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.

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 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.

An electric braking system (1) for braking an aircraft, the system comprising: a brake (3) comprising an electromechanical actuator (5) designed so that when it applies a force to the friction members (4) that is less than or equal to a first maximum threshold, no degradation of the actuator occurs, and when it applies a force to the friction members (4) that is greater than the first maximum threshold, degradation is likely to occur; control means (7) configurable to occupy a first mode in which the controlled braking force cannot exceed the first maximum threshold, and to occupy a second mode in which the controlled braking force can reach the second maximum threshold; and configuration means (10) arranged to configure the control means (7) to occupy the second mode when in a situation preceding a potential interruption of takeoff (RTO) of the aircraft, and otherwise to occupy the first mode.

A device is for assisting the piloting in acceleration of an aircraft in taking in order to control its speed. The comprises a control member, adapted to be actuated by a pilot from a neutral position to define a taxiing piloting command for controlling the speed of the aircraft 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 taxiing piloting command is an acceleration or deceleration command of the aircraft during taxiing.

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.

A method for controlling an aircraft when taxiing comprising the steps of: measuring an angle of rotation of an active side stick about a first axis and a second axis; receiving an aircraft signal representative of an actual state of the aircraft; generating a control signal based on at least one of: the aircraft signal and the angle of rotation of the active side stick about a first axis and a second axis; transmitting the control signal to the aircraft, whereby the control signal causes an action affecting the actual state of the aircraft; determining a required state of the aircraft; generating a user feedback signal based on at least one difference between the actual state and the required state; and carrying out a user feedback action based on the user feedback signal.

Braking systems and methods for an electrical vertical takeoff and landing aircraft are provided. A braking system may contain a pilot control device, brakes, wheels, sensors, and a controller. Pilot controls the pilot control device to transmit information to the controller such that the aircraft will slow down.

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.