As switched reluctance machines (SRM) generally offer a simple and robust design, they are very suitable for an aircraft main engine fuel pump drive which needs to be actuated by fault-tolerant drives. In this paper two different fault-tolerant SRM topologies for fuel pump drive in aircraft are analytical compared: Firstly a 6/4-topology with two identical motors on one axis as a dual-redundancy drive system, and secondly a dual-channel 12/8-topology, where one 3-phase-system uses every other stator tooth and the second 3-phase-system that provides redundancies uses the rest of the stator teeth. The first of two schemes is turned out to be the better solution concerning ruggedness, weight, inertia, torque quality and magnetic isolation.
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