Abstract: An electrical supply system for an aircraft includes a generator having a neutral point, an AC network, a bipolar DC network, and a neutral point clamped converter. The neutral point is connected to ground, in at least one operating mode. The converter has an AC side with AC connectors couplable with at least one phase of the generator. The converter also has a DC side with a first DC connector, a second DC connector and a neutral DC connector. The AC side of the converter is coupled with the generator, the DC side is coupled with the bipolar DC network, and the neutral DC connector is connected to ground. The convertor provides a DC voltage on the DC side upon receiving an AC voltage on the AC side, and provides an AC voltage on the AC side upon receiving a DC voltage on the DC side.

Abstract: An actuating apparatus for a polyphase motor includes five phase terminals for connecting of in each case one phase of the polyphase motor, a high terminal for applying a supply voltage (UB), a low terminal for applying a reference potential of the supply voltage (UB), a control device, wherein the control device is adapted, in four of the five phase terminals, to impress a pulse-width-modulated voltage pattern by connecting the phase terminals to the high terminal or the low terminal so that in the first phase terminal, an evaluation signal which is dependent on the angle of rotation of the polyphase motor is produced, and wherein the control device is adapted to determine the angle of rotation and/or a commutation condition of the polyphase motor from the evaluation signal.

Abstract: A motor actuating apparatus includes three phase connections for three motor phase connections, a high-connection for a supply voltage and a low-connection for a reference potential of the supply voltage, three bridge branches having a series connection of a high-switch and a low-switch and a control device for actuating the switches of the bridge branches. The high-switches are connected to the high-connection and the low-switches are connected to the low-connection. Each of the three phase connections is connected to exactly one of the three bridge branches between the high-switch and the low-switch. The control device is adapted for actuating the switches of the bridge branches such that during a first time period a first phase connection is switched to passive and the second phase connection and third phase connection are alternatingly connected to the high-connection and the low-connection in a predeterminable duty cycle if the supply voltage is applied.

Abstract: A high voltage conductor for transmitting high voltage is provided. The high voltage conductor includes a power wire, a fault detection unit, and a monitoring unit. The power wire is configured for transmission of electrical energy. The fault detection unit is configured for detecting an electromagnetic field emanated by the power wire, and the monitoring unit is configured for detection of degradation in an isolation of the high voltage conductor. The monitoring unit is connected to the fault detection unit and is configured to receive an electrical signal induced in the fault detection unit, which electrical signal is induced as a result of a degradation of the isolation of the high voltage conductor. Thus, degradation of the isolation of the high voltage conductor may be recognized at an early stage.

Abstract: An electrical power supply system for an aircraft includes a plurality of generators, each being couplable to and rotatable by an aircraft engine. and a plurality of electrical conversion units, each having a plurality of inputs and at least one output. Each generator includes at least four AC phases. The inputs of each individual electrical conversion unit are connected to a plurality of phases of at least two of the plurality of generators. The electrical conversion units each includes a rectification and conversion device for providing an output voltage having a predeterminable frequency and voltage level at the output.

Abstract: A cooling system for cooling electronic aircraft equipment comprises a primary cooling arrangement configured to provide basic cooling energy for cooling the electronic aircraft equipment and a supplemental cooling arrangement configured to provide supplemental cooling energy for cooling the electronic aircraft equipment. The supplemental cooling arrangement comprises a coolant supply system and a coolant distribution system. The coolant supply system is configured to supply a compressed coolant to the electronic aircraft equipment to be cooled, and the coolant distribution system is configured to selectively direct the compressed coolant supplied by the coolant supply system to at least one of a plurality of components of the electronic aircraft equipment.

Abstract: An electrical supply system for an aircraft includes a generator having a neutral point, an AC network, a bipolar DC network, and a neutral point clamped converter. The neutral point is connected to ground, in at least one operating mode. The converter has an AC side with AC connectors couplable with at least one phase of the generator. The converter also has a DC side with a first DC connector, a second DC connector and a neutral DC connector. The AC side of the converter is coupled with the generator, the DC side is coupled with the bipolar DC network, and the neutral DC connector is connected to ground. The convertor provides a DC voltage on the DC side upon receiving an AC voltage on the AC side, and provides an AC voltage on the AC side upon receiving a DC voltage on the DC side.

