| 摘要 |
<p>An electric aircraft brake control system has a plurality of wheel and brake assemblies, each having a wheel, wheel speed transducer (40b), brake assembly (40) and a brake actuator (40d). Electromechanical control units (96,100,104,108) are uniquely associated with and connected to certain of the wheel and brake assemblies (40-46), and each of the electromechanical control units is provided with an antiskid system as an integral portion thereof. Brake data concentrators are provided for receiving data corresponding to various aircraft operational parameters, including brake pedal position, and provide operational signals to the electromechanical control unit as a function thereof. A controller (80) for emergency and park braking is connected to the electromechanical actuator controllers through one of the brake data concentrators to effect emergency braking action on the brake assemblies, such emergency braking action having incident antiskid control. The system allows for a redundancy in brake control circuitry and operation, which increases the dispatchability of an associated aircraft by ensuring continued effective operation of the aircraft even in view of a failure of one of the redundant circuits or systems. A reduction in weight is also achieved by reducing lengthy cable runs.</p> |
