An electrically actuated braking system 100 for an aircraft, comprising: an electro-mechanical brake actuator (EMAbrake) 151a-d, 152a-d, 153a-d & 154a-d proximate a wheel 161, 162, 163 & 164 of the aircraft, the EMAbrake including a motor; an electro-mechanical actuator controller (EMAC) 141, 142, 143 & 144 including a first motor controller for generating a first drive signal for the EMAbrake, and a second motor controller for generating a second drive signal for the EMAbrake, wherein the first motor controller and the second motor controller are dissimilar so as to provide protection against common mode failure of the first and second motor controllers. The first and second motor controllers may comprise a different hardware selected from a: microprocessor, microcontroller, digital signal processor, application specific integrated circuit, programmable logic device, complex programmable logic device, field programmable gate array and a transistor based discrete electronics switching circuit.
Aircraft electric braking system
2015-06-03
Patent
Electronic Resource
English