Mtu Aero Engines Gmbh

Airbus Defence and Space Gmbh

Eads Deutschland Gmbh

Airbus Operations Gmbh

Daimler Chrysler Ag

Deutsches Zentrum Fuer Luft-und Raumfahrt E.v

Dornier Gmbh

Daimler-benz Ag

Airbus (sas)

Juergen Steinwandel

Erwin Bayer

Albin Platz

Martin Bussmann

Thomas Kraenzler

Joerg Hoeschele

Theodor Staneff

Helmut Piringer

Rainer Willneff

Christian Karch

Martin Stroeer

Claus Wahl

Martin Englhart

Dietrich P Jonke

Eggert Reese

Friedrich Wirbeleit

Bernd Krutzsch

Guenter Wenninger

Manuel Hertter

Stefan Schneiderbanger

Rainer Schmidberger

Blanka Lenczowski

Walter Jehle

Michael Hofmann

Paulin Fideu

Alexander Kaiser

Domenico Furfari

Bernt Obkircher

Jan Van Toor

Axel Heuberger

Bernard Duprieu

Heiko Fietzek

Roland Lang

Johannes Stuhlberger

Alexander Ohnesorge

Michael Pilawa

Theo Hack

Wilhelm Wulbrand

Nikolaus Ohrloff

Harald Geiger

Claudio Dalle Donne

Jochen Laun

Ante Kurtovic

Dietrich Jonke

Burkhard Wagner

Walter Rothammel

Markus Heller

Philip Betz

Friedrich Oeffinger

Hans G Mueller

Florian Stagliano

Ulrike Heckenberger

A heating element for in-flight de-icing of aircraft is disclosed. The heating element includes a carbon fiber material that is designed to be arranged on a component of an aircraft. The carbon fiber material includes at least two electrical contacts for connecting to an electrical wiring system, and at least one insulation layer for electrical insulation.

Electrical de-icing for aircraft

A structural component for a vehicle has a surface with a riblet structure. The riblet structure includes a plurality of grooves, including a first groove having a first longitudinal section forming a first angle with a main longitudinal direction of the structural component. The first angle is larger than 0&#xb0; and the main longitudinal direction corresponds to a flow direction of a fluid along the surface of the structural component.

Structural component with a riblet surface

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.

Unmanned aircraft and operation method for the same

An induction heating system and a method for controlling a process temperature for induction heating of a workpiece. The induction heating system comprises an inductor configured to generate an alternating magnetic field in response to an alternating current supplied thereto, a magnetic load comprising a magnetic material, the magnetic material having a Curie temperature and being configured to generate heat in response to the alternating magnetic field being applied thereto, the magnetic load being connectable to the workpiece in a heat-conducting manner so as to transfer the generated heat to the workpiece, and a control unit configured to control the process temperature for manufacturing the workpiece by adjusting the alternating magnetic field when the temperature of the magnetic material is in a temperature control range around or below the Curie temperature of the magnetic material, the temperature control range being dependent on the magnetic material of the magnetic load.

Active temperature control for induction heating

Specified is a lightning protection layer for an aircraft. The lightning protection layer has a first stratum and a second stratum. The second stratum is coupled to the first stratum along a connecting surface. The first stratum has a metal foil and the second stratum has carbon allotropes. It is thus made possible that damage to a structure of the aircraft by lightning strike is reduced.

Lightning protection layer for fiber composite structures

A gas turbine includes a combustion chamber and a microwave source to produce microwave radiation. The gas turbine is arranged to guide the microwave radiation into a cavity of the combustion chamber. Due to the microwave radiation, in the cavity of the combustion chamber, combustion in the cavity may be supported and thus lean operation of the gas turbine is made possible.

High frequency-stabilized combustion in aircraft gas turbines

A method for producing a surface structure with a lightning strike protective system involves providing a support structure based on a fiber-reinforced composite material. At least one arrangement of a lightning strike protective material made from or with a conductive material is applied onto the support structure so that the lightning strike protective material arrangement adheres to the support structure in such a way that it is held securely in its position. A cover material is applied in such a way that it embeds the at least one arrangement of a lightning strike protective material that is held securely in its position on the support structure, and the cover material is solidified.

Method for producing a surface structure with lightning protection, and surface structure which can be produced in this way

An ice protection system for de-icing an aircraft and/or for keeping the aircraft free of ice includes a composite structure for an aircraft component and a structural element of an aircraft with an ice protection system that is integrated in the composite structure. The ice protection system includes a flat surface-like electric heating element that is embedded in the composite structure below an outer layer of an outer surface of the aircraft component.

