Abstract: A component has a base bushing, which has a first axial end and an opposite second axial end and a first inner diameter, wherein the base bushing is equipped with a first internal thread with a first thread direction, and has a fastening bushing, which has a third axial end and an opposite fourth axial end and a second inner diameter. The fastening bushing is equipped with a second internal thread with a second thread direction which is opposite to the first thread direction, wherein the second inner diameter is smaller than the first inner diameter and the base bushing and the fastening bushing are separate elements and are arranged coaxially with respect to one another in the component. Alternatively, the base bushing and the fastening bushing are formed as a single piece.

Abstract: The disclosure relates to an apparatus configured as an electrochemical battery cell. The apparatus includes an anode, a cathode, and an electrolyte which is configured to allow ions to travel between the anode and the cathode. The apparatus further comprises an actuator. The actuator is configured to adjust a parameter of an electrochemical reaction in which the actuator and/or an actuated portion of the battery cell is chemically involved. Additionally or alternatively, the actuator and/or the actuated portion is a permeable portion of the battery cell which is configured to allow the ions to permeate into the permeable portion, wherein the actuator is configured to adjust an ion permeability of the permeable portion to the ions. The actuated portion of the battery cell is in operative interaction with the actuator.

Abstract: A component has a base bushing, which has a first axial end and an opposite second axial end and a first inner diameter, wherein the base bushing is equipped with a first internal thread with a first thread direction, and has a fastening bushing, which has a third axial end and an opposite fourth axial end and a second inner diameter. The fastening bushing is equipped with a second internal thread with a second thread direction which is opposite to the first thread direction, wherein the second inner diameter is smaller than the first inner diameter and the base bushing and the fastening bushing are separate elements and are arranged coaxially with respect to one another in the component. Alternatively, the base bushing and the fastening bushing are formed as a single piece.

Abstract: An observation satellite is used for obtaining information about electromagnetic energy emitted from the earth. The observation satellite orbits the earth in an orbit having an inclination larger than 90° and smaller than 270°. Further, the observation satellite comprises at least one receiving antenna, the at least one receiving antenna having a receiving pattern directed towards the earth, and suitable for receiving electromagnetic energy in the radio frequency range as the observation satellite is orbiting relative to the surface of the earth. The observation satellite also comprises a transmitter configured for at least one of: (i) retransmitting, to a relay spacecraft, the received electromagnetic energy, (ii) transmitting, to the relay spacecraft, information representing the received electromagnetic energy, and (iii) transmitting, to the relay spacecraft, information derived from the received electromagnetic energy. The invention also relates to systems and methods therefor.

Abstract: Fuel cell arrangement having an improved efficiency. The arrangement comprises one or more fuel cell units 110 and a methanation unit 200 and a control unit 300. The fuel cell unit comprises a water inlet 111, a hydrogen outlet 112 and an oxygen outlet 113. The methanation unit comprises a catalyst 222, a hydrogen inlet 213, a carbon oxide inlet 214 having a first controllable valve 215 and a methane outlet 216, wherein the hydrogen outlet of the first fuel cell unit is coupled to the hydrogen inlet of the methanation unit, and the methanation unit is adapted to convert hydrogen and carbon oxide into methane, wherein the control unit is adapted to control the first controllable valve so as to obtain an optimum converting process to convert hydrogen and carbon oxide into methane.

Abstract: A head rest is illustrated and described that has a head box (11) by which at least one support rod (12) can be secured to a vehicle seat, wherein at least one end of the support rod (12) is received in a bearing (14) carried on the head box (11) or the vehicle seat, wherein the support rod (12) can be latched releasably to at least one bearing (14) by a latch (15) movable between a latching position and a release position, wherein the latch (15) has at least one notch (16) that extends over a region of the circumference of the support rod (12) and has a latch element (17) carried by the bearing (14). The special feature is that the latch element (17) is movably mounted, so that in the latching position, in the event of a relative rotation between the support rod (12) and the bearing (14), it is movable out of a starting position into at least one crash position.

