Safran Landing Systems

Messier-Bugatti-Dowty

Safran Electrical & Power

Sylvain Jaber

Gilles Eluard

Vincent Bellenger

Nicolas Moretti

Raffi Cekic

Thierry Fontalbat

Florent Challas

Eric Wissemer

Quentin Galy

Christophe Cassagnet

Loic Blanco

Aircraft landing gears include at least one wheel, an electric taxiing system including an electric taxiing motor, brakes capable of slowing down or stopping the rotation of the wheel, and a cooling system for cooling the electric taxiing motor and the brakes. The cooling system includes ventilation means capable of mixing a first air flow originating from the brakes and a second air flow originating from outside the landing gear and of ventilating the electric taxiing motor with a mixture of the two air flows.

Landing gear of an aircraft and method for cooling an electric taxiing motor and brakes of such a landing gear

An aircraft wheel comprising a hub for mounting the wheel on a landing gear axle for rotation, and a rim with edge flanges for receiving a tire, the rim being secured to the hub by a web. The hub receives releasably a bearing box comprising two bearings, each having an inner and an outer ring mounted between a bushing for engaging on the axle with an outside wall shaped to receive the inner rings, the bushing having one end shaped as an abutment and another end shaped to receive a pre-loading nut. A sleeve extends around the bushing and has (1) an inside wall with shoulders to hold the outer rings axially and (2) an outer wall shaped to be received as a sliding fit in a bearing of the hub, with one end shaped as an abutment and another end shaped to receive a stop nut.

Aircraft wheel with a separable bearing box

The invention relates to a method for connecting in rotation an output member () of an electric motor () and an element () that is to be driven in rotation, comprising the use of at least one fusible pin () that links the output member and the element that is to be driven, and that has at least one section that is prone to fail in shear when a torque transmitted by the fusible pin exceeds a predetermined threshold. The method comprises the step of interposing, between the pin and either the output member or the element that is to be driven, at least one elastic member () comprising a first travel with a first stiffness followed by a second travel with a second stiffness greater than the first stiffness.

Method for connecting the rotor of an electric motor to an element that is to be driven

A method for rotationally driving an aircraft wheel, the wheel being equipped with a rim comprising two half-rims assembled by bolts (). According to the method, a drive member for generating a torque for driving the wheel is controlled. The transfer of the drive torque to the wheel is accomplished via the rim assembly bolts.

Method for rotationally driving an aircraft wheel

The invention relates to a method for managing an electric motor () intended to drive rotationally a wheel () of an aircraft (), the method comprising the step of short-circuiting the phases of the electric motor () when the aircraft () is in a period of deactivation of the motor () during which it is envisaged not using the electric motor ().

Growing community of inventors

Velizy-Villacoublay, France

Sylvain Jaber