Actuation system for an aircraft engine lubrication pump and associated aircraft

Actuation system for a lubrication pump of an aircraft engine, including a generator rotating electric machine, a drive rotating electric machine, a control device and a matrix of switches,

• the generator rotating electric machine comprising a first rotor, intended to be mechanically coupled to a shaft of the engine forming a drive shaft, and a first stator comprising at least one output stator winding,
• the drive rotating electric machine comprising a second rotor, intended to be mechanically coupled to the lubrication pump for its actuation, and a second stator comprising at least one input stator winding,
• the matrix of switches being electrically connected, on the one hand, to the at least one output stator winding and, on the other hand, to the at least one input stator winding so as to electrically connect or disconnect the at least one output stator winding and the at least one input stator winding to/from each other according to a state of the matrix of switches,
• the control device being configured to, according to a state of a control signal, control the matrix of switches so as to electrically connect the at least one output stator winding and the at least one input stator winding to each other or not,
• the control device further being configured to control the matrix of switches, according to a direction of rotation of the first rotor of the generator unit, in order to connect the at least one output stator winding and the at least one input stator winding to each other so that a direction of rotation of the second rotor remains unchanged, regardless of the direction in which the first rotor of the generator unit is driven in rotation.