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

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 (), —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.