Abstract: An observation satellite is used for obtaining information about electromagnetic energy emitted from the earth. The observation satellite orbits the earth in an orbit having an inclination larger than 90° and smaller than 270°. Further, the observation satellite comprises at least one receiving antenna, the at least one receiving antenna having a receiving pattern directed towards the earth, and suitable for receiving electromagnetic energy in the radio frequency range as the observation satellite is orbiting relative to the surface of the earth. The observation satellite also comprises a transmitter configured for at least one of: (i) retransmitting, to a relay spacecraft, the received electromagnetic energy, (ii) transmitting, to the relay spacecraft, information representing the received electromagnetic energy, and (iii) transmitting, to the relay spacecraft, information derived from the received electromagnetic energy. The invention also relates to systems and methods therefor.

Abstract: Fuel cell arrangement having an improved efficiency. The arrangement comprises one or more fuel cell units 110 and a methanation unit 200 and a control unit 300. The fuel cell unit comprises a water inlet 111, a hydrogen outlet 112 and an oxygen outlet 113. The methanation unit comprises a catalyst 222, a hydrogen inlet 213, a carbon oxide inlet 214 having a first controllable valve 215 and a methane outlet 216, wherein the hydrogen outlet of the first fuel cell unit is coupled to the hydrogen inlet of the methanation unit, and the methanation unit is adapted to convert hydrogen and carbon oxide into methane, wherein the control unit is adapted to control the first controllable valve so as to obtain an optimum converting process to convert hydrogen and carbon oxide into methane.

Abstract: Fuel cell arrangement having an improved efficiency. The arrangement comprises one or more fuel cell units 110 and a methanation unit 200 and a control unit 300. The fuel cell unit comprises a water inlet 111, a hydrogen outlet 112 and an oxygen outlet 113. The methanation unit comprises a catalyst 222, a hydrogen inlet 213, a carbon oxide inlet 214 having a first controllable valve 215 and a methane outlet 216, wherein the hydrogen outlet of the first fuel cell unit is coupled to the hydrogen inlet of the methanation unit, and the methanation unit is adapted to convert hydrogen and carbon oxide into methane, wherein the control unit is adapted to control the first controllable valve so as to obtain an optimum converting process to convert hydrogen and carbon oxide into methane.

Abstract: A head rest is illustrated and described that has a head box (11) by which at least one support rod (12) can be secured to a vehicle seat, wherein at least one end of the support rod (12) is received in a bearing (14) carried on the head box (11) or the vehicle seat, wherein the support rod (12) can be latched releasably to at least one bearing (14) by a latch (15) movable between a latching position and a release position, wherein the latch (15) has at least one notch (16) that extends over a region of the circumference of the support rod (12) and has a latch element (17) carried by the bearing (14). The special feature is that the latch element (17) is movably mounted, so that in the latching position, in the event of a relative rotation between the support rod (12) and the bearing (14), it is movable out of a starting position into at least one crash position.

Abstract: A protection element for a meshed energy supply network of a means of transport, in particular of an aircraft, a meshed energy supply network having such protection elements, a method for protecting such a meshed energy supply network and a computer program for executing the method. The protection element comprises a control unit, which is formed to deduce a trigger time value from a detected fault impedance value of a network error that has occurred in the energy supply network and to adapt the trigger time value in the event of a subsequent change in the fault impedance value of the network error, and a separation unit for interrupting a connection between the protection element and the network error depending on the trigger time value.

Abstract: The present invention relates to an electric power supply system for an aircraft having a transformer-less HVDC architecture, the system including: at least one multiphase engine generator in a star configuration which provides a multiphase alternating (AC) voltage; a converting circuit for converting the multiphase AC voltage into a corresponding direct (DC) voltage for supplying at least one aircraft load; an electric power supply interface for connection with a standardized GPU plug of an external GPU, the electric power supply interface comprising a supply voltage output terminal coupled to a self-contained power source for providing a low voltage control signal for driving a GPU internal switching circuit wherein the power source is decoupled from the AC voltage and DC voltage. The present invention further relates to an aircraft and an airport power supply system.

