Safran Landing Systems

Messier-Bugatti-Dowty

Nicolas Nguyen

Thierry Blanpain

Philippe Henrion

Yves Courtois De Lourmel

Dominique Ducos

Jean-Baptiste Kamis

Bertrand Dubacher

Sébastien Messe

Laurent Mallet

Frédéric Ivaldi

Arnaud Le Breton

Alexandre Daulny

Clément Castellan

Matteo Capurro

An aircraft landing gear includes a stationary element and one or more movable elements which can move relative to the stationary element between a first position and a second position, and one or more shape sensors, connected to an electronic processor arranged to deduce the position of the movable element of the shape of the shape sensor. The shape sensor includes a first section rigidly connected to the stationary element and a second section rigidly connected to the movable element so that the first section and the second section are immobile with respect to the stationary element and the movable element respectively, and are movable relative to one another.

Aircraft landing gear provided with a shape sensor

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

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

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

Aircraft landing gear having a leg () for hinging to a structure of the aircraft so as to be movable between a deployed position and a retracted position, a main brace (), a secondary brace (), and a double-acting type unlocking actuator () having a first end coupled to the secondary brace and controllable for causing its links to move out of alignment against the action of the resilient member during retraction or deployment of the landing gear. The landing gear includes couplers () for coupling to a second end of the unlocking actuator, which couplers ensure movement of said second end relative to the leg so that, for a given action, the unlocking actuator tends to break the alignment of the links when the landing gear is in one of its positions and tends to confirm said alignment when the landing gear is in its other position.

Growing community of inventors

Velizy Villacoublay, France

Nicolas Nguyen