Messier-bugatti-dowty

Safran Landing Systems

Messier-bugatti Inc.

Emmanuel Colin

Julien Thibault

Jean-Baptiste Vaney

Frédéric Ragot

Stephane Mudry

Franck Selles

Stéphane Mudry

Pierre Girod

The invention relates to a method of managing parking braking in a braking system for a vehicle fitted with at least one electric brake including at least one electric actuator having a pusher actuated by an electric motor for selectively applying a force against friction elements of the brake, the method comprising the steps of:

Method of managing parking braking in a braking system for a vehicle fitted with electric brakes

An electric brake for an aircraft wheel comprising a supportformed by a torsion tubeand by an actuator-carrier, a stackof disks mounted around the torsion tube, electromechanical actuatorscarried by the actuator-carrier, each actuator comprising an electric motorand a pusher, the electric motorbeing adapted to move the pusherfacing the stackof disks in order to apply a braking force selectively to the stackof disks; and temperature measurement means for measuring a temperature representative of a temperature that exists in the stackof disks. The temperature measurement means comprises at least one temperature sensorarranged in the pusherof one of the electromechanical actuatorsso as to be located in the immediate proximity of the stackof disks when the pusheris brought into contact therewith.

Electric brake for an aircraft wheel, the brake including an electromechanical actuator fitted with a temperature sensor

An asymmetrical electric braking architecture for aircraft, having plural electro-mechanical brake actuators (EBAs) for selectively applying a braking force on friction elements of braked wheels. The architecture comprises (1) a brake control unit (BCU) for acting in normal mode to generate braking setpoint values in response to a braking order, (2) electro-mechanical actuator controllers (EMACs), each including at least one inverter for supplying power to the EBAs in response to the braking setpoint values, (3) at least one emergency brake power and control unit (EBPCU) including at least one inverter for supplying power to some of the EBAs in response to a braking order; and (4) protection means for channeling power supplied by the EMACs or the EBPCU towards the actuators while preventing power from being diverted towards the architecture.

Asymmetrical electric braking architecture for aircraft

A braking system for an aircraft with electric brakes comprising plural electromechanical actuators (). The system comprises a braking control unit () delivering a normal braking setpoint () for one or more controllers () of the actuators, and selection logic () for causing the braking system to operate in a plurality of modes. The system includes: a normal braking mode where the control unit generates a normal braking setpoint () for the controller(s); an ultimate braking mode, having priority over the normal braking mode, being responsive to a parking control member, and controlling actuators to respond to the actuation of the parking control member; and a parking braking mode, applied in response to the parking control member and only if the aircraft is stationary, in which the actuators are controlled to apply a force in response to the parking control member being actuated and are then blocked in position.

Method for managing a braking system for an aircraft fitted with electromechanical brakes

The invention relates to a braking system architecture for an aircraft fitted with electromechanical brakes including at least one electromechanical actuator. In accordance with the invention, the architecture comprises at least one proximity unit disposed in the proximity of the brakes at the bottom of the undercarriage and including input/output means for collecting and calibrating at least signals coming from sensors associated with the brakes, and for transmitting the signals as processed in this way to control members for controlling the actuators by means of a communications bus running along the undercarriage, the proximity unit further including control means for controlling the blocking members of the actuators.

Braking system architecture for an aircraft fitted with electromechanical brakes

A wheel brake for an aircraft, the brake comprising a support () that receives at least one electromechanical actuator () fitted with a pusher () facing friction elements () and movable under drive from an electric motor () to apply a braking force selectively against the friction elements. The actuator is non-reversible such that a reaction force applied on the pusher cannot cause the electric motor to turn, and the actuator is associated with elements () for selectively switching off an electric power supply to the electric motor, which elements allow power to be delivered to the actuator in normal circumstances, and switch off the power if (a) the measured speed of rotation (w) of the electric motor drops below a first predetermined threshold (S); and (b) the commanded speed of rotation () of the electric motor drops below a second predetermined threshold (S).

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Paris, France

Emmanuel Colin