Abstract: An apparatus for phase balancing in a three-phase power distribution system provided on board a transport vehicle, a three-phase power distribution system comprising the apparatus, a transport vehicle comprising at least one of the apparatus and the three-phase power distribution system, the use of the apparatus on board a transport vehicle and a method for phase balancing in a three-phase power distribution system. An apparatus for phase balancing includes one or more multi-way switching devices and a control unit. Each of the one or more multi-way switching devices is configured to selectively connect a load of one or more loads with the phases of the three-phase power distribution system, thereby enabling a plurality of switching states between the one or more loads and the phases of the three-phase power distribution system. The control unit includes one or more communication interfaces with the one or more multi-way switches.

Abstract: Fuel cell and/or high-pressure electrolysis cell and a fuel cell membrane arrangement for improved control of a fuel cell by an actuator connected to the fuel cell membrane.

Abstract: An energy supply system, an aircraft and spacecraft using such an energy supply system and a method for providing electrical energy with the energy supply system. The energy supply system comprises an energy source which generates a direct current or a direct voltage. A converter is coupled to the energy source and is designed to convert the generated direct current or the generated direct voltage into an output current specified for the energy supply system or an output voltage specified for the energy supply system. A switching device is designed to couple an output of the energy supply system to the converter or directly to the energy source as a function of the electrical power required by the energy supply system.

Abstract: Fuel cell arrangement having an improved efficiency. The arrangement comprises one or more fuel cell units 110 and a methanation unit 200 and a control unit 300. The fuel cell unit comprises a water inlet 111, a hydrogen outlet 112 and an oxygen outlet 113. The methanation unit comprises a catalyst 222, a hydrogen inlet 213, a carbon oxide inlet 214 having a first controllable valve 215 and a methane outlet 216, wherein the hydrogen outlet of the first fuel cell unit is coupled to the hydrogen inlet of the methanation unit, and the methanation unit is adapted to convert hydrogen and carbon oxide into methane, wherein the control unit is adapted to control the first controllable valve so as to obtain an optimum converting process to convert hydrogen and carbon oxide into methane.

Abstract: Fuel cell and/or high-pressure electrolysis cell and a fuel cell membrane arrangement for improved control of a fuel cell by an actuator connected to the fuel cell membrane.

Abstract: A protection element for a meshed energy supply network of a means of transport, in particular of an aircraft, a meshed energy supply network having such protection elements, a method for protecting such a meshed energy supply network and a computer program for executing the method. The protection element comprises a control unit, which is formed to deduce a trigger time value from a detected fault impedance value of a network error that has occurred in the energy supply network and to adapt the trigger time value in the event of a subsequent change in the fault impedance value of the network error, and a separation unit for interrupting a connection between the protection element and the network error depending on the trigger time value.

Abstract: The invention relates to an air volume flow and pushing force control device for a vacuum cleaner that has at least a motor, a dust receptacle and a suction nozzle, comprising a controller for controlling the motor power, a first sensor for detecting the air volume flow, which in conjunction with the controller forms a first control loop in order to maintain the air volume flow at a prescribed air volume flow value on the basis of the signal of the first sensor. The control device further comprises a second sensor for detecting a pushing force that is required for pushing the suction nozzle, and in conjunction with the controller, forms a second control loop in order to maintain the pushing force below a prescribed value on the basis of the signal of the second sensor, and a control loop selection device that activates one of the two control loops as a function of the signals of the two sensors.

Abstract: The present invention relates to an electric power supply system for an aircraft having a transformer-less HVDC architecture, the system including: at least one multiphase engine generator in a star configuration which provides a multiphase alternating (AC) voltage; a converting circuit for converting the multiphase AC voltage into a corresponding direct (DC) voltage for supplying at least one aircraft load; an electric power supply interface for connection with a standardized GPU plug of an external GPU, the electric power supply interface comprising a supply voltage output terminal coupled to a self-contained power source for providing a low voltage control signal for driving a GPU internal switching circuit wherein the power source is decoupled from the AC voltage and DC voltage. The present invention further relates to an aircraft and an airport power supply system.