Abstract: This system comprises one of the battery modules coupled to at least one control device and formed of battery cells arranged in parallel coherent strings of battery cells, the battery modules being distributed in two independent networks including a high-voltage network and a low-voltage network coupled in series, the low-voltage network including a battery module including a first sub-network and a second sub-network electrically separated from the first sub-network by a physical separation element arranged on the battery module of said low-voltage network, characterised in that each battery module of the high-voltage network includes a number of parallel coherent strings of battery cells equal to the number of parallel coherent strings of battery cells of each battery module of the first sub-network.

Abstract: An electrical converter includes an inverter configured to provide at least one input AC voltage from an input DC voltage. The electrical converter further includes an AC-to-AC voltage converter configured to provide an output AC voltage from the at least one input AC voltage such that the output AC voltage has an amplitude that depends on a frequency of the at least one input AC voltage. A rectifier designed is configured to provide an output DC voltage from the output AC voltage.

Abstract: The present invention relates to a system for converting and transporting electrical energy in a turbomachine-propelled aircraft, said system including: at least a first rotary electric machine connected mechanically to the low-pressure shaft by means of a coupling device, a second rotary electric machine connected mechanically to the high-pressure shaft by means of an accessory gearbox, and said first electric power module and said second electric power module being connected electrically to an internal electrical network of the turbomachine, a generator coupled to the accessory gearbox and intended to supply an electrical network of the aircraft with electricity, and a control device for controlling start-up of the turbomachine by at least one rotary electric machine, for compensating for power consumed by the generator, and for implementing distribution between the power absorbed by the high-pressure shaft and the power absorbed by the low-pressure shaft.

Abstract: An electrical architecture for an aircraft includes a first propulsion power distribution system distributing a high DC voltage, a second propulsion power distribution system distributing a high DC voltage, a first AC power distribution system distributing a three-phase AC voltage, a second AC power distribution system distributing a three-phase AC voltage, a first inverter connected between the first propulsion power distribution system and the first AC power distribution system, a second inverter connected between the second propulsion power distribution system and the second AC power distribution system, and an electronics module connected to the first inverter and to the second inverter in order to control the frequency of the three-phase AC voltage generated by the first inverter and the frequency of the three-phase AC voltage generated by the second inverter.

Abstract: The present invention relates to a system for converting and transporting electrical energy in a turbomachine-propelled aircraft, said system including: at least a first rotary electric machine connected mechanically to the low-pressure shaft by means of a coupling device, a second rotary electric machine connected mechanically to the high-pressure shaft by means of an accessory gearbox, and said first electric power module and said second electric power module being connected electrically to an internal electrical network of the turbomachine, a generator coupled to the accessory gearbox and intended to supply an electrical network of the aircraft with electricity, and a control device for controlling start-up of the turbomachine by at least one rotary electric machine, for compensating for power consumed by the generator, and for implementing distribution between the power absorbed by the high-pressure shaft and the power absorbed by the low-pressure shaft.

Abstract: An electrical converter includes an inverter configured to provide at least one input AC voltage from an input DC voltage (VE). The electrical converter further includes an AC-to-AC voltage converter configured to provide an output AC voltage from the at least one input AC voltage such that the output AC voltage has an amplitude that depends on a frequency of the at least one input AC voltage. A rectifier is configured to provide an output DC voltage from the output AC voltage.

Abstract: An electrical architecture for an aircraft includes a first propulsion power distribution system distributing a high DC voltage, a second propulsion power distribution system distributing a high DC voltage, a first AC power distribution system distributing a three-phase AC voltage, a second AC power distribution system distributing a three-phase AC voltage, a first inverter connected between the first propulsion power distribution system and the first AC power distribution system, a second inverter connected between the second propulsion power distribution system and the second AC power distribution system, and an electronics module connected to the first inverter and to the second inverter in order to control the frequency of the three-phase AC voltage generated by the first inverter and the frequency of the three-phase AC voltage generated by the second inverter.

Abstract: Electrical distribution system for an aircraft comprising at least one computer communicating with the avionics (2), at least one computer (1) suitable for communicating with at least one computer communicating with the avionics (2), each computer containing stored data. The system comprises a context information storage device (4), suitable for storing a copy of the data stored in the different computers, and an updating device, suitable for determining that a computer has been replaced by determining that it does not hold the same data as the other computers of the distribution system and/or as the context information storage device (4), the updating device being suitable for controlling the downloading of the data from the context information storage device or from a computer communicating with the avionics, into the replaced computer.

Abstract: Electrical distribution system for an aircraft comprising at least one computer communicating with the avionics (2), at least one computer (1) suitable for communicating with at least one computer communicating with the avionics (2), each computer containing stored data. The system comprises a context information storage device (4), suitable for storing a copy of the data stored in the different computers, and an updating device, suitable for determining that a computer has been replaced by determining that it does not hold the same data as the other computers of the distribution system and/or as the context information storage device (4), the updating device being suitable for controlling the downloading of the data from the context information storage device or from a computer communicating with the avionics, into the replaced computer.