US 12,338,780 B2
Electro-hydrostatic actuation system for a thrust reverser for an aircraft turbojet engine nacelle
Jean-Baptiste Kamis, Moissy-Cramayel (FR)
Assigned to SAFRAN LANDING SYSTEMS, Velizy-Villacoublay (FR)
Appl. No. 18/556,057
Filed by SAFRAN LANDING SYSTEMS, Velizy-Villacoublay (FR)
PCT Filed Apr. 11, 2022, PCT No. PCT/FR2022/050686
§ 371(c)(1), (2) Date Oct. 18, 2023,
PCT Pub. No. WO2022/223904, PCT Pub. Date Oct. 27, 2022.
Claims priority of application No. 2104072 (FR), filed on Apr. 20, 2021.
Prior Publication US 2024/0200508 A1, Jun. 20, 2024
Int. Cl. F02K 1/76 (2006.01); F15B 7/00 (2006.01); F15B 20/00 (2006.01)
CPC F02K 1/763 (2013.01) [F15B 7/003 (2013.01); F15B 7/006 (2013.01); F15B 20/00 (2013.01); F15B 2211/20515 (2013.01); F15B 2211/20561 (2013.01); F15B 2211/40523 (2013.01); F15B 2211/426 (2013.01); F15B 2211/428 (2013.01); F15B 2211/7057 (2013.01)] 11 Claims
OG exemplary drawing
 
1. 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.