Abstract: The invention relates to a method of managing parking braking in a braking system for a vehicle fitted with at least one electric brake including at least one electric actuator having a pusher actuated by an electric motor for selectively applying a force against friction elements of the brake, the method comprising the steps of: establishing a series of direct adjustment tables for parking braking, corresponding to braking situations at different energy levels; when applying parking braking, selecting a direct adjustment table corresponding to a braking situation preceding the application of parking braking; and directly adjusting a parking braking force in application with the selected direct adjustment table.

Abstract: The invention relates to a method of managing parking braking in a braking system for a vehicle fitted with at least one electric brake including at least one electric actuator having a pusher actuated by an electric motor for selectively applying a force against friction elements of the brake, the method comprising the steps of: establishing a series of direct adjustment tables for parking braking, corresponding to braking situations at different energy levels; when applying parking braking, selecting a direct adjustment table corresponding to a braking situation preceding the application of parking braking; and directly adjusting a parking braking force in application with the selected direct adjustment table.

Abstract: An electric brake for an aircraft wheel comprising a support 4 formed by a torsion tube 5 and by an actuator-carrier 6, a stack 7 of disks mounted around the torsion tube 5, electromechanical actuators 8 carried by the actuator-carrier 6, each actuator comprising an electric motor 12 and a pusher 14, the electric motor 12 being adapted to move the pusher 14 facing the stack 7 of disks in order to apply a braking force selectively to the stack 7 of disks; and temperature measurement means for measuring a temperature representative of a temperature that exists in the stack 7 of disks. The temperature measurement means comprises at least one temperature sensor 18 arranged in the pusher 14 of one of the electromechanical actuators 8 so as to be located in the immediate proximity of the stack 7 of disks when the pusher 14 is brought into contact therewith.

Abstract: An asymmetrical electric braking architecture for aircraft, having plural electro-mechanical brake actuators (EBAs) for selectively applying a braking force on friction elements of braked wheels. The architecture comprises (1) a brake control unit (BCU) for acting in normal mode to generate braking setpoint values in response to a braking order, (2) electro-mechanical actuator controllers (EMACs), each including at least one inverter for supplying power to the EBAs in response to the braking setpoint values, (3) at least one emergency brake power and control unit (EBPCU) including at least one inverter for supplying power to some of the EBAs in response to a braking order; and (4) protection means for channeling power supplied by the EMACs or the EBPCU towards the actuators while preventing power from being diverted towards the architecture.

Abstract: A braking system for an aircraft with electric brakes comprising plural electromechanical actuators (2). The system comprises a braking control unit (20) delivering a normal braking setpoint (21) for one or more controllers (10) of the actuators, and selection logic (15) for causing the braking system to operate in a plurality of modes. The system includes: a normal braking mode where the control unit generates a normal braking setpoint (21) for the controller(s); an ultimate braking mode, having priority over the normal braking mode, being responsive to a parking control member, and controlling actuators to respond to the actuation of the parking control member; and a parking braking mode, applied in response to the parking control member and only if the aircraft is stationary, in which the actuators are controlled to apply a force in response to the parking control member being actuated and are then blocked in position.

Abstract: An electric brake for an aircraft wheel comprising a support 4 formed by a torsion tube 5 and by an actuator-carrier 6, a stack 7 of disks mounted around the torsion tube 5, electromechanical actuators 8 carried by the actuator-carrier 6, each actuator comprising an electric motor 12 and a pusher 14, the electric motor 12 being adapted to move the pusher 14 facing the stack 7 of disks in order to apply a braking force selectively to the stack 7 of disks; and temperature measurement means for measuring a temperature representative of a temperature that exists in the stack 7 of disks. The temperature measurement means comprises at least one temperature sensor 18 arranged in the pusher 14 of one of the electromechanical actuators 8 so as to be located in the immediate proximity of the stack 7 of disks when the pusher 14 is brought into contact therewith.

Abstract: The invention relates to a braking system architecture for an aircraft fitted with electromechanical brakes including at least one electromechanical actuator. In accordance with the invention, the architecture comprises at least one proximity unit disposed in the proximity of the brakes at the bottom of the undercarriage and including input/output means for collecting and calibrating at least signals coming from sensors associated with the brakes, and for transmitting the signals as processed in this way to control members for controlling the actuators by means of a communications bus running along the undercarriage, the proximity unit further including control means for controlling the blocking members of the actuators.

