公开(公告)号：US20230234700A1

公开(公告)日：2023-07-27

申请号：US18009260

申请日：2021-06-10

Applicant: SAFRAN LANDING SYSTEMS

Inventor： Sébastien DUBOIS ,  Philippe HENRION ,  Florent FORTIER

IPC: B64C25/32 ,  B64C25/34 ,  B64C25/42 ,  B64C25/60

CPC classification number: B64C25/405 ,  B64C25/34 ,  B64C25/42 ,  B64C25/60 ,  B64C2025/008

Abstract: A landing gear of an aircraft having an upper portion intended to be joined to a structure of the aircraft and a lower portion provided with a first and second axle, the first axle being provided with a braked wheel and the second axle being provided with a motorised wheel, includes a first actuator that moves one of the axles between remote and close positions with respect to the upper portion while the other axle is kept stationary with respect to the upper portion. In one of the remote and close positions, and the wheels on the axles are simultaneously in contact with a running surface while, in the other position, each wheel on the second axle is at a distance from said running surface.

公开(公告)号：US20240199202A1

公开(公告)日：2024-06-20

申请号：US18565017

申请日：2022-05-25

Applicant: SAFRAN LANDING SYSTEMS

Inventor： Florent FORTIER ,  Sébastien DUBOIS ,  Philippe HENRION

IPC: B64C25/32 ,  B64C25/00

CPC classification number: B64C25/405 ,  B64C2025/008

Abstract: An aircraft has an upper portion and a lower portion provided with a first and second axle. The first axle is provided with a braked wheel and the second axle is provided with a motorized wheel. A landing gear of the aircraft includes a main arm pivoting with respect to the strut on which the first axle is fixed. The second axle is fixed on the strut, and a main actuator moves the first axle between a remote position and a close position with respect to the upper portion. In the close position, the braked and motorized wheels are simultaneously in contact against a running plane, and in the remote position, the braked wheels are in contact against the running plane while the motorized wheel is at a distance from the running plane.

公开(公告)号：US20230356830A1

公开(公告)日：2023-11-09

申请号：US18011939

申请日：2021-06-21

Applicant: SAFRAN LANDING SYSTEMS

Inventor： Sébastien DUBOIS

IPC: B64C25/22 ,  B64C25/26

CPC classification number: B64C25/26 ,  B64C25/22

Abstract: A locking device locks a landing gear mounted in rotation on an aircraft and includes a deployment hydraulic jack including a first chamber connected to a first hydraulic supply and a second chamber connected to a second hydraulic supply. The locking device includes a hydraulic actuator connected to a rotary distributor. The rotary distributor includes a coupling operationally connecting the rotary distributor to a strut of the landing gear, a first supply port fluidly connected to the first hydraulic supply, and a first outlet port fluidly connected to the hydraulic actuator.

公开(公告)号：US20190176972A1

公开(公告)日：2019-06-13

申请号：US16214964

申请日：2018-12-10

Applicant: SAFRAN LANDING SYSTEMS

Inventor： Philippe HENRION ,  Sébastien DUBOIS ,  Bertrand EUZET ,  Marc QUENERCH'DU

IPC: B64C25/24 ,  B64C25/34

Abstract: The invention provides a method of moving an aircraft undercarriage comprising a leg (1) that is movable between a deployed position and a retracted position in which the leg is held stationary by means of a strut (2) held in an aligned position by a stabilizer member (4), the method including using a drive actuator (10) for raising the undercarriage from the deployed position to the retracted position. According to the invention, the actuator is coupled firstly to the leg and secondly to the stabilizer member in such a manner that on being activated the actuator begins by causing the stabilizer member to unlock and then moves the undercarriage leg towards the retracted position.

公开(公告)号：US20180111678A1

公开(公告)日：2018-04-26

申请号：US15395058

申请日：2016-12-30

Applicant: SAFRAN LANDING SYSTEMS

Inventor： Florent DAUPHIN ,  Florent FORTIER ,  Sébastien DUBOIS

IPC: B64C25/62 ,  B64C25/34 ,  B64C25/50

CPC classification number: B64C25/62 ,  B64C25/34 ,  B64C25/50 ,  B64C25/505

Abstract: A landing-gear assembly (1) for an aircraft, the landing-gear assembly comprising: an axle shaft (2); a leg (3) presenting a first portion (3a) carrying said axle shaft (2) and a second portion (3b) connected to a carrier structure of the aircraft; a main damper (5); and a first secondary damper (6a) distinct from the main damper (5). The first secondary damper (6a) is carried by the axle shaft (2) and comprises: an inertial mass (M); and connection means (7a) between the inertial mass (M) and the axle shaft (2) damping movements of the inertial mass (M) along a first axis (X1) of movement of the inertial mass (M) relative to the axle shaft (2), said first axis of movement (X1) extending in a plane (P) perpendicular to said steering axis (Z).