Abstract: The invention relates to a system architecture for managing aircraft landing gear and suitable for extending/retracting retractable undercarriages, steering steerable wheels, and braking braked wheels. According to the invention, the architecture comprises a communications network having connected thereto extension/retraction actuators, steering actuators, and braking actuators, together with one or more control units adapted to control all of the actuators connected thereto, the communications network having transmission characteristics that are adapted to enabling the control unit(s) to implement antilock servo-control for controlling the braking actuators.

Abstract: The invention relates to an electrical power distribution architecture specially adapted for actuating in sequence aircraft moving elements such as doors, undercarriages, or high-lift elements, said moving elements being actuated by electromechanical actuators powered in sequence from electrical power delivered by at least one electrical power bus of the aircraft. According to the invention, the architecture comprises at least one power distribution member comprising: calibrator means for calibrating the electrical power coming from the power supply bus of the aircraft; and switch means for selectively directing the calibrated electrical power to one or the other of the electromechanical actuators.

Abstract: The invention relates to a system architecture for managing aircraft landing gear and suitable for extending/retracting retractable undercarriages, steering steerable wheels, and braking braked wheels. According to the invention, the architecture comprises a communications network having connected thereto extension/retraction actuators, steering actuators, and braking actuators, together with one or more control units adapted to control all of the actuators connected thereto, the communications network having transmission characteristics that are adapted to enabling the control unit(s) to implement antilock servo-control for controlling the braking actuators.

Abstract: The invention relates to an architecture for a braking system for an airplane fitted with a plurality of undercarriages each carrying a plurality of wheels, at least some of which are fitted with brakes, the architecture comprising at least two braking computers each having two modules such that in each computer, one of the modules controls a first fraction of the brakes and the other module controls a second fraction of the brakes complementary to the first. According to the invention, the architecture is configured to operate in any one of the following modes of operation: a first normal mode in which both modules of one of the braking computers are active for controlling all of the brakes; a second normal mode in which both modules of the other braking computer are active for controlling all of the brakes; and an alternative mode in which one module of one of the braking computers and one module of the other braking computer are active for controlling all of the brakes.

Abstract: A device for controlling aircraft maneuvering units includes at least one control unit and a central computing unit. The control unit may be actuated by a pilot for issuing maneuvering commands. The central computing unit is capable of establishing control signals for at least one maneuvering unit from the maneuvering commands. Each central computing unit is being provided with its own failure detection system. The device further includes at least one backup electronic module respectively associated with a maneuvering unit and capable of also establishing control signals for this maneuvering unit from maneuvering commands. The electronic module lacks any failure detection system of its own, but it is connected to a central failure detection system.

Abstract: Device for controlling aircraft maneuvering units including:

Abstract: A method is provided for arranging the components and power connection points within an electromechanical braking system architecture in order to better maintain isolation of the power busses, and thereby improve overall integrity of the system, while still meeting system redundancy, performance and safety requirements as in the past. In addition, a method is provided for connecting and efficiently using available power in emergency braking and parking modes.