 2015
Publication date:
March 31, 2016
Applicants:
Airbus Operations GmbH, Airbus Defence and Space GmbH
Abstract: A method for image processing involves collecting image data of a scene as electromagnetic radiation and processing the image data to improve the signal-to-noise ratio of the image data. The image processing involves dividing a raw image that contains the image data into lines and columns, to create a raster image, superimposing a central raster filter element of a raster filter having an odd number of lines and an odd number of columns onto a raster image element, determining the brightness values of each of the raster image elements covered by the raster filter, wherein except for the central raster filter element, every other raster filter element has an individual light-reducing property, and adding up the brightness values to produce a total brightness value, and assigning this total brightness value to the raster image element covered by the central raster filter element.
Abstract: A solid propellant gas generator releases a flowing mixture from a solid propellant, separated from a surrounding area, into the surrounding area. The solid propellant gas generator includes a cooling system for cooling the flowing mixture. The cooling system has at least one feed device for feeding a gas from the surrounding area to the flowing mixture in order to mix the flowing mixture prior to entering into the surrounding area with the gas from the surrounding area.
Type:
Grant
Filed:
September 11, 2013
Date of Patent:
March 15, 2016
Assignee:
Airbus Defence and Space GmbH
Inventors:
Jens Lemke, Elizabeth Richter, Sebastian Schulz
Abstract: A data transmission between a device and a first and a second optical maintenance port involves a transmission reflector in the form of a solid-state bound data line having a gap and a Y coupler. This allows recording of the communication between the device to be read out and the first optical maintenance port in real time by means of the second optical port. Likewise, communication by means of electromagnetic energy is possible between the first and the second optical maintenance ports.
Abstract: A fiber composite component includes a composite including cured matrix material and a fiber material embedded therein. At least one partial area of the fiber composite component is provided with at least one thread, which undulates as it extends along a surface area of the composite, so that sections of the thread alternately run inside of the composite and outside of the composite. An adhesive arrangement for such fiber composite components is also disclosed. Finally, methods for manufacturing such a fiber composite component or for manufacturing such an adhesive arrangement are disclosed.
Abstract: An air generation unit for an aircraft, an air generation arrangement, an aircraft and a method for operating an air generation unit in an aircraft are described. The air generation unit for an aircraft includes an air supply means and a control unit. The air supply means is configured to supply air to an air conditioning system of an aircraft's cabin. The air supply means is further or alternatively configured to supply air to a flow control system of an aircraft. The control unit is configured to provide, during cruise conditions of the aircraft, a larger amount of the air to the air conditioning system than to the flow control system. The control unit is further configured to provide, during take-off and/or landing conditions of the aircraft, a larger amount of the air to the flow control system than to the air conditioning system.
Abstract: A circuit for frequency-dependent matching of a high-frequency amplifier stage includes high-frequency stage with an output to a total high-frequency path that divides a total frequency band into a plurality of partial frequency paths for respectively preset partial frequency bands. The outputs of the plurality of partial frequency paths are reunited again into the total high-frequency path, following the processing of the partial frequency bands of these partial frequency paths. The partial frequency paths include a matching network surrounded by a first and second pass filter. At least one partial frequency path is switchable, when a control signal is supplied thereto.
Abstract: A control force transmission arrangement for an aircraft is provided. A transmission device has a first and a second force transmission point, and a coupling unit disposed between them. The coupling unit has a first and a second side element and a connecting element. The first and the second side elements are each connected to the first force transmission point and to the connecting element. At least the first side element has an element for altering the length of the side element. The second force transmission point is provided on the connecting element and is adjustable at least between a first and a second position.
Abstract: A nozzle arrangement for a gas turbine engine includes an engine nozzle and an ejector nozzle arranged axially downstream thereof. A gap S is formed between the outlet of the engine nozzle and the inlet of the ejector nozzle, and a flange which reduces the gap S is arranged at the outlet of the engine nozzle.
Abstract: An engine for propelling an aircraft includes an annular fuel cell arrangement having at least one fuel cell, at least one electric motor couplable to the fuel cell arrangement, at least one fan couplable to the electric motor and a cowling having an inlet and an outlet nozzle. The fuel cell arrangement is arranged inside the cowling, the at least one fan is arranged between the inlet and the fuel cell arrangement inside the cowling, the electric motor is operable under consumption of electric power delivered by the fuel cell arrangement and the at least one fan is designed to produce a thrust force by creating an accelerated airflow at the outlet nozzle. The engine is extremely efficient and comprises a distinct low noise.
