ELECTRICAL ARCHITECTURE OF AN AIRCRAFT

The invention relates to an electrical architecture of an aircraft comprising: a plurality of primary generators (GEN1, GEN2) each associated with a propulsion engine of the aircraft; a plurality of primary electrical networks (AC1, AC2, essential AC) each associated with a primary generator in nominal operating mode; a single-part secondary electrical network (RES); an electrical energy accumulation device (BAT-HVDC) connected directly to the secondary network; a first electrical energy converter (CP1) arranged between the secondary electrical network and a first of the primary electrical networks, allowing energy to be transferred from the first of the primary electrical networks to the secondary electrical network, the first electrical energy converter (CP1) being intended to supply electrical energy to the electrical energy accumulation device in nominal operating mode; a second electrical energy converter (CP2) arranged between the secondary electrical network and a second of the primary electrical netwo