Abstract: A high voltage conductor for transmitting high voltage is provided. The high voltage conductor includes a power wire, a fault detection unit, and a monitoring unit. The power wire is configured for transmission of electrical energy. The fault detection unit is configured for detecting an electromagnetic field emanated by the power wire, and the monitoring unit is configured for detection of degradation in an isolation of the high voltage conductor. The monitoring unit is connected to the fault detection unit and is configured to receive an electrical signal induced in the fault detection unit, which electrical signal is induced as a result of a degradation of the isolation of the high voltage conductor. Thus, degradation of the isolation of the high voltage conductor may be recognized at an early stage.

Abstract: An electrical drive system for an aircraft includes: at least one first and one second electrical direct voltage sources for supplying a direct voltage, and a first and a second electrical machine modules configured to convert electrical alternating voltage into mechanical movement and vice versa. The first and second modules are connected to a first and a second power inverters, respectively. The first and second inverters are connected in series and the first and the second direct voltage sources are connected in series to generate an overall direct voltage to which the inverters are connected. The power inverters each has one voltage measuring device for measuring the power inverter direct voltage present at the respective inverter and a power inverter control device for controlling the operation of the inverters in accordance with the power inverter direct voltage.

Abstract: A high-voltage DC voltage unit with a first DC voltage apparatus providing a first high-voltage DC voltage between a first output connection and a second output connection of the DC voltage apparatus or can be fed with a first high-voltage DC voltage. A second DC voltage apparatus provides a second high-voltage DC voltage or can be fed with a second high-voltage DC voltage. A first DC voltage connection is coupled with the first output connection of the first DC voltage apparatus. A second DC voltage connection is coupled with the second output connection of the second DC voltage apparatus. A reference potential connection is coupled with the second output connection of the first DC voltage apparatus, with the first output connection of the second DC voltage apparatus and with an earth potential, the first and second high-voltage DC voltages realizing a bipolar power supply.

Abstract: An actuating apparatus for a polyphase motor includes five phase terminals for connecting of in each case one phase of the polyphase motor, a high terminal for applying a supply voltage (UB), a low terminal for applying a reference potential of the supply voltage (UB), a control device, wherein the control device is adapted, in four of the five phase terminals, to impress a pulse-width-modulated voltage pattern by connecting the phase terminals to the high terminal or the low terminal so that in the first phase terminal, an evaluation signal which is dependent on the angle of rotation of the polyphase motor is produced, and wherein the control device is adapted to determine the angle of rotation and/or a commutation condition of the polyphase motor from the evaluation signal.

Abstract: A motor actuating apparatus includes three phase connections for three motor phase connections, a high-connection for a supply voltage and a low-connection for a reference potential of the supply voltage, three bridge branches having a series connection of a high-switch and a low-switch and a control device for actuating the switches of the bridge branches. The high-switches are connected to the high-connection and the low-switches are connected to the low-connection. Each of the three phase connections is connected to exactly one of the three bridge branches between the high-switch and the low-switch. The control device is adapted for actuating the switches of the bridge branches such that during a first time period a first phase connection is switched to passive and the second phase connection and third phase connection are alternatingly connected to the high-connection and the low-connection in a predeterminable duty cycle if the supply voltage is applied.

Abstract: A cooling system for cooling electronic aircraft equipment comprises a primary cooling arrangement configured to provide basic cooling energy for cooling the electronic aircraft equipment and a supplemental cooling arrangement configured to provide supplemental cooling energy for cooling the electronic aircraft equipment. The supplemental cooling arrangement comprises a coolant supply system and a coolant distribution system. The coolant supply system is configured to supply a compressed coolant to the electronic aircraft equipment to be cooled, and the coolant distribution system is configured to selectively direct the compressed coolant supplied by the coolant supply system to at least one of a plurality of components of the electronic aircraft equipment.

