Aircraft electric or hybrid propulsion architecture

An aircraft electric or hybrid propulsion architecture including at least two propulsion lines, each propulsion line including at least one electric motor supplied from at least two energy sources of the propulsion architecture through at least two energy supply paths, each energy supply path including at least one energy inverter, an energy source of the at least two energy sources and one electrical protection delivering a DC voltage for a HVDC bus, each HVDC bus distributing this DC voltage to the at least one electric motor through at least one additional energy inverter and at least one additional electrical protection,

• wherein a first energy source of the at least two energy sources, the at least one energy inverter, the at least one electrical protection and the HVDC bus of one of the at least two energy supply paths are each dissimilar in hardware or software, respectively, from a second energy source of the at least two energy sources, from the at least one energy inverter, from the at least one electrical protection and from the HVDC bus of at least one other of the at least two energy supply paths.