Abstract: Aircraft wheel and brake assembly, including: a wheel (20) and a brake (21) comprising at least one friction member (31), an actuator bracket (24), and at least one brake actuator (25) held by the actuator bracket; a first measuring device arranged to measure a rotation speed of the wheel (20); a second measuring device arranged to measure a temperature of the friction member (31); a data concentrator (40) arranged to acquire measurement signals produced by the first measuring device and by the second measuring device, and to process and transmit the measurement signals to the outside, the data concentrator (40) being mounted on the actuator bracket (24).

Abstract: A method of monitoring aircraft tire operating parameters includes pairing of transmission modules with wheel positions of an aircraft to obtain a cartography associating emission modules with wheel positions, storing the obtained cartography, transmitting data including information identifying the emission module, and operating parameter values of tire operating parameters measured by a sensor, checking an existence of an association between the information identifying the emission module and a wheel position on a given aircraft in the cartography to ensure that the information received belongs to the given aircraft, and displaying the operating parameter values and the wheel on which the one operating parameter values have been measured.

Abstract: Aircraft wheel and brake assembly, including: a wheel (20) and a brake (21) comprising at least one friction member (31), an actuator bracket (24), and at least one brake actuator (25) held by the actuator bracket; a first measuring device arranged to measure a rotation speed of the wheel (20); a second measuring device arranged to measure a temperature of the friction member (31); a data concentrator (40) arranged to acquire measurement signals produced by the first measuring device and by the second measuring device, and to process and transmit the measurement signals to the outside, the data concentrator (40) being mounted on the actuator bracket (24).

Abstract: The invention relates to an electromechanical braking method for an aircraft having at least one electromechanical brake 2 fitted to at least one braked wheel 1 of the aircraft, the brake 2 having friction members 3 and a plurality of electromechanical actuators 4, each actuator 4 comprising a pusher 5 suitable for being moved by means of an electric motor 6 to selectively apply a pressing force on the friction members 3. According to the invention, for a given braking operation, a total braking force to be applied against the friction members 3 of the brake is distributed in non-uniform manner amongst the actuators 4 of the brake, such that at least two actuators 4 apply respective different forces.

Abstract: An aircraft landing gear comprising an axle (100), a wheel (102) borne by the axle, a stack of discs (104) arranged to impose a braking torque on the wheel in response to a pressure imposed on the stack of discs, at least one electromechanical actuator (106) extending facing the stack of discs in order in a controlled manner to apply the imposed pressure to the stack of discs, and an actuator bearer (107) designed to bear the electromechanical actuator. The electromechanical actuator is fixed to the actuator bearer while at the same time being demountable. The actuator bearer is incorporated into the axle in such a way that the axle and the actuator bearer form a single component. There also is a method of demounting a stack of discs from such a landing gear.

Abstract: The invention provides a method of unblocking an aircraft wheel brake having at least one electromechanical actuator 5 with at least one electric motor and a pusher 10 movable under drive from the motor facing friction elements 8 of the brake in order to apply a braking force selectively against the friction elements 8, the actuator 5 being provided with a blocking member 12 for blocking the pusher in position, at least after the actuator has been operated to apply a parking brake force. According to the invention, the unblocking method comprises the steps of: connecting an external control unit to the brake, the external control unit being adapted to act at least on the blocking member 12 of the actuator; and using the external control unit to cause the blocking member 12 to unblock the pusher.

Abstract: A method for monitoring at least two aircraft wheel electromechanical braking actuators. For each electromechanical actuator, the method includes first determining a current value representative of the power supply current of the electromechanical actuator and determining a reference current value estimated from the power supply currents of at least one other electromechanical actuator. Then, the representative current value and the reference current value are compared. Any abnormal operation of the electromechanical actuator is detected when the difference between the representative current value and the reference current value is above a predetermined threshold.

Abstract: Aircraft landing gear comprising an axle (100), a wheel (102) borne by the axle, a stack of discs (104) arranged to impose a braking torque on the wheel in response to a pressure imposed on the stack of discs, at least one electromechanical actuator (106) extending facing the stack of discs in order in a controlled manner to apply the imposed pressure to the stack of discs, and an actuator bearer (107) designed to bear the electromechanical actuator, the electromechanical actuator being fixed to the actuator bearer while at the same time being demountable. The actuator bearer is incorporated into the axle in such a way that the axle and the actuator bearer form a single component. Method of demounting a stack of discs from such a landing gear.

Abstract: A method for monitoring a blocking member (12) of an electromechanical actuator (1). The monitoring method comprising the steps of: determining a value representative of a power supply current of a motor (11) during an off-load operating phase of the electromechanical actuator (1); comparing the value representative of the power supply current with a predetermined current threshold defined from nominal off-load operating characteristics of the electromechanical actuator (1); and detecting an accidental locking of the blocking member (12) when the value representative of the power supply current is above or equal to the predetermined current threshold. There also is an electromechanical actuator (1) comprising a blocking member (12) monitored by such a method.

Abstract: A method for monitoring at least two aircraft wheel electromechanical braking actuators. For each electromechanical actuator, the method includes first determining a current value representative of the power supply current of the electromechanical actuator and determining a reference current value estimated from the power supply currents of at least one other electromechanical actuator. Then, the representative current value and the reference current value are compared. Any abnormal operation of the electromechanical actuator is detected when the difference between the representative current value and the reference current value is above a predetermined threshold.

