A thrust reverser device for an aircraft turbojet engine nacelle an electro-hydrostatic actuation system that includes a motor pump and a first actuation assembly. The first actuation assembly includes a series of at least two actuators configured to be attached to a movable cover of the thrust reverser and to move the movable cover or covers between a retracted position and a deployed position relative to the nacelle. The first electro-hydraulic actuation system further includes a volumetric flow divider with an inlet connected to the motor pump and at least two outlets, wherein each outlet is connected to an actuator. The volumetric flow divider is configured to receive a fluid and to supply the fluid to the actuators with an equal flow rate.

The disclosure relates to a hydraulic system for pressure supply of a hydraulic actuator, comprising a double-acting hydraulic cylinder having two pressure chambers, and a rapid traverse device integrated into a valve unit and configured to hydraulically interconnect the two pressure chambers in a rapid traverse mode and hydraulically separate the two pressure chambers in a normal traverse mode. The valve unit connects to the pressure chambers via first and second connections and comprises a third connection for applying pressure via a hydraulic pump. A displaceably mounted shift piston separates the first and second connections in normal traverse position and connects them, separated from the third connection, in rapid traverse position. The valve unit integrates a preload device having a switchable preload element configured to separate the third connection from the second connection in a locking position, thereby locking the pressure chamber connected to the second connection towards the outside.