Electro-hydrostatic actuation system for a thrust reverser for an aircraft turbojet engine nacelle
AssigneeSafran Landing Systems
InventorJean-Baptiste Kamis
Life of this patent
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Abstract
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.
Claims11
A thrust reverser device for an aircraft turbojet engine nacelle comprising a first 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, each of the at least two actuators being attached to the first movable cover of the thrust reverser device and to move the first movable cover 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, a first of the at least two outlets being connected to a first of the at least two actuators and a second of the at least two outlets being connected to a second of the at least two actuators, the volumetric flow divider being configured to receive a fluid and to supply each of the at least two actuators with an equal flow rate.
Dependencies are inferred from the claim text.