The invention relates to a hybrid electrical architecture (101) for an aircraft (103) which comprises a turbomachine (107) and a reduction gearbox (111) intended to rotate at least one propulsion member (105) of the aircraft (103). The architecture (101) also comprises at least one low-voltage electrical network (113) with at least one low-voltage electric machine (117, 118) mounted on the reduction gearbox (111) or on the turbomachine (107) and a high-voltage electrical network (125) with high-voltage electric machines (129) mounted on the turbomachine (107).
ARCHITECTURE ELECTRIQUE HYBRIDE D'AERONEF
HYBRID ELECTRICAL ARCHITECTURE FOR AN AIRCRAFT
HYBRIDE ELEKTRISCHE ARCHITEKTUR FÜR EIN FLUGZEUG
12.03.2025
Patent
Elektronische Ressource
Französisch
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