Safran Landing Systems

Messier-bugatti-dowty

Messier-bugatti Inc.

Dominique Onfroy

Olivier Frey

Brian Goyez

Julien Thibault

David Frank

Philippe Chico

Eric Evenor

Thomas Lepage

François Bonigen

Franck Selles

Steve Coustenoble

Raphael Pierra

Frédéric Ragot

Stephane Mudry

Raphaël Pierra

Frederic Ragot

Frédéeric Ragot

Stéphane Mudry

A wheel-braking system architecture for an aircraft is provided. The architecture includes a friction brake; an electromechanical actuator associated with a power module connected to a digital communication module by a first driver module; and a controller having both a power supply unit for powering the power module by delivering a power supply voltage (Vc) thereto, and also a control unit connected to the digital communication unit in order to transmit a digital control signal to the digital communication module. The control unit can be connected to the driver unit by an analog wired connection in order to transmit that to a first analog braking order from which the first driver module drives the power module to produce a degraded power supply current for the actuator.

Distributed braking architecture with improved safety

An aircraft brake system comprising: The invention also relates to an aircraft equipped with this system.

Aircraft brake system with dissimilar control devices and software module used in the event of a fault

Aircraft braking system architecture comprising:

Aircraft braking system architecture

A braking system architecture for aircraft, the architecture comprising: a brake including friction members and electromechanical actuators for exerting a braking torque on the wheel; a computer situated in the fuselage of the aircraft and arranged to produce first control signals; and a junction box situated on the undercarriage, the junction box being connected to the computer and to the electromechanical actuators, the junction box being configured to receive the first control signals and to use the first control signals to produce second control signals for application to the electromechanical actuators in order to control the electromechanical actuators.

Braking system architecture for aircraft

An aircraft braking system comprising: a first group (Ga) of actuators and a second group (Gb) of actuators. A first control module () is adapted, in a nominal mode, to control the first group, and in a reconfigured mode, to control the first group and the second group. A second control module () is adapted, in a nominal mode, to control the second group, and in a reconfigured mode, to control the first group and the second group. A monitoring unit adapted is adapted to monitor the first control module and the second control module, and to put the first control module into the reconfigured mode of operation when the monitoring unit detects a failure of the second control module, and to put the second control module into the reconfigured mode when the monitoring unit detects a failure of the first control module.

Aircraft braking system having a high level of availability

An aircraft landing gear comprising an axle (), a wheel () borne by the axle, a stack of discs () arranged to impose a braking torque on the wheel in response to a pressure imposed on the stack of discs, at least one electromechanical actuator () extending facing the stack of discs in order in a controlled manner to apply the imposed pressure to the stack of discs, and an actuator bearer () designed to bear the electromechanical actuator. The electromechanical actuator is fixed to the actuator bearer while at the same time being demountable. The actuator bearer is incorporated into the axle in such a way that the axle and the actuator bearer form a single component. There also is a method of demounting a stack of discs from such a landing gear.

Aircraft landing gear

Architecture of an aircraft braking system having a brake () comprising a plurality of electromechanical actuators (), with each electromechanical actuator () comprising a power module and a digital communication module (). The brake digital communication modules are interconnected to form a digital network (). The system also has two control units () adapted for generating digital signals for controlling electric motors and one network interconnection member () connected to two control units and incorporated in the digital network for distributing the digital control signals to the digital communication modules via the digital network.

Architecture of an aircraft braking system

An aircraft electromechanical braking system comprising a braking control unitand at least one electromechanical brake, the brakebeing fitted with at least one electromechanical actuatorhaving a pushersuitable for being moved by means of an electric motor. The actuatoralso has a blocking memberfor blocking the pusherin position. The control unitis adapted to cause the braking system to operate in an additional braking mode referred to as 'combined' mode, in which the motoris activated to bring the pusherinto a position in which it exerts a given holding force, and then the blocking memberis activated, while activation of the motoris maintained.

System for maintaining a pressing force by the combined action of two members

The invention relates to a method of controlling a vehicle brake adapted to exert a braking force in response to an actuation setpoint, in which:

Method of controlling a vehicle brake with adaptive torque correction

The invention relates to a method of controlling a vehicle brake that is adapted to exert a braking force in response to an actuation setpoint, the method comprising the following steps:

Growing community of inventors

Velizy-Villacoublay, France

Dominique Onfroy