ELECTRIC DRIVE SYSTEM FOR AN AIRCRAFT WITH A MINIMAL YAWING MOMENT

The disclosure relates to an electric drive system for an aircraft and to a corresponding operating method. The electric drive system includes a multiplicity of electric thrust generators, wherein each electric thrust generator has an electric motor, and a subsystem group including a multiplicity of subsystems. The thrust generators are apportioned unambiguously between the subsystems so that each subsystem includes two or more of the thrust generators. Furthermore, a control system for operating the drive system is provided, wherein the control system is configured to operate the drive system in such a way that, at least in the event that one of the subsystems of the subsystem group is faulty, an overall yawing moment which is composed of the sum of the yawing moments of the thrust generators of each non-faulty subsystem of the subsystem group essentially disappears.