Safran Landing Systems

Safran Aircraft Engines

Jean-Baptiste Kamis

Jean-Charles Roger

Caroline Marie Frantz

Nicolas Nguyen

Yves Courtois De Lourmel

Sébastien Messe

Christelle Pettenazzi

Arnaud Le Breton

Thomas Prado

An actuator includes a body and at least a first offset connection port that is connected to the body by a first duct projecting from the body. The first connection port is mechanically connected to the body at least by first and second struts. The first strut and the second strut extend from the first connection port, respectively, to a first segment of the body and to a second segment of the body that is axially spaced apart from the first segment. An undercarriage includes such an actuator as its locking or unlocking actuator.

Actuator with offset supply port

A hydraulic assembly for an aircraft engine includes a pump with a housing and a rotor arranged inside the housing. The housing has at least one hydraulic line configured for the passage of a fluid; and a hydraulic transfer unit comprising: a hydraulic transfer block attached to the housing and comprising an internal fluid passage channel which communicates with the hydraulic line, and a casing which covers the transfer block and which is guided in rotation about an axis of revolution (Y) and about the transfer block, the casing having a fluid outlet port that communicates with the internal channel.

Hydraulic assembly for an aircraft engine

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.

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

A method for filling a hydraulic circuit of an electro-hydrostatic system includes connecting first and third shut-off valves to a discharge valve, and connecting a second shut-off valve to a filling valve, while the second and third shut-off valves are closed, opening the filling valve, the discharge valve and the first shut-off valve and operating a vacuum generator, once a vacuum has been established in the hydraulic circuit, opening the second shut-off valve in order to fill the hydraulic circuit with pressurized hydraulic fluid while the vacuum generator is still in operation, once the hydraulic circuit has been filled with fluid, closing the first shut-off valve and then opening the third shut-off valve in order to bypass the vacuum generator and circulate the fluid through the electro-hydrostatic system until the fluid contained in the hydraulic circuit reaches a predetermined pressure, and closing the discharge valve and the filling valve.

Method for filling a hydraulic circuit of an electro-hydrostatic system using a filling device

The invention relates to a hydraulic actuator comprising a cylinder () in which a piston () secured to a rod () is mounted so as to slide in a sealed manner in order to delimit in the cylinder a hydraulic extension chamber () and a hydraulic retraction chamber () that are connected to respective ports, the hydraulic actuator comprising means for slowing the piston when the piston approaches a retracted position. According to the invention, the slowing means comprise first and second hydraulic lines () extending between the extension port and the extension chamber, the first hydraulic line comprising a seat () while the piston bears a retractable finger () having an end () that comes to bear against the seat in order to close the first hydraulic line () when the piston approaches the retracted position, such that only the second hydraulic line () remains open while the piston completes its travel towards the retracted position. Landing gear and aircraft comprising such an actuator.

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Moissy-Cramayel, France

Jean-Baptiste Kamis