An aircraft with hybrid thermal/electrical propulsion includes a turbomachine; a first electrical source; a second electrical source equipped with an electrical energy storage device; a non-propulsion electrical distribution network; a low-voltage electrical distribution network; and a propulsion electrical distribution network. The three electrical distribution networks are electrically supplied by the first and second electrical sources and electrically interconnected by static converters.
ARCHITECTURE ÉLECTRIQUE POUR PROPULSION HYBRIDE
ELECTRIC ARCHITECTURE FOR HYBRID PROPULSION
ELEKTRISCHE ARCHITEKTUR FÜR HYBRIDANTRIEB
2024-06-26
Patent
Electronic Resource
French
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