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 and one electrical protection delivering a DC voltage for a HVDC bus, each HVDC bus distributing this DC voltage to at least one electric motor through at least one of said energy inverters and one of said electrical protections,

• the propulsion architecture being characterized in that the energy source, the energy inverter, the electrical protection and the HVDC bus of one energy supply path are each dissimilar, respectively, from the energy source, from the energy inverter, from the electrical protection and from the HVDC bus of at least one other energy supply path.