Electro-hydrostatic actuation system for a thrust reverser for an aircraft turbojet engine nacelle

A thrust reverser device for an aircraft turbojet engine nacelle comprising at least one movable cover configured to move between a retracted position and a deployed position with respect to the nacelle and an electro-hydrostatic actuation system, the electro-hydrostatic system comprising a motor pump, and a first actuation assembly, comprising:

• a series of at least two actuators configured to be attached to a movable cover of the thrust reverser device and to move the movable cover or covers between a retracted position and a deployed position relative to the nacelle;
• and
• a volumetric flow divider having an inlet connected to the motor pump and at least two outlets, each outlet being connected to one of the at least two actuators, the volumetric flow divider being configured to receive a fluid and to supply the actuators with an equal flow rate.