Pump actuating device, and associated pumping system, aircraft and fuel supply method

An actuating device intended to drive at least one fuel pump of a fuel pumping system for an aircraft engine, the actuating device comprising:

• a motor rotating electric machine,
• a generator rotating electric machine, and
• an electrical connection member,
• the motor rotating electric machine being an asynchronous machine with Dahlander coupling comprising a first rotor, intended to be mechanically coupled to each pump for actuation thereof, and a first stator comprising at least one input phase, each input phase comprising two windings,
• the generator rotating electric machine comprising a second rotor, intended to be mechanically coupled to a shaft of the engine forming a drive shaft, and a second stator comprising at least one output phase,
• the electrical connection member being configured to electrically connect each output phase to an input phase,
• the electrical connection member being further configured so to connect, for each input phase, the corresponding windings in series or in parallel according to a speed of the engine.