Safran Landing Systems

Messier-bugatti-dowty

François Bonigen

Philippe Chico

Thomas Lepage

David Frank

Dominique Onfroy

Olivier Frey

Brian Goyez

Frédéric Ragot

Raphael Pierra

Raphaël Pierra

Frederic Ragot

Method for braking at least one wheel of an aircraft, the wheel being provided with a brake having at least one braking actuator, comprising the steps of:

Aircraft braking method comprising a dynamic correction of the braking command

Generally described, an architecture for an aircraft braking system is provided. The architecture includes a brake having friction members and electromechanical actuators, each electromechanical actuator having an electric motor and a power module; a computer arranged to produce digital control signals; a power unit arranged to produce an electrical power supply for powering the electric motors; and a junction box disposed on the undercarriage. The junction box may be configured to receive and to distribute the electrical power supply. The junction box generally includes an electrical motor control module that produces digital motor command signals from the digital control signals, and an electrical converter module that converts the digital motor command signals into analog motor command signals for the power modules of the electromechanical actuators.

Architecture for an aircraft braking system

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

A method for monitoring at least two aircraft wheel electromechanical braking actuators. For each electromechanical actuator, the method includes first determining a current value representative of the power supply current of the electromechanical actuator and determining a reference current value estimated from the power supply currents of at least one other electromechanical actuator. Then, the representative current value and the reference current value are compared. Any abnormal operation of the electromechanical actuator is detected when the difference between the representative current value and the reference current value is above a predetermined threshold.

Method for monitoring at least two electromechanical braking actuators

A method for monitoring a blocking member () of an electromechanical actuator (). The monitoring method comprising the steps of: determining a value representative of a power supply current of a motor () during an off-load operating phase of the electromechanical actuator (); comparing the value representative of the power supply current with a predetermined current threshold defined from nominal off-load operating characteristics of the electromechanical actuator (); and detecting an accidental locking of the blocking member () when the value representative of the power supply current is above or equal to the predetermined current threshold. There also is an electromechanical actuator () comprising a blocking member () monitored by such a method.

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Velizy-Villacoublay, France

François Bonigen