Braking system architecture for aircraft

Patent metadata

Field	Value
Publication number	US-10604240-B2
Application number	US-201715853408-A
Country	US
Kind code	B2
Filing date	Dec 22, 2017
Priority date	Dec 23, 2016
Publication date	Mar 31, 2020
Grant date	Mar 31, 2020

Abstract

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.

First claim

The embodiments of the invention in which an exclusive property or privilege is claimed are defined as follows:

1. A braking system architecture for aircraft, the architecture comprising:
a brake for braking a wheel of an undercarriage of the aircraft, the brake including friction members and electromechanical actuators for applying a braking force against the friction members and thereby 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 and arranged to receive the first control signals, the junction box comprising electrical processor means configured and arranged to use the first control signals to produce second control signals for application to the electromechanical actuators in order to control the electromechanical actuators,
wherein each electromechanical actuator includes a body having integrated therein an electric motor, a power module for generating a power supply current for the electric motor, and a digital communication module, and
wherein the electrical processor means of the junction box including a digital switch.

2. The architecture according to claim 1 , wherein the first control signals and the second control signals comprise digital signals for controlling the electric motors.

3. The architecture according to claim 1 , wherein the digital communication module is arranged to perform a function of monitoring and controlling the electric motor of the electromechanical actuator, and wherein the first control signals and the second control signals comprise digital braking control signals.

4. An aircraft, comprising:
a brake configured to brake a wheel of an undercarriage of the aircraft, the brake including one or more electromechanical actuators;
a computer situated in a fuselage of the aircraft and configured to produce first control signals; and
a junction box situated on the undercarriage and electrically connected to the computer and to the one or more electromechanical actuators, the junction box being configured to receive the first control signals, the junction box comprising an electrical processor configured to use the first control signals to produce second control signals for application to the electromechanical actuators in order to control the electromechanical actuators,
wherein each electromechanical actuator includes a body having integrated therein an electric motor, a power module for generating a power supply current for the electric motor, and a digital communication module, and
wherein the electrical processor means of the junction box includes a digital switch.

5. The aircraft according to claim 4 , wherein the first control signals and the second control signals comprise digital signals for controlling the electric motor.

6. The aircraft according to claim 4 , wherein the digital communication module is configured to perform a function of monitoring and controlling the electric motor of the electromechanical actuator, and wherein the first control signals and the second control signals comprise digital braking control signals.

Assignees

• Goyez Brian
• Onfroy Dominique
• Frey Olivier
• Safran Landing Systems

Inventors

• Goyez Brian
• Onfroy Dominique
• Frey Olivier

Classifications

• B60T8/325

  Systems specially adapted for aircraft · CPC title

• F16D2121/24

  using motors · CPC title

• B64C25/44 Primary

  Actuating mechanisms · CPC title

• B60T8/1703

  for aircrafts · CPC title

• B60T13/741

  acting on an ultimate actuator · CPC title