A device is for assisting the taxiing of an aircraft, using at least one engine and at least one braking member. The device includes a control member, adapted to be actuated by a pilot from a neutral position to define a taxiing piloting command and a central controller, adapted to operate pilot at least one engine of the aircraft to apply the taxiing command defined by the pilot. The central controller is also configured to pilot at least one braking member of the aircraft to apply the taxiing piloting command defined by the pilot.

An electrical architecture of an aircraft includes a plurality of primary generators each associated with a propulsion engine of the aircraft, a plurality of primary electrical networks each associated with a primary generator in nominal operating mode, a single-part secondary electrical network, an electrical energy accumulation device connected directly to the secondary network, a first electrical energy converter arranged between the secondary electrical network and a first of the primary electrical networks, allowing energy to be transferred from the first of the primary electrical networks to the secondary electrical network, the first electrical energy converter being intended to supply electrical energy to the electrical energy accumulation device in nominal operating mode, a second electrical energy converter arranged between the secondary electrical network and a second of the primary electrical networks, allowing energy to be transferred from the secondary electrical network to the second of the primary electrical networks.

A multi-disk brake system comprises an electrical generator disposed therein. The electrical generator is configured to convert mechanical energy to electrical energy. The mechanical energy may be generated during a braking event of the multi-disk brake system. The electric generator may power various electrical components on the aircraft or store the electrical energy in a capacitor bank. The electric generator may also act as a motor and/or power a landing gear in a motor configuration.

A convertible ducted fan engine and mounting system. The convertible ducted fan engine has a shroud encircling a mechanical fan. The convertible ducted fan engine includes a fluid-propulsion configuration in which the mechanical fan rotates freely with respect to the shroud to produce thrust through fluid flow, and a drive-wheel configuration in which the shroud rotates about the rotational axis.

A landing gear system includes wheel rotatably coupled to an axle. A driveshaft extends through a cavity formed in the axle and is rotatable about an axis. A planetary gear includes a sun gear operably coupled to the drive shaft and a planet gear operably engaging the sun gear. The planetary gear further includes a ring gear that surrounds and is operably coupled to the planet gear so that rotation of the drive shaft rotates the ring gear. A clutch assembly is selectively moveable between an engaged state and a disengaged state. The clutch assembly transfers rotation of the ring gear to the wheel when the clutch assembly is in the engaged state, and the clutch assembly does not transfer rotation of the wheel to the ring gear when the clutch assembly is in the disengaged state.

A landing gear of an aircraft includes a pair of wheels between which an electric actuator at least partially covered with a lightning arrester cowl is placed. The lightning arrester cowl has an insulating matrix onto which at least an electrical conductor is attached. The electrical conductor includes electrical connection means for connecting the electrical conductor to a ground conductor of the aircraft.

A landing gear of an aircraft having an upper portion intended to be joined to a structure of the aircraft and a lower portion provided with a first and second axle, the first axle being provided with a braked wheel and the second axle being provided with a motorised wheel, includes a first actuator that moves one of the axles between remote and close positions with respect to the upper portion while the other axle is kept stationary with respect to the upper portion. In one of the remote and close positions, and the wheels on the axles are simultaneously in contact with a running surface while, in the other position, each wheel on the second axle is at a distance from said running surface.

In one or more embodiments, the ground roll assist system is based on the electric in-wheel motors integrated with the main landing gear of an aircraft and linked to the aircraft control system. It is well known that modern electric motors possess superior torque density characteristics, potentially exceeding best in class internal combustion engines by more than an order of magnitude. Furthermore, electric motors performance is generally thermally limited, which makes it possible to achieve even higher performance for a short period of time.

An aircraft undercarriage including electrical equipment (2, 3) fastened to a portion (1) of the undercarriage and a lightning protection device (10) comprising at least one shield fastened to said portion (1) of the undercarriage by fastener means so as to extend in register with the electrical equipment (2, 3) in a position that is spaced apart therefrom, the shield comprising at least a first plate (11) made of electrically conductive material that is arranged to absorb a major portion of the heat energy that is generated by the passage of a lightning wave and to discharge the electric charge of the lightning wave. An aircraft fitted with such an undercarriage.

An improved serviceability gearing element generally includes a support having a plurality of obstacles for co-operating with teeth of a neighboring gearing element. The gearing element further includes a pin, a roller mounted to move in rotation about the pin via a rotary guide, blocking bearings shaped substantially to prevent the roller from moving in translation along the pin, and one or more fasteners for fastening at least one of the blocking bearings to the support.