Abstract: A method for monitoring a blocking member (12) of an electromechanical actuator (1). The monitoring method comprising the steps of: determining a value representative of a power supply current of a motor (11) during an off-load operating phase of the electromechanical actuator (1); comparing the value representative of the power supply current with a predetermined current threshold defined from nominal off-load operating characteristics of the electromechanical actuator (1); and detecting an accidental locking of the blocking member (12) when the value representative of the power supply current is above or equal to the predetermined current threshold. There also is an electromechanical actuator (1) comprising a blocking member (12) monitored by such a method.

Abstract: The invention relates to an electromechanical brake, in particular for aircraft, the brake comprising a support carrying at least one electromechanical actuator comprising a pusher that is axially displaceable towards friction elements in order to apply a braking force to the friction elements, selectively, wherein the actuator is mounted on the support via a connection member allowing at least a portion of the actuator carrying the pusher to tilt angularly.

Abstract: The invention relates to an electromechanical braking method for an aircraft having at least one electromechanical brake 2 fitted to at least one braked wheel 1 of the aircraft, the brake 2 having friction members 3 and a plurality of electromechanical actuators 4, each actuator 4 comprising a pusher 5 suitable for being moved by means of an electric motor 6 to selectively apply a pressing force on the friction members 3. According to the invention, for a given braking operation, a total braking force to be applied against the friction members 3 of the brake is distributed in non-uniform manner amongst the actuators 4 of the brake, such that at least two actuators 4 apply respective different forces.

Abstract: The invention provides a method of unblocking an aircraft wheel brake having at least one electromechanical actuator 5 with at least one electric motor and a pusher 10 movable under drive from the motor facing friction elements 8 of the brake in order to apply a braking force selectively against the friction elements 8, the actuator 5 being provided with a blocking member 12 for blocking the pusher in position, at least after the actuator has been operated to apply a parking brake force. According to the invention, the unblocking method comprises the steps of: connecting an external control unit to the brake, the external control unit being adapted to act at least on the blocking member 12 of the actuator; and using the external control unit to cause the blocking member 12 to unblock the pusher.

Abstract: The invention provides airplane landing gear comprising at least one axle for carrying at least one brake-and-wheel assembly comprising a rim mounted to rotate on the axle and a stack of disks and a support carrying modular electromechanical actuators that are individually removable, the landing gear and the brake-and-wheel assembly being organized in such a manner that each actuator is in at least one of the following configurations: an empty space of dimensions sufficient for receiving the actuator extends on a disassembly path directly facing the actuator when it is in an operating position; the actuator is associated with displacement means enabling it to be moved from an operating position to a disassembly position, an empty space of dimensions sufficient to receive the actuator extending along a disassembly path directly facing the actuator when it is in the disassembly position.

Abstract: The invention relates to an electromechanical brake, in particular for aircraft, the brake comprising a support carrying at least one electromechanical actuator comprising a pusher that is axially displaceable towards friction elements in order to apply a braking force to the friction elements, selectively, wherein the actuator is mounted on the support via a connection member allowing at least a portion of the actuator carrying the pusher to tilt angularly.

Abstract: The invention relates to a protection method for protecting from overheating in a vehicle brake system comprising at least one brake provided with at least one electromechanical actuator which comprises a pusher actuated by an electric motor to apply a force selectively onto friction elements of the brake, it being possible for the brake system to operate, at the request of the pilot of the vehicle, either in a controlled mode in which the pusher of the actuator is actuated by the electric motor so as to apply a braking force selectively to the friction elements in response to a braking instruction, or in a parking mode in which the pusher of the actuator is locked in a position in which it exerts a parking force on the friction elements.

Abstract: The invention relates to a method of managing a parking force in a brake system for a vehicle equipped with at least one electric brake having at least one electromechanical actuator which comprises a pusher actuated by an electric motor to apply a force selectively onto friction elements of the brake, the method including the step of causing the pusher to exert a parking force that is initially equal to a nominal parking force on the friction elements so that the parking force is maintained in the absence of drive from the electric motor. According to the invention, the method includes the step of adjusting said parking force at least once.

Abstract: The invention provides airplane landing gear comprising at least one axle for carrying at least one brake-and-wheel assembly comprising a rim mounted to rotate on the axle and a stack of disks and a support carrying modular electromechanical actuators that are individually removable, the landing gear and the brake-and-wheel assembly being organized in such a manner that each actuator is in at least one of the following configurations: an empty space of dimensions sufficient for receiving the actuator extends on a disassembly path directly facing the actuator when it is in an operating position; the actuator is associated with displacement means enabling it to be moved from an operating position to a disassembly position, an empty space of dimensions sufficient to receive the actuator extending along a disassembly path directly facing the actuator when it is in the disassembly position.

Abstract: The invention provides a method of actuating an airplane brake fitted with at least one electromechanical actuator including a pusher that can be displaced in controlled manner in register with a stack of disks to apply a force on the stack of disks in response to a braking reference signal, the method comprising the steps of: when the braking reference signal crosses a contact threshold, controlling the actuator so that the pusher approaches the stack of disks, until the pusher reaches a contact position with the stack of disks; storing said contact position; and then immediately afterwards, controlling the actuator so that the pusher applies a force on the stack of disks in response to the braking reference signal.