Safran Landing Systems

Florent Fortier

Sébastien Dubois

Florent Dauphin

Philippe Henrion

Sebastien Dubois

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

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:

Landing-gear assembly for an aircraft, the landing-gear assembly including a secondary shimmy damper

Aircraft landing gear () comprising: The first secondary damper () is carried by the first strut part () and comprises:

Growing community of inventors

Velizy Villacoublay, France

Florent Fortier