Safran Landing Systems

Bertrand Dubacher

Philippe Henrion

Marc Quenerch'Du

Nicolas Nguyen

Sébastien Dubois

Bertrand Euzet

Marc Quenerch'du

Sebastien Dubois

Marc Quernerch'Du

Marc Quernerch'du

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

The invention provides a locking device for preventing movement between two elements () that are mounted to move relative to each other, the locking device including a lock () mounted to rotate relative to one of the elements in order to present successive angular positions for locking and for release in which the lock alternates between preventing and allowing relative movement between the two elements, the lock being constrained to rotate with a selector () of an angular indexing mechanism () actuated by a pulse-controlled actuator () arranged to push the selector against a spring member () in order to cause it to turn on each pulse and thereby cause the lock to pass from one angular position to the other.

Locking device with a pulse-controlled rotary lock

The invention relates to a method of driving an aircraft undercarriage between a deployed position and a retracted position, the undercarriage comprising a leg () that is hinged to a structure of the aircraft in order to be movable between those two positions and being stabilized in the deployed position by means of a brace member () comprising two limbs () that are hinged to each other, one of which is coupled to the leg and the other of which is coupled to the structure of the aircraft, the limbs being brought into an aligned position when the leg is in the deployed position. According to the invention, a rotary actuator () is arranged on the aircraft, which actuator comprises first and second cranks () that are mounted to turn freely about a common axis of rotation but that have a relative angular position that can be controlled, and that are arranged to stabilize the limbs of the brace member in the substantially aligned position.

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

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Velizy-Villacoublay, France

Bertrand Dubacher