ELECTRIC ARCHITECTURE FOR A HYBRID THERMAL/ELECTRIC PROPULSION AIRCRAFT AND TWIN-ENGINED AIRCRAFT COMPRISING SUCH AN ARCHITECTURE

摘要

The invention relates to an electric architecture for a twin-engined, hybrid thermal/electric propulsion aircraft and, for each turboshaft engine, the architecture comprises: - a high-voltage DC propulsive electric distribution network (32), - a non-propulsive electric distribution network (56) which is connected to loads of the aircraft, and - an electric distribution network (76) 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.