Type:
Application
Filed:
November 21, 2014
Publication date:
October 29, 2015
Applicants:
Airbus Operations GmbH, Airbus Defence and Space GmbH
Abstract: The invention relates to a drive device for an aircraft, at least comprising a battery for storing electrical energy, an electric motor for driving a propeller, a conducting means for transferring the electrical energy from the battery to the electric motor, and a first control means for controlling the electric motor. The invention is characterized in that: the battery is a lithium-air battery; the electric motor is a high-temperature superconductor motor; at least one store is provided for a coolant and a cooling system which is connected to the store for cooling the high-temperature superconductor motor, the cooling system comprising a second control means for controlling the cooling system; a first means is provided for variably arranging the lithium-air battery and/or a second means is provided for variably arranging the store in the aircraft; and a third control means is provided for controlling the first and/or the second means.
Abstract: A sensor for detecting and localizing laser beam sources, includes a beam-sensitive detector which is arranged in the image field of an imaging optic, an electric image processing device which is connected to the detector, and an optical diffraction element which is arranged in the beam path. The diffraction properties of the optical diffraction element are such that incident laser light on different wavelength bands produce diffraction patterns with different shapes, and the electronic image processing device is designed such that it can detect and evaluate the different forms of the diffraction pattern.
Abstract: An unmanned aircraft includes a propulsion system having a diesel or kerosene internal combustion engine and a charger device for engine charging. The propulsion system can be a hybrid propulsion system or a parallel hybrid propulsion system.
Type:
Application
Filed:
October 22, 2013
Publication date:
October 8, 2015
Applicant:
Airbus Defence and Space GmbH
Inventors:
Juergen Steinwandel, Florian Stagliano, Jan Van Toor
Abstract: A circuit is designed to be executed in a predeterminable operating mode of a plurality of operating modes. The circuit includes a first functional unit and a second functional unit. The first functional unit is designed as a static functional unit that in each of the plurality of operating modes of the circuit carries out a consistent function. The second functional unit is designed as an adaptable functional unit that is designed to be configured, prior to the circuit being put into service, according to a first configuration of a plurality of different configurations and during the operating time of the circuit to maintain the first configuration so that the first configuration of the second functional unit defines the predeterminable operating mode of the circuit. This makes it possible to reduce the verification expenditure for the circuit because verification can be limited to the adaptable functional unit.
Type:
Application
Filed:
March 17, 2015
Publication date:
September 24, 2015
Applicant:
Airbus Defence and Space GmbH
Inventors:
Daniel J. Muench, Michael Paulitsch, Michael Honold, Wolfgang Schlecker
Abstract: An ion dosage apparatus for an energy storage apparatus includes a first energy guiding device with a first energy supply device and a separating device. The separating device is configured to control, via supplied energy, a number of ions that are transported around the first energy guiding device and/or blocked.
Type:
Grant
Filed:
August 11, 2014
Date of Patent:
September 8, 2015
Assignee:
Airbus Defence and Space GmbH
Inventors:
Alexander Ohnesorge, Michael Pilawa, Juergen Steinwandel, Michael Hofmann, Alexander Kaiser
Abstract: A diaphragm arrangement is disclosed to be fitted to a structural component or fixing ring for the purpose of generating sound. The diaphragm arrangement includes two piezo crystals fitted opposite one another on either side of an electrically conductive diaphragm, which can oscillate, and the piezo crystals are each fastened to the diaphragm. The piezo crystals are each electrically conductively connected to a contact plate on their opposing sides.
Abstract: Aircraft with an emission-free drive and method for emission-free driving of an aircraft. The aircraft includes a drive device, having a flapping wing device, structured and arranged to generate thrust, a lift device structured and arranged to generate lift, and a heat engine, having at least one flat-plate Stirling engine drivable by solar thermal radiation, structured and arranged to convert thermal energy into kinetic energy to drive the drive device. The flapping wing device includes at least one flapping wing, which is pivotable transverse to a flight direction.