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.

An aircraft brake control system for controlling antiskid braking of an aircraft wheel is disclosed including a control assembly having a mode controller which sets the mode of operation of an antiskid brake calculator, configured to set a first mode, when an input of the indication of a brake energy supply configuration indicates a first brake energy supply being used, in which the antiskid brake calculator applies a first restriction level on a rise rate of the antiskid brake command, and a second mode, when the input 305 indicates a second brake energy supply being used, in which the antiskid brake calculator applies a second, lower, restriction level on a rise rate of the antiskid brake command.

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.

There is provided a pivot turn load alleviation (PTLA) brake system for alleviating structural loads on a pivoting main landing gear of an aircraft in a pivot turn maneuver. The PTLA brake system includes a brake control system operatively coupled to at least two main landing gear, each having two or more wheels. The PTLA brake system further includes a PTLA brake inhibit subsystem coupled to the brake control system. The subsystem inhibits braking of one or more of the two or more wheels of the pivoting main landing gear, in the pivot turn maneuver, so that at least one wheel of the two or more wheels is in an unbraked state, and a remaining number of the two or more wheels are in a braked state. The PTLA brake system alleviates structural loads, and reduces wear on the at least one wheel that is in the unbraked state.

An aircraft or other vehicle includes a system and method for selectively allocating which friction brakes of a plurality of friction brakes are utilized in response to a braking demand. Said differently, the present disclosure provides a system and method that includes dynamically switching which friction brakes of a plurality of friction brakes are active (e.g., in use) at a given time in response to a braking demand. This dynamic switching may not only be based on the received braking demand (e.g., from a pilot or auto-braking module), but may also be based on one or more of the following: respective measured brake parameters of the plurality of friction brakes (e.g., temperature, extent-of-wear), aircraft parameters, external parameters, and respective calculated brake conditions.

A brake system for a vehicle is disclosed and includes an energy storage device configured to store and discharge energy, a plurality of wheels, one or more processors operatively coupled to the energy storage device, and a memory coupled to the one or more processors. The memory stores data comprising a database and program code that, when executed by the one or more processors, causes the brake system to determine the brake system is operating in a backup mode of operation. In response to determining the brake system is operating in the backup mode of operation, the brake system calculates a dynamic slip of the plurality of wheels. The brake system is caused to determine a slip error by comparing the dynamic slip with a target slip value of the plurality of wheels. The brake system is also caused to calculate an antiskid command based on the slip error.

An aircraft system for an aircraft having a controller configured to determine, based on a criterion indicative of an aircraft condition or a runway condition, a maximum braking level able to be applied to a brake of the aircraft in an emergency braking mode.

Systems and methods for shutoff valve control are provided. The system may receive a first hardware logic input, a second hardware logic input, and a weight-on-wheels (WOW) status wherein each of the first hardware logic input, the second hardware logic input, and the WOW status report a binary true or a false. The system may open the shutoff valve when each of the first hardware logic input, the second hardware logic input, and the WOW status report true. The system may close the shutoff valve when any of the first hardware logic input, the second hardware logic input, and the WOW status report false.

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.

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.