Abstract: An electrically-powered tip-jet engine system for turning an aircraft rotor blade comprises first and second fan assemblies having substantially the same moment of inertia and configured to rotate at the same angular speed, each fan assembly comprising a respective plurality of fan blades and a respective electric motor rotor; and a rigid frame assembly comprising an electric motor stator assembly and configured for mounting to the aircraft rotor blade. The first fan assembly is effective to create thrust in a thrust direction by rotating clockwise with respect to the thrust direction, and the second fan assembly is effective to create thrust in the thrust direction by rotating counter-clockwise with respect to the thrust direction. The rotation in opposing directions of the first and second fan assemblies is effective to eliminate gyroscopic effect on the aircraft rotor blade.