| CPC H02K 16/04 (2013.01) [B64D 27/24 (2013.01); H02K 1/182 (2013.01); H02K 1/2793 (2013.01); H02K 7/003 (2013.01); B64U 50/19 (2023.01)] | 19 Claims |

|
1. An aircraft electric motor comprising:
a rotor comprising a plurality of magnet segments arranged on a frame of the rotor, the rotor being an annular structure defining an internal cavity within the plurality of magnet segments;
an output shaft arranged radially inward from the rotor and operably coupled to the rotor, the output shaft defining a motor axis;
a stator comprising at least one winding wrapped about a support structure, the stator arranged within the internal cavity of the rotor; and
a stator support comprising a portion extending radially inward from the support structure and a portion extending parallel with the output shaft, the stator support configured to supply at least a current into the at least one winding, wherein the support structure of the stator is structurally supported on the stator support;
wherein the magnet segments are symmetrically arranged about the stator to balance axial forces applied to the rotor when a current is induced within the at least one winding and maintain a gap between the plurality of magnet segments and the at least one winding,
wherein the at least one winding defines a longitudinal axis that is parallel to the motor axis and a radial axis that is normal to the longitudinal axis and parallel with an axis or line extending radially through the stator support,
wherein the symmetrical arrangement of the magnet segments creates a symmetric magnetic field about the at least one winding, and
the output shaft is supported on the stator support at one or more bearings.
|