The invention relates to an electrical architecture (2) for an aircraft, comprising: - a first propulsion power distribution network (16) distributing a high DC voltage, - a second propulsion power distribution network (18) distributing a high DC voltage, - a first AC power distribution network (46) distributing a three-phase AC voltage, - a second AC power distribution network (54) distributing a three-phase AC voltage, - a first inverter (44) connected between the first propulsion power distribution network and the first AC power distribution network, - a second inverter (52) connected between the second propulsion power distribution network and the second AC electrical distribution network, - an electronics module (60) 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.
ARCHITECTURE ÉLECTRIQUE POUR AÉRONEF
ELECTRICAL ARCHITECTURE FOR AN AIRCRAFT
ELEKTRISCHE ARCHITEKTUR FÜR EIN FLUGZEUG
2024-05-15
Patent
Electronic Resource
French
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