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.
ARCHITECTURE ÉLECTRIQUE POUR AÉRONEF
ELECTRICAL ARCHITECTURE FOR AN AIRCRAFT
ELEKTRISCHE ARCHITEKTUR FÜR EIN FLUGZEUG
15.05.2024
Patent
Elektronische Ressource
Französisch
Europäisches Patentamt | 2021
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