| 摘要 |
PROBLEM TO BE SOLVED: To provide an electric brake mechanism for an aircraft where a normal line system and an emergency line system are reduced in risks of common mode failures. SOLUTION: The electric brake mechanism includes a brake control unit having several electromechanical brake actuators (EBAs) for generating brake set values in response to a brake command in a normal mode, a plurality of electromechanical actuator controllers (EMACs) fed with AC power, and the electromechanical actuator controllers include at least one inverter for supplying power to the EBA in response to the brake set value, at least one emergency brake power supply and control unit (EBPCU) fed only with DC power, and the emergency brake power supply and control unit include at least one inverter for supplying power to the several EBAs in response to the brake command, and a protecting means for transmitting to the actuator the power supplied by the EMACs or EBPCU while preventing the flow of power in the mechanism. COPYRIGHT: (C)2011,JPO&INPIT
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