Abstract: A process is proposed for producing a bipolar plate for an electrochemical device, said process comprising providing a first main plate body and a second main plate body as fibrous shaped bodies including carbon fibers and each having a joining face and an opposing useful face, infiltrating the main plate bodies with at least one carbon allotrope, locally applying silicon to respective joining sites in the joining faces, placing the joining faces against one another, such that the joining sites rest against one another and the useful faces of the two main plate bodies face away from one another, and at least locally heating the joining sites, such that the silicon melts and reacts with adjoining carbon to form a silicon-carbon bond.

Abstract: An energy recovery assembly, fuel cell system and vehicle, with an electrolyzer configured to provide a fuel and an oxidant, a fuel cell configured to convert the fuel and an oxidant to electrical energy, a tank configured to store the fuel or the oxidant, and a conduction pathway connecting the tank to the electrolyzer and the fuel cell. The assembly also includes: an expansion machine disposed in the conduction pathway and configured to expand a fluid flowing through the expansion machine and to obtain mechanical energy; and a valve arrangement configured to put the pathway in a first mode in which the fuel or the oxidant is guided to the tank, or in a second mode in which the fuel cell or the oxidant is guided to the fuel cell, wherein the fuel or the oxidant in the first and second modes flows through the expansion machine.

Abstract: An electrical energy supply system for mobile platforms includes an electrical arrangement having at least two fuel cell units in a serial interconnection in relation to one another in the electrical arrangement and configured to provide an electrical voltage to supply at least one consumer. The electrical energy supply system includes a ground unit which is assigned an electrical reference potential, and at least two control units, which are each assigned to at least one of the fuel cell units, wherein each of the at least two control units is configured to detect an electrical voltage of the assigned fuel cell unit in relation to the reference potential. An aircraft is disclosed having an electrical energy supply system.

Abstract: A battery comprising a fluid electrolyte, a casing configured to contain the electrolyte, an anode placed in contact with the electrolyte in the casing, and a cathode placed in contact with the electrolyte in the casing. The battery comprises a temperature control device configured to modify the temperature of the electrolyte, a circulating device configured to circulate the electrolyte in the casing and between the casing and the temperature control device. Also, a method for regulating the temperature of a battery in which a fluid electrolyte is circulated in a battery casing comprising an anode and a cathode, and through a temperature control device configured to modify the temperature of the electrolyte.

Abstract: A cooling device for use in alternating magnetic fields include an evaporator part defining a first volume for evaporating a cooling medium contained therein, the evaporator part being made of an electrically and magnetically non-conductive material, and a condenser part defining a second volume for condensing the cooling medium contained therein, the condenser part being in fluid connection with the first volume.

Abstract: An aircraft drive device (10) for creating propulsion and/or lift of an aircraft, the drive device comprising a rotating shaft (12), a rotating shaft bearing (14, 16), a rotating shaft drive machine (18) for rotationally driving the rotating shaft (12), and a housing (20), wherein the rotating shaft bearing (14,16) and the rotating shaft drive device (18) are arranged in an interior of the housing (44) and the rotating shaft (12) protrudes to the outside of the housing (20) through a housing opening (42) of the housing (20), wherein in the region of the housing opening (42) an overvoltage arrester device (52) is arranged which is designed for diverting an overvoltage present at the rotating shaft (12).

Abstract: A structure for high temperature applications includes a base structure which includes a ceramic composite material, and a coating of a metal-semimetal compound, a metal boride, a metal carbide and/or a metal nitride. Furthermore, a production method and a coating device produces structures which resist high temperature applications with higher process temperatures and difficult chemical conditions.

Abstract: A battery comprising a fluid electrolyte, a casing configured to contain the electrolyte, an anode placed in contact with the electrolyte in the casing, and a cathode placed in contact with the electrolyte in the casing. The battery comprises a temperature control device configured to modify the temperature of the electrolyte, a circulating device configured to circulate the electrolyte in the casing and between the casing and the temperature control device. Also, a method for regulating the temperature of a battery in which a fluid electrolyte is circulated in a battery casing comprising an anode and a cathode, and through a temperature control device configured to modify the temperature of the electrolyte.

Abstract: A structure for high temperature applications includes a base structure which includes a ceramic composite material, and a coating of a metal-semimetal compound, a metal boride, a metal carbide and/or a metal nitride. Furthermore, a production method and a coating device produces structures which resist high temperature applications with higher process temperatures and difficult chemical conditions.

Abstract: 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.

Abstract: A vertical take-off aircraft with a propulsion drive for generating a driving force being effective in a horizontal direction and with a lift drive for generating a lifting force being effective in a vertical direction includes a motor for providing mechanical energy for the propulsion drive and a first generator for providing electrical energy for the lift drive. Moreover, the aircraft includes an exhaust gas turbocharger for the motor with a first turbine being driven by an exhaust gas flow of the motor, wherein the first turbine is configured to provide mechanical energy for the propulsion drive.

Abstract: 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° and the main longitudinal direction corresponds to a flow direction of a fluid along the surface of the structural component.

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.

Abstract: A structure for high temperature applications comprises a base structure which includes a ceramic composite material, and a coating of a metal-semimetal compound, a metal boride, a metal carbide and/or a metal nitride. Furthermore, a production method and a coating device produces structures which resist high temperature applications with higher process temperatures and difficult chemical conditions.

Abstract: The embodiments relate to a switch device for an electrochemical energy store having: a film transistor device that comprises at least one organic transistor, can be mounted in a planar manner on at least one electrode of the electrochemical energy store, can be controlled by an external voltage source, and is designed in the form of a controllable electrical resistor that is connected, in series, to an internal resistor of said electrochemical energy store.

Abstract: 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.

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.

Abstract: An aircraft drive device (10) for creating propulsion and/or lift of an aircraft, the drive device comprising a rotating shaft (12), a rotating shaft bearing (14, 16), a rotating shaft drive machine (18) for rotationally driving the rotating shaft (12), and a housing (20), wherein the rotating shaft bearing (14,16) and the rotating shaft drive device (18) are arranged in an interior of the housing (44) and the rotating shaft (12) protrudes to the outside of the housing (20) through a housing opening (42) of the housing (20), wherein in the region of the housing opening (42) an overvoltage arrester device (52) is arranged which is designed for diverting an overvoltage present at the rotating shaft (12).

Abstract: A light metal material having a tensile strength of >180 MPa at room temperature is provided, as well as a method for producing such a light metal material and the use of such a light metal material as a piston component in a rotary piston engine.

Abstract: 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.