Abstract: Aircraft braking system architecture comprising: a brake comprising electromechanical actuators (1, 2); a principal control channel (6) and an alternative control channel (7) comprising electrical components that are at least partly different and adapted to provide respectively a principal braking control function and an alternative braking control function that are at least partly different; power modules (15, 16) comprising electrical components that are at least partly different and adapted to generate electrical power supply currents (I1, I2) on the basis of principal control signals or alternative control signals; a surveillance unit (8) adapted to ensure that in normal operation the principal control signals are used and that in the event of a fault the alternative control signals are used to generate the electrical power supply currents.

Abstract: A braking system architecture for aircraft, the architecture comprising: a brake (20) comprising a plurality of electromechanical actuators (26), each electromechanical actuator including a digital communication module; at least one power supply unit (21, 22); two control units (23, 24), each control unit being connected to a distinct group of one or more electromechanical actuators and comprising an upstream digital communication module (27), a control module (28) arranged to generate digital control signals (Sn1, Sn2), and a downstream digital communication module (29) connected to the digital communication modules of the electromechanical actuators of said group in order to transmit the digital control signals to the power modules of said electromechanical actuators; and a digital communication network (25) to which the upstream digital communication modules (27) of both control units are connected.

Abstract: A piece of electrical equipment for connecting both to at least one electromechanical braking actuator and also to at least one electromechanical drive actuator, the piece of electrical equipment (13a) comprising a housing (30), means for fastening the housing to the undercarriage, and inside the housing: a processor unit (32) arranged to generate a braking motor control signal and a drive motor control signal; a power supply unit (37) arranged to generate an equipment power supply voltage, a braking power supply voltage, and a drive power supply voltage; a power converter unit (40) arranged to generate a braking control voltage and a drive control voltage; and a distribution unit arranged to distribute the braking control voltage to the electromechanical braking actuator and the drive control voltage to the electromechanical drive actuator.

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.

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.

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.

Abstract: A detection method for detecting the blocked or unlocked state of a parking brake member including a bistable linear electromagnet (1) connected both to a power supply component (14) arranged to generate a control voltage (Uc) and also to a current sensor (15) arranged to measure the control current (Ic), the detection method comprising the steps of: controlling the power supply component (14) to generate a test voltage (Utest) across the terminals of the coil and thus generate a test current (Itest) flowing in the coil, the test voltage having an amplitude less than a predetermined voltage threshold so that a test magnetic field generated by the test current does not move the shuttle; acquiring measurements of the test current as produced by the current sensor (15); and analyzing the measurements of the test current and detecting the blocked or unlocked state of the parking brake member on the basis of this analysis.

Abstract: 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.

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.

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.

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.

Abstract: Aircraft braking system architecture comprising: a brake comprising electromechanical actuators (1, 2); a principal control channel (6) and an alternative control channel (7) comprising electrical components that are at least partly different and adapted to provide respectively a principal braking control function and an alternative braking control function that are at least partly different; power modules (15, 16) comprising electrical components that are at least partly different and adapted to generate electrical power supply currents (I1, I2) on the basis of principal control signals or alternative control signals; a surveillance unit (8) adapted to ensure that in normal operation the principal control signals are used and that in the event of a fault the alternative control signals are used to generate the electrical power supply currents.

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.

Abstract: 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.

Abstract: A piece of electrical equipment for connecting both to at least one electromechanical braking actuator and also to at least one electromechanical drive actuator, the piece of electrical equipment (13a) comprising a housing (30), means for fastening the housing to the undercarriage, and inside the housing: a processor unit (32) arranged to generate a braking motor control signal and a drive motor control signal; a power supply unit (37) arranged to generate an equipment power supply voltage, a braking power supply voltage, and a drive power supply voltage; a power converter unit (40) arranged to generate a braking control voltage and a drive control voltage; and a distribution unit arranged to distribute the braking control voltage to the electromechanical braking actuator and the drive control voltage to the electromechanical drive actuator.

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.

Abstract: Architecture of an aircraft braking system having a brake (20) comprising a plurality of electromechanical actuators (25), with each electromechanical actuator (25) comprising a power module and a digital communication module (26). The brake digital communication modules are interconnected to form a digital network (30). The system also has two control units (22a, 22b) adapted for generating digital signals for controlling electric motors and one network interconnection member (23) 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.

Abstract: Architecture of an aircraft braking system comprising: a brake (20) comprising a plurality of electromechanical actuators (25), with each electromechanical actuator (25) comprising a power module and a digital communication module (26), with the brake digital communication modules being interconnected to form a digital network (30); two control units (22a, 22b) adapted for generating digital signals for controlling electric motors; one network interconnection member (23) 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.