Composite structure having an ice protection device, and production method

The present invention provides a method for preventing the forming of cracks and slowing the crack propagation in metallic airplane structural parts by laser shock peening with the following steps: Providing an airplane structural part having a crack; irradiating a first surface area of the airplane structural part close to the crack with a first pulsed laser beam having a first wavelength and a first pulsation frequency, wherein energy of the first laser beam is absorbed by the airplane structural part and a shock wave runs through the airplane structural part, which creates compressive prestressings in the airplane structural part.

Method for preventing crack formation and for slowing down the advancement of a crack in metal aircraft structures by means of laser shock rays

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.

Ions metering device for an energy storage device, method of manufacturing a metering device and ion energy storage device

A corrosion detection apparatus for permanently and integrally monitoring a state of corrosion of a component is provided. The corrosion detection apparatus makes it possible to use the change in electrical conductivity to detect corrosion of a component to be monitored. A corrosion-sensitive bridging element that establishes an electrical connection between a first electrical line section and a second electrical line section of a sensor circuit is used to change certain electrical properties of the sensor circuit. On account of the corrosion-sensitive property of the bridging element, the latter changes its electrical conductivity when corrosion starts. This makes it possible to use the sensor circuit to detect corrosion of the bridging element and thus of the component to be monitored.

Corrosion detection apparatus for monitoring a state of corrosion

A process and a system for creating internal stress in a metallic workpiece by laser shock peening is provided. In the process, a first laser pulse is applied to a treatment site of the workpiece covered by a surface layer. A second laser pulse follows the first laser pulse in time, and is applied to the treatment site of the workpiece. A covering layer, such as flowing water, is provided over the treatment site during the application of the laser pulses.

Process and system for creating internal stress in a metallic workpiece

A method and device for surface peening, particularly ultrasonic shot peening, of a component in the region of a passage opening is disclosed. A vibration device impinging the blasting material is disposed on one side and a counter-element is disposed on an opposite side relative to a component region having the passage opening. The counter-element is disposed at a distance relative to the corresponding side of the component region.

Method and device for surface peening of a component in the region of a passage opening

A method for machining workpieces provides a machining electrode, which is guided at a specific distance to the workpiece. An electrolyte is provided between the workpiece and the machining electrode, through which an operating current flows between the machining electrode and the workpiece. The operating current results from an operating voltage (U), which is produced at the machining electrode, the workpiece being connected to ground. To perform the machining procedure, the distance between the machining electrode and the workpiece is regulated and the operating voltage (U) is determined in such a way that the resulting operating current is a DC current or a pulsed DC current&#x2014;i.e., the operating voltage is a DC voltage of fixed or specific dimension. A measuring voltage (U) is superimposed on the operating voltage (U) for producing the operating current. The measuring current resulting because of the application of the measuring voltage (U) is detected and the distance between the machining electrode and the workpiece is concluded from the relationship between the measuring voltage (U) and the measuring current.

Method for machining workpieces

The invention relates to a method for the production of aero-dynamic structures during the production of integrally bladed gas turbine rotors. Aerodynamic structures of an integrally bladed gas turbine rotor are produced on a rotor disk base body, whereon the end contours are precise, by removing material according to an electrochemical removal process, i.e. by means of an electrochemical machining (ECM)-process. The method comprises the following steps: a) preparing a rotor disk base body which is made of a material which is difficult to machine; b) removing the material which is between the blade wings until a specific dimension is obtained, according to a removal process; c) preparing at least one working electrode in order to finish at least one aerodynamic structure of an integrally bladed gas turbine rotor. The contours of the or each of the working electrodes are adapted to the contours of the aerodynamic structure, which are produced by means of the respective working electrode, such that a gap between the rotor disk base body and a working electrode are produced in an approximately identical manner during the removal process of the material; d) electrochemically machining the or each aerodynamic structure in an electrochemical sinking by placing the rotor disk base body and the or each working electrode in an electrolyte and by applying voltage and/or current, whereby the applied current and/or voltage is temporally pulsed; e) pressure-rinsing the gap which is filled with electrolytes between the aero-dynamic structure and the or each working electrode by a pulsed movement of the or each working electrode.

Method for producing aerodynamic structures in the manufacturing of integrally bladed gas turbine rotors

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Uhldingen-Muehlhofen, Germany

Juergen Steinwandel