Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: The invention relates to a method for connecting in rotation an output member (5) of an electric motor (1) and an element (2) that is to be driven in rotation, comprising the use of at least one fusible pin (11) 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 (20) comprising a first travel with a first stiffness followed by a second travel with a second stiffness greater than the first stiffness.

Abstract: The invention relates to a method for connecting in rotation an output member (5) of an electric motor (1) and an element (2) that is to be driven in rotation, comprising the use of at least one fusible pin (11) 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 (20) comprising a first travel with a first stiffness followed by a second travel with a second stiffness greater than the first stiffness.

Abstract: The invention relates to an aircraft wheel comprising a hub (52) for mounting the wheel on a landing gear axle to enable the wheel to rotate about an axis of rotation, and a rim (55) with edge flanges for receiving a tire, the rim being secured to the hub by a web (56). The hub is adapted to receive releasably a bearing box (60) comprising two bearings (53, 54) each having an inner ring and an outer ring mounted between a bushing (61) for engaging on the axle with an outside wall shaped to receive the inner rings of the bearings, the bushing having one end (63) shaped as an abutment and another end shaped to receive a pre-loading nut (67); and a sleeve (62) extending around the bushing and having an inside wall presenting two shoulders to hold the outer rings of the bearings axially, the sleeve having an outer wall shaped to be received as a sliding fit in a bearing of the hub, with one end (68) shaped as an abutment and another end shaped to receive a stop nut (70).

Abstract: A method for rotationally driving an aircraft wheel, the wheel being equipped with a rim comprising two half-rims assembled by bolts (5). 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.

Abstract: The invention relates to a method for managing an electric motor (6) intended to drive rotationally a wheel (4) of an aircraft (1), the method comprising the step of short-circuiting the phases of the electric motor (6) when the aircraft (1) is in a period of deactivation of the motor (6) during which it is envisaged not using the electric motor (6).

Abstract: The invention relates to a method for rotationally driving an aircraft wheel, the wheel being equipped with a rim comprising two half-rims assembled by bolts (5), in which method a drive member for generating a torque for driving the wheel is controlled, characterized in that the method comprises the transfer of the drive torque to the wheel via the rim assembly bolts.

Abstract: The invention relates to a method for managing an electric motor (6) intended to drive rotationally a wheel (4) of an aircraft (1), the method comprising the step of short-circuiting the phases of the electric motor (6) when the aircraft (1) is in a period of deactivation of the motor (6) during which it is envisaged not using the electric motor (6).

Abstract: Method for managing the braking of a wheel (4) of an aircraft (1) fitted with a brake (11), the aircraft comprising brake control means suited to implementing an anti-skid function of the wheel (4), requiring an estimate of a rotational speed of the wheel, the aircraft further comprising means of driving the wheel including an electric motor (6) intended to drive the wheel (4) in rotation, the said electric motor (6) being fitted with a position sensor (8) intended to provide measurements of the angular position of a rotor of the motor (6). The method comprises the step, for implementing the anti-skid function, of estimating the rotational speed of the wheel (4) from measurements of the angular position of the rotor which are supplied by the position sensor (8).