Abstract: Embodiments of the disclosure relate to a power electronics apparatus. The power electronics apparatus includes at least a first electrically conductive element and a second electrically conductive element. The elements are intended to be at a first electrical potential and at a second electrical potential, respectively. At least a first and second power electronics components are mounted on the first and second elements, respectively, a first portion and a second portion of a sink are mounted on the first conductive element and on the second conductive element, respectively, so as to permit the transfer of heat from each power component to the corresponding portion of the sink through the corresponding conductive element. An electrical insulator is present between each portion of the sink so as to prevent the risk of flashover between the two portions.

Abstract: An electrical module configured to be connected to a power shaft of a turbine engine of an aircraft. The electrical module being configured to draw off power from/inject power into the power shaft. The electrical module comprising an electric machine comprising a machine housing in which a stator and a rotor is mounted, configured to be mechanically connected to the power shaft, the machine housing having a cylindrical shape extending along a cylinder axis, a first electric converter mounted in a first housing, a second electric converter mounted in a second housing, the second converter being independent of the first converter, the first housing and the second housing each being in the shape of a half-cylinder extending along the cylinder axis so as to form a cylindrical assembly that is mounted as an extension of the machine housing of the electric machine to limit the size of the electrical module.

Abstract: An electric architecture for a twin-engined, hybrid thermal/electric propulsion aircraft and, for each turboshaft which includes a high-voltage DC propulsive electric distribution network, a non-propulsive electric distribution network which is connected to loads of the aircraft, and an electric distribution network which is connected to loads of an electrified control system of the turboshaft engine, and wherein power supply sources are shared for these different networks.

Abstract: Embodiments of the disclosure relate to a power electronics apparatus. The power electronics apparatus includes at least a first electrically conductive element and a second electrically conductive element. The elements are intended to be at a first electrical potential and at a second electrical potential, respectively. At least a first and second power electronics components are mounted on the first and second elements, respectively, a first portion and a second portion of a sink are mounted on the first conductive element and on the second conductive element, respectively, so as to permit the transfer of heat from each power component to the corresponding portion of the sink through the corresponding conductive element. An electrical insulator is present between each portion of the sink so as to prevent the risk of flashover between the two portions.

Abstract: An electrical module configured to be connected to a power shaft of a turbine engine of an aircraft. The electrical module being configured to draw off power from/inject power into the power shaft. The electrical module comprising an electric machine comprising a machine housing in which a stator and a rotor is mounted, configured to be mechanically connected to the power shaft, the machine housing having a cylindrical shape extending along a cylinder axis, a first electric converter mounted in a first housing, a second electric converter mounted in a second housing, the second converter being independent of the first converter, the first housing and the second housing each being in the shape of a half-cylinder extending along the cylinder axis so as to form a cylindrical assembly that is mounted as an extension of the machine housing of the electric machine to limit the size of the electrical module.

Abstract: Embodiments of the disclosure relate to a power electronics apparatus. The power electronics apparatus includes at least a first electrically conductive element and a second electrically conductive element. The elements are intended to be at a first electrical potential and at a second electrical potential, respectively. At least a first and second power electronics components are mounted on the first and second elements, respectively, a first portion and a second portion of a sink are mounted on the first conductive element and on the second conductive element, respectively, so as to permit the transfer of heat from each power component to the corresponding portion of the sink through the corresponding conductive element. An electrical insulator is present between each portion of the sink so as to prevent the risk of flashover between the two portions.

Abstract: Overvoltage protection device for a variable-speed and constant-frequency electrical energy generation system includes at least one DC current generator connected, via a DC current bus to the input terminals of at least one inverter and to at least one regulation module for regulating the output voltage of the at least one inverter. The device includes a circuit including at least one switch in series with a resistor, the circuit being connected between the input terminals of the at least one inverter, at least one measurement sensor for measuring the DC voltage across the input terminals of the at least one inverter, a control circuit connected to the at least one measurement sensor and able to receive a voltage measured by the at least one measurement sensor, compare the measured voltage against a threshold and command the closure of the at least one switch if the measured voltage is greater than the threshold, and command opening thereof if not.

Abstract: The invention relates to an electric architecture for a twin-engined, hybrid thermal/electric propulsion aircraft and, for each turboshaft engine, the architecture comprises: —a high-voltage DC propulsive electric distribution network (32), —a non-propulsive electric distribution network (56) which is connected to loads of the aircraft, and—an electric distribution network (76) which is connected to loads of an electrified control system of the turboshaft engine, and wherein power supply sources are shared for these different networks.

Abstract: Overvoltage protection device for a variable-speed and constant-frequency electrical energy generation system includes at least one DC current generator connected, via a DC current bus to the input terminals of at least one inverter and to at least one regulation module for regulating the output voltage of the at least one inverter. The device includes a circuit including at least one switch in series with a resistor, the circuit being connected between the input terminals of the at least one inverter, at least one measurement sensor for measuring the DC voltage across the input terminals of the at least one inverter, a control circuit connected to the at least one measurement sensor and able to receive a voltage measured by the at least one measurement sensor, compare the measured voltage against a threshold and command the closure of the at least one switch if the measured voltage is greater than the threshold, and command opening thereof if not.

Abstract: A method for controlling a system for generating electric power for a power distribution network of an aircraft, the system for generating electric power comprising a generator, a rectifier, an inverter which produces a voltage according to several fixed-frequency phases, a DC voltage bus which connects the rectifier to the inverter, the control method comprising: —a correction step to determine at least one correction quantity GC, —a step of determining a signal SO for controlling the inverter from the determined correction quantity GC, —a step of determining a signal SG for controlling the generator from the determined correction quantity GC and —a step of transmitting the control signals SO, SG to the inverter and to the generator, respectively.

Abstract: A method for controlling a system for generating electric power for a power distribution network of an aircraft, the system for generating electric power comprising a generator, a rectifier, an inverter which produces a voltage according to several fixed-frequency phases, a DC voltage bus which connects the rectifier to the inverter, the control method comprising: —a correction step to determine at least one correction quantity GC, —a step of determining a signal SO for controlling the inverter from the determined correction quantity GC, —a step of determining a signal SG for controlling the generator from the determined correction quantity GC and —a step of transmitting the control signals SO, SG to the inverter and to the generator, respectively.

Abstract: A system for dissipating regenerated electric energy produced by an electric actuator of an aircraft, the dissipating system including: a resistor; two switching arms, each switching arm being connected in series with the resistor, the two switching arms being connected together in parallel, each switching arm including two switches connected to one another in series, each switch including two terminals and a control grid, each switch being capable of being controlled by controlling the potential applied to the control grid thereof; and a measurement system capable of measuring the voltage at the terminals of each switch.

Abstract: A system for dissipating regenerated electric energy produced by an electric actuator of an aircraft, the dissipating system including: a resistor; two switching arms, each switching arm being connected in series with the resistor, the two switching arms being connected together in parallel, each switching arm including two switches connected to one another in series, each switch including two terminals and a control grid, each switch being capable of being controlled by controlling the potential applied to the control grid thereof; and a measurement system capable of measuring the voltage at the terminals of each switch.