Messier-bugatti-dowty

Messier-bugatti Inc.

Safran Landing Systems

Julien Thibault

Emmanuel Colin

Dominique Onfroy

Florent Nierlich

Olivier Frey

Stephane Mudry

Stéphane Mudry

Pierre Girod

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

The invention relates to a braking system architecture for an aircraft having wheelsbraked by means of respective brakes, each brake having a plurality of electromechanical actuators, the braking system having controllersfor distributing electric power Ps to the actuatorsin response to a braking setpoint, each controllerbeing associated with some of the actuators of any given brake. According to the invention, each controllerhas an input Ev for receiving information about the rotary speed of the wheelbraked by the actuators associated with said controller, the controller including processor meansfor modulating the power transmitted to the actuators as a function of the speed of rotation of the wheel in order to provide anti-skid protection.

Electromechanical braking system architecture

A braking actuator for a brake of an aircraft, the actuator comprising: The motor has first and second exciters adapted to move the movable portion of the motor and adapted to be powered independently from each other. The transmitter member of the position sensor comprises first and second transmitters adapted to be powered independently, and the receiver member generates the signal representative of position on being excited by at least one of the transmitters.

Electromechanical actuator with dual excitation

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

A method for distributing braking energy between a group of the braked wheels numbered 1 . . . p and fitted to N undercarriages of an aircraft, each of the braked wheels having a brake furnished with a stack of discs to which a load is selectively applied so as to generate a torque for braking the wheel. Each brake is equipped with a unit for measuring a thickness of the stack of discs, and in which&#x2014;the setting is an individual setting of braking to be generated by brake j, where p is the number of wheels concerned, C is the general setting of braking to be developed by the braked wheels of one and the same undercarriage, Eis the thickness of the stack of discs of the brake of wheel j, and Cthe individual braking setting for wheel j. Each brake is controlled according to the individual braking setting thus determined.

Method for distributing braking torque between braked wheels fitted to at least one undercarriage of an aircraft

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

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:

Method of controlling a vehicle brake with torque correction

The invention relates to a method of controlling an electromechanical brake for a vehicle wheel, the brake including an actuator provided with a pusher that is actuated by an electric motor and that is adapted to exert a braking force selectively on friction elements in response to an actuation setpoint, the method comprising the following steps:

Method of controlling a vehicle brake with compensation for expansion

The invention relates to a method of managing an electromechanical brake actuator comprising an electric motor adapted to move a pusher against a stack of disks to apply a braking force to the stack of disks, selectively, the method comprising the step of causing the actuator to operate in a given operating domain in the current/speed plane in such a manner that the operating domain is selected to present a boundary having a portion that extends substantially along a constant power curve plotted in the current/speed plane.

Method of managing an electromechanical brake actuator in particular for aircraft

The invention relates to a method of servo-control in a vehicle brake system including at least one electric brake having at least one actuator comprising a pusher facing friction elements and driven by an electric motor to apply a force selectively against the friction elements in response to a braking setpoint, the method making use of a plurality of relationships between various operating parameters of the actuator including a relationship between a pusher position and a corresponding force applied by the pusher to the friction elements. According to the invention, the method comprises the step of adjusting a particular relationship between position and force.

Method of servo-control in a braking system having electric brakes

The invention relates to a method of servo-control in a vehicle braking system that includes at least one electric brake provided with at least one actuator comprising a pusher facing friction elements and driven by an electric motor to apply a force selectively against the friction elements in response to a braking setpoint, the method making use of a relationship for transforming a setpoint for the braking that is to be applied by the pusher into a setpoint for the position of the pusher. The method of the invention includes the step of adjusting a particular relationship by imposing pauses in the position of the pusher.

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Gif sur Yvette, France

Julien Thibault