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 wheel-braking system architecture for an aircraft is provided. The architecture includes a friction brake; an electromechanical actuator associated with a power module connected to a digital communication module by a first driver module; and a controller having both a power supply unit for powering the power module by delivering a power supply voltage (Vc) thereto, and also a control unit connected to the digital communication unit in order to transmit a digital control signal to the digital communication module. The control unit can be connected to the driver unit by an analog wired connection in order to transmit that to a first analog braking order from which the first driver module drives the power module to produce a degraded power supply current for the actuator.

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: The invention provides a method of electrically powering an electromechanical braking actuator (1) fitted to an aircraft wheel brake, in which the power supply current (I) delivered to the electromechanical braking actuator is saturated to a saturation value (Isat) in order to limit the current consumed by the electromechanical braking actuator and thereby limit the forces developed by the actuator. The method includes the step of determining the saturation value (Isat) as a function of an internal temperature (T) of the electromechanical braking actuator while it is in operation.

Abstract: Disclosed herein is a transport device comprising a first section of an outer container comprising a shell on the inside having the shape of a spherical cap with an inner diameter and an opening, wherein the opening of the spherical cap faces upwards, and an inner container having an upper section, a lower section and an inner hollow volume defined thereby, wherein at least the lower section has a spherical shape on the outside, the outer diameter of which is smaller than the inner diameter of the spherical cap of the outer container. The inner container is suitable to be arranged in the spherical cap of the outer container in a freely pivotable fashion, and is capable of accommodating a payload.

Abstract: A control method of an electrical braking system for aircraft includes a plurality of electromechanical actuators capable of applying a braking force on friction members. Each electromechanical actuator includes an electric motor equipped with one or more windings. The braking system further includes at least one power module configured to send to each electric motor winding a phase current and at least one control module configured to control, in response to a braking setpoint, the sending by the power module of a setpoint phase current determined depending on the braking force to be applied. The method further includes the variation of the phase current transmitted to each winding of the electric motor so as to cause the phase current to oscillate around the setpoint phase current.

Abstract: An aircraft brake system comprising: a first group of at least one electromechanical actuator, a second group of at least one electromechanical actuator, a first control device with a first software module and a second software module, the second software module being configured to control the first group of at least one actuator at least in the event of a fault of the first software module, a second control device with a third software module and a fourth software module, the fourth software module being configured to control the second group of at least one actuator at least in the event of a fault of the third software module, wherein the first device module and the second control device are dissimilar. The invention also relates to an aircraft equipped with this system.

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: Disclosed herein is a transport device comprising a first section of an outer container comprising a shell on the inside having the shape of a spherical cap with an inner diameter and an opening, wherein the opening of the spherical cap faces upwards, and an inner container having an upper section, a lower section and an inner hollow volume defined thereby, wherein at least the lower section has a spherical shape on the outside, the outer diameter of which is smaller than the inner diameter of the spherical cap of the outer container. The inner container is suitable to be arranged in the spherical cap of the outer container in a freely pivotable fashion, and is capable of accommodating a payload.

Abstract: A control method of an electrical braking system for aircraft includes a plurality of electromechanical actuators capable of applying a braking force on friction members. Each electromechanical actuator includes an electric motor equipped with one or more windings. The braking system further includes at least one power module configured to send to each electric motor winding a phase current and at least one control module configured to control, in response to a braking setpoint, the sending by the power module of a setpoint phase current determined depending on the braking force to be applied. The method further includes the variation of the phase current transmitted to each winding of the electric motor so as to cause the phase current to oscillate around the setpoint phase current.

Abstract: An electrical harness including at least one upstream connector arranged to be electrically connected to a computer, at least one downstream connector arranged to be connected to a complementary connector of an electromechanical actuator, and at least one electric wire electrically connecting the upstream connector and the downstream connector, the electric wire configured such that primary digital control signals produced or transferred by the computer travel over the electric wire via the upstream connector. The electrical harness may also include an electronic unit integrated in the electrical harness, the electronic unit configured to transform the primary digital control signals into analog control signals and to transmit the analog control signals to the electromechanical actuator via the downstream connector.

Abstract: The invention provides a method of electrically powering an electromechanical braking actuator (1) fitted to an aircraft wheel brake, in which the power supply current (I) delivered to the electromechanical braking actuator is saturated to a saturation value (Isat) in order to limit the current consumed by the electromechanical braking actuator and thereby limit the forces developed by the actuator. The method includes the step of determining the saturation value (Isat) as a function of an internal temperature (T) of the electromechanical braking actuator while it is in operation.

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.