An electric architecture for a twin-engined, hybrid thermal/electric propulsion aircraft and, for each turboshaft which includes a high-voltage DC propulsive electric distribution network, a non-propulsive electric distribution network which is connected to loads of the aircraft, and an electric distribution network which is connected to loads of an electrified control system of the turboshaft engine, and wherein power supply sources are shared for these different networks.
Electric architecture for a hybrid thermal/electric propulsion aircraft and twin-engined aircraft comprising such an architecture
24.09.2024
Patent
Elektronische Ressource
Englisch
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