Abstract: A braking system for an aircraft with electric brakes comprising plural electromechanical actuators (2). The system comprises a braking control unit (20) delivering a normal braking setpoint (21) for one or more controllers (10) of the actuators, and selection means (15) for causing the braking system to operate in a plurality of modes. The system includes: a normal braking mode where the control unit generates a normal braking setpoint (21) for the controller(s); an ultimate braking mode, having priority over the normal braking mode, being responsive to a parking control member, and controlling actuators to respond to the actuation of the parking control member; and a parking braking mode, applied in response to the parking control member and only if the aircraft is stationary, in which the actuators are controlled to apply a force in response to the parking control member being actuated and are then blocked in position.

Abstract: A wheel brake for an aircraft, the brake comprising a support (2) that receives at least one electromechanical actuator (1) fitted with a pusher (8) facing friction elements (3) and movable under drive from an electric motor (6) to apply a braking force selectively against the friction elements. The actuator is non-reversible such that a reaction force applied on the pusher cannot cause the electric motor to turn, and the actuator is associated with elements (30, 31, 32, 33, 34) for selectively switching off an electric power supply to the electric motor, which elements allow power to be delivered to the actuator in normal circumstances, and switch off the power if (a) the measured speed of rotation (wmes) of the electric motor drops below a first predetermined threshold (S1); and (b) the commanded speed of rotation ( ?) of the electric motor drops below a second predetermined threshold (S2).

Abstract: The invention relates to a method of managing parking braking in a braking system for a vehicle fitted with at least one electric brake including at least one electric actuator having a pusher actuated by an electric motor for selectively applying a force against friction elements of the brake, the method comprising the steps of: establishing a series of direct adjustment tables for parking braking, corresponding to braking situations at different energy levels; when applying parking braking, selecting a direct adjustment table corresponding to a braking situation preceding the application of parking braking; and directly adjusting a parking braking force in application with the selected direct adjustment table.

Abstract: The invention relates to an asymmetrical electric braking architecture for aircraft, comprising a certain number of electro-mechanical brake actuators (EBAs) for selectively applying a braking force on friction elements in order to slow down rotation of braked wheels, said architecture comprising: a brake control unit (BCU) for acting in normal mode to generate braking setpoint values in response to a braking order; electro-mechanical actuator controllers (EMACs), each including at least one inverter for supplying power to the EBAs in response to the braking setpoint values; at least one emergency brake power and control unit (EBPCU) including at least one inverter for supplying power to some of the EBAs in response to a braking order; and protection means for channeling power supplied by the EMACs or the EBPCU towards the actuators while preventing power from being diverted towards the architecture.

Abstract: The invention relates to an aircraft braking circuit having brakes with electromechanical actuators for braking wheels located at the bottom end of at least one undercarriage. In accordance with the invention, a remote unit is located at the bottom of the undercarriage close to the actuators and connected to a certain number of said actuators, the remote unit receiving a power supply via a power supply cable going down along the undercarriage, and having as many controlled switches as connected actuators for selectively powering blocking members fitted to the connected actuators, the switches being controlled independently of one another by software parking orders generated by a control unit and passing via a single communications bus going down along the undercarriage to the remote unit.

Abstract: The invention relates to a braking system architecture for an aircraft fitted with electromechanical brakes including at least one electromechanical actuator. In accordance with the invention, the architecture comprises at least one proximity unit disposed in the proximity of the brakes at the bottom of the undercarriage and including input/output means for collecting and calibrating at least signals coming from sensors associated with the brakes, and for transmitting the signals as processed in this way to control members for controlling the actuators by means of a communications bus running along the undercarriage, the proximity unit further including control means for controlling the blocking members of the actuators.

Abstract: The invention relates to a wheel brake for a vehicle, in particular for an aircraft, the brake comprising a support (2) that receives at least one electromechanical actuator (1) fitted with a pusher (8) facing friction elements (3) and movable under drive from an electric motor (6) to apply a braking force selectively against the friction elements. In accordance with the invention, the actuator is non-reversible such that a reaction force applied on the pusher cannot cause the electric motor to turn, and the actuator is associated with means (30, 31, 32, 33, 34) for selectively switching off an electric power supply to the electric motor, which means allow power to be delivered to the actuator in normal circumstances, and switch off said power if: the measured speed of rotation (?mes) of the electric motor drops below a first predetermined threshold (S1); and the commanded speed of rotation ( ?) of the electric motor drops below a second predetermined threshold (S2).

Abstract: A laminated glazing includes at least one sheet (1) and a second sheet (2) bound to each other by an intercalated adhesive layer (3). The first sheet (1) projects beyond the second sheet (2) to form an exposed edge. The intercalated adhesive layer (3) extends over an exposed portion of the edge of the first sheet (1), and the edge of the intercalated adhesive layer (3) is at least in part covered by an intermediate element (4) suited to bond between the glazing or its constitutive elements (3) and on the body (5) through the intermediary of a cement element. This glazing has use as an automobile windshield with high crash test resistance.