Safran Landing Systems

Messier-Bugatti-Dowty

Safran Electrical Components

Thierry Blanpain

Nicolas Nguyen

Edouard Campbell

Dominique Ducos

Philippe Henrion

Pierre-Yves Liegeois

Vincent Pascal

Sébastien Remond

Yves Courtois De Lourmel

Aurélien Doux

Yannick Senechal

Frédéric Ivaldi

Laurent Mallet

Alexandre Daulny

Remi Finet

Olivier Piqueux

Stéphane Basset

Didier Brun

Matteo Capurro

Clément Castellan

Alexis Tovar

Yann Simonneaux

Dominique Chauvet

Martial Monseu

Frederic Ivaldi

Aurelien Doux

Sebastien Remond

Rémi Finet

Pierre-Yves Liegois

A landing gear for an aircraft having an axle carried by a strut, the axle including a rotatably-mounted wheel and a drive device for rotating the wheel about a rotation axis. The drive device can have a motor mounted at one end of the axle for transmitting a rotational torque to the wheel, a body projecting out of the motor and snugly received in the axle, and at least a first harness extending along the body and connecting the motor to at least a first coupler carried by a free end of the body to cooperate with a second coupler of the landing gear to supply the motor with power. The second coupler received in an opening formed in the axle at the junction between the strut and the axle, the opening extending along an axis perpendicular to the axis of rotation of the wheel.

Device for rotating an aircraft wheel

An aircraft landing gear having a male part interlocked with a female part along an interlocking direction is provided. The external contact surface of the male part, when it is observed along the interlocking direction, can be an exclusively convex closed surface having external contact surface portions in the form of rounded lobes that form obstacles to the pivoting of the female part with respect to the male part about the interlocking direction. The aircraft landing gear is suitable for use with an aircraft.

Aircraft landing gear having interlocked male and female parts for transmitting mechanical torque

An aircraft undercarriage comprising: a leg connected to an aircraft structure to be movable between a deployed position and a retracted position; a brace member for holding the leg in its deployed position and comprising a first rod hinged to the aircraft structure and a second rod hinged to the first link and to the leg; a stabilizer member for holding the first and second rods in an aligned position and comprising a first link and a second link that are hinged to each other, with at least one of them being hinged to the brace member; and a spring for elastically urging the hinges of the first and second links into a generally aligned position. The spring comprises at least one spring blade arranged to be subjected to an axial compression force when the first and second links leave the generally aligned position.

Aircraft landing gear provided with a leaf spring locking device

A landing gear includes structural parts arranged to connect a wheel to a structure of an aircraft, each structural part including two or more interfaces for connection to one or more other of the structural parts or to the structure of the aircraft and two or more webs which extend so as to face one another while delimiting between them a free space and which connect the two interfaces in order to transmit the forces from one to the other.

Landing gear with reinforcing web

A method of moving a door of a well for an aircraft undercarriage during sequences of deploying or retracting the undercarriage includes: using a temporary mechanical connection between the door and the undercarriage that is effective when the undercarriage is close to its retracted position, causing the door to be opened by the undercarriage while the undercarriage is being deployed and causing the door to be closed by the undercarriage while the undercarriage is being retracted, but releasing the door from the undercarriage when the undercarriage is close to its deployed position, and using a door actuator acting on the door to close and open the door when the undercarriage is in its deployed position and the temporary mechanical connection is interrupted.

Method of moving doors of a well for an aircraft undercarriage

An aircraft undercarriage having a sliding rod slidably mounted in a strut-leg, and a scissors linkage () having one branch () hinged to the strut-leg or to a turning element of a control for steering the sliding rod mounted to turn in the strut-leg, and one branch () hinged to the sliding rod, the branches being hinged to each other by a pivot pin (), the undercarriage being fitted with a shimmy-attenuator device () placed on the pivot pin of the shimmy-attenuator, the attenuator device including threshold resilient return means generating a force returning the branches towards a rest position, and at least damping means generating a damping force when the branches move axially along the pivot pin. The attenuator device comprises two modules () placed on either side of the scissors linkage in order to co-operate with the pivot pin, each of the modules performing at least one of the damping function and the threshold resilient return function.

Aircraft undercarriage fitted with a shimmy-attenuator device

The invention provides a method of mounting an aircraft wheel drive member () on an undercarriage having an axle () that carries the wheel and that is provided with a torque plate () having an outside face against which a brake can be fitted, the method comprising the steps of fitting a support () that bears against an inside face of the torque plate opposite from its outside face against which a brake () is fitted, and of fitting the drive member on the support.

Method of fastening an aircraft wheel drive member on an undercarriage carrying a wheel

The invention relates to an aircraft landing gear equipped with a steering device () for orienting the wheels (), the steering device () comprising a body () in which is incorporated an electromechanical actuator () equipped with an electric motor (). The landing gear is further equipped with damping means intended to limit the transmission of vibration from the wheel () to the rest of the landing gear () when the aircraft is on the ground. The body () of the steering device () is mounted with the ability to rotate with a limited amplitude of rotation. The damping means are mounted between the body () of the steering device () and the strut assembly () of the landing gear to damp the vibration between the body () of the steering device () and the strut assembly ().

Aircraft landing gear

Aircraft undercarriage leg including an axle () that bears at least one wheel (), the undercarriage leg being equipped with a unit () for driving rotation of the wheel, wherein the drive unit is rigidly fixed to the axle and a deformable support () extends between a cantilevered portion of the drive unit and a portion of the undercarriage leg not including the axle to support the cantilevered portion of the drive unit.

Aircraft undercarriage leg including a unit for driving the wheels

A device for coupling an actuator for operating an aircraft undercarriage to an aircraft structure. The device comprises a lever having a first end for hinging to the structure of the aircraft, and a second end to which the actuator is hinged, a pre-loading structure acting on the lever to urge it towards a stable rest position that is occupied by the lever in the absence of any force transiting through the actuator; and an abutment structure defining at least one working position for the lever when the actuator is activated.

Device for coupling an actuator for controlling the landing gear of an aircraft

The invention provides a device () for guiding a cable () in a duct (), the device () being characterized in that it comprises at least one guide tube () receiving the cable () and at least one expandable clamp () secured to one end () of the tube (), the expandable clamp () being deployed so as to be blocked against the inside wall of the duct () in order to hold the tube () in the duct (). The device serves to guide and hold the cable in the duct without damaging the duct.

Growing community of inventors

Velizy-Villacoublay, France

Thierry Blanpain