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This paper considers existing more electric technologies in commercial aircraft and observes modern reliability data and redundancy techniques to highlight the reasons restricting the application of new components featuring electric drives and electromechanical actuation. Two techniques for maintaining a constant torque when faulted are applied to two very different fault-tolerant drives. Taking into consideration the test results and reliability data, conclusions are drawn as to the suitability of these and other drive configurations with regard to the stringent aerospace reliability and fault tolerance standards.
Bennett et al. (Mon,) studied this question.