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 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.

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: An aircraft bipolar high-voltage network includes a DC voltage converter comprising two unipolar input connections, two bipolar output connections and a reference potential connection, and at least one unipolar device having two electrical connections which are each coupled to one of the two unipolar input connections. The DC voltage converter has a first DC voltage converter module coupled to a first of the unipolar input connections via a module input connection, to the reference potential connection via a module reference potential connection and to a first of the bipolar output connections via a module output connection, and a second DC voltage converter module coupled to a second of the unipolar input connections via a module input connection, to the reference potential connection via a module reference potential connection and to a second of the bipolar output connections via a module output connection.

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: 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 aircraft bipolar high-voltage network includes a DC voltage converter comprising two unipolar input connections, two bipolar output connections and a reference potential connection, and at least one unipolar device having two electrical connections which are each coupled to one of the two unipolar input connections. The DC voltage converter has a first DC voltage converter module coupled to a first of the unipolar input connections via a module input connection, to the reference potential connection via a module reference potential connection and to a first of the bipolar output connections via a module output connection, and a second DC voltage converter module coupled to a second of the unipolar input connections via a module input connection, to the reference potential connection via a module reference potential connection and to a second of the bipolar output connections via a module output connection.

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 aircraft bipolar high-voltage network includes a DC voltage converter comprising two unipolar input connections, two bipolar output connections and a reference potential connection, and at least one unipolar device having two electrical connections which are each coupled to one of the two unipolar input connections. The DC voltage converter has a first DC voltage converter module coupled to a first of the unipolar input connections via a module input connection, to the reference potential connection via a module reference potential connection and to a first of the bipolar output connections via a module output connection, and a second DC voltage converter module coupled to a second of the unipolar input connections via a module input connection, to the reference potential connection via a module reference potential connection and to a second of the bipolar output connections via a module output connection.

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 bipolar high-voltage network for an aircraft or spacecraft. The network includes at least one DC-DC converter having two unipolar input connections and two bipolar output connections as well as a reference potential connection, at least two fuel cell stacks which are coupled in series between the two unipolar input connections, and at least two discharge diodes, each connected in parallel with the output connections of one of the at least two fuel cell stacks. The DC-DC converter is operable selectively in a step-up converter mode of operation or a step-down converter mode of operation, as a function of an input voltage between the unipolar input connections.

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: 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.

Abstract: A bipolar high-voltage network for an aircraft or spacecraft. The network includes at least one DC-DC converter having two unipolar input connections and two bipolar output connections as well as a reference potential connection, at least two fuel cell stacks which are coupled in series between the two unipolar input connections, and at least two discharge diodes, each connected in parallel with the output connections of one of the at least two fuel cell stacks. The DC-DC converter is operable selectively in a step-up converter mode of operation or a step-down converter mode of operation, as a function of an input voltage between the unipolar input connections.