Safran Landing Systems

Sébastien Dubois

Florent Fortier

Philippe Henrion

Florent Dauphin

Marc Quenerch'Du

Bertrand Euzet

Bertrand Dubacher

Aurélien Doux

Vincent Pavoine

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.

Aircraft landing gear with at least one motorized wheel configured to be positioned close to and remote from landing gear strut

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.

Aircraft landing gear with a motorized wheel selectively positionable relative to a landing gear strut

A method for protecting the landing gear of an aircraft against stroke-end shocks, the landing gear being manoeuvrable between a retracted position and a deployed position by means of a single electromechanical operating actuator () between these two positions. According to the invention, the method involves the step of equipping the electromechanical operating actuator with an internal damping device () arranged between an output shaft () of the electromechanical actuator coupled to the landing gear and a motor shaft () with a motor () of the electromechanical actuator.

Method for protecting the landing gear of an aircraft against impacts that may affect it

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.

Landing gear locking device

The invention provides a method of moving an aircraft undercarriage comprising a leg () that is movable between a deployed position and a retracted position in which the leg is held stationary by means of a strut () held in an aligned position by a stabilizer member (), the method including using a drive actuator () 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.

Method of moving an aircraft undercarriage between a deployed position and a retracted position

Methods of moving an aircraft undercarriage that is movable between a retracted position and a deployed position generally include: using a rotary electromechanical type drive actuator coupled to a portion of the aircraft undercarriage to raise it from the deployed position to the retracted position; disengaging the drive actuator during a descent of the undercarriage from the retracted position to the deployed position and using a hydraulic linear shock absorber coupled to a portion of the undercarriage to regulate the rate of descent and to absorb shock on arrival of the undercarriage in the deployed position; and neutralizing the shock absorber while raising the undercarriage.

Methods of moving an aircraft undercarriage between a retracted position and a deployed position

A landing-gear assembly () for an aircraft, the landing-gear assembly comprising: The first secondary damper () is carried by the axle shaft () and comprises:

Growing community of inventors

Velizy Villacoublay, France

Sébastien Dubois