Abstract: An electrical power supply system for an aircraft includes a plurality of generators, each being couplable to and rotatable by an aircraft engine. and a plurality of electrical conversion units, each having a plurality of inputs and at least one output. Each generator includes at least four AC phases. The inputs of each individual electrical conversion unit are connected to a plurality of phases of at least two of the plurality of generators. The electrical conversion units each includes a rectification and conversion device for providing an output voltage having a predeterminable frequency and voltage level at the output.

Abstract: An electrical drive system for an aircraft includes: at least one first and one second electrical direct voltage sources for supplying a direct voltage, and a first and a second electrical machine modules configured to convert electrical alternating voltage into mechanical movement and vice versa. The first and second modules are connected to a first and a second power inverters, respectively. The first and second inverters are connected in series and the first and the second direct voltage sources are connected in series to generate an overall direct voltage to which the inverters are connected. The power inverters each has one voltage measuring device for measuring the power inverter direct voltage present at the respective inverter and a power inverter control device for controlling the operation of the inverters in accordance with the power inverter direct voltage.

Abstract: A method for detecting a device that generates spurious signals in an electrical network, to which several devices and at least one fault detection device are connected, includes the steps of monitoring the electrical network for electrical spurious signals, sequentially deactivating each device for a predetermined time T when an electrical spurious signal has been detected, and checking the electrical network for the disappearance of the respective spurious signal, and signaling as soon as the respective spurious signal has disappeared upon deactivating a respective device. This makes it possible to especially reliably detect a device in an electrical network that couples an undesired spurious signal into the network.

Abstract: An electrical consumer of an aircraft comprises an electric motor and an inverter for producing an alternating voltage for the electric motor. A method for controlling the electrical consumer comprises determining a rotational frequency for the electric motor. The method also includes establishing whether the rotational frequency leads to oscillations in the input current of the inverter which are below a predefined threshold, the oscillations being produced by the inverter when producing a supply voltage for the electric motor, and changing the rotational frequency if it has been established that the rotational frequency leads to oscillations below the predefined threshold.

Abstract: A heat exchanger for cooling air, with a coolant onward-flow connection for feeding liquid coolant for cooling air and a coolant return-flow connection for discharging liquid coolant. For removing ice by melting accumulated ice in the heat exchanger, a heater is provided that is associated with an electrical heating element. An operational safety device prevents overheating of the heater. The operational safety device comprises a fault-current detection device. Such a heater, with a heating element for heating air for subjecting accumulated ice to heated air, and with such an operational safety device is provided. Also, a galley for a commercial aircraft is provided with a receiving space for trolleys, and a cooling device for cooling the receiving space. The cooling device comprises such a heat exchanger for cooling air.

Abstract: An electrical consumer of an aircraft comprises an electric motor and an inverter for producing an alternating voltage for the electric motor. A method for controlling the electrical consumer comprises determining a rotational frequency for the electric motor. The method also includes establishing whether the rotational frequency leads to oscillations in the input current of the inverter which are below a predefined threshold, the oscillations being produced by the inverter when producing a supply voltage for the electric motor, and changing the rotational frequency if it has been established that the rotational frequency leads to oscillations below the predefined threshold.

Abstract: A cooling unit in a transport unit includes power electronics; a heat exchanger for thermally coupling a cooling agent of a central cooling system of the transport unit with air of the cooling unit to cool one or more generating devices; and a heat pipe for heat dissipation of the power electronics. At a first portion of the heat pipe, at least some of a working agent is in the liquid phase and, at a second portion of the heat pipe, at least some of the working agent is in the gas phase. In the first portion of the heat pipe, heat from the power electronics is absorbed by evaporating the working agent in the liquid phase. In the second portion of the heat pipe, heat is released to the cooling agent by condensing the working agent in the gas phase.