TECHNICAL FIELD

Embodiments of the present disclosure relate to the field of braking system architectures for aircraft.

BACKGROUND

With reference toFIG. 1, a known centralized architecture for an electric aircraft braking system comprises a plurality of brakes1, each serving to brake a wheel of an undercarriage of the aircraft.

Each brake1has four electromechanical braking actuators2, which are grouped together in two distinct groups of two electromechanical actuators2. The two electromechanical actuators2of each distinct group are connected to the same computer3situated in the fuselage of the aircraft, above the undercarriage.

The electric motor of each electromechanical actuator2receives three-phase electrical power from the computer3to which the electromechanical actuator2is connected, and each electromechanical actuator2transmits measurements of a servo-control parameter to the computer3, e.g. measurements of the angular position of the rotor of the electric motor. The computers3implement functions of monitoring and controlling the electromechanical actuators2, and also functions of generating power by making use of inverters.

It can be seen that that centralized architecture requires the use of at least ten electric wires per electromechanical actuator2: three power supply wires4for the three phases for powering the electric motor, four communication wires5for returning the measurements of the angular position of the rotor of the electric motor to a centralized computer3, and two power supply wires and a ground wire (not shown inFIG. 1) for controlling a member that blocks the electromechanical actuator2so as to act as a parking brake.

These electric wires are integrated in harnesses that run from the fuselage of the aircraft to the brake1and that are therefore bulky and heavy. The long length of the harnesses conveying the power supply wires4(and thus conveying the currents powering the electric motors) requires the computers3to incorporate common mode filter circuits. The filter circuits add weight, complexity, and cost to the computers3and thus to the braking system.

SUMMARY

In accordance with an aspect of the present disclosure, a braking system architecture for aircraft is provided. In an embodiment, the architecture comprises:

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 arranged to receive the first control signals, the junction box is 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. In an embodiment, the junction box employs an electrical processor means or processing circuit for using the first control signals to produce second control signals for application to the electromechanical actuators in order to control the electromechanical actuators.

Using the junction box makes it possible to mutualize generating the second control signals from the first control signals, thereby reducing the number of cables extending from the fuselage of the aircraft to the brake. The number of components for performing functions is also reduced, since they can be mutualized in the junction box, thereby reducing the weight and the complexity of the braking system, and